boletines turbocommander

ATPINDEX

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FORM BY ANY MEANS, ELECTRONIC, MECHANICAL, PHOTOCOPYING, RECORDING OR OTHERWISE, WITHOUT PRIOR WRITTEN PERMISSION OF THE

PUBLISHER.

b~cL Aircraft Technical Publishers Customer Service

P~i"lOl South Hill Drive 6AM-5PM PST M-F

Brisbane, CA 94005 (800)227-4610

ATP Grid Index to Manufacturer’s Publications:

Twi n Commander A/C

695, 695A, 695B

SERVICE INFORMATION

Issue Type Eye-Readable Code

SERVICE BULLETIN SE

SERVICE LETTER SL

SERVICE INFORMATION SF

SERVICE ALERT SRA

CUSTOM KIT CK

AD’S ADs

End of Index

04/04/2002 Copyright Aircraft Technical Publishers Page 1 of 1

GC 0853 SI)

Aircraft Technical Publishers Customer Service

101 South Hill Drive 6AM-5PM PST M-F

Brisbane, CA 94005 (800)227-4610


Twi n Commander A/C

695, 695A, 695B

SERVICE BULLETIN

1) Applicable AD

2) Part Kit (1)

Issue Number 3) Part Kit (2)

Issue Date Issue Description 4) Compliance Time

171 UNFEATHERING PUMP SUPPLY 1)

04/08/1980 HOSE REPLACEMENT 2) SEE ISSUE

3)

4) SEE ISSUE

172 FUEL VENT SYSTEM INSPECTION 1)

05/19/1980 2)

3)

4)

175 R1 OIL FILTER ADAPTER REPLACEMENT 1)

08/06/1980 AND ENGINE MOUNT RETAINER 2)SEE ISSUE

MODIFICATION 3)

4) SEE ISSUE

176 MAIN CABIN DOOR BAYONET 1) 89-18-08

08/22/1980 RIGGING CHECK 2) SEE ISSUE

3)

4) W/IN 25 HRS

177 MAIN LANDING GEAR STRUT HOOK 1)

09/26/1980 INSTALLATION 2)SEE ISSUE

3)

4)SEE ISSUE

178A R1 AILERON ACCESS DOOR INSPECTION 1)

03/16/1981 AND REPLACEMENT 2)SEE ISSUE

3)

4)SEE ISSUE


GC 0853 SI SE

1) Applicable AD

2) Part Kit (1)



180 INSPECTION OF SIDE WINDOW 1)

01/08/1981 HEATER INSTALLATION 2)SEE ISSUE

3)

4)SEE ISSUE

1818 INSTALLATION OF FAIRLEADS ON 1)

07/15/1981 AFT FUSELAGE FRAMES 2)SEE ISSUE

3)

4) SEE ISSUE

183 EXHAUST PIPE SEAL REPLACEMENT 1)

07/07/1981 2)SEE ISSUE

3)

4)SEE ISSUE

184 MAIN CABIN DOOR FASTENER 1)

06/10/1981 INSPECTION 2)SEE ISSUE

3)

4)SEE ISSUE

185 CABIN CHIMES INSPECTION AND 1)

08/28/1981 MOC I FICATION 2)SEE ISSUE

3)

4) SEE ISSUE

186 TRIM TAB FREE PLAY MEASUREMENT 1)

12/23/1981 2)SEE ISSUE

3)

4)SEE ISSUE

187 ANTENNA INSPECTION AND 1)

02/05/1982 MODIFICATION 2)

3)

4)SEE ISSUE

188 R1 SECURING ENGINE CONTROL CABLES 1)

02/22/1982 2)SEE ISSUE

3)

4)SEE ISSUE


GC 0853 SI SE

1) Applicable AD

2) Part Kit (1)



189 APPLICATION OF ABRASION 1)

03/12/1982 RESISTANT TAPE ON DOWTY-ROTOL 2)SEE ISSUE

PROPELLER 3)

4)SEE ISSUE

190A EXHAUST PIPE INSPECTION AND 1)

09/22/1982 MODIFICATION 2)SEE ISSUE

3)

4)SEE ISSUE

191A R1 NOSE LANDING GEAR CENTERING 1)

12/14/1984 CAM AND/OR CENTERING PIN 2)SEE ISSUE

REPLACEMENT 3)

4)SEE ISSUE

193 PASSENGER OXYGEN DISPENSER 1)


3)

4)SEE ISSUE

194A EXTENDED PROPELLER DEICER 1)

03/23/1983 BOOTS 2) SEE ISSUE

3)

4)SEE ISSUE

1958 RUDDER CONTROL CABLE 1)

08/26/1985 INSPECTION AND/OR REPLACEMENT 2)

3)

4) 25 HRS

196 FUEL LEAK INSPECTION AND WING 1)

06/15/1983 COMPARTMENT SEALING BETWEEN 2)

WING STATION 103.0 AND 113.0 3)

4) SEE ISSUE

197 MODIFICATION OF PITOT TUBE 1)

09/09/1983 ASSEMBLY INSTALLATION 2)

3)

4)SEE ISSUE


GC 0853 SI SE

1) Applicable AD

2) Part Kit (1)



198A R1 ELEVATOR TRIM TAB INSPECTION 1)

06/05/1987 AND MODIFICATION 2) SEE ISSUE

3)

4)SEE ISSUE

200 MODIFICATION OF NOSE GEAR 1)

03/28/1984 STEERING COMMAND POTENTIOMETER 2)SEE ISSUE

INSTALLATION 3)

4) 25 HRS

201 ENGINE ISOLATOR ASSEMBLY 1)84-19-05

05/11/1984 INSPECTION AND/OR REPLACEMENT 2)

3)

4)SEE ISSUE

202 NOSE GEAR STEERING COMMAND 1)

08/15/1984 POTENTIOMETER ALIGNMENT 2)

3)

$)SEE ISSUE

203 INSPECTION AND REPLACEMENT OF 1)

02/08/1985 COLLINS AP-106 AND AP-107 2)SEE ISSUE

AUTOPILOT CAPSTAN ASSEMBLIES 3)

4) SEE ISSUE

204 INSPECTION AND REPLACEMENT OF 1)

02/08/1985 COLLINS APS-65 AUTOPILOT 2) SEE ISSUE

CAPSTAN ASSEMBLIES 3)

4) SEE ISSUE

205 VA PLACARD INSTALLATION 1)

12 /20 /1985 2) 860783 689

3)

4)SEE ISSUE

206 INSPECTION OF EMPENNAGE 1)

08/17/1987 A~TACH AREA AT FUSELAGE 2)

STATION 409.56 3)

4)SEE ISSUE


GC 0853 SI SE

1) Applicable AD

2) Part Kit (1)



207A INSPECTION AND/OR REPLACEMENT 1)

08/16/1988 OF DEVORE TEL-TAIL LOGO/ 2)SEE ISSUE

RECOGNITION LIGHT BULBS 3)

4)SEE ISSUE

209 INSPECTION AND/OR REPLACEMENT 1)

11/15/1990 OF NOSE LANDING GEAR AXLE 2) P/N 9545

3)

4)SEE ISSUE

210 REPLACEMENT OF FLAP MASTER 1)

02/01/1991 PULLEY AND CABLE WITH 2)

INSPECTION OF REMAINING FLAP 3)

SYSTEM 4) MANDATORY

213 WING FATIGUE INSPECTION AND 1)95-12-23

07/29/1994 MODIFICATION 2) SB213-1

3) SB213-2

4) MANDATORY

214 Thorough examination of the 1) 2003-07-03

03/01/2000 pressurized cabin structure 2)

(the cockpit, passenger cabin 3)

and the inboard portion,contd. 4) None Found

214 R1 Wing and fuselage fatigue 1) 2003-07-03

04/19/2000 inspection and modification 2) See Issue

3)

4) None Found

214 R2 Wing and fuselage fatigue 1) 2003- 07-03

05/21/2001 inspection and modification 2)

3)

4)See Issue

216 FUELING PLACARD AND FLIGHT 1)

06/09/1992 MANUAL ADDENDUM 2) SB216-1

3) SB216-2

4)SEE ISSUE


GC 0853 SI SE

1) Applicable AD

2) Part Kit (1)



218 R2 EMPENNAGE-VERTICAL STABILIZER 1)95-13-02

09/23/1994 INSPECTION AND MODIFICATION 2)SEE ISSUE

3)

4) MANDATORY

218 R2 EMPENNAGE-VERTICAL STABILIZER 1) 95-13-02


3)

4) MANDATORY

220 MANDATORY REDUCTION IN SPEED 1) 95-19-18

02/01/1995 DURING TURBULENCE 2)SEE ISSUE

3)

4) MANDATORY

223 R2 WING LEADING EDGE A~TACHMENT 1)98-08-19


3)

4)SEE ISSUE

224 RC REPLACEMENT OF NOSE LANDING 1)98-08-25 R1

07/25/1996 GEAR BOLT 2) ED10055

3)

4) MANDATORY

226 R1 FLAP SYSTEM INSPECTION 1)98-07-17

07/15/1997 2)

3)

4) MANDATORY

227 INSPECTION AND MODIFICTION OF 1)

08/01/1997 LOWER MAIN GEAR SCISSORS 2)

3)

4)SEE ISSUE

228 Nose gear steering pin 1)

01/04/1999 2)See Issue

3)

4) Mandatory


GC 0853 SI SE

1) Applicable AD

2) Part Kit (1)



233 Engine nacelle firewall 1)

10/15/2003 rei nforcement 2) S8233 -1

3)

4) Recommended

235 Upper rudder structural 1)

04/16/2003 inspection 2)

3)

4)See Issue

End of Index


GC 0853 SI SE

i

IjB RoCkwelllntematlansl

Service Bulletin O´•nNJ Av*tlon Divition

5001 North Roc~well Avenue

Bethlny. OLlahoma 74005

SERVICE BULLETIN NO. 171 j8 April 1980

f UNFEATHERING PUMP SUPPLY HOSE REPLACEMENT

MODELS AFFECTED: MODEL 690C, SERIAL NO’S 11600 THRU 11619, 11621 AND MODEL 695, fSERIAL NO’S 95001 AND 95002.

REASON FOR PUBLICATION: POSSIBILITY OF OIL LINE CHECK VALVE BEING FORCED OUT OF

HORIZONTAL POSITION DUE TO HOSE ASSEMBLY BEING TOO SHORT.

POTENTIAL ALSO EXISTS FOR POSSIBLE HOSE ASSEMBLY FAILURE

BY CONTINUED TIGHT HOSE INSTALLATION AND ENGINE MOTION.

i COMPLIANCE: WITHIN NEXT TWENTY-FIVE (25) HOURS TIME ]N SERVICE.

54075

JF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH

I THIS SERVICE BULLETIN, CONTACT YOUR NEAREST ROCKWELL

COMMANDER AUTHORIZED SERVICE FACILITY. ff

A P MECHANIC OR EQUIVALENT.BY WHOM WORK WILL BE ACCOMPLISHED:

APPROVAL: ’FAA WA SW-2 Approved.

ESTIMATED MAN HOURS: TWO (2) HOURS. fPARTS DATA: Parts required to comply with this Service Bulletin may be procured through your nearest

Rockwell Commander Authorized Service Facility at no charge. Reference this Service Bulletin, aircraft

model and factory serial number when ordering Service Bulletin No. 171 kit consisting of the following: fDESCRIPTION fQTY PART NO.

2 ea. S- 0421(308-155 Hose Assy fI lea. Compliance Card

lea. Service Bulletin No. 171 Instructions fSPECIAL TOOLS: NONE.

ACCOMPLISHMENT INSTRUCTIONS:

1. Remove lower left cowl door from left and right engines. ff

Remove and discard elristing hose assembly (P/N 5-0421G08-136) that is routed from check valve to Iunfeathering pump inlet port (see Figure i.).

d 3’ Ensure that the check valve is in a horizontal plane with the engine. If check valve is not in a horizontal fplane with the engine, loosen "B" nut, on steel tube assembly, at lower aft end of oil tank, rotate tube f

f assembly until check valve is in a horizontal plane with the engine and then retighten "B" nut.

1 4. Uiarnll 5-0(21MB-lil Mle .sspmb$ rm otleo* ua~ue aM un~P´•ihtnlq ~ump iolrt pml´• Ensur. L~t

check valve is not in a ’pre-loaded" condition when hose assembly is installed and then secure hose fassembly to engine using eldsting clamps and hardware (see Figure 1.).

WOTIE

Push check valve up as high as clamps will allow it to go and still fmaintain a horizontal plane with the engine. Assure 0.05-inch

f clearance between check valve and/or steel tube and the engine fuel

tube(s). ff Page 1 of 2

f

i////////////////////////I////

SERVICE BULLETIN NO. 171

FWDIB~ hlore. PU"" CHECK VALVE UP AS HIGH

AS CLAMPS WILL ALLOW IT TO

GO AND STILL MAINTAIN A

HORIZONTAL PLANE WITH THE

ENGINE. ASSURE 0.03-INCHCLEARANCE BETWEEN CHECK

VALVE AND/OR STEEL TUBE

AND THE ENGINE FUEL TUBE(S).

~;Jl"lg;s

-BCHECK VALVE

i~ (REF)BT~ L-;.a:

g,i 8a

h;ilr ;i~

EXISTING CLAMPS UNFEATHERING PUMPREMOVE EXISTING HOSE

(REF) ASSY AND INSTALLINLET PORT (REF)

S-0421G08-155 HOSE ASSY

figure I.

5. Select Airstart and operate unfeathering pump and check installation for leaks.

6. Reinstall cowl doors on engines.

7. Fill out and mail Compliance Card. ORIGINALELECTRICAL IX)AD: NO CHANCE. As Received By

ATPWEIGHT AND BALANCE: NO CHANGE.

SPARESAFFECTED: NO.

PUBLICATIONS AFFECTED: The Illustrated Parts Catalog change required by this document will be

incorporated at the next scheduled change/revision.

RECORD COMPLIANCE: Make an appropriate entry In the airplane maintenance records as follows:Service Bulletin No. 171, dated 8 April 1980, entitled "Unfeatherrig Pump Supply Hose Replacement",accomplished (date)

Page %ofa

Service Bulletin Roc:kwell

smt N~h l)rm1l *mu


18 Mag 1880

FUEL VENT SYSTEM INSPECTION

MODELSAFFECTED: MODEL 880C, SERIAL NO’S 11800 THRU 11618, 11821 THRU 11621 AND

lloae AND MODEL 885, SERIAL NO’S 85000 THRU 89004 AND 86008 THRU

85010.

REASON FOR PUBLICATION: TO ENSURE THAT NO BLOCKAGE M1828 IN FUEL VENT BY6TEM WHICH

COULD CAUSE POSSIBLE STRUCTURAL DAMAGE TO WING.

COMPLIANCE: WITHIN TWENTY-FIVE (25) HOURS TIME IN SERVICE

AFTER RECEIPT OF TH18 SERVICE BULLETIN.

*011

FLIGHT INTO KNOWN 1ChNO CONDITIONS I PROHIBITED PRIOR TO

COMPLIANCE WITH THIS 8ERVICE BVLLETIN.

IF ANY PROBLEMS ARE ENCOU~PERED WHILE COMPLYING WFIH

THIS 8ERVICE BULLETIN, CONTACT YOUR NEAREG~ ROCKWELL

COMMANDER AUTHORIZED SERVICE FACILITY.

BY WHOM WORX:WILL BE ACCOMPL1SHED: A P MECHANIC OR EQUIVALENT.

APPROVAL: FAA DOA SW-a Approved.

EmIMATED MAN HOURS:

PARTS DATA: 1 Be. Compliance Card.

8PECIAL TOOLS: NONE.


i. Remove aft secess door, located above fuel vent scoop, from left and right upper ~uing surface to gain

access to fuel vent check valve.

a. Inspect existing Left and right cheek va~ves (P/W PC?50), located on art side of front spar lust inboard

of W. S. 285. 82, for presence of shipping "cap" on end of valve (see Figure I.).

S. U cap is present, remove and discard.

4. Remove the rubber hose that connects the main vent line to the cheek wive (Pj~ PC750) and check inside

of hose and check valve to there is no obstruction. Clean or clear ang obstruction if necessary.

5. Reinatall hose on check valve and main vent line. Tonpe hose clamps 26 to 90 inch-pounds.

8. Inspect vent system plumbing for security of attachment and en~re that no tube assembly or shipping

caps are LnstaYed on any ports.

7. Reinstall access doors on upper alng surface.

8. Fill out and mall Compliance Card.

page 1 of 2

8ERVEB BULLETIN NO. 112

FWDCOUTED a.l.

sa.ll

U12

n)sOCnlCI LI.

VLLVI IREII 191.11

A A i j

Ii.1 i’ i __Z u~unrm*r

’i

i’Sml.soarl.~OTCIPIID

1U1D *eleae NO

VIEW A-A s~ocr*o.rxllrs

IN nOgEIUELVENT

LEFT INSTALLATION SHOWN

RIGHT INSTALLATION OPPOSITE

ripur´• 1.

ELECTRICAL LOAD: NO CHANCE.

WEIOIfI~ AND BALANCE: NO CHANGE.

8PARES AFFECTED: NO.

PUBLICATIONS AFFECTED: NONE.

RECORD COMPLIANCE: Mere an npproprinte entry in drplsne mointennnce secards as Service

DvUetln No. l?a, dated 19 May 1880,entltleb "FueI Vent 8getem Inspectim’j gccompliahed (dpte)

Page a or a

SERVICE PUBLICATIONS Rockwell international

revision notice a~nl ari´•aon oiri´•im

6m( Norh R~c*ail

SERVICE BULLET1N NO. 115

Revision No. i

BAugust 1980

OIL FILTER ADAPTER REPLACEMENT AND ENGINE MOUNT RETAINER MODIFICATION

APPROVAL: FAA DOA SW-2 Approved.

SUPPLY DATA Page 1 of 1

CHANGE: 5-9413-613 DWng to S-9413-519 ~rlng in all appllcatlona

PART n ACCOMPLISHMENT INSTRUCTIONS:

Page 5 of 1

ADD: l?a. Modify exis~ing left inboard and light outboard engine stde mount

brackets by machilung or filing brackets in area shown in Figure 4.

I.Cl~iUTioN 1CAUTION

DO NOT GRIND brackets as permanent damage to the

beat treat may occur.

NOlr

Bracket must be removed to aooompllsh this work.

ADD: Figure 4. as shown below.

a CLAMP PLATE

r

1.40"~1 MOUNT BRACKETo.lz~yo.sa´•´•

(REF)~I RADIUS

i

MAX o0.03"

MATERIAL MAY BE

REMOVED FROM SHADED

AREA TO PROVIDE

CLEARANCE BETWEEN

CLAMP PLATE AND

MOUNT BRACKETVIEW LOOKING FWD

~ieu,s 4.

Page 1 of i

Service BulletinRockwell intemanonal

r~ Nan Roa*all annu

s´•mm*.o*l´•hom´•l~ce

SERVICE BULLETIN No. 115

21 July 1880

OIL FILTER ADAPTER REPLACEMENT AND ENGINE MOVNT RETAINER MODIFICATION

MODELS AFFECTED: MODEL 690C, SERIAL NO’S 11800 THRU 11830 AND MODEL 895,SERIAL NO’S 85000 THRU 85011.

REASON FOR PUBLICATION: TO PREVENT POSSIBLE CONTACT BETWEEN ENGINE OIL FILTER

ADAPTER AND ENGINE SIDE MOUNT WHICH COULD CAUSE LasS OF

OR DAMAGE TO OIL FILTER RESULTING 1N LOSS OF OIL.

COMPLIANCE: PART I IMMEDIATELY UPON RECEIPT OF THIS SERVICE BULLETIN.

*011

IF UPON INSPECTION OF OIL FILTER ADAPTER, BETWEEN

ENGINE SIDE MOUNT AND OIL FILTER ADAPTER IS EVIDENT, COMPLY

WITH PART n of THIS SERVICE BULLETWNhlMEEDAATEL.

PART n AT NEXT IOO-HOUR INSPECTION OR WITHIN NEXT

50´•HOUR8 TIME IN SERVICE, WHICHEVER OCCURS FIRST.

~OTI

IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS

SERVICE BULLETIN, CONTACT YOUR NEAREST ROCKWELL COMMANDER

AUTHORIZED SERVICE FACILITY.

BYWHOMWORK WILL BE ACCOMPLISHED: A P MECHANIC OREPUIVALENT.


ESTIMATED MAN HOURS: PART I and PART n EIGHTEEN (18) HOURS TOTAL.

na´•rr

RoLwell InlernaUona~, General Aviation Division, will allow a credit of 18

hours upon receipt of a properly e~eeutsd Warranty Claim and a CompUaneeCard.

PARTS DATA: Parts required to comply with this Service Bulletin may be procured through your nearest

Rockwell Commander AuLorieed Service Facility for )2,211.81. A hll credit will be issued upon receipt of

old adapter P/N 89411?-2, a properly e.eecuted Warranty Claim and a Compliance Card. Reference this

Serdce Bulletin, aircraft model and factory serla~ number when ordering service Bulletin No. 115 hit con-

slstlng of the following:

QTY PART NO. DESCRIPTION

2 ea. 820090-501 Retainer

2 ea. 3102590-1 Adapter2 ea. 3102616-2 Clamp Plate

2 ea. 885014-1 Swivel

2 ea. 8-9413-115 O-Wng2 ea. 5-9419-251 O-Wng

2 ea. 8-9413-813 O-Rlngi a.. Compliance Card

1 ea. Service Bulletin No´• 1?5 Instructions

Fags 1 of?

SERVICE BUiLETIN NO. 115

c~

INSERT A ´•Iv’ 2"

BLOCK HERE

MOUNT RETAINER i

"iIgEE STEP 11)TW ISOLATOR

ASSY IREF)ISEE STEP B

IREFIISEE STEP II

(SEE STEP 121

MOUNT BRACKET IREF)


RIGHT IN STALLATION TYPICAL

Pigur´• i.

Pageloi?


SPECIAL TOOLS: PROPELLER SLIN(I AND ENO1NE HOISIT

ACCOMPLISHMENT IN8TRUCTION8:

PART I INSPECT OIL FILTERADAPTER

I. Remove upper cowllng from lan and right engines.

2. Inspect oil tilter adapter, located on upper right side of engine, for evidence at possible contaot with

engine side mount. Look Lor scratch mads on adapter and EheoL raised letters on adapter for possible

worn spots.

3. If contact between oil filter adapter and engine side mount is evident, comply with Part 1l of this

Service Bulletin immediately

If no contact is evident between oil filter adapter and engine side mount, comply with Part n of this

Service Bulletin at ned 100-hour inspection or within next ill-hours time in service, whichever occurs

first.

5. Reinstall upper cowllng on engines

a. Fill out and mall Compliance Card specifying that Part I has been accomplished and note the results

of the inspection.

PART n REPLACE OIL FILTER ADAPTER

The following procedures apply to both left and right engines.

I. Remove upper and Lower cowllng from engine.

2. Attach propeller sling to propeller blades and connect sling mi ring to engine hcdst and assure that

engine is Supported by sllllg and hoist.

9. Remove engine torque limiter and torque limiter amMlg to facilitate remova~ of oil filter and oil

biter adapter.

Remove engine plumtdng in area of oil tilter, as necessary, to facilitate removal of oil biter and oil

filter adapter.

Do not damage oil lifer cap, buaN~g, tebon washer and filter Pement

when removing them because they are to be relnstalied on engine

5. Loosen oil tilter cap bushi~ and remove oil tilter cap, bushing and titter element from engine.

B. Remove bolt attaching left and right engine aide mount braoket. to mount isolators (see Figure 1.).

Remove bolt (4 places) attaching engine top mount isolator assembly to top mount (see Figure 1.).

8. Allow the e~ine to move forward and insert a 1-1/2 inch to 2 inch block between e~ine tap mount

and mount retainer. This will teep the engine from moving aft and will allow removal of oil fiber

adapter

Page 3 of if

SIT(VICE LIUiLETIN NO. llJ

’1

a.lo´•´• MIN. n~

CLOSESTPOINT

RUN´•OUT

~00

i~tetR

VIEW IOOKINO *FT A~

LEFT INBD MOUNT OR

RIBHT OUTBO MOUNT

lipur´•

Page 4 oi


TOROUE BOLT (4 PLS)3W TO 980 IN´•LBS

WITH THREADS DRY

TOR(IUE BOLT IJ PLSI350 TO 380 IN-LEE

WITH THREADS DRY\

rOROul eOLT

480 TO 600

roROuE BOLT Il4WTOSWIN´•Lss

P~NDSPIFETYWIRE

TOROUE BOLT400 TO Sm IN´•LB9

~ilur´• 3.

8. Raise hoist to allou. lower portion of engine to move forward lust far enough to aYow for removal of

oil filter adapter.

10. Remove oil filter adapter (P/N 884111-2) from engine.

ffoTg

Adapter is to be returned to Rookwell international for credit (see PARTS DATA).

11. Remove bolt (3 places) attaching left inboard and right outboard engine side mount retainers to

engine mount (see Figure 1.).

12. Remove bolt (4 places) attaching left Lnboard and right outboard mount braLets to engine (999 Figure i.).

13. Remove mount bracltets from engine.

14. Remove and discard elds~ing Left inboard and right outboard engine side mount retainers from engine

(see Figure 1.).

15. Chamfer corner on Left inboard and right outboard engine side mounts as shown in Figure 2.

16. Prime reworkea area on engine side mounts with zinc chromate primer.

i?. Install 620090-501 mount retainer on left in~aard and right outbaard engine side mrunta using eidstllg

hardware. Torque bolts 350 to 390 inch-pounds with threads dry (see Figure 3.).

18. Reinstall e~dsting Left inboard and right outboard aids mount braelets on engine using e~eting hardware.

Tor~ue bolts 400 to 500 inch-pounds and safety wire (see Figure 3.).

page 5oL?

SERVICE BULLETW NO. 115

SBd13´•1160´•RIN(i

R:

S´•8~13´•P1

Ilo?ssol

885074´•1 SWIVEL

TOROUE NUT 14 PLS)50 IN-LBS

~1028162 CLAMP PLATE

FLAT SPOT MUST BE

INSTALLIDDOWN

EXISTIN13 TEFLON

W~SHER IREF)

EXISTIN(IOIL FILTER

ELEMENT (R5FL

55018418 O´•RIN(I

EXISTIN(I CPIP IREF)

BUSIIIN(I (R5FL

Agure 4.

PageBof?

SERMCE BULLETIN NO. 11I

is. Install 5-9413-351 O-ri~, 9103080-1 adapter and 3102818-2 clamp plate on engine uslRB

hardware (see Figure 4.) as follows:

a. Lightly coat 5-9419-251 0´•ri~ with an approved clean engine oil.

b. Install 5-8413-231 Drlng on 3102580-1 adopter.

c. Install 3102588-1 adapter and 3102818-2 clamp plate on e~ne using existing hardware. Rotate

adapter, as necessary, to assure that no interference slats between adapter and engine mount.

Torque nuts to 50 inch-pounds (see Figure 4.).

20. Lower hcdst to allow engine to settle bacL into place and remove bloc~, inserted in step 8., from

engine top mount.

21. ReinstaU, eidsting hardware that attaches engine top mount isolator assembly to engine tap mount.

Torque bolts 350 0 380 inch-pounds with threads dry (see Figure 3.).

22. Reinstall eldsting hardware that attaches left and right el\gine side mount brackets to mount Lsolabrs.

Torque bolt 400 to 500 inch-pounds (see Figure S.).

25. Insta~ 5-8413-115 O-rl~g and 8850’14-1 swivel in cdl Biter adapter (see Figure 4.).

24. Install existing teBon washer, oil tilter element and 5-9413-813 ~ring in oil filter adapter (see

Figure 4.).

25. Install els~lng cap over filter element and secure with edstlng bushing. Tighten bushing hand tight

and safety wire (see Figure 4.).

26. Reinstalltems removed in steps 3. and 4.

2?. Remove sling from propeller.

as. Assure there are no lea~a.

29. Reinstzll upper and Lower eowU~g on engines.

SO. Fill out and mail Compliance Card speeifying that Part II has been accomplished.

ELECTRICAL LOAD: NO CHANGE.

WEIGHT AND BALANCE: NO CHANGE.

BPARES AFFECTED: NO.

PUBLICATIONB AFFECTED: The Airplane Maintenance Manua~ and illustrated Parts Cats~ag changes

required by this document will be incorporated at the next sehsm~lad

change/redden.

RECORD COMPLIANCE: Ma~re an appropriate entry in airplane maintenance records as follows: Serdee

Bulletin No. 1?5, dated 21 July 1BBO, entitled "Oil Filte. Adapter Replacement and Engine Mount Retainer

Modification", Part I accomplished (date) Part IL

Page? of?

SEBVICE NO. 118

2. The recommended procedure for inspeett~ bayonet penetration is as lollou,s:

a. With door open and bzyonets in extended position, apply layout inr to bayonets.

b. Retract bayonets by placing handle in open position.

c. Close door and eqage baganets in retaining blalls Mt, handle in loe*ed position.

d. LLghtly scribe a mar*,ln the layout init only, on inboard surface of bayonet along surface of

door lamb as shosn:

WOR WOR

(REF) JAMs

(REFI

1NBD II in INeo) JO~´•RIREF)

RET~ININ(IBLDCI (RIFI

gRIIY

SCRIBE(REF)

AFT BA’IONETS UPPER BIYONRS

e Measure distance from nose of bayonet to scribe line and record for each blyonet´•

WOA IREFI

INBD

INeD

WOR (REF)

SCRIBE

L~NE

SCRIILLINI

AFI BAIONETS UPPER BAYONETS

Page 2 oI I

SERYICE BULLETIN NO. 110

3. Recheck pnetration of bayonets pr step 2.o. Urru 2.g.

*011

IL minimum penstratlon of bayonet(s) Into fuselage retaining blocl(s)is not obtainable, contact Rockasll InterMtlmPL Customer BsNlce

for further instructions.

4. 11 removed, upholstery on main cabin door.

S. Ineert Maintenance Manual Interim Change Notice In applicable Maintenance Mplual.

B. Fill out and mall Compliance Card.

ELECT~CAL. LOAD: NO CHANGE.

WEIGHT AND BAW\NCE: NO CHANGE.

SPAREB AFFECTED: NO´•

PWL1CCA1ONB AFFECTED: The Airplane Maintenance Manual Interim Change Notice is furnished

with this Service Bulletin.

RECORD COMPLIANCE: Mate an appropriate entry in the airplane maintenance records as follows: Se~oe

Bulletin No. 118, dated 21 August 1980, entitled "Main Cabin Door Bayonet Rlggl~ Cheer", aceompllahat

(date).

Page 4 014

SERVICE BULLETIN NO. 1??

(CFWDMAIN LANDING GEAR

STRUT (REF)

RAMP (REF)

0.125" RADIUS

(MINIMUM)

MAMFER O. 08" X 450

SIDES)

71v I

o.so´•yo.sz~´•


RIGH’I INSTALLATION OPPOSITE

E)CISTING RAMP (REF)

400-1S8-RE3 HOOK

0.032 CORROSION

RESISTANT STEEL

SAFETY U~XE

O.I56"/0. 180" DIA.

HOLE 11IRU RAMP TO MATCH

400-138-RE3 HOOK. INSTALL

LINE UP HOOK MS18582-42 ROLL PIN AND

WITH RAMP SURFACE SAFETY WIRE ROLL PIN TO

HOOK AND RAMP

FILL OAF (0.020" NOMINAL)WITH EC1151 B/A (OR EQUIY.)

STRUCTURAL ADHESIVE

FiQura 1.

Page2o~3

SERVICE BULLETIN NO. 1??

8. Apply EC1151 B/A (or equivalent) strueblral adhesive to UU any gap between hook and ramp (see

Figure i.).

WOll

If adhesive other Dan EC1151 B/A is used, the adhesive should be

suitable for steel to aluminum bonding with minimum shear strengthof 2180 psi.

9. Install 400-139-RE3 hook on existing ramps using MSIBSBI-IP rall pin and safety wire roll pin (see

Figure

11011

Do not disturb loeatton of hook until structural adhesive has cured.

EC1?S1 B/A Cure Temperature Time

150F 24 to 48 Hmre

150"F 1 Hour

Far adhesives other than EC 1751 B/A, follow the manufacblrers

recommended cure times and temperatures.

10. Touchup paint an ramps.

11. Perform an aperahonal cheek of main landing gear system to assure that system is functioning properly.

12. With the landing gear in the retracted position, check for any possible interference with the eldsting330086 yoke or the e~daLLng 330087 link. If there is interference, remove material from yoke or link

or from both to clear hook by 0.03 inch and blend ail cuts with a 0. 50 inch minimum radius. Brush

alodine yoke and/or link after removal of material.

WOll

It is recommended that the roller be removed from the U~r if Lt La

necessary td remove any material for clearanee.

1S. Remove lacks from airplane´•

14. Fill out and mail Compliance Card.



SPARESAFFECTED: NO.

PUBLICATIONS AFFECTED: The Model 69(IC/685 IHustrated Parts Catalog changes required by this

document will be incorporated at the next scheduled revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane mafntenance records as follows: Service

Bulletin No. 177, dated 26 September 1980, enlltled’Uain Landing Osar Strut Book Installation", accomplished(date)

Page3ofa

SERVICE BULLETIN NO. 118A, REVISION NO. 1



O

BACKDRILL OR USE HOLE FINDER TO

DRILL 0.180~’10.184" DIA HOLE IN DOOR

AT EXISTING STRUCTURE HOLE POINTSEXISTIY(12SW06-25 (TYP BOTH DOORSI

AFToovs~EnEXISTING NUTPLATES IREF)

~oureD/( 8 O Ls 18o.oo"l0.a?" GAp ~TYP)

BOTTOM SIDE I ~-Msaes3sz72 SCREW

MS2IDIQL3K i~ :li ITYP 27 PLS)

(NUTPLATE 4 PLSI r0.30" E.D.260006-28 LOWER

MS21D18L3 NUTPLATE IC EOSPACESDOOR

USE EXISTING HOLE IN

RlB ar THIS POSITION

FOR LOCATING NEWMS27038-1´•25

0.180..10.184’. oln

A HOLE PLSI B ITYPIPLS) DOOR

BA

IT M~Y BE NECESSARYTOUSELONOERORSHORTER SCREWS DUE

TOTHICINE6SOFWEIGHTS.

Ic0.38.. 0.25’.MIN.

m0054´•513. -615 WEIGHTS MAY It--- -r +I MIN. ITYPI´•MS27038´•(´•12

no~ll n

BE TRIMMED TO OBTAIN CORRECT-CV- VSCREW ITYP 3 PLSI

BALANCE IDO NOT TRIM BEYONDO.SO"MIN. 2SW94´•528WEIOHT

MINIMUMSSHOWN)260036-1 GANG CHANNEL

Msno38´•l-26sCREW-~ k26W1S-M)1 GANG CHANNEL

ITYP I PLSI

4´•651 OPPOSITE

WEIGH THE WEIGHTS WEIGHTS IAS REODL

WOll 250034-513. -515. ´•527. -635

WEIGHTPRIOR TO INSTALLATION.WEIOHTADOEOSHOULDEounL WEIGHT REMOVED VIEW B_B

VIEW A-A

fiour´• 2.

’GPageaofS

IER~CE BULLETIN NO. 1?BA

*011

WEIGH THE WEIGHTS WHEN THEY ARE

REMOVED. AND RECORD SANE

EXISTING 1636201-272 SCREW (3 PLS)EXISTING

1 EXISTING 260034-517

210034´•518 BALANCE WEIGHTS

260034´•526 OPPOSITE

WEIGHTS

B

260036´•1 GANG8

B CHANNEL

EXISTING

mW1S´•SO1 GnNG4 O 8 O m

CHANNEL EXISTING 260005-23O C C C CG

ACCESS DOOR

C t C C C C t C C C C C C C C C, C\ 26005-24 OPPOSITE

0~

Ccocoooocooopo~

~ourso~ILERON I\SSY IREFI

VIEW LOOKING DOWN


R1G HT INSTALLATION OPPO SITE

~ipur´• i._4

Psge 2 of B

SERVICE BULLETIN NO. 118A



BACKDAILL OR USE HOLE FINDER TO

DRILL DIA HOLE IN DOORAT EXISTING STRUCTURE HOLE POINTSITYP BOTH DOORSI

AFT \I I EXISTING NUTPLATES IREFL

CoursD´•i O 8

o.w´•7o.o3´•´• onP cTvPI

BOTTOM SIDEMS21048L3K

ITYP 17 PLS)

MS21048L31N:TPLI\TE E.O.

EOSPACES 25000525 LOWER

DOOR

-"-__ EXISTING HOLE IN

RIB AT THIS POSITION

FOR LOCATING NEW

ACCESSDOORS

AcC, HOLE !4 PLSI MS27034-1-12 SCREW UPPERB ITYP 3 PLSI DOOR

A B

i?

*01.-j iLI11´•´• I´•Ps´•MIN

250034´•613. ´•5~6 WEIGHTS MAY (t-- i MIN. ITYP)MSZ1034´•1´•1Z

BE TRIMMED TO OBTAIN CORRECTBALANCE IDO NOT TRIM BEYDND

SCREW ITYP 3 PLSL

MINIMUMSSHOWNI 0.60’~MIN,mW34´•528WEIOHT

2500361 GANG CHANNEL

M970JB-1-21SCREWITYs 7

PLSI.~.,...,26WJS´•SD1(I~NO CHANNEL

11011250034613. ´•515. ´•527. -655

WEIGH THE WEIGHTS WEI(IHTS(*S RE(IDL

´•53( OPPOSITE PRIOR TO INSTALLATION

WEIGHT ADDED SHOULD

EOUAL WEIGHT REMOVED VIEW 8~gVIEW A-A

FiOur´•


19. Mark onfive (5) equal spaces between holes and drill four (4) additional holes through both doors.

20. Remove both dmts and dimple holes.

21. Install nualate. PiN MS21049L3 on doubler, PIN 240005´•25 securing with rivets, PIN MS20426AD3.

22 install four (4) nutp)ates. PiN MS21049L3K on inside of lower door securing with rivets, MS2042BAD3.

23. Install upper doors, PIN 250005´•27 -28 using screws, PIN MS24093S272.

NOTE

Prior to installing weights in step 24. place weight on scale.

Add this to weight recorded in step 4. or step 5. Total weight

should equal weight removed and recorded in steps 2. and 3

if not, use any combination alweighta, PIN’s 250034´•513,

515, -527, or 535 to obtain correct weight Weights, PIN

250034-613, or 515 may be trimmed as necessary to obtain the

correct weight, provided they are not trimmed in excess of

minimums illustrated in Figure 2.

24 Install weight, PIN 250034´•529 and gang channel, P/N 250035´•1 in leading edge of upper door and secure with

screws, PIN MS27039-1-1213 placesl.

25. Install lower doors, PIN 250005-29, -30 using screws. P/N MSZ4093S272.

26. Balance aileron in accordance with procedures outlined in Chapter 57 of the Maintenance Manual

NOTE

Any combination of weights, PIN’s 250034-513, -515. -527, or

´•535 may be added in leading edge of upper door to balance

ailemn. If weight, PIN 250034-513 or -515 is too heavy, it

may be trimmed as required to obtain correct balance weight,

provided it is not trimmed in excess of minimums illustrated

in Figure 2.

27. Install aileron on airplane in accordance with procedures outlined in Chapter 27 of the Maintenance Manual

28 Fill out and mail Compliance Card, specifying that Part II of this Service Rulletin has been complied with.

ELECTRICAL LOAD: NO CHANGE

WEIGHT AND BALANCE: NO CHANGE

SPARES AFFECTED: NO

PUBLlCATIONS AFFECTED: The airplane Maintenance Manual and Illustrated Parts Catalog changes required by

this Service Bulletin will be incorporated at the next scheduled revision

RECORD COMPLI~NCE: Make an appropriate entry in airplane maintenance record as follows: Service Bulletin No.

118A, dated 1 February 1981, entitled "Aileron Access Door inspection and Replacement, PART I accomplished

(datel PART I1 accomplished (date)

Page B of 6

SERMCEBULLETLI NO´• 1BO

a~a/g c~ RIGHT INSTALLATION SHOWN

LEFT INSTALLATION OPPOSITE

~i

rLOIELIN(I

II1DEWINDOWOUTLET

HUTER, Y -MERHALWYITCH

CUUIP (WP)

ELECTRIWLWIRINO

d

cuus mpl

BLOWERMbrrR

~lpu,´• i.

PylofS

[IISRVICE BULLETIN NO. 188

UPPER COWLINOSHELL

O EXHAVSTPIPE

EXTENSION ASSY

EXH*USTPIPEASSEMBLY

b

FonwnRDFnlmNo

LOwEn

NOSE RIN(I COWLINO

ASSEMBLY SHELL

EXHP~VSTPIPE

~SSY

ENGINE

EXHAUST

OI~PHRAOM

BOLT

COLLAR

~80WB´•17

ENGINEEXHAUSTSEAL

IYPOHER

NUT

Fags 2 d 6

:o;L!.E:TIN NO. 188

FLANOE ASSY (REFIRESTRAINT ASSY IREF)

B1OBS1´•RE13 SEAL IMODEL BBOC)OR

B1OBBI-RE(IGEI\L (MODEL 8861

EXHAUST PIPE ASSY IREFI

HSZM21M3´•3 RIVET. At REOD. WITH FIL´•PRO

MAXIMUM SPPICIN(I OF RIVETS 06/\ OR E(IUIVALENT COPPER

TO BE APPRDXIMATELY 2~’, BASE LUBE TO FACILITATE

ASSEMBLY OF EXHAUST PIPE

DETP~IL A

no~r

BUCK RIVETS SECURELY

TO FACILITATE ASSEMBLY

OF EXHAUST PIPE ONTO

FLANGE ASSY.

CUT ENDS PIT 460 AND BUTT TOGETHER

INO O~P PERMITTEDIMS20127M3´•3

RIVET IREFI~ I SEAL cREFI

o o

VIEW LOOK1N(i AT 8EAL

INSIDE EXHAUST PIPE AgSY

FlpnZ.

Page 4 of 5

LIERVICE BULLETIN NO. 184

~RUTOB.IIP.CTrD

4

STRAP IREF) INSERT SHIM STOCKHERE TO CHECK rOR

SHEARED FISTENER

WOR FRAME IREFL

olo! I ~EEIECIION IREF)

INSPECT 8111 (BI FASTENERS

*TTACHINO THIS CLIPOUTER SKIN IREFI

Rpun

Page a ola

~IIService Bulletin CulF8tFeamAmerican

CORPOR*TION

ComMndn Dirkion

6WI Norm Ra;LMIII Avenue.Bamanl, OLlahome 73W8

SERVICE BULLETIN NO 186

23 December 1981

TRIM TAB FREE PLAY MEASUREMENT

MODELS AFFECTED: MODEL 685, SERIAL NOS. 12000 THRU 12066, MODEL 690, SERIAL NOS. 11001 THRU11079, MODEL 690A, SERIAL NOS. 11100 THRU 11344, MODEL 690B, SERIAL NOS. 11350 THRU 11566. MODEI.69OC. SERIAL NOS. 11600 THRU 11614, 11676 THRU 11694, 11696, 11698, 11100 AND 11101, MODEL 6951 SERIALNOS. 96000 THRU 95084 AND MODEL 695A, SERIAL NOS. 96001, L~003, 96005 THRU 86007, 96009, 96011 AND96018.

REASON FOR PUBLICATIDN: TO ASSURE THAT NO EXCESSIVE FREE PLAY EXISTS ON AILERON,ELEVATOR AND RUDDER TRIM TABS

COMPLI*NCE: WITHIN NEXT TWENTY-FIVE (26) HOURS TIME IN SERVICE.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE BULLETIN, CONTACTYOUR NEAREST GULFSTREAM COMMANDERAUTHORIZED SERVICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT.

APPROYAL: FAA DOA SW-2 APPROVED.

ESTIMATED LIIN HOURS: THREE (S) HOURS.

PARTS DATA: 1 EA. COMPLIANCE CARD

SPECIAL TOOLS: DIAL INDICATOR WITH A RANDE OF 0-1.00 INCH IN INCREMENTS OF 0.001 INCHRESOLUTION. BRACKET (FABRICATED LOCALLY) TO ATTACH DIAL INDICATOR HOLDER TO CONTROLSURFACES.


NOTE

The procedures for measuring trim tab free play for controlsurfaces (aileron, elevators and rudder) are very similar. The

setup procedure for measuring rudder him tab free play is

slightly different f~om the setup made when measuringsilemn and elevator trim tab fre~ play.

1. Determine free play of the control surface trim tab in accordance with the following procedures:

a. Position control surface in a streamlined position.

b. Rigidly fasten the dial indicator holder to the control surface:n line with trim tab actuator so that dial indicatoris positioned as in Figure 1.

NOTE

Position dial indicator so that plunger tip contacts the trailingedge of the trim tab an olthe actuator rod. Dial indicatormust have a range of 0-1.00 inch, in increments of 0.001 inch.

Page 1al7

8ERVICE BULLETIN NO. iBB

’t

´•t

TRIM T~B FREEPLAY i:I‘i

WORK1HEET:ii

ii’ ii

’1"

i:l i’

i’

i i

i I’i’

I :i’

i:

i:: ii Ii

I i

i i-::::I

::I:::i:

ii _IlilUPLDAD

ji-- i;

10. i i: i -B -1t2 tB itib

oowhlLono i~ssl:i:

I´• i:li

´•i: ´•;i i

´•-i-I-4r t :i

i

i

1::i ´•:::I:

i.. i..... iiii i ´•:I::I:

i;

:1, i´•I

ii:: ii::i

:i :.I, i:i

Flmn.

PPgeSofl

BERVICE BULLETIN NO. 188

ii polrT?

FREE FLAT DEFLECTION

PIILERON DEFLECTION POINT(’POINT 2 OR 0.010 0.011 0.061 INCH.

L. ELEVATOR DEFLECTION I WINT 3 POINT 1 OR O.W8 -0.ON I O.WJ INCH.

*OII:WHEN ONE POINT Is LOCATED BELOW TnE O DEFLECTION LINE

AND THE OTHER POINT IS LOCATED ABOVE IT. ADD THE moNUMERICAL VALUEITO OBTAIN TOTAL DEFLECTION. WHEN

BOTH POINTS ARE EITHER ABOVE DR BELOW THE O DEFLECTION

LINE SUBTRACT THE SMALLER VALVE FROM THE LAR(IER VALUETO OBTAIN TOTAL DEFLECTION.

ppgeloI?

BERYICE BULLETIN NO. 186

PUBUCITION8 AFFECTED: The Airplane Maintenance Manual change required by this document will beincorporated at the next scheduled revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: brviee Bulletin No.186, dated 29 Derember IsB1, entitled "Rim Tab Free Play Meaaurement", accomplished (date)

PPge?ofl


2. Remove baggage compartment liner, as necessary, to expose antenna attaching hardware.

NOTE

The antenna connector and attaching hardware are located

directly above the aileron servo.

3 Inspect fuselage skin, both internally and externally, in area of antenna base for possible cracks.

4 If no eracks are found, assure that antenna attaching hardware is in place and secured (tight) and then proceed to

step 6.

5. If cracks are found in fuselage skin, proceed immediately to step 3. of Part II (CI 119 antenna) or step 3. of Part III

(VF10-1IS antenna).

6. Reinstall baggage eompartment liner.

7. Fill out and mail Compliance Card specifying that part I has been accomplished noting if all antenna attachinghardware was in place and secured (tight).

P*RT II MODIFY CI119 ANTENNA ATTACHMENT.

I. Gain access to antenna connector through baggage compartment door.

2 Remove baggage compartment liner, as neecessary, to facilitate removal and installation of antenna.

3. Disconnect antenna connector from antenna

4. Remove screws attaching antenna to top of airplane and remove antenna. Discard gasket from bottom of antenna if

installed.

5 Remove aileron servo, if necessary, to facilitate installation of antenna doublers. Capstan and Cable rigging are to

be left intact

6 If fuselage skin is creaeked around antenna base and cracks are outside the area to be covered by a 8-inch by 10-inch

doubler as shown in Figure 2., contact GulFstream American Corporation, Commander Division Customer Service

Department, Bethany, Oklahoma 73008 for further instructions.

7 Ifno creeks are found or cracks found are within area to be covered by a B-inch by l0-inch doubler, proceed as follows

(refer to Figure Il:

a. Remove rivets from fuselage skin in area where a Ii-inch by 10-inch doubler is to be installed (refer to Figure2).

b. Fabricate a doubler,ll-inches by l0-inches, from 0.010-inch, 2024-118 clad aluminum sheet.

e. Fabricate an angle, l.50-inches long, from AND10134´•1201, 2024-T3511 aluminum extrusion or from 0.063-inch,2024-T3 clad aluminum sheet.

NOTE

Trim angle on installation as necessary.

d. Fabricate a spacer, 0.75-inch wide by 3.85-inches long, from 0.(183-inch, 2024-’13 clad aluminum sheet.

NOTE

Trim spacer on installation as necessary.

i-

Page 2 of 10

SERYICE BUUETIN WO. Is?

O

O Q

Qoo.~´• DIA´• HOLE

I4PLS)

ACTUAL SIZE USE AS TEMPLATE

FI\BRICe~TE METAL CASKET FROM

O.DM". ZMLTJ CLAD ~LUMINUMSHEET

BEND UP 80"

E BEND~1ACTUAL S12E USE AS TEMPLATE

FABRICATE PICLIP FROM O.OQ1"

mZ4´•TO CLAD ALUMINUM SHEET

Figun 1.(9*´•12 ot II

PaQ.e 4 ot 10


6. If fuselage skin is cracked around antenna base and cracks are outside the area to be covered by a 8.?0-inch by 12.60-

inch doubler as shown in Figure 4., contact Gulfstream American Ca~orstion. Commander Division Customer

Service Department, Bethany. Oklahoma 13008 for further instructions

7 If no cracks are found or cracks found are within area to be covered by a 6.70´•inch by 12.60-inch doubler, proceedas follows (refer to Figure 3):

a. Remove rivets from fuselage skin in area where the 6.70-inch by 12.50-inch doubler is to be installed (refer to

Figure 4).

b. Fabricate a doubler, 6.70-inches by 12.50-inches,.60-inches, from o.0l0´•inch. 2024-’13 clad aluminum sheet.

c Fabricate two (2) clips from 0.063-inch, 2024-T3 clad aluminum sheet.

d. Fabricate a plate from 0.063-inch, 2024´•T3 clad aluminum sheet and install two (2) MS21069L08 nutplates on

fabricated plate.

e Fabricate an angle, 1S-inches long, From 0.063-inch, 2024-’13 clad alurmnum sheet.

8. Dye check cracks to determine ends of cracks and stop drill using a No. 40 drill.

9. Locate and drill parts, fabricated per step 7., on airplane (refer to Figure 4).

NOTE

Dimple holes in doubler that pick up existing holes in fuselageskin and countersink holes in doubler that match new holes

drilled through fuselage akin.

10 Remove fabricated parts from airplane and deburr all holes.

L1. To assure proper grounding of doubler, remove paint from fuselage skin, in area where fabricated doubler is to be

installed, using an appropriate solvent and then apply alodine to this area.

CAUTION

To prevent damage to skin surface, abrasives and scrapers,other than the rotary stainless steel brush, should not be used

to remove paint.

12. Locate, drill and install MS21469LOB nutplate (2 places) on fabricated angle (refer to Figure 4).

13. Install all fabricated parts on airplane (refer to Figure 4).

NOTE

All rivets used are MS2042BAD4 rivets unless otherwise

noted. NAS1309B or NAS1139B blind rivets may be

substituted For MS20426AD4 rivets. Length of rivets to be

determined on installation.

14. Reinstall existing antenna using existing hardware (refer to Figure 4).

15. Fillet seel around the antenna, doubler and antenna mounting screws as outlined in Chapter 20 of the AirplaneMaintenance Manual.

16 Prime doubler with zinc chromate primer and paint as necessary.

17. Reconnect antenna connector to antenna.

18. Reinstall any equipment that has been removed for this modification.

19 Reinstall baggage compartment liner.

:s 20 Fill out and mail compliance Card specifying that Part III has been aceomplished noting if any crack, were found

and the extent of cracks

Page 7 of 10

SERVICE BUlLETIN NO. 181


NOCHUIDB

SPARES AFFECTED: NO.

PUIUCATIONS AFFECTED: NONE.

RECORD CO~PLIANCE: Make an appmpriate entry in airplane maintenance records as follows: Service Bulletin No.

187, dated 6 February 1982, entitled "Antenna Inspection and ModiBeation", Part I accomplished (date)Part II accomplished (date) :Part In accomplished (date)

Page 10 of 10

BWVICE BULLETIN WO. 188

YOll

THOROUBHLY CLEAN TnREADS ON CABLE ASSEMBLIES

IIITH METHYL ETHYLKEYTONE IMEKI PRIOR TO APPLYING

LOCTITE 280 ON TnREADS

SAFETY IYIRE JAM NUT TO ROD END OR LOOSEN JAM NUT. APPLY LOCTITE 281 TO THREADSAND RETOROUE NUT TO

SMPINCHPOUND6.

O LOOSEN JAM NUT. APPLY LOCTITE 220TO THREAOS AND RETOROUE NUT TO 2040 INCHWUNDS.

O LOOSEN 8ECOND~RY JAM NUT. APPLY LOCTITE 220 TO THREADSAND RETOROUE NUT m 210220 INCHOOUNDg

*011

DO NOT LOOSEN PRIMARY JPIM NUT.

LOOSEN JAM NUT. APPLY LOCTITE 290TO THREADS AND RETOROUE NUT TO 12(6 INCRWUNDG.

´•O LOOSEN JAM NUT. APPLY LOCTITE 280 TO THREADLIAND RETOROUE NUT TO W07111 INCHQOUNDS.

´•O LOOSEN JAM NUT, APPLY LOCTITE 220 TO THREADS AND RETOROUE NUT rO aos~ Irrcn~ou*wr.

LOOSEN JAM NVT. APPLY LOCTITE 190 TO TnREADS AND RETOROUE NUT TO 210280 INCHPOUNaR

cnvrlore

EMERGENCY CONTROL~8E SURE EMERGENCY CONTROL CABLE IS

BPROPERLY RIOOED PER MAINTENANCE MANUAL

AFTER APPLYING LOCTITE TO CABLER

OIL COOLER DOOR

CABLE AgSY (REFI

CONDITION CONTROL

CABLE ASSY IREFI

rowERCONTROL ii ICABLE ASSY (REF)

I

t~12PLS1

EMERGENCY FUEL

LEFT INSTALLATION SHOWN SHUTOFFMNTROL

CABLE IREF)

~unl´•~´•r´•

ppge 2 or a

SERVICE BULLETW NO. 188

4TY PART NO. DESCRIPTION

13 it. 8661 Tape1 ea. Compliance Card

1 ea. Service Bulletin No. 189 Instructions

SPECULIOOLS: HARD RUBBER ROLLER AND HEAT DUN WITH loO’F TO 160’F CAPABILITY.

ICCOMPLISHMENT INSTRUCTIONS:

NOTE

The air temperature and surface of propeller blades must be

above 60’F during installation ofabrasion resistant tepe.

1. To prepare propeller blades for installation of abrasion resistant tape PIN 8661, proceed as follows (refer to Figure

NOTE

Area to be cleaned is the leading edge of propeller blades and

an area, minimum of i-inches, an each side ofleading edge.

a. Remove existing sealer at end of propeller de-ieer boot and clean surface using Methyl Ethyl Ketone (MEK).

b. Remove paint from propeller blade in area where tape is to be applied.

c. Smooth out rough areas using "fins’~ emery cloth.

d Weahpro.sll.rbllde~wiB hn Nlte~ Donotuss POI~BFPI I(iBp

e. Drythe surfacewith alintfreeeloth.

f Clean area using a 50150 ratio of Isopropyl alcohol to water solution and wipe surface using a lint Eres cloth

CAUTION

To avoid sconng damage to blade surface, the tape must not

be cut or trimmed on the blade.

2. Apply 8561 tape to propeller blades using a hard rubber roller. Apply tape starting at de-icer boot edge and work

outboard. Speciai care should be taken so as not to touch adhesive side of tape during installation.

3. Inspect tape to insure no lifting edges, air bubbles, wrinkles or overlaps are present. If unsatisfactory, remove and

install a new length of tape

i. After tape has been rolled smooth, use heat gun to apply heat to tape such that surface temperature of tape is raised

to at least 100’F (but not over 160%). Maintain this temperature while accomplishing step 5.

CAUTION

Do not allow heat to remain in any position so long that

discoloration or deformation of tape occurs.

5 Reroll tapeduringapplication of heat.

6. When tape has cooled down, reseal end of propeller de-icer boot using sealant compound per MIL-S-7502, MIL-S-8802

or an equivalent.

7. Repaint black side of propeller blades using Sherwin Williams F-63B-12 carbide black texised polane along with

Sherwin Williams Y66V29 polane catalyst (two part mixture) or equivalents. (Available from Local propeller jrepair agencies or Dowty-Rotoll. Do not paint over the abrasion resistant tape.

Page aof(


BUTT TAPE AGAINST DE-ICER

BOOT I\ND SEAL AFTER TAPE

HAS BEEN INSTALLED PROPELLER BLADE ITYs)

DE-ICER ~ROPF; Zg.0..

.I

W NOT PAINT OUT WHITE

APPLY 8581 x TAPE UNE WHEN REPAINTINGSO THAT TAPE EXTENDS PROPELLER BLADES.EOUALLY ON EACH SIDE OFPROPELLER BLADE CENTERLINE.INSTALLATION TO BESMOOTH ANO FREE OF AIRBUBBLES OR WRINILE~.

RUBBER ROLLER IREFL

c

PROPELLER BLADE IREFI

USE HARO ROBBER ROLLER TO APPLY 8581 TAPE

Eisur´• i.

Page S of 4

8ERVICE BULLETIN NO. 180A

EXHAUST IIPE AJ6V (AEFI

AWE SEAL IREF)EXHAUSTIlFE

PSSY rREF)

REMOVE EXHAUSTPIPE

A6SY FROM ENL31NE AT

THIS WINT BY REMOVING

BOLTS.

SILICOFIE SEAL

IREFI

C-:BENYEEN ~POT´•WELD(

a.zs rO O.Sd´•’ i I ITYP 12 PL81

´•INOIWTEI6POT´•WELO~

INDICnrEI) INTERSI*CID RIVETs I

0.25"

WB81BLE TACK

a RIYET LOCATION

MOUNTING BRACKET (AEFI

Fi(un

Psse S ol 5

SERVICE BULLETIN NO. 1slA

no 1 No.lKIT KIT

BTY BTY PART NO DESCRIPTION

1 ea. 1 ea. ED10057´•S01 Centering Pin

1 ea. ED1O1S9 Centering‘Cam1 ea. 1 ea. 5201-31 Nameplate1 ea. 1 ea. Compliance Card

1 ea. 1 ea. Service Bulletin Na. 191A Instructions

SPECIAL TOOLS: TWO (2) HYDRAULIC PRESSURE GAGES WITH 0 TO 1000 PSI CAPABILITIES AND AN

EXTERNAL HYDRAULIC PRESSURE SOURCE CAPABLE OF PRODUCING AN AIRCRAFT

SYSTEM PRESSURE OF 0 TO 1015 PSIG.

ACCOMPUSHMENTINSTRUCTIONS:

NOTE

SERIVCE BULLETIN NO. 191 WAS EFFECTIVE ON

MODEL 690D, SERIAL NOS. 15002, 15003, 15006, 15008,15(109 AND 15012 AND ON MODEL 695A, SERIAL NOS.96001 THRU 86030, 96082, 96034 AND 96035. ONLY

THESE AIRPLANES ARE REPUIRED TO ADJUST

THEIR POWER BRAKE VALVES. IF YOUR AIRPLANE

WAS NOT AFFECTED BY SERVICE BULLETIN NO. lsl

OR COMPLIED WITH SERVICE BULLETIN

NO. 191, DISREGARD STEPS 3 THRU 6 AND ALL OF

STEP 15.

1. Jack airplane as outlined in Chapter 7 of the Airplane Maintenance Manual.

n.

3. Remove upper cowling from left engine.

4. Close fuelihydraulicshutoffvalves

5. Disconnect hydraulic pump lines from firewall and cap off

NOTE

Do not rotate engine with hydraulic pump lines capped off

6. Conned an external hydraulic system pressure source, capable of producing a system pressure of 0 to 1075 psig,to hydraulic system flttings on engine Brewall. Open fuelihydraulic shutoff valves.

7 Place landing gear handle in the up position to bleed hydraulic presaure to zero. Place nose Landing gear at an

approximate 45" aft position. If bleed pressure did not pull gear from over-center, this can be done manually byapplying upward pressure on center ofdrag brace assembly.

8. Remove existing centering cam, centering pin and orifice tube as follows (refer to Figure i):

a Reduce nitrogen pressure to zero by removing cap on the nitrogen and hydraulic fillport valve and

depressing valve core.

b. After pressure has bean removed, remove valve core from nitrogen and hydraulic fillport value.

c. Cover nose wheel and tire assembly ulth a plastic bag to moted them from hydraulic fluid.

d. Remove cotter pin and nut from lower drag brace bolt.

a. Hemove center bolt from scissors.

F Remove snap ring and washer that retain fork and rod assembly in strut body.

Page2olS

4

S~RVICE BULLETIN NO. 181A

EXISTING ED10121

ORIFICE TUBE

(REF)

--1

EXISTING HOLESDRILL 0. 457" DIA. HOLE ALL (REF)

THE WAY THRU ORIFICE TUBE.

CLEAN AND DEBURR HOLE ON

BOTH SIDES OF ORIFICE TUBE.

VIEW A-A

Figure 2.

Page lafS

SERYICE BULLETIN NO. 191A

G.i:

UAIN LANDING GEAR (REF)

INSTALL HYDRAULIC Ij I1


PRESSURE OAOE ON bFl I RIGHT INSTALLATION OPPOSITETHIS TEE F~TINO

LEFT AND RIGHT

MAIN GEAR

Figure 9.

PageGolS

B


POWER BRAKE VALVE(REF)

c

BALL

(REF)

8INSERT FABRICATED~BAR BETWEEN BOTH

POWER BRAKE VALVESAND DEPRESS BRAKE PEDALS

PRESSURE AATUGTINO VALVE LEVER

CHECI(NUT IREF) (REF)

PRESSURE ADJUBTING

SCREW (REF)

VIEW LOOKING INBD

FROM LEFT ACCESS DOOR

Fiyre i.

Page 8 of 9

Service Bulletin CulfstreamAmericanCORPOR*TION

Comm~Nln ~rblon

1001 North R~twall ~usnus.Bsmany, OLI´•h~nu 73WB


29 October 1982

PASSENGER OXYGEN DISPENSER MODIFICATION

MODELS AFFECTED: PART I MODEL 690C, SERIAL NOS. 11719 THRU 11721, 11126 AND 11727

MODEL 690D, SERIAL NOS. 15002, 15003 15004, 15006, 15008, 15009, 15011

AND 16014.

MODEL B9SA, SERIAL NOS. 96001 THRU 96030, 96032 THRU 96035, 96037,

96039, 96040 AND 96042.

PART I1´• MODEL 690C, SERIAL NOS .11119 THRU 11727.

MODEL 690D, SERIAL NOS. 16001 THRU 15014.

MODEL 695A, SERIAL NOS. 96001 THRU 96042.

REASON FOR FUBLICI\TION: TO PREVENT POSSIBLE MALFUNCTION OF OXYGEN MASK DLSPENSING

LIDS.

COMPLIANCE: WITHIN NEXT TWENTY-FIVE (25) HOURS TIME IN SERVICE

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILE

COMPLYING WITH THIS SERVICE BULLETIN,CONTACT YOUR NEAREST GULFSTREAM

COMMANDER AUTHORIZED SERVICENTER.

BY WHOM WORK WILL BE ~CCOMPLISHBD: A B P MECHANIC OR EQUIVALENT.

PIFPROVAL: FAA DOA SW-2 APPROVED.

ESTIMATED MAN HOURS: PART I MODIFY LIDS SEVEN (7) HOURS.

PART II INSTALL PLACARD AND TEST SYSTEM ONE (1) HOUR.

PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE BULLETIN MAY BE PROCURED

THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KIT NO. 1 $17.13

OR KIT NO. 2 52.46. A FULL CREDIT WILL BE ISSUED UPON RECEIPT OF A PROPERLY EXECUTED

WARRANTY CLAIM AND A COMPLIANCE CARD. REFERENCE THIS SERVICE BULLETIN, AIRCRAFT MODEL

AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE BULLETIN NO. 193 KIT CONSISTING OF THE

FOLLOWING:

pnr´• ´•uala I~ ~moa nocio´•.

Kit No. 1 Part I

Kit No. 2 Part II

Kit Kit

No. 1 No. 2

QTY. BTY. PART NO. DESCRIPPION

8 ea. 860183-663 Placard

8 ea. 862061-460 Washer

1 ea. 1 ea. Compliance Card

1 ea. 1 ea. Service Bulletin No. 193 Inatructians

Page 1 of 7

SERVICE BULLETIN NO. 1BU\

VIEW LOOKING AFT

AT F.S. 260.00

B~GOn(lECOMPARTMENT8TRUCTURE IREF)

aNeeoalownsHER 1 8112031-247

MSZIOMN) NUT AN(ILE

12PUI)

ACFT

rnsu~l. Ishat tot zl

Page 4 of 11

SERVICE BULLETIN NO´• 184A

CHUB FACE

1.75" 1~1. -8125)

INNER EDGE OF BOOT

DEICER BOOT

IREF)

PROPELLER BLADE

IREFI

FlgureJ

nEwA´•n

MSS3B7´•I´•STIEDOWNI~RnP

FITTEDBIIWEENOUTER

AND CENTRAL CABLE

M533872´•8 TIEOOWN 8TRAF

BRACKET

MS3387´•2´•8 TIEDOWN STRPIP

FITTED AROUNO WIRE

HARNESS AND INDENTED

AREA OF CONNECTOR BRACKET

A

C aPmo*s~*aEnPwarl*.CONNECTOR INSTALLATION

FiCn O

Page B of 171

SERVICE BULLETIN Na 18SB

nuooEncnsLE RUODER HORN

IREFI IREFI

d.,e\

9CLEVIS IREPI

inlp~s i.

Page a d S


SPECIAL TOOLS: NONE.

*CCOMPUSHMEM INSTRUCTIONS:

i. Gain access to rudder control cables and cable pulleys just forward of fuselage station 409.00 to inspect Fables

for paseible fraymg (refer O Figure 1).

NOTE

On some airplanes, access to pulleys and rudder cables may

be gained through access door installed just sit of fuselagestation 386.82 par Service Latter No. 345. On later model

airplanes, access to pulleys and rudder cables may be

gained thmugh lower fuselage access door att of fuselagestation386.60.

2. Inspect rudder control cables, beginning at Ridder born clsvis and extending for a length of six (6) inches forward

of rudder horn clevis, for possible fraying of cables.

3. VNdder control cables are not frayed, proceed to step

4. If any rudder control cable is frayed, it is accaptable for an slrplane to remain in service with up to Wires (S) wires

broken, provided no two (2) wires are in the same strand ofthethe rudder cable. Airplanes ~u?th this condition must

have thecables rglacsd at the nsxt 100´•hour inspection period.

NOTE:

control cable consists of seven strands and

each strand consists of 19 single wires.

5. Inspect Ridder control cable pulleys and replace ifnacsssary.

B. If any rudder control cable does not meat the requirements stated in step 4., replace cable and check rudder

control rigging as outlined in We applicable Airplana Maintenance Manual.

7. Fill out and mail Compliance Card and note condition of cables on Compliance Card.


WEIGHT ANO 8*L~NCE: NO CHANGE.

SPARES I\FFECTED: NO.

PVBUCATIONS bFFECTEO: The Aicplane Maintenance Manuals atrected by this document will be changed at Be nea

scheduled ranaion.

RECORD COMPLIINCE: Malts an appmpria~e entry in alrplana mountanancs records asfollows: Service Bulletin No.

195B, dated 28 AuSuat 1985, entitled ´•Rudder Control Cable InspeEtian andlor Replseement", aceompiished 9(date)

NOTE

if inspection of Ridder control cables meet the reqlursmentsas noted in step 4.. make an entry in airplane maintenance

records stating that cables are to be replaced at the next

100-hour inspection period.

i page S ol 3


c.o

~o´•rl

APPLY SEALANT TO PITOT TUBE

Agpy PRIOR TO INSTALLING ON

MOUNTING BRACKET.

CNsElaor.nN

IREFI

MOUNTINB BRACKET

e, IREFI

O

SEAL WITH EC1239 "Br’SEALANT OR AN EOUIVALENT

MII;SISOZCSEI\LANTO

plmr TUBE ASW

(REFI

C

Fieurs 2.

Page Soil

SERVICE BULLETIN NO. 19?

ELECTRIC*L



PUBLICATIONS AFFECTED: NONE

RECORD COMPLIANCE: Malts an appropriate entry in airplane maintenance records as follows: Service Bulletin No.

107. dated 9 September 1983, entitled "Modifieation of Pitat Tubs Assembly Installation", accomplished Ldate)

page Boil

II

i Service Bulletin GulfstreamAerospace

~RVICE BULLETIN NO. IssA

Revision No. t

5 June 1981

ELEVATOR TRIM TAB INSPECTION AND MODIFICATION

APPROVIL: ENGINEERING DESIGN ASPECTS ARE FAA APPRO~D.

PPIRTS OITA:

Page 3 of 6

Change quantity of CR3243-C1 blind rivets in Kit No. 2 to 30 ea.

e

Psgelofl

-I

Sewice Bulletin GulfstreamAerospace


(Supersedes Ssrvice Bulletin Na. 198 in its entirety),,,,,,, IELEVATOR TRIM TAB INSPECTION AND MODIFICATION

MODELS AFFECTED: MODELS 500, 500A, 520, 660, 560A, 560E, 680, 680E, 720: 5008, S0OU, 560F, 680F, 680F(P), IB80FL, 680FL(P), 680T, B80V AND BB0W, SERIAL NOS. 1 THRU 1854.

MODEL 6008 SERIAL NOS. 1166 THRU 1876 AND 3050 THRU 3323.

MODEL 681, SERIAL NOS. 6W1 THRU 6072.

MODEL 685, SERIAL NOS. 12000 THRU 12066.

MODELS 690, 690A AND 690B. SERIAL NOS 11001 THRU 11566.

MODEL 690C, SERIAL NOS. 11600 THRU 11132.

MODEL 690D, SERIAL NOS. 15001 THRU 15012, 15014 THRU 15024 AND 15029 THRU

15032


MODEL 695A, SERIAL NOS. 96001 THRU 96055, 96059, 96060, 96083 THRU 96069, 96072.

96015, 96078 AND 96085.

NOTE

SERVICE BULLETIN NO. 198A REPLACES SERVICE

BULLETIN NO. 198 AND IS BEIND ISSUED TO ADD

AIRPLANES WITH SERIAL NOS. 1 THRU 1397. IF PART

II OF SERVICE BULLETIN NO. 198 HAS BEEN

COMPLIED WITH, DISREGARD THIS SERVICE

BULLETIN, IF PART II OF SERVICE BULLETIN NO,

198 HAS NOT BEEN COMPLIED WITH, COMPLIANCEWITH THI~ERVICE BULLETIN IS REQUIRED.

REASON FOR PUBLICATION: POSSIBLE CRACKS IN INTERNAL RIBS.

COMPLIANCE: WITHIN NEXT TWENTY´•FIVE 1251 HOURS TIME IN SERVICE AND EVERY 100 HOURS

THEREA~TER UNTII. BOTH ELEVATOR TRIM TABS HAVE BEEN MODIFIED PER PART II OF

THIS SERVICE BULLETIN

NOTE

LF ANY PROBLEMS ARE ENCOUNTERED WHILE

COMPLYING WITH THIS SERVICE BULLETIN,CONTACT YOUR NEAREST GULFSTREAM


BY WHOM WORK WILL sE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT.

APPROVAL: ENC1INEERING DESIGN ASPECTS ARE FAA APPROVED.

ESTIMATED MAN HOURS: PART I INSPECT FOR CRACKS ONE I1)HOUR

PART II MODIFY TRIM TABS THREE B ONE-HALF 13.6) HOURS EACH TAB

PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE BULLETIN MAY BE PROCURED

THROUGH YOUR NEAREST DULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KIT NO, 1 $0.67

OR KIT NO. 2 518.68. REFERENCE THIS SERVICE BULLETIN, AIRCRAFI~ MODEL AND FACTORY SERIAL

NUMBER WHEN ORDERING SERVICE BULLETIN NO 198A KIT CONSISTING OF THE FOLLOWING: I

a*´• ´•uaM *Imoul nl~

Page 1 of 5


.or.

HOLIP LIRI TO II LOCITTO ON

UPPIA 91(IN O( LL~T IRIM1P1B

IND ON LOWIR IKIH OIRI(IHTTAI~TRB.

0.(0" IIIA. H(I11~lls PLUG IUTTONI1PLOL

1.10"

D o o o s o o~ o o o o.o o o o o o o

d

.I

´•r´•i

n o

A

VIEW LOOKING DOWN CON LEFT ELEVATOR TRIM TAB Inrrl

O

SUPPDRT IIRI\EKITO IRERTO BIINSPECTEO

B B ~ORPOSJIIIEERI\EIIAISYIRE~l

IIONE RI\BIUIO~ RIIIS

OrRIMTaa

1KINIAs~lO

i"iL-

ACTUATORSUs~ORTIA~(I(ET arSY IRsR /I I I ~INsrrcrron

mrFI maerrssnl

Rlewrs

IAIR

VIEW B-B

VIEW A-A

Fieun i.

PageDofSii


KIT No. i PIRT I

KITNO.Z PARTn

Kit Kit

No. I No. 2

9TY BTY PART NOS. DESCRIPTION

4 ea. SS48152 PlugButton2 ea. 410001-RE13 Tee

Ib ea. CR3243-4-1 Blind RivetB ea. MS21011L3 Nutplate

1 ea. 1 ea Compliance Card1 ea. 1 ea. Service Bulletin Na. 198A Instructions

SPECIALTOOLS: BORE SCOPE OR SMALI. DENTAL TYPE INSPECTION MIRROR AND BLIND RIVET GUN.

P.CCOMPLISHMENT INSTRUCTIONS:

1. Drill two (2) O.S(I´•inch diameter holes, one II) on eeeh side of actuator support bracket amembly. in the skin thatis opposite the actuator support bracket assembly (refer to Figure 1).

2. Using a bore scope or dental type inspection mirror, inspect both inboard and outboard sections of ribs in bendradius (refer to View A-A, Figure 1).

3. If no cracks are found, proceed as follows:

a Clean plug buttons and area around edge of holes, drilled in step 1., with alcohol.

b. Apply a thin bead of commercial RTV1OB (elear) or an equivalent sealant to edge of holes and install8348152 plug buttons.

Cc. Clean offexeess RTV and smooth out around edge of plug buttons.

d. Proceed to step 5.

NOTE

Inspection for cracks must be accomplished every l(l0-hourstime in service until Part II of this Service Bulletm hasbeen accomplished

4. If creeks are found in either rib, proceed to Part 11 of this Service Bulletin.

5. Fill out and mail Compliance Card specifying that Part I has been accomplished

PART II MODIFY TRIM TABS

1. Remove existing elevator trim tabs as outlined in the applicable Airplane Maintenance Manual.

2. Remove existing actuator support bracket assembly from trim tab.

CAUTION

When performing the following steps, care should be takenso as not to damage trim tabs.

Page 3 of 5

’i´•


nmlno´•i\lan~nr uunno~rruaronELIYI\TORTRIMTAB IRET) SUPPDRT BRI\CI(ETI\SSI

fRIrI

i Y~ o D

ER11~´•I IO oD

BLINO AIVIT

II PLSI IO --2-r.

THISSKIN

00111341 BLIND RIVITRLL RIVETS I\RIMS2WIOIOJ IPLSI

BXEIPT WHERE BLIND RIYETS 888 USEOC

f C f

IRrn

Ho~EToaarcHi-IXISTINO SUPPOAT

THISSUR~I\CI 01 TEE BAACKITASSYTO 88111 LINE am MS1101113 NUTPLATT

rlnn~ae or ExlsnNo I II L~ C: (In.INTIRSPICI I 0180

Ms2IYIIOnDI ;It,.lo´•´•

naolus

i I I I ’ExISTINO DIBS

mErlrx,snaa HOLI TOTRIMRNO/OR

111101111181 RIVET EHAMIIR EPOIOITsl TO MLIEHI3rLS) III R1OIUS O~ RII1 t

EENTIRLINI

Or RIBS

DO NOT RIMOYE

THIS RIYET

TRIM EXISTING DIBSC

nsslown

EXISTING TAAILINO sOOESTRIPNOTAPPLln\IIETDMODE LS BM)O. BOOP. 885 OA 1811\ ;1 i-i

VIEW C-C LliC;i

rigura

Page 4 of 5

SgKVICE BI~LI.ETIN NO. 198A

Carefully drill out all rivets and remove skin that is located on sanle side as the actuator ruppol´•t bracret

assembly. Skin is to be reinstalied on b’im tab Il´•eLr to Figure 2).

NOTE

If cracks extend beyond material to be removed ~ol´•

instnilntiur, of tee ol´• cracks are Found in other areas of i´•ibs.replace I´•ibs

´•I. Drill out and remove existing nutplates From ribs.

5. Rsmo´•e three (31 forward rivets that attach the two (21 ribs together. Do not i´•emovr Liic aft ,ivet irefrr to view

C-C, Figure 21.

6. Using a ,’outer bit, trim forward end olnanges from ribs. Smooth routed edges of ribs with ~400 gl´•it emery cloth

ireEer to Figure 21.

7. Locate, drill and install 440001-RE13 tee an existing ribs using MS20170AD4 rivets irefel´• to Figure 21.

8. Position existing skin, removed in step 3., on trim tab assembly, align all holes and clamp skin in p’ace.

9 Using existing hole pattern in skin, drill lour 0.192 1+0.0021 inch diameter holes in 440001-RE13 tee for

attachment of existing actuator support bracket assembly. Care should be Laren to assure that holes in actuator

support bracket assembly match holes in 440001´•RE13 tee (reEer to Figure 2)

10 Remove skin from trim tab

L1. Drill and install MSZlo71L3 nutplates (4 places) on 440001-RE13 tee using MS20426AD3 rivets trefer to Figure2).

i?. ReineUII .rintlna ´•X,n.n trim Ub vine MSZW70*D9 nrofa ~indial CR9213-.-L Llind n~T. Irabr to F~purp 2)

13 Reinstall existing actuator support braeret assembly on trim tab using existing hardware il´•efel´• tu Figure 21.

14 Repaint elevator trim tubs as necessary

L5 Reinstall existing trim tab on elevatoi´• as outlined in the applicable Ail´•plane Maintenance Manual

is Cheer rigging olelevator trim tabs as outlined in the applicable Airplane Maintenance Manual.

17 Fill out and mail Compliance Card specifying that Part II has been accomplished

ELECTRICP~L LOAD: NO CHANGE

WEIGHT AND BALPINCE: NO CHANGE.

SPARES AFFECTED: NO,

PUILICC\TIONS AFFECTED: The Lllustl´•oted Parts Catalog ebangr re~uilpd by this document will be incorpo,arcd at

the next scheduled revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Bulletin No.

198A, dated 3 July 1985, entitled Trim Tub inspection and Modification", Ps,´•t I accomplished d~Part 11 accomplished idatel

Page 5 of5

I

B~Q seaini-llerosg~cle

SERVICE BULLETIN NO, 200

28 March 1984

MODIFICATION OF

NOSE GEAR STEERING COMMAND POTENTIOMETER INSTALLATION

MODELS AFFECTED: MODEL 6900, SERIAL NOS. 11729, 11131 AND 11732.

MODEL 690D, SERIAL NOS. 15021 THRU 15032 AND 15037.

MODEL 695A, SERIAL NOS, 96053 THRU 86061, 96063 THRU 96069, 96072, 96075, 96078,96085 AND 96088.

REASON FOR PUsLICATION: M PREVENT LIMITED RUDDER CONTROL AND FALSE TURN SIGNAL IF THE

NOSE GEAR STEERING COMMAND POTENTIOMETER ROD SHOULD BECOME

JAMMED,


MOTE

LF ANY PROBLEMS ARE ENCOUNTERED WHILE

COMPLYING WITH THIS SERVICE BULLETIN,

C CONT~CT YOUR NEAREGI~ 00LISTRE*M


BY WHOM WORK WILL sE P.CCOMPLISHED: A P MECHANIC OR PBUIVALENT.

APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED

ESTIMATED MAN HOURS: ONE (1) IIOUR.

PARTS DATA: PARTS REBUIIIED TO COMPLY WITH THIS SERVICE BULLETIN MAY BE PROCURED

THROUGH YOUR NEAREST GULPSTREAM COMMANDER AUTIIORTZED SERVICENTER POn 83.68.IIEPEPIBNCF. THIS SERVICE BULI.ETIN, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN

ORDERING SERVICE BULI.ETIN NO, 200 KIT CONSISTING OF THE FOLLOWING:

PliiD IY4~1 ID (n´•n0´• lilhDYI

~TY PART NO. DESCIIIPTION

t ea. 790348-11 Clamp2 ea. ANOGOI)LO Washer

1 ea. Compliance Card

1 ea. Service Builetin Na. 200 InJtruetions

SPECIAL TOOLS: NONE


1. Gain access to nose gear.teering command patontiometcr, located in nose section, through lower forward nose

access door (refer to Figure 1).

2. Apply tape to bath ,´•udder cable and potenliometcr rod, just below and against existing clamp rssembly. Lo .Issul´•e

that cliln,p assembly is rcinstalicd in same position on potentiometer rod and rudder cnble ~rom which it was

removed iro(er to FiEure ii.

9. Remove ciamp assembly attaching hardware and discard existing AN964D10L washers only

Page 1 of 3


I 1LEAVE OPEN

EXISTING IOLT

nND NUT IREFI

POTENTIOMETERSHAFT (REF)

EXISTING

RUDDER CABLEANIB0D10WASHER (REF)

780)48´•11

CLAMP IREFLA

VIEW A-AEXISTINGCLAMPASSY

(REF)

790548´•11 CLAMPEXIGTING

BRACKET ASSY

IREFLAPPLY TAPE TO RUDDER CABLE ANDPOTENTIOMETER ROO PRIOR TO REMOVINGCLAMP assv

EXISTINGRUDDER CABLE

IREF)

EXISTING NOSE GEAR

COMMAND POTENTIOMETERIREFI

VIEW LOOKING FORWARDREMOVE THIS ACCESS

AT R IG HT SIDE DOOR TO GAIN ACCESSTO COMMAND POTENTIONETER

Filun I.

Page 2 oI 3

SEHYICB BULLETIN NO. 200

C R.iyrtsa .rl.sne.lsmr and 790918´•11 ebmi~ on rod ~nd mdd.r.kll. u.ng.*ating

bolts, AN960D10 washers (under nuts) and existing nuts. Assure that bottom of existing clamp assembly and

700348-11 clamp align against tape applied to potentiameter rod and rudder cable per step 2. Torque bolts 20

to 25 inch-pounds and remove tape (refer to Figure 1)

NOTE

Rudder cable is to be muted between 790548-11 clamp and

sn side of existing clamp assembly. Leave hole open in

existing clamp assembly where rudder cable was routed.

6. Functional check nose gear steering system and rudder travel limits.

6. Reinstall lower forward nose access door using existing hardware

Fill out and mail Compliance Card.

ELECTRICI\L LOAD: NO CHANGE.


SPARES PIFFECTED: NO.

PUBLICATIONS PIFFECTED: The Illustrated Parts Catalog change required by this document will be incorporated at

the next scheduled revisian.

RECORD COMPLIANCE: Make an appmpriate entry in airplane maintenance records as follows: Service Bulledn Na.

200, dated 28 March 1984, entitled "Modifieation of Nose Gear Steering Command Potsntiometer Instellation~’,

accomplished (date)

C

page 8 of 3

c Se~ce ~B1Beain GulfstreamAerospace


11May 1984

ENGINE ISOLATOR ASSEMBLY INSPECTION AND/OR REPLACEMENT

YODELS AFFECTED: A. MODELS 690 AND 690A, SERIAL NOS. 11001 THRU 11284 WHICH HAVE HAD

ENGINE ISOLATOR ASSEMBLIES REPLACED AFTER JULY 28, 1975.

B. MODEL 690A, SERIAL NOS. 11285 THRU 11344

MODEL 6B0B, SERIAL NOS. 11350 THRU 11566.


MODEL 690D, SERIAL NOS. 1SO(I1THRU 16033 AND 15037.

MODEL 695, SERIAL NOS, 95000 THRU 96084.

MODEL 696A, SERIAL NOS, 86001 THRU 96061, 96063 THRU 96072, 96075, 96078,98085 AND 96088.

REASON FOR PUBLICATION: SOME BARRY WRIGHT CORP. ENGINE ISOLATOR ASSEMBLIES HAVE A

MANUFACTURING DEFECT WHICH COULD PREVENT PROPER BOLT

PRELOAD AND RESULT IN PREMATURE FATIGUE FRACTURE OF ISOLATOR

ASSEMBLY THRU-BOLT.

COMPLIANCE: PART I INSPECT AND CHECK ENGINE ISOLATOR ASSEMBLIES USING SPECIAL CHECK

TOOL WITHIN NEXT TEN (10) HOURS TIME IN SERVICE.

PARTII- IF INY ISOL^TOR ISSE~WLY THRVBOLT IB PR*CTVR.O. REPLACI ALL

THREE (3) FORWARD ISOLATOR ASSEMBLIES ON THAT ENGINE PRIOR TO

NEXT FLIGHT.

IF ISOLATOR ASSEMBLY ON RIGHT SIDE OF EITHER ENGINE IS FOUND TO RE

DEFECTIVE. REPLACE THAT ISOLATOR ASSEMBLY PRIOR TO NEXT FLIGHT.

IF MORE ~HAN ONE (1) ISOLATOR ASSEMBLY IS FOUND TO BE DEFECTIVE ON

AN ENGINE, REPLACE DEFECTIVE ISOLATOR ASSEMBLIES ON THAT ENGINE

PRIOR TO NEXT FI.IGHT

IF UPPER ISOLATOR ASSEMBLY ONLY OR LEFT ISOLATOR ASSEMBLY ONLY IS

FOUND TO BE DEFECTIVE:

(1) REPLACE ISOLATOR ASSEMBLY PRIOR TO OR AT ENGINE HOT SECTION

[NSPECTION IF AIRPLANE HAS LESS THAN 1850 HOURS TIME IN SERVICE.

(2) REPLACE ISOLATOR ASSEMBLY AT NEXT 100-HOUR INSPECTION IF

ENGINE HOT SECTION INSPECTION HAS ALREADY BEEN ACCOMPLISH OR

AIRPLANE HAS MORE THAN 1860 HOURS TIME IN SERVICE.

NOTE

IF ONLY UPPER OR LEET ISOLATOR ASSEMBLY IS

FOUND TO BE DEFECTIVE, NOTE IN AIRFRAME LOD

BOOK (SPECIFY TIME) WHEN ISOLATOR ASSEMBLY

MUST BE REPLACED AS N(Y~ED PER COMPLIANCE.


C ooMPLYINO ~nTH THIS S&IIYICI BVLLETIN.

CONTACT YOUR NEAREST GULFSTREAM


Page t of 11


s~WHo.WDRKWIILBE*CCOMPL16l(e.; B P MECH*NIC OR EQUIv*LENT i*N *PPROYED CGULFSTREAM AEROSPACE SERVICENTER IS RECOMMENDED).

APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.

ESTIMATED MAN HOURS: PART I INSPECT ISOLATOR ASSEMBLIES ONE (1) HOUR.

PART II REPLACE ISOLATOR ASSEMBLIES TEN (10) HOURS PER ENGINE

PARTS DATA: ENGINE ISOLATOR ASSEMBLIES REQUIRED TO COMPLY WITH PART II OF THIS SERVICE

BULLETIN MAY BE PURCHASED THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED

SERVICENTER USING NORMAL PARTS ORDERING PROCEDURES. A FULL CREDIT, BOR ENGINE ISOLATOR

ASSEMBLIES THAT WIRE FOUND TO BE DEFECTIVE, WILL BE ISSUED UPON RECEIPT OF A PROPERLY

EXECUTED WARRANTY CLAIM, DEFECTIVE ISOLATOR ASSEMBLIES AND A COMPLIANCE CARD.

SPECIAL TOOLS: GULFSTREAM AEROSPACE SERVICENTERS HAVE ENGINE ISOLATOR ASSEMBLY CHECK

TOOL PART NUMBER 9348-1. IT WILL BE NECESSARY TO FABRICATE A SPECIAL TOOL

FOR REMOVAL AND TORQUE OF BOLTS (REFER TO FIGURE 3).


PART I INSPECT ENGINE ISOLATOR ASSEMBLIES.

i. Remove upper and lower cowling shells from left and right engines.

2. Using a flashlight and an inspection mirror, eheek isolator assembly brackets to determine if the isolator

assemblies are manufactured by Barry Wright Corp, or Lord Mfg. Co. Barry brackets are identified with raised

letters and Lord. braeketa are identified by ink stamped letters (reBr to Figure 1).

3. If all engine isolator assemblies are manufactured by Lord Mfg. Ca., preceed to step 11.

4. If all engine isolator assemblies are manufactured by Barry Wright Corp., proceed to step 6.

i. If ~in an.n. ia f~u.d is have irma~F a~ambim in.laiied tbar era not dl ~rom the lams.endm .ilher the BeFEl

or the Lord isolator assembly(s) should be removed and replaced, per Part II of this Service Bulletin, to assure

that all isolator assemblies on that engine are ham the same vendor.

6. Visually check to see if isolator assembly thru-bolt is broken.

Using engine isolator cheek tool PIN 9348-1, inspect upper and both side engine isolator assemblies by checkinghow far the isolator assembly thru-bolt protrudes through the aft end of isolator assembly (refer to Figure 2).

8. If any isolator assembly thru-bolt is found to be broken, cheek all engine mount support structure for damage

and check for possible damage to oil filter housing or engine hard lines, remove and replace as necessary. Fill

out and mail Compliance Card specifying that Part I has been accomplished, whet was found and proceed to Port

II and replace all engine isolator assemblies an that engine.

NOTE

Note on the Compliance Card the location of broken thru-

bolt (ieft or right engine on left side, right side or upper)and specify hours in service on part and airplane if

different.

9. If all engine isolator assemblies are found to be geeeptable, apply a 060-inch mart (dot), using white aorylic

point (or equivillent) on aft end of isolator assemblies near cast.llated nut as shown on Figure 2. Proceed to step11

10. If any engine isolator assembly thru-bolt checks No-Do (eontaets check tool), refer to Part II Compliance, an Page

1, and proceed to Part II as required.

11. Reinstall upper and lower eowling shells on left and right engines.

Page 2 of 11

SERVICE BULLETM ND. 201

ENGINE UPPER MOUNT RACK OF ENGINEIREFI GEAR CASE

IREFIA

IREF, eRncKET

O IREFI

BRACKET

IREF) O

SAFETYWIRE Yo) (oY

A VIEW A-A

UPPER ISOLATOR ASSY

IREF)

ANCHOR IREF)

STRUT ASSYS

IREFI *011

LORD BRACKETS SHOULDsE IDENTIFIED WITH

VENDOR NAME PRINTEDON BRACKETS.

aoE MOUNTS

ITYPL IREFI

LORD SIDE ISOLATOR ASSYS

WVESHOULDERONTHRU´•BOLTS

(REFI

InEFI

O

SIDE 1SOLATORIREFL

WIRE

O

PACK OF ENGINE -appnoxlMnrE

GEARCASE LOCATION

B ’AE" VIEW 8-B

LORD ISOLATOR ASSY IDENIIFICATION

~iours 1. ISh´•´•tl of

Page S of 11

SERVICE BULLETIN NO. aal

UPPER 16OLATOR ASS_Y ,BACK OF EN(IINE

GEAR CASE

IRE FL

(REF)

BRACKET

111661 ~P)V(O/) E~:O)~(OOR

0) yo) \(q

SAFETYWIRE LocnnoN

ENIIINE UPPER MOUNT

IREFI C VIEW C-C

IRE Fl

ASSYS

IREFI

*011

BARRY BRACKETS SHOULDBE IDENTIFIEO WITH VENDOR

NAME IN RAISED LETTERS.

ENOINEgDEBARRY 6161 ISOLATOR ASSYS

MOUNTRAVE FLAT AREA ON BOTH

(REF)61DE8 OF THRU´•BOLT.

BACK OF ENGINE

GEAR CASEIREFI

RETAINER

Illm

s~LTlnrrl

;j BRACKET

IREF)

/,,,,,,,,,IM,,,m LOCATION

SAFETY

SIDE WIRE

A6EY IREFI D ~L´• VIEW D-D

BARRY ISOLATOR ASSY IDENTIFICATION

Plpurs i. (Sh´•´•l 2 ol 2)

Page 4 of 11

SERVICE BULLETIN NO, aol

12. Fill out and mail Compliance Card specifying that Pert I has been accomplished and what type of isolators are

installed on engines (Barry or Lord)

NOTE

Note on Compliance Card if Part II needs to be Compliedvlth.

PART II REPLACE ENGINE ISOLATOR ASSEMBLIECI.

i. To replace side and upper isolator assemblies, proceed as follows (refer to Figure 4).

NOTE

To replace only the upper isolator assembly, proceed to step

a Disconnect batteries.

b Remove upper and lower cowling shell, from engine.

c. Remove propeller spinner dome, drain Lines ham lower cowl support end (manifold gang drain) and Lower

cowlingsupport.

d. Install "A" frame sling an propeller and position lack stand under aft end of engine to support engine

during engine isolator assembly removal.

e Disconnect bleed air line from engine firewail and disconnect electrical cables from starter-generator.

f Disconnect any hose assemblies or tube assemblies that may restrict side or forward movement of engine

of approximately one (1) inch. The following item. may have to be removed to facilitate the approximateone (i) inch movement of engine:

(1, Wing ice light.(2) Starter-generator inlet duct assembly to allow for wrench movement.

(9) Engine case negative line and raw pressure lines and flttings on engine.(4) Px and Py lines on engines with Bendix Fuel Control Units.

(5) P3 line to inlet sensor.

(6) Fuel 8lter lines on engines with Bendia Fuel Control Umta.

g. Remove bolts that attach upper isolator assembly retainer plats;ta upper engine mount and remove bolts

that attach upper isolator assembly to engine gear osse.

h. Remove spindle bolt that attaches side isolator assembly bracket to isolator assembly thru-bolt.

i. Remove screws that attach lett and right beam assembly to nose cowl support ring and engine mount

structure.

j. Remove Lower bolt that attaches aR engine mount to engine.

k. Fabricate a wrench, as required, for removal and installation of bolts that attach isolator assemblybrackets to engine gear case (refer to Figure 3 for a typical tool outline).

i. Cut safety wires and remove bolts that attach side isolator assembly brackets to engine gear case.

m. Remove bolts that attach aide isolator assembly retainer to side engine mounts.

Page 5 of 11

BERYICE BULLETIN NO. aol

ISOLATOR AasvIREFI

MOUNTCHECnTOOL

Q (REFI

APPLY LI(IHT PRESSURE

WITH INDEX FINGER TOWING NUT AS MAINTAIN POSITIVE

NECESSARY TO ROTATEHANDLE WHEN INSERTIN(I

TOOLCONTACTTO

CHECK TOOL THRU *FT ISOLATOR ASSY SURFACE

OPENING IN MOUNT

IF COTTER PIN iS BENT OVER

END OF BOLT. REBEND COTTER

pin OVER SIDE OF BOLT.WITH BOTH LEGS OF CHECK TOOLFIRMLY AGAINST BASE OF ISOLATORCOTTER PINASSY. CHECK TOOL MUST PASS OVEREND OF ISOLATOR ASSY THRU%OLT

WITHOUT TOUCHING. U6E INSPECTIONMIRROR TO VERIFY.IF CHECK TOOL

END OF BOLT.ISOLATOR ASSY

MUST BE REPLACED. PER PART II.

PAINT WHITE DOT IMIN. 0.504THISAREA. IT MUST BE VISIBLEWHEN ISOLATOR 1\SSY iS INSTALLED

IN ENGINE MOUNT.

*011

DO NOT CHECK TOROUE OR

DISTURB NUT ON THRU-BOLT.

Figure 2.

BageBofll


CAUIK)N

When pulling engine forward, assure that engine is

properly supported by propeller sling and jack stand to

prevent any damage to engine or equipment.

n. Pull engine forward, approximately one (1) inch, and push to side to facilitate removal of isolator

assemblies.

o Prior to installing new isolator assembly(s). assure that isolator assembly has a white dot painted on

aft end (refer to Figure 2).

NOte

if white dot is not an isolator assembly, cheek isolator

assembly with 9948-1 check tool to assure that isolator

assembly is acceptable. If acceptable, paint a dot on isolator

assembly, as shown in Figure 2.. using white acrylic paintor equivalent prior to installing on engine.

T;n’;n~"lCI\VTION

When removing and installing an isolator assembly, care

should be taken so 88 not to scratch inside surface of enginemount. Do not use a petroleum base mold release when

inserting isolator assembly in engine mount.

p Remove and replace isolator assemblies, as required, one at a time. Apply mold release (or equivalent)to isolator assembly or inside surface of engine inserting isolator assembly into

engine mount.

1~1cnurlou

When tarqueing bolts that attach isolator assemblybrackets to engine gear case, using fabricated wrench, refer

to Figure 8. for torque value calculations.

q. Reinstall side isolator brackets on engine gear case usmg existing hardware. Torque bolts and safetywire (refer to Wgurea 0 and 4).

r. Reinstall side isolatar assembly retainers on side engine mounts using existing hardware. Torque bolts

as shown in Figure 4.

s Reinstall bolts that attach upper isolator assembly plate to upper engine mount. Torque bolts as shown

in Figure 4.

t. Push engine back into position and install existing hardware that attaches aR eng~ne mount. Finger

tighten bolt only.

u. Install spindle bolt that attaches side isolator braelrets to isolator assembly thru-bolt, align and then

install bolts that attach upper isolator assembly to engine gear osse. Torque bolts and safety wire (refer

to Figures 3 and 4).

NOTE

Torque lower bolt on aft engine mount 160 to 190 inch-

pounds.

v. R8install screws that attach left end right beam assemblies to nose oowl support ring and engine mount

structure

Page 7 of 11


CUT BOX fND WRENCH OFF

I\ND WELD A PIECE OF 0.250"

THICISTEEL PLATE TO0.250" STEEL PLATE WRENCH.

BOXEND

WRENCH

IcO.BZS..

MnKECurOUrro

TOROUE WRENCH DRIVE0.576" ALLEN SOCKET

WRENCH1)011!

IT IS ADVISABLE TO

HEATTREATWRENCHFOR LONG TERM USE

i. INSERT ALLEN WRENCH IN BOLT HEAD.

2. POSITION BOX ENDWRENCH OVER ALLEN WRENCH.

3. INSERTTOROUEWRENCH DRIVE SOCKET INTOCUTOUT

IN BOTTOM OF FABRICPITEDWRENCH.

BOLT

WRENCH

FORMULA FOR FIGURING TOROUE

r-x_ VALUES UEINO EXTENSION ON WRENCH

LwT1~400

GLw

5.01’ T1-450

4 i/ r, ..,,,,,,,,,,,E WRENCH READING

FOR PROPER BOLT TOROUE.

TZ.MAXIMUM TOROUE WRENCH READING

FOR PROPER BOLT TOROUE.

X 3 ANGLE BETWEEN CENTERLINE

OFTOROUEWRENCHANDFABRICATEDWRENCH.

LwIF X.00. THEN 4 Lw tP’.

Lt DISTANCE FROM MIDPOINT OF

TOROUE WRENCH HANDLE IALON(IWRENCH THE WRENCH) TO POINT EVEN WITH

BOLT.

Lw C DISTANCE FROM MIDPOINT OF

HANDLE TO CENTERLINE OFMIDPOINTOF TOR(IUEWRENCHW)CI(ETHANDLE

CENTERLINE OF

TOROUEWRENCH

LwTO OBTAIN MINIMUM ALLOWABLE READING ON TOROUE WRENCH.MULTIPLY 408 IN´•LBS

lwTO OBTAIN MAXIMUM ALLOWABLE READING ON TOROUE WRENCH. MULTIPLY 450 IN´•L88x

ligur´• 3.

Page B of 11


w. Reinstall any hose assemblies tube assemblies or equipment that may have been removed ordisconnected in order to move engine forward.

x. Assure that electrical cable connectors are cleaned and then reconnect electrical cables to stsrter-generator and rec~nnect batteries

Y´• Reinstall lower cawl auppart and drain lines.

rr Remove ding from propeller and removejack stand from aft end of engine,

as. Reinstall spinner dome an propeller using existing hardware and proceed to step 3

2 To replace only the upper isolator assembly. praceed as follows (refer to Figure 4):

a. Remove upper eowling shell from left andlor right engme.

b: Disconnect clamps from upper engine mount strut assemblies Wat support hose assemblies and electricalcables.

c. Mark location of fire deteetars (if installed), located on upper engine mount strut assemblies loosenclamps and lay f,re detectors out arthe way.

d. Remove safety wire and remove bolts that attach upper isolator assembly bracket to engine gear ease

e Remove bolts that attach engine mount strut assemblies to strut anchors (refer to Figure 4).

cnurlow

When removing upper engine mount strut assemblies,assure that rod ends and lamb nuts are not disturbed whichcould affect We adjustment of strut length.

f Remove upper engine mount, isolator assembly and engine mount strut assemblies, as a unit, fromengine.

6´• Remove baits, through plate, that attach upper isolator assembly to upper engine mount and removeisolator assembly. Assure that barrel nuts and looking devices are still in place in engine mount.

b. Prior to installing new upper isolator assembly, assure that isolator assembly has a white dot paintedan aft end (refer to Figure 2).

NOTE

If white dot i, not on isolator assembly, cheek isolatorassembly with 9548-1 oheck tool to assure that isolatorassembly is acceptable. If acceptable, paint a dot an isoiatar

assembly, as shown in Figure 2, using white acrylie paint(or equivalent) prior to installing on engine.

install new isolator assembly in upper engine mount using existing hardware. Align bracket and enginemount as required and Lighten bolts to hold in alignment.

i Reinstall upper engine mount, isolator assembly and engine mount strut assemblies on strut anchorsusing existing hardware.

k. Reinstall bolts that attach upper isolator assembly bracket to engine gear ease. Torque bolts and safetywire (refer to Figures 9 and 4).

i. Attach existing hose assemblies and electrical cables to engine mount strut assemblies using existinghardware and clamps.

Page 9 of 11


UPPERENGINEMOUNT

PLATE

REMOVE THISBOI.T.WASHERAND NUT

TOROUE BOLT310980 IN´•LBS

ROD ANCHORISOLATOR

ASSv I nFT ENGINE MOUNT

iORoUE BOLT I ~6n 1 -C5nl ,TOROUE BOLT

(IOOaOD IN´•LBS 180´•1801N´•LBS

AND SAFEN WIRE

SUPPORT RIN(I

smurnssvsMauNTNOSE

TWO 12) SCREWS

REMOVE TWO 121 SCREW8 IZPLB)

ATTACHING BEAM ASSY

TO NOSE COWL SUPPORT EN(IINE

RING 12 PLSI

BEAM ASSY

SIDE ISOLATOR

TOROUE BOLTi

400´•500 IN´•LB~AND SAFETY WIRE

BRACKET g j V LEFT ENGINE MOUNT

Q

REmlNER

THRU-BOLTTOR(IIIE BOLT

SPINDLE BOLT 3505801N´•L88 no´•rr

TOA(1UE450´•6WIN´•LBS LEFTSHOWNAND ~FETYWIRE RIGHTOPPOSITE

(BARRY)

Pi8ura 4.

Page 10 of 11


m. Reinstall engine fire detectors on engine mount strut assemblies using existing clamps. Assure that

detectors are installed in same place from which they ware removed.

n. Reinstall upper cowling shell on engine and proceed to step 3.

5. Apply a relect tag on all defective isolator assemblies and note isolator assembly hours in service, airplane serial

number, where engine isolator assembly was located on engine, failed gags test or broken thru-bolt. Assure that

Lag is securely attached to isolator assembly. (This is required if credit for parts is to be given).

4. Fill out and mail Compliance Card specifying that Part II has been accomplished and note on Compliance Card

what isolator assemblies were replaced (left or right engine, upper, left or right) and hours in se~ice.

ELECTRICPIL LOAD: NO CHANGE.

WEIGHT AND BALI\NCE: NO CHANGE.

SPARES AFFECTED: ALL ISOLATOR ASSEMBLIES IN SPARES STOCK MUST BE CHECKED AND IDENTIFIED

WITH A O.LO-INCH DOT USING WHITE ACRYLIC PAINT (OR EQUIVALENT) IF

ACCEPTABLE.

PUBLICPIT(ONS AFFECTED: The Airplane Maintenenee Manual change required by this document will be

incorporated at the next scheduled revision.

RECORD COMPLIPINCE: Malts an appropnate entry in ai~hne maintenance records as follows: Service Bulletin Na

201, dated 11 May 1884, entitled "Engine Isolator Assembly inspection andior Replacement’: Pert I accomplished(date) Part II (if required) accomplished (date)

Page 11 of 11

Se~ice GulfstreamAerospace


15 August 1984

NOSE GEAR STEERING COMMAND POTENTIOMETER ALIGNMENT

MODELS AFFECTED: MODEL 600C, SERIAL NOS. 11727 AND 11729 THRU 11732.

MODEL 690D, SERIAL NOS. 15021 THRU 15033 AND 15037

MODEL 6958, SERIAL NOS. 96055 THRU 96072, 96075, 96078, 96086 AND 96088.

NOTE

IT IS RECOMMENDED THAT SERVICE BULLETIN NO.

200 (1F APPLICABLE) BE ACCOMPLISHED IN

CONJUNCTION WITH THIS SERVICE BULLETIN

REASON FOR PUQLICATION: IMPROPER ALIGNMENT CAUSES FAILURE OF POWER STEERING COMMAND

SIGNAL. WITH SYSTEM ON, AND PILOT HAS NO CONTROL OF STEERING.


NOTE

IF *NY PKDRLEMS *KE ENC~UNTERED WXILE

COMPLYING WITH THIS SERVICE BULLETIN

CONTACT YOUR NEAREST GULFSTREAM

COMMANDER AUTHORIZED SPRVICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A 8 P MECHANIC OR EqUIVALENT


ESTIMATED MAN HOURS: TWO (2) HOURS

PARTS DATA: ONE(1) EACH COMPLIANCE CARD.

SPECIALTOOLS: NONE.


i. Gain access to nose gear steering command potentiometer. located in right fuselage nose section, through lower

forward nose access door (refer to Figure 1).

2. Check parallel alignment of rudder cable and nose gear steering command potentiameter as follows:

a Place rudder pedal in full right position.

b Choose a point of reference on either the rudder cable or the nose geal´• steering command potentiomoter

~od and note measurement of distance between rudder cable and potentiometer rod

c. Place rudder pedal in full left position.

d. Measure distance between rudder cable and potentiometer rad st same point of reference that was chosen

in step b A maximum of0.020-inch misalignment is allowed hem full right to full left rudder position.

Page 1 of3


c

P3

REMOVE THIS ACCESS

DOOR TO GAIN ACCESS

TO COMMAND POTENTIOMETER

A --.--i.f

FwopnEssunE

WELL BULKHEADBULKHEAD (REF)

(888)

TO ACHIEVE PARALLEL RE(IUIREMENTS.SHIM AS REO’D BETWEEN BRACKET

ASSv AND POTENTIOMETEH. ATTACH

SH(M TO BRACKET nSSY WITH A

MINIMUM OF ONE (1) No´• 3 FLUSH

snacKETassv ii R’VET. RIVET SHALL NOT INTER-

FERE WITH INSTALLATION DO NOTEXISTING

ATTACH SHlM TO POTENTIOMETER.RUDI)ER CABLE

(REFI

CABLE I\NO ROD RUN PARALLEL TOEXISTING NOSE

PREVENT DAMAGE TO POTENTIOMETERGEARCOMMANDPOTENTIOMETER

//I I1(nEF)RUODERCABLE

(REF) iicEan

COMMAND POTENTIOMETER

C~TO I\CHIEVE P~RI\LLEL ci~inOF BRACKET ASSY WITH CONTROL

CABLE. 8HIM AS AEO´•D nT TOp on

BOTTOM. ATTACH snlM To BRACKET EXISTING

WITH A MINIMUM OF ONE (1) NO. 3 BRACKET ASSY

FLUSH AIYET. RIVET SHALL NOT (nEF)INTERFERE WITH INSTI\LL~TION

VIEW LOOKING FORWARD VIEW LOOKING INBOARD

AT RIGHT SIDE jFigure

PaCe2ofS


e. If rudder cable and potentiometer rod are not parallel or exceed 0.020-ineh dimension noted in step d.

C ’isting brarlrat ~asembly ´•a nrluirrd Iul io Oo(amch) Lo miseiignment rref.r b figure

NOTE

Fabricate shims from 2024T3 or 2024114 aluminum sheet

stock.

f if shimming does not achieve a parallel system within tolerance noted in step d., iemove existing bracket

assembly and replace with new 790348´•3 bracket assembly.

3. Actuate putentiomrter rad (by hand) to assure that movement of the potentiometer rad is a smooth continuous

movement during extension and retraction althe rod. Do not lubricate the potentiometer rod.

4. IEpotendameterpotendameter rod binds or has rough spots through stroke, remove and replace existing potentiometer with new

46991A patentiometer

5 Functional cheek nose gear steering, system as outlined in Chapter 32 of the Airplane Maintenance Manual.

6 Heinstall lower forward nose access door using existing hardware.

Fill out and mail Compliance Card.

ELECTRICAL LOAD: NO CHANDE.

WEIGHT AND BALANCE: NO CHANCE.


CPUBLICATIONS AFFECTED: The Airplane Maintenance Manual change required by this document will be incorporated

at the next scheduled revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Bulletin

No. 202, dated 15 August 1984, entitled "Nose Dear Steering Command Potentiometer Alignment", accomplished

rdate)

C

rage 3 of3

C~IIService Bulletin GulfstreamAerospace


8 February 1985

INSPECTION AND REPLACEMENT OF COLLINS AP-106 AND AP-107AUTOPILOT CAPSTAN ASSEMBLIES

MODELS AFFECTED: A. THE FOLLOWING MODELS WITH FACTORY INSTALI.ED hP-106 AUTOPILOT.

MODEL 690C. SERIAL NOS. 11728 AND 11730 THRU 11732.

MODEI. 690D, SERIAL NOS. 15017. 15019, 15021 THRU 15025, 15027. 15029, 15031.15093 AND 15057

MODEL 695A. SERIAL NOS. 96043, 96045 TRRU 96048, 86050 THRU 96055. 96059,96061, 96064. 96068 AND 96072.

R. THE FOLLOWING MODELS THAT HAVE EITHER REPLACED CAPSTANS,BETWEEN I OCTOBER 1982 AND 8 FEBRUARY 1985, ON THEIR AP-106 OH AP-107AUTOPILOT OR HAVE HAD AN AP-106 OR AP-107 AUTOPILOT INSTALLED.BETWEEN 1 OCTOBER 1982 AND 8 FEBRUARY 1985, BY A SOURCE OTHER THANTHE FACTORY:

MODEL 100, SERIAL NOS. 10001 THRU 10032.MODEI. 690A, SERIAL NOS. 11100 THRU 11344.

MODEL 690C, SERIAL NOS. 11600 TBRU 11721ANI) 11729.

MODEL 690D, SERLAI. NOS 16001 THRU 15016. 15018. 15020, 16088, 15028, 15030AND 15032.

MODEL 695. SERIAL NOS. 95000 THRU 95084.MODEI. 69SA. SERIAL NOS 96001 THHU 96042. 96044, 96049. 96057, 96058, 96060AND 96066.

REASON FOR PUBLICAT1ON: CERTAIN CAPSTAN ASSEMBLIES IN COLLINS AP-106 AND AP-10? AUTOPII.OTINSTALLATIONS ARg SUBJECT TO CORROSION WHICH COULD CAUSE THEFRICTION SI.IP CLUTCH TO SLIP AT A HIGHER THAN NORMAL TORqUE ORELSE NOT SI.IP AT ALL REFER TO COLLINS 334C-9Aill SERVICE BULLETINNO 2 (KF.VISION NO. II AND 3341)´•6( i SERVICE BULLETIN NO. 11(REVISIONNO, ii.

COMPLIANCE: INSPECTION WLTLIIN NEXT TWINTY-FIVF:(211 HOURS 1´•LME IN SERVICEREPLACEMENT REFER TO STEP 5. PAGE 4.

NOTE

IF ANY PROBI.BMS ARE ENCOUNTERED WHILE(:OMPLYING WITII THIS SERVICE BULLETIN.CONTACT YOUR NEAREST DUI.FSTREAMCOMMANDER AUTHORIZED SIRVICENTER.

8Y WHOM WORI( WILL sE *CCOMPLISHED: INSPECT CAPSTAN ASSEMBLIES A L P MECHANIC OREQUIVAI.ENT

REMOVAI. AND REPLACEMENT OF CAPSTAN ASSEMII1.LRSAN AUTHORIZED COLLINS AUTOPILOT INSTALLATION ANL)

j;

RerAms*crr.pru

--*PPROVPIL: ENGINEERING IIESIGN ASPECTS ARE FAA APPROVED.

Page 1 oT4


INIPECTC*PST*N I199EMBLIES-TWO I1)HoUHS

REMOVE ANI) REPLACE CAPSTAN ASSEMBLIES REFER TO PARTS DATA FOR

TIME ESTIMATE.

PARTS DATA: AF.I’LACEMENT CAPSTAN ASSEMBLIES IF REQUIRED, MAY DE OBTAINED ON A NO

CRARGI WARRANTY EXCHANGE BASIS BY CALLING COLLINS ATLANTA FACTORY SERVICE CENTER AT

1401) 996-5406, ~PELEX: 64´•2259 COLLINSRAD ATL TO THE ATTENTION of MR DEE ATWOOD. UPON

COMI1I.ETLON OF THIS SERVICE BULLETIN, THE ORIGINAL UNITS IAFFECTED CAPSTAN ASSEMULIESI

MUSP BE IIE1’IIRN~D (WITHIN TnFE UNITED STATES, SHIP FEDERAL EXPRESS STANDARD AIR COLLECT OR

INTBKNI\’I‘IONI\L1.Y. SHII’ AIll FREIGHT COLLECTI TO COLLINS ATLANTA FACTORY SERVICE CENTER. II

SUSI’ECT UNITS ARE NOT RETURNED WITHIN 15 DAYS 130 DAYS INTERNATIONALLYI OF THE SHIPMENT

OF’rHE WARRANTY EXCHANGE UNITS. THE AIRCRAFT OWNEKIOPERATOR WILL BE BILLED FOR THE

EXCHANGE UNITS THIS OFFER OF NO CHARGE WARRANTY EXCHANGE WILL EXPIRE 1 JULY 1985.

CO1.LINS AVIONICS WILL PROVIDE UP TO TWO (21 HOURS PER UNIT ICAPSTANI FOR REMOVAL AND

REPI.ACEMENT BY AN AUTHORIZED COLLINS DEALERISERVICE AGENCY REFERENCE AIRORAW MODEL

AND FACTORY SERIAL NUMBER WHEN ORDEKIND CAPSTAN ASSEMBLIES. FOLLOWING IS A GULFSTREAM

AEROSPACE CORP. CERTIFICATION APPROVED LISTING, BY MODEL AND SYSTEM POSITION, OF THE

CAPSTAN ASSEMBLY PART NUMBERS:

GUI.FSTREAM AEROSPACE CORP. CAPSaN ASSEMBLY PARTS LISTING

MOL)$I. AII.ERON ELEVATOR RUDDER ELEVATOKTRIM

700 618-5973-002 618-5973´•002 618-5973-003 618-5957-001

6904\ 618´•5973-002 618´•5873´•002 618-5913´•003 618-5957-001

fi(MR 618-59731-002 618-5973-002 618-6913-(103 618-5917-001

69(1(: 6L8-5973-003 6L8-5973´•002 618-5913-003 618´•5957-001

GOOC 618-5Ln3´•0113 618-5973-002 618-6913-003 618-6957-001

B~il (ilS-5975-003 618-5973-002 618-5973-008 618-5957-001

68Bn filX-59?S´•OO3 618-5913-002 618-5978-003 618-5967-001

SPECIAL TOOLS: REFER TO COI.I.INS B54C-9Alll SERVICE BULLETIN NO 2 IREVLSION NO I)AND 331113-6( 1

SERVICE DULI.B1‘IN NO. IltHEVISION NO. II.


NOT6

Only the eapstan nssemhlics are to be replaced. Originalservo ilssemblics are to be retained for reinslnllntion.

I Cain ;I.usJE to oilen,n, elevator. ruddel´• and elevator trim autopilot capston sssomblies. Refer to applicnblrC~,llinl Sol´•vice Info,.miltion Letter for ;Ippmximute loa,tion of eapatnn assemblies in airplane (rrfel´• to Figul´•eII.

MOI)I1L COLLINS PUBLICATION

700 SERVICE INFORMATION I.ETTER 5-78 (REV !)For AP-107

6~OA SERVICE LNI?ORMATION LETTER 11-14 tKEV 4) Far AP-106

69011 SERVICE INFORMATION I.E~EK 11-14 (REV 4) For AP-106

6Y0C SERVICE INFORMATION I.E~IR 3-80 (REV 1)For AP-106

6901) SERVICE INFORMATION LETTEH 1-81 (REV 4)For AP´•1O(I

695 SgllVICF. INFORMATION LET~ER 8-80 IRIV 1) Far AP-1OB

6984\ SERVICE INFORMATION LE1TER 1´•81 (REV 4) Far AP-106

Figure I.

2. Inupoct uilrran, elevator, rudder and elevator trim eapstan assemblies br revision letter, loented next to the

purl number, on the edge of capatan mounting plate irefer to Figure 21.

Page 2 oft


CnPaaLTRIM TYPICALTRIMCAPSTAN ASSY SERVO ASSY(REF)

INSPECT CAPSTAN ASSYAPPLY WHITE PAINT TO THIS MOUNTING PLATE FOR

AREA ANO INK STAMP SLIP REVISION NUMIIERCLUTCH TORGUE SETnNO

TYPICAL PRIMARY NplcnLpnlMnnvcaPSrAa assY seRvonssv(REF) IREF)

INSPECTCAPSTANAS8YAPPLY WHITE PAINT TO THIS MOUNTING PLATE FOR

AREA AND INK STAMP SLIP REVISION NUMBERCLUTCH TORDUE SETTING

NOTE

i IT MI\Y BE NECESSARY TO USE AN

INSPECTION MIRROR TO LOCATEPART NUMBER AND REVISION LETTER.

Figure 2.

Pageaof 4


9 iT th. ..uilan I.Lta. i´• RIV L’(plimoo ro.atnn.l or REV K iLnm eiquUn.) and yaarin.nth and isr~rr RWK(are NOT stamped on the capstan assembly, the capstan assembly must be replaced. Proceed to step 5.

NOTI

Only primary capstan aaaembliss stamped with REV P andtrim capstan assemblies stamped with REV K are the

affected capatan assemblies.

4. If eapstan assemblies are stamped with any revision letter other than those listed in step 3 or are stamped with

the revision letters listed in step 3 but are also stamped with yeadmonth and letters RWK and have the number2 on sel´•vo mad plate marted out, they do not have to be replaced Proceed to step 8.

5. If eapstan assemhlylsl need to be replaced, contact the Collins Atlanta Factory Service Center to schedule the

ilpplapl´•inte quantity of exchange capstan assemblies. If the exchange assemblies will not be received in a timelymannel´•.lnd it is necessary for the airplane to continue operating until capstan assemblies are available, the

airplane owneriopel´•stor must have the break-away torque setting of the capstan assembly safety Friction slipclutch verined by a Collins approved maintenance facility. The airplane can then be returned to normal

ope,´•nting service if the break-away torque is within specified range listed in the applicable Collins ServiceInformation Letter listed in Figure i. This return to service will be time limited and capstan assemblyis) must

still be replaced by 1 July 1985: however, ilthe inspection indicates that a capstan assembly has been partiallycnl´•mded or completely frolen. it is recommended that the airplane be suspended from all night operations untiltbs capstan assembly is replaced.

6. Remove and replace capstan assembly(s) as follows:

a Disconnect and remove control cables fiom copstan drumb Remove servo assembly and capstan assembly from airpfane.

c. Sat slip clutch torque on new capstan assembly(si per applicable Collins Service Information Letterlisted in Figure i.

d Apply white paint on side of capstan assembly and ink stamp slip clutch torque setting on painted area

(reLr to Figure 2).

e l’ag identify capstan assembly(sl with airplane model. airplane serial number and system position(silemn, elevator, rudder or elevator trim) to assure that capstan assemblies are not intermixed priorto installation.

F Remove identifying tag (see step e)and install capstan asesmblyls) on airplane using e*istinghsldware.

g. Inspect and replace any night control cables as necessary.b. Reconnect cables to capston oasembly(s).

Set primary control cable tensions as outlined in the applicable GulFstream Aerospace Corp AirplaneMaintenance Manual.

j. Set bridle control cables as outlined in the applicable Collins Service Information Letter listed in Figure

k. Reinstall existing servo assemblies on capstan assemblies using eristing hardware.

7. Functional check autopilot system.

8. Fill out and mail Compliance Cord Specify the Following on Compliance Card:

a Inspected and Found that capstan assemblies do not need to be replacedb. Inspected and Found that ispecify aileron, elevator. rudder or trim) capstan assemblies need to be

replaced. Compliance will be in accordance with Collins, Atlanta per step 5, page 4

c. Inspected and replaced capston esfiembliel. List quantity of capstan assemblies replaced and systemposition (aileron, elevator, rudder or trim).


WEIGHT AND BAL*NCE: NO CWANG&.

SPARES*FFECTED: AI.L AFFECTED AP-106 ANI) AP-107 AIITOPILOT CAPSTAN ASSEMBLIES MUST nE

PULLED FROM SHELF STOCK, INSPECTIO ANO REPLACED AS NECESSARY

PUBLICATIONS I\FFECTED: NONE.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as Follows: Specify paragraphBu., 8h. or He. of Service Bulletin No 203, dated 8 February 1985, entitled "lnspeetion and Replacement of Collins AP-IOB and AP-IU1 Autopilot Capstan Assemblies", accomplished tdoto)

page I of 4

Senrice Bulletin GulFstreamAerospace


8 Frbrusry 1985

INSPECTION AND AEPLACEMENT OF COLLINS APS-65AUTOPILOT CAPSTAN ASSEMBLIES

MODELS AFFECTED: MODEL 695A, SERIAL NO. 96051MODEL 695R, SERIAL NOS. 96063, 96069, 96016, 86018, 96085 AND 96201 THRU 96202.

THIS SERVICE BULLETIN APPLIES TO THE FOLLOWING COLLINS SMT SERVOMOUNTS (CAPSTAN ASSEMBLIES):

COLLINS

PART APPLICABLE TOUNIT NUMBER SERIAL NUMBER

SMT´•GS 622-5755-001 24 thru 51, 261 thru 285,288 thru 304, SO? thru 831,347, 363 and 316.

SMT-6S 622-6135-002 63, 68 thru 77. 80 thru 96,485 thlu 620. 634, 154,136,739, 140,143, 146,149 and 750.

SMT-GSD 622-6411-002 43, (6 thru 48, 60 thru 69,?1 thru 73, 78, 19 and 81.

REASON FOR PUBLICATION: CERTAIN CAPSTAN ASSEMBLIES IN COLLINS APS-BS AUTOPILOTINSTALLATIONS ARE SUBJECT TO CORROSION WHICH COULD CAUSE THEFRICTION SLIP CLUTCH TO SLIP AT A HIGHER THAN NORMAL TORFLUE ORELSE NOT SLIP AT ALL. REFER TO COLLINS SMT-66( SERVICE BULLETINNO. 1(REVISION NO. 1).

COMPLII\NCE: INSPECTION WITHIN NEXT TWENTY-FIVE (26) HOURS TIME IN SERVICE.REPLACEMENT REFER TO STEP 5, PAGE 2.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE BULLETIN,CONTACT YOUR NEAREST GULFSTREAMCOMMANDER AUTHORIZED SERVICENTIR.

BY WHOM WORK WILL BE ACCOMPLISHED: INSPECT CAPSTAN ASSEMBLIES A d P MECHANIC OR

EQUIVALENT.

REMOVAL AND REPLACEMENT OF CAPSTAN ASSEMBLIESAN AUTHORIZED COLLINS AUTOPILOT INSTALLATION ANDREPAIR FACILITY.


ESTIMATED MAN HOURS: INSPECT CAPSTAN ASSEMBLIES TWO (2) HOURS.

REMOVE AND REPLACE CAPSTAN ASSEMBLIES REFER TO PARTS DATA FORTIME ESTIMATE.

Page I of 3

SERVICE BULLETIN No 204

CHARGE WARRANTY ExcHarraa a*as su C*LLMC COLLINS *TUINT~ ~CToRY BERVICE CENT~R *TPARTS DI\TA: KgPLACEMENT CAPSTAN ASSEMBLIES, 1F RE~UIKED, MAY BE OBTAINED ON A NO

(404) 896´•540G. TELEX: 51-2239 COLLINSRAD ATL TO THE ATI‘ENTION OF MR. DEE ATWOOD UPON

COMPLETION OF THIS SERVICE BULLETIN. THE ORIGINAL UNITS (AFFECTED CAPSTAN ASSEMBLIES)

MUST BE RETURNED IWITAIN THE UNITED STATES. SHIP FEDERAI. EXPRESS STANDARD AIR COLLECT OH

INTERNATIONALLY, SHIP AIR FREIGHT COLLECT) TO COLLINS ATLANTA FACTORY SERVICE CENTER. IF

SUSPECT UNITS ARE NOT RETURNED WITHIN 15 DAYS (30 DAYS INTERNATIONALLY) OF THE SHIPMENT

OF TIIE WARRANTY EXCHANGE UNITS, THE OWNEWOPERATOR WILL BE BILLED FOR THE

EXCHANGE UNITS. THIS OFFER OF NO CHARGE WARRANTY EXCHANGE WILL EXPIRE 1 JULY 1985.

COLLINS AVIONICS WILL PROVIDE UP TO TWO (2) HOURS PER UNIT (CAPSTAN) FOR REMOVAL AND

REPLACEMENT RY AN AUTHORIZED COLLINS DEALERISERVICE AGENCY. REFERENCE AIRCRAFT MODEL

ANI) FACTORY SERIAL NUMBER WHEN ORDERING CAPSTAN ASBEMBLIES. FOLLOWING IS A DULFSTREAM

AEROSPACE COKP. CERTIFICATION APPROVED LISTING, BY MODEL AND SYSTEM POSITION, OF THE

CAPSTAN ASSEMBLY PART NUMBERS:

GULFSTREAM AEROSPACE CORP. CAPSTAN ASSEMBLY PARTS LISTING

MODEI. AILERON ELEVATOR RUDDER ELEVATORTRIM

696A 622-5135-002 622-5735´•001 622-6735-002 622´•6411-002

BSSB 622-5135-002 622-6736-001 622-5736´•002 622´•6411-002

SPECIP~LTOOLS: REFER TO COLLINS SMT-65( )SERVICF. BULLETIN NO. 1 IREVISION NO. 1)


NOTe

Only the capatan assemblies are to be replaced. Originalservo assemblies are to be retained far reinstellation.

1 Gain access to aileron, .I~uatar, ´•udder and Bl.v.tor Vim ~spstan s~xmblra Re(sr ia Collins Sprui..~I

information Letter 3-83 for SCS-65 for approximate location of capston assemblies in airplane.

2. Inspect aileron, elevator, rudder and elevator trim capstan assemblies for serial numbers. The serinl number

is located on the capxlan assembly identification plate (refer to Figure I),

3 if the capstan assemblies have one of the serial numbers affected as listed under "MODELS AFFECTED~’, the

capstun assembly(si must be replaced. Proceed to step 5.

4. If the capatan assemblies are not any of the serial numbers affeotad as listed under "MODELS AFFECTED",

they do not have tu be replaced. Proceed to Step 8.

5. Il eupsten assembly(s) need to be replaced, contact the Collins Atlanta Factory Service Center to schedule the

appropriate quantity of exchange eapstan assemblies. If the elehnnge assemblies will not he received in a timely

manner and it is neceasary for the airplane a continue operating until capstan assemblies are available, the

airplane ownedoperntur must have the break-away torque setting of the capstan assembly safety friction slip

clutch verilied by a Collins approved maintenance facility. The airplane ran then be returned to normal

operating service if the break-away torque is within spsei8ed range listed in the applicable Collins Service

(nfbrmution Letter 5-88 for SCS-65. This return to service will be time limited and Eoptan assembly(sl nlust

still he replaced by 1 July 1985: however, if the inspection indicates that a capstan assembly has been partially

corroded or completely it is recommended that the airplane be suspended from all night operations until

the cnpstnn assembly is replaced.

6. Remove and replace cnpstan assembly(s) as follows:

a. I)isconnect and remove control cables E~am capstan drum.

b. Remove servo assembly and capstan assembly from airplane.

c. Set slip clutch torque on new capstan assembly(s) pr Collins Service Information i.etter 3-83 for SCS-

65. i

Page 2 of 3


enpsrahl nSsu

IDENTIFICATIONPLATE IREFI

NPIC~L SERYO

ASSY (REFI

TYPICAL C/\PSTAN

ASSY (REFI

norr

IT M~Y BE NECESE~RY TO USE I\ FLASHLIORT

nND INSPECTION MIRROR TO CHECK SERIAL NUMBERS.

Figure i.

d. Tag identify eapstan assembly(s) with airplane model, airplane serial number and system position(aileron, elevator, rudder or elevator trim) to assure that eapstan assemblies are not intermixed priorto installation.

a. Remove identifying tag (see step d.) and install capstan assembly(s) on airplane using existing

hardware.

f inspect and replace any flight control cables as necessary

g. Rewnneet cables to capstan assembly(s).

h SeC primsn. mntmi cabl. ta~ioos .a ouflind in th. applunbl. O.h~sm h~roalirr. Gory ~rplanE

Maintenance Manual.

i. Set bridle control cables as outlined in Collins Service Information Letter 3-85 for SCS-GS

j. Reinstall existing servo assemblies on capstan assemblies using existing hardware.

Functional cheek autopilot system.

8. Fill out and mail Compliance Card. Specify the following on Compliance Card:

a. Inspected and found that capstan assemblies do not need to be replaced.

b. Inspected and found that (apeeib aileron, elevator, rudder or trim) capstan assemblies need to be

replaced. Compliance will be in accordance with Collins, Atlanta per step 5, page 2.

e. Inspected and replaced capstan aas.mblies. List quantity of capstan assemblies replaced and syetem

position (aileron, elevator, rudder or trim).


WEIGHT ANI) BALANCE: NO CHANCE.

SPARES AFFECTED: ALI. AFFECTED APS-BS AUTOPILOT CAPSTAN ASSEMBLIES MUST BE PULLED FROM

SHELF STOCK,INSPECTEO AND REPLACED AS NECESSARY.


RECORD COMPLI~NCE: Malts an appropriate entry in airplane maintenance records as Follows: Specify paragraph

Be., 8b., or 8c. of Service Bulletin No 2011. d.ted II February 1985. entitled "lnspeetion and Replacement olCollins APS-

,,..,,ilat Capstan Assemblies accomplished (date)

Page 3 of 3

Culfstream Aerospace Corporation

Wiley Poll Qi,portP. O. Box 22500

Oklahoma City, Oklahoma 73123

Telephone: (4051 7895000 Tslsx:796 200

December 20, 1985

TO: OPERATORS OP COMMANDER TURBO PROP AIRCRAFTSUBJ: DESIGN MANEUVERING SPEED

A review of the Pilot Operating Handbook (P.O.H.) or Plight Manual (P~M) for

Commander Turbo Prop Aircraft has revealed a possible lack of emphasis of

the importance of the Design Maneuvering Spaed in aircraft operations.

As explained below, the enclosed P.O.H. or F/M changes end the placard state

that abrupt control movements above Maneuver Speed (111-149 Kts, dependingon aircraft model and weight) can result in dangerous structural damage and

possible loss of the aircraft. The P.O.H. or F/M changes are in the Airspeed

Limitation, Flight in Severe Turbulence and Definition sections. When you install

the placard and make the P.O.H. or P/M page changes, please read and understand

what is stated and that the possible consequences of making abrupt control

movements above maneuvering speed for any reason could result in structural

damage and possible loss of the aircraft.

Design Maneuvering Speed, Va is the speed defined by Vs (~j) where Vs is the

stalling speed with flaps retracted and N is the design maneuvering load factor.

This means that the aircraft, when operating at speeds equal to or less than Va,will stall prior to, or at the design load factor and thus not be overloaded byfull travel abrupt control surface movements or from gust encounters. Va varies

with the aircraft operating weight. The change pages attached hereto present

operating weight versus Va information for your specific aircraft.

We have made changes in the various Pilot Oparsting Handbooks or Flight Manuals

to emphasiee the importance of understanding Va, and have included a placardto be placed on the centerpost in the cockpit. The authorization and instructions

for installing the placard are contained in the enclosed copy of Service Bulletin

Ii you have any questions regarding the importance of this warning, please call

our Service Department at the following number; (405) 789-5000.

_

Se~iee BLeB getin g~llGulfstreamAerospace

SERVICE BULLETIN NO. Zo5

20Deccmber1985

Vn PLACARD INSTALLATION

MODELS AFFECTED: MODELBS0, SERIAL NOS. 11001 TIIRU 11079.MODEL 690A, SERIAI. NOS. 11100 THKU 11344.MODEL 690R, SERIAL NOS 11350’PHRU 11566.

MODE1.690C, SERIAI. NOS. 11600 THRU 11703, 11709 AND 11119 THRU 1 1?85.MODEL 690D, SERIAL NOS. 15001THRU 15042.MODEL 695, SERIAL NOS. 85000 THRU 95084.MODEL 695i\. SERIAL NOS 96001 THRU 96061, 96064 THRU 96068, 96070 THRU 96074.96076, 96077, 96019 THRU 96084AND 96086 THT(U 96100.MODEL 69IB, SERIAL NOS 96063, 96069. 96075, 96078, 96085 AN1)96201 THRU 96207.

REASON FOR PUBLlCATION: TO EMPAASIZE THE IMPORTANCE OF ORSERVINGVn SPEEDS.

COMPLlANCE: UPON RECEIPT OPTHIS SERVICE BULLETIN.

BY WHOM WORK WILL BE ACCOMPLlSHEI): OWNEWOPEKATOR, A P MECHANIC OR EQUIVALENT.


ESTIM~TEDMI\N-HOURS: THIRTY(SO)MINUTES.

PARTS DATA: PLACARD P/N 860783-689 COMPLIANCE CARD AND AIRPLANE FLIGHT MANUAL OR PILOT’SOPERATING HANDBOOK REVISION IS BEING FURNISHED WITII THIS SERVICE BULLETIN

SPECIALTOOLS: NONE.

/ICCOMPLISHMENT INSTRUCTIONS:

i. Apply860783-689 placard inch above any existing placards on windshield centerpost cover (referto Figure i).

2. Insert applicable revision in Airpfane Flight Manual or Pilot.. Operating Handbaaltas noted:

MODEL MANUAL REVISIONNO.

680 FlightManual 21690A FlightManual 28690B Pilot’s Operating Handbook 21690C Pilot’s Operating Handbook 19690D Pilot’s Operating Handbook 10696 Pilot’s OperatingHandbook 10695A Pilot’s OperatingHandbook 1869511 Pilot’s Operating Handbook 7

3. Fillautand mail Compliance Card.

ELECTRICALLOAD: NoChange.

WEIOHTPINDBALANCE: NoChange.

SPARESAFFECTED: No.

PUBLICATIONS AFFECTED: The Airplane Flight Manual or Pilot´•s Operating Handbook revision is furnished with thisSelvieeBulletin.

RECORDCOMPLII\NCE: Make an appropriate entry in airplane maintenance records as Bllaws: Service Bulletin No. 205,dated 2(1 December 1985, entitled "V* PLACARD INSTALLATION". aeeomplished (date)

Page 1 oE2

SERYICEnULLETINNOlao6

,o\ m o ~h

WINDSHIELDCENTERPOST COYGR

(REF)

0. 5" ABOVE UPPERMOST

880185´•888 PLACARD

PLACARD L

MAGNETIC COMPASS I I EXIS~ID PLACARDS

(REF) AND COMPASS CARDS

(REF)

CENTERLINE OF

AIRPLANE

VIEW LOOKING FORWARD AT

WIN DSH IELD CENTERPOST COVER

Figure 1.

Page 2 of 2

Sewice Bblllefin CulfstreamAerospace


1? August 1881

INSPECTION OF EMPENNAGE ATTACH AREA AT

FUSELAGE STATION 409.56

MODELS AFFECTED: MODELS 690, 690A, AND 690B, SERIAL NOS. 11001 THRU 11566.MODEL 690C, SERIAL NOS. 11800 THRU 11135.MODEL 89OD, SERIAL NOS. 15001 THRU 15042.MODEL 695, SERIAL NOS. 95000 THRU 95084.MODEL G9SA, SERIAL NOS. 96001 THRU 96100.MODEL 695B, SERIAL NOS. 96082, 98063, 96069, 96015, 96078, 96085 AND 86201 THRU98208.

REASON FOR PUBLICATION: TO CHECK EMPENNAGE ATTACHMENT FOR CORRECT HARDWARE ANDTOR~UE. INSPECT FOR POSSIBLE CRACKSIDAMAGE IN AREA.

COMPLIANCE: AT 2000 HOURS TOTAL AIRFRAME TIME OR WITHIN NEXT 25 HOURS IF BEYOND 2000

(.3HOURS *ND BEPE~T E~CX L1 MONTHS OR im Bouns, wmcwEvER COMES RRST

BY WHOM WORK WILL BE ACCOMPLISHED: A p,P MECHANIC OR EQUIVALENT.


ESTIMATED M*N HOURS: MODELS 690, 690A AND 69011 UP TO SIX (B) HOURS.MODEL 690C, SERIAL NOS. 11601) THRU 11718 UP TO FOURTEEN (14) HOURS.MODEL 690C, SERIAL NOS. 11719 THRU 11135 UP TO SIX (6) HOURS.MODEL 690D UP TO SIX (6) HOURS.MODEL 696 UP TO FOURTEEN (141 HOURS.MODEL 895A, SERIAL NOS. 88001 THRU 98013 AND 96018 UP TO FOURTEEN (14)HOURS.MODEL 695A, SERIAL NOS. 96014 THRU96011 AND 96019 THRU 96100 UP TOSIX (6) HOURS.MODEL 695B UP TO SIX (6) HOURS.

PARTS DATA: AN AND MS HARDWARE (IF REQUIRED), PROCURE LOCALLY.

SPECIAL TOOLS: Torque wrench with 330 inch-pound oapability.

Page 1 of 6


INSPECT~REAAROUNO

80LT HOLES AND FLANOES

OF 8PPIR CAP FOR CRACKS

CONTROL LINI(AOE

ACCESS DOOR IREFI

VERTICAL STABILIZER

AFT SPAR IREF)

HORIZONTAL

SIABlLIZER

FRONT SPAR

O IREFI

O o o e9 O

dlo

0 o,oo e

00

00 O

6\1 I O "N"OD5’8 WASHER

~NS´•B BOLT

IUNDER NUT ONLY)

0´•O Mnlazs´•a NUT

MS2(888´•132 COTTER PIN

TOROLIE 180 TO 208 1N´•LBS

(4 PLSID

O O

0000

DO 00 O

INSPECT AREA BELOW

8PI\R FOR CRACI(S

0c00 eo

NOTE

VIEW LOOKING FORWARD 00 NOT INSTALL ANY WASHERS

AT FUSELAGE STA. 409.56 UNDER HEAD OF BOLT

FilYla 1´•

Page aoi8


*CCOMPLISHIENT INSTRUCTIONS:

1. Remove left and right rudder control linkage access doors that are lacated just aft of iuselage station 409.56.

2. Remove screws attaching tail cone

3 Disconnect electrical wiring from tail position lights and remove tail cone,

Install tail stand on tail skid.

5. Inspeet the following areas, at station 409.58, where vertical stabilizer attaches to horizontal stabilizer, forpossible craeksidamage:

a. Area around bolt holes (refer to Figure 1).

b. Upper and lower spar cap nsnge (refer to Figure II,

Spar web.

d. Station 409.56 bulkhead below horizontal spar (refer to Figure 1)

a. Around rivete that attach lower vertical stabilizer skin to ribs (refer to Figure 2).

F Lower ribs in vertical fin.

g. If no cracksldamage is found, proceed to step 8.

h. If cracks/damage is found, contact Gulfstream Aerospace product Support.

6. Inspect arear noted in step 5 for sheared. working or loose fasteners. Replace fasteners as necessary,

C ..r.

Working rivete are usually indicated by blaekidark coloring aroundrivet heads andlor black streaks on outer surface of the skin,around fasteners.

Inspect four (4) bolts attaching vertical stabilizer to front spar of horizontal stabilizer Lr installation ofcastellated nuts on bolts and washers under bolt heads (refer to Figure 11

NOTE

Service Letter No. 345 installs castellated nuts and an access doorfor saay access to empennage attach balte.

8. If there are castellated nuts installed and no washers under bolt heeds, proceed as follows:

a. Remove existing cotter pins and check bolt torque. Torque to be iso to 200 inch-pounds.

b Assure that nut. can be secured properly with new MS24665-132 cotter pins (refer to Figure 31.

c. If nuts cannot be secured prope’ly´• remove nut. Install an additional AN960D516 washer (under nutaniy), reinstall existing nut and torque 160 to 200 inch-pounds by tightening nut to low side of torrluerange and. if necessary, continue to tighten until a nut slot aligns with hale in bolt. Install new11´•1524665´•132 cotter pins.

d. Praceed to step II,

9. Ifcaateliaied nuts are not installed, replace existing vertical stabilizer attach bolt (4 places), one at a time, osfollows irefer to Figure 1):

a. Remove bolt and inspect bolt hole for possible damage.b. if hole is not damaged. install ANS´•B bolt, AN860D516 washer lunder nut only) and MS11815-6 nut.

Torque bolt LBO to 200 inch-pounds by tightening nut to law side of torque range and, if neeessery.eontinur to tighten until a nut slot aligns with hole in bolt. Install MS21665-132 cotter pin (refer toFigure 31

Page aolB

SER~CE OULLETIN NO. 20(i

n?

-i:g

X4

VERTICAL 1?

C

INSPECT LOWER RIBS

FOR CRACKS

INSPECT FOR CRACKSI\ROUND RIVETS ATTACHINGRIBS TO SKIN

Figure 2.

Page lofs

SERYICE BUI.LETIN NO ?I)h

I\DDITION*L WPISHER M*Y BEUSEO IF REOUIRED TO ~LIONHOLE IN BOLT WITH SLOT IN NUT

VIEW SHOWING INCOARECT VIEW SHOWING CORRECT~LIONMENT OF HOLE (N BOLT I\LIGNMENT OF HOLE IN BOLT

Figure 3.

NOTE

An additional AN960D6iB washer may be installed lunder nut

oniyl. if necessary. to assure proper alignment of hole in holt withslots in nut.

fxe i) hol. is damng.d, it is acceptable to use ANG-7 bolt 0.3;9" diameter hale) only if an edgedistance of(l.56inch or more can be maintained.

d ilit is determined, prior to reaming existing hole, that an edge distance of 0S6-inch or more cannotbe maintained, contaet OulUream Aerospace Product Support for further inrtructions.

e II it is determined, prior to reaming existing hole, that an edge dirtmee uP O.SB-inch or more can bemaintained ream damaged hole to 0.315"10.379" diameter and install ANG´•i bolt, AN960D616 w~her(under nut onlyl and M517825-6 nut Torque bolt 300 to 330 ineh´•paonds by tightening nut to low sideof torque range and. if necessary, continue to tighten until a our slot aligns with hole in bolt. InstallMS2J665-1311 cotter pin (refer to Figure 3)

NOTE

An additional ANSBODB1G washer may be installed lunder out

only), if necessary to assure proper alignmem of hole in bolt withslots in nut.

10. if there are castellated nuts installed and washers under bolt heed, proceed as follows:

a P\emo~r bolts affected, one at a time, and inspect bolt heir. for poalibls damage

NOTE

Do not have more than one (1) bolt out at the same tin,e

b If IloleJ are not dnmnged, reinstall existing ANS-B bolt. ANYI(OD,IB ~unshel. .,r w;lsberx (under nutonl,´•l and existing MS11825-5 nut. Torque bolt to L60 to 200 incb-pilunlis by tightening nut to low sideof tol´•qus range and. if necessary, continue to tightm until r nut Jlot nliiinx with bile in holt. Installnew MS21665-131 cotter pin (refer to Figure 31.

Pab’eSofG


c If hales are damaged, it is acceptable to use AN6-? bolt (0.376"10.379" diameter hole) only if an edgedistance of OS6-inch or more can be maintained.

d. If it is determined. prior to reeming existing holes, that an edge distance of O.58-inch or more cannotbe maintained, contact Gulfstream Aerospace Product Support for further instructions.

e if it is determined, prior to reaming existing holes, that an edge distance of 0.56-inch or more can bemaintained, ream damaged hole or holes to 0.376"10.379" diameter and install ANB-? bolt, ANSB~TiGIBwasher (under nut only) and MS11825-6 nut. Torque bolt S00 to 330 inch-pounds by tightening Rut tolow side of to~que rang. and, if necessary, continue to tighten until a slot aligns with hole in bolt.Install MS24685-134 cotter pin irefer to Figure 3).

NOTE

An additional AN960D616 washer may be installed (under nutonly), if necessary, to assure proper alignment of hale in bolt withslOtP in nut. The above listed hardware is to be procured Lacelly.

11 Reconnect electrical wiring to tail position lights and reinstall tail cone on airplane using elisting hardware

12. Reinstall lelt and right rudder control linkage access doors using existing hardware.

13 Touchup paint as necessary.

14. Fill out end mail Compliance Card specifying if cracks were found and if oversi.e bolts were installed.

ELECTRICAL LOAD: NO CHANCE

WEIGHS AND BALANCE: NO CAANOE.

SPPIRES AFFECTED: NO.

PUsUC*TUINS*FFECICO: NONE C_RECORD COMPLI*NCE: Make an appropriate entry in airplane maintenance records as follows: Sely-ice Bulletin No.206, dated I? Au~ust 1981, entitled "lnspection of Empennage Attach Area at Fuselage Station 409.56,,’ accomplished:(date)

page BufB

cko~l,Service Bwlletin GulfstreamAerospace

SERVICE BULLETIN NO. 20?A

BUI~Y´•NI IINSPECTION AND/OR REPLACEMENT OF DEVORE TEL-TAIL

L00O1RECOGNITION LIGI´•IT BULBS

MODELS AFFECTED: THE FOLLOWING MODELS WITH DEVORE TEI,TAIL LOGOIRECOGNITION LIGHTING8YSTEM INSTALLED PER 8TC gA1O1?EA OR FACTORY INSTALLED PER COMMANDERDRAWINGS 890449 OR 880453 AND IPPILIZING DEVORE TEL-TAUL BULBS P~ DA-21AND DA-1S:

MODELS 500, 50OA, SOOB, 50011, 520, 660, 560A, 560E, 5608, 680, 680E, 680F, 680F(P),680n, 680FL(P), 680T, 680V, 680W AND 720, SERIAL NOS. 1 THRU 1876.MODEL 5005, SERIAL NOS. 1166 THRU 1816 AND 3080 THRU 3313.MODEL BB1, SERIAL NOS. 6001 THR~ 60?a.MODEL 685, SERIAL NOS. 12000 THRU 12066.MODELS 690, 69(IA AND BgOB, SERIAL NOS. 11001 THRU 11666.MODEL 690C, SERIAL NOS. 11600 THRU 11135.

MODEL B9oD, SERIAL NOS. 15001 THRU 15042.

MODEL 695, SERIAL NOS. 86000 THRU 95084.MODEL 695A, SERIAL NOS. 96W1 THRU 96061, 86064 THRU 86068, 96010 THRU 96014,116016, 96011, 86018 THRU 9608´•1 AND 96088 THRU 96100.MODEL 69511, SERIAL NO8. 96062 AND 86201 THRU 96207.

REASON FOR PUBLICATION: REPORTS OF GLASS BEADS VIBRATING OUT OF LOoOlRECOCNBION LIGHTBULB BASE DUE TO POTI~INCr PROBLEMS. GLASS BEADS COLLECTED INGREASE ON ELEVATOR TRIM CHAIN AND CAUSEDA JERKEY OR JAMMEDCONDITION.

COMPLIANCE: WITHIN NEXT TWEEFI~Y-FIVE (25) HOURS TIME IN SERVICE AND EVERY TWENTY-FIVE (25)HOURS THEREAFI~ER UNTIL LIGHT BULBS ARE REPLACED WITH DA61 OR DA?2 BULBS. I

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYINGWITH THIS SERVICE BULLETIN, CONTACT YOUR NEARESTGULFSTREAM COMMANDER AUTHORIZED SERVICENTER.

BY WHOM WORK WILL sE ACCOMPLISHED: OWNER/OPERATOR, A L P MECHANIC OR E$UIVALENT.

AFPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.

ESTIMATED MAN HOURS: 1.6 HOURS.

PARTS DATA: CONTACT DEV(IRE AVIATION CORPORATION PRODUCT SUPPORT DEm.. 6104B KLRCHERBLVD., N.E. ALBUQUERBUE, NEW MEXICO 81108 TO ARRANGE FOR BULB P/N DA-16 OR DA-21REPLACEMENT EXCHANGE.


Psgs 1 of S

SER~ICE BULLFNN NO. aO?A

RH LO(IOIREW(INITIONLIGHT

LH LO(OOREECWNTTIONLIGHT

LINI(I\(IEACCES8DMIR

IN8PECT WTTIN(I COMWVNPELEVATOR FOA CR*CI(S. OHIPPINO ANO

DISLODOEMENT(REF) ~4

~Pa-E"F9"

ROLLERCHI\IN

IREFIE~EvnroRTl\sIREFI

fRPP~CKET

FCra i.

PpgePofS

~t


)ACCOMPUSHMENT INSTRUCTIONS:

i. Assure that battery switch is in the OFF position.

a. Remove covers hem left and right logoiremgnition lights (refor to Figure 1).

3. Remove bulbs from logolrecognition lights.

4. Check bulb potting compound for cracks, chipping or dislodgement. If any of these conditions exist, the bulbsI

must be replaced with new bulbs. The new bulbs should be P~ DA61 or DA?O.

NOTE

Tbs 0116 bulb (II MC Ivatan~) i, by Dh61 ´•nd 0~7 1bulb (28 VDC system) is replaced by DA?2.

5. Contact DeVore Aviation Product Support Dept., 61048 Kircher Blvd. N.E., Albuquelque, NM 87109 to arrange

for obtaining improved DA61 OR DA72 light bulbs,

NOTE

If new improved DA61 or DA72 bulbs are not immediately

available, it is acceptable to use new DA1S or I)AZ? bulbs if the

potting compound is acceptable. These bulbs must be replaced when

new improved DAS1 or DA?2 bulbs are available.

6. Install bulbs in logoirecognition lights.

NOTE

Handling bulbs with bare fingers will deposit finger prints and

grease on bulbs. Clean bulbs witb a grease-free solvent such as

acetone before illuminating bulbs.

If the logoirecognition light system has been deactivated, the

airplane should not be operated witb non-functioning bulbs. It is

recommended that bulbs be removed ham the fixture and wiring be

capped and stowed, Alternate deactivation of the system would be

removal of the entire light assembly and installing cover plate,DeVore Pi~ 00033078-1, and insulation and tie back of wires.

7. Install covers an logoirecognition lights usmg existing hardware. Torque screws 8 to 8 inch-pounds.

8. Remove left and right rudder control linkage access doors that are located just below horizontal stabilizer on

aft fuselage tail section (refer to Figure i).

9. Inspect elevator trim chains and sprockets for grease contamination with glass beads (refer to Figure i).

10. Check cavities in horizontal stabilizer and empennage far glass bead contamination. Remove ail glass beads.

11 if glass heads are present in greese on elevator trim chains and sprockets, clean elevator trim chains and

spmckets and remove contaminated grease and glass beads.

12. Lubricate elevator trim chains and sprockets as outlined in the applicable Airplane Maintenance Manual.

1S. Functional check elevator trim system to assure that system i. operating properly and smoothly.

14. Reinstall rudder control linkage access doors using existing hardware.



WEIGHT FIND BI\LANCE: NO CHANGE.

SPARES AFFECTED: ALL DA1B AND DA21 BULBS SHOULD BE REMOVED FROM STOCK AND REPLACEDI

WITH DAS1 AND DA72 BULBS.

PUBLICI\TIONS AFFECTED: NONE

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Bulletin No.

20?A, dated 18 Augustl988,entitled "Inspection sndlor Replacement of DeYore TeI-Tail LogolRscognition Light Bulba.’´• Iaccomplished: (dste)

Page 3 of 3

,Service Bulletin IIRCRIIFT CORPORIT)ON

P.O. Box 3389

Adinm~n. WA 98223

Tel: (206) 4358797 Fax:1206)~1112

8ERVICE BULLETIN E10. 209 original: November 15, 1990

INBPECTION AND/OR REPLACEMENT OF NOBE WUmINO OEAIL AXLE

MODeL8 AFFECTEDI

The following medals that have replaced nose landing gear axlesbetween January i, 1986 and February 24, 1988:

All Commander twin-engine models equipped with reciprocatingengines or turboprop engines except Serial Nos. 1 through 190 andModel 700.

NOTEIf you have not replaced an axle, P/N 9545, duringthe time noted shove, inspection is not required

REABON FOR FWLICATIONt

Possible error in heat treatment. Material may be of a lesserstrength than drawing requires.

COMPLIANCE:

Within next twenty-five (25) flight-hours time in service.

8Y ISgOn IPORX wILL BE ACCOMPLISBED:

n 8 P Mechanic (or equivalent).

APPR(IVAL:

Engineering design aspects are FAA approved.

ESTIMATED MAN HOVRS:

Two (2) hours.

Page 1 of 4


PARTS DATA:

Parts required to conply with this service bulletin may be procuredthrough your nearest Twin Commander Servicecenter. If axle is

found to be defective, a credit of two (2) hours labor and creditfor nose landing gear axle will be issued upon receipt of a

properly executedwarranty claim, accompanied by the defective axle

and proof of compliance. Reference this service bulletin, aircraft

model and factory serial number when ordering Service Bulletin No.

209 Kit consisting of the following:

QTY Part No. Description

1 ea. 9545 Axle

1 as. Service Bulletin No. 209 Instructions

SPECIAL TOOLS:

Material hardness tester.

ACCOMPLISHMENT INSTR~OCTIONSt

1. Jack airplane as outlined in the airplane Maintenance Manual.

2. Remove nose landing gear axle as follows:

a. Remove axle bolt nut, axle bolt and plugs.

b. Remove axle from fork assembly.

c. Remove nose wheel assembly and spacers.

3. Using a material hardness tester, check hardness of nose landing

axle. Axle must teet 150 ksi minimum (Rockwell hardnesss of C34

to C37) (refer to Figure i).

4. If axle test is acceptable, proceed to step 6.

5. If axle test is not acceptable, replace with new 9545 axle and

proceed to step 6.

Page 2 of 4


)6. Tnstall new or enistin~J 954~ axle as iallare:

a. Clean wheel bearings/races in high grade kerosene.

NOTE

Do not clean bearings in gasoline.

b. Dry bearings with compressed air. Do not spin bearings.

c. Inspect bearings for pits, scoring, corrosion and wear.

Replace if necessary.

d. Pack bearings with clean bearing grease as outlined in

the airplane Maintenance Manual.

e. Install bearings in wheel asssembly.

NOTE

Additional grease may have to be added to

hearing housing after bearing has been installed.

f. Lubricate load bearing surfaces of axle, washer and

axle nut.

g. Install spacers in gear fork assembly.

h. Install nose wheel assembly in gear fork assembly.

i. Insert axle through fork and nose wheel.

i. Install axle plugs, axle bolt and nut. Tighten axle bolt

until wheel bearings begin to bind, then back off until

bearings are just free.

k. Functionally check gear operation.

7. Remove jacks and tail stand from airplane.

8. Fill out and mail Compliance Card and note on Compliance Card

if axle was replaced.

Rage 3 of 4


PLUO

AXLE BOLTAXLE WHEELAGSYBOLT

NUT

SPACER

AXLEI/

TSPACER

ACCEPTABLE TO PERFORM

HARDNESS TEST HERE

PAEFERREOTOPERFORMHPIRDNESS TEST AT ENDS

OF AXLE

Piguee i.


IPEIORT AND BALANCE1 NO CHANGE.

SPARES AFFECTED:

All axles in spares stook must be checked for hardness and removed

if found to be defective.

POBLTCATIONB APBECBED: NONE.

RECORD COMPLIANCEr

Make as appropriate entry in airplane maintenance records as

follows:

Service Bulletin No 209, dated November 15, 1990, entitled

"Inspection and/or Replacement of Nose Landing Gear Axle"

accomplished: (date).

Page 4 of 4

,Senn’ce Bu iletinBox 3388

IIRCRIFT CORPORITION

Arlington. WA 98223Tsl: (208) 435´•8791 Fax: (208) lCH12

SERVICE BULLETIN NO. 210 Original: February 1,1991

OF FLAP MASTER POLLEY A~D CABLE wITB INSPECTION OF

REMAINING FLAP 8Y8TEM

HODELB AFFECTED:

All models of piston and turbine twin engine Aero Commanders

except the model 700.

REASON FOR PWLICATIONt

Part I: Complete flap system cable inspection.

Part II: Mandatory replacement of the master cable pulley.

Note: A master pulley is located on the leftside of the fuselage, and is attached to

the flap actuator. On one aircraft the

groove of the master pulley was Found to

be too narrow for the cable. The cablewas forced to ride on the sides of the

groove rather than seated in the bottom of

thegroove. This condition accelerates

cable fatigue. A review of the drawingsshows that the master pulley dimension isin error throughout the fleet.

On the right side of the fuselage is a

slave pulley attached to the master pulleyby a pushrod. Review of all drawingseffecting allpulleys in the cable flapdrive system for the models effected,demonstrates that only the master pulleygroove dimensions are in error. However,one slave pulley has been found to alsohave groove dimensions that were in error.

With respect to the inhoard and outboard

flap pulleys, two outboard flap pulleyswere found to be rubbing on their mountingbrackets. The pulley clip retaining the

cable was nearly worn through due to

rubbing.

Page 1 of 7


The Part I inspection if. for the purposeof inspecting slave pulley grooves and to

detect any other flap system pulleycausing accelerated cable fatigue.

Outboard pulleys are also to be inspectedfor bracket and clip rubbing.

COHPLUUYCE:

Timing: Part I, inspection, and Part II, master cable pulleyreplacement, shall occur within the next 100 hours

for aircraft with less than 2200 landings and within

20 hours for aircraft with greater than 2200

landings or with an unknownnumber of landings.

Part I: A. Cable inspection of all Flap system cables shall

be done with a soft cotton cloth.

8. Inspect all flap pystem pulleys for rubbing with

their support brackets.

C. Gage inspection of slave pulley.(Refer to Figure

Part II: A. Mandatory master pulley replacement.(Refer to

Figure i)

B. Mandatory replacement of master pulley cable.

BY wBOM BORX wILL BE ACCOMPLIQHED:

A P Mechanic (or equivalent)

APPB~AL:

Engineering design aspects are F.A.A. approved.

Pace 2 of 7


ESTIIIATED MAN BOIIR8:

Part A. 18 hours (both sides)

B. 2 hours (both sides)

c. 1 hour (both sides)

Part II A. 2 hours

B. 2 hours

PARTS DATA:

Figure I leads into Table I for identifying the master andslave pulley numbers and their respective cable numbers.

SPECIAG TOOL81

Make a gage for inspecting the groove in the slave pulley.The gage may be:

a. An 0.125 +1- 0.001 diameter sphere

cl4.

B. An 0.125 o.001 diameter rodC. A flat gauge with the following profile: 0. 5 NIN

PICCOMPLISBXENT IN8PROCPI~ONB:

Part I A. With a soft cotton cloth, rub each flap systemcable over it’s length. where it snags, inspectfor bro]renwires. If there are any broken wires,the cable must be replaced.

8. Inspect each flap system pulley on both sides for

signs of rubbing against the upper and lower

support brackets. Be especially alert for wear on

the clip that secures the cable. Replacement is

mandatory if any clip is being worn.

Page 3 of 7


C. Insert the gage (made under the Special Tools

section) into the slave pulley groove. Back lightthe gage. If the gauge does not touch the bottom

of the groove, the slave pulley and it’s cable rrm~be replaced.

Part II A. Replace the master pulley.

8. Replace the master pulley cable and any slave

pulley cable when the slave pulley is replaced.

Figure 1. and Table i. coordinate the component parts with the

appropriate aircraft.


1(IIOHT AND BALANCE: NO CHANGE.

SPARED AFFECTED: Purge inventory of all master pulleys.Gauge inspect all slave pulleys for

dimension error, and purge inventory of

those slave pulleys found to have wrong

dimension.

PWLICATIONB EFFECTED: NONE.

RECORD COMPLIANCEt

Make an appropriate entry in aircraft log book as follows:

Service Bulletin No. 210, dated February i, 1991

entitled "REPWLCEMENT 08 FLAP EASTER POLLEY AND

CABLE wITE INSPECTION O~’RI~MAININO FLAP SYSTEM"

Part I Accompliahad:(date) State what was found on

cable/pulley inspection and slave pulleyinspection.

Part II Accomplished:(date) State what cables and

pulleys were replaced in addition to the

master pulley and cable if any.

Pace 4 of 7

SERVICE BULLFTIN NO. 210

TABLE I MASTER RULLEY ~D CABLE REPLACEMENT PART NOMBER8

nODEL EASTER PULLEY SERIAL EASTER PULLEP CABLE SERIAL

"A" in Figure I NOHBERB "1" in Figure I N~1MBER8

500 510101- 7 411 500012- 89 ALL

SUBS

500 A 510101- 7 ALL 500012- 89 ALL

500 B 510101- 7 ALL 500012- 89 ALL

500 U 510101- 7 ALL 500012- 89 ALL

500 S 510101- 7 ALL 500012- 89 ALL

520 510101- 5 1 500012- 89 ALL

150

560 510101- 5 151 500012- 89 ALL

230

560 A 510101- 5 231 500012- 89 ALL

410

560 A 510101- 7 411 500012- 89 ALL

SUBS

560 E 510101- 7 411 500012- 89 ALL

SUBS

560 F 510101- 7 411 500012- 89 ALL

SUBS

680 510101- 5 231 500012- 89 ALL

410

680 510101- 7 411 500012- 89 ALL

SUBS

680 E 510101- 7 411 500012- 89 ALL

SUBS

680 F 510101- 7 ALL 500012- 89 ALL

680 F(P) 510101- 7 ALL 500012- 89 ALL

Piiga 5 Of 7

8EBVICE BULLETIN NO. 210

MODEL KA8TW PULLEY 8ERULL HABTER PULLEY CABLE BWIAL

IIAll i, Figure I NUPIBERB "1" in Figure I NUWEERB

680 FL 510101- 7 ALL 500012- 89 ALL

680 FL(P1 510101- 7 ALL 500012- 89 AU

680 T 510101- 7 ALL 500012- 89 1413

680 V 1725

680 W 510101- 7 ALL 500012- 89 1473

1850

681 510101- 7 ALL 500012- 89 6001

6063

681 510101- 7 ALL 500012-272 6064

6072

685 510101- 9 ALL 500048-1 ALL

690 510101- 9 ALL 500048-1 ALL

690 A 510101-11 ALL 500048-1 ALL

690 B

690 C 510101-11 11600 500048- 1 11600

11999 11999

690 D 510101-11 15000 500048- 1 15000

15939 15999

695 510101-11 95000 500048- 1 95000

95999 95999

695 A 510101-11 96000 500048- 1 96000

695 B 96999 96999

720 510101- 7 411 500048- 1 ALL

SUBS

Paae 6 of 7


k?bd3 i

B L~n.Ylarhl.´•n. Idonthva DI Mh. CO.RIUCE WRO

A Maater Pulley (le(t aide (uaelage)TYPICAL

Slave Pulley (rigM aids. *aslage)CLIP c lnboard Flap Pulley (lan or dgh0

a Oumaerd flap Pulley lien or dgM)5i;

1 cable (lsRaida)

2 cable (riQM lids)3 ~sbls(lsnordgM)

cable (lener dgM)

cable (Isn or righh

Figure I Flap Pulley and Cable Assembly

Page 7 of 7

COXPLIANCE CARD

8ERVICE BOLLIITIN NO 210

REPWLCEHEN~ OF FLAP ~LAS’PER POLLEY AND CABLE WITII INSPEC~ION OF

REWAIHIN(I FLAP 8Y8TM

Model: Airplane:

Total Time: Total Number of Flights:

owner:

Address:

Part I IN8PECalON

A. Using the cable numbers in Figure I, give the cable

number, whether left or right wing, and number of

wire breaks, if any, found.

cable number left right no. of wire breaks

8. Identify any pulleys found to be rubbing with the

brackets.

Rubbing pulley identity:

C. Did the gauge touch the bottom of the slave pulley?

yes no

From the grease tracks does it appear that the cable

has been riding in the bottom of the groove as it

should7 yes no

Part II REPWACEMENT

A and B: state all pulleys and cables replacedincluding master pulley and cable.

Inspected By:

Date:

Telephone No.

MANDATORY

Se rvice Bulletin AIRCRAFT CORPORA TIONtsom Bgth Dr. N´•e, AT110110n. WAg8nJTel: (203) 4U8787´• Fu: (208) 41111iZ

Service Bulletin No. 213 Date: July 29, 1994

WING FATIGUE INSPECTION AND MODIFICATION

MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11730

MODEL 685, SERIAL NOS. 95000 THRU 95084MODEL BgOC, SERIAL NOS. 11731 THRU 11735 (PART I. ITEM 10 ONLY)

REASON FOR PUBLICATION:

PART I: TO PROVIDE INSTRUCTIONS FOR WING STRUCTURAL INSPECTIONS IN AREAS SUBJECTTO FATIGUE.

PART II: TO PROVIDE MODIFICATIONS TO WTEND FATIGUE LIFE AND REDUCE FUTURE MINSPECTION RECIUIREMENTS. PART II IS TERMINATING ACTION AND NO FURTHERSPECIAL INSPECTIONS PER THIS SERVICE BULLETIN ARE REQUIRED FOR ALL ITEMS AU(CEPT PART I. ITEM 10.

NTHIS INFORMATION IS AVAILABLE FROM FULL SCALE FATIGUE TESTING OF AMODEL B95A WING AND PRESSURE CABIN. THE MODEL 880C/695 WING IS THE SAME I DCONFIGURATION AS THE TESTED 695A WING.

A

COMPLIANCE: ITPART I: (INSPECTION) loINITIAL INSPECTION: BOW HOURS TOTAL AIRFRAME TIME IN CONJUNCTION WITH MAJOR I R

INSPECTION GUIDE I. IvSECOND INSPECTION: 7500 HOURS TOTAL AIRFRAME TIME IN CONJUNCTION WITH MAJOR

~RSPECTION GUIDE II, UNLESSPAR771 PREVIOUSLY ACCOMPLISHED.

SVBSWUENT 1000 HOUR INTERVALS UNTIL ACCOMPLISHMENT OF PART II. PART I. ITEM

INSPECTIONS: 10 IS TO BE REINSPECTED AT 1000 HOUR INTERVALS (SEE FIGURE 5).

PART II: (MODIFICATIONS)

INCORPORATION OF THE MODIFICATIONS AT THE TIME OF THE FIRST INSPECTION IS

RECOMMENDED IN ORDER TO MINIMIZE THE POSSIBILITY OF STRUCTURAL DAMAGEREQUIRING REPLACEMENT OF PARTS OR ADDITIONAL REPAIRS, AND TO ELIMINATE

FURTHER PART I INSPECTIONS.

Page 1 of 16


BY WHOM WORK WILL BE ACCOMPLISHED:

A 8 P MECHANIC (OR EQUIVALEN1) AND A CERTIFIED NDT INSPECTOR (OR EQUIVALENT) PERINSPECTION ~UALIFICATIONS.

NOTE:DUE TO THE COMPLEXITY OF THIS SERVICE BULLETIN IT IS RECOMMENDED THAT THEMODIFICATION PORTION BE COMPLETED BY AN AUTHORIZED MIIN COMMANDERSERVICE CENTER.


~SUMATED MAN HOURS: (INCLUDING ACCESS PER SIDE)

PART I: INSPECT WIND RIBS W.S. 39 AND W.S. 89 38 HRS

INSPECT WIND STRINGER ENDS 12 HRSINSPECT WING UPPER SKIN W.S. 103 W.S. 113 11 HRSINSPECT FUSELAGE STATION 144 FRAME 5 HRS

PART I: 88 HRS

PART II: M001N WIND RIBS WiS. 39 AND W.S. 80 -1 KIT 20 HRS

MODIFI WING STRINGER ENDS 3 HRSMODIFI WING UPPER SKIN W.S. 103 TO W.S. 113 -2 KIT 10 HRS

PART II: E 33 HRS

PARTS DATA: PART I: NOT APPLICABLE

PART II: PARTS RE~VIRED TO COMPLY WITH THIS SERVICE BULLETIN MAYBE PURCHASED FROM YOUR NEAREST TWIN COMMANDERFACTORY AUTHORIZED SERVICE CENTER UNDER KlT NUMBERSLISTED BELOW.

Kit Number 61213.1:

City Part Number Desoridlon1 170425-1 Angle1 170425´•2 ´•Angle1 170428´•1 Angle1 170426-2 Angle2 K180010-505 Filler2 K160015-1 Shlm1 170428-1 Angle1 170428´•2 Angle1 170428-501 Angle1 170428-502 Angle4 HL20PB´•5-3 Pin20 HLZ1PB-5-12 Pin

24 HL88-5 Collar

Page 2 ot 18


Kit Number 58213-2:

alv Part Number Descriotion1 K170316-1 Doubler

t K170318´•2 Doublert K170316-3 Doubler1 K1703164 Doubler

1 K170316-5 Filler

NOTE:

DESOTO 825309 POLYURETHANE PRIMER USED FOR TOUCH UP ON PARTS FURNISHED

WITH THIS KIT TO BE PROCURED LOCALLY.

KIT NUMBER ARV\ TO BE MODIFIED

58213-1 LEFT 3 RIGHT WING Rl8 WIND STATION 39 AND 69

88213-2 LEFT 3 RIGHT WING UPPER SKIN WING STATION 103 TO 113

SPECIAL TOOLS: NONE

INsPECTloNsunLlnCnTIoNS: (PART I)

1. PERSONNEL CIVALIFICATIONS

a. Level II Liquid Penetnnt with documented experience of no less than 200 hours.

b. Vision acuity requirements of MIL-STD-410E, or latest revision.

c. Documented training in accordance with MIL-STO-4108, or latest revision and recommended practiceSNT-TC-1A of the American Society for Nondestructive Testing,

2. MATERIALS ANDIOR EOUiPMENT

a. Solvent Cleaner, SKC-NF (Magnaflux) or equivalent per MILI-25135E.

b. Water Washable Fluorescent Penetrant, ZL60C, Level II (Magnanux) or equivalent per Mll-I-2513JE.

c. Non-Aqueous Developer, ZP-OE (Magnanux) per Mll-I´•25135E or equivalent.d. ZB-lOO Blacklight (Magnaflux), 100w, 115v, 60Hr or equiv.a. Inspection minor.

f. Cleaner. Penetrant and Developer to be from the same manufacturer,

3. PROCESS

a. Per MIL-STD´•B~BB.

b. Sensitivity Type I. Method A. Level II

PART I ACCOMPLISHMENT INSTRUCTIONS (INSPECTIONS)

1. Disconnect batteries.

2. Os-fuel airplane as outlined in the Airplane Maintenance Manual.

3. Perform a general structural $speotlan in acco~anca with applicable Maintenance Manual procedures and

inspection Program selected per Maintenance Manual Chapter 5. Particular attention should be given to

rivet lines, end fastener locations in splices, nn$gs or doublers and at any changes in cross se*lon. Also

areas having curved members and areas having small (less than 2 limes fastener diameter) edge distances.

Pace 3 ct 16


PART I ACCOMPLISHMENT INSTRUCTIONS (INSPECTIONS) (cont’d)

4. Close visual inspection is required, using Fluorescent Penetrant method as an aid in disclosing cracks.

Carefully remove sealants or finishes as necessary in o~er to allow inspection of the structural elements.

Moderate hand pressures applied between pans, in order to produce any relative movement allowed, may

assist in the detection of failure of the parts or joining fasteners. AIso, observe any rub marks indicatingrelative movement of parts under load. Finishes or sealants must be restored per recommended

Maintenance Manual practices after inspections are completed. Inspections refer to both right and left

aides of the airframe unless specified otherwise,

5. Remove upper wing skin access doon inboard and autboad of Wing Station 38.00 ribs.

6. Gain access to the lower nanges of the Wing Station 39.00 rib between the Main Spar Lower Cap and

stringer No. 7.

NOTE:

THESE INSPECTIONS REQUIRE THAT THE AFT INBOARD AND OUTBOARD FUEL

CELLS SE MOVED ASIDE TO GAIN ACCESS TO THE RIBS (L DOUBLERS. REFERENCE

MAINTENANCE MANUAL CHAPTER 28 FOR PROCEDURES.

7. Inspect the Wing Station 39 rib and doubler lower flanges, an of the main spar and foma~d of stringer No,

7, for cracks in or near the flange radius or adjacent to rivets (reference Figure 1), using Fluorescent

Penetrant Method.

Inspect the Wing Station 39 and 69 ribs at the stringer No, 3 cut-out at the upper nange area for cracks in

or near the flange radius, web or flange adjacent to rivets (reference Figure 2), using Fluorescent

Penetrant Method,

8. Inspect wing upper Stringers, No, 1, 2, and 2A at their inbaalrl termination for cracks in the stringen or

attaching structures and for any failed fastenen (reference Figure 3), using Fluorescent Penetrsnt Method.

The inboartl 4.5 Inches of the stringers are to be inspected for cracks from the forward side, The

corresponding area of the frame is to be inspected from the an side. All visible fanenen in the inboard

end of the stringer; are to be inspected for loose, working or sheared conditions.

NOTE:

THIS INSPECTION WILL REQUIRE THE REMOVAL OF A PORTION OF: THE PASSENGER

CABIN INTERIOR TO GAIN ACCESS TO THE STRINGERS IN THE UPPER CABIN. IN

AODITION, THE CABIN OXYGEN LINES IN THE AREA OF THE STRINGERS ARE TO BE

DBCONNECTED FOR ACCESS,

9. Inspect the upper skin in the area outboed of Wing Station 103 and an of stringer No. 1, for cracks in the skin

(reference Figure 4), using Fluorescent Penetranl Method.

NOTE:

SERIAL NUMBERS 11620, 11864, AND 95038 ARE EXCLUDED FROM STEP 8.

10. Inspect Fuselage Station 144 frame, doublers at wing attach nnlngs above Water Line -10 for cracks and for tailed

fasteners (reference Figure 5), using Fluorescent Penetrant Method.

CAUTION:

THE 144 FRAME IS TO BE INSPECTED THRU THE EXISTING PANEL LIGHTING HOLE

FROM THE FRONT 91DE ONLY. DO NOT REMOVE THE FIBERGLASS CABIN PRESSURE

SEAL COVERING THE AFT SIDE OF THE FRAME AT THE WING ATTACH FITTING,

Page 4 of 19


PARTII ACCOMPLISHMENT INSTRVCTIONS (MODIFICATIONSI

NOTE:FOR LOCAL TOUCH UP ON EXISTING STRUCTURE, USE ZINC CHROMATE. DO NOT MIXCHROMATE AND POLYURETHANE PRIMERS ON THE SAME PART. ALL NEW ALUMINUMPARTS FROM TWIN COMMANDER ARE POLYURETHANE PRIMED.

i. -1 KIT. MODIFICATION OF WING STATION 39 AND 68 RIBS.

DAMAGE LIMITS

THIS MODIFICATION IS APPLICABLE:A. IF THE WING STATION 39 RIB LOWER FLANOE CRACKS ARE IN THE BEND RADIUS

ONLY (DO NOT EXTEND UPWARD INTO THE RIB WEBS SEE FIGURE 1.B. IF THE WING STATION 39 AND 69 R1B AT THE UPPER WING STRINGER NO. 3 iS NOT

CRACKED SEE FIGURE 2.

IF THESE LIMITATIONS ARE EXCEEDED, DO NOT PROCEED WITH MODIFICATION.DAMAGED PARTS MUST BE REPLACED OR AN APPROVED REPAIR MUST BE INSTALLEDPRIOR TO COMPLETION OF THE MODIFICATION AND RETURN TO SERVICE.

CAUTION:EXERCISE EXTREME CARE WHEN CUTTING TO AVOID DAMAGING THE MAIN SPARLOWER CAP, SPAR DOUBLER PLATES OR OTHER WING STRUCTURE. USE STAINLESSSTEEL SHIMSTOCK OR OTHER MEANS AS APPROPRIATE TO PROTECT THE STRUCTUREFROM DAMAGE. TO REMOVE RIVETS, DRILL OFF HEADS AND DRIVE OUT. DO NOTDRILL OUT. TO REMOVE HVCKBOLTS, USE A COLLAR SPLITTER FIND DRIVE THE STEMOUT. ACCEPTABLE TO USE A 3X RIVET GUN OR SMALLER. WHEN REMOVING ANDIORINSTALLING INTERFERENCE FIT FASTENERS (HUCKBOLTS OR HI-LOKS) BACKUP THESTRUCTURE WITH AN APPROPRIATE BUCKING BAR.

a. Modify the Wing Station 39 rib and doubler lower flanges per Figure B which replaces the formed flangesbetween the main soar and stringer No. 7 with back to back extruded angles.

b. Trim away the lower existing wing station 39.00 rib nan8es (rib has both inboard and outboard nanges).including the bend radius from the Main Spar LowerCap to stringer No. 7 -(reference Figure 1 and 8).00 NOT DAMAGE THE EXISTING INTERNAL ALUMINUM STRAP UNDER THE RIB FLANGE.

c. Remove existing fasteners g rivets common to the rib and 170318-1/-2 cap angle sind 10 fastenerscommon to the rib lower nanges and lower wing skin.

d. Discard the removed db nangeo.

CAUTION:

THE HI-LOK COLLARS WILL BE VERY CLOSE TO THE VERTICAL LEG OF THE ADDED170425-1 AND 170020-1 ANGLES ON SOME AIRPLANES, MARK THE ANGLES BEFOREDRILLING TO DETERMINE IF THE COLLARS CAN BE INSTALLED. IF THE COLLARS

CANNOT BE INSTALLED, DETERMINE IF A SUBSTITUTE MSZ1OIZ OR M521043 NUT CANBE INSTALLED. IF THE NUTS CANNOT BE INSTALLED, CONTACT TWIN COMMANDERAIRCRAFT CORPORATION BEFORE CONTINUING.

o~..


1 KIT. MODIFICATION OF WING STATION 39 AND 69 RIBS (cont’d)

a. Fit the 170425-1,170426-1 angles and K160010-505 fillers to the rib and lower wing skin.

i. Check for gaps between the 170625-1. 170428-1 angles and the lower wing skin. If a gap is present.select a K180015-501 tapered shim as required to prevent prelaading the structure. Shlms may hereworked and cut to sire to fill gaps. Shims must pick up a minimum of two fasteners. A MS2d426AD4rivet may be installed between existing Hi-Loks (minimum pitch .75 inch).

NOTE:IN LIEU OF A SOLID METALLIC SHIM, THE USE OF CAST PLASTIC SHIM MATERIAL (EPON934 OR EOUIVALENT, PER THE MANUFACTURES DIRECTION) IS PERMITTED UP TO AMAXIMUM OF.020 INCHES. ANY NECESSARY REMAINING SHIM MATERIAL REQUIREDBEYOND .020 SHALL BE METAL AS ABOVE. CHECK ALL INSTALLED FASTENERS WITH A.002 INCH THICK BRASS FEELER GAGE FOR SHANKING. GAGE MUST NOT TOUCH THESHANK OF THE FASTENER BEMIEEN PARTS.

9´• Remove all parts, break and smooth all sharp edges, deburr and prime per item i., as required.

h. Refinish all bare areas of the new parts with Desoto polyurethane paint 825-309 (added scarfs, reworkof tapered Shlms K180015, act.).

i. Line ream all Hi-Lok holes to the limits indicated on Figure 6.

j. Drill out any remaining fastener holes.

k. Permanently install all pans and fasteners;.

I. Modify the Wing Station 39 and 88 ribs per Figure 6, Detail B which adds a doubler angle to the upperflange and web ad]acent to the stringer and wire bundle cutout at stringer No. 3.

2. MODIFICATION OF END TRIMS OF STRINDER NO 1, 2 AND 2A.

NOTE:IF DAMAGE IS FOUND, DO NOT PROCEED WITH MODIFICATION. DAMAGED PARTSMUST BE REPLACED OR AN APPROVED REPAIR INSTALLED PRIOR TO COMPLETION OFMODIFICATION AND RETURN TO SERVICE.

a. Modify the end trims of st~nger No. 1, 2 and 2A per Figure 7 which´•adds a radius to the bulb section filletradius see Figure 3.

CAUTION:

THE 63 FINISH CALLED FOR ON FIGURE I IS EOUIVALENT TO A SMOOTH MACHINEDSURFACE, EXERCISE CARE TO NOT UNDERCUT THE EXTRUSION LEGS.

eano PI nf IR


3. -2 KlT. MODIFICATION OF WING UPPER SKIN WING STATION 103 TO 113.

DAMAGE LIMITS

(SEE FIGURE 4)

THIS MODIFICATION IS APPLICABLE FOR:A MAXIMUM CRACK LENGTH OF 1.00 INCH IN THE UPPER WING SKIN WHICH EXTENDSFROM THE INTERSECTION OF THE LEADING EDGE SKIN (STRINDER #1) AND THENACELLE FAIRING (W.S. 103.5), AFT AND OUTBOARD AT APPROXIMATELY A 45

DEOREEANGLE.ii UPPER WING 5KIN BUCKLE IN THE BnY.

SKIN BUCKLES BETWEEN RIVETS ON STRINGER #2.

THIS MODIFICATION IS NOT APPLICABLE FOR:

t~ I\ CRI\CI( LONGER THIIN l.L)O INCH.CRACKS IN THE UPPER WIND SKIN IN AREAS OTHER THAN A OF THESE LIMITATIONS.

IF THESE LIMITATIONS ARE EXCEEDED, DO NOT PROCEED WITH MODIFICATION. DAMAGEDPARTS MUST BE REPLACED OR AN APPROVED REPAIR INSTALLED PRIOR TO COMPLETIONOR MODIFICATION AND RETURN TO SERVICE.

CAUTION:EXERCISE CARE IN DRILLING RIVETS AT WING STATION 113. THE THIRD RIVET FROMTHE FRONT OF THE 110316-3 IS DIRECTLY OVER AN EXISTING TUBE WITH NO CLEARANCETO REINSTALL A RIVET. DO NOT DRILL THIS RIVET OUT. MARK THE RIVET BUTT ON THE

ADDED PARTS AND TRIM THE PARTS (U SHAPE) TO CLEAR THE BUTT.

a. Stop drill the ends of all crackswith a No. 30 stop drill hale. Dye penetrant inspect to ensure crack does

not extend beyond stop drill.

b. Modify the wing upper Jkin per Figure 8 which adds a spacer and stiffening angles to the skin bay between

Wing Station 103 and 113, and stringer No. 1 and 2.

NOTE:

COMPLY WITH THOSE PORTIONS OF SERVICE BULLETIN 198 NECESSARY TO ENSURESEALING OF THE WING STATION 113 RIB.

NOTE:

SERIAL NUMBERS 11620, 11684, AND 99038 ARE EXCLUDED FROM STEP 3.

4. Restore finishes, sealants and paint and reinstall fuel cells, access doors and interiors as required.

NOTE:

THE FUEL CELL NIPPLE CLAMP TOROUE PROCEDURES IN SERVICE BULLETIN 167,"FUEL CELL INSPECTION ANDIOR REPLACEMENT," ALSO COULD BE OF ASSISTANCE INTHE REINSTALLATION OF ANY FUEL CELLS DISTURBED OR REMOVED.

Refuel aircraft as outlined in the Airplane Maintenance Manual.

NOTE:THE FUEL SYSTEM PRESSURE CHECK PROCEDURE OUTLINED BY SERVICE BULLETIN

185, "FUEL CELL INSPECTION ANDIOR REPLACEMENT", COULD POSSIBLY EXPEDITE

THE LEAK CHECK OF THE FUEL SYSTEM FOR THE REINSTALLED FUEL CELLS WHICHWERE DISTURBED OR REMOVED.

ntlfi


6. Fill out the information on the Compliance Card and send to:

Twin Commander Aircraft CorporationService DepartmentP.O. Box 3388

Arlington, WA 88223

ELECTRICAL LOAD: No change.

WEIGHT AND BALANCE: No significant change.

SPARES AFFECTED: None.

RECORD COMPLIANCS; Make an appropriate entry In Airplane Maintenance Recods as follows: Senrice

Bulletin No. (213), dated June 2, 1884. entitled "WING FATIGUE INSPECTION

AND MODIFICATION," complied with as follows:

Part I inspection: List inspection items accomplished by item no., title, airplane total time, and date.

If the recommended modification of the inspection item listed has not been accomp-lished, list the next scheduled inspection times to repeat inspection of the item.

Part II Modification: List modincalions accomplished by drawing and dash no., title, airplane total time.and date.

Pane a nt 18


w.s.

O O 0~0)F3 01C

U -io-i- ij

NSP ITEM 7 (LIR)

INSPECT FOR CRACKS

(REF. FIGURE B FOR MOD.)

MAIN 1703154 RIB (REF.)

Figure I

LEFT W.S. JB SHOWN

aTR 1i7" (Rshrrnsa 1.P.C. Figure 2-19)W.P. W.S.

INSPECT FOR CRACKSLREF. FIDURE B. OETAII B

FOR MOI)IFICATIONIO a~Ma or o

UOCIU!OCI1C~

13

i..

OTRIH3W(RBLCI

INSP. ITEM 7 C 1IOU(´•MI SlIFFENER (Rrr)(L 6 R)

~I I I i VIEW LOOKING INBOARD

FigmlLEFIWb. 38 8nOWN. W.8. 89 MI.

(Ra(aacsl.P.C.Rgun~Js)

PROS 9 0(16


,.:5\

P

a "~.XINSP. ITEM 8 (L 6 R) P’

OISCONNECTOXYGEN I ;jIINE AT STR tll *NO #2

hlJm~,FORCRACKS (O

CHECKULF/ISTENIRS FlpuraJi*´•~IPcnwnwn

INSP ITEM g (L 1 R)

W.S.INSPECT FOR CRACKS IN THESE W.I.

AREAS (REF FIGURE 7 FOR MOO.) 1(*0 (01.5UPPER NACELLEFAIRING

LUAOINOSKIN

"01o

noio,

SrR´•I

INSPECTFOROAMIOE I

i

SEE FIGURE B I

I

n

LJRgun 4

(Rs~rsnso I.P.E. Rgwa u7. ZJg)

VIEW LOOKING DOWNgB UPPER WING SKIN

Pegs ~O of l6


INSP ITEM 10

(i a R)

144.W

FOR CRACKS FS.

r"NO INSPECTIONi II

I i II FROMAFTSIOE

I 1 it i REOLIIRED

tW I--C----j

nu

i iil/ ~WING A~TACH i iii.YI FII1~NO (REF) I U’ I II

W

--W~TERLINE´•(O.OO

VIEW n-n I-~-n

FbnsRIGHT HAND SnOWN. LEFT HAND OPPOSITE

(Rslsranca I.P.C. FiQurr~230. 2~52)

Page 11 of 16

COMPLIANCE CARD


WING FATIGUE INSPECTION AND MODIFICATION

MODEL: AIRPLANE SERIAL NO. TOTAL TIME (HRS)

AIRPLANE REGISTRATION NO.:

OWNER NAME:

ADDRESS:

City State Zip

TELEPHONE NO. AIRPLANE AGE: CIEARS)

PART I INSPECTION:

ilST INSPECTION ITEMS COMPLIED WITH BY ITEM NO.. TITLE, AND DATE OF COMPLIANCE.LIST DETAILS OF ANY CRACKS OR DAMAGED FOUND.

INSPECTED BY: TELEPHONE NO.

DATE SIGNATURE

PARTII MODIFICATION:

LIST MODIFICATIONS COMPLIED WITH BY MODIFICATION DRAWING AND DASH NO., TITLE.AND DATE OF COMPLIANCE.

MODIFIED BY: TELEPHONE NO.

ADDRESS:

Cny State Zip

DATE SIGNATURE

r~lllY

AIRCRAFT CORPORATION

SERVICE BULLETIN 214

March 2000

Operators of Model 900 (690D) and 1000 (695A/695B) Twin Commanders soon will

be able to bring their aircraft up to the service life standards of the last of these

models produced. Twin Commander Aircraft Corporation has developed a series of

airframe inspections and modifications, which will accomplish this. The inspectionsand modifications are explained in SE (Service Bulletin) 214.

This service bulletin provides a very thorough examination of the pressurized cabin

structure (the cockpit, passenger cabin and the inboard portion of the wing between

the two engines). The modifications involve the installation of new parts and

reinforcement of existing parts in various locations.

The areas requiring inspection andlor modification were identified by extensive

fatigue testing of a fuselage. The test fuselage accumulated significantly more

cycles than any airplane will ever experience in service. Due to the time required to

complete the testing, airplanes were being produced before the testing was

concluded. As the testing identified changes, they were incorporated into productionairplanes as they were being built. Thus, the later serial number aircraft had more of

the modifications incorporated at the factory than earlier serial number aircraft. SE

214 addresses these differences and outlines procedures required to upgrade each

aircraft to the very latest production configuration.

To complete this service bulletin, access to the complete inside of the fuselage is

required. The interior is removed; as well as the windshields, cockpit and cabin

windows, control yokes, instrument panel, cabin flooring and ductwork.

Pressurization sealer and anti corrosion compounds must also be removed in the

areas requiring inspection and modification.

Incorporation of SE 214 will ensure the continued safe and reliable operation of

these aircraft while enhancing their value. The issuance of this service bulletin is a

continuation of Twin Commander Aircraft Corporation’s commitment to support the

owners and operators while maintaining the airworthiness of the Twin Commander

fleet.

Contact your Twin Commander Service Center for additional information and details

on this service bulletin. They have knowledge, capabilities and have completed the

required training for the incorporation of SE 214 at a factory-authorized school. A

listing of Twin Commander Service Centers is attached.

Bill D. HurleyVice President and General Manager

nnJIN COMMANDER AIRCRAFT CORPORATION Arlington Airport 19010 591h Dr. N.E. Arlington, WA 98223 Telephone: (360) 435-9797 FAX: (360) 435-1112

SERVICE PUBLICATIONSLfLIAll~nAU17~EIQ

revisionII

notice A /RCRAFi’ CORPORA 7~ON19010 59’h Dr. N.E. Arlinglon,WA 98223-7832

Tel:(360)435-9797 FAX:(360)435-11~2

Service Bulletin No. 214

Revision No.

Release Date: April 19, 2000

WING AND FUSELAGE FATIGUE INSPECTION AND MODIFICATION

APPROVAL:


REVISED ITEMS AS INDICATED.

1) Part I INSPECTION I MODIFICATION TIMES, Table I, Pages 7, 8, 9, 8 10 of 72

a) Changed LEGEND at right hand side ofpage to read:

L FIGURE(S) 8 88

2) Part I INSPECTION, Figure #8B, Page 28 of 72

a) Changed REFERENCE at uppermost center ofpage to read:

TCAC DRAWING #300006-11 -529 ASSY FOR MODIFICATIONS

b) Changed FIGURE EFFECTIVITY at lower right hand corner ofpage to read:

EFFECTIVITYMODEL SIN

690D 15001 THRU 15034

695A 96014THRU 96017

695A 96019THRU 96076

EXCEPT SIN 96063,96069 96075

3) Part I INSPECTION, Figure #8C, Page 29 of 72

a) Changed REFERENCE at uppermost center ofpage to read:


b) Changed FIGURE EFFECTIVITY at lower right hand corner ofpage to read:

EFFECTIVITYMODEL S/N

690D 15001THRU15034

695A 96014THRU 96017

695A 96019THRU 96076

EXCEPT SIN 96063.96069 3 96075

Page No. of i

MANDATORYr~lAI

Service Bulletin A /RCRAFT C~RPORA T/ON19010 59’" Dr.N.E. Arlington.WA 98223-7832

Tsl:(360)435-9797 FAX:(360)435-1112

Service Bulletin No. 214 Date: January 26, 2000

WING AND FUSELAGE FATIGUE INSPECTION AND MODIFICATION

EFFECTIVITY: MODEL NO,690D (Serial Numbers 15001 thru 15040, Except as Noted)695A (Serial Numbers 96001 thru 96100, Except as Noted)6958 (Serial Numbers 96063, 96069, 96075, 96078, 96085 8 96204 thru 96208)

NOTE:

SERIAL NUMBERS 15037, 15041, 15042, 96064, 96072, 96088, 96201, 96202 AND 96203 ARE

NOT SUBJECT TO THE PROVISIONS OF THIS SERVICE BULLETIN (REF. TCAC SE 232

WING AND CARGO DOOR FUSELAGE FATIGUE INSPECTION AND MODIFICATION

MREASON FOR AThis Service Bulletin information is based on data devslopsd during the iull scale Fatigue Te~t conducted I Non the Model 695A wing and pressurized cabin. These modifications are required at the specific time

Dintervals indicated to maintain airframe life of 7,500 Hours or more. This Service Bulletin does not

superrade any prior Se~vice Publicaiions issued with respect to inspections or structural modlflaatiens IAT

COMPLIANCE:O

This Service Bulletin contains three (3) time compliance schedules. There is a schedule for inspectionRmodification set forth ´•in Part I, Table I; a schedule for recurring inspections set forth in Par! II, Table I; and

the following Table A, "lnitial Compliance Times".

YINITIAL COMPLIANCE TIMES

CURRENT AIRFRAME COMPLIANCE REQUIRED PRIOR TO (HOURS TIS)OURS/ TIME-IN-SERVICE) I OR WITHIN THE NEXT TMONTHSJ WHICHEVER COMES FIRST

0000-1700 (2700) Hours or [36]Months1701-2500 (3400) Hours or [36] Months

2501-3000 (3800) Hours or [36]Months3001-5000 (5500) Hours or [30]Months5001-6000 (6400) Hours or [24] Months

6001-7500 (7800) Hours or [181MbnthsOver 7500 121 Months

Table A

The interrelationship of these schedules is as follows:

No inspections i modifications are required before the expiration of the time period set forth in Tabk~.-L

applicable to the airplane; however it is highly recommended that all of the Part r, Table I inspections I

modifications be accomplished at the earliest practicable time.

Page No. 1 of 72

2/


COMPLIANCE: (cont.)

Before the expiration of the time period set forth in Table A applicable to the airplane, all inspectionsmodifications that are overdue according to Part I, Table I must be accomplished. Thereafter all remaininginspections I modifications described in Part I, Table I must be accomplished in accordance with the time

periods set forth in that table.

It is highly recommended by Twin Commander Aircraft Corporation that all inspections modifications

specified in Part I, Table I be completed at the time of first compliance with this Service Bulletin regardlessof total airframe hours. This will eliminate removing the same assemblies parts multiple times, and

reduce the possibility of damaging these assemblies I parts with subsequent airframe disassembly.

After initial inspections modifications have been accomplished, recurring inspections must be

accomplished in accordance with the schedule set forth in Part II, Table I.

EXAMPLE.. Aircraft has 5000 airframe Hours I Time-in-Service. The items with 1700, 2500, 3000, and 5000

Hour Aircraft Inspection Time Periods as required by Part I, Table I "INSPECTION

MODIFICATION TIMES" must be completed at or prior to 5500 Hours Time-in-Service or

30 Months, whichever comes first. It is recommended that the 6000 Hour and 7500 Hour items

also be accomplished at that time. If the 6000 Hour and 7500 Hour items are not accomplishedat the time of initial compliance, then these items must be accomplished as they come due

according to Part I, Table I. All aircraft will be subject to the recurring inspections set forth in

Part II, Table I commencing with the first compliance which includes the 3000 Hour inspection I

modification.

Part~ INSPECTIONS I MODIFICATIONS

i. All inspections modifications are MANDATORY and are set forth in Part I, TableI

2. If CRACKING or DAMAGE is found in the existing structure, and structure IS NOT REQUIRED TO BE

REPLACED WITH NEW PARTS, damaged parts must be replaced or an approved repair installed prior to

completion and return to service, except as noted per S8 214, Part I and indicated by FIGURES 21, 22 and

24 where limited cracking is allowed.

3. If CRACKING or DAMAGE is found in the existing structure, and structure IS’REQUIRED TO BE

REPLACED WITH NEW PARTS (Machined Frames, Intercostals, Angles, Clips; Fasteners, Etc.) the

modification is acceptable.

4. Twin Commander Aircraft Corporation requests that all damaged parts if any, be returned to TCAC

(Freight Postage Paid) to help us further our efforts to support the fleet for analysis.

Part II: RECURRING INSPECTIONS

There are four areas of the airc;aft depending on the model that require a recurring inspection at a specified time

interval. These areas will require a recurring inspection program, and are defined per Part II, Table I.

EXAMPLE: Aircraft has 3000 airframe Hours Time-in-Service. Full compliance with items 1700, 2500,

3000, 5000, 6000, and 7500 Hour Aircraft Inspection Time Periods per Part I, Table I was

accomplished at 1900 Hours. Compliance with Part II, Table I(Cabin Door, Figures 1 -1E

1000 Hour intervals) must be completed at this time, with the next inspection due at 4000 Hours

Time-in-Service and subsequently thereafter.

Page No. 2 of 72

/5


INFORMATION FORMS:

For further assistance, the following forms have been included in this Service Bulletin:

COMPLIANCE FORM This form will be used as a guide for determining which InspectionsModifications have been accomplished during the course of the Service Bulletinand allows the Mechanics and Inspectors to check off or initial each item as

they are completed. After the completion of the items required by the Service

Bulletin, a copy of the Compliance Form will be added to the aircraft logbookand a copy submitted to Twin Commander Aircraft Corporation.

TRACKING FORM This form will be used as an internal guide for receiving modification parts at the

repair station facility, installations, inspections and man hour estimates.

MATERIAL DISCREPANCY This form will be used for reporting deviations, damage and or corrective

FORM action required.


A P Mechanic (or Equivalent), and An ASNT Level II Certified NDT Inspector (or Equivalent) per INSPECTION

QUALIFICATIONS.

NOTE:

´•IT IS RECOMMENDED THAT ALL MODIFICATIONS BE COMPLETED ONLY AT AN AUTHORIZED

TWIN COMMANDER SERVICE CENTER. TCAC HIGHLY RECOMMENDS THAT AT LEAST ONE

MECHANIC, AND ONE QUALITY INSPECTOR RECEIVE TRAINING FOR IMPLEMENTING THIS

BULLETIN. THIS TRAINING IS AVAILABLE AT FLIGHT SAFETY INTERNATIONAL (FSI) IN

BETHANY OKLAHOMA.

APPROVAL:

Modifications and Repairs described by this Service Bulletin are FAA DER Approved.

RELATED PUBLICATIONS:

SE SERVICE BULLETIN TITLE AD AD TITLE

196 Fuel Leak Inspection Wing Compartment SealingBetween W.S. 103.00 8 113.00

209 Inspection and I or Replacement of the Nose Landing Gear

Axle

218 Em Vertical Stabilizer Modification 95-13-02 Vertical Stabilizer

223 Wing Leading Edge Attachment Inspection Modification 98-08-19 Inspect Wing to FuselageAttach Points for Cracks

224C R ent of the Nose Landi Gear Bolt 98-08-25 NLG Link Bolt

226 Fla S em Ins 98-07-17 Fla S em Cable

227 ´•1 Modification of Lower Main Gear Scissors

229 Inspection of Front Spar Lower Cap at Left and Right WingStation 39.00

Page No. 3 of 72


RELATED PUBLICATIONS: (cont.)

SL SERVICE LETTER TITLE

347 Replacement of Inner Structural Cabin Window Glass

349A Elevator Push-Pull Tube Assembly Inspection Replacement

350 1 Cockpit Insulation Overhead Switch Panel

352 Fuel Cell Interconnect Hose

353 Flight Control Chain Connector Link I

355 Fuselaae Station 386.82 Screw Torque

359 1 Fuselane Station 386.82 Frame Assembly Modification

ESTIMATED MAN HOURS:

Per Table II

PARTS DATA:

Kit parts required to comply with this Service Bulletin may be purchased through any of the nearest

TWIN COMMANDERFACTORY AUTHORIZED SERVICE CENTERS. Reference SE 214, aircraft model and

factory serial number when submitting order.

Supplied with the applicable modification kits:

TCAC DRAWING NO. 300004, 300005, 300006, 300007, and 300008 defining each modification

TCAC DOCUMENT NO. MP3-4, MP3-5, MP3-6, MP3-7, and MP3-8 detail each inspection modification

procedure sequence

TCAC PROCESS SPECIFICATIONS NO. 10.10, 30.6, 30.8, 260.1, and 260.8

May be required to be replaced, if damaged during compliance:

CABIN ENTRY DOOR PRESSURE SEAL (Part No. 90-935)

TO BE PROCURED LOCALLY: las required)

i. Polyurethane primer used for touch up on parts furnished with the Modification Kits. MIL-C-23377 per TCAC

Process Specification 30.8 or MIL-C-27725 TYPE II, CLASS A per TCAC Process Specification 30.6

2. Plexiglas Scrapers3. Fasteners required for specific modifications and I or re-installation of removed parts

CODE IDENTIFICATION DESCRIPTION

BE MS20426AD Countersunk Head Solid Rivet

BJ MS20470AD Head Solid Rivet

LZ NAS1097AD Countersunk Reduced Mead Solid Rivet

BF MS20427M Countersunk Head Monel Solid Rivet

LN MS20615M Head Monel Solid Rivet

SPECIAL TOOLS:

1. CherryMax fastener installation equipment2. GO-NO-GO gages for HI-LOK fastener inspection3. Expanded sheet metal tool kit for difficult access areas

Page No. 4 of 72

4


GENERAL INSPECTION CRITERIA:

TYPES OF INSPECTION FOUND IN THIS SERVICE BULLETIN PER AC 43.13-18 CHAPTER 5

"NONDESTRUCTIVE INSPECTION" (NDI).

OPerform close VISUAL structural inspection as an aid in disclosing crack indications, and or failed or

working fasteners along rivet lines, terminal fastener locations in splices, fittings or doublers and at any

changes in cross section. Also areas having curved members and areas having short fastener edgedistances. Carefully remove sealant as necessary in order to allow inspection of structural elements.

Perform FLORESCENT DYE PENETRANT structural inspection as an aid in disclosingcrackingindications or other failures not detectable by visual means. Carefully remove sealant and or finishes

as necessary in order to allow inspection of the structural elements. Moderate hand pressure appliedbetween parts, in order to produce any relative movement allowed, may assist in detection of failure of

parts or joining fasteners. Also obsen/e any rub marks indicating relative movement of parts under load.

Perform either VISUAL or FLORESCENT DYE PENETRANT inspections as indicated per each applicablefigure, Part I, Table I has been arranged by INSPECTION I MODIFICATION TIMES, with the items grouped to

four basic areas of the airframe for convenience of compliance.

Areas to be inspected are identified by Part Number and i or Name and are located per the applicableFIGURE(S) and or INSPECTION FIGURE LOCATOR diagrams located on pages 13, 19, 52. Removal of

Access Panels, Pilot I Passenger Seating, Carpeting, Interior Panels, Windows, Equipment, Fuel Cells and in

some cases the removal of Structural Elements may be required to gain adequate access to the structure of the

aircraft being inspected modified.

NOTE:

ILLUSTRATED PARTS CATALOG MAY BE USED FOR ASSISTANCE IN LOCATING INSPECTION

AREAS (REFERENCE ONLY)

INSPECTIONS APPLY TO LEFT AND RIGHT HAND SIDES OF THE AIRCRAFT UNLESS

OTHERWISE SPECIFIED BY THE APPLICABLE FIGURE(S)

INSPECTION REQUIREMENTS:

i. PERSONNEL QUALIFICATIONS

a. Level II Liquid Penetrant.

b. Vision acuity requirements of M11-STD-410E, or latest revision.

c. Documented training in accordance with MIL-STD410E, or latest revision and recommended practiceSNT-TC-1A of the American Society for Nondestructive Testing.

2. MATERIALSAND EQUIPMENT

a. Solvent Cleaner, SKC-NF (Magnaflux) or equivalent per MIL-I-25135.

b. Water Washable Fluorescent Penetrant, ZLGOC, Level II (Magnaflux) or equivalent per MIL-I-25135.

c. Non-Aqueous Developer, SKD-NF (Magnaflux) per MIL-I-25135 or equivalent.d. ZB-?OO Blacklight (Magnaflux), ?OOw, 115v, 60Hz or equivalent.e. Inspection mirror.

f. Cleaner, Penetrant and Developer to be from the same manufacturer.

3. PROCESS

a. Per MIL-STD-6866.

b. Sensitivity- Type I, Method C, Level 3.

Page No. 5 of 72


ACCOMPLISHMENT INSTRUCTIONS Partl INSPECTIONS I MODIFICATIONS

1. Refer to Part I, Table I, locate the applicable INSPECTION I MODIFICATION TIMES for the aircraft. Parr I,

TPble I defines the appropriate INSPECTION FIGURE(S) and or REQUIRED MODIFICATION DASH

NUMBER per TCAC DRAWING NO. 300004, 300005, 300006, 300007, 8 300008.


3. De-fuel airplane as outlined in the Airplane Maintenance Manual.

4. Support fuselage with wing jack stands and tail tie-down stand as outlined in Airplane Maintenance Manual.

5. Remove all interior i exterior components (Access Panels, Interior Panels, Cabin Windows and Equipment) as

required to gain access to the applicable areas of the aircraft.

6. Follow the inspection criteria specified by each FIGURE(S) to determine if any cracking or damage is present.Coordinate with the appropriate REQUIRED MODIFICATION DASH NUMBER to modify the inspected area(s).

7. For further assistance in regard to modification procedures, reference TCAC DOCUMENT NO. MP3-4, MP3-5,

MP3-6, MP3-7, and MP3-8. These procedures have been developed to aid in the inspections and or

installation of the modification parts and I or assemblies and have been arranged by REQUIRED

MODIFICATION DASH NUMBER.

NOTE:

IF CRACKING OR DAMAGE IS FOUND REFER TO ITEM #2 #3 IN COMPLIANCE SECTION.

8. Sealant and finishes must be restored per recommended Aircraft Maintenance Manual practices after

inspections modifications are completed.

NOTE:

FOR LOCAL TOUCH UP ON EXISTING STRUCTURE, CHROMATE PRIMER MAY BE USED.

DO NOT MIX CHROMATE AND POLYURETHANE PRIMERS ON THE SAME PART. ALL NEW

PARTS SUPPLIED FROM TCAC ARE ~OLYURETHANE PRIMED.

9. Perform operational check of cabin pressurization system for leaks per Aircraft Maintenance Manual practices.

10. Re-install items removed as noted per Item 5.

Page No. 6 of 72c~jr

PARTI SERVICE BULLETIN N0.~214INSPECTION /-MODIFICATION TIMES TABLE IMODEL 690D

1700 2500 1 3000 1 5000 1 6000 1 7500 AIC INSP. TIME PERIOD

AIC RND WING r FWD i PILOT I FWD AFT I PILOT FWD I AFT I PILOT FWD I AFT WING I PILOT FWD AFT WING AIC LOCATION BY TCACCABIN CABIN COMPT. CABIN CABIN COMPT. CABINI CABIN COMPT. CABIN CABIN COMPT. CABIN CABIN DRAWING NO.

SIN 300006 300008 300006 300005 300006 300007 300005 3000061 300007 300005 300006 300007 300008 300005 3000~6 300007 300008

j S: LnN cJ TI~INIC\I Ol~lr N C~ O N O 010 O S: jl O

m c3 o~lTlo cr, cr,Lno

,le---- REaD.MOD. DASH NO.

LO ~n in 1 Ln I In I In I ~n I u~l LO LnllOllnlro In Inllollollnllolln to Inllo to ~o IlolrollolYn to In I in rolln LnllnllnlLo in to rn Ln I LO NO CURRENTLY APPROVEDMODIFICATIONS AVAILABLE

15001 1 a d I LIA E E I C. F P P R S IW X Y Y Y Y via G Ii TIW V VI H O O V Z Y L a Z IIJK I- t~O O b c L~GENLI15002 1 O d LJA E E I C F P P R S IW X Y Y Y Y YIB G T TIW ‘J VI H O O V Z Y 2 a 2 ~IJ K n b c

15003 I d Ia L A E E I C F P P R S W X Y Y Y YIB G T TIW V VI H O O V 2 Y 2 a 2 ~IJ K n~ o b cl A=FIGURE(S) 1A. 1B. 1D81E

15004 1 I d IQ L A E E I C F P P R S W X Y Y Y IB G T TIW VI H a O V Z Y Z a 2 IIJ K ~3 b CI B=FIGURE1D

15005 1 1 d a LIA E E 1 C F P P R S W X Y Y Y IB G T TIW \I VI H O a V 2 Y 2 a 2 IIJ K ~3 b cl C=F’GURE1C

D=FIGURE1F15006 d I LIA E E 1 C F P P R S IW X Y Y Y IB G IT TIW V VI H O OiV Z Y 2 a Z ~IJ K b C

15007 1 I d I L A E E I C F P P R S W X Y Y Y IB G i TIW V VI H o o v z v z a Z ~IJ K Q ~1 ~I O b c

E FIGURE(S)Z g 2A

F FIGURE 2A

15008 1 I d I L A E E I C F P P R S IW X Y Y Y IB G T TIW ?I VI H O a V 2 Y Z a 2 IIJ K a ~3 ~3 b C

G FIGURE 3

15009 I d I L A E E I C F P P R S W X Y Y Y IB G IT TI-W :J VI H O O V 2 Y 2 a Z ~IJ K I Q~tlO O b c

H FIGURE 4

isoio I I d 1 LIA E E I C F P P R S IW X Y Y Y IB G T TIW V VI H O OIV 2 YI 2 a 7 ~IJ K a ~T3 b c

FIGURE 5

15011 1 d I L A E E I C FI- P P R S W X Y Y Y IB G T TIW V VI H O OIV 2 Y 2 a 2 IIJ K O b C

J FIGURE 6

15012 1 I d L A E E I C F P P R S W X Y Y Y IB G T TIW VI H O a V 2 YI Z a 2 ~IJ K a b c

K FIGURE 7

15013 1 I d I L A E E I C F P P R S W X Y Y Y (B G T TIW VI H O a V 2 Y Z a Z ~IJ K a O b cL FIGURE(S) 8. 8A. 8D 8 8E

15014 d L A E E I C F P P R S 1W X Y Y Y IB G T TIW \I VI H O OIV 2 Y Z a 7 ~IJ K 1~3 b cM FIGURE(S) 8. 8B, 8C 8 8E

15015 1 I d LIA E E I C F P P R S W X Y Y Y IB G T TIW VI H O a V 2 Y 2 a Z ~IJ K bN=FIGURE(S)S-9E

15016 1 I d L A E E i C FI P P R S IW X Y Y Y IB G T TIW V VI H O O V 2 Y 2 a Z ~IJ K b cO=FIGURE10

15017 d I LIA E E I C F P P R S W X Y Y Y IB G T TIW \I VI H O a V 2 Y Z a Z ~IJ K O b cP=FIGURE11

15018 1 I d I LIA E E I C F P P R S IW X Y Y Y IB G T TIW V VI H 10 O\V Z Y Z a 2 ~IJ K a b cQ=FIGURE12

15019 1 I d L A E E I C F P P R S IW X Y Y Y IB G T TIW V VI H O O V Z Y 2 a 2 ~IJ K I~7 b CI R=FIGURE13

15020 1 d I L A E E I C F P P R S W X Y Y Y IB G T TIW W VI H O O V Z Y 2 a Z ~IJ K Q b cl -s=FIGURE14

15021 1 I d L I A E E I C F P P R S IW X Y Y Y 18 G T TIW V VI H O O V Z Y Z a Z ~lj K b c I T FIGURE(S) 14 8 15A

15022 d I LIA E E 1 C F P P R S W X Y Y Y IB G IT TIW V VI H O a V Z Y 2 a 2 ~IJ K a 1f1 b c) U=FIGUREIS

15023 1 I d I L A E E I C F P P R S W X Y Y Y I IT TIW V VI H O O V 2 YI Z a 7 ~IJ K Q~O b cl V=FIGURE1G

15024 I d I L A E E 1 C F P P R S W X Y Y Y I IT TIW V VI H O O V 2 Y 2 a 2 ~IJ K QRO O b cl W=FIGURE17

15025 1 I d LI D E E C F P P R S W X Y Y Y I I IW V VI H O a V 2 Y 2 a Z ~LIJ K B Q IElO O b cl X=FIGURE18

15026 1 I d I L D E E C F P P R S IW X Y Y Y I I Iw v vl H lo OIV Z YI 2 a 2 ~IJ K B Q~ISZj If\ b CI Y=FIGUREIS

15027 1 I d I L D E E C F P P R S W X Y Y Y I I IW c VI H O a V 2 Y 2 a 2 ~IJ K 8 a O O b c I Z FIGURE 20

15028 1 I d I L D E E C F P P R S W X Y Y Y I I IW I’ VI H O O V Z Y Z a 2 ~IJ K B Q~O O b cl a=FIGURE(S)21821A

15029 1 I d D E E C F M P P Y Y I I IW V VI H O a V Y Z IJ K B a I~1 O O b c I b FIGURE 22

15030 I d 1 1 D E E C F M P P I v v I I I v vl H 10 O V Y I 2 IJ K B a O I~ O b c c FIGURE(S) 23 8 23A

15031 1 I d D E E C F M P P Y Y I I I L; VI H O O V Y Z IJ K B a O b c I d FIGURE 24

15032 1 I d D E E C F M P P Y Y I i I V VI H O O V Y Z IJ K B a O O b c I a FIGURE 25

15033 1 I d O E E C F M P P Y I I I L. VI H O O v Z IJ K B a O O b c I f FIGURE 26

15034 d I 1 o E E C F M P P v I I v vl H IO 01 YIZ IJ K BIQ ~j O O b cl I=\NSTAL~ MODIFICATIONAS REQUIRED

15035 1 I d D E E F P P Y I I I ~1 10 O YIZ IJ K B a ~O O b ciTR INSPECT PER APPLICABLE

15036 1 I d D E E F P P v I I I vl 10 a v 2 IJ KB Cfl b c FIGURE 8 MOD!P/ PER THEAPPLICABLE REQD. MOD.

15038 1 1 d D E E F P P I I I I V Y IZ IJ K B a I~ O O b I DASH NUMBER (-11-5XX)

15039 1 I d I I o E E F I I I I I vlz IJ K Bla 1 1 CI=FIRST INSPECTIONREQUIREOca, THE ABOVE TIME PERIOD.

15040 d I o E E F I I I I I ’J vl IJ K B a ~O REOCCURRING INSPECTIONSPER ~´•IRf II. I;lBIEI

Page No. 7 of 72

PARTI SERVICE BULLETIN NO. 214INSPECTION MODIFICATION IIMES TABLE co~MODEL 695A

1700 1 2500 1 3000 5000 1 6000 7500 AIC INSP. TIME PERIOD

:i AIC FYD WING I FWD I PILOT FWD I AFT I PILOT FWD AFf I PILOT R/VD I AFT WING I PILOT FWD AFT WING 1 AIC LOCATION BY TCACCABIN CABIN COMPT. CABIN CABIN COMPI. CABIN CABIN COMPT. CABIN CABIN COMPI. CABIN CABIN DRAWING NO.

SIN 300006 300008 300006 300005 300006 300007 300005 300006 300007 300005 300006 300007 300008 300005 300006 300007 300008

i o o (3) C3 10 O) LD a, In o, In o o,~cr, In t~ ~o (3 r? m In o, ,I~---- REQD.MOD. DASH NO.

In I In jun I Inlln mllnllnllnllnl~nl .I~nllo u, lolull~llnllnlm in LO G~IS: Inllo InlLn ~n S: O O O O O O O O 6 aN r*1 C\I O C~ CV I- O O O O O (U OIn in In In in to in to to In In u7 In to LO ~t NO CURRENTLY APPROVED

MODIFICATIONS AVAILABLE

960O1 1 d Q fA E E C F P P R S ´•I~IW X Y Y Y Y YIB G T TIW V Vf H O O V Z Y Z a Z ~IJ K ~I O b c

96002 1 d Q IA E E I C F P P R S OIW X Y Y Y Y YIB G T TIVJ V VI H O O V Z Y 2 a Z ~IJ K b C

96003 1 I d Q IA E E I C Fl P P R S NIIW X Y Y Y Y YIB G T TIW V VI H O O1V Z Y Z a Z ~(J K ~3 ~3 A FIGURE(S)1A. 1B, ID&1Ea b c

96004 1 I d Q IA E E I C F P P R S NIIW X Y Y Y Y YIB G IT TIVJ V VI H O O V Z Y Z a Z IIJ K b clB=F’GURE1D

96005 1 I d IQ A E E I C F P P R S NIIW X Y Y Y Y YIB G T T W V VI H O OrV Z YI 2 a 2 IIJ K ~OC=FIGURE1C

O b c

D=FIGURE1F96006 a IA E E C FI P P R S I)I~1W X Y Y Y Y vie G T i w v vl H to o v 2 v z a 2 ~IJ K I ITil~ ~3 b c

96007 1 I d Q IA E E C F P P R S ´•~IW X Y Y Y Y YIB G T TIVJ V VI H O O V Z Y Z a Z ~IJ K ~O O b cE=FIGURE(S)2g2A

F FIGURE 2A

96008 d I Q IA E E C F P P R S I) OIW X Y Y Y Y YIB G T TIVJ V VI H O O V Z Y 2 a 2 ~,IJ K ~3 ~3 [~3 b C

G FIGURE 3

96009 I I d I Q A E E I C F P P R S OIW X Y Y Y Y YIB G T T \rJ V VI H O O V Z Y 2 a 2 IIJ K ~3 Jb C

H FIGURE 4

96010 d I Q IA E E C F P P R S OIW X Y Y Y Y YIB G T T W V VI H 10 OIV 2 Y 2 a Z ~IJ K ~3 b c

FIGURE5

96911 I I d JQ A E E I C F P P R S ´•I~JW X Y Y Y Y YIS G T TIVJ V VI H O OIV 2 Y1 2 a 2 ~IJ K I~3 b c

J FIGURE 6

96012 d I Q IA E E C F P P R S OIW X Y Y Y Y Y1B G T TIW V VI H O O V 2 Y 2 a 2 ~IJ K b cK FIGURE 7

96013 1 I d Q IA E E C F P P R S OIW X Y Y Y Y Y(B G T TIW V VI H 10 O V Z Y 2 a Z ~IJ K b cL FIGURE(S) 8. 8A, 8D 8 8E

96014 j I d Q LIA E E C FI P P R S W X Y Y Y Y YIB G T T W V VI H O O V Z Y 2 a 2 IIJ K ~3 b CM FIGURE(S) 8. 8B, 8C 8 8E

96015 1 I d Q L IA E E C F P P R S W X Y Y Y Y YIB G T T W V VI H O O V 2 Y 2 a Z ~IJ K ~3 b c

N=FIGURE(S)S-SE

96016 d Q LIA E E 1 C F P P R S IW X Y Y Y Y YIS G IT TIVr! V VI H 10 O\V 2 Y\ 2 a 2 ~IJ K ~llul b cO=FIGURE10

96017 d IQ LIA E E C F P P R S IW X Y Y Y Y YIB G T TIVJ V VI H O O V 2 Y 2 a 2 ~IJ K ~3 b cP=FIGUREII

96018 1 I d Q IA E E C F P P R S O(W X Y Y Y Y YIB G T T W V VI H 10 O V Z YI Z a Z ~IJ K I~3 bO=FIGURE12

96019 d IQ LIA E E C F P P R S W X Y Y Y Y YIB G T T V VI H 10 O V Z Y Z a 2 ~IJ K L~ ~3 ~3 b clR=FIGURE13

96020 d IQ LIA E E C F P P R S W x v v v v vie G T TIVII V VI H O O V Z Y Z a Z ~IJ K b clS=FIGURE14

96021 1 8 Q L I A E E C FI P P R S W X Y Y Y Y YIB G IT TIW V VI H O O V Z YI Z a Z ~IJ K O b c I r FIGURE(S)14 8 1SA

96022 d IQ L IA E E C F P P R S W X Y Y Y Y YIB G T T V~ V VI H 10 O V 2 Y Z a Z ~IJ K O b clU=FIGUREIS

96023 1 I d Q L IA E E C F P P R S w x Y Y Y Y YIB G T T W V VI H O OIV 2 Y Z a 2 IIJ K b clV=FIGUREIG

96024 d 1 (3 L I A E E C F P P R S W X Y Y Y Y YIB G T T W V VI H O O V 2 Y Z a Z ~IJ K L~ O I~ b c IW FIGURE 17

96025 d IQ L IA E E C F P P R S W X Y Y Y Y YIB G T T W V VI H 10 O V Z Y Z a Z ~IJ K ~7 b clX=FIGURE18

96026 1 Q d I LIA E E C F P P R S W X Y Y Y Y YIB G T T W V VI H O O V 2 Y Z a Z ~IJ K O b c(y=FIGUREIS

96027 Q d I L I A E E C F P P R S W X Y Y Y Y YIB G T T V~ V VI H O O V 2 Y 2 a Z A(J K I O b c I 2 FIGURE 20

96028 Q d I L IA E E C F P P R S W X Y Y Y YIB G T T W V VI H 10 O V Z Y Z a 2 ~IJ K ~O O b c a=FIGURE(S)21821A

96029 d I Q L i A E E C F P P R S W X Y Y Y YIB G T T Vv V VI H O O V 2 Y Z a Z ~IJ K O b c I b FIGURE 22

96030 1 I d Q L I A E E C F P P R S W X Y Y Y IB G T T W V VI H O O V 2 Y Z a 2 ~IJ K b c I c FIGURE(S) 23 8 23A

96031 1 I d Q L I A E E C F P P R S W X Y Y Y IB G T T Me V VI H O O V Z Y Z a Z ~IJ K O O b c Id FIGURE 24

96032 1 I d I Q L A E E C F P P R S W X Y Y Y IS G T T W V VI H 10 O V Z Y Z a 2 ~IJ K O O b c I a FIGURE 25

96033 d I L I A E E C F P P R S W X Y Y Y IB G T T VV V VI H O O V 2 Y Z a 2 ~IJ K g O O b c I f FIGURE 26

96034 d I L I A E E C F P P R S W X Y Y Y IB G T T V~ V V I H O O V Z Y Z a Z IIJ K O b c I I INSTALL MODIFICATIONAS REQUIRED

96035 d I L IA E E C F P P R S W X Y Y Y IB G T T W V VI H 10 O V Z Y 2 a Z ~IJ K a~III1 ~3 b cINSTALL MODIFICATION.

96036 d I L IA E E I C F P P R S W X Y Y Y 18 G T T W V V I H IO O V Z Y Z a Z IIJ K Q ~il O b cNO INSPECTION REQUIRED

96037 I d I LIA E E I C F P P R S W X Y Y Y IB G T T WV VI H 10 O V Z Y 2 a Z 1~IJ K b cTR= INSPECT PERAPPLICABLE

FIGURE 8 MODIFY PER THE

96038 d I L IA E E C F P P R S W X Y Y Y IB G T T W V VI H 10 O V 2 Y Z a 2 ~1J K ~3 b cAPPLICABLE REQD. MOD.DASH NUMBER (-II -5XX)

96039 I d L I A E E C F P P R S W X Y Y Y IB G T T W V V i H I O O V Z Y Z a Z IIJ K Q O O b ~jO FIRST INSPECTIDN REQUIRED

96040 d I L IA E E C F P P R S W X Y Y Y IB G T T V\’ V VI H O O V Z Y z a Z ~IJ K I~ O b c ~ETHE ABOVE TIME PERIOD.OCCURRING INSPECTIONS

d I L I A E E C F P P R S W X Y Y Y IB G T T W V VI H O O V Z Y Z a Z IIJ K O I b c I PER P.JRTIL TABLEI

PARTI SERVICE BULLETIN NO. 214INSPECTION MODIFICATION TIMES

MODEL 695A TABLE I~1700 1 2500 1 3000 1 5000 1 6000 1

AIC FwD I WING RND I PILOT I RND AFT I PILOT I FWD AFT PILOT I FWD AFT WING PILOT FVVC AFT WING A/C LOCATION BYTCACCABIN CABIN COMPT. I CABIN CABIN COMPT. I CABIN CABIN COMPT. i CABIN CABIN COMPT. CABIN CABIN DRAWING NO.S/N 300006 300008 300006 300005 1 300006 300007 300005 1300006 300007 300005 1 300006 300007 300008 300005 300006 300007 300008

I m o (3) ~n I r3 0, cT)I1D I ~j r-lln I~ I o o c~lln a,ln ,If----- REQO.MOD.DASH NO.N

LD C: N N O N N O 10 1 O O 01010 O N l(r Oin ul ~llc: LII u, ul lo ~llo I ul lnIlnIln to Imlu, mim mllolvllu, ml~n in in ln I m NO CURRENTLY APPROVED’Ilnilni1niu3


96043 I d LIA E E I C Ff P P R S W X Y Y Y IB G 7 T WV VI H 10 a V Z Y Z a Z A(J K t a i~ 01 c

96044 d L A E E I C FI P P R S W X Y Y Y B G T T W V VI H lO O V Z Y 2 a Z ~IJ K IIi3 b c

96045 d I LIA E E I C FI P P R S W X Y Y Y 18 G T T W V VI H 10 O V 2 Y Z a 2 IIJ K .i~01 c/ A=FIGURE(S)1A. 1B, 1D81E

96046 1 I d L I A E E I C F/ ’P P R S W X Y Y Y IB G T TIW V VI H 10 O V Z Y Z a 2 ~IJ K a j~ O [I~ b c 1 B FIGURE 10

96047 1 I d L I A E E I C Fi P P R S W X Y Y Y lB G T T w v vl H lo O v z v 2 a Z ~IJ K a 1~3 O C FIGURE 1CIII b c

96048 i I d I LIA E E I C FJ P P R S W X Y Y Y IB G T TlW \I VI H 10 O V Z Y Z a Z ~IJ K ofZ11~3D=FIGURE1F

b c

96049 1 I d LIA E E I C FI P P R S W X Y Y Y IB G T TIW V VI H lO O V Z Y Z a Z ~IJ K a ~O b cj E=FIGURE(S)28 2A

F FIGURE 2A96050 1 I d LIA E E I C FI P P R S W X Y Y Y IB G T TIW V VI H lo O V Z Y Z a Z ~IJ K O b c

G FIGURE 396051 1 I d I L(A E E I C FI P P R S W X Y Y Y IB G T T W V VI H 10 OIV Z Y 2 a 2 ~IJ K a ~t10 n b c

H FIGURE 496052 1 I d LIA E E I C FI P P R S W X Y Y Y IB G T T W V VI H 10 O V 2 Y Z a 2 ~iJ K a O b c

FIGURE 596053 d I LIA E E I C F´•l P P R S W X Y Y Y iB G T T W V VI H 10 O V Z Y Z a 2 ~IJ K b c

J FIGURE 696054 d I LI E E I C FI P P R S W X Y Y Y I AIT T W V VI H 10 O V Z Y Z a Z ~IJ K a b c

K FIGURE 796055 1 I d L I E E I C FI P P R S W X Y Y Y I AIT T W V VI H 10 O V Z Y 2 a Z ~IJ K a ~3 b c

L FIGURE(S) 8, 8A, 8D 8 8E96056 1 I d I L I D E E C FI P P R S W X Y Y Y I I Iw v vl H lo OIV Z YI 2 a Z ~IJ K B a ~7 ~3 tll b c

M FIGURE(S) 8. 8B, 8C 8 8E

96057 I d I LI D E E C FI P P R S W X Y Y Y I I IW v vl H lo O V Z Y Z a Z ~IJ K B O (b c

N=FIGURE(S)S-9E96058 1 i d L I D E E C FI P P R S W X Y Y Y I I IW v vl H to O V Z Y 2 a Z ~IJ K B Q r~IO ~7 b c

O=FIGUREIO

96059 1 I d I I o E E C FIM P P v v I I Iw v vl H lo O V YI 2 IJ K B O b cP=FIGUREI1

96060 d I I D E E C FIM P P v v I Iw v vl H 10 O V Y 2 IJ K B b cQ=FIGURE12

96061 I I d I I D E E C FIM P P v v I I Iw v vl H 10 .O V Y 2 IJ K B a O b cR=FIGURE13

96062 d I I D E E C FIM P P v v I I I v vl H lO O V Y 2 IJ K B aOO O b cS=FIGURE14

96065 I I d I D E E C FIM P P v Y I I I v vl H lo O V Yi 2 IJ K B a IZC1 D O b c I T FIGURE(S)14 8 15A

96066 1 I d o E E C FIM P P v v I v vl H lo O V Y Z IJ K B a b c I U FIGURE 15

96067 1 I d I I o E E C FIM P P v I I I v vl H to O Y Z IJ K B Q~O b cl V=FIGUREIG

96068 d I I D E E C FIM P P v I I I v vl H lO O Y Z IJ K B Q I~O O b cl W=FIGURE17

96070 1 I d I D E E C FIM P P Y I I I v vl H lo O YIZ IJ K B a C~O O b cl X=FIGURE18

96071 d I I D E E C FIM P P v I I V V H 10 O Y Z IJ K B Q O~ O b cl y=FIGURE1S

96073 1 I d I D E E C F(M P P v I I v vl H lo O YIZ IJ K B Q If~ O b c 2 FIGURE 20

96074 d I I D E E C FIM P P v I I I v vl H lo O Y Z IJ K B Q O b c I a FIGURE(S)21 8 21A

96076 1 I d D E E FIM P P v I I I v vl H lO O Y IZ IJ K B Q I~ O O b c I b FIGURE 22

96077 d I I D E E F I P P Y I I I vl io O Y IZ IJ K B a b c I c FIGURE(S) 23 8 23A

96079 1 I d D E E F I P P v I 1 I v I to o Y IZ IJ K B a n o CSI b c I d FIGURE 24

96089 I I d D E E F I P P v I I I v I lo O v 2 IJ K B a O b c I a FIGURE 25

96081 I I d I I D E E F P P v 1 v I \O O v It IJ K B a O b c I f FIGURE 26

96082 I d D E E F I P P v I I I vl lo O y IZ IJ K B a O O b c I A INSTALL MODIFICATIONAS REQUIRED

96083 d i D E E F I P P I I I vl I I v 2 IJ K B a 1~ O O b cLTR INSPECT PER APPLICABLE

96084 d I I D E E F P P I I 1 vl I I v z IJ K B a O b c FIGURE 8 MODIFY PER THEAPPLICABLE REQD. MOD.

96086 I d I I o E E F I P P I I I I vl I I v 2 IJ K B Q D D b I DASH NUMBER (-11-5XX)

96087 d I I D E E F I P P I I 1 I v I I I v z IJ K B Q O O O b O FIRST INSPECTION REQUIREDB THE ABOVE TIME PERIOD.

96089 d I I D E E FI P P I I I I vl I I v z IJ K B(Q n b REOCCURRING INSPECTIONSPER P.JRTII. TrlBLE I

96090 d I I D E E FI P P I I I I v! I I v z IJ K B O 0096091 d I I D E E F I P P I I I I vl I I Y I IJ K B a [~j O O b

96092 d I I o E E FI I I I I vl I I v J K B a O

Page No. 9 of 72

PARTISERVICE BULLEIIN NO. 214

INSPECTION MODIFICATION TIMESMODEL 695A TABLE I co~r,

1700 1 2500 1 3000 5000 6000 i3 AIC FWD I WING FWD I PILOT FWD I AFT I PILOT FWD AFT PILOT FWD AFT WING PILOT NWD AFT WING 1´• AIC LOCATION BY TCACCABIN CABIN COMPT. CABIN CABIN COMPT. CABIN CABIN COMPT. CABIN CABIN COMPT. CABIPJ CABINS/N 300006 300008 300006 300005 300006 300007 300005 300006 300007 300005 300006 300007 300008 1 300005 300006 300007 300008

DRAWING NO.

I ct I lr I r-lmm re

N o o a n ,It-- REao. MOO. DASH ND.~-ln m In

oN CI 00 NN 00 a D N

1O _ _ _ in LO in YI Y1 in Lnln mlu~ NO CURRENTLY APPROVED

o N o o NIn In in Ln to LD LO ~n to In to to to In to to to to


96093 1 I d I D E E FI I I I r vl I I YI IJ K Bin96094 d D E E F vl i I Yl IJ K B Q

96995 r I d I I D E E F I I I I I vl I I Y J K B Q ~O I 1 A FIGURE(S)1A. 16. 1D81E

96096 d I I D E E FI I I i vl I I Y J K B Q I~O O I 1 B=FIGURE1D

96097 1 I d I I D E E F I I I I I v Yl iJ K B Q I I C FIGURE 1C

96098 1 I d I I O E E F I I I I i vl I I Yl IJ K B Q I I D FIGURE 1F

96999 I I 6 I I D E E FI I I I I vr I I Y J K BIQ I I E=FIGURE(S)28 2A

96100 1 I 6 I I D E E F I I I I I v Y I I B la 1I~ I IF FIGURE 2A

G FIGURE 3

H FIGURE 4

PARTI I I FIGURE 5

INSPECTION MODIFICATION TIMESJ FIGURE 6

MODEL 695BK FIGURE 7

1700 1 2500 1 3000 5000 1 6000 7500 L FIGURE(S) 8. 8A, 8D 8 8E

AIC FWD W’NG I FWD I PILOT FWD AFT I PILOT FWD AFT I PILOT FWD AFT WING PILOT FWD AFT WING 1 M FIGURE(S) 8. 88. 8C 8 8ECABIN CABIN COMPT. CABIN CABIN COMPT. CABIN CABIIJ COMPT. CABIN CABIN COMPT. CABIN CABIN

SIN 300006- 300008- 300006 300005- 300006- 300007- 300005- 300006- 300007-1300005- 300006- 300007- 300008- 1 300005- 30000r3- 300007- 300008- N=FIGURE(S)S-SE

O=FIGUREIOcr, I cr, IT I(nllOlPI r- 10 m

o o 8 (S,LnO N O O O hi (V O CV O (V 0 O O O ~1 o o P FIGURE 11

cu (u hi O O hito 10 in in in tn Ln to Ln in In In In to in In Ln to in ~o In In tn In in to to In to In to Lo un Ln In

in In In to in In In Ln to In-

Q=FIGURE1296063 d I I 1 I I I I I I I Lf_l I I. R=FIGURE1396069 d I I I I 1 I I I I I I I I no o I ~=FIGURE1496075 d I I I I I I I I I I 1 00 O I T=FIGURE(S)14B1SA96078 1 I d I I I I I I I 1 ~7 U FIGURE 15

96085 d I I I I I I I I I I I I n V=FIGUREIG

96204 d I I E FI I I I I vl I I v a O W=FIGURE17

96205 1 I d I I E F1 I I I I v YI I la O ~3 ~3 X=FIGURE18

96206 d I I E FI I I 1 I v YI I la Y=FIGUREIS

96207 1 1 d I I E FI I I I v Y I lo 1~3 2 FIGURE 20

96208 d I I I I I I I I 1 I I I I ~a o o a FIGURE(S) 218 21A

b FIGURE 22

FIGURE(S) 23 8 23A

d FIGURE 24

a FIGURE 25

f FIGURE 26

LTR INSPECT PER APPLICABLEFIGURE 8 MODIFY PER THEAPPLICABLE REQD. MOD.DASH NUMBER (-11-5XX)

(7 FIRST INSPECTION REQUIREDTHE ABOVE TIME PERIOD.

REOCCURRING INSPECTIONSPER P,IRTII, T~BLE I

Page No. 10 of 72


?114BL~ IIMAN HOUR ESTIMATES

COLUMN 2 (INSPECT1ON)TIME REQUIRED FOR GAINING ACCESS, INSPECTION 8 RE-INSTALLATION OF REMOVED PARTS

COLUMN 4 (MODIFICATION)TIME REQUIRED FOR INSTALLATION OF M001FICATION PARTS

PILOT’S COM PARTM ENT

TCAC DRAWING 300005

INSPECTION ESTIMATED MAN MODIFICATION ESTIMATED MAN

FIOURE(S) HOURS (INSP.) DASH NO. HOURS (MOD.)

6 10.0 HR -i 4.0 HR

7 12.0 HR ´•501 4.0 HR

4 4.0 HR -503 42.0 HR

1A, 18, iD 8 if 48.0 HR 505 66.0 HR

if i.O HR 507 1.0 HR

1D ´•1.0 HR 509 1.0 HR

iD 25.0 HR -511 18.0 HR

2 8 2A 60.0 HR 513 24.0 HR

282A 1.0 HR -515 2.0 HR

3 8.0 HR 517 5.0 HR

5 6.0 HR -519 20.0 HR

1C 8.0 HR 521 2.0 HR

1A, is, 1D 8 if 26.0 HR .523 18.0 HR

2A ´•1.0 HR 525 3.0 HR

FORWARD CABIN

TCAC DRAWING 300006


FIGURE(S) HOURS (INSP.) DASH NO. HOURS (MOO.)

8, 8B, 8C 8 88 3.0 HR -i 1.0 HR

10 15.0 HR ´•501 32.0 HR

´•10 2.0 HR -503 2.0 HR

11 8.0 HR -507 2.0 HR

ii 20.0 HR -509 60.0 HR

13 6.0 HR 14.0 HR

14 1.0 HR -513 1.0 HR

14 <1.0 HR -515 6.0 HR

14 8 15A 134.0 HR -517 60.0 HR

12 2.0 HR -519 2.0 HR

12 iZ.O HR -521 16.0 HR

12 iZ.O HR -523 i 4.0 HR

12 12.0 HR -525 16.0 HR

NIA 15.0 HR -527 8.0 HR

8, 8A, ED 8 8E i 2.0 HR ´•529 20.0 HR

9 98 10.0 HR NIA NIA

15 40.0 HR NIA NIA

25 8.0 HR NIA NIA

Page No. ?1 of f2


TABLE IlconrMAN HOUR ESTIMATES

COLUMN 2 (INSPECTION)TIME REQUIRED FOR GAINING ACCESS, INSPECTION 8 RE-INSTALLATION OF REMOVED PARTS

COLUMN 4 (MODIFICAflON)TIME REQUIRED FOR INSTALLATION OF MODIFICATION PARTS

AFT CABIN

TCACbRAWING 3(r0007


FIOURE(S) HOURS (INSP.) DASH NO. HOURS (MOD.)

16 <1.0 HR -1 2.0 HR

20 16.0 HR 501 24.0HR

17 <1.0 HR 503 4.0 HR

18 2.0 HR 505 5.0 HR

17 8;0 HR 607 6.0 HR

19 80.0 HR 609 2.0 HR

19 60.0 HR 511 34.0 HR

19 ~1.0 HR 513 8.0 HR

19 8.0 HR 518 2.0 HR

16 <1.0 HR 617 1.0 HR

19 8.0 HR 521 2.0 HR

19 8.0 HR 523 4.0 HR

18 8.0 HR 525 6.0 HR

26 16.0 HR NIA NIA

WING

TCAC DRAWING 300008


FIGUR#S) HOURS (INSP.) DASH NO. HOURS (YOD.)

20 4.0 HR -1 4.0 HR

20 8.0 HR 501 16.0 HR

21 8 21A 60.0 HR 503 32.0 HR

20 i 2.0 HR 505 3.0 HR

22 12.0 HR 507 24.0 HR

23 8 23A 16.0 HR -509 24.0 HR

NIA ~1.0 HR -511 16.0 HR

24 32.0 HR ´•513 32.0 HR

Page No. 12 of 72

SERVICE BULLETIN NQ. 214

Part I

INSPECTION

FIGURE #IB zzPOF~BL´•

FIGURE #~D

l~Z."Ooo, I\ II o

O o

oO oo

b.´•~e

´•0O

FIGURE #IA "a~Lb r FIGURE #IEi I 1 L 8 RM S1DE

i 1 JFIGURE#IC-’ I

1 111

:0’’’I, I

(I 1

IiiI,,y II

FIGURE #~F

L.B.L. 6.05

FIGUREFORWARD PRESSURE BUL~KHEAD

MODELS 690D, 695A 6958

INSPECTION FIGURE LOCATOR

VIEW LOOKING AFT F.S. 5.50

Page No. 13 of 72


Part I

INSPECTION

REFERENCE

TCAC DRAWING #300005505 8 -523 ASSY FOR MODIFICATIONS

TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES

R.B.L.310933-33 CAP 6.05(REF.)

lea~lNSPECT FOR CRACKS U(TENDINGFPI IABOVE 8 BELOW THE INBD END

OF THE 310933-29 STIFFENER IN THE

310933-11 WEB

NOTE:REMOVE THE 310933-29 STIFFENER

310933-11 WEB TO GAIN ACCESS TO THE 310933-11 WEB II(REF.) FOR INSPECTION PURPOSES

310933-29 STIFFENER

(REF, I+II

W.L. -48.00

rtJ--

/II/f

‘INSPECT FOR CRACKS ALONG EDGEIFPI OF 310933-29 STIFFENER IN THE

310933-11 WEB FROM R.B.L. 6.05 TO THE

OUTBOARD TERMINATING END OF PART.

INSPECT FROM THE FORWARD SIDE OF

THE PRESSURE BULKHEAD (F.S. 5.50)

IIINSPECT FOR MISSING MATERIAL

(FPI., CRACKS ON THE 310933-29

STIFFENER UP

OUTEDcj-DETAIL

INBD END OF 310933-29

STIFFENER

FIGURE #1A QVIEW LOOKING AFT THE RIGHT HAND

FORWARD PRESSURE BULKHEAD (F.S. 5.50)

Page No. 14 of 72


Pari~

INSPECTION

REFERENCE



I II 1 INSPECT RIVETS ALONG UPPER EDGEI V 10F THE 310933-11 WEB FOR LOOSE OR

SHEARED CONDITIONS FROM W.L. -40.00TO THE AIRCRAFT CENTERLINE

‘INSPECT FOR CRACKS EXTENDING~FPIooWNWARDs FROM THE UPPER OUTED a THE 310933-55 STIFFENERCORNER OF THE 310933-57 DOUBLER

TO GAIN ACCESS TO THE 310933-11WEB FOR INSPECTION PURPOSES

f 1 111 1 /-310933-55 STIFFENER

O (REF.)

f’

O +I

f( Ical INSPECT FOR CRACKS ALONG THEx FPI JVERTICAL EDGEOFTHE 310933-55

O +i!JV STIFFENER ANO 31033557 OOUBLER.

INSPECT FROM THE FORWARD SIDE

OF THE PRESSURE BULKHEAD

310933-57DOUBLER II+ O (F.S. 5.50)

(REF.)

O310933-11 WEB t

(REF.)UP

O310933-21 CAP

O O..~M-I

(REF.) +I

-r

PJ i +I

W.L. -40.00

1 INSPECT FOR CRACKS EXTENDINGFPI i UPWARDS FROM THE LOWER OUTED R.B.L. 12.00

CORNER OF THE 310933-57 DOUBLER

NGURE #?BVIEW LOOKING AFT THE UPPER RIGHT HAND


Page No. 15 of 72


Part I

INSPECTION

REFERENCETCAC DRAWING #300005-521 ASSY FOR MODIFICATIONS

TCAC DOCUMENT #MP3-5 FOR MO01F1CAT10N PROCEDURES

I IIIINSPECT RIVETS COMMON TO THEV 1310944-33 CLIP FOR LOOSE OR

SHEARED CONDITIONS L.B.L.INSPECT FROM THE AFT SIDE OF THE 6.OSPRESSURE BULKHEAD (F.S. 5.50) 310933-21 CAP

(REF.)

3- t t t t tt: i

------I--W.L. 40.00=-r-------------

I~

,,~r--W.L. -41.20310944-33 CLIP

(REF.) I -C II

=c’(

,-7

-511_,==-’~I t

c=-------,310933-15 FRAME

I+ (REF.)

310933-9 WEB

(REF.) +I

310933-13 DOOR

(REF.)

FIGURE CVIEW LOOKING FORWARD THE LEFT MAND


eage No. 16 of 72


Pari I

INSPECTION

REFERENCE

TCAC DRAWING #300005-505, -509, -511 8 -523 ASSY FOR MODIFICATIONS


NOTE: INSPECT RIVETS ALONG UPPER EDGE

OF THE 310933-9 WEB FOR LOOSE ORREMOVE THE 310933-23 BEAM AND

310933-27 STIFFENER TO GAIN ACCESS SHEARED CONDITIONS FROM W.L. -40.00

TO THE 310933-9 WEB FOR INSPECTION TO AIRCRAFT CENTERLINE

PURPOSES ~7 INSPECT FOR CRACKS ALONG THECIL 310933-9 WEB FP

310933-23 BEAM ~\1+ SVERTICAL EDGE OF THE 310933-27

(REE)7 INSPECT FROM THE FORWARD SIDE

STIFFENER.

OF THE PRESSURE BULKHEAD

(F.S. 5.50)(REF.) f It 3-

+I310933-27

STIFFENER

(REF)

+IR~I

+i;\ il!+

\II´•++I’+ +I

)+I+i! I+ ~I I I!+

.;u I,

r+

´•Iti´•, 7 UP

-tlli-/tt-\+ +i f f fW.L. -40.00

U

~INSPECT RIVETS COMMON TO LOWERL.B.Li6.a5 \--310433-21CAP CB.L 12.00

U (REF.)I 1ENDOFTHE310933-23 BEAMFOR

LOOSE OR SHEARED CONDITIONS

INSPECT FOR CRACKS AROUND THE RINGleal INSPECT FOR CRACKS ALONG THE

I i OUTFLOW VALVE DOUBLER RINGS.IFPJVE,T,CAL EDGE OF THE 310933-23REMOVE DOUBLER RING TO INSPECT

BEAM ON THE 310933-9 WEB.


OF-THE PRESSURE BULKHEAD (F.S. 5.50)

FIGURE #?DVIEW LOOKING AFT THE UPPER LEFT HAND


Page No. 17 of 72


PartlINSPECTION

REFERENCE


TCAC DOCUMENT #MP3-5 FOR MODIFICATION P~ROCEDURES

310933-3 FRAME NOTE:(REF) REMOVE THE AFT CORNER GUSSET

310933-11 WEB TO GAIN ACCESS TO THE CORNER

(REF)-;r RELIEF CUT-OUT

310933-21 CAP

(REF.)

iT’;-T--+----+-----t’;~CORNER GUSSET

LOCATED ON AFT SIDE

OF FWD PRESSURE

BULKHD(REF)WL. -40.00----

UP

I INSPECT FOR CRACKS AROUND THE INBOARDFPI J END OF THE ANGLE RELIEF CUT-OUT IN THE

310933-11 WEB.INSPECT FROM THE AFT SIDE OF THE

PRESSURE BULKHEAD (F.S. 5.50)

FIGURE #?EVIEW LOOKING FORWARD THE LEFT HAND


REFERENCE

TCAC DRAWING #300005-507 ASSY FOR MODIFICATIONS


L.B.L.

6.05310933-13 DOOR 310933-9 WEB NOTE:

(REF.)----\ (REF.)~ DO NOT REMOVE THE 310933-35

310933-31-\ STIFFENER F~PECTIONCAP (REF.

$-II

W.L. -55.50-

C f I c

I 11 1 INSPECT RIVETS ALONG 310933-35

310933-35 STIFFENER

L.~..tlIcl B

I! jfj I

(REF.)U JSTIFFENER AND GENERAL AREA FOR INSPECT FOR CRACKS ALONG THE UPPER

LOOSE OR SHEARED CONDITIONS IF PI LOWER EDGE OF THE 310933-35 STIFFENER

IN THE 310933-9 WEB.


OF THE PRESSURE BULKHEAD (F.S. 5.50)

NGURE #1F gVIEW LOOKINGAFT THE LOWER LEFT HAND


Page No. 18 of 72

B


Part IINSPECTION

FIGURE #~7FIGURE #~6FIGURE #~4

;´•n FIGURE#23AFIGURE

#20FIGURE #~OFIGURE #2 FIGURE #5-

FIGURE #~5A

Page #24 7 /r

Page #20 Page #38 Page #42 Page #51 Page #41 Page #48

FIGURE #2A R/H Side Only 4 UH Side 8 4 R/H Side

(8 Total Locations) F.S- FIGURE #~9 FIGURE #26Page #21 FIGURE #15A

7 Page #57164.82

W.L. Page #46 Page #46 Page #50 Page #60

+2.001111 11 I

IW.L. ~I

0.00W.L. j Ij-10.00

FIGURE #4Page #23

W.L.

-28.00

W.L.

-40.00

W.L.

11\ 111\1111111 1 1111 1 1 11) 111~ 11,

W.L.

12.50 37.00 52.67 69. 87.00i

108.00 126.00 144.00163.50 178.715 198.00F.S. F.S. F.S. F.S.

65.00

iF.S. F.S. F.S. F.S. F.S. F.S. F.S.

217.14 230.00

F.S. F.S.

F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S.

5.50 23.50 45.34 60.50 78.00 96.50 99.00 117.00 135.00 155 54 172.50 188.00 209.24 223.98

FIGURE #6 FIGURE #3 FIGURE #12 FIGURE FIGURE #25 FIGURE #~8

Page #25 Page #22 Page #40 Page #39 Page #59 Page #49

UH Side Only I UH Side 6 10 NH Side

FIGURE #7 (17 TotalLocati~ns)FIGURE #25

Page #25Page #59

R/H Side Only

FUSELAGE STATION DIAGRAM

MODELS 690D, 695A 695B

INSPECTION FIGURE LOCATOR

Page No. l9 of 72


Part

INSPECTION

REFERENCE

TCAC DRAWING #300005-513 8 -515 ASSY FOR MODIFICATIONS


NOTE:

PARTIAL REMOVAL OF THE 31~928-31 INNER INSPECT ALL RIVETS COMMON TO THEFRAME DOUBLER IS REQUIRED TO GAIN ACCESS 310928-31 INNER FRAME DOUBLER FORFOR INSPECTION PURPOSES LOOSE OR SHEARED CONDITIONS

INSPECT

5.00 INCH

Q310928-31 INNER FRAME

DOUBLER (REF)

COCKPIT OVERHEAD 61~x

xWINDOW (REF.)31089913 EYEBROW

NOTE:FRAME (REF.)

REMOVE THE 310883-1 INTERCOSTAL

i:W.L. -10.00) TO GAIN ACCESS FOR

INSPECTION PURPOSES

:Bx~--LEFT HANDCOCKPIT

310883-1 INTERCOSTAL

(REF)WINDSHIEtD(REF.)

+´•´•´•´•´•~f-W.L. -lo.ooz’

I\ UP

FS.

48.00WINDOW(REF.)

ZI´•~.\ X;

AFTCOCKPIT SIDE

a~s´•s(~P)INSPECT FOR CRACKS IN THE 310883- O

´•INTERCOSTAL(~W.L. -10.00) INNER/OUTER

FLANGE, RADIUS AND WEB FROMF.S. 40.00 TO 48.00. INSPECT PART AFTER

IT HAS BEEN REMOVED FROM THE AIRCRAFT

)C

(FpllNSPECT FOR CRACKS IN THE 310898-501

´•CANTEDWINDSHIELD FRAME INNERIOUTER

FLANGE, RADIUS AND WEB 5.00 INCHES ABOVEW.L. -10.00 TO 5.00 INCHES ABOVE W.L. -28.00.

INSPECT FROM THE AFT SIDE OF THE FRAMES, I L 310898-501 CANTEDTHROUGH THE WINDOW OPENINGS IN THE SKIN FRAME (REF.)

FS. 40.00

FIGURE #2VIEW LOOKING UP, FORWARD AND OUTBOARD

THE UPPER LEFT HAND CANTED WINDSHIELD

FRAME INTERSECTION AREA (F.S. 40.00)

RIGHT HAND SIDE OPPOSITE

Page No. 20 of 72


PartINSPECTION

REFERENCE



310899-13 EYEBROW

FRAME (REF.)FP INSPECT FOR CRACKS IN THE 31089413

EYEBROW FRAME INNER i OUTER FLANGE,RADIUS AND WEB FROM THE OUTBOARD

END W.L. -10.00 EXTENDING 5.00 INCHES

‘f‘ INBOARD INTO THE FRAME. GAIN ACCESSAND INSPECT FROM THE FORWARD SIDE

X

X

NOTE:

REMOVE THE 310776-71 CLIP TOGAIN ACCESS FOR INSPECTIONPURPOSES

310776-71 CLIP

O (REF)INSPECT

5.00 INCHES _(7 PRIOR TO REMOVAL OF THE 31077871 CLIP

44V/-CLJ INSPECT ALL FASTENERS COMMON TO THE

310716-71 CLIP FOR LOOSE OR SHEAREDCONDITIONS

/C" FP INSPECT FOR CRACKS IN THE 310898-501CANTED WINDSHIELD FRAME INNER I OUTER

FLANGE, RADIUS AND WEB 5.0 INCHES ABOVEW.L. -10.00 TO 5.00 INCHES ABOVE W.L. -28.00.

INSPECT FROM FORWARD OR AFT SIDE OF

o310898-501 CANTED

~O’ FRAME(REF)

O

310883-1 INTERCOSTAL

(REF.)

FIGURE #2AVIEW LOOKING UP, AFT AND OUTBOARD

THE UPPER LEFT HAND CANTED WINDSHIELD bFRAME INTERSE%TION AREA (40.00)


Page No. 21 of 72


Parl~lINSPECTION

REFERENCE



NOTE:REMOVAL OF THE AILERON DRUM

PULLN MAY BE REQUIRED TO GAIN IINSPECTALLRIVETS COMMONTOTHE

ADEQUATE ACCESS TO THE LOWER AIRCRAFTV 1530466-1 BRACKET ASSY BETWEEN

BRACKET STRUCTURE

7 CIL F.S. 23.50 AND F.S. 37.00 FOR LOOSE

OR SHEARED CONDITIONS

F.S. 23.50

IfFWD

´•B’~ 530169-9 AILERON

fI’’fII, DRUM (REF.)

I´•’II I-1~- 530465-1 CHANNEL

I1_I‘\(REF.)

P

litIIIt II I I

Ih

I´•-fB r‘--------c\(l

530466-1 BRACKETk’ASSY (REF.)

‘J --1

I\f-]l, ,Lt~:I I

u II I LOWER FUSELAGEI II SKIN (REF.)IfO I’ I

zI_ F.S. 37.00

F/GURE #3VIEW LOOKING UP FUSELAGE LOWER SKIN

AILERON DRUM BRACKET STRUCTURE

Page Noi 22 of 72


Part IINSPECTION

REFERENCE



INSPECT RIVETS COMMON TO THE FRAMEI U IATTACHMENT SMEAR CLIP F.S. 23.50 8 W.L. -28.00

FOR LOOSE OR SHEARED CONDITIONS

O O

W.L. -28.00

j jI

Ije ji

UP

nnro

INSPECT FOR CRACKS IN THE INTERCOSTAL(F Pi W.L. -28.00 IN THE INBOARD RETURN FLANGE

AND WEB 1.00 INCH FORE I AFT OF F.S. 23.50F.S.

FRAME WEB23.50

FIGURE #4VIEW LOOKING OUTBOARD AFT THE LEFT HAND

W.L. -28.00 INTERCOSTAL@ F.S. 23.50 FRAME INTERSECTION


Page No. 23 of 72

q


PartlINSPECTION

REFERENCE



III INSPECT ALL RIVETS AROUND THE PERIMETERI Y JOF THE PILOTS WINDOW SIDE SKIN FOR LOOSE OR

SHEARED CONDITIONS COMMON TO:

INTERCOSTAL W.L. -10.00, F.S. 40.00 THRU 60.50INTERCOSTAL W,L. -28.00, F.S. 37.00 THRU 60.50

F.S. 60.50 FRAME W.L. -10.00 THRU W.L. -28.00WINDOW CANTED FRAME W.L. -10.00 THRU W.L. -28.00

a

310832-11 SKIN F.S. 40.00 F.S. 60.50

(REF.)

a tO O O 9 O

~0+W.L. -10.00

310832-47 SKIN Z

(REF.)---,a 310832-13 SKIN

a(REF.)

"´•r 8/UP e~

O

Fwo

Ot

90 a

ai’

16

+81 lo

+Z te C+

a

W.L. -28.00

F.S. 37.00

310832-7 SKIN INSPECT FOR CRACKS IN THE OUTER SKIN AROUND 8

(REF) BETWEEN FASTENER HEADS 8 COUNTERSUNK SCREW

HEAD HOLES AROUND THE PERIMETER OF THE PILOTS

WINDOW COMMON TO:

INTERCOSTAL W.L. -la.oo, ES. 40.00 THRU 60.50

INTERCOSTAL W.L. -28.00, ES. 37.00 THRU 60.50

F.S. 60.50 FRAME W.L. -10.00 THRU W.L. -28.00

WINDOW CANTED FRAME W.L. -10.00 THRU W.L. -28.00

F/GURE #5VIEW LOOKING INBOARD THE LEFT HAND

PILOTS WINDOW AND SURROUNDING SKIN

RIGHT HAND GO-PILOTS SIDE OPPOSITE

Page No. 24 of 72


Pa~rlINSPECTION

REFERENCE



FS.10.09 /-310772-71 SUPPORT310772-11 ANGLE

(REF.)7 IJ (REF.)310785-501 DOUBLER

(REF.)NOTE:

+++++\1+c!W.L. -55.50

REMOVAL OF THE NOSE

GEAR WHEEL WELL DOORS

WILL PROVIDE BETTER

\h ’------I ACCESS INTO fHE AREA

It~

310817-503 WEB

(REF.) INSPECT FOR CRACKS UNDER THEIFPI,,,,,,_,, SUPPORT ANGLE IN THE

f310817-503 WEB. INSPECT FROM

INSIDE WHEEL WELL AREA310772-5TEE P(REF.)

UP

FWD-4FIGURE #6

VIEW LOOKING INBOARD THE LOWER

LEFT HAND FORWARD KEEL BEAM AREA


REFERENCE



rFplREMOVE THE 320025-15 FLOOR WEB AND

´•INSPECT THE HORIZONTAL ROW OF FASTENERHOLES FOR CRACKS. IN ADDITION, INSPECT

310924-3 WEB THE 310924-3 WEB FOR CRACKS AROUND THE

(REF.) WISTING NUT-PLATES (6 PLACES)

t´•

f

W.L.-55.50UP

f C/L

320025-15 FLOOR WEB

(REF.)

FIGURE #7 BVIEW LOOKING FORWARD THE LOWER CENTERLINE FLOOR

WEB AREA, AFT SIDE OF NOSE GEAR WHEEL WELL BOX (F.S. 13.00)

Page Mo. 25 of 72


PartlINSPECTION

FIGURE #8B F.S. B1.10 F.S. !4.45 FIGURE #8B

i \e i c i i i i i i i

c i I C I o Ii i i i i ii o k I i

I VU/

FIGURE#BDi FIGURE#BC 1

+b~iOJ30Q0010

!-E´•l I~_i I! 9:1+O/ \e

I/:I D--W.L. -15.05´•cXO

+I~ O \o I+f I u,l++I:´•

+I(+I I PI o io

Clcl I rl ol I, I+t I Ic’l++I I I fl I UP I~ Ifi’ I r 1+

3 e.FwDclO ;4 B+f

o a+I% .I i iJ+J FIGURE #8D

cl~´• "FI

ii ‘1 ~rl O o

II"1 D--W.L. -26.60d JJoaaJJo~

i

O Oa

+I:i O a I~a a

ses

81+O

CI~ i II I Ic5/ I 11 18

Cli~l mi I+ I II I 1,i O a CI FIGURE #8Da a

ii I

tl% i t.l iii

Oi a II+:I D-W.L. -37.57

t

c+Ce

i a6

+Ile +:I+i

O 3CE+

fl: I I I I a I I I ;I+i

sl U r ~LL IC

+t i I r a It I+I I 1 L I 1+3~

ii; I I ci

i +:IC

FIGURE #8A i

’I FIGURE #8DeE+

it

CIF% IL i iiiIll :L~r

W.L. -48.90+I’ I e

el I 12I \I i

II

tBs:BI ,9~1L

;~s´•, ;e)l 1+

3r i t

FIGURE #8VIEW LOOKING OUTBOARD EFFECTIVITY (Ref. FIG.

MOOEL SIN

THE MAIN CABIN ENTRY DOOR ssoo 15001 THRU 15034

695A 96014 THRV 96017

695A 96019THRU 96076330407 FAIL SAFE DOOR EXCEPT SIN 96063.

CONFIGURATION SHOWN 1 1960698 96075

Page No. 28 of 72


Pa~i IINSPECTION

REFERENCE



CA UTION: 330410-1 ANGLE

USEOCTREMECAREWHEN REMOVINGTHEOUTERI_

DOOR FRAME WEB (REF)

DOOR SEAL, IF ANY RUBBER NIPPLES ARE DAMAGED (REF.OR TORN OFF DURING DISASSEMBLY,THE SEAL MUST BEREPLACEOi II o

lcj

orr I iIiO~ ii"I i I ~----;II (D II

OOOO BiO,!i

O i

rFp’INsPECT FOR CRACKS IN THE DOOR FRAME WEB I 330432-509STRAP

I ~AND OUTER FIANGERADIUSAROUND THE j j (REF.)BAYONET GUIDE BLOCK 4.00 INCHES ABOVE AND O 330421-505 PLATE3.00 INCHES BELOW W.L. -48.90 FROM THE AFT

SIDEONLYI (REF.)

INSPECT 4.00

O OINCHES ABOVE

01(O IIOj

WL. -48.90-- II)(O

O

INSPECT 3.00 co II~INCHES BELOW O

i ´•ilr ´•~B,I. Ilh(0’

BAYONET GUIDEBLOCK ~REF.)

OUTER DOORSKIN (REF.)

NGURE #8AVIEW LOOKING OUTBOARD FORWARD

THE W.L. -48.90 AFT DOOR BAYONET

(BAYONE~PIN OMlTTED FROM I/I~WFOR CLARITY)MODEC SIN I b690D 15001THRU15028

330407 FAIL SAFE:DOOR ONLY 695A 96014THRU 96017

AFT BAYONET PIN @W.L.-48.90 ONLY 1695A 96019THRU 96058

Page No. 27 of 72


Part I

INSPECTION

REFERENCE



CAUTION: ’F P1’NSPECT FOR CRACKS ORIGINATING FROM THE

OR TORN OFF DURING DISASS~MBLY, DIAMETER FROM THE CENTER OF THE HOLE

USE WTREME CARE WHEN REMOVING THE OUTER ~J8AYONET PIN HOLE AND GUIDE BLOCK

DOOR SEAL, IF ANY RUBBER NIPPLES ARE DAMAGED ATTACHMENT FASTENERS 1.50 INCHES IN

THE SEAL MUST BE REPLACED IN THE OUTER DOOR FRAME WEB

’9 OO DOOR FRAME

,INSPECTRIVETS COMMONIOTHEVERTICAL \s WEB (REF)V d

I JWINDOW CHANNEL UPPER END, SMEAR CLIPS OAND BAYONET GUIDE BLOCK FOR LOOSE OR OSHEARED CONDITIONS----------~ o ~--A´•, o

o’0- .0‘1 O

8 O

//B0/

o:O

ieo

0\O

I’ oc~ ~P

VERTICAL WINDOW

OUTER DOOR CHANNEL (REF.)

SKIN (REF.)

FIGURE #88VIEW LOOKING OUTBOARD DOWN THE

UPPER AFT CORNER OF THE CABIN DOOR(BAYONET PIN OMI’ITED FROM VIEW FOR CLARIT~ I EFFECTIVITY

MOOEL SIN

6900 15029THRU 15034

330407 FAIL SAFE DOOR ONLY 695A 96059 THRU 9607_6AFT UPPER PIN F.S. 91.10 SHOWN 1 D(CEPT SIN 96063,

FORWARD UPPER PIN F.S. 74.45 TYPICAL I I 98069 8 96075

Page No. 28 of 72

q


Parr IINSPECTION

REFERENCE



r P1INSPECT FOR CRACKS IN THE BEAM UPPER FLANGEIT ~F’1RADIUS 3.00 INCHES FORWARD FROM THE AFT

IITERMINATING END OF THE PART AND THE AFT

NOTE: VERTICAL RETURN FLANGE RADIUS OF THE BEAM

IT WILL BE NECESSARY TO REMOVE

THE BAYONET GUIDE BLOCK TO INSPECTTHE UPPER DOOR BEAM RAOIUS O

DOOR FRAME

61wee (REF)

O \Oa I´•~-\\

a

UPPER AFT BAYONETGUIDE BLOCK (REF.)

I i,,,,,,,,BEAM (REF)

OUTER DOOR

FS. 91.781

\NCHES

SKIN (REF.)

(NSPECT?OL)

VERTICAL WINDOW

CHANNEL (REF)

NGURL3 #8CVIEW LOOKING OUTBOARD UP THE

UPPER AFT CORNER OF THE CABIN 0OOR(BAYONET PIN a LINKAGE OMITTED FROM VIEW FOR CLARIP~

330407 FAIL SAFE DOOR ONLY r EFFECTIVIT(

AFT UPPER PIN F.S. 91.10 SHOWN s/N

FORWARD UPPER PIN F.S. 74.45 TYPICAL 6900 15029THRU 15034 ;B695A 96059THRU 96076

EXCEPT S/N 96063,

ICOOROINATE WITH INSPECTION FIGURE #8B) I I 96069 a 96075

Page No, 29 of 72


Part I

INSPECTION

REFERENCE



IF PJ’NSPECT FOR CRACKS IN THE OUTER DOOR

DOOR FRAME /II’ 1 FRAME PLATE DOUBLER AROUND THE BAYONET

GUIDE BLOCK 1.00 INCH ABOVE I BELOW THEUPPER I LOWER ENDS OF THE PLATE DOUBLER

WEB (REF) CAUTION:

O use EXTREME CARE WHEN REMOVING THE OUTER

IDOOR SEAL, IF ANY RUBBER NIPPLES ARE DAMAGED

OR TORN OFF DURING DISASSEMBLY.i 2, THE SEAL MUST BE REPLACED

O \I rNsPECT 1.00j INCH

O ilis

INNER DOOR STRAP

O

O

i O W.L. -26.60

DOUBLER (REF.) ‘OO

~-IFPI ’NSPECT FOR CRACKS IN DOOR

;/8 ~U FRAME RADIUS ALONG THE

OUTBOARD EDGE OF PLATE

DOUBLER

O ’O

O OINSPECT 1.00

fj INCH BE~OW

’1YiOUTED O I--I 7--\1 I

O

‘s~OUTER DOOR FRAME --J

DO NOT REMOVE THE OUTER DOOR FRAME PLATEPLATE DOUBLER (REF.) DOUBLER OR BAYONET GUIDE BLOCK (UNLESS

SPECIFIED 8Y THE MODIFICATION DRAWINGS) FORINSPECTION PURPOSES, ONLY INSPECT ON 8 TO

THE EXISTING EDGE OF PART

FIGURE #80VIEW LOOKING OUTBOARD AFT THE

W.L. -26.60 FORWARD DOOR BAYONET DOUBLER

(BAYONET PIN OMITTED FROM VIEW FOR CLARIP~

330407 FAIL SAFE DOOR ONLY I EFFECTIV!~FORWARD BAYONET P1N W.L. -15.05 TYPICAL I MOOECI S/N

FORWARD BAYONET PIN W.L. -26.60 SHOWN 690D 15001 THRU 15028

FORWARD BAYONET PIN W.L. -37.57 TYPICAL 695A 96014 THRU 96017

FORWARDBAYONETPIN ~W.L. -48.90NPICAL i 695A ~196019 THRU 96058

Page No. 30 of 72


Prrrt I

INSPECTION

REFERENCE

TCAC DRAWING #300006-1 a -529 ASSY FOR MODIFICATIONS


\INSPECT RIVETS COMMON TO THE OUTER INSPECT RIVETS COMMON TO THE OUTERI V 1 SKIN AND VERTICAL WINDOW CHANNELS U i SKIN AND DOOR FRAME AROUND THE

ON THE FORWARD I AFT SIDE OF THE DOOR I PERIMETER OF THE DOOR FOR LOOSE.OR

FOR LOOSE OR SHEARED CONDITIONS I SHEARED CONDITIONS

F.S. I F.S:

74(451

91110

ii%i ii:5i

´•I:~+:W.L. -15.05-

’I:Zcl

i/E:

:;xl16i

i:f: i´•c´•l

i3:. iiW.L. -26.60- g:

~’,.’..+..=.+.t.t.t.?.t.t.t=..+..+.t,t.t,t.:;:

IiW.L. -37.57- I;iI,:I~

f:i~c

i +i

f~:i :C

iiW.L.i18.90-- ij f~f.

tl: lil i E,:I ii,

FIGURE #8E TIVINMODEL SIN

VIEW LOOK1NGINBOARDI@ 6900 15001THRU 15034

THE CABIN DOOR OUTER SKIN 695A 96014 THRU 96017 d695A 96019THRU 96~EXCEPTSIN 96063.

330407 FAIL SAFE DOOR ONLY I I 96069 a 96075

Page No. 31 :of 72

\d


Partl

INSPECTION

FIGURE #9B ES´• 91.10 F.S. !4.45 FIGURE #9B

s t i c c i

f i i o f t i C f +Ionl+

1

IYLY\

FIGURE #9D cEcl I r FIGURE #9C ---J 1 I, FIGURE #9D

ossoo;:ooC~e

ia o

´•LI ´•f I I II+ W.L. -15.OSii II fl L+I

c/ ii o 3 I

ii I 1 o io

ii I I ol I^ r I Ic:lf

+li I I I UP I~ II I :ICfl:

o

c18 a a++i

FIGURE#SD o 1

FIGURE#SD+IQ

a i

o 9I I I~e

cC I~ I I %VI II+

cll sl O oa (I iLD-- W.L. -26.60

ooooiDioo+1C

o oO

9% i

g O $L~+ +c~++l 00~1o:I+

i 8~ I II I8 a

i I r I 1~ 01++

’1’13 I i I I 1+1+i

i c:l+

FIGURE #9DFIGURE #9D i O O

i I I I I I~C

+CQ to aAL:l´•+E I~ h, LI r II ~I+

O W.L.-37.57b c

f i I ~Y, 1+

o~ co

FIGURE #9A Ic ia~ e aCC+I -ri I :I r I I+il+

+I Y I I+:I++I I lil I ´•li

i i

on II no’+I\ I II+ I I Ilt

+I\ I I\ ´•I II I

FIGURE #9D ~J\ f B II’ ol I ilfl FIGURE #9Df O

+:lfC L I ;I I i

fF-l\+:i PILI F’ i +;I+´•--c--, I

r iiii I I+II D-W.L. -48.90

II ii i

+;I iii \I+

ii Ii

’LII I I Ic~+i i

i

W/s.l+

c~. i t i s s c -s s L ~rL

FIGURE~ #9VIEW LOOKING OUTBOARD

THE MAIN CABIN ENTRY DOOR

EFFECTIVITYMOOEL SIN

330247 1 330430 DOOR 1695A 196001 THRU 96013

CONFIGURATION SHOWN 1695A 96018

Page No. 32 of 72


Part I

INSPECTION

I IINSPECT FOR CRACKS ORIGINATING FROM THE

ZEE CHANNEL7 TFP1’’11.00 INCH DIAMETER PUSH ROD HOLE IN

THE ZEE CHANNEL WEB W.L. -48.13

INSPECT FROM THE UPPER SIDE ONLY

(REF.) INTERCOSTAL a

(REF.) 6.

""""’"’7/-"\/

e

a

YC~

i8

r’ AFT

~II O

oo g o o

O9\\0 0 ---W.L. -48.13

INNER DOOR STRAPo

INNER PLATEDOOR FRAME

\r INNER STRAP

DOUBLER (REF.)

(REF.)(REF.) NOTE:(REF.)

DO NOT REMOVE ANY RIVET MOUNTED

DOOR PARTS FOR INSPECTION PURPOSES

FIGURE #9AVIEW LOOKING OUTBOARD DOWN THE

LOWER AFT CORNER OF THE CABIN DOOR(PLISH ROD LINKA GE OMITTED FROM VIEW FOR CLARIP~ I EFFECTIVITY

MODEL SIN

695A 96001 THRU 96013

330247 1 330430 DOOR ONLY 1695A )96018

Page No. 33 of 72


Part~INSPECTION

CAUTION: I IINSPECT FOR CRACKS ORIGINATING FROM THE

OR TORN OFF DURING DISASSEMBLY, $gfP DIAMETER FROM THE CENTER OF THE HOLE

USE EXTREME CARE WHEN REMOVING THE OUTER BAYONET PIN HOLE AND GUIDE BLOCK

DOOR SEAL, IF ANY RUBBER NIPPLES ARE DAMAGED ATTACHMENT FASTENERS 1.50 INCHES IN

THESEL\L MUST BE REPLACED IN THE OUTER DOOR FRAME WEB

O DOORFRAME

(7 INSPECT RIVETS COMMON TO THE VERTICAL \O WEB (REF.)V a

I IWINDOW CHANNEL UPPER END, SMEAR CLIPS OAND BAYONET GUIDE BLOCK FOR LOOSE OR OSHEARED CONDITIONS

o

,;s~8 o.O\I O

0// OO0,/

O

O i,oo\lo

1 042i U,P

VERTICAL WINDOW

OUTER DOOR \j CHANNEL (REF.)

SKIN (REF.)

FIGURE #9BVIEW LOOKING OUTBOARD DOWN THE

UPPER AFT CORNER OF THE CABIN DOOR(BAYONET PIN OMITTED FROM VIEW FOR CLARIPI)

FECTIVITY330247 1 330430 DOOR ONLY MOOEilSIN

AFT UPPER PIN F.S. 91.10 SHOWN 695A 96001 THRU 96013

FORWARD UPPER PIN F.S. 74.45 TYPICAL 1695A (96018

Page Na, 34 of 72


Part IINSPECTION

CAUTION:

NOTE: EXERCISE EXTREME CARE WHEN REMOVING THESE

IT WILL BE NECESSARY TO REMOVE FASTENERS NOT TO ENLARGE OR ELONGATE EXISTING

THE BAYONET GUIDE BLOCK TO INSPECT HOLES IN THE DOOR FRAME OR BAYONET GUIDE BLOCK

THE UPPER DOOR BEAM RADIUS

FOR REINSTALLING THE GUIDE BLOCK TO THE

DOOR FRAME WEB, IT IS ACCEPTABLE TO I IINSPECT fOR CRACKS IN THE BEAM UPPER FLANGE

SAME SIZE AS REMOVED aFp VERTICAL RETURN FLANGE RADIUS OF THE BEAM

SUBSTITUTE HI-LOK FASTENERS FOR THE RADIUS 3.00 INCHES FORWARD FROM THE AFT

FACTORY INSTALLED STEEL LOCKBOLTS (4 PLACES) TERMINATING END OF THE PART AND THE AFT

HUOPB6 PIN d HL86-5 COLLARO DOOR FRAMEHOLE LIMITS (.1625~1.1600)

O ol \O WEB (REF.)

0\~c--- e~

Q

IUPPER AFT BAYONETGUIDE BLOCK(REF.)

3 BEAM (REF.)

OUTER DOOR

F.S. 91.78f

\NCHES

SKIN (REF.)

I

VERTICAL WINDOW

CHANNEL (REF.)

FIGU~E #9CVIEW LOOKING OUTBOARD UP THE

UPPER AFT CORNER OF THE CABIN DOOR(BAYONET PIN LINKAGE OMITTED FROM VIEW FOR CL9R17Y)

220247/ 330430 DOOR ONLYAFT UPPER PIN F.S. 91.10 SHOWN

FORWARD UPPER PIN F.S. 74.45 TYPICALMODEL SIN I

695A 96001THRU96013

(COORDINATE WITH INSPECTION FIGURE #98) 695A 96018

Page No. 35 of 72


Part I

INSPECTION

(~p) INSPECT FOR CRACKS IN THE OUTER ~DOOR

DOORFRAME

I’ 1 FRAME PLATE DOUBLER AROUND THE BAYONETGUIDE BLOCK 1.00 INCH ABOVE I BELOW THE

UPPER I LOWER ENDS OF THE PLATE DOUBLER

WEB (REF.) ~-CAUTION:USE EXTREME CARE WHEN REMOVING THE

O OUTER DOOR SEAL, IF ANY RUBBER NIPPLESI6 ARE DAMAGED OR TORN OFF DURING

I~ DISASSEMBLY,.Jr THE SEAL MUST BE REPLACEDAl

O ~I

INSpECT1~00I INCH A,BOVE

OO

i o

OilO -w.L.-26.aa

INNER DOOR STRAP

DOUBLER (REF)II O

OFP

INSPECT FOR CRACKS IN DOOR

FRAME RADIUS ALONG THEOUTBOARD EDGE OF PLATE

~dl DOUBLER

O lo

I’-O

o

\NCH BEL´•OW;i" (NSPECT 1.00

.~so Oat

OUTER DOOR FRAME DO NOT REMOVE THE OUTER DOOR FRAME PLATEPLATE DOUBLER (REF.) DOUBLER OR BAYONET GUIDE BLOCK FOR

INSPECTION PURPOSES, ONLY INSPECT ON 8 TOTHE EXISTING EDGE OF PART

FIGURE #9DVIEW LOOKING OUTBOARD AFT THE

W.L. -26.60 FORWARD DOOR BAYONET DOUBLER

(BAYONET PIN OMITTED FROM VIEW FOR CLARIP~

3330247 1 330430 DOOR ONLYFORWARD 8 AFT BAYONET PIN ~2 W:L. -15.05 TYPICAL I EFFECTIVITYFORWARD 8 AFT BAYONETPIN W.L. -26.60 SHOWN MODEL I SIN

FORWARD 8 AFT BAYONET PIN W.L. -37.57 TYPICAL 1695A 96001 THRU 96013

FORWARD 8 AFT BAYONET PIN W.L. -48.90 TYPICAL 1695A 96018

Page No. 36 of 72

,7


PartlINSPECTION

r 1 INSPECT RIVETS COMMON TO THE OVTER I 1 INSPECT RIVETS COMMON TO THE OUTERV ~U1 SKIN AND DOOR FRAME AROUND THEI V JSKIN AND VERTICAL WINDOW CHANNELSON THE FORWARD I AFT SIDE OF THE DOOR I\ PERIMETER OF THE DOOR FOR LOOSE ORFOR LOOSE OR SHEARED CONDITIONS I SHEARED CONDITIONS

F.S. I F.S.

74145_

1 \91110i’

i:i~ r:S

r+

:i+i++c+.!t

Bi :a

:5:f I Tc:

,II:

W.L. -26.60i´•l

t

i

r:"’""’-Tci~i i*ii:i j=ji=i i:

:ia

ii i’

II

W.L. -48.90--

3-(iiil------------------------------------------------------------’i+i’

ir’iii

F/GURE #9EVIEW LOOKING INBOARD

THE CABIN DOOR OUTER SKIN I EFFECTIVINMOOELISIN

695A 96001THRU96013

330247 1 330430 DOOR ONLY 695A 96018

Page No. 37 of 72


Part~INSPECTION

REFERENCE



F.S. 96.50FS. 99.00 310841-501 FRAME

ASSY (REF.)

310774-503 FRAME II+I IflllfASSY (REF.) --7 Ilr~tf;t;rh ---W.L.-14.00

’F P’ PARZ B fl Ifili+´•INSPECT FOR CRACKS ON THE OUTER I+iliFLANGE 8 WEB OF THE 330382-17 GUSSET +ili+FOR CRACKS EXTENDING ACROSS THE ft +Il:-tFS. 96.50 8 99.00 FRAMES X+j +’rNOTE: .II r?-P7PARTATHIS INSPECTION IS ONLY REQUIRED IF I +ili iii ~eINsPECT FOR CRACKS ON THE OUTER

CRACKS ARE FOUND IN THE 96.50 OR jj+j FLANGE 8 WEB OF THE FS. 96.50 8 99.00

99.00 FRAMES PER PARTA lilt: iii FRAMES 8 FRAME ANGLE DOUBLER FROMI+ -t W.L. -14.00 TO W.L. -45.00

111 330382-21 INNER GUSSETfr

330382-17 OUTER GUSSET +i I+ill (REF.)LOWER AFT (REF.) 310780-2 INTERCOSTAL

+I ,~I+1 (REF.)330382-71 LOWERCHANNEL (REF.) W.L. -28.00

f__f~e

~++´•--+-li+j j+:I:+I-tl

I I iti~iiil i1t: I~li+ili NOTE:

REMOVE W.L. -10.00 8 -28.00 INTERCOSTALS

OUTER AIRCRAFT Ifll AFT OF F.S. 99.00 FRAME, 99.00 FRAME SECTION

SKIN(REF.) ~I I AND ANGLE DOUBLER. DETACH AT THE

EXISTING FRAME SPLICE LOCATIONS TO

GAIN ACCESS FOR INSPECTION PURPOSES

fll!i I

t:ll

W.L. -45.00UP

FWD-1- I

FIGURE #~OVIEW LOOKING OUTBOARD THE R/H

F.S. 95.50 99.00 FUSELAGE FRAMES

RIGHT HAND SIDE ONLY

Page No. 38 of 72

Iq


Part I

INSPECTION

REFERENCE

TCAC DRAWING #300006-507 8 -509 ASSY FOR MODIFICATIONSTCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES

W.L. -48.9

NOTE:IT WILL BE NECESSARY TO DRILL BACK

THE 310928-45 INNER FRAME STRAP ItTO GAIN ACCESS TO THE INNER FLANGE -tOF THE FRAME

I’ I

I 1INSPECT FOR CRACKS IN THE LOWER FRAME j:FPII1’’12.00 INCHES ABOVE I OUTED AND 2.00 INCHES

BELOW I INBD ON THE INNER FRAME FLANGE, I i!RADIUS AND WEB ;--ii

-3´•~1

iW.L. -54.45

MAY VARY IN DESIGN PER \,I

’9" W.L. -55.50

I ~I )INSPECT FOR CRACKS ORIGINATING AT

FOR LOOSE OR SHEARED CONDITIONS ill\ I~ W.L. -57.75

I V IFASTENER HOLES IN THE FRAME WEB

COMMON TO SUPPORTS, BRACKETS

AND LINE BLOCKS

I310773-503 FRAME

’REF.’

i+

f Up

INBDi7 R.B.L. 22.57

R.B.L. 19.38

1 INSPECT FOR CRACKS IN FRAME WEBFP1 11.00 INCH DIAMETERAROUND UPPER

END OF STRINGER CUTOUT

FIGUREVIEW LOOKING ATT THE LOWER LEFT HAND

F.S. 96.50 FUSELAGE FRAME SECTION

TYPICAL ON THE UH F.S. 96.50 99.00 FRAMES ONLY

Page No. 39 of 72

2/0


Part IINSPECTION

REFERENCE

TCAC DRAWING 4300006-519, -521, -523 8 -525 ASSY FOR MODIFICATIONS


W.L. -45.001PARTB’FPI IINSPECT FOR CRACKS IN THE FRAME W.L. -49.00

t´•;WHERE THE INNER FRAME DOUBLERS-~ND 1.00 INCHABOVE AND ~.00 INCH BELOW IN THE INNER FRAME

FLANGE, RADIUS AND WEB

PA~PrB r ’ooNOTE: (PART B, ONLY)IT WILL BE NECESSARY TO DRILL BACK THE 31092853

-WL4900f

THE INNER FLANGE OF THE FRAME

(FPI INSPECT FOR CRACKS IN THE LOWER FRAME fI-jleal PART A

BELOW THE FLOORLINE 2.00 INCHES ABOVEI.,,,,\I

AROUND THE OUTBOARD LIGHTENING HOLE

AND z.ao INCHES BELOW I INBO ALONG THE INNER~ r FLOOR BRACKETFRAME FLANGE, RADIUS AND WEB

t(REF.)

----W.L. -55.50

lul INSPECT FOR CRACKS ORIGINATING AT-tr~7 INSPECT PER PARTA 8 B EFFECTIVITY

FOR LOOSE OR SHEARED CONDITIONS,d~FASTENER HOLES IN THE FRAME WEB

COMMON TO SUPPORTS, BRACKETS, oOLINE BLOCKS kND DOUBLERS i_

I I

OUTED LIGHTENINGii

HOLE (REF.)I

I\j/

i\II I\L

II I

c ii’l i -t UPf s

~____’I~Lf i

NOTE:DEPENDING ON THE MODEL BEING INSPECTED,THE INNER FRAME DOUBLERS MAY VARY ASSHOWN. IT MAY BE NECESSARY TO DRILL OFF

Ir al INSPECT PER PART A 8 B EFFECTIVIN

L.B.L. 22.57AND REMOVE THE DOUBLERS ON THE FORWARDSIDE OF THE FRAME TO GAIN ACCESS FOR

INSPECTION PURPOSES

FPIINSPECTFORCRACKS IN FRAMEWEB1.00 INCH DIAMETER AROUND UPPEREND OF STRINGER CUTOUT

A-INSPECTIONUODEL SIN

690D 15001THRU 15032

6954 96001THRU 96067

EXCEPT S/N 96063

PART B INSPECTION

FIGURE #12 MOOEL ISIN

690D 15033THRU 15040VIEW LOOKING AFT THE LOWER LEFT HAND 8954 96068THRU 96100

FUSELAGE STATION 69.00 FRAME SECTION 16958 196204 THRU 96208

EXCEPT SIN 96069,

96075, 96078, 96085

RIGHT HAND SIDE OPPOSITE 1 18 96208

Page No, 40 of 72

-21


Part I

INSPECTION

REFERENCE



rFpl’NSPECT FOR CRACKS ALONG THEIWELD PANASSEMBLY INNER RADIUSAROUND THE PERIMETER OF THE

DOOR FRAME

330109-109 FRAME 330109-109 FRAME

(REF.) Ih, (REF.)

-I IINSPECT FOR CRACKS ALONGFPI ITHEWELDPANASSEMBLY

INNER RADIUS AROUND THE

PERIMETER OF THE DOORFRAME CHANNEL

(REF.)NOTE: /IREMOVE THE FORE I AFT INNER

33010913 PANS TO GAIN ACCESS (j~lNSPECT FOR CRACKS ALONGFOR INSPECTION PURPOSES L’ 1THE VERTICAL WINDOW STIFFENING

CHANNELS ALONG THE OUTBOARD

RADIUS OF THE PART

33010913 PAN

SECTION A-A (REF.) SECTIONB~B

i7 INSPECT FOR CRACKS ON THE WELD ASSEMBLY PAN,FPI JRADIUS BETWEEN INNER FVANGEAND WEB.

WINDOW VERTICAL STIFFENING CHANNELS,RADIUS BETWEEN OUTBOARD FLANGE AND WEB

INSPECT BOTH FORE IAFT SIDES OF THE EMERGENCY FS. 96.50F.S. 69.00U(IT HATCH AS INDICATED

W.L. -10.00 I--

I I I I a

I I

O IIiC;iOjl

Al II\A

i j

UP OI

OR~VD1 Q j/l /I i 0,jj jj i

W.L. -28.00

FIGURE#~3 jVIEW LOOKING OUTBOARD THE

EMERGENCY EXIT ESCAPE HATCH

Page No. 41 of 72

Y


PartlINSPECTION

RE~ERENCETCAC DRAWING #300006-513, -515 -517 ASSY FOR MODIFICATIONS


117.00fll:f

INSPECTINSPECT

FS.

310928~5 GUSSET

(REF.) i+

310928-3 GUSSET ~iil+ LOOKING DOWN~REF.) +si\+

iI+i+:II Irsl PART BOUTER AIRCRAFT

j+I’ ’JFP INSPECT FOR CRACKS ON THE OUTERSIDE SKIN (REF.)

FLANGE 8 WEB OF THE FRAME AND FRAME

ICE SHIELD (REF.)k

OUTER AIRCRAFT I i ]li ANGLE DOUBLER 7.00 INCHES ABOVE AND

5.00 INCHES BELOW W.L. -28.00

r U ’PAR’ BI 1 I NOTE

COMMON TO THE OUTER ICE%/iJ7.a0REMOVE THE CABIN WINDOWSI V 1 INSPECT THE FIRST RIVET ABOVE

W.L. -28.00 F.S. 117.00 8 126.00 j Ii TO PREVENT ACCIDENTAL DAMAGE

.----~---´•111’- IDURING INSPECTION I MODIFICATION

SHIELD ON THE RIGHT HAND SIDE PROCEDURES

ONLY FOR LOOSE OR SHEAREDCONDITIONS

W.L. -28.00++f+ft- fi

NOrr~ (PnRTB. ONLY) II I

PVRPOSES I+fi]i II)

REMOVE THE LOWER WINDOW I +’IIINTERCOSTAL W.L. -28.00 ANO ATTACHING

5.00

SMEAR CLIPS FORE I AFT OF THE FRAME i"’ I_jTO GAIN ACCESS FOR INSPECTION

ifj ii

NOTE: (PARTB, ONLY3 ’iIiREMOVE THE VIBRATION DAMPER ASSY +ililAND ATTACHING STRUCTURE AS REQUIRED

REMOVE THE 310928-3 8 3109285GUSSETSff+ I;jltf I

TO GAIN ACCESS FOR INSPECTION PURPOSES

NOTE: (PARTS, ONLY)

TO GAIN ACCESS FOR INSPECTION PURPOSES. i jlij:DO NOT REMOVE FASTENERS UNTIL THEY HAVE j +ilj/S.BEEN VISUALLY INSPECTED FOR LOOSE OR

SHEARED CONDITIONS IIf

COMMON TO IHE FUSELAGE--/\~I I~il/ ´•eFWDIll1PARTAI V )INSPECT RIVETS

INNER FRAME FLANGE AND THE 310928-3 -5

INNER FRAME GUSSETS FOR LOOSE OR

SHEARED CONDITIONS

FIGURE #~4VIEW LOOKING OUTBOARD THE UH

PART INSPECTIONF.S. 117.00 FRAME, FRAME ANGLE INNER MODEL I S/N

FRAME GUSSET DOUBLER’S 690D 15001 THRU 15028

NPICAL F.S. 126.00, 144.00 155.54 1695A 196001 THRU 96058

FUSELAGE FRAMES I PAR~gS-MODEL SIN

6900 15001THRU 15024

RIGHT HAND SIDE OPPOSITE 1695A (96001 THRU 96055

Page No. 42 of 72

23


PerilINSPECTION

FIGURE ~5 GENERAL SKIN INSPECTION CRITERIA

P/PICAL SIGNS OF WORKING FASTENERS INCLUDE:

CHIPPED OR CRACKED PAINT AROUND FASTENER HEADS

BLACK OXIDE OR (SMOKING) USUALLY TRAILING THE FASTENER HEAD 1F EXPOSED TO THE

AIRSTREAM

WHITE CRYSTALLINE DEPOSITS MAY FORM AROUND WORKING FASTENERS FROM WATER BEING

TRAPPED

iO I~jn-7

i ~L´•I

LL~CRACKED RIVETHEAD AROUND SHEARED OR MISSING BLACK OXIDE OR SMOKING TIPPED RIVET HEAD

CIRCUMFERENCE OF SHANK RIVETHEAD OR BU77 AROUND RIVET HEAD

NOTE:

ANY SIGNS OF WORKING FASTENERS SHOULD BE IDENTIFIED AND NOTED PRIOR TO

STRIPPING AIRCRAFT PAINT FINISH TO DETERMINE AREAS OF POSSIBLE INTERNAL DAMAGE

TYPICAL SKIN LAP CROSS SECTION

INSPECT FOR CRACKS IN THE OUTER~SKIN LAP AREA AROUND OR BETWEEN n INSPECT SKIN RIVET LINES COMMON TO

FASTENER HOLES FOR CRACKS

7 ?rI V i INTERNAL STRUCTURE FOR CRACKED,TIPPED, SMOKING, WORKING OR SHEARED

CONDITIONS

FRAME, ANGLE OR

STRINGER (REF.)

SHEARED OR MISSING --r II CRACKED SKIN BETWEEN

RIVET HEAD OR BUTT II RIVET HEADS

Page No. 43 of 72


PartlINSPECTION

FIGURE 15 GENERAL SKIN INSPECTION CRITERIA (cont.)

NOTE:

BEFORE PROCEEDING WITH THE LNSPECTION ITEMS IDENTIFIED PER FIGURE 15, THE

EXTERIOR SKIN IN THE PRESSURE VESSEL AREA SHOULD BE CHEMICALLY STRIPPED OF

PAINT, NO MECHANICAL MEANS MAY BE USED.

INSPECT THE FOLLOWING AREAS PER FIGURE 15: (see next pagel

1. FUSELAGE SKIN LAP W.L. -10.00 -14.00, F.S. 40.00 THRU 178.715

2. FUSELAGE SKIN LAP W.L. -28.00, F.S. 5.50 THRU 209.24



5. FUSELAGE SKIN F.S. 172.50 178.715 FRAMES FROM, W.L. -15.00 TO -28.00

6. FUSELAGE LOWER BELLY SKINS F.S. 78.00 THROUGH 163.00, ALONG FR4ME RIVET LINES

FROM THE LEFT TO RIGHT HAND KEEL BEAM CAP ANGLE INTERSECTION

7. FUSELAGE UPPER SKIN F.S. 155.54 ALONG FRAME RIVET LINE FROM AIRCRAFT CENTERLINE

U(TENDING OUTBOARD TO THE LEFT AND RIGHT HAND WING FAIRINGS

NOTE:IF ANY DAMAGED FASTENERS ARE FOUND DURING COMPLIANCE WITH FIGURE 15 ITEMS

O.NE THRU SEVEN, REPLACE WITH THE SAME TYPE AND SIZE FASTENER AS REMOVED. IT IS

ACCEPTABLE TO INCREASE THE FASTENER BY ONE SIZE IF ALLOWABLE PITCH AND EDGE

DISTANCE CRITERIA CAN BE MAINTAINED.

Page No. 44 of 72


Part IINSPECTION

FIGURE~5,1TEM2Left Hand Side

Cb

FIGURE 15 ITEM 4 ,oLeft Right Hand Sides 4´•28’

FIGURE 15 ITEM 6

GB’

FIGURE 15 ITEM 7

FIGURE 15 ITEM 1Left g Right Hand Sides

FIGURE 15 ITEM 5r

FIGURE 15 ITEM2iLeft Right Hand Sides

Right Hand Side

URE 15 ITEM 3Left g Right Hand Sides

FIGURE #153 DIMENSIONAL EXTERIOR

SKIN LOCATION DIAGRAM

Page No. 45 of 72


Part I

INSPECTION

REFERENCE



NOTE:

IFP1 INSPECT FOR CRACKS ALONG THE W.L. -28.00 FULL OR PARTIAL REMOVAL OF THEJ INTERCOSTAL ON THE INBOARD I OUTBOARD W.L. -28.00 INTERCOSTAL WILL BE

RETURN FLANGES AND WEB REQUIRED TO GAIN ACCESS FOR

INSPECTION PROCEDURES

F.S.FS.

i ii+’WL. -28.00

f L~ i´•U~ ii

-t i 9 ?~aOUP

(i I I+ili AFF

i ,I 1 INSPECT RIVETS COMMON TO THE INTERCOSTALI V J FORWARD I AFT SMEAR CLIP ATTACHMENT AREAS

FRAME INTERSECTIONS FOR LOOSE OR SHEARED

CONDITIONS

FIGURE #15AVIEW LOOKING INBOARD FORWARD THE LEFT HAND

W.L. -28.00 INTERCOSTAL FUSELAGE FRAME INTERSECTIONS

SKIN OMITTED FROM VIEW FOR CtARIN

INSPECT THE FOLLOWING AREAS

LEFT RIGHT HAND SIDES TYPICAL

W.L. -28.00, F.S. 37.00 THRU 60.50

W.L. -28.00, F.S. 99.00 THRU 209.24

Page No. 46 of 72

2-3(

SERWCE BULLEfN NO. 214

Parl I

INSPECTION

REFERENCE

TCAC DRAWING #300007-1, -517 8 -525 ASSY FOR MODIFICATIONS


rylPARTAINSPECT RIVETS COMMON TO THE310926 CLIP OW.L. -13.00 FOR LOOSE

OR SHEARED CONDITIONS4 -t

4W.L. -13.00

~CiL 370828

INTERCOSTAL

(REF.)

178.715 lj2.50

310926 CLIP

F.S. (REF.)

OUTER AIRCRAFTSIDE SKIN (REF.)

’I\r 310850-501 f (REF.)310811-1 FRAME

leplPARTB FRAMEil+i(FPJ INSP~CT FOR CRACKS ON THE INNER I OUTER (REF.)

FLANGE 8 WEB F.S. 172.50 FRAME 7.00 INCHES I

NOTE: (PARTB, ONLY)(REF.)

ABOVE 8 5.00 INCHES BELOW W.L. -28.00 i 310871-1f(/lNTERCOSTAL f /UP

STRAPS TO GAIN ACCESS FOR INSPECTIONf

I ;LPFWDREMOVE THE 310928-39 1 -41 INNER FRAME 7.00

PROCEDURESF.S. +I

188.00

WL. -28.00+"t 1+ 1

II!CLI Ii

5.00L310928-39 DBLR~I n +I I+310928-41 DBLR

(REF.) X.lli~ +Ii IPARTB

INSPECT FOR CRACKS IN THE INNER FRAME IJj f f

INTERCOSTAL d W.L. -28.00. IN ADDITION,j f

INSPECT THE INNER FRAME STRAP

DOUBLERSPARTC +il I 1310928-39 8 310928-41 BETWEEN FS. 172.50 L

THRU 188.00

I V I INSPECT RIVETS COMMON TO THE LOWERWINDOW INTERCOSTAL W.L. -28.00, CLIP

ATACHMENT AREAS AND INNER FRAME

STRAP DOUBLERS FOR LOOSE OR SHEAREDCONDITIONS I PARTA- INSPECTION

MODEL S/N

690D 15001THRU15032695A 96001THRU96066

EXCEPT SIN 96063

PART B 4 C INSPECTIONSMODEL ISIN

690D 15001THRU15040695A 96001THRU981006958 96201THRU96208

EXCEPT S/N 96063,

NGURE #f 6 1 8 96208

VIEW LOOKING OUTBOARD THE UH,,,,~,NsPEcnolY

F.S. 172.50, 178.715 8~ ~88.00 MODEL IS/N

FUSEtAGE FRAMES 690D 15001 THRU 15034695A 96001 THRU 960ZF B

EXCEPT S/N 96063,

RIGMT MAND SIDE OPPOSITE 96069 8 96075

Page No. 47 of 72

7J"h


PartlINSPECTION

REFERENCETCAC DRAWING #300007-503 8 -507 ASSY FOR MODIFICATIONS


310968-9 ANGLE

(REF.)

310868-51 WEB

(REF.)F.S. 209.24

I IPARTBIFPI INSPECT FOR CRACKSIN THE 310868-51 WEB

SECTION A-A

RADIUS

310868-39 ANGLE(REF.).I´•~"

310868-37 ANGLE

(REF.)

~ze"OL´•

i;:i

i Ic’ Lt

1 PARTA I´•rlU I (+II I INSPECT RIVETS COMMON TO THE INTERCOSTAL-----~

SMEAR CLIP AND AFT PRESSURE BULKHEAD

OUTER FRAME W.L. -28.00, FS. 209.24 FOR LOOSE 310868-35 ANGLEOR SHEARED CONDITIONS

lic*’ (REF.)310968-9ANGLE ~I

(REF.) I 310868-11 ANGLE

310868-51 WEB(REF.)

I lil(REF.) ´•I

,,I

aso t=UP

ct~8’;O

I:: o´•

‘PARTB(FPI INSPECT FOR CRACKS IN THE 310868-51 lit

BULKHEAD WEB ALONG THE VERTICAL ~cl Fk/ORADIUS WHERE SUPPORTED BY AFT SIDE

iANGLE B.L. 19.15, W.L. -13.00 TO -53.50rL:

’rg

FIGURE #77~S .,,E,PARs~NA-INSPECTION

VIEW LOOKING AFT OUTBOARD 690D 15001THRU15028

THE LEFT HAND AFT PRESSURE 695A 96001THRU96058

BULKHEAD (F.S. 209.24) PART B INSPECTIO~MODEL SIN

690D 15001THRU 15029

RIGHT HAND SIDE OPPOSITE 695A 96001THRU96061

Page No. 48 of 72

2-CI


Part~INSPECTION

REFERENCE



310868-25 WEB

(REF.)

320027-1 ANGLE

(REF.)

W.L -53.50

320037-1 PANELAFT (REF.)

SECTION A-A

I II IINSPECT RIVETS COMMON TO THEI V ]LOWER 320027-1 ANGLE (BOTH FLANGES)


10.00 INCHES INBDI OUTED OF CENTERLINE

UP

310868-25 WEB

(REF.)

320027-1 ANGLE

(REF.)

~-t,,4

W.L.-S3.50

iZINSPECT

10.00 INCHES

AFT (REF.)320037-1 PANELAIRCRAFT

C/LI INSPECT

10.00 INCHES

FIGURE #~8VIEW LOOKING DOWN FORWARD LOWER

AFT PRESSURE BULKHEAD (F.S. 218.40)

Page Na. 49 of 72


ParilINSPECTION

REFERENCE

TCAC DRAWING #300007-501, 300008-1, -501 8 -505 ASSY FOR MODIFICATIONS

TCAC DOCUMENT #MP3-7 8 MP3-8 FOR MODIFICATION PROCEDURES

I II 1 INSPECT ALL VISIBLE FASTENERS COMMON TOI V ITHE STRINGER ENDS FOR LOOSE. WORKING OR

SHEARED CONDITIONS. TYPICAL FOR STRINGER

310859-1 FRAME NO. 1, 282A

(REF.) F.S.

155.54 4.170317-5 STRINGER

NO. 2 (REF.)

FS. 164.82 S

FS. 1~170317-3 STRINGER

171.00 O NO. 1 (REF.)

O /I

INSpECT 1.Pg INCNC

INfjpECT3.001NCHFR4ME 8 GUSSETPIP~CAL "-310809-3 FRAME

(REF.)

170317-7 STRINGER

NO. 2A (REF.)

310398-13 GUSSET j(REF.)

310392-7 GUSSET

(REF.)

170314-13 RIB

V_QSTRINGERS NO. 1, 2 8 2A FROM THEIR INBOARD

(REF.) INSPECT FOR CRACKS IN THE UPPER WING

TERMINATING END 4.50 INCHES OUTBOARD,UP FROM THE FORWARD A~TACHING SIDE310828-503 INTERCOSTAL

~--tNn(REF.)NOTE:

INSPECT FOR CRACKS IN ALL A~TACHING

STRUCTURES(FRAMES,GUSSETS,ETC.)INBD i OUTED FLANGES 8 WEBS FROM

1.00 INCH ABOVE 8 3.00 INCHES BELOW

THE ATTACHING STRINGERS

FIGURE #20VIEW LOOKING OUTBOARD AFT THE LEFT HAND

STRINGER I FRAME INTERSECTION (STRINGER #1, 2 2A)


Page No. 51 of 72

W.S.

91.46AIRCRAFT cn

W.S. 0.0W.S. W.S.

103.46 ~L, 79.46 W.S.24.07

FIGURE #22 FIGURE #24

113.00 I) /W.S. W.S.

Page #55

W.S. W.S. W.S. W.S. W.S.197.32 178.66 160.00 142.00 69.00 39.00

~-FIGURE #23O Page #56

Zu, v,

m-oz ~NGURE #21

n (nG)Ocn O O, o,

z mZ

Z v, 00n

o co O MAIN SPAR CAP rC z (REF.) O r

a o, ~L1 m=!m cor 01P Z ZO bO z

poP IS h)

\-FIGURE #26

O 0) RfAk SPAR CAP P;D ~O (REF.)

01

LEFT 4 R/H SIOE

jFIGURE#21A

Page #60

Page #54


Part~INSPECTION

REFERENCE

TCAC DRAWING #300008-503 ASSY FOR MODIFICATIONSTCAC DOCUMENT #MP3-8 FOR MODIFICATION PROCEDURES

ALLOWABLE DAMAGE LIMITS

CRACKS ARE ALLOWED THAT EXTEND ALONG THE LOWER 2D MINIMUM FASTENER

RETURN FLANGE OF THE W.S. 39.00 RIB BEND RADIUS. EDGE DISTANCE

CRACKS ARE ALLOWED THAT EXTEND UPWARDS INTO THE MEASURED FROM CENTER

VERTICAL WEB OF THE W.S. 39.00 R1B WEB, IF 2D OR 170318-1 CAPI OF FASTENER HOLE TO

(2 x FASTENER DIAMETER) EDGE DISTANCE CRITERIA CAN ANGLE (REF.) CRACK TERMINATING END

IF CRACK INDICATIONS ARE WITHIN THE APPLICABLE CRACKS(REF.) f-

1BE MAINTAINED ALONG THE EXISTING LOWER FORE AFT

FASTENER ROW. T(PICALACCEPTABLE

DAMAGE LIMITS, REFER TO TCAC DWG. 300008-503 ASSY

FOR MODIFICATION PROCEDURE. 170315-3 RIB

NOTE: -4_ 1

IF CRACK INDICATIONS EXTEND BEYOND SPECIFIED LIMITS

DAMAGED PARTS MUST BE REPLACED OR AN APPROVED

REPAIR INSTALLED.

DAMA GE UMITS

VIEW LOOKING INBOARD

1 INSPECT FOR CRACKS ALONG THE LOWER HORIZONTALFPI i FLANGE AND RADIUS OF THE 170315-3 RIB ON.S. 39.00)

FROM THE LOWER MAIN SPAR CAP AFT TOi 703 1 5-7 ANGLE I STRINGER #7

(REF.)

MAIN SPAR WEB 4Y

u-\ /‘CI(REF.) 4

MAINSPARLOWERk X h ‘h

CAP (REF.)

Y--~-t- x

~170315-3 RIBx

4~ ~x (REF. jx ‘i-xx -h /-170318-1 CAP

x~ xANGLE (REF.)

xx xx

xX~ X

x x

x X

xx

x Lt

rx

x

x

x

X

(REF.)

S

"oox ~-170317-33 STRINGER #7

o~sOx

´•Q~z x

s´•p‘*"~PFIGURE #2~

VIEW LOOKING INBOARD FORWARDTHE LEFT HAND W.S. 39.00 RIB LOWER FLANGE


Page No. 53 of 72


Parl I

INSPECTION

TCAC DRAWING #30000&503 ASSY FOR MODIFICATIONS


170317-11 STRINGER #3

(REF.)7 i 1 INSPECT FOR CRACKS IN THE 1703183 RIB-

r- ’NsPECT

FPi’’J Onl.s. 39.40 3 69.00) ~g STRINGER #3 CUTOUT

RIB WEB, UPPER RETURN FLANGE AND FLANGE

RADIUS2.00 INCHES INSpECT2.00 !NCHES7

INSpECT

-f‘ :i -C- -j-f-

I-L

1703341 CAP ANGLEFWD_e c170315-3 RIB(REF.)170321-501 STIFFENER (REF.)

(REF.)

FIGURE #2?AVIEW LOOKING INBOARD THE LEFT HAND

W.S. 39.00 UPPER RIB STRINGER #3 CUTOUT

W.S. 39.00 SHOWN, W.S. 69.00 T/PICAL


Page No. 54 of 72

7/


Part~INSPECTION

REFEREEJCETCAC DRAWING #30000&501 ASSY FOR MODIFICATIONS



MAXIMUM CRACKS LENGTH OF 1.00 INCH IN THE UPPER WING SKIN

UPPER WING SKIN BUCKLE IN´•THE BAYSKIN BUCKLES BETWEEN RIVETS ALONG STRINGER #2

IF DAMAGE INDICATIONSARE WITHIN THE APPLICABLE

DAMAGE LIMITS, REFER TO TCAC DWG. 300008-507 ASSYFOR MODIFICATION PROCEDURE.

NOTE:IF DAMAGE INDICATIONS EXTEND BEYOND SPECIFIED LIMITS,DAMAGED PARTS MUST BE REPLACED OR AN APPROVEDREPAIR INSTALLED.

I 1 INSPECT FOR CRACKS IN THE UPPER WING SKINFP

170400-1 LEADING~’’IWHICH EXTENDS FROM THE INTERSECTION OF THE

LEADING EDGE SKIN (STRINGER #1) AND THE NACELLEEDGE SKIN (REF.) FAIRING (W.S. i 03.46) AFT AND OUTBOARD APPROX.

A 45 DEGREE ANGLE

NOTE:

DO NOT REMOVE THE UPPER

II NACELLE FAIRING FOR INSPECTION

\-t +;I -t -t~STRINGER 41 CI,It

+9 i (V

.i t ;I i’~J/

I’;I I

-t++ 1- 7´• J170197-501STRAP

f.’ :-t. (REF.)~:i+iit

i- -------_

~tL_ I’ i) :-STRINGER #2

W.S. 113.00

170346-503 SKIN I ’‘’------‘---IW.S. 103.46(REF.)

U IINSPECT UPPER WING SKIN FOR BUCKLES

FWD ~BETWEEN STRINGERS #1 8 #2 W.S. 103.46 8 113.00

.~.II rFp’INSPECT UPPER WING SKIN ALONG STRINGER #2\’’IFOR CRACK INDICATIONS BETWEEN FASTENER

HEADS FROM W.S. 103.46 TO 113.00

FIGURE #22VIEW LOOKING DOWN

THE LEFT HAND UPPER WING SKIN


Page No. 55 of 72

5


Part I

INSPECTION

REFERENCE



UP IFPI INSPECT FOR CRACKS IN THE 1-70314-13 RIB

FUSELAGE STATION 165.00, STRINGER #2 CUTOUT

170317-5 STRINGER(W.S. 24.07) ALONG THE VERTICAL FASTENER ROW

#2 (REF.)

AND AROUND VERTICAL RIB BEADS BETWEEN

STRINGERS #1 AND #2 F.S. 165.00

170317-3 STRINGER #1

(REF.) F.S.155.54

ff170339-1 CAP ANGLE

(REF.)4

4

f

,’t \t~iII+I+

;li

(III I

fI II

170314-13 RIB II i

(REF.)(REF.)II

I/I) j17[)302-503 BRACKET ii

’li/f11 2

170317-19 ANGLEI I I I I I I I II(REF.)7

I

t_l_+ -7~ ~Inf I

f

+I c

[FPJ INSPECT FOR CRACKS IN THE 170314-13 RIB LOWER FUSELAGE :\I170317-23 STRINGER

170317-21 ANGLEINSPECT

IcalPARTA (REF.)

OnV.S. 24.07) ALONG THE LOWER FLANGE RADIUS SKIN (REF.) 45 (REF.)AND 110197-13 FAIRING ALONG THE FLANGE

RADIUS ONE INCH FORE AFT OF THE EXISTING 110197-13 FAIRING 170338-1 CAP ANGLEVERTICAL RIVET LINE FS. 155.54 (REF.) (REF)NOTE:

CRACKS DETECTED IN THE WING TO FUSELAGEFAIRING MAY INDICATE POSSIBLY INTERNAL

STRUCTURE FAILURE

FIGURE #23VIEW LOOKING INBOARD THE

LEFT HAND W.S. 24.07 RIB


NOTE: REFERENCE TCAC SE 223. FIGURES 4 d 5

PART A SPECIAL CONDITIONS PART B SPECIAL CONDITIONS

IF SE 223. PARTI HAS BEEN ACCOMPLISHED, IF SE 223, PART II HAS BEEN ACCOMPLISHED,

INSPECTION REQUIREMENTS PER FIGURE #23, PART A INSPECTION REQUIREMENTS PER FIGURE 423, PART B

ARE NOT REQUIREDI ARE NOT REQUIRED!

Page No, 56 of 72

t\

SERVICE BULLETIN N0.214

Part I

INSPECTION

REMOVE THE 170405-1 VERTICAL TEEBRACKET AND INSPECT FOR CRACKSON ALL FLANGES AND ALONG PART

RADIUS

BRACKET~MAY BE RE-INSTALLED PERENGINE CONTROL

THE PROCEDURES SPECIFIED BYCABLES (REF.) TCAC SE 223, PART II, ITEM 4, a

OO ~o

Q

8 8 8 8 i´•i I,"i 1 INSPECT FOR CRACKS IN THEFP1 1310777-501 FRAME(F.S. 144.00)

WEB 5 INNER RETURN FLANGE1.00 INCH ABOVE I BELOW THE

O g g O THE 170405-1 BRACKET BASEINSPECT FROM THE FORWARDAND INBOARD SIDE OF FRAME

e oo iij

170302-503 BRACKET i/I U

(REF.) l.OO\FICH170405-1BRACKET II(REF.)

NOTE: ouTBD

310777-501 FRAMEF.S. 161.00 (REF.)

REMOVE SEALANT TO GAIN

ACCESS FOR INSPECTIONPROCEDURES

FIGURE #23AVIEW LOOKING OUTBOARD FORWARD

THE LEFT HAND F.S.´• 144.00 W.S. 24.07 R1B

BRACKET ATTACHhiENT AREA


NOTE: REFERENCE TCAC SE 223, FIGURE 7

INSPECTION SPECIAL CONDITIONS

IF AREA WAS PREVIOUSLY INSPECTED PER SE 223. PARTII

INSPECTION REQUIREMENTS PER FIGURE #234

ARE NOT REQUrREDI

Page No. 57 of 72

MAXIMUM ALLOWABLE CRACK LENGTH ---t~.90 1.15 -----~t---MAXIMUM ALLOWABLE CRACK LENGTH

STEEL AND I OR ALUMINUM BULKHEADS TYPICAL I‘ I TYPICAL STEEL AND I OR ALUMINUM BULKHEADS

.90 INCH TYPICAL INBOARD AND I OR I I I 1 1.75 INCH TYPICAL INBOARD AND I OR

OUTBOARD FROM THE UPPER TWO (112) 1 I I I OUTBOARD FROM THE UPPER TWO (#1)ENGINE MOUNT ATTACHMENT HOLES ENGINE MOUNT ATTACHMENT HOLES

W.S. 91.46AND ALONG THE UPPER BEND RADIUS

STOP DRILL ENDS OF CRACKS I I I I I OF THE BULKHEAD

PER TCAC DOCUMENT MP3-8

AS REQUIRED O T~ INSPECT FOR CRACKS IN THE FORWARD-rIFPI STEEL AND AFT ALUMINUM FIREWALL

BULKHEAD ASSEMBLY ORIGINATING FROM

O EXISTING FASTENER HOLES AND ALONG THE

UPPER BEND RADIUS OF THE BULKHEAD

r- II -I

I II1--i-- c--I I o

11 6

’I1

I’ og

I I I O

coII 11~1

cn71 71-4< m

;dLI II ~Z 9a

I I ,I I I lo I~C) m C)I

~D --I I II I ~Ormr II ACCEPTABLE Ps O

TYPICAL CRACKS ’r’o Zm

P1 I r -n O ~n IIcn II II(P m -10 I, II o~o

o,z t I o o c

Z t I 7F Y’ _II II -nP~ V, 01Z t3 rgo 11W

O~ rO I IIIm r

z,1~ III I

ImUP OJ, *r --I

73 IIII

II

OUTED

m

9 o0710 11 I V911- P

-I II ---r--- _~m z

cn II II I ao zn v, ____l_____j II r(a Oh) O L0[3 ;D I I 48

II OIcn mmo II II z0 Y-I ~O II II I´• o Pm71

C NOI~It PPI_ -II II THE AFT ENGINE MOUNT

OoII II

_

BRACKETS MUST BE o~II II -I m-IREMOVED TO GAIN ACCESSI I _I, o--_

IIaO

zli~J II SIDE OF THE FIREWALL "o,

m’I 1!1 I I BULKHEAD ASSEMBLY v,

FOR INSPECTIONPROCEDURES

IF CRACK INDICATIONS ARE WITHIN THEFIREWALL

MAXIMUM ALLOWABLE CRACK LENGTH


3.00 INCHESOUTBOARD3’-

3.00 INCHESINBOARDIMAXIMUM ALLOWABLE CRACK LENGTHS STEEL AND I OR ALUMINUM BULKHEADS

AS SPECIFIED. REFER TO TCAC .50 INCH TYPICAL INBOARD AND I ORINSPECT BULKHEAD INSPECT BULKHEAD

DWG. 300008-513 ASSY FOR OUTBOARD FROM TI-(E LOWER TWO (115)MODIFICATION PROCEDURE. ENGINE MOUNT ATTACI-1MENT IIOLES

NOTE:

IF CRACK INDICATIONS EXTEND BEYONDSPECIFIED LIMITS, DAMAGED PARTS MUST

BE REPLACED OR AN APPROVED REPAIR

INSTALLED.


Part I

INSPECTION

W.L. -45.00FLOOR BRACKET CONFIGURATIONAND FASTENER PATTERN MAY VARY I fIN DESIGN PER FRAME (REF.)

L.B.L. 22.57

f-tf

‘INSPECT FOR CRACKS IN THE LOWER FRAMELFPIAROUND THE OUTBOARD LIGHTENING HOLE

BELOW THE FLOORLINE 2.00 INCHES ABOVE i OUTED +iAND 2.00 INCHES BELOW I INBD IN THEINNERFRAME FLANGE, RADIUS AND WEB

NOTE:

TO GAIN ADEQUATE ACCESS TO THE LOWER OUTBOARDFRAME LIGHTENING HOLES IT WILL BE NECESSARY TO

REMOVE THE FOLLOWING ITEMS:

OVTBOARD SEAT TRACK RAILSe

FORE I AFT OUTBOARD FRESH AIR DUCTS

OUTBOARD FLOOR PANELS

ELECTRICAL WIRE BUNDLES

ETC., AS REQUIRED FOR ACCESS R----W.L. -55.50

I t-, I

00

I

NOTE:REFER TO TCAC DRAWING NO. 300004,jj+

OUTBOARD CABIN FLOOR FRESH AIR DVCTSSHEET 2 OF 2 TO MAKE THE D(ISTING

REMOVABLE FOR FUTURE REOCCURRING ~IINSPECTIONS

j/2’ OUTED LIGHTENINGHOLE ALL FRAMES

I

I

D<CEPT WH 96.50 8 99.00

(REF.)

f,I

UP

INBD

INSPECT FOR CRACKS IN FRAME WEBFP

l.oo INCH DIAMETER AROUND UPPER

INSPECT FOR CRACKS ORIGINATING AT

END OF STRINGER CUTOUT

I 9 JFASTENER HOLES rN THE FRAME WEB


COMMON TO SUPPORTS, BRACKETSAND LINE BLOCKS

F/GURE #25VIEW LOOKING FORWARD THE LOWER

RIGHT HAND FUSELAGE STATION 87.00 FRAME SECTION

TYPICAL ON THE RIH F.S. 78.00, 87.00, 96.50 99.00 ONLY

TYPICAL ON BOTH THE L R/H F.S. 60.50 108.00 THRU 155.54

(17 LOCATIONS TOTAL)

Page No, 59 of 72

SERVICE BULLETIN MO, 214

Part I

INSPECTION

INSPECT FOR CRACKS IN THE 310844-29/-39 HOODIF PJ FORMER ALONG THE UPPER RETURN FLANGE, RADIUS,

AND FORMER WEB FROM L.B.L. 10.80 TO THE OUTBOARD

TERMINATING END

INSPECT FOR CRACKS IN UPPER SKIN HOOD

NOk: ~1 FORMER WEB AROUND THE LOWERINBOARD

TO GAIN ADEQUATE ACCESS TO THE UPPER OUTBOARD CORNER OF THE LIGHTENING HOLE,FIANGE RADIUS, IT WILL BE NECESSARY TO REMOVE OR I U(TENDING FROM LOWER RELIEF

DISCONNECT THE FOLLOWING ITEMS:

NOTE:CABLES GAIN ACCESS THROUGH THE FORWARDNITROGEN LINES UPPER FUSELAGE I BAGGAGE COMPARTMENT PANELHYDRAULIC LINES SKIN (REF)STATIC LINES

ETC., AS REQUIRED FOR ACCESS

eg a

a ees

a iia!

e~T V~ I I\ Q QO

;i 8

310844-29/-39 HOOD

FORMER (REF)

W.L. -5.10

QQg Q g Q g g g/~ g Q g~Q 9.UP

.I --_I

310844-29/-39 HOODWING REAR

SPARiF.S. 209.24 BULKHEAD

FORMER (REF.) L.B.L. 10.80UPPER CAP (REF.) (REF.)

FIGURE #26VIEW LOOKING UP FORWARD THE UPPER

LEFT HAND F.S. 209.24 BULKHEAD UPPER SKIN HOOD FORMER


Page No, 60 of 72

-J

SERVICE BULLETIN Nd, 214

Part ~IIRECURRING INSPECTIONS

ACCOMPLISHMENT INSTRUCTIONS %rlll RECURRING INSPECTIONS

1. Refer to Pan Il, Table I, and proceed with the applicable RECURRING INSPECTIO’N ITEMS which

defines the appropriate INSPECTION FIGURE(S).


3. Support fuselage with wing jack stands and tail tie-down stand as outlined in Airplane Maintenance Manual.

4. Remove all interior I exterior components as required to gain access to the applicable areas of the aircraft.

5. Follow the inspection criteria specified by each FIGURE(S) to determine if any cracking or damage is present.

NOTE:

IF CRACKING OR DAMAGE IS FOUND REFER TO ITEM #2 #3 IN COMPLIANCE SECTION.

6. Sealant and finishes must be restored per recommended Aircraft Maintenance Manual practices after

inspections are completed.

NOTE:

FOR LOCAL TOUCH UP ON EXISTING STRUCTURE, CHROMATE PRIMER MAY BE USED.

DO NOT MIX CHROMATE AND POLYURETHANE PRIMERS ON THE SAME PART.

7. Perform operational check of cabin pressurization system for leaks per Aircraft Maintenance Manual practices.

8. Re-install items removed as noted per Item 4.

Page No. 61 of 72

5

SERVICE BULLETIN NO.´•214

TABLE IPart II b

RECURRING INSPECTION INTERVALS

Part I Part II EFFECTIVITY.INSPECTION RECURRING INSP. MODEL/ SERIAL NO.FIRST INSPECTION

ITEM HOURS/ FIGURE(S) HOURS I FIGURE(S)

1. CABIN DOOR 3000 HRS i FIG. 9 98 1000 HRS I FIG. 1 lE 695A

96001 MRU 96013

8 96018 ONLY

2. 1 LOWER CABIN SKIN 7500 HRS I FIG. 15 750 HRS i FIG. 2 690D ALL

CRACKS 695A -ALL

6958 -ALL

3. LOWER CABIN FLOOR 7500 HRS i FIG. 25 1500 HRS I FIG. 3 690D ALL

FRAMES 695A ALL

6958 ALL

4. AFT PRESSURE 7500 HRS FIG. 26 1500 HRS I FIG. 4 690D ALL

BULKHEAD HOOD 695A ALL

FORMER 209.24 6958 ALL

INITIAL INSPECTIONS OF THE ABOVE AREAS ARE REQUIRED FOR ALL MODELS AND SERIAL

NO.’S AS SPECIFIED BY SE 214, Tart I, Table 1;

Item 1

EXAMPLE: Aircraft has reached 3000 airframe Hours Time-in-Service. Full compliance with items 1700,

2500, 3000, 5000, 6000, and 7500 Hour Aircraft Inspection Time Periods per Pmt I, Table I was

accomplished at 1900 Hours. Compliance with PartlI, Table I (Item #1 Cabin Door, Figures #1

#18 1000 Hour Intervals) must be completed at 3000 Hours, with the next recurring inspectiondue at 4000 Hours Time-in-Service and subsequently thereafter.

Item 2

EXAMPLE: Aircraft has reached 7500 airframe Hours I Time-in-Service. Full compliance with items 1700,

2500, 3000, 5000, 6000, and 7500 Hour Aircraft Inspection Time Periods per Parr I, Table I was

accomplished at 1900 Hours. Compliance with Part Il, Table I(ltem #2 Lower Cabin Skin Cracks,

Figure #2 750 Hour Intervals) must be completed at 7500 Hours. with the next recurring

inspection due at 8250 Hours I Time-in-Service and subsequently thereafter.

Item 3 &4

EXAMPLE: Aircraft has reached 7500 airframe Hours I Time-in-Service. Full compliance with items 1700,

2500, 3000, 5000, 6000, and 7500 Hour Aircraft Inspection Time Periods per Parr I, Table I was

accomplished at 1900 Hours. Compliance with Part U, Table I (Item #3 Lower Cabin Floor Frames,

Figure #3 and Item #4 Aft Pressure Bulkhead Former at 209.24, Figure #4 1500 Hour Intervals)must be completed at 7500 Hours, with the next recurring inspection due at 9000 Hours I

Time-in-Service and subsequently thereafter.

Page No, 62 of 72


Part. IIRECURRING INSPECTIONS

FIGURE #~B 1F.S. 81.l0 F.S. 74.45 ,FIC;URE 1118

\i

t o c c o c c

1 .Il\e

+r I~LYI \f

FIGURE #lD FIGURE #lDFIGURE #lCc

OOQQOJOOOf +Je

D I r I II II+~-L-W II II+ W.L. -15.05r

+I ~I++I ii o

O II Y+:le

´•cl o1

o +:lfJ

UP c

+eco hFWD

1

J

o

+10 a8 $1++

FIGURE IIlU o3

~LI (3 1 jl+l FIGURE #~D

0\ /3´•r

-r

cll\cDI o5

a (I+j~ D-W´•L1~26.60D D O O O J S 3 O

O O8c

+L+I I I I I+

c a8 ~i+

’I I+a

+I:ra c

FIGURE #1D a 9 a FIGURE HD+Le +’I+

a ~I.. ..I-´• I´• 71 ..~19 a d+a

c a I I+ :I D- W.L. -37.57c

a

a8 a

FIGURE #1A3 8

CI I I

:I+c

I ´•I+

OQ

f

C I I ~lt

Tl\l I\ I I 11 I Il:li

FIGURE#1D---\ IIli I~lo Cor I ;I+ FIGURE IIlU

’I"I I+

+I I- L C´•(

t

’:L D--W.L.-48.90c I+ Ic

FIGURE #1VIEW LOOKING OUTBOARDTHE MAIN CABIN ENTRY DOOR

(REF. SE 214, PART I, FIGURE #9)EFFECTIVITY

MODEL SIN

330247 i 330430 DOOR 695A (96001 THRU 96013

CONFIGURATION SHOWN 695/4 96018

Page No. 63 of 72


Part IIRECURRING ’INSPECTIONS

(Fpl’NSPECT FOR CRACKS ORIGINATING FROM THE

ZEE CHANNEL

7 r1’’1´•1.00 INCH DIAMETER PUSH ROD HOLE IN

THE ZEE CHANNEL WEB W.L. -48.13

INSPECT FROM THE UPPER SIDE ONLY

(REF.) INTERCOSTAL a

T~ (REF´•)

CLIP(REF.)--\~\I j /i"

’Ie

i´•8 8

om

(7>

C3~ XAFTs-----IC~s

O

Ooo Ci; o b

----W.L. ~8.13

INNER DOOR STRAPo

o

INNER PLATEDOOR FRAME

INNER STRAP

DOUBLER (REF.)

(REF.)(REF.) NOTE:(REF.)

DO NOT REMOVE ANY RIVET MOUNTED

DOOR PARTS FOR INSPECTION PURPOSES

FIGURE #?AVIEW LOOKING OUTBOARD DOWN THE

LOWER AFT CORNER OF T~-1E CABIN DOOR(PUSH ROD LINKAGE OMITTED FROM VIEW FOR CLARIP~

(REF. SE 214, PART I, FIGURE #9A)

330247 1 330430 DOOR ONLY

NOTE:

RECURRING INSPECTIONS REQUIREDMODEL yN

~1000 HOUR INTERVALS PER SE 214.695A 96001 THRU 96013

PART II, FIGURE #1A695A 96018

Page No. 64 of 72

18

SERVICE ~ULLETIN Nb. 214

Pari IIRECURRING INSPECTIONS

CA UTION: I 1 INSPECT FOR CRACKS ORIGINATING FROM THE

OR TORN OFF:DURING-DISASSEMBLY,FP DIAMETER FROM THE CENTER OF THE HOLE

USE U(TREME CARE WHEN REMOVING THE OUTER BAYONET PIN HOLE AND GUIDE BLOCK

DOOR SEAL, IF ANY RUBBERNIPPLES ARE DAMAGED ATTACHMENT FASTENERS 1.50 INCHES IN

THE SEAL MUST BE REPLACED IN THE OUTER DOOR FRAME WEB

’g OO DOORFRAME

~7 INSPECT RIVETS COMMON TO THE VERTICAL \o dWEB (REF.)

V Oi IWINDOW CHANNEL UPPER END, SMEAR CLIPS

AND BAYONET GUIDE BLOCK FOR LOOSE OR 9~5SHEARED CONDITIONS

O~8‘´•, o

;"´•~s8 8.O\I O

O OB

0/

0/ ~G/

oi

o

o

o

i UP

VERTICAL WINDOW ~jt/""OUTER DOOR CHANNEL (REF.)

SKIN (REF.)

NGURE #~BVIEW LOOKING OUTBOARD DOWN THE

UPPER AFT CORNER OF THE CABIN DOOR(BAYONET PIN OMITTED FROM VIEW FOR CLARIP~

(REF. SE 214, PART i, FIGURE #9B)

3302471 330430 DOOR ONLYAFT UPPER PIN F.S. 91.10 SHOWN

FORWARD UPPER PIN F.S. 74.45 TYPICAL

NOTE:EFFECTIVITY

RECURRING INSPECTIONS REQUIREDMODEL S:N

1000 HOUR INTERVALS PER SE 214, 695A 96001 iHRU96013PART II, FIGURE #1 B

695A 96018

Page No, 65 of 72


Part IIRECURRING INSPECTIONS

NOrr: CAUTION:IT WkL BE NECESSARY TO REMOVE THE BAYONET DUE TO REPEATED REMOVALS OF THE BAYONETGUIDE BLOCK TO INSPECT THE UPPER DOOR BEAM GUIDE BLOCK FOR INSPECTIONS EXERCISERADIUS EXTREME CARE WHEN REMOVING THESE FASTENERS

NOT TO ENLARGE OR ELONGATE EXISTING HOLES IN

FOR REINSTALLING THE GUIDE BLOCK TO THE THE DOOR FRAME OR BAYONET GUIDE BLOCKDOOR FRAME WEB, IT IS ACCEPTABLE TO INSTALLHL20P6-5 PIN 8 HL86-5 COLLAR ~7INSPECT FOR CRACKS IN THE BEAM UPPER FLANGE

IF REQUIRED, THE HL20PB-5 PIN 8 HL86-5COLLARPP

VERTICAL RETURN FLANGE RADIUS OF THE BEAM

HOLE LIMITS (.1625 1.1600) RADIUS 3.00 INCHES FORWARD FROM THE AFFTERMINATING END OF THE PART AND THE AFT

MAY BE TAKEN TO THE NEXT SIZE FASTENER

HL20PB-6 PIN 8 HL86-6 COLLAR

HOLE LIMITS (.1885 1.1855) O I)OOR FRAME

O ,1WEB (REF.)

0\a

UPPER AFT 8AYONET

l~e

GUIDE BLOCK(REF.)

I ji,,,,,,,.

BEAM ~REF.)

OUTER DOOR

1SKIN (REF.)

~NSPECTSaOFS. 91.78 INCHES

VERTICAL WINDOWCHANNEL (RE~)

O~’e,

FIGURE #~CVIEW LOOKING OUTBOARD UP THE

UPPER AFT CORNER OF THE CABIN DOORIBA YONET PIN 4 LINKAGE OMI~ED FROM VIEW FOR CLARITY)

(REF. SE 214, PART I, FIGURE #9C)

220247 1 330430 DOOR ONLYAFT UPPER PIN F.S. 91.10 SHOWN

FORWARD UPPER PIN F.S. 7;4.45 TYPICAL

(COORDINATE WITH INSPECTION FIGURE #´•1B)

NOTE:

RECURRING INSPECTIONS REQUIREDh~ODEL SIN

1000 HOUR INTERVALS PER SE 214,695A 96001 THRU96013

PART II, FIGURE #1C695A 96018

Page No. 66 of 72



(Fj~ INSPECT FOR CRACKS IN THE OUTER DOOR

DOOR FRAME

I")FRAME PLATE DOUBLER AROUND THE BAYONETGUIDE BLOCK 1.00 INCH ABOVE I BELOW THEUPPER I LOWER ENDS OF THE PLATE DOUBLER

WEB (REF.) /--CAUTION:USE UCTREME CARE WHEN REMOVING THE

O

J-/6OUTER DOOR SEAL, IF ANY RUBBER NIPPLESARE DAMAGED OR TORN OFF DURING

DISASSEMBLY,THE SEALMUST BE REPLACED

~T1?O IsINSPECT 1.00INCH ABO~E

O

o W.L. -26.60

INNER DOOR STRAPDOUBLER (REF.)

O j/oIFP’ INSPECT FOR CRACKS IN DOOR

I~I" I FRAME RADIUS ALONG THEOUTBOARD EDGE OF PLATEDOUBLER

BAYONET GUIDE-/-I! a

P_O

O

O INSPECT 1.00

j I\NCH BECOW

iYi,.. O I"

V-NOTE:DO NOT REMOVE THE OUTER DOOR FRAME PLATE

PLATE DOUBLER (REF.) DOUBLER OR BAYONET GUIDE BLOCK FOR

INSPECTION PURPOSES, ONLY INSPECT ON 8 TOTHE U(ISTING EDGE OF PART

FIGURE #?DVIEW LOOKING OUTBOARD AFT THE

W.L. -26.60 FORWARD DOOR BAYONET DOUBLER(BAYONET PIN OMITTED FROM VIEW FOR CLARITY)

(REF. SE 214, PART I, FIGURE #9D)

3330247 1 330430 DOOR ONLYFORWARD 8 AFT BAYONET PIN W.L. -15.05 TYPICALFORWARD 8 AFT BAYONET PrN W.L.. -26.60 SHOWN

FORWARD 8 AFT BAYONET PIN W.L. -37.57 TYPICAL

FORWARD 8 AFT BAYONET PIN W.L. -48.90 TYPICAL

NOTE:

RECURRING INSPECTIONS REQUIRED EFFECTIVITYMODEL S,N

1000 HOUR INTERVALS PER SE 214,695A 96001 THRU96013

PART II, FIGURE 410695A 96018

Page No. 67 of 72

SERVICE BULLETIN-MO. 214


INSPECT RIVETS COMMON TO THE OUTER 1-7INSPECT RIVETS COMMON TO THE OUTERU jSK,NAND VERTICAL WINDOW CHANNELS UI I SKIN AND DOOR FRAME AROUND THEON THE FORWARD I AFT SIDE OF THE DOOR I PERIMETER OF THE DOOR FOR LOOSE ORFOR LOOSE OR SMEARED CONDITIONS I SHEARED CONDITIONS

F.S. I F.S:

74(45 91110

f:::: fff

li:fit5

WL. -15.05-- I´•:S

,J I;;

i

EIWL. -26.60--Tq:ji \iT5 I’ 3=3

I:i

fsl

W.L. .37.57- i´•I i:iii i,i

xiI~

:+;;+i sL~´•-j

r:l

E i:i,,

1

.;b I´•!

FIGURE #~EVIEVV LOOKING INBOARD

THE CABIN DOOR OUTER SKIN

(REF SE 214, PART I, FIGURE #9E)

330247 1 330430 DOOR ONLY

NOTE CLEAN AREA FOR VISUAL INSPECTION PROCEDURES ONLY!DO NOT REMOVE PAINT FROM THE SIDE SKIN SURFACE!

NOTErRECURRING INSPECTIONS REQUIRED TrVIPI

MODEL S/N1000 HOUR INTERVALS PER SE 214.

695A 96001 THRU 96013PART II, FIGURE #1E

695A 96018

Page No. 68 of 72



INSPECT ALONG RIVETS LINES COMMON TO FUSELAGEI U I FRAMES FOR CRACKED, TIPPED, SMOKING, WORKING

OR SHEARED FASTENER CONDITIONS

INSPECT FUSELAGE SKIN ALONG RIVET LIMES COMMON

TO FUSELAGE FRAMES FOR CRACKING BFMIEEN RIVETHEADS

NOTE:

IF DAMAGED RIVETS OR CRACKING INDICATIONS ARE

NOTED DURING VISUAL INSPECTION PROCEDURE,REMOVE PAINT AND CONTINUE WITH FLORESCENT

DYE PENETRANT INSPECTION PROCEDURE

ii Irl Itl\ B_EP_MKEELCAPL.B.L. 9.07

j AIRCRAFT

NTERLINEFWD--’ -L;-,,,,-L"-,-,’~,,--LL;L-----U;LC-L 8. L. 0~0

KEELBEAMCAP

R.B.L. 9.07

87.00 108.00 1 126.00 144.00F.S. F.S. ES. F.S.

F.S. F.S. F.S. F.S. F.S.

78.00 96.50 99.00 117.00 135.00

FIGURE #2VIEW LOOKING UP THE LOWER FUSELAGE

(REF. SE 214, PART I, FIGURE #15)

INSPECT THE FOLLOWING AREAS ALONG

FRAIME RIVET LINES (SKIN 8 RIVETS ONLY)F.S. 78.00, L.B.L, 9,07- R.B.L. 9.07

F.S. 87.00, L.B.L. 9.07- R,B.L. 9.07

F.S. 135.00, L.B.L. 9.07- R.B.L. 9.07

F.S. 144.00, L.B,L. 9.07- R.B.L. 9.07

NOTE: CLEAN AREA FOR VISUAL INSPECTION PROCEDURES ONLY!

DO NOT REMOVE PAINT FROM LOWER SKIN SURFACE!

NOTE:

RECURRING INSPECTIONS REQUIRED750 HOUR INTERVALS PER SE 214,

PART II, FIGURE #2

Page No. 69 of 72



FLOOR BRAGKET CONFIGURATIONAND FASTENER PATTERN MAY VARY W.L. ~5.00

ill INSPECT FOR CRACKS IN THE LOWER FRAME IN DESIGN PER FRAME (REF.)I v ]AROUND THE OUTBOARD LIGHTENING HOLE

fU

P´• -eBELOW THE FLOORLINE 2.00 INCHES ABOVE I OUTEDAND 2.00 INCHES BELOW I INBD ALONG THE INNERFRAME FLANGE, RADIUS AND WEB

NOrr:

IF DAMAGED RIVETS OR CRACKING INDICATIONS ARE\ I fNOTED DURING VISUAL INSPECTION PROCEDURE, L.B.L. 22.57

REMOVE PRIMER AND CONTINUE WITH FLORESCENT

DYE PENETRANT INSPECTION PROCEDURE

NOrr:TO GAIN ADEQUATE ACCESS TO THE LOWER OUTBOARDFRAME LIGHTENING HOLES 1T WILL BE NECESSARY TOREMOVE THE FOLLOWING ITEMS:

FORE I AFT OUTBOARD FRESH AIR DUCTS

ETC., AS REQUIRED FOR ACCESSWL. -55.50

i +I

i a´•i~J FASTENER HOLES IN TnE FRAME WEB

FOR LOOSE OR SHEARED CONDITIONS t\ I~COMMON TO SUPPORTS, BRACKETSAND LINE BLOCKS

OUTED LIGHTENINGHOLE ALL FRAMESE(CEPT R/H 96.50 99.00

(REF.)f jl~L

UP

.~LeU

INSPECT FOR CRACKS IN FRAME WEB1.00 INCH DIAMETER AROUND UPPEREND OF STRINGER CUTOUT

FIGURE #3VIEW LOOKING FORWARD THE LOWER

RIGHT HAND FUSELAGE STATION 87.00 FRAME SECTION

(REF SE 214, PART I, FIGURE #25)

TYPICAL ON THE R/H F.S. 78.00, 87,00, 96.50 8 99.00 ONLYTYPICAL ON BOTH L 8 R/H F.S. 60.50 8 108.00 THRU 155,54

(17 LOCATIONS TOTAL)

NOTE: THE R/H FS. 96.50 8 99.00 FRAMES WILL NOT REQUIREINSPECTION THE OUTBOARD LIGHTENING HOLE

NOTE:RECURRING INSPECTIONS REQUIRED

1500 HOUR INTERVALS PER SE 214,PART II, FIGURE #3

Page No, 70 of 72


Pa~r IIRECURRING INSPECTIONS

‘INSPECT FOR CRACKS IN THE 310844-29/-39 HOODCF~ FORMER ALONG THE UPPER RETURN FLANGE, RADLUS.

AND FORMER WEB FROM L.B.L. 10.80 TO THE OVTBOARDTERMINATING END

NOTE:

1F CRACKING INDICATIONS ARE NOTED DURINGVISUAL INSPECTION PROCEDUREi REMOVE PRIMER

AND CONTINUE WITH FLORESCENT DYE PENETRANT

INSPECTION PROCEDURE

rii~ 1NSPECT FOR CRACKS IN UPPER SKIN HOOD

NOtE: JFORMERWEBAROUNDTHE LOWERINBOARD

TO GAIN ADEQUATE ACCESS TO THE UPPER OUTBOARD CORNER OF THE LIGHTENING HOLE,

FLANGE RADIUS, IT WILL BE NECESSARY TO REMOVE OR U(TENDING FROM LOWER RELIEF

DISCONNECT THE FOLLOWING ITEMS:NOTE:

CABLES GAIN ACCESS THROUGH THE FORWARDUPPER FUSELAGE BAGGAGE COMPARTMENT PANELNITROGEN LINES

HYDRAULIC LINESSKIN (REF.)

STATIC LINES

ETC., AS REQUIRED FOR ACCESS

e~ g Q

iia!

!I\ o QO

O310844-29/-39 HOOD

FORMER (REF)

W.L. -5.10

a o g g Q O Q g O/Q O g Qj~Q gUP

Q

310844-29/-39 H000WING REAR

SPARiF.S. 209.24 BULKHEADFORMER (REF.) L.B.L. 10.80UPPER CAP (REF.) (REF.)

FIGURE #4VIEW LOOKING UP FORWARD THE UPPER

LEFT HAND F.S. 209.24 BULKHEAD UPPER SKIN FORMER

(REF. SE 214, PART I, FIGURE #26)


NOTE:

RECURRING INSPECTIONS REQUIRED1500 HOUR INTERVALS PER SE 214,

PART II, FIGURE #4

Page No, 71 of 72

\3


ELECTRICAL LOAD:

No change

WEIGHT AND BALANCE: (Partl, ONLY)

Perform LEVELING AND WEIGHING as outlined in the Airplane Maintenance Manual per Chapter 8

SPARES AFFECTED: (PariL ONLY)

None

RECORD COMPLIANCE:

PARTJT Make an appropriate entry in the Aircraft Maintenance Records as follows: Service Bulletin No. 214,Dated JANUARY 26, 2000, entitled "WING AND FUSELAGE FATIGUE INSPECTION AND

MODIFICATION", complied with (either) FULL COMPLIANCE or PARTIAL COMPLIANCE (list specificitems) as specified by Part I, "COMPLIANCE FORM". Attach copy of Part I, COMPLIANCE FORM to

aircraft logbook. If FULL COMPLIANCE is selected, only Part LT RECURRING INSPECTIONS will be

required. Identify next recurring inspection time hours, per item, in the aircraft logbook. If PARTIAL

COMPLIANCE is selected, identify the next required INSPECTION I MODIFICATION TIME per

Partl; Tablel.

PARTU Make an appropriate entry in the Aircraft Maintenance Records as follows: Service Bulletin No. 214,Dated JANUARY 26, 2000, entitled "WING AND FUSELAGE FATIGUEINSPECTION AND

MODIFICATION", complied with items 1. 2. 3. or 4. as specified by Part II,’COMPLIANCE FORM".

Attach copy of Part II, COMPLIANCE FORM to aircraft logbook. Identify next recurring inspection time

hours, per item, in the aircraft logbook.

SUBMIT A COMPLETED COPY OF THE COMPLIANCE FORMS TO:

TWIN COMMANDER AIRCRAFT CORPORATION

Attn.: SERVICE DEPARTMENT

19010 59’" DRIVE N. E.

ARLINGTON, WA. 98223

Page No. 72 of 72


rWIIY COMPLIANCE FORMPartlIVLIEIQ I a/e MODEL: 695A FULL COMPLIANCE g PCEASECHECK

A/RCRA~T. CORPORA 7~ON PARTIAL COMPLIANCE [7 ONLY ONEAIC S/N: 96006

If partial compliance is selected. identify next I ICURRENT DATE: Jan. 26, 2000 AIC TOTAL HOURS: 1,900.0 required INsPECTIONI MODIFICATIONTIME

REQD.MOD.DASH 300005 1 300006 1 300007

NO. I MOD. MOD. FIG. I MOD. MOD. FIG. I MOD. MOD. FIG. I~noo. I/MDD. FIG.INSTL. INSP. INSP. I INSTL. INSP. INSP. I INSTL. INSP. INSP. I INSP.

isi /fNS~.-1 .*´•sc: NIA NIA N/A ;~s.e i NIA

\5’

-501Isi ~1 I5~j ~CficjSB2~1

-503 :ASC

ni~p´•-505 1 ls~l S.J.

-507 1 N/A NIA NIA r~Tj-509 ~X j~T-5111 N/A N/A N/A

sB~i~i. NIA NIA NIA

-515isi

-517s C.i I~sc.

ILI11

(/N/Aisl

S.J.-521 iSB~lli

-523 1 N/A N/A I/N/A I MIA\ I NI sezc~ ~SC i

i"ls NIA A /Y N/A ~51-525 1S"nt"l

-527 Hood Former/ Figure 26

-529 N/A ly N/A N/A

Cabin Door IS.J. Figures 9 9E

,ifi~´• I Cabin Skin Cracks

Figure 15

Lower (1Frames I Figure 25

sueTOTAL 11/I 11 1 10 10 1 12 1 13 13 14 1 6 6 5

TOTAL1 MOD. I~STL.POMPLETE 40 1 MOD. INSP COMPLETE 40 1 FIG. INSP COMPLETE 42

MOD. Required Modification Dash No. Installed INSPECTION:INSTL. (Techniclan Sign-off far Worle Accomplished 1 58-214 STAMP)

MOD. Required Mod. Dash No. Inspected after Installation NAME: "~e DATE:INSP. (Inspector Sign-oft for Wor(e Accomplished I COMPANY STAMP)

FIG. 1"5pection Completed per Applicable Figures

INSP. (1"5pecror Sign-off for Work Accomplished COMPANY STAMP)NAME: ~eal Cr~C DATE.

NIANOt Applicable for This Aircraft Serial No.

AIR.511 is Only Required if Short Edge Distance is Found

per TCAC Dwg. No. 3D0008-505NAME: Steoe ~oltes DATE.

No recurnng inspections are required if the -5CO Modifications are installed.

Four (4) items do not have approved modiftcatians and require recurringInspections per SE 214. Part II. Table i. Initial Inspections per (Figures 9-9E. 15.

This FORM to be Added to the Aircraft Logbook and a COPY Sent to

25. 8 26)8 recurring inspections per ?an II (Figures l-1E. 2. 3. 8 4)TCAC for Compliance.

Page No. 1 of 2

COMPLIANCE RECORD

SE~ICE BULLETIN: N~ 214

WING AND FUSELAGE FATIGUE INSPECTION ANDIOR MODIFICATION

AIRPLANE REG. TOTAL

MODEL S/N NO. TIME (HOURS)

OWNER NAME

ADDRESS

TELEPHONE NO FAXNO

COMPLIANCE WITH SE 214:

DATE

WORK PERFORMED BY

COMPANY

ADDRESS

TELEPHONE FAX

I~


Part I

~WIIY COMPLIANCE FORM

%tlllllWAULJEIQI AICMO~L: FULL COMPLIANCE C? PLEASE CHECK

A /RCRAF;T CORPORA 7-/ON A/C S/N:PARTIAL COMPLIANCE O DNLY ONE j

CURRENT DATE: IAIC TOTAL HOURS: required INSPECTION I M001FICATICH TIME I IIf partial compliance is selected, idemify next

REQD.MOD.

DASH 300005 1: 300006 1 300007 1 300008

NO. I MOD. MOD. IFIG. I MOD. MOD. FIG. I MOD; IMOD. FIG. I MOD. MOD. FIG.INSTL. INSP. INSP. I INSTL. INSP. I INSP. I INSTL. INSP. INSP. I INSTL. INSP. INSP.

-501

-503

-505

-507

-509

-5111 1 I I I I I I 1 IA/R ~VR

-513

-515

-517

-519

-521

-523

-525

A ressure u ead-527 Hood Fonner/ Figure 26

-529

Cabin Door/

Figures 9 9E

abin Skin Cracks

Figure 15

Lower Cabin Floor(l7)Frames Figure 25

sueTOTAL

TOTAL I MOD. INSTL. COMPLETE I MOD. INSP. COMPLETE I FIG. INSP COMPLt:r

MOD. Required Modification Dash No. Installed INSPECTION:INSTL. (Technician Sign-off for work Accomplished 1 68-214 STAMP)

MOD. Required Mod. Dash No. Inspected after Installation NAME: DATE.INSP. (I"spector Sign-off far Worle Accomplished I COMPANY STAMP)

FIG. I"spaction Completed per Applicable FiguresINSP. (I"specror Sign-off for Wor)e Accomplished I COMPANY STAMP) NAME: DATE.NIA

NOt Applicable for This Aircraft Serial No.

A/R-511 is Only Required if Short Edge Distance is Found

per TCAC Dwg. No. 300008-505NAME: DATE.

No recurring inspections are required a the -500 Modifications are Installed.

Four (4) items do not have approved modifications and require recumng

Inspections per SE 214. Part II. Table I. Initial Inspections per (Figures 9-9E. 15.This FORM to be Added to the Aircraft Logbook ane a COPY Sent to

25, 6 26) 6 recurnng inspections per Part II (Figures l-1E. 2. 3. 6 4).TCAC for Compliance.

PageN~.lafZ


Partl

rrWIAI COMPLIANCE FORM

UICIEIQ I Ale MoDEL: FULL COMPLIANCE PLEASECHECK

PARTIAL COMPLIANCE C1 oNLY ONEA/RCRAF7- CORPORA T70N AIC S/N:

CURRENT DATE: A/C TOTAL HOURS: required INSPECTION I MODIFICATION TIMEI IIf partial compliance is selected. identify next

~JI I

This FORM to be Added to the Aircraft Logbook and a COPY Sent to TCAC for Compliance.

Page No. 2 of 2

117


~JCWIY COMPLIANCE FORMPartII%L~WAIAULIEIQIAle MODEL: B95A

A /RCRAFr CORPORA ;r/ON AIC SIN: 96006

CURRENT DATE: March 15, 2002 AIC TOTAL HOURS: 3,000.0

Part I Part IIINSPECTION INITIAL INSPECTION RECURRING INSP. TIVIP(:

ITEM HOURS FIGURE(S) HOURS I FIGUREIS)DE 7 IAL NO.

1. CABIN DOOR 3000 HRS FIG. 9 98 1000 HRS I FIG. 1 1 SIN

TH

9601

NEXTINSPECTION DUE@ 4000.0 TOTALAIRFRAMEHOUR ANDSUBSEQ TH R

OF C CKING G

1 Na crack indications noted of l-1E

INSPECTED BY: 03/15 00

2. LOWER CABIN SKIN 7500 HRS i FIG. 1 S1 .2 690D ALL

CRACKS 695A ALL

6958 ALL

NEXT INSPECTION DUE ZSI1Qa~TbTAL Aid AND SUBSEQUENTLY THEREAFTERLIS ET SOF NYC CKIN G F

Not until 7500 hours

INSPECTED BY: DATE: 03/15/2002

3. LOWER CABI LOO 7500 FIG. 1500 HRS i FIG. 3 690D ALL

FRAMES 695A ALL

6958 ALL

N TION TOTAL AIRFRAME HOURS AND SUBSEQUENTLY THEREAFTERD S ANY ING OR DAMAG

INSP BY: DATE: 03/15/2002

4. SSU 7500 HRS i FIG. 26 1500 HRS i FIG. 4 690D ALL

BU EAD OD 695A ALL

FOR R 209.24 6958 ALL

NEXT INSPECTION DUE ZSDOS TOTAL AIRFRAME HOURS AND SUBSEQUENTLY THEREAFTER

LIST DETAILS OF ANY CRACKING OR DAMAGE FOUND:

Not required until 7500 hours

INSPECTED BY: Biee SHfitk DATE: 03/15/2002


/Y

COMPLIANCE RECORD

SERVICE BULLETIM: NO. 214.

WING AND FUSELAGE FATIGUE INSPECTION AND/OR MODIFICATION

AIRPLANE REG. TOTAL

MODEL S/N NO. TIME (HOURS)

OWNER NAME

ADDRESS

TELEPHONE NO FAXNO

COMPLIANCE WITH SE 214:

DATE

WORK PERFORMED BY (PRINTED)

(SIGNATURE)

COMPANY

ADDRESS

TELEPHONE FAX

r2~)


Pari I~

~WIY COMPLIANCE FORM

~IAJIMAULIEIQ I An: MODEL:

A~CRAF7- CORPORA ;T/ON AJC SIN:

CURRENT DATE: AIC TOTAL HOURS:

a

Part I Part UINSPECTION FIRST INSPECTION RECURRING INSP. O EFFECTIVITY:

ITEM HOURS FIGURE(S) HOURS FIGrlRE(S) MODEL I SERIAL NO.

i. CABIN DOOR 3000 HRS FIG. 9 98 1000 HRS FIG. 1 -18 695A S/N

96001 THRU 96013

96018 ONLY

NEXT INSPECTION DUE TOTAL AIRFRAME HOURS AND SUBSEQUENTLY THEREAFTERLIST DETAILS OF ANY CRACKING OR DAMAGE FOUND:

INSPECTED BY: DATE:

2. LOWER CABIN SKIN 7500 HRS FIG. 15 750 HRS FIG. 2 6908 ALL

CRACKS 695A ALL

6958 ALL

NEXT INSPECTION DUE TOTAL AIRFRAME HOURS AND SUBSEQUENTLY THEREAFTERLIST DETAILS OF ANY CRACKING OR DAMAGE FOUND.

INSPECTED BY: DATE:_

3. LOWER CABIN FLOOR 7500 HRS I FIG. 25 1500 HRS FIG. 3 6908 ALL

FRAMES 695A ALL

6958 ALL


INSPECTED BY: DATE:’

4. AFT PRESSURE 7500 HRS I FIG. 26 1500 HRS FIG. 4 6908 ALL

BULKHEAD HOOD 695A ALL

FORMER 209.24 6958 ALL


INSPECTED BY: DATE:


Service Bulletin AIRCRAFT COF)PORATION

p~O. BoX 3389

Arlington. WA 98223

Tel: POB) 43~i-9787 FEU: (208) 435´•1~12

SERVICE BULLETIN NO. 216 Original: June 9, 1992

FUELING PLACARD AND FLIGHT MANUAL ADDENDUM

MODELS AFFECTED:

All Twin Commander Airplanes

REAI1ON FOR PUBLICA1CION:

Twin Commander airplanes (like many others) are equipped with

multiple interconnected fuel tanks. Extended fueling time is

required for fuel to flow and equalize the fuel level among the

interconnected tanks. This is necessary to assure that the desired

proper fuel level is achieved. Although this fueling characteristic

is believed to be well-known among operators and service personnel,Twin Commander Aircraft Corporation has received a report of a

ditching of a Model 5005 in Hawaiian waters which was attributed to

fuel exhaustion, caused by insufficient fuel. This Service Bulletin

;heing issued in an effort to prevent the possibility of the above

iccurring. It provides additional warning and guidance to Twin

Commander operators and fueling personnel to assure proper fuel level

is achieved during fueling.

COMPLIANCE:

Accomplish at next convenient opportunity, not later than the next

required periodic inspection.

APPROVAL:


ESTIMATED MAN HOOR8:

Less than one hour.

PARTS DATA:

Enclosed herewith:Part No.

a ea Warning Placard 58216-1

1 ea Aircraft Flight Manual Special Supplement Fueling... 55216-2

Page 1 of 2


ACCOnPLI8H IN8TRUCTI~091B

i. Select a smooth area near each fuel filler port. Clean the

aircraft surface and install Warning Placard, P/N SB216-1 in

each area so as to be highly visible during fueling.

2. Place Aircraft Flight Manual Special Addendum Fueling P/N58216-2 at the front of the Aircraft Flight Manual or Pilots

operating Handbook, whichever is available for your airplane.

RECORD COMPLIANCE:

i. Make an entry in the Aircraft Logbook as follows:

Service Bulletin 216, dated June 9, 1992, "Fueling Placard

and Flight Manual Addendum" accomplished (DATEI.

2. Mail attached compliance card to Twin Commander Aircraft

Corporation.

Page 2 of 2

TWIN COHHANOER ATRCIIAFT

AIRCRRlrT CORPDI~TION FLl:aHT MANUAL Date: May 29. 1992

BPECIAL ADDENDUM F6ELINO

WARN~ND

This aircraft is equipped with multiple interconnected fuel tanks. To

assure proper fuel level it is necessary for fueling personnel to allow

extended fueling time for fuel to flow and equalize level among the

interconnected tanks.

I~ ACTION REOUIRED

Insure that fueling personnel understand the requirement to allow

extended fueling time to assure proper fuel level.

Verify proper fuellevel prior to flight dep8r~ure.

PLACARD

The following placard is to be permanently maintained adjacent to

each fuel filler port:

WARNING

TO ASSURE PROPER FUEL LEVEL,ALLOW EXTENDED FUELING TIME

TO EOUALIZE FUEL LEVEL AMONG

TnE INTERCONNECTED TANKS.

P/N 58216-1

NOTE: Permanently retain this Special Addendum at the front

of the aircraft Flight Manual or Pilots OperatingHandbook.

PIN 58216-2

COMP LIANCE CARD

Se~ica Buiierin/L´•rrer,; Iniormarion No.

airc:art Mooel Si N

1 Owner:

COMPLIANCE:

WOrK Periormed By:

Dare:

Signature

TC 14 OW191

~IIIAl

AIRC RA FT CO RPO RA TION

27 June 94

Dear Twin Commander OwnedOperator:

This cover letter is included with Service Bulletin No. 218 to explain the use of the wordMANDATORY on the first page of the service bulletin.

Twin Commander Aircraft Corp. (TCAC) considers our service bulletins to be mandatory.Therefore,;ill TCAC service bulletins will have MANDATORY written on the first page. Thiswill eliminate confusion regarding compliance with TCAC service bulletins. Compliance withall service bulletins issued by TCAC, both new and existing, is required and mandatory.

In some cases TCAC will recommend rather than require compliance with a service

publication. In these cases a Service Letter or Service Information will be issued, rather than a

service bulletin. Compliance with service letters and service information is stronglyrecommended.

All questions regarding this letter or any TCAC service publication should be addressed to theTCAC Engineering Dept.

Sincerely,

,_PMathesonGeneral Manager

JKM/gw

rwlu Cnhl*asoea alaea~FT E0apananoN o, NE L\llln.f.n Wa II111 nl´•ononl~mr F´•r ul loM, al.n~l?

SE RVICE PUB LICATIONS ~HMRNDERAIRCRAFTCORPORATION

revision notice p.g. sox 3388

Adington. WA 98283

Tel: (208) 433-8187 Fax: (208) 435-1112


Revision No. 1

Release Date: July 11, 1994

EMPENNAGE VERTICAL SLABILIZER INSPECTION AND MOD.CICATION

APPROVAL:


1. Delete (80) MS27039DD1-09 screws from 58218-501 paris list.

2. Add (80) MS35206-264 screws to 58218-501 parts list.

REVISE ACCOMPLISMMENT INSTRUCTIONSAS NOTED:

1. Replace "MS27039DD1-08" with "MS3520B-264" at all locations.

2. Add the following NOTE after step 15c.

NOTE:

Twin Commander Aircraft Corp. recommends the use of an anti-seize compoundwhen installing the M535206-264 screws in the MSZ7130-A19 -AaO rivnuts.

REVISE FIGURES AS N~ED:

Replace "MS27039D01-09" with "MS35206-264" at all locations.

SERVICE PUBLICATIONSAIRCRAFT CORPORATION

revision notice Fo. sox 3388

Mington. WA 9a223TaI: (208)~359181 Far: (206) 435´•1112

Service Bulletin 218

Revision No. 2

Release Date: September 23, 1994

EMPENNAGE VERTICAL STABILIZER INSPECTION AND MODIFICATION

APPROVAL:

REVISE FIGURES AS NOTED:

1. Please note on page 15 of 20 FIGURE 2 bottem of page under "MS20426AD4through nut ring, sltin and doubler flush N.S. 10 FL" NOTE: THE DOUBLERREFERRED TO IS THE EXISTING DOUBLER WHICH IS UNDER THE SKIN. THIS ISNOT REFERING TO THE NEW DOUBLER K410008-1.

2. R]ote:an page 22 of 22 FIGURE 8 bottem of page NOTE: BE SURE TO CUT OUTDOUBLER K410008-1 SO THAT ACCESS DOOR K410008-3 IS FLUSH WITHK410008-1 DOUBLER WHEN COMPLETE.

--MANDA TORY

~ervice Bulletin AIRCRAFT CORPORATION

p.o. B~x

*,lington. WA 08221

Tsl: (20(1) 435´•8187 Pax: (20a) 45?1´•11(2


Dated: May 19, 1994

EMPENNAOE VERTICAL STABILIZERIISPECTION AND MODIFICATION

NOTE:

This Service Bulletin supercedes and replaces Service Bulletin No. 206 in its

entirety for the effective models.

I;SEE~ULIIY;

A685 12000 thru 12066

690 11000 thru 11079 1 NB90A 11100 thru 11344 D6908 11350thru11566

690C 11800 thru 11735 IA690D 15001thru15042 T695 85000 thru 95084

695A 98001 thru 98100 10

RNOTE:

Model 6958 airplanes (Serial Numbers 96062, 96063, 96069, 96075, 96078, IY96085, and 96201 thru 96208) are excluded from this Service Bulletin. Service

Bulletin 206 is still effective for 6958 airplanes.

REASON FOR PVBLICATION:

TCAC has received several reports of aircraft with damage to the vertical stabilirer.

These reports include: cracks in lower ribs, wrinkles and/or cracks in skin near lower

ribs, cracked shear clips between lower ribs and rear soar, and cracks in upper relief

cutouts of FS 409.58 bulkhead. If left unrepaired, this damage could propagate? to

the point of failure of the Vertical tail. This Service Bulletin defines the requirementsfor inspection of these areas. In addition, modifications are defined which eliminate

the need for further action.

If any of the above damage is found, then the Part II modifications must be

completed immediately as damage could propagate to the point of failure.

PAGE 1 OF 22


COMPLIANC~

At 2000 hours total airframe time or within next 50 hours if

beyond 2000 hours and repeat each 12 months or 500 hours, whichever comes first.

EXCEPTION:

Airplanes recently inspected per Service Bulletin 206 and found to be free of

damage shall be inspected per Service Bulletin 218 within 12 months or 500

hours, whichever comes first, from the date of the last Service Bulletin 206

inspection.

Part II: Modification Before further flight if damage is found during Part I inspection.Part II is terminating action and no further special inspections per this service bulletin

are required.NOTE:

If no crac)cs are found during the Part I inspection the ownerloperator can

choose between repetitive inspections teach 12 months or 500 hours) or

completing Part II.

BYWHOM WORK WILL BE ACCOMPLLSHED:

1. A P Mechanic or equivalent.2. Eddy Current inspectors shall be Level II or Level III certified per MIL-STM1OE

and SNT-TC-1A.

APPROYBL:

Modifications described by this Service Bulletin are FAA DER approved.

i. Service Bulletin 206,"lnspection of Empennage Attach Area at Fuselage Station

409.56".

2. Service Letter 345, "Vertical Stabilizer Attach Bolts Inspection".

Part I Inspection: 10 hours tall models).Note: The time noted assumes that an access hole per Service Letter No. (SL) 345

has already been installed on the applicable models.

Part II Modification: 90 hours (models 685, 690, 690A, 690B, 690C, and 695).85 hours (models 690D and 695A).

ZL OF 4.


PARTS DATA:

Parts required to comply with this Service Bulletin may be ordered from your nearest

Twin Commander Service Center under kit number listed below for the applicableairplane model. The kits consist of parts listed below.

Part I. access door only

Kit number SB218-501:

Otv Part Number DeScriDtion1 K410008-3 Access door

1 K410008-5 Nut ring20 NASBB03-2 Screw

60 MS271 30-A19 Rivnut

30 MS271 30-A20 Rivnut

80 MS270390D1-09 Screw

80 ANBBOPD1OL Washer

Part II. Modification

Models 685. 690. 690A. 690B. 690C, and 895 kit number S8218-503:

Qt~ Part Number Descriotion

1 K310025-1 Strap1 K310025-2 Strap2 K310025-3 Filler

1 K310025-5 Doubler

1 1<310025-6 Doubler

2 K310025-7 Filler

2 K310025-9 Strap1 K410009-1 Doubler

1 K410009-3 Filler

1 K410009-5 Angle1 K410009-7 Angle2 K410008-1 Lower Skin Doubler

2 K410008-7 Strap2 M535489-46 Orommet

18 HL18PB5-2 Hilok

4 HL18PB5-3 Hilok

8 HL18PB5-4 Hilok

12 HL18PBS-6 Hiiok

4 HL18PBB-3 Hilok

6 HL18PB6-4 Hilok

2 HL1LIPBB-~ Hilok

20 HL19PBB-2 Hilok

4 HLB5PB6-7 Hilok

PAGE 3 nF 22


PARTS DATA: Kit number SB218-503 (cont’d)

4 HL18PB6-2 Hilok

40 HL70-5 Collar

36 HL70-6 Collar

4 HL87-6 Collar

Models 690D and 695A kit number SBZ18-505:

2 K310025-3 Filler

1 K310025-5 Doubler

1 K310025-6 Doubler

1 K410009-1 Doubler

1 K410009-3 Filler

1 K410009-5 Angle1 K410009-7 Angle2 K410008-1 Lower Skin Doubler

2 K410008-7 Strap2 N15335488-46 Grommet

16 HL18PB5-2 Hilok

4 HL18PB5-3 Hilok

8 HL18PB5-4 Hilok

12 HL18PB5-8 Hilole

4 HL18PBB-3 Hilok

6 HL18PB6-4 Hilok

2 HL18PB6-5 Hilok

4 HL18PB6-6 Hilok

20 HL19PB6-2 Hilok

4 HLB5PB6-7 Hilok

40 HL70-5 Collar

36 HL70-6 Collar

4 HL87-8 Collar

OPTIONAL Right hand access panel. kit number 58218507:

Otv Part Number

1 31101711 Door

1 311017-6 Doubler

1 311017-7 Angle1 311017-9 Angle1 311017-11 Doubler

1 311017-13 Doubler

10 MS21049L3K Nutplate10 MS246Q4S49 Screw

1 Service Letter 345 instructions

4 OF i.ri


PARTS DATA: (cont’d)

Airplanes that do not have the left hand access panel per SL 345 can order and

install the following kits:

SL 345-1 Models 685, 690, 690A, 690B,690C 11600 thru 11529, and

695 95000 thru 95010

SL 345-2 Models 690C 11630 thru 11681 11709 and

695 95011 thru 95079

TO BE PROCURED LOCALLY AS REQUIRED:

1. MS20470AD4, AD5, AD6, MS20428AD4, AD5, AD6, ~173243-4,-5,-6,and CR3242-4 RIVETS,

2, 825-309 (DESOTO) POLYURETHANE PRIMER FOR TOUCH-UP ON

PARTS SUPPLIED WITH KIT.

3, R411N SEAL (RUBATEX) AND EC-1403 OR EC-1300L ADHESIVE

(3M) OR EQUIVALENT.

4. LOCTITE 609 OR EQUIVALENT.

SeEWBCZQPLS: Torque wrench with 330 inch-pound capability

ACCOMPLISHMENT INSTRUCTIONS: PART I-INSPECTION

i. Install tail stand on tail skid and shore horirontal tail per procedure in applicableAirplane Maintenance Manual.

2. Remove left and right rudder control linkage access doors that are located justaft of fuselage station 409.56.

3. Remove:

a) The left and right vertical-to-horirontal stabilizer fairings.

b) The rudder hinge cover.

4. Install the left hand access panel per SL 345, if not already installed. Remove

the access panel, if installed,

NOTE:

The SL 345 access panel is not required for 690C sin 11719 thru 11735, 690D

all, and 695A s/n 96014 thru 96017 96019 thru 96100. For these airplanes,gain access through the door in the belly of the fuselage forward of FS 386,

Pnc.F 5 nF 33


ACCOMPLISHMENT INSTRUCTIONS: Part I (cont’d)

5. Visually inspect vertical stabilizer skin, left and right sides, for cracks (refer to

Figures 2 and 3.)

CAUTION:

If cracks are found in the vertical stabilizer side skin at the holes identified as A

and B in figure 2, or if the holes indicate working fasteners, then the holes

must be Eddy Current inspected for cracks in the spar caps. If no cracks are

found, continue with the Part I inspection,the airalsne is notto csntinue in senn~: contact Twin Commander Aircraft

Corp. prior to further flight.

NOTE:

Working rivets are usually indicated by blackldark coloring around rivet heads

andlor black steaks on outer surface of the skins around fasteners.

6. Inspect the following areas, both fore and aft, at station 409.56, where vertical

stabilizer attaches to horizontal stabilizer, for possible cracks/damage (refer to

Figure 1):

a. Area around bolt holes.

b. Upper and lower spar cap flange.

c. Station 409.56 bulkhead below horizontal spar, pay special attention to the

corner reliefs.

d. Horizontal spar web.

e Vertical stabilizer rear spar web, pay special attention to the joggle in the

spar web,

f. Aft clip (refer to Figures 1 and 2)

7. Cut a hole in the vertical stabilizer left hand side to accommodate the access

door, but do not install the door at this time (refer to Figure 2). Inspect for cracks

in the following areas through hole:

a. Around rivets that attach lower vertical stabilizer skin to ribs (refer to Figure

3).

b. Lower two ribs in the vertical stabilizer, pay special attention to the corner

reliefs.

c. Vertical stabilizer rear spar web, between the two lower ribs.

PAGE 6 OF 22


ACCOMPLISHMENT INSTRUCTIONS: Part I, step 7 (cont’d)

d. The forward clip.

8. Inspect fairing fastener holes around access hole. Plug any fairing fastener

holes with less than .35 edge distance using MS20426AD4 rivets, flush both

sides. Install K410008-5 nutring per Figure 2. Acceptable to cut K410008-5

nutring approximately in half to simplify installation if desired.

9. If cracks/damage are found in steps 5, B, 7, then modify per Part II of this Service

Bulletin prior to further flight.CAUTION:

If cracks are beyond the limits shown in Figures 1 and 2, or if cracks intersect

resulting in loose or missing material, then the damage is not covered by this

service bulletin, lLamaged Darts_not covered bv_tbls seoricebulletin must be

realacebnran aooroved repair mustbemade Driorto comoletion of the

and return of thaa~licplanatP_saod?Ik

10. Inspect areas noted in steps 5, B, and 7 for sheared, working, or loose fasteners.

Replace fasteners as necessary.

NOTE:

Working rivets are usually indicated by blackldark coloring around rivet heads

andlor black streaks on outer surface of the skins around fasteners.

11. Inspect four bolts attaching vertical stabilizer to front spar of horizontal stabilizer

for installation of castellated nuts on bolts and washers under bolt heads (referto Figurel).

12. If there are castellated nuts installed and no washers under bolt heads, proceedas follows:

a. Remove existing cotter pins and check bolt torque. Torque to be 160 to 200

inch-pounds.

b. Assure that nuts can be secured properly with new MS24665-132 cotter pins(refer to Figure 4).

c. If nuts cannot be secured properly, remove nut, Install an additional

AN8600516 washer Imrt~nutPnly, reinstall existing nut and torque 160 to

200 inch-pounds by tightening nut to low side of torque range and, if

necessary, continue to tighten until a nut slot aligns with hole in bolt. Install

new MS24665-132 cotter pins.

13. If castellated nuts a~Pt installed, replace existing vertical stabilizer attach bolt

(4 places), one at a time. as follows (refer to Figure 1):

Dar~s 7 nE

SERVICE BVLLETIN NO. 218

ACCOMPLISHMENT INSTRUCTIONS: Part I, step 13(cont’d)

NOTE:

Do not have more than one bolt out at the same time,

a. Remove bolt and inspect bolt hole for possible damage.

b. If hole is not damaged, install AN5-6 bolt, ANBBODB1B washer undernut

only, and MS17825-5 nut. Torque bolt 180 to 200 inch-pounds by tighteningnut to low side of torque range and, if necessary, continue to tighten until a

nut slot aligns with hole in bolt. Install M524665-132 cotter pin (refer to

Figure 4).

NOTE:

An additional AN960DS16 washer may be installed under nut only, if necessary,

to assure proper alignment of hole in bolt with slots in nut.

c. If hole is damaged, it is acceptable to use ANBJ bolt (0.375"/0.370"diameter hole) only if an edge distance of 0.58 inches or more can be

maintained.

d. If it is determined, prior to reaming existing hole, that an edge distance of

0.58 inches or more cannot be maintained, contact Twin Commander Aircraft

Corporation for further instructions.

e. If it is determined, prior to reaming existing hole, that an edge distance of

0.56 inches or more can be maintained, ream damaged hole to

0.375"/0.379" diameter and install ANB-7 bolt, ANBBOD616 washer under nut

only and MS17825-6 nut. Torque bolt 300 to 330 inch-pounds by tighteningnut to low side of torque range and, if necessary, continue to tighten until a

nut slot aligns with hole in bolt. Install M524885-134 cotter pin (refer to

Figure 4).

NOTE:

An additional AN960D616 washer may be installed ImdBLIUbtPnly, if necessary,

to assure proper alignment of hole in bolt with slots in nut.

14. If there are castellated nuts installed and washers under bolt head, proceed as

follows:

a. Remove bolts affected, one at a time. and inspect bolt holes for possible

damage.NOTE:

Do not have more than one bolt out at the same time.

pnc,F R nF 37


ACCOMPLISHMENT INSTRUCTIONS: Part I, step 14 (cont’d)

b. If holes a~nnt damaged, reinstall existing AN5-6 bolt, AN860D518 washer

under nut only, and existing MS17825´•5 nut. Torque bolt to 180 to 200 inch-

pounds by tightening nut to low side of torque range and, if necessary,continue to tighten until a nut slot aligns with hole in bolt. Install new

MS24665-132 cotter pin (refer to figure 4).

NOTE:

An additional AN960D516 washer may be installed under nutsnlv if necessary,to assure proper alignment of hole on bolt with slots in nut.

c. If holes are damaged, it is acceptable to use AN6-7 bolt(0.375"/0.379"diameter hole)only if an edge distance of 0.58 inches or more can be maintained.

d. If it is determined, prior to reaming existing holes, that an edge distance of

0.56 inches or more cannot be maintained, contact Twin Commander Aircraft

Corporation for further instructions.

e. If it is determined, prior to reaming existing holes, that an edge distance of

0.58 inches or more can be maintained, ream damaged hole or holes to

0.375"10.379" diameter and install ANB-7 bolt, AN960DB16 washer imdar~t

MJY~ and MS17825-6 nut. Torque bolt 300 to 330 inch-pounds by tighteningnut to low side of torque range and, if necessary, continue to tighten until a

slot aligns with hole in bolt. install MS24665-134 cotter pin (refer to Fig. 4).

NOTE:

An additional AN980DB16 washer may be installed under nut only if necessary,to assure proper alignment of hole on bolt with slots in nut. The above listed

hardware is to be procured locally,

15. Make vertical-to-horizontal fairing removeable (refer to Figure 5).

a. Install MS27130-A19 and a20 rivnuts in every other fastener hole in

designated areas unless two adjacent holes were plugged in step 8. Use

-A1B rivnuts through thinner sections and a20 rivnuts through thicker

sections. If two adiacent holes are plugged, install rivnuts in fastener holes

on either side. In areas outside of designated areas, install rivnuts in all

fastener locations. Install rivnuts using Loctite 808 or equivalent. Excess

rivnuts may be discarded. Install fasteners in horizontal spar cap as noted in

Figure 5. Flush plug all other holes with "AD" rivets (salid or blind as reqd.)

CAUTION:

Use drill stops, steel shims, etc. as required to avoid damaging adjacentstructure while drilling rivnut holes. Penet install rivnuts thru vertical or

horizontal stabilizer spar caps.

panF~ CIF ~7


ACCOMPLISHMENT INSTRUCTIONS: Part I, step 15(cont’d)

b. Flush plug holes in fairing that will not be used with MS20426AD4 rivets.

Open holes that will be used to diameter .218-.229. Bond R411N seal to

fairing using EC-1403 or EC-1300L adhesive.

c. Install fairing using two existing screws on forward edge and

MS27039DD1-09 screws and ANgBOPD1OL washers at all rivnut locations.

CAUTION:

Remove all aluminum shavings from the rudder and elevator roller chains.

Relubricate the chains par the applicable maintenance manual.

16. Reinstall left and right rudder control linkage access doon using existinghardware.

17. Reinstall SL 345 access panel or door in belly of fuselage using existinghardware.

18. Install K410008-3 access panel per figure 2 using NAS8603-2 screws.

19. Reinstall vertical-to-horirontal fairing (refer to Figure 5).

20. Touch up paint as necessary.

21. If no damage is found and if Part II is not completed at this time ahotocoov the

Compliance Card. Fill out and mail the Compliance Card copy to:

Twin Commander Aircraft Corp.19010 59th Drive NE

Arlington,WA 98223

NOTE:

Partial completion of Part II is not allowed, All the Part II modlncatlons (exceptstep 1 which is optional) must be completed at one time.

1. Optional to install kit number 58218-507, righthand access panel. The pads in

SB218-507 are opposite hand parts to the parts in SL 345. Refer to SL 345 for

installation instructions.

2. Remove rudder from vertical stabilizer per instructions in the applicable AirplaneMaintenance Manual.

3. Remove rudder torque tube per instructions in the applicable AirplaneMaintenance Manual.

on~e ~n ne


ACCOMPLISHMENT INSTRUCTIONS: Part II (cont’d)

4. Following are instructions for modifying the aft spar web (refer to Figure 8).

a. If the aft spar web is within the crack limits allowed in figure 1, stop drill

crack ends with a 0.125" stop drill hole. Dye penetrant inspect to ensure

crack does not extend past stop drill.

CAUTION:

Do not stop drill into spar caps. Insert thin stainless steel shim stock between

web and spar cap to protect spar cap extrusion prior to stop drilling, ItslaLis not to return to service uotiLtLlgsBEIUrBiS

b. Touch up exposed surfaces with brush alodine and and zinc chromate as

required.

c. Install K410009-1 doubler, K410009-3 filler, K410009-5 angle, and

K410009-7 angle as shown in Figure 8.

5. Following are instructions for modifying the F.S. 409.56 bulkhead upper relief

cutouts and stiffening angle (refer to Figure 7).

a. Permissible to trim inboard edge of leading edge skin of horizontal stabilizer.

Maintain 20 edge margin.

b. If the bulkhead upper reliefs are within the crack limits allowed in figure 7,

stop drill crack ends with a 0.125" stop drill hole. Dye penetrant inspect to

ensure crack does not extend past stop drill.

c. Touch up exposed surfaces with brush alodine and zinc chromate as

required.

d. Install K310025-1 8 -2 straps, (2) K310025-3 fillers, K310025-5 8 -6

doublers, (2) K310025-7 fillers, and (2) K310025-9 straps as shown in

Figure 7.

Note:

~310025-1 8 -2 straps, (2) K310025-9 straps, and (2) K310025=7 fillers are not

required for models 690D and 695A

6. The following are instructions for modifying the lower vertical stabilizer side

skins. Refer to Figure 8.

a. If the side skin is cracked within the limits allowed in Figure 2, then stop drill

the ends of the cracks using a .125 diameter hole. Dye penetrant inspect to

ensure crack does not extend past stop drill.

onne ilncll


ACCOMPLISHMENT INSTRUCTIONS: Part II, step 6 (cont’d)

b. Disconnect deicer boot pressurization lines through skins of vertical

stabilizer.

c. Remove and discard grommet.

d. Cut hole thru right side skin similar to hole shown in Figure 2. Hole is to be

same shape, same distance from existing structure but opposite, and same

size or smaller as hole on left side.

e. Pilot drill (2) K410008-1 lower skin doublers.

f. Mark the door and grommet holes on the K410008-1 doublers and carefullycut holes. Do not cut door in right side doubler.

g. Countersink the hole identified as "A" in Figure 8 .34/.38 X 100 degrees.Dimple holes "A" 8 "8" in the K410008-1 doublers.

h: Install (2) K410008-1 doublers, (2) K410008-7 straps, K410008-3 door, and

(2) MS35489-48 grommets per Figure 8. The K410008-1 doublers may be

trimmed on installation, maintain 2D edge distance.

i. Add (10) new fasteners each side to attach the vertical stabilizer side skin to

the forward leg of the vertical stabilizer rear spar cap. The fasteners to be

added are above the K410008-1 doublers.

Note:

Ten new fasteners each side are not required for models 690D and 696A. On

all other airplanes this area is difficult to inspect and the spar cap leg tapers.To locate these fasteners with proper edge distance it is recommended that a

straight line be drawn between existing rivets that attach the ribs above and

below this area to the spar caps. Locate the fasteners on the straight line at

1.00 inch pitch.

i. Reconnect deicer boot pressurization lines.

CAUTION:

Remove all aluminum shavings from the rudder and elevator roller chains.

Relubricate the chains per the applicable maintenance manual.

7. Reinstall vertical-to-horizontal fairing, access panels, torque tube, rudder, and

rudder hinge cover per applicable Airplane Maintenance Manual.

8. Cycle check deicer boot operation per the applicable Airplane Maintenance

Manual.


ACCOMPLISHMENT INSTRUCTIONS: Part II (cont’d)

9. Touch-up paint as necessary and return aircraft to service.

10. Fill out and mail Compliance Card stating that Palt II of this Service Bulletin was

accomplished.

No change.

Part I: Not significant

Part II: Weight 5 poundsMoment/1000 2.25 in-lbs

SeABESBFFFECTED: No.

None.

BEL;PRD COMPLIA~E: Make an appropriate entry in airplane maintenancerecords as follows:

Part I of Service Bulletin 218, dated May 8, 1994, entitled "Empennage VerticalStabilizer inspection and Modification" accomplished: (date)

ORParts I and II of Service Bulletin 218, dated May 8, 1994, entitled "EmpennageVertical Stabilizer inspection and Modification" accomplished: (date~

PAGE 18 OF 22


.75 INCH TYP MAXIMUM

CRACK LENGTH ALLOWED

VERT~CAL

IN WEB

STAB

SPAR WEB

VERTICAL

STABILIZER

AFT SPAR

INSPECT AREA

AROUND BOLT

HOLES AND RUOOER CONTROL LINKA(IEINSPECT FOR

PICCESS 0O0R IREFIFLANGES OFIN

SPAR CAPJOGGLE AREA

FOR CRACKSOF WEB

INSPECT FOR CRACKS

IN FWD AND AFT CLIPS

HORIZONTAL

STABILIZER

PRONTSFARboa ,(REFI

o oO

a. a a a o~ a

a aa a a,

a a O O a

a a,a oo

oo

O 05 O

o ~j n#es BOLT

a nNBaoDBls wns~ltl

a IUNDER NUT ONLYI.75 INCH

TYP MAX ~I D~MS~dBB&132 CDTFER PIN

Mn78P6 NUT

CRACKa a iOROUE 180 T1 2W IKLBS

LENGTH o

ALLOWED I4PLSIa

O o

IN WEB 8_ O a a O

oO 00 O

INSPECT BELOW

SP*R FOR CRPICKS

0000000

NOTE

\’IEW LOOK1NG FORWARD 00 NOT INSTALL I\NY W~SHERS

.T FUSELAGE STA. 409:56 UNDER HE~D OF BOLT

FIGURE 1

Page 14 of 22


1-7

7" cl

I’ RUDDER HINGE

iCOVER

STnslLIZER RIB BELOWIREFI

Fan ~RncKs

INSPeCT FOR CRIICKI

~ROUND RIVETJ I\TT~CHINO

AIBSTO SKIN

FIOWE 3

Page 16 of 22


I\DDITIONAL W/\SHER MIY BEUSED IF AEaUIRED TO ~LIGN’10LE iN BOLT WITH SLOT IN NUT ij

YIEW SHOWING INCDRRECT YIEN SHOWING CORRECTOF HOLE IN BOLT ILIONMENT OF HOLE IN BOLT

FIGURE 4

Page 17 of 22


EX,ST,NG SK,N a

F.S. 409.56

BULKHEAD

K310025-9 STRAP 7 iiil

K310025-5

K310025-7 FILLER

K310025-1 STRAP" .01-.031~e /I

EXISTING FAIRING---~

FWD

VIEW AARLL MODELS EXCEPT 690D AND 695A

F. S. 409.56, 11

K310025-5

EXISTING FAIRING

jiFWD

vlEw AAMODELS 690D AND 695A ONLY

FIGORE 7

SHEET 2 OF 2

Page 21 of 22

COMPLIANCE CARD

Page 1 of 2


EMPENNACIE VERTICAL STABILIZER INSPECTION AND MODIFICATION

PLEASE PILL IN THE REPUESTED INFORMATION AND CXECK THE

APPROPRIATE BOXES.

MODEL: AIRPLANE SERIAL NO. TOTAL TIME (AOURS)

AIRPLANE REGISTRATION NO. Airplane Age (YEARS)

OWNER NAME

ADDRESS

City State Zip

TELEPHONE NO.(

PART I INSPECTION

Vertical Stabilizer Skin:

i No damage found.

Crack(s) within S8218 limits.

I i Crack(s) exceeding SB218 limits.

Vertical Stabilizer Rear Spar Web:

No damage found.

i Crack(s) within 58218 limits.

Crack(s) exceeding SB218 limits.

Horizontal Stabilizer Spar Web:

i No damage found.

Crack(s) within SBZ18 limits.

i Crack(s) exceeding SB218 limits.

Forward and Aft Clips:

i No Damage found.

Crack(s) in forward clip.

Crack(s) in aft clip.

%s

COMPLIANCE CARD

Page 2 of 2

PART I INSPECTION, continued.

Vertical Stabilizer Ribs:

No damage found.

Crack(s) found.

Rivets, Hiloks, Hucks, and Lockbolts:

No missing or loose fasteners found.

Missing fastenerls). Where?

Loose fastener(s). WhereP

Bolt Holes which attach Vertical Horizontal Stabilizers:

No damage found, fasteners correctly installed.

Fastener(s) found incorrectly installed tie. missingwashers, missing cotter pins, etc.)

Crack(s) within SBals limits.

Crack(s) exceeding SB218 limits.

INSPECTED BY: TELEPHONE NO.(

DATE: SIGNATURE

EART I1: MODIFICATION:

Modifications determined not to be required at thistime.

Modified by:

TELEPHONE NO.(

ADDRESS

CITY STATE ZIP

DATE

SIGNATURE

21

-----MANDATORY

Se rvice Bulletin AIRCRAFT CORPORA TION(8010.58m Dr. NE, Adkgtm, WA Dllp37832

Ta: FsC (580) U51112

SERVICE BULLETIN NO.: 220 DATE: Februaryl, 1995

MANDATORY REDUCTION IN SPEED DURING TVRBULENCE

MODELS AFFECTED: MODEL 680T/680V, SERIAL NO. 1473 THRU 1720MODEL 680W. SERIAL NO. 1721 THRU 1850MODEL 681, SERIAL NO. 6(101 THRU 6072MODEL 690, SERIAL NO. 11001 THRU 11079MODEL 690A, SERIAL NO. 11100 THRU 11344

MODEL 6906, SERIAL NO. 11350 THRU 11566MODEL 8g0C, SERIAL NO. 11800 THRU 11735MODEL 890D, SERIAL NO. 15001 THRU 15042MODEL 695, SERIAL NO. 95000 THRU 95084

MODEL 695A, SERIAL NO. 96000 THRU 86100

MODEL 6956, SERIAL NO. 98201 THRU 96208 INIA


There have been two accidents involving Model BgO senes aircraft resulting in loss of the aircraft, due to Dencountenng turbulence while descending at high airspeed. The purpose of this bulletin is to re-emphasize to

operators the importance of always reducing airspeed before starting descent or immediately upon experiencing Atu~ulence at any time.

Excessive airspeed in turbulence can cause structural damage or loss of the aircraft. Adverse gusts associated Owith turbulence cause an instantaneous increase in angle of attack. A sudden change in angle of attack producedby gusts creates increased loads which can lead to structuraldamage. Reducing airspeed reduces the effect of Rgust induced loads from turbulence. Maintaining airspeed at Turbulent Air Penetration or#aneuverlng YSpeed (hoth well below the red-line limits of Vnn01MIO)~ provides an increase in structural margin when

encountering turbulence. This is extremely impoRant if areas of forecast or reported turbulence cannot beavoided. or even in cruise Right, if turbulence is encountered. Since a finite period of time is required to reduceaircran speed from the onset of turbulence, a speed reduction should be accomplished in anticipation of suspectedturbulence areas, whenever possible. The need for additlonel airspeed matgin in descent arises because of theother unknowns introduced by descending from one air mass to another, and dmloulty of reducing speed whiledescending.

Operating the aircraft at Maneuvering Speed is the safest speed forfllght in turbulence. ManeuveringSpeeds are listed in the "Limitations" section of the AFMIPOH.

Specific guidance, including a Placarcl and AFMIPOH revisions is provided in this Service Bulletin to adviseoperators of ta~get speeds, as a function of night conditions.

PAGE I OP 5


1. Service Bulletin 205, "VA Placard Installation", December 20, 1985. Issued to emphasize importance of robserving VA speeds. A waming placard was added to the instrument panel and a rev.ion was made tothe Airplane Flight Manual or Pilots Operating Handbook of the venous models of the 690 and 695 senesTwin Commander airplanes.

2. Airman’s Information Manual (AIM), ’7urbulence Reporting Criteria Table". Lists turbulence Intensity andaircraft reaction to vanous intensity levels. Copy included with this Service Bulletin.

COMPLIANCE:

Part I: (Order appropriate service kit) Upon receipt of this Service Bulletin.

Part II: (Install kit) Upon receipt of Service Bulletin Kit.


Owner/Operator. A&P Mechanic (or equivalent).

APPROVAL:

Engineenng design aspects are FAA approved.

ESTIMATED MAN HOURS: G

One hour,

PARTS INFORMATION:

Pads required to comply with this Service Bulle8n may be purchased from your nearest Twin Commander FactoryAuthorized Service Center under kit numbers listed below:

L(Ui~Le hdaPEL PLACARD Bn~e58220-1 660T 110205-1 Airplane Flight Manual 1558220-2 6B0V 110205-3 Airplane Flight Manual 1358220-3 B50W 110205-3 Airplane Flight Manual 1058220-4 881 110205-5 Airplane Flight Manual 1358220-5 690 110205-7 Airplane Flight Manual 25$82206 690A 110205-7 Airplane Flight Manual 32$8220-7 B908 110205-9 Pilots Operating Handbook 2458220-8 6g0C 110205-11 Pilafs Operating Handbook 2588220-9 6908 110205-13 Pilots Operating Handbook 1458220-10 685 110205-11 Pilots Operating Handbook 1558220-11 685A 110205-15 Pilots Operating Handbook 2488220-12 6958 110205-17 Pilot’s Operating Handbook 11

SPECIAL TOOLS: None. C

pAoe 2 OP S


I. Incorporate in the Airplane Flight Manual (AFM) or Pilot’s Operating Handbook (POH), the appropriaterenslon sent by Twin Commander as part of the Service Kit.

2. Attach the placard received from Twin Commander as part of Lhe Service Bulletin Kit on the windshieldcenterpost.

Mi( me anachsd C.mpllancs Cam. Se~Nre B.letb No. 220, t. Twin Commander*ircran


SPARES AFFECTED: None.

WEIGHT AND BALANCE: No change.

PUBLICATIONS AFFECTED:

AFM or POH revision to include procedures for Flight in Moderate to Severe Turbulence and Recovery frominadvertent Overspeed and table of airspeeds for safe operation,

RECORD OF COMPLIANCE:

Make an entry in the airplane maintenance records as follows: SERVICE BULLETIN NO. 220, DATED(Oate, ENTITLED "MANDATORY REDUCTION IN SPEED DURING TURBULENCE. ACCOMPLISHED(Datel

COMPLIANCE CARD:

Upon completion of all actions required under Service Bulletin 220. complete the attached Compliance Card andmail (postage is prepaid) to Twin Commander Aircraft Carporation.

FACE 3 OF 5

TURBULENCE REPORTING CRITERIA TABLE

INSIDE REPORT(NOINTENSITY AIRCRAFT REACTION AIRCRAFT I TERM-DEFMITION

Turbulence that momentarily Occupants may feel Occasional-Less than 113causes slight, erratic changes in a slight nrrain against of the time.altitude and/or attitude (pitch, roil, seat belts or shoulderyawl. Report as Lieht Turbuience;´• straps. Unsecured Intermirtenr-113 to 2/3.

Lieht or objects may be displacedTurbulence that causes slight, rapid slightly. Food service Continuous-More that 2/3.and somewhat rhythmic bumpiness may be conducted andwithout appreciable changes in little or no difficultyaltitude or attitude. Report as is encountered in

LiPhr~hpn´• walking.

Turbulence that is similar to Light Occupants feel deiinite P~PTE.Turbulence but of greater intensity. mlinr against near belts

Changes in altitude and/or attitude or shoulder straps. I. Pilots rhould reportoccur bur the aircraft remains in Unsecured abjecrs are locarion(s), rime (UTC),positive control at all rimes. It dlsiodged. Food service intensitv, whether in or

usually causes variations in indicated and walking are difficult. near clouds, altitude,MPrlewll airspeed. Repon as Mpderate type of aircraft and,

rurbulence:’ when applicable,or duration of mrbulence.

Turbulence that is similar ra Lighf t2. Duration may be based

Chop but of greater intensity, on time between twoIt causes rapid bumps orjoltr locations or over awithout appreciable changes in single location. Allaircraft altitude or anirude. locations should beReport as MPd~ateChPp. readily identifiable.

EXAMPLES:

a. Over Omaha, 12322,Turbulence that causes large, Occupants are farced Moderate Turbuience.abrupt changes in altitude and/or violently against rear in cloud, Flight Levelamtude. It usually causes large belts or shoulder stmpp. 310, 8707.

SeYere variations in indicated airspeed. Unsecured objects are b. From 50 miles southAircrafl may be momentarily tossed about. Food of Albuquerque to 30out of control. Report an service and walking are miles north of Phoenix.Snura3CurbulenEe,´• impossible. 12102 to IZ~OZ,

occasional Moderate

Chop, Flight LevelTurbulence in which the aircraft 330, DC8.is violently tossed about and is

Extreme practically impossible to control.

It may cause srmctursl damage.Repan as Extreme Turbulence."

High level turbulence (normally above 15,000 feet ASL) not associated with cumuliformcloudinem, inciuding thunderstorms, should b~ rsponed as CAT (Clear Air Turbulence) ipreceded by the appropriate intensity, or light ormoderate chap.

PAGE 4 OF 5

COMPLIANC1~ RECORD

BULLETIN NO. 220

MANDATORY REDUCTION IN SPEED DURING TURBULENCE

MODEL: AIRPLANE SIN REG. NO._

TOTAL TIME IHOURS)

OWNER NAME:

ADDRESS:

TELEPHONE NO: AIRPLANE AGE:

COMPLIANCE WITH SERVICE BULLETIN 220.

DATE

WORK PERFORMED BY:

COMPANY

FAX

PA(IB 5 OF 5

SERVICE PUBLICATIONS ~"Y

revision notice A/RCRAFT~ T/ON(9010 19" Dr. N.e. n,llnssn, wa 8822~´•1812

ral: gee) 4Jse7sl pnx:(3(PJ dSB´•1HZ


Revision No. 2

Release Date: August 18, 1997

WING LEADING EDGE ATTACHMENT INSPECTION_AND MODIFICATION

REVISE KIT 58223-503 EFFECTIVITY

Change to read:

KIT NO. S8223´•503

Qty Part Number Description Model Eftectivitv

1 K17046717 LEFT BRACKET ALL 690C, 695, 6908, 695A,1 K170467-8 RIGHT BRACKET &6958

1 K170467-11 LEFT DOUBLER

1 K~7046712 RIGHT DOUBLER

1 FIBERGLASS CLOTH

SERVICE PUBUCATIONS ~r~"Y

C~MIIJILI, WLIEIP

revision notice A/RCRAF’I~CORPOR4 nON1P0(010’" O,. H.e. i\rlington. W*

r´•I: FaX: (560)

Sen/ice Bulletin No. 223

Revision No. 1

Release Date: May 8. 1997

WING LEADING EDGE ATTACHMENT INSPECTION AND MODIFICATION

REVISE BY WHOM. WORKWILL BE ACCOMPUSHED:

Change to read:

NOTE:

IT IS RECOMMENDED, BUT NOT REQUIRED, THAT THIS SERVICEBULLETIN BE COMPLETED BY AN AUTHORIZED TWIN COMMANDERSERVICE CENTER.

REVISE ACCOMPLISHMENT INSTRUCTIONS AS NOTED:

1. Revise Page 7 hole callout as follows:

.312 DIAMETER HOLEDRILL IN FAIRING ONLY

SEAL HOLE WITH SEALANT AFTER

DOOR INSTALLATION

2. Revise Page 11, Note 15 to read’FOR ALL MODELS EXCEPT 630D,695A, AND

6958, GO TO ITEM 17.

------MANDA 70RY

jlwrw~e rvice Bulletin COM~AIANDER

A IR CRA FT C ORPORA nON19110 5Rh Dr. NE. Allingtm. W~ OBPj~7832

Tal: 1360) U58197. Far (380) 4351(12

Service sulletin No. 223 Date: October 24, 1996

_WING LEADING EDGE ATTACHMENT INSPECTION AND MODIFICATION

EEE~LK: ~MeDLL NO.

500 SERIES AIC (500, 500A, 5008, 5008, 500U, 520, 560, 560A, 5608 and 560F)600 SERIES AIC (680, 6808, 680F, B80FL, 680FLP, 680FP, 6807, 680V, 680W,

681, 685, 690, 690~, 6908, 690C, 690D, B95, 695A and 6858)700 SERIES AIC (720)

Twin Commander Aircraft Corporation has received several tepo~s of aircraft with damaged leadingedge to fuselage attachment(s). These reports include: Cracks in the wing to fuselage attachmentbracket(s)/ strap(s), wing leading edge close-out(s), wing station 24.0 rib(a) and fuselage frame(s). Iflan unrepalred, this damage could propagate to the point of failure in the wing leading edge tofuselage attachment.

AThis Service Bulletin defines the requirements for inspection, modification and repair of these areas.Future inspections can be accomplished thru the added wing access door.. N

ID

PART I: MODIFICATION 8 INSPECTION AModels 520 8 560 are excluded from the wing leadingedge secess doon, and inspection per PART I I T

Provides Installation instructions for wing leading edge access doors. The access holes will provideO

adequate means for inspection of the wing leading edge to fuselage attachment area. The Initial Rinspection must be performed at or before total airframe time or within ifbeyond 690ehours. If no damage is found, the airplane may be returned to service and reinspected Yat intervals. If damage is found, PART II is required. After the access door has beeninstalled, inspection of the bracket(s) I strap(s) can be done thru this access door and removal of thefalrings is not required. If no damage is found and new bracket(s) I strap(s) an, installed through thewing leading edge access doors and the PART II inspection is not accomplished at that time, thePART II is required on or before the next 19PB_hP~. The reinspection of the new bracket(s) Istrap(s) will be required at 69Mdeurs and SE 223 inspections will be repeated as applicable fromthat time.

PARTII: INSPECTION& REPAIR

If damage is found during PART I, before further flight PART II (INSPECTION 8 REPAIR) must beperformed. After completion of PART II, PART I reinspection is required at 890ehour intervals for allareas, except as noted in PART III.

Medals 520 8 560 only, at or before 6.900 hours or within 1Pehnurs it beyond 5.000 hours, PART IIIINSPECTION g REPAIR) must be pe~ormed. PART II reinspection is required at 89Mbou1 interval.for all areas, except as noted in PART III.

Page 1 of 25


COMPLIANCE: (cont.)

PART m: INSPECTION OF F.S. 144.0 (EXTENDED FUSELAGE) I F,S. 100.0 (SHORT FUSELAGE)(All models except, BgOC and B95 Reference Service Bulletin No. 213)

If PART 1l is not accomplished PART m must be complied with at 8.000 hours total airframe time for pressuri2edairplanes and 12.000 hours for unpressuriled airplanes with reinspection required at 1.000 hour intervals.


A 8 P MECHANIC (OR EQUIVALENT), AND A CERTIFIED NDT INSPECTOR (OR ECIUIVALENT) PERINSPECTION LIUALIFICATIONS.

NOTE:THIS MODIFICATION MUST BE COMPLETED ONLY BY AN AUTHORIZED TWIN COMMANDERSERVICE CENTER.

APPROVAL:

MODIFICATIONS AND REPAIRS DESCRIBED BY THIS SERVICE BULLETIN ARE FAA DER APPROVED.


SE 112’INSPECTION OF WING RIB AT W.S. 24.07 FOR INSTALLATION OF RIVETS’: IT IS REQUIREDTHAT SE 112 BE ACCOMPLISHED AT THIS TIME.

SE 213 "WING FATIGUE INSPECTION AND MODIFICATION" IT IS RECOMMENDED THAT SE 213 BEACCOMPLISHED ON THE MODELS 8809 AND 885, IF PART n of TH1S SERVICE BULLETIN IS REOUIRED.

IF THE 12 OR 15 YEAR INSPECTION OF THE AIRPLANE 18 DUE, IT IS RECOMMENDED THAT THEINSPECTION BE ACCOMPLISHED IN CONJUNCTION WIM PART n of THIS SERVICE BULLETIN.

ESTIMATED MAN HOURS: (INCLUDING ACCESS PER SIDE

PART I:

WIND LEADIND EDGE ACCESS DOOR MODIFICATION 78 HRSINSPECT FORWARD ATTACH. BRACKET(S)/ STRAP(S) (FROM WIND ACCESS HOLE) 4 HRS

PARTI: i 82 HRS

PART n:

REPLACE FWD ATTACH. BRACKET(S) I STRAP(S) (FROM WING ACCESS HOLE) 3 HRSINSPECT WIND LEADING EDGE CLOSE-OUTS (FROM INSIDE 1171E WING) 22 HRSINSPECT W.S.24,0 UPR L LWR RETURN FLANGE RADIUS (FROM INSIDE THE WIND) 22 HRSINSPECT FUSELAGE FRAME WHERE tEE BRACKET ATTACHES (FROM INSIDE THEFUBELAOO 25 HRSINSPECT INBD SIDE OF WS. 24.0 ATTACH. BRACKET (FROM INSIDE ME FUSELAGE) 24 HRSINSPECT FRAME TEE BRACKET (SENCH INSPECTION) 4 HRS

PARTB: 3 108HRS

Page Z of 25


ESTIMATED MAN HOURS: (cont.)

PART m:

REMOVAL OF AIRCRAFT INTERIOR FOR ACCESS TO FUSELAGE 100.0 144.0 FRAMES 6 HRSINSPECT FWD SIDE OF FUSELAGE FRAME WHERE TEE B~ACKET ATTACHES 1 HRS

PARTIII: 7 HRS

PARTS DATA:

PART I: ONING LEADING EDGE ACCESS DOOR KITS ONLY BOTH LEFT 8 RIGHT WINGS)

KIT NO. 58223501

PadP~umber OesodPlion Model Effectivity1 K170487-1 LEFT DOOR ALL 500, 600 AND 720 SERIES AIC1 K170487-2 RIGHT DOOR EXCEPT 520 580

1 Klj04b7-3 LEFT TEMPLATE1 K17D4b7-4 RIGHT TEMPLATE

1 K17048’1-5 LEFT DOUBLER

1 K170467-8 RIGHT DOUBLER28 NAS1088-A08 NL~PLATE

26 NASBB02-2 SCREWS

PARTII: (RfPAIRS BOTH LEFT AND RIGHT WINGS)

NOTE:THE FOLLOWING KITS WILL REPAIR DAMAGE 70 ONLY THE BRACKET(S)/ STRAP(S) THATATTACH THE WING LEADING EDGE CLOSE-OUT TO THE FUSELAGE FRAME AS SEEN THRU THEPART I ACCESS HOLES. FOR REPAIR OF DAMAGE FOUND IN OTHER AREAS, PARTS MUST BE

REPLACED OR AN APPROVED REPAIR MUST BE INSTALLED PRIOR TO RETURN TO SERVICE.

KIT NO. 88223-503

otv Part Number DegcriDtion Model Effec(lvilv1 K170487-7 LEFT BRACKET ALL 69OC, 695, B90D 5 6958

1 K170487´•8 RIGHT BRACKET 895A EXCEPT S~ 96083, 88, 89,1 K170487-11 LEFT DOUBLER 75, 78 5 85

1 K17MB7-12 RIGHT DOUBLER

1 MIL-Y-1140 FIBERGLASS CLOTH

KIT NO. 58223505

My P4LNvmber ~escrfdlon Model Effectlvnv1 K170487-8 LEFT BRACKET ALL 885, 6g0A 5 6808

1 K170467-10 RIGHT BRACKET 690, S/N 11041 ONLY

1 K170467-13 LEFT DOUBLER1 K170487-~4 RIGHT DOUBLER

1 MIL~-1140 FlBERGLASS CLOTH

KIT NO. 58223-50’1

ah Pad Number DesPdPtlon_

Modal Enectlvltv1 K170487-15 LEFT BRACKET ALL 880 EXCEPT S/N 11041

1 K178487-18 RIGHT BRACKET

1 K17W87-17 LEFT DOUBLER

1 K~70487-18 RIGHT DOUBLER

1 Mll´•Y-1140 FIBERGLASS CLOTH

Page 3 of 25


PARTS DATA: (oont.)

KIT NO. 58223409

gtv Part Number DesclfPtlon ModelEffectivitv1 170052-5 LEFT UPPER STRAP ALL 880T, 680V, 680W a 6811 170052-6 RIGHT UPPER STRAP 880FL a 680FLP. SIN 1281 SUBCI.1 170052-7 LEFT LOWER STRAP

1 1’10052-8 RIGHT LOWER ST~AP-1 MILY-1140 FIBERGLASS CLOTH

KIT NO. 58223-811

1 170038-5 LEFT UPPER STRAP ALL 500,1 1700388 RIGHT UPPER STRAP ALL J60A, 5808. 580F a 7201 17003&P LEFT LOWER STRAP ALL 680, 6806, 880F a 680FP1 170038-8 RIGHT LOWER STRAP 680FL a 880FLP, S/N 1281 1280.

MIL-Y-1140 FIBERGLASS CLOTH


i. HL1BPBS/ -8 PIN, HL20P&5 Is PINS, HL86-51 -B COLLARS. HL94-5 /-B COLLARS, MSZ0470AD4. AD5

RIVETS, MS20426AD3, AD4 RIVETS, CR3242 AND CR3243 RIVETS.2. DESOTO 825-308 POLWRETHANE PRIMER USED FOR TOUCH UP ON PARTS FURNISHED WITH

TH1S KIT.

3. EC-1300L ADHESIVE (3M) OR EOUIVALENT.

4. M5212865 OROMMET.5. .60 INCH SPIRAL WRAP (ICORALLY CORP.)8. PR890A1R SEALANT

SPECIAL TOOLS:

NONE

INSPECTION RE9UIREM~NTS:

1. PERSONNEL OUALIFlCATIONS

a. Level Il Uquld Psnetrant

b. Vision acully requirements of MILSTM1OE, or latest revision.c. Documented trahlng in accordance with MIL-STM1OE, or latest revision and recommended practice

SNT-TC-1A Of the Amedean Society for Nondestructive Testing,

2. MATERIALS AND E(IVIPMENT

a. Solvent Cleaner, SKC´•NF (Magnenux) or equivalent per Mltl-25135.b. Water Washable Pluoreseent Penetrant. ZL60C. Level II (Magnanux) or equivalent per MIL-I-25135.c. Non-Aqueous Developer, SKD´•NF Flaenanux) per MIL-I-25135 or equivalent.d. 28-100 Blackllght (Magnanux). 10hv, 115v, 60Hr or equivalent.a. Inspection mlrmr.

f. Cleaner, Penetrant and Developerto he from the same manufacturer.

3. PROCESS

a. Per MIL-STaa8BB.b. Sensltlvlty- Type I. Method C, Level 3.

Pa(le~ of 26


PART I -ACCOMPLISHMENT INSTRUCTIONS IM013IFIC~ION 8 INSPECTIONI

1. Disconnect baneries.

2. De-fuel airplane as outlined in the Airplane Maintenance Manual.

3. Protect aircraft fuselage and cabin windows directly forward and ah of the wing leading edge with an appropriatemedium. (See Figure i, far items 3 thru 8)

4. Remove upper wing skin access doom between Wing Station 24.0 and 38.0 ~bs, fomald of the Main Spar.

5. Push back the fuel cell located between Wing Station 24.0 and 38.0 ribs lomad of the Main Spar as outlined in

die Airplane Maintenance Manual.

CAUTION:

a) IF THE FUEL CELL IS NOT PUSHED BACK. REMOVAL OF THE FA1RINO FASTENERS MAY

DAMAGE THE FUEL CELL.

b) USE CARE IN REMOVING THE FAIRING ON PRESSURIZED AIRCRAFT SO THE PRESSURE SEAL,

WHICH MAY ADHERE TO THE FAIRING DUE TO EXCESS SEALANT, IS NOT DAMAGED.

NOTE:

FUEL CELL MUST BE DISCONNECTED AND REMOVED IF PART II OF THIS SERVICE BULLETIN IS

REOUIRED.

a. Cautiously drill out rivets and remove the fomarrl inboad left and right hand wing leading edge fairings.

7. If airplane is equipped with factory supplied inboard delcer or abrasion boots, remove locally.

a) Use Methyl Ethyl Ketone (MEK) or Toluol as a dissolving agent forthe adhesive used to adhere the boot to

the leading edge of the wing.

b) Loosen an inboard area olthe boot lame enough to grab hold of.

c) Pull the deioer boot while applying liberal solvent, with an even, steady pulling power until a 10 inch section

has been peeled outboa~d from the inboard edge.

d) Fold boot back and tape to wing.

CAUTION:

DO NOT RUSH, EXCESSIVE FORCE MAY CAUSE UNREPAIRABLE DAMAGE TO BOOT.

8. Clean excess sealer residue from wing leading edge with (MEK) and plastic scraper.

Page B of 25


PART~I- ACCOMPLISHMENT INSTRUCTIONS (cont.)

PART I-ACCESS

PUSH BACK FUEL? r REYOM ACCESS EXEEsICELL (mM I) WOR (ITEM SEALER (mM LI)

REMOM FAIRING(IrrMB)

FUSELAGE(REF.)

REMOVE BOOT FOR(D.O INCHES (ITEM I)

I II II II I /C4

I

I I

PROTECT FUSELAGE/vro WINOOWS (ITEM S)

FOR BVBSTI’IUTE FASTENERSSEE PART I. (ITEM l8)

FIGURE1VINV LWKIN(I Am ~1NBOARD gJ WH WING LEADINCI EWE

LeeTWINOOPPOSm

8. Place the applicable K170487-3 -4 template on the wing leading edge with the inboalri lawar edge flush with the

wing skin (W.S. 24.0) inboa~ edge. Equal space the upper and lower edges between the existing inboard

outbaard civet lines. Mark ail fastener locations and the skin cut-out. If existing fasteners interfere, install hush

or double gush AD rivets as required. Pick-up existing rivets whets 2 x fastener diameter minimum edgedistance and 4 x fastener diameter m$imum pitch can be maintained. (See FiBure 2 or 2A for hems 8 thru 12)

CAUTION:

ON MODELS 690, A, B, C, D AND 696, A, B THE CONTROL CABLES ARE LOCATED DIRECTLY AFT OF

LEADING EDGE SKIN, W(ERCISE U(TREME CAUTION NOT TO CUT OR NICK CONTROL CABLES

10. Cut the leading edge skin to the inside doubler line. 00 NOT CUT ANY DEEPER THAN NECESGARYI It is

recommended that the tap inboad outboard cut be made first, then wt dorm one inch ham the outboa~ upper

comer. Bend the nap forward. Locate the engine aontml cables ton sppllcab* models) and move them to the

upper cut with safety wire, continue wtting the access hole.

11. Place the K170467-2 door snug an the wing leading edge skin with the inboard edge hush with the wins skin

inbaard edge. Equal space the door between pilot holes. Mad: amund the outside of the door. Maintain a

minimum of 2 x diameter edge distance (center of hole to edge of pert) an all fasteners. Remove the door end

make the final skin wt for a gush door installation.

Page 8 of 28

SERV1CE BULLETIN NO. 223

PART I-ACCOMPLISHMENT INSTRUCTIONS

12. Remove any excess sealer from famed sumce of wing leading edge attachment bracket(s) I strap(s).

13. inspect wing leading edge attachment bracket(o) or srrap(s) for cracks with special attention to the bend radius

and adjacent to rivets, using Fluorescent Penetrant Method. (See Figure 3, A, or B for applicable Models)

NOTE:

Close visual inspection is required, using Fluorescent penetrant method as an aid in disclosingcracls. Carefully remove sealants ornnishes as necessary in order to allow inspection of the

strunuralelemenle. Moderate hand pressures applied between parts, in order to produce anyrelative movement allowed, may assist in the detection of cmcks in parts or sheared or workingfasteners. Also, observe any rub marks indicating relative movement of parts under load.

Inspections refer to both left and right hand sides of the simama unless specified otherwise.

PART I´•INSPECT16N

INsPECT FOR CW\CKS (ITEM 13)IF CW\CKS ARE FOUND. PART 11 18 RE(IUIAED.

FINISH CUT IF NO CR~CKS *RE FOUND. CONTINUE WITH(REF) ITEM (5.

ENGINECONTROL REMOVE UCUSUBLECUT-OVTC*BLEs (REF.) SULER nIEH 12) MODELS seOC. (IBJ. seOD

O OO

OFUSEL90E(REF)

O I;1 10

O O O1 O

--L I

KODELS BeOh L18(la a

888 ~N HO(’I ONLY

(rrH iS)

mNe LEADING EWEHolE´• ATTACHMENTBR*CKST

IF cR*cKs *RE FOUND OH dNB aoe. MODELSBOTH LEFT a RIGHT BTUcKETS YUST

BIREPUCED. seo/l 8808. tiB(IC. IBS.(195A~L1958

FIOORE3 sea snr ONLY

VIEW LOOKING AFT a INBOARO 81 RM mNO L~V)INO EOiE

page B of 26


PART I-ACCOMPLISHMEN7 INSTRUCTIONS (cont.)

PART I-INSPECTION

INSPECT FOR CRACKS (ITEM 1J)IF CRACKS ARE FOUND. PART II IS REOUIRED.

FINISHCUT IF Nb CRACKS ARE FOUND. CONTINUE WlTHIREF.) ITEM le.

CONTROL REMOYE EXCESSC*sLss (REF.) SWER (ITEM 12)

O OO oV

oi FUSEV\OEO

(RIF.)I

0’o o

O O 0~o

U)h~ROLW\BLECUTOUTMODEL (iQO ONLY. EXCEPTSM 1(061

(ITEM iS)

WING LEADING EDGENOTE: hTTACHMEMsRACKET

IP CR*CKS*Re FOUND ON aNe SIDE. MODELSSOTlI LEFT L RIGHT BRACKETS MUST

BPIREPUCED. (iBO. EXCEPT S~ 1(M~

FIOORE3AVIEW LOOKING AF7 b INBOARD 69 RM WING WING EDGE

LEFTHANDOPPMITE

Pass 10 ar 21


PART I-ACCOMPLISHMENT INSTRUCTIONS (cont.)

PART I-INSPECTION

FINISH CUT REMOVE EXCESS

(868.) SEALER (ITEM 12) ssoTNNV. SB1.S/N (181 SUB~.

INSPECT FOR CRACKS (ITEM 10)IF CRACKS ARE FOUND. PART 1118 REOUIREe. MODELS 5001AlslSN. (BO/WFIF Na CRACKS ARE FOUND. CONTINUE WITH BIIOMkP It~OFUFLP 9~ (?siITEM Iii. i i I 1 -1290 ONLY) MODELS ~20 a 1110

EXCLUDED

~O do

oUoo

FUSELAGEO(REF.I

O o o

(ITEM 13)

WING LEADING EDGENOn~ ATTACHMENTSTWIPB

IF CRACKS me Faum, ON aNE sOm

FIOURE38VINY LOCKING AFT a INBOAIO 80 wn WING LEADING EDGE

LEFTH~UIDOPWSITE

14. If no udcks are found in the wing leading edge attachment bracket(s)/ strap(s), continue with next step.

(F CRACKs ARE FOUND. COMPLIANCE WITH PART n is REQUIRED before con~lnuing with access door

installation.

15. Install wing leading edge acCessdoor modification pads as indicated. (Ses Figure 2 or 23 for applicable Medals)

FOR ALL MODELS U(CEPT 890D, 895A AND BBSB. GO TO ITEM 18.

Page 1( of 25

SERVICE BULLETIN NQ. 223

PART I-ACCOMPLISHMENT INSTRUCTIONS (cont.)

18. On mpdels 890D, 895A and 8958 series aircraft, inspectthe Wing Station 24.0 Ribs (fmrn inside the wing).

a) Inspect the rib radius for cracks one inch fomsd and one inch aft per Figure 4.

b) Inspect the rivet line at Fuselage Station 185.0 for cracks as shown per Figure 5.

NOTE:

IF CRACKS ARE FOUND IN THE RIB PARTS MUST SE REPLACED OR AN APPROVED REPAIR

MUST BE INSTALLED PRIOR TO RETURN TO SERVICE.

c) If no cracks are found, continue with ned hern.

PART I-INSPEC710N

UIOTINOMS1OI~AM

Qw.s.naonle(REF,1

’lmP02838R4CKET,,

,,I~, .II

(REF.) I j1703(7~(BANOLE

(R"’ /j!la -e

Y~ O 1111 (REF.)

OI i

-F

iOO

JII/iii

INSPECTfORCRICKSINLOWER RIB RAOIVS, ONE

INCH RVDI~FT OF U1SnNORNETLINE

FIOUREIVI~W LOWER RIB

Page 12 ct 28


PART I-ACCOMPLISHMENT INSTRUC710NS (oant~rn´•

17. Sealant and Finishes must be reston,d per recommended Aircraft Maintenance Mamsl practices affer

modification and inspections are completed.

NOTE:

a) RESEAL CABIN WITH PR 8901\112 SEALER PER MIXING INSTRUCTIONS.

b) FOR LOCAL TOUCH UP ON EIXISTINO STRUCTURE, USE ZINC CHROMATE. DO NOT MIX

CHROMATE AND POLYURETHANE PRIMERS ON THE SAME PART. ALL NEW ALUMINUM PARTS

FROM TWIN COMMANDER ARE POLYURETHANE PRIMED.

18. Reinstall faidn8s. Existing cabin sealer may prevent reinstalling factory rivets at the lower faidng row. It is

acceptable to substitute CR3242 or CR3243 ilvets same size as removed for the existing factory rivals (SeeFigure 1)

19. Reinstall items removed Foam. Fuel Bags, Doon, Etc.

20. Pressure test the cabin for leaks per approved methods, for applicable models.

21. Resaal the deice boots perthe applicable Aircraft Maintenance Manual.

Page 13 of 26


PART II-ACCOMPLISHMENT INSTRUCTIONS IINSPECTION& REPAIR)

The following areas are to be inspected using Fluorescent Penetrant Methods per Pan I, both left and right hand wing

1) Thru the upper wing skin aCcess door:

a) Remove sealant from all areas requiring inspection below.

b) Inspect for cracks in the bend radius of the wing leeding edge close-out, both upper and lower nanges.Inspect from the Wing Station 24.0 rib outboad for a minimum of B.O inches. (See Figure 5)

c) Some models have a vertical nange or angle that attaches the leading edge dose-out to the Wing Station

24.0 rib. Inspect for cracks in the nange or angle from top to bottom.

d) Inspect for cracks inlhe bend radius of the wing station 24.0 rib, both upper and lower nanges. Inspectfmm the wing leading edge closeout to the main spar caps.

e) inspect for cracks in between rivet lines and around beads of the Wing Station 24.0 rib. Inspect from the

wing leading edge closeout to the main soar caps.

PART II-INSPECTION

INSPECTFOR UPPERWINOSKIN(REF.)INBPECrFORcWIU(s

WINQLUV)INOEWE I cnEu 1, a

IN BEND RMIUs OF cA*CKs

CL08eOLIT(rrM D) o

INSPECT aLI.(XIINW

O

b~ob.%T~ a

Olj~ a

o~o oo___o__p o LIo o o

a

;OIJO/n I ’I wnG sanaNI.ORIB(REP.I

OI I OI OI I O

O I INSPECIFORCR4CISD D /o

o r(mM(, a)

ol I o ol I O

a a INspEcTponw\cnsIN BENo AM)IUGOF

a W.s. 2~.0 RIB (mM I, d)a

a

LE*oIMO eWE IUDSE*IUT(REF´•) I

neuow SE*UM

mr*l.´•)

LOWERWINOSKIHIREF.)

UP OacePrsemaseuRNEIMlnrro 7_ \o

FIQUREBYIRW LOOKING FORW*RD 6 INBO*RD do VH WING LUDING

EDGE CLOSE-OUT AND WING gRnM12~.0 R1BRI(IHTWDO~POSITE

Page 14 of 25

SERVICE BULLEalN NO. 223

PART II ACCOMPLISnMENT INSTRUCTIONS RNSPECTION REPAIRI (cont.)

2) From insldelhe fuselage:

a) Protect the inside surface of the cabin windows.

b) Remove the cabin interior in the area of the wing leading edge anachment.

c) On aircraft with Picture Windows, drill back the inner frame aluminum panels. (600 Figure a)

PART II-ACCESS

F.s. 144.0 (Ensnded Fuselsga) ORILlBACKINNERFR*ME

F.S. 1M.O (Sh.n Fuaalaga) ALUMINUM PANELS TO W\INACCBSSTOFmlNG8(ITEM 2 c)

LEADING EWE TO W.S. 24.0

RIBATTACNMENTF~INO(REF.)

Lr´•; DO

L

t~L.

pROrrCTINSIOESURWIAEOFCABINWINWWS

(ITEMZ.a)REINSTAIL FASTENERSPER PART II. (mM 4. b)

FIGURE 6VIEW LOOKING OVTBOARD e) Wn W.S. 24.0 RIe ATCACHMENT

FITTING ANO INNER FRAME ALUMINUM PANELSLEFT HAND OPWSISI

Page 16 of 26

SERVICE BULLeTIN NO. 225

PART II -ACCOMPLISHMENT IN~STRUCTIOFIS IINSPECTION B REPAIRI (cont.)

d) Remove the cabin sealant (mm the leading edge attachment nnlngs as indicated. (See Figure 7)

a) Remove the vertical tee bracket (822 Figure 7) from the aircraft.

O inspect for cracks in the vertical tee bracket.

g) Inspect for clacks in the forward side of the fuselage frame imm one inch above to one inch below where

the vertical tee bracket was removed end around the fastener holes from the ah side.

PART II´•INSPECTION

REMOVE BVILANT

(ITEM 2, 0)

1.00 O

I

o o

INOPECTFWIME IO

I

(ITEM 2. 1) I OO o oREINSTUL I

FABrrNERSPER PART II. I I O(ITEM 1. a) I O O

I OI

LEMINO EWE TOW.8. 2~.0 RIBATTACHMEM

1.00 O F~NG(RV.)

REMOVE AND INLIPECT

I MRTICAL TEE BRACKETI (ITELI 2. a)

FUSELADE FWUIE(REF.)

FMaURE 7VIEW UXZKING OLIT8OARD 6 FORWARO Q) R~ VUITIW TEE BRACKET

LEm HAND OPPOSITE

Palls IB ol 2fi


PART II-ACCOMPLISHMEN7 INSTRVCTIONS IINSPECTION& REPAIR) (cont.)

hf inspect for cracks in the rib anachmeni wing leading edge to the Wing Station 24.0

db. (800 Figure 8). it is not required to inspect the ah vertical nange of this fitting.

PART II-INSPECTION

LEMINCI EODE rO w.s. 2´•.0

FUsEVIOE FRIMERls A1TACHMENT FITnNO (REF.)

(REF.)r w.s. 24.0 RIB (REF)

sPAUWT?,d) O

O

o ~o

..´•o o~Oo~l o

o I: oa o \JI

oci olo IOO h9. O o ol

oo oo o

INsPECT FOR CR*CKS

1N FISTING (ITEM 2, h)

AFSMRTICMFUNOE.NO IHSPECTION REOD.

FIGURE BVIEW LWI(INO OVTBOARD O WH W.S. 11.0 RIB ~TACHMENT FmlNG

LEFT H~NO OPPOSITE

3) If any damage is found in the above areas, parts must be replaced or an approved repair must be installed

p~or to retum to service.

4) If no damage is found, reinstall the parts removed.

a) For reinstalllnp the vertical tee bracket section to the fuselage frame and the rib attachment fitting, n is

acceptable to substitute HUOPBS -8 Pins (00010 size as removed) and HL865 -8 Collar for Factory

installed aluminum or steel lockbolts. If total hole cleanup cannot be obtained, n is acceptable to install

the 1184" oversired HLB4P&5 1 -8 Pin end nL87-5 /-g Collar. Solid rivets must be installed where

removed. Install the vertical tee bracket to the frame using a faylng surface seal (PR890A1R Sealer).

b) For nlndslllng the inner frame aluminum panels, It is acceptable to substitute ChenyMax blind fasteners

CR3243 for solid rivets per TCAC Custom Kit No. 144, item D.

Papa I~o(28

SERVICE! BULLETIN NO. 223

PART II AC_CqMPL!SHMENT INSTRVCTIONS nNSPECTION 8 REPAIR) (cod.)

5) Replacement ol the wine leading edge dose-out brscket(s)/ strap(s).

NOTE:

IF ONLY ONE BRACKET I STRAP IS DAMAGED, ALL MUST BE REPLACED, ON BOTH THE LEFT

AND RIGHT HAND WINGS. REPAIR PARTS ARE PROVIDED IN THE APPLICABLE KITS.

a) Drill off and remove the existing leading edge dcse-out bracket(s)/ ntting(r).

b) Select the applicable SB223-XXX Kit fmm the Pads Data Section.

c) Install the Kit perthe applicable Figure.

KIT NO. FIGURE PAGE MODEL EFFECTIVITY58223-503 8 18 ALL B9OC. 895, BgOD, BgSA 5 8858

58223-505 10 20 ALL 890A. 8808 5 890 S/N 11041

58223-507 11 21 ALL 890 EXCEPT SIN 11041

58223´•509 12 22 NOTED

58223-511 12 22 NOTED

Page 15 o( 25

SERVICE BUUETIN NO. 223

PART II-ACCOMPLISHMENT INSTRUCTIONS (INSPECTION 8 REPAIR) (cont.)

8) For applicable models, replace sealant as rembved fmm the lorwad edge of the W.S. 24.0 rib attachment Mtlngas per Part n. (Figure 7 8 8), see pmcedure below.

a) Cut 3 sections of fiberglass cloth far eacllside´• (total of 8 pieces) approximately 8 inches square (8 x 8).

b) Mix 1/2 cup (8 oz.) of 8B0A1/2 sealer and ha~dware per mixing instmctions and apply with a stiff bristle paintbrush.

c) Inside the cabin, coat the left 8 right W.S. 24.0 fitting, vertical tee bracket and adjacent wing mot areas. Placeone layer of fiberglass cloth on the wet sealer and form the cloth over the nttlng onto the tee, fuselage frameand wing mot fsidng in o~erto complete seal overthe wing leading edge root area. Stipple the cloth into thesealerwith the paint brush and fold the cloth where necessary in oder to make it lay down and adhere to thepads. For models with engine codml cables running thmugh the fitting. cut a slot in the cloth and form theedges of the cloth amund the cables as much as possible.

d) Allow at lea11/2 hour for the first application of sealer to harden, then mix 1 pint of 880A1R sealer and harden

per mixing instructions. Recoat the previously covered area. Lightly saturate the first layer of cloth with sealer.If there went~ly areas on the cloth fmm the first application, the entire area of the cloth can now be wetted.

a) Apply a second layer of nbemlass cloth on top of the first layer and stipple the cloth into the wet sealer until thesecond layer of cloth is saturated. Cut a slot in the cloth to form around control cables if necessary. Make surethe second layer of cloth overlaps onto the tee, frame and adjacent wing mot structue same as the first layer.

O it is not necessary to walt for the second application of sealer and cloth to harden before applying the third andfinal layers. Lay a ihild layer of cloth on top on the second layer. It may be necessary to recoat areas withadditional wet sealer in Mderta saturate the thld layer of cloth. Cut a slot for control cables if necessary.Small pieces of cloth can be added st this time to fill in gaps or to overlaploints in the cloth.

g) When nnlshed, the tree layers of fiberglass cloth saturated in sealer should form so airtight seal of the wingmot between the fitting and the closest fuselage structure. Clean up excess wet sealerwlth MEK or lacquerthinner.

7) Finish the installation of the 58223-501 Kit (See Figure 2 8 2A)

8) See Patt i, Items 17 thru 21.

PART iII: INSPECTION OF F,S. IEXT. FUSELAGEI I F.S, 100.0 ISHORT FUSELAGE)

1) Pmted the inside surface of the cabin windows with appmprlate medium.

2) Remove the cabin interior above the windows to gain access to the forward side ofthe frame.

3) inspect F.S. 144.0 (UCTENDED FUSEU\GO I F.S. 100.0 (SHORT FUSELAGE) frame, at the tee bracketattachment above W.L. 10 for cracks orfalled fasteners. inspect the forwarri side of the frame fmm one inchabove to one inch below the area where the tee bracket is installed, using the Flarescent Penetrant Method.

(See Figure 13)

Page 23 of 26


PART III: INSPECTION OF F,S, 144.0 IEXT. PllsEU\aEII F.S, 100.0 ISHQRT FUSELAGE) (cont.)

CAUTION:

THE 144.0 FRAME IS TO BE INSPECTED THRU THE EXISTING INNER FRAME PANEL LIOHTENINO

HOLE FROM THE FORWARD SIDE ONLY.. DOINOT REMOVE THE FIBERGLASS CABIN PRESSURE

SEAL COVERING THE AFT SIDE OF THE FRAME AT THE TEE BRACKET.

NOTE:

IT 19 ACCEPTABLE TO DRILL OFF THE INNER FRAME PANEL TO REMOVE SEALER FROM THE

FORWARD SIDE OF THE 144.0 FRAME. DO NOT RESEAL THIS AREA. AFTER INSPECTION,

REINSTALL THE REMOVED INNER FRAME PANEL PER Psrt II, ITEM 4), b).

PART III´•INSPECnON

F.8. 10I.O(E*tsrdad FMsOa)F.S. Imo (s~od Fusslags)

INSPECS FOR CW\CK(I

NO INgPECSIONFROM

SIDEOFFW~ME

TEE BRACI(ETj jj i(RV~

YWTERUNE- ~o.m

VIEW A-A

FIOURE~SY1EWLOOKINO OUTBOARD O RIH BtOE

LEFTW\NDOPPOSITE

Pa~e 24 d 26


PART III: INSPECTION OF F.S. 144.8 IEXT, FUSELAGE) IF.S. 1D~.O ISHORT FUSELAGEI (cont.)

4) Finishes must be restored per the recommended Airuan Maintenance Manual practices after inspection are

completed.

NOTE:

FOR LOCAL TOUCH UP ON EXISTING STRUCTURE, USE ZINC CHROMATE. DO NOT MIX

CHROMATE AND POLYVRETHANE PRIMERS ON THE SAME PART. ALL NEW ALUMINUM PARTS

FROM TWIN COMMANDER ARE POLYURETHANE PRIMED.

5) Reinstall all cabin interior panels.

Fill out the information an the Compliance Ca~d and send to:

Twin Commander Alrciaft CorporationService DepartmentPO Box 3369

Arlington, WA. 98223

ELECTRICAL LOAD:

No change

WEIGHT AND BALANCE:

No significant change

SPARES AFFECTED:

None

RECORD COMPLIANCE:

Make an appmp~ate entry in Airplane Maintenance Recods as follows: Service Bulletin No. 223, dated

240CTOBER1898, entitled ’WING LEADING EDGE ATTACHMENT INSPECTION AND MODIFICATION’,

compiled with as follows:

Pan I List inspection hems accomplished by item no., title, airplane total time, and date performed. If the

recommended modmcalion of the inspection hem listed has not been accomplished, list the next

scheduled inspection times to repeat inspdlon of the item.

pan n List modlflcaUons and inspection hems accomplished by drawing and dash no., tie, airplane total

time, and date perfoned.

Panm List modifications and inspections accomplished noting airplane total time end date performed.

Page 25 or 21

COMPUANCE CARD

Pzlpe~ o~Z


WING LEADING EDGE ATTACHMENT INSPECTION 4ND MODIFICATION

MODEL: AIRCRAFT SERIAL NO. TOTAL AIC TIME (HRS)

AIRCRAFT REGISTRATION NO.

OWNER(S) NAME:

ADDRESS:CIP/ STATE ZIP CODE

TELEPHONE NO. AIRCRAFT AGE: C(EARS)

PART I(MODIFICATION (L INITIAL INSPECTION)

LIST INSPECTION ITEMS COMPLIED WITH BY ITEM NO.. TITLE. AND DATE OF COMPLIANCE. LIST

DETAILS ON ANY CRACKS OR DAMAGE FOUND.


DATE: SIGNATURE:

PART II (INSPECTION LL REPAIR)

LIST INSPECTION ITEMS COMPLIED WITH BY ITEM NO.. TITLE, AND DATE OF COMPLIANCE. LIST

DETAILS ON ANY CRACKS OR DAMAGE FOUND.


DATE: SIGNATURE:

h(p

COMPUANCE CARD


WING LEADING EDGE ATTACnMEM INSPECTION AND MQDIFICATION

PART III(INSPECTION OF F.S. ~46.0 (EXT. FUSELAGE) I F.S. 100.0 (SHORT FUSELAGE)

LIST INSPECTION ITEMS COMPLIED WITH BY ITEMNO.. TITLE, AND DATE OF COMPLIANCE. LISTDETAILS ON ANY CRACKS OR DAMAGE FOUND.

INSPECTED BY: TELEPHONE NO. I

DATE: SIGNATURE:

TWINjCoMA~HANoERService Bulletin A IR CRAFT C ORPORA TION

PO. 3369 Arlinglon. Wa 3822]

~el: (360) 435-9797 ~ax: (3801 4i5-I:;1

Service Bulletin 224 rev C’

July 25, 1996

REPLACEMENT OF NOSE LANDING GEAR BOLT

EFFECTIVITY: This Service Bulletin applies to airplanes of the following models with the

following serial numbers: 5005:3185,3228.3230.3262,3291:500U:1765;680F:1195:

680V:1677:681:6027;690:11b35,11053,11068. 11074:690A:11111.11134. 11146.

11153,11173,11177,11205.11215,11237,11249,11271,11273,11282:6908:11360,11382,11409,11424 11451.11455, 11463,11491, 11513,11521,11535,11536.11539.

11566;690C:11638,11643.11689,11719;880D:15041;695:95010,95033.95044.95066:695A: 96010, 96041, 96056, 96061. IMREASON FOR PUBLICATION: Improperly heat-treated landing gear drag link bolts may Ahave been installed on these airplanes. I N

COMPLIANCE: It is mandatory, within the next 10 hours of operation, that the nose gear dragD

link bolt be replaced on those airplanes whose serial numbers are listed above.

BY WHOM WORK WILI BE ACCOMPLISHED: A P Mechanic or equivalent iTAPPROVAL: Technical aspects of this service bulletin are FAA approved. I o

ESTIMATED MAN HOURS: One hour I R

PARTS DATA: Nose landing gear drag link bolts part numbers 750076-1 (for models 6900 IYand 695A), and ED10055 (for models 690C and earlier) may be obtained from any factory-

authorized Twin Commander Service Center.

INSTRUCTIONS: Replace the bolt that attaches the forward end of the nose landing gear

drag link to the strut (see the pictures on the next page) with a new bolt obtained from any

factory-authorized Twin Commander Service Center. Follow the procedure in the airplane

maintenance manual for workingon the strut. Return the bolt that was removed to Twin

Commander´•

RECORD COMPLIANCE: Make an entry in the airplane maintenance records:

’Complied with SE 224C. Replaced nose gear bolt on date i with part number i".

Fill out and return the Compliance Record that is included in this Service Bulletin.

REIMBURSEMENT: See attached Compliance Record for details.

Revision A superseded theoriginal release of S.B. 224 and limited the effectivity to certain

serial numbers. Revision B added serial numbers 3228, 11074, 11249, 11491, 11521. 115aB.

95010.95066.96010.96041.96056.96061. 11643 was 11676. Rev C adds S/Ns 1677.

11153. 95044 and adds 750076-1 bolt for later models.

Page 1 of 2

Service Bulletin 224 c

BOLT 1750076-1

(for 6900 and 695A)ED10055

(for 690C and earlier)

´•69

Page 2 of 2

COMPLIANCE.RSCORD

SERVICE BULLETIN NO. 224C

REPLACEMENT OF NOSE LANDING GEAR BOLT

AIRPLANE MODEL SIN REG. NO. TOTAL TIME (HRS)

OWNER’S NAME

ADDRESS

TELEPHONE FAX

COMPLIANCE WITH SERVICE BULLETIN 224C:

TCAC WILL REIMBURSE OWNERIOPERATOR FOR THE PRICE OF THE BOLT. PIN 750076-1 OR ED10065,

(BY CREDIT MEMO THROUGH THE FACTORY-AUTHORIZED SERVICE CENTER WHERE THE BOLT WAS

PURCHASED) AND IF THE WORK IS PERFORMED BY A TCAC FACTORY-AUTHORIZED SERVICE

CENTER TCAC WILL PAY 550 FOR LABOR CONTINGENT UPON RECEIPT OF THE FOLLOWING:

1. THIS COMPLETED COMPLIANCE RECORD.

2. THE REPLACED BOLT.

9. COPY OF THE LOGBOOK ENTRY SHOWING RECORD OF INSTALLATION.

4. COPY OF RECEIPT OF PURCHASE DMTH PIN) FOR NEW BOLT FROM A

TCAC FACTORY-AUTHORIZED SERVICE CENTER.

5. THIS OFFER APPLIES ONLY TO COMPLIANCE WITH S.B. 224 REV C.

BOLT REPLACED ON I DATE)

PART NUMBER OF NEW BOLT~SERIAL NUMBER OF NEW BOLT


(SIGNATURE)

COMPANY

ADDRESS

TELEPHONE FIV:

SERVICE PUBLICATIONS((f17AIWAULII~:IP

revision notice A/RCRAFT CORPORA T/ON19010 59’" DI. N.E.~rlin.ton. W~ 9822578J2

r.l: (180) 49(19197 45~-1’112


Revision No. 1

Release Date: July 15, 1997

FLAP SYSTEM INSPECTION

APPROVAL:


REVISE ESTIMATED MAN HOURS:

Change to read:

Part II: A. 1 Hour/Pulley(Rework)

B. 5 Hours/Side

REVISE SPE~AL TOOLS:

Change to read:

A gage is available at Twin Commander Aircraft Corporation Service Centers foruse in conducting the inspection: PN TOOL-S8226

IMANDATORY

Senrice Bulletin A/RCRAF~CORPORAT70N(8010 68’" O1. N.e. nrl..ton. WA 88883-1888

rtll: (3110) 411´•8181

SERVICE BULLETIN NO, 226 April 14, 1997

FLAP SYSTEM INSPECTIPN

MODELS AFFECTED:

All models of piston and turbine twin engine Twin Commanders except themodel 700.


Twin Commander has received a report from the field of two flap pulleyassemblies with cable grooves that were found to be too narrow. There arethree pulley assemblies per side in all Twin Cammsndsrs except the Model Ib~700. The two pulleys were the right inboard (slave pulley) and the rightoutbaara sssemblis~. The inboard assembly was included in service Bulletin W210 which required inspection of the cable groove. This service bulletin willreplace SE 210 in its entirety and require inspection of all pulley assemblies Mon both left and right sides of the aircraft. Compliance with SE 210 does notreplace any requirements of this service bulletin. BPan I: Inspeclion of all flap system pulleys and cable aspemblisE. I w

Part II: Replacement or rework of any pulley assemblies as determinedb’OPart I inspection. Replacement of cables, support brackets, or clips

as determined by Part I inspedian. aPart ill: Identify pulleys complying with this service bulletin. Il v

COMPLIANCE:

Timing: Part I inspection shall occur within the next 100 hours of airplaneflight time.

Part I: A. Gage inspect all Rep system cable grooves. (Refer to Figure 1)

B. Inspect all flap pulleys for rubbing on the support brackets.

C. Inspect all flap pulley cables for frayed wires.

Part II: A. Mandatory pulley rework or replacement if cable grooves aretoo narrow.

Page 1 or 7


8. Mandatory replacement of cables if cable grooves are toonarrow or cables are frayed.

Part III: A. Permanent identification of all pulleys with the proper groove radius.


A P Mechanic (or equivalent)

APPROVAL:


ESTIMATED MAN HOURS:

Part I: A. 16 hours (both sides)

8. 2 hours (both sides)

C. 4 hours (both sides)

Part II: A. 1 hour(rework per pulley), 2 hour (replace both sides)

8. 10 hours (both sides)

PARTS/REWORK INFORMATION:

Replacement Part Numbers can be obtained from the Twin Commander PartsCatalog for the model being inspected.

Pulley assemblies can, as an option to replacement, be reworked by TwinCommander Aircraft Corporation. Contact a Twin Commander Service Center orTwin Commander Aircraft Corporation for rework instructions.

SPECIAL TOOLS:

A special tool, part number 58228, to inspect the cable grooves is available fromTwin Commander.


Part I: A. Insert the gage marked ’A’ into each of the cable grooves in each ofthe 6 flap system pulleys. This checks for a cable groove that has a

bottom radius that is too narrow. If the gage does not contact thebottom of the groove (see figure 2), refer to Part II paragraphs A andD for corrective action. Recheck the cable grooves with the gage

Page 2 ol 7


marked ’B’. This checks for e~ble groove that has a bottom radiusthat is too wide. If the gage can be moved from side to side in thecable groove bottom radius (see figure 3), refer to Part II paragraphB for corrective action.

If the pulley cable grooves have the proper radius, refer to Part illformarking the pulley.

Any pulley cable grooves that are found to have an out of toleranceradius must either be destroyed, reworked or replaced.

B. Inspect each of the 6 flap system pulleys on both sides for signs of

rubbing against the upper or lower support brackets. Be especiallyalert for wear on the clips securing the cables. If worn clips or

support brackets are found, refer to Part II paragraph C for correctiveaction.

C. With a clean soft cloth, rub each flap system cable over its length. If

snags are found, inspect for broken wires. If broken wires are found,refer to Part II paragraph D for corrective action.

Part II: A. Replace any pulleys that have a cable groove bottom radius that istoo narrow. As an alternative to replacement, pulleys may bereworked by Twin Commander Aircraft Corporation. Contact a TwinCommander Service Center or Twin Commander Aircraft Corp. forrework instructions.

B. Replace any pulley that has a cable groove bottom radius that is toowide.

C. Replace any damaged support brackets and any worn clips.

D. Replace associated cable assembly when any pulley is replaced or

reworked for a cable groove bottom radius that is too narrow.

Replace any frayed cables.

Part III: A. Using a permanent marker, draw two(2) parallel lines on the pulleyvisible for future inspections indicating compliance with SE 226.

B. Reworked pulleys will be marked with ’SB 226’, the date of rework,and an inspection stamp.


WEIGHT AND BALANCE: No change.

SPARES AFFECTED: Any spares found in inventory must be inspected perPart 1 and either scrapped or reworked.

Page 3 or 7


PUBLICA7I0NS AFFECTED: None.

RECORD COMPLIANCE:

Make an entry in the aircraft log book as follows:

Complied with Service Bulletin No. 226, dated April 14, 1997,entitled "Flap System Inspection".

Part I Accomplished: (Date) State results of the pulley and cable

inspections.Part II Accomplished: (Date) State which if any, pulleys were

replaced or reworked, and which cables were replaced.

Complete the information requested on the self addressed Compliance Card and returnto Twin Commander Aircraft Corp.

Page 4 of 7


+.007.064R~ .000

TYPICAL RADIUS ON

ALL CABLE GROOVES

FIGURE 1

Page 5 of 7

CD


Gage Can Be Rotated

SE 226 Gage

F9Cg

ReDlaee or Rework

Cable Groove Too Narrow Cable Groove

Within Tolerance

FIGURE 2

Page 6 or 7


Gage Can Be Rotated

SE 226 Gage

d

e3

Gape Can Be Moved

Side to Side Replace Pulley Cable Groove

Within TDleranee

FIGURE 3

Paae 7 a17

COMPLIANCE CARDSERVICE BULLETIN NO. 226

MODEL AIRCRAFT SERIAL NO. TOTAL AIC TIME (HRS)


OWNER(S) NAME

Street P.O. BOX

CITY STATE ZIP CODE

TELEPHONE NO.:(

LIST RESULTS OF PULLEY GROOVE INSPECTION FOR EACH PULLEY.

*CCEPII\BLE

LEFTOUTBOARD 7]LEFT CENTER 17 C1 C1

LEFT INBOARD(MASTER) CI [7 7]

RIGHT OUTBOARD O O 7]

RIGHT CENTER O O 77

RIGHT INBOARD(SLAVE) O O O

INSPECTED BY TELEPHONE NO.:

DATE: SIGNATURE:

LIST ACTION TAKEN FOR OUT OF TOLERANCE PULLEY GROOVES.

REWORK REPLACE

PULLEY PULLEY

GROOVE

LEFT OUTBOARD C1 C7

LEFT CENTER I~ [7]LEFT INBOARD(MASTER) O [7

RIGHT OUTBOARD 73 C1

RIGHT CENTER O 7]

RIGHT INBOARD(SLAVE) D 7]


DATE: SIGNATURE:

MANDATORY

Sesvice Bulieiin ~´•rr~Y’Y

A/RCRAF)- CORPORA T/ON

11~10 611" D I. N.e. arllnolon, warot: IP101115´•)711 FaX: (3.0) ~31.(1(2

Service Bulletin No. 227 August 1, 1997

Insoection and Modification of Lower Main Gear Scissors

EFFECTIVIPI

All models of piston and turbine engine Twin Commanders except the model 700.


Twin Commander has received reports from the field of interference between thelower main gear scissors and the upper portion of the main gear fork. The scissorswere redesigned from a machined forging to allow machining from plate material.This resulted in areas that were thicker than the forging since the new machined

part did not require draft angles. This interference occurs when the strut isextended and could result in failure of the scissor assembly causing loss ofdirectional control during landing. I FII

COMPLIANCE IA

Part I: Inspection loLeft and right main gear scissor assemblies must be inspected before the next I A

flight to determine if there is any interference between the scissor assembly and I Tthe main gear fork. I o

Part II: Modification I R.

If damage is found, the scissor must he modified before further flight.

BY WHOM WORK WILL BE ACCOMPLISHED

A 8 P Mechanic (or Equivalent),

APPROVAL:

DESIGN ASPECTS OF THIS BULLETIN ARE F.A.A. APPROVED


None

Page 1 of _5_

Service Bulletin Na. 227

SSTIMATED ~N HPURS:

PART i:

Inspect left and right scissorslforks for damage 2.OHR(Both)

PART II:

Modify left end right scissor 2.0 HR(Both)Prime and paint left and right 1.0 HR (Both)

10 BE PROCURED LOCALLY:

1. DESOTO 825-309 Polyurethane primer (or Equivalent)2. Paint for touch up

SPECIAL TOOLS:

None

INSPECTION R~C\UIREMENTS:

1. Personnel Quaiifications

a) A&P Mechanic

PART I-ACCOMPLISHMENS INS7RVCTIONS (INSPECTION)

1. Refer to the Maintenance Manual and lack the airplane up to fully extend both maingear.

2. Inspect the area shown in Figure 1 for interference between the scissor and thegearfork.

3. If there is no inte~erence, no further action is required.

4. If interference is found, lower the aircraft to the ground, remove both scissorhalves (Vpper and Lower), and inspect the bushing holes in the scissors and forkfar damage. Replace damaged bushings, scissors or hardware as required.

5. Modify the lower scissor per Part II.

Page2o1_5_


PART II-ACCOMPLISHMENT INSTRUCTIONS IMOD1FICATION1

i. Verify whether the part is made from a forging or if it is machined from platematerial. The forging will have rounded edges in the nonmachined areas and theplate material will have sharp corners. If the part is a forging do not proceedbefore contacting Twin Commander Aircraft Corporation.

2. Remove material on the lower scissor in the area of interference being careful notto exceed the maximum allowable as shown in figure 2. Be sure to burnish anytool marks that may have occured in the area of material removal.

3. Prime and paint the area of removed material.

4. Reinstall the scissor halves. With the strut fully extended inspect for clearancebetween the scissor and the gear fork. If the scissors still interfere with the maingear fork, contact Twin Commander Aircraft Corporation before proceeding.

ELECTRICAL LOAD:

No Change

WEIGHT AND BALAN~

No Change

SPARES AFFECTED:

None

RECORD COMPLIANCE:

Make an entry in the aircraft log hook as follows:

Complied with Service Bulletin No. 227, dated August 1, 1997,entitled "lnspection and Modification of Lower Main Gear Scissors".

Complete the information requested on the self addressed Compliance Check Card andreturn to Twin Commander Aircraft Corp.

Pagelof_S_

Secvice Bullenn No. 227

MAIN GEAR STRUT

AREA OF INTERFERENCE

O

QII~

o

0~ MAIN GEAR STRUT

MAIN GEAR FORK

Figure 1

Paga´•ld_S_

Service Bulletin No.:227

View B

A

-r iS I-Atl 15

leSECTION A-A

Centerline of

scissor

-+t ;;Op.

.50R

Typ.V \/L-- ´•15

(Ref)

View B

PageSof_S_

COMPLIANCE RECORD


INSPECTION AND MODIFICATION OF LOWER MAIN GEAR SCISSORS

MODEL AIRPLANE SIN REG. NO. TOTAL TIME (HOURS)

OWNER NAME

ADDRESS

TELEPHONE NO FAX NO

COMPLIANCE WITH SERVICE BULLETIN 227:

INTERFERENCE BETWEEN SCISSOR ASSEMBLY MAIN GEAR FORK FOUND?

YES O NO CII

IF YES, PLEASE GIVE DESCRIPTION OF INTERFERENCE AND A DESCRIPTION OF HOW

REPAIR WAS ACCOMPLISHED AND PARTS USED:

DATE


(SIGNATVRE)

COMPANY

ADDRESS

TELEPHONE FAX

~WVDATORY

Sen/i~e BuI letin%LIW~WAUIIEIQA/RCRAFTCORPORAT70N18(110 58’D Dr. N.E. Arlington. WA 90229´•7832

rat: (Jao) 455´•8187 FAX: 1555) 451´•(112

SERVICE BULLETIN NO, 228 January 4, 1999

MODELS AFFECTED:

All models of piston and turbine twin engine Twin Commanders.


Twin Commander has received a report from the field of nose gear steeringpins that did not have the required hole for a cotter pin. This service bulletin

provides the instructions to inspect, and if necessary, rework the pin.

Part I: Inspect and verify configuration of part.MA

Part II: Remove nose gear steen’ng pin and drill hole for cotter pin as shown.

NReinstall pin using castellatednut and cotter pin instead of lockingnut. ID

AcoMpLlaruce:

TTiming: Inspection and nnn~oit, if required, shall oocur wnhin the next O

100 hours of airplane flight time or at next annual inspection

(Whichever comes first). RY


A 8 P Mechanic (or equivalent)

APPROVAL:


ESTIMATED MAN HOURS FOR REWORK:

4 hours

Page 1 of 5


PARTSIREWORK INEORMATION:

AN320-4 Nut or equivalent (Obtaln locally)MS24665-132 Cotter Pin or equivalent (Obtain locally)

Existing part may be reworked by an A 8 P Mechanic (or equivalent).

Replacement Part Numbers can be obtained from the Twin Commander Parts

Catalog for the model being inspected.

SPECIAL TOOLS:

No special tools are required for this Service Bulletin.


Part I: Locate the nose gear steering pin as shown on Figure 1. Determineif the pin is inst~illed with a castellated nut and cotter pin. If It Is, no

rework is required. If it is not, continue to Part II.

Part II: Remove the nose gear steering pin and discard the lock nut. Drill the

cotter pin hole as shown in Figure 2 using accepted shop practices.Reinstall the nose gear steering pin using a AN320-4 nut (orequivalent) and M524685-132 cotter pin (or equivalent).


WEIQHT AND BALANCE: No change.

SPARES AFFECTED: Any spares found in inventory must be inspected perPart 1 and reworked if necessagl.

PUBLICATIONS AFFECTED: None.

RECORD COMPLIANCE:

Make an entry in the aircraft log book as follows:

Complied with Senice Bulietln No. 228, dated January 4, 1899,entitled "Nose Gear Steering Pin".

Accomplished: (Date) State whether or not the pin was modified.

Complete the information requested on the self addressed Compliance Card and retum

to Twin Commander Aircraft Corp.

Page 2 of 5


NITROGEN ~ND HYOAAULIC

FILLPORTVALVE

o\ I te~) I--BODY

PIN

oil iUPPER

CENTERING

IICoLLnR nssv

PISTON ROD

ORIFICE TVBE

CENTERING PIN

ATTACH BOLT

COLLAR

DOWN STOP ANo/ I ICo~dl I I BUSHINO

CINTERIN(I PIN

SCISSORANTISHIMMY II ‘YWI L/1 I I II II nspv

FRICTION

CYLINDER STEERIN(I CYLINDERBRACKET POINT

s~P a.alm.ouao

RING

SCISSOR BUSHIN(I

AVSY

Fl GU RE

Paae 3 of 5


750080-1

DRILL #48 .076 +.004/-.001 THRU

FIGURE 2

Page 4 of 5

COMPLIANCE CARD


NOSE GEAR STEERING BOLT

MODEL_

AIRCRAFT SERIAL NO. TOTAL AIC TIME (HRS)


OWNER(S) NAME

P.O. BOXStreet

CITY STATE ZIP CODE

TELEPHONE NO.:~)

DlD THE PIN NEED TO SE REWORKED? YES~ NO~


DATE: SIGNATURE:

COMPANY

ADDRESS

TELEPHONE FAX

ALERTZUIIAI

Service Bulletin %OIIIIMAU17;EIQA /RCRAF7- CORPORA T~ON

19010 59th Drive N.E. Arlington, WA. 98223Tel: (360)-435-9797 Fox: [360)-435-1112

Service Bulletin No, 233 Date: October 15, 2003

ENGINE NACELLE FIREWALL REINFORCEMENT

EFFECTIVITY: MODEL NO.

690C (Serial Numbers 11600 thru 11735)695 (Serial Numbers 95000 thru 95084)


The above aircraft have experienced cracking indications in the aluminum and or stainless steel webs of

the engine firewall assembly at the aft engine mount location. The firewall assembly is built of

components consisting of a stainless steel fire shield (forward side) and formed aluminum bulkhead (aftside). The firewall cracks were found radiating from the fastener holes that secure the aft engine mount

to the firewall, and or along the upper radius of the bulkhead directly above the two upper mount holes.

COMPLIANCE:

INITIAL COMPLIANCE TIMES

CURRENT AIRFRAME COMPLIANCE REQUIRLED PRIOR TO (HOURS TIS)(HOURS/ TIME-IN- OR WITHIN THE NEXT [MONTHS] WHICHEVER COMES

FIRST

0000-1700 (2700) Hours or 136] Months

1701-2500 (3400) Hours or [36]Months2501-3000 (3800) Hours or [36] Months

3001-5000 (5500) Hours or (30]Months5001-6000 (6400) Hours or [24]Months6001-7500 (7800) Hours or [18]MonthsOver 7500 1 1121 Months

Tabk A

No inspections modifications are required before the expiration of the time period set forth in Table A

applicable to the airplane; however it is highly recommended that all of the inspections i modifications be

accomplished at the earliest practicable time. Firewall modifications per this Service Bulletin are

terminating action.

Page No. 1 of 9

SERVICE: BULLETIN NO. 233


A P Mechanic (or Equivalent), and An ASNT Level II Certified NDT Inspector (or Equivalent) per INSPECTIONQUALIFICATIONS.

NOTE:

IT IS RECOMMENDED THAT ALL MODIFICATIONS BE COMPLETED ONLY AT AN AUTHORIZEDTWIN COMMANDER SERVICE CENTER.

APPROVAL:

Modifications described by this Service Bulletin are FAA DER Approved.

ESTIMATED MAN HOURS: (INCLUDING ACCESS L 8 RH SIDES)

Inspection of firewall assembly forward (STEEL) and aft (ALUMINUM) bulkheads 32 HRS

Reinforcement modification of firewall assembly forward (STEEL), 32 HRS

aft (ALUMINUM) bulkheads and lower fire shield

Total Installation Time 64 HRS

PARTS DATA:

Kit parts required to comply with this Service Bulletin may be purchased through any of the nearest

TWIN COMMANDER FACTORY AUTHORIZED SERVICE CENTERS. Reference SE 233, aircraft model and

factory serial number when submitting order.

S~olied with modification kit:

TCAC DRAWING NO. 610681

TCAC PROCESS SPECIFICATIONS NO. 260.8

KITNO. SB233-1 (Left and Right Hand Engine Nacelle Firewall Reinforcement)

Parf Number

1 610681 DWG SE 233 ENGINE NACELLE REINFORCEMENT 610681-1

2 K660000-3 ANGLE

2 K660000-4 ANGLE

2 K660000-5 ANGLE

2 K660000-6 ANGLE

2 K660000-7 PLATE

2 K660000-9 CLIP

2 K660000-10 CLIP

1 K660000-11 ANGLE

1 K660000-12 ANGLE

1 K660000-13 ANGLE

1 K660000-14 ANGLE

Page No. 2 of 9


PARTS DATA: (cont)

KIT NO. SB233-~ (Left and Right Hand Engine Nacelle Firewall Reinforcement)

1 I K660001-3 IDOUBLER

1 1 K660001-4 1 DOUBLER

2 1 K660001-5 1 RADIUS BLOCK

AIR MS20427M3 COUNTERSUNK HEAD MONEL SOLID RIVET

AIR I MS20427M4 COUNTERSUNK HEAD MONEL SOLID RIVET

AIR I MS20615M4 I PROTRUDING HEAD MONEL SOLID RIVET

A/R I MS20615M5 PROTRUDING HEAD MONEL SOLID RIVET

12 1 HL20PB6-6 I PIN

8 1 HL20PB6-8 I PIN

4 1 HL20PB6-10 I PIN

24 1 HL86PB6 I COLLAR


i. Polyurethane primer used for touch up on parts furnished with the Modification Kit. MIL-C-23377 per TCAC

Process Specification 30.8 or MIL-C-27725 TYPE II, CLASS A per TCAC Process Specification 30.6

SPECIAL TOOLS:

i. GO-NO-GO gages for HI-LOK fastener inspection

GENERAL INSPECTION CRITERIA:

TYPES OF INSPECTION FOUND IN THIS SERVICE BULLETIN PER AC 43.13-18 CHAPTER 5

"NONDESTRUCTIVE INSPECTION" (NDI).

Perform FLUORESCENT DYE PENETRANT structural inspection as an aid in disclosing crackingindications or other failures not detectable by visual means. Carefully remove sealant and I or finishes

as necessary in order to allow inspection of the structural elements. Moderate hand pressure appliedbetween parts, in order to produce any relative movement allowed, may assist in detection of failllie of

parts or joining fasteners. Also observe any rub marks indicating relative movement of parts under I´•iad.


GENERAL INSPECTION CRITERIA: (cont.)

Areas to be inspected are identified by Part Number and I or Name and are located per the applicableINSPECTION FIGURE(S).

NOTE:

ILLUSTRATED PARTS CATALOG MAY BE USED FOR ASSISTANCE IN LOCATING INSPECTIONAREAS (REFERENCE ONLY)

INSPECTIONS APPLY TO LEFT AND RIGHT HAND AIRCRAFT ENGINE FIREWALLS

INSPECTION REQUIREMENTS:

i. PERSONNEL QUALIFICATIONS

a. Level II Liquid Penetrant.

b. Vision acuity requirements of MIL-STD-410E, or latest revision.

c. Documented training in accordance with MIL-STD-410E, or latest revision and recommended practiceSNT-TC-1A of the American Society for Nondestructive Testing.

2. MATERIALSAND EQUIPMENT

a. Solvent Cleaner, SKC-NF (Magnaflux) or equivalent per MIL-I-25135.

b. Water Washable Fluorescent Penetrant, ZL6OC, Level II (Magnaflux) or equivalent per MIL-I-25135.

c. Non-Aqueous Developer, SKD-NF (Magnaflux) per MIL-I-25135 or equivalent.d. ZB-100 Black light (Magnaflux), 100w, 115v, GDHz or equivalent.e. Inspection mirror.

f. Cleaner, Penetrant and Developer to be from the same manufacturer.

3. PROCESS

a. Per MIL-STD-6866.

b. Sensitivity- Type I, Method C, Level 3.



1. Disconnect Batteries.

2. Secure and jack aircraft per Maintenance Manual.

3.; Bleed the air i nitrogen charge from the Main Landing Gear emergency extension system per the Aircraft

Maintenance Manual.

4. Remove upper and lower cowling shells from engine.

5. Remove engine oil cooler in accordance with the following procedures:Remove and cap engine oil lines from firewall fittings.Remove jam nuts from bulkhead fittings of oil cooler.

Remove oil cooler I firewall attachment fasteners immediately below hydraulic fittings (two total).Remove oil cooler fire detector probe and fasteners (three total) from forward side of the firewall.

Remove oil cooler door screws (37 total) and door.

Remove oil cooler by rotating aft end of cooler down and forward to clear landing gear.

6. Remove ejector assembly and exhaust pipe in accordance with the following procedures:Remove the (three) bolts attaching the ejector to the outboard skin of the nacelle,

(NOTE: Access to the bolts is from the inside of the nacelle, outboard of the landing gear.)Remove attaching screws from forward and aft ejector fairing.Remove fairing and ejector assembly, being careful not to damage exhaust pipe assembly.Loosen forward clamp and aft clamps from exhaust pipe and seal and remove.

Remove bolts that attach the exhaust pipe assembly to the engine (18 totalj.Remove exhaust pipe assembly from aft side of the firewall.

7. Disconnect the landing gear door linkage from the landing gear.

8. Remove the bolts from the hydraulic reservoir lower attachment to the nacelle (L/H SIDE ONLY).

9. Disconnect and cap the plumbing line from forward side of the emergency gear extension system gage

(LIH SIDE ONLY).

10. Remove the insulation from the bleed airline and elbow at the rear spar and separate the forward bleed

airline from the elbow. (NOTE: Secure aft end of bleed airline prior to nacelle removal.)

11. Remove the hydraulic plumbing clamp fasteners that are common to the upper aft nacelle bulkhead and the

lower aft nacelle bulkhead, if nacelle is equipped with clamshell doors.

12. Disconnect and cap plumbing lines and remove fittings that are common to the mating bulkheads, if so

equipped. (NOTE: Support the lower aft nacelle prior to proceeding.)

13. Remove the lower aft nacelle and firewall attachment bolts from the forward side of the firewall (16 total).

14. Remove the attachment bolts that secure the common bulkheads together (four upper and ten lower,

14 total places).

15. Drop down and support lower aft nacelle on appropriate material to prevent any damage.

16. Remove the landing gear bungee to permit the drag brace to be folded over center and to allow the gear to

rotate aft.

Page No. 5 of 9


ACCOMPLISHMENT INSTRUCTIONS: (cont.)

17. With the gear clear of the lower aft nacelle, remove the nacelle.

18. Remove the engine controls support bracket from the aft top center location of the engine to allow access tothe aft engine mount and upper firewall.

19. Remove the aft engine mount link assembly from the firewall bracket and the engine attach point.

20. Disconnect the Prop. Sync. Actuator from the firewall to allow access to the forward side of the repair area

(R/H SIDE ONLY IF EQUIPED WITH WOODWARD TYPE 1 SYSTEM).

21. Remove aft engine mount firewall fitting and brace from forward side of firewall.

22. Remove sealer and primer and perform inspection for cracks at locations indicated per Figure #1 on both theforward stainless steel and aft aluminum engine nacelle firewall bulkheads.

23. If cracks are not present in either bulkhead, proceed with modification per item 26).

24. If cracks are present, and DO NOT extend inboard or outboard beyond the limits as indicated perNGURE stop drill the ends of cracks with .098 inch diameter bit (#40 drill). (CAUTION: Do not stop drill

through both the forward steel or aft aluminum bulkhead, insert steel shim stock material between firewallsto prevent damage during stop drilling procedures.)

25. DAMAGE LIMITS Modifications are only applicable if damage (if any) is within the following limits.

Maximum allowable crack length steel and I or aluminum bulkheads 1.75 INCH TYPICAL inboard and I

or outboard from the upper two engine mount attachment holes and along the upper bend radius of thebulkhead.

Maximum allowable crack length steel and I or aluminum bulkheads .90 INCH TYPICAL inboard and IOF outboard from the upper two (second row from top) engine mount attachment holes.

Maximum allowable crack length steel and I or aluminum bulkheads .50 INCH TYPICAL inboard and Ior outboard from the lower two engine mount attachment holes.

Page No. 6 of 9

MAXIMUM ALLOWABLE CRACK LENGTH---t~-.90 --I~ ~t-- 1.75 ---r+--MAXIMUM_ALLOW~BLE CRACK LENGT_HSTEEL AN D OR ALUMINUM BULKH EADS TYPICAL TYPICAL STEEL AND I OR ALUMINUM BULKHEADS

.90 INCH TYPICAL INBOARD AND OR I 1 ~7 1 i 1.75 INCH TYPICAL INBOARD AND OR

OUTBOARD FROM THE UPPER TWO (#2) 1 I I w.s. I OUTBOARD FROM THE UPPER TWO ~1)ENGINE MOUNT ATTACHMENT HOLES I I 91´•46 I I ENGINE MOUNT ATTACHMENT HOLES

AND ALONG THE UPPER BEND RADIUS

STOP DRILL ENDS OF CRACKS --7 1 I I I OF THE BULKHEAD

PER ACCOMPLISHMENT

INSTRUCTIONS, ITEM #24 1~7 O ~7 INSPECT FOR CRACKS IN THE FORWARDr STEEL AND AFT ALUMINUM FIREWALL

BULKHEAD ASSEMBLY ORIGINATING FROM

O /I I EXISTING FASTENER HOLES AND ALONG THE

UPPER BEND RADIUS OF THE BULKHEAD

i;, .I

II II _liII II I 1

1,1~11rl II

II V)a II I I I i I II m

mi II ii AO mm

I r~ II o

P 1r,, I~ II OJ o

ACCEPTABLE m

TYPICAL CRACKS mca I rT10~1 II II

b m O II IIII II c

Z Z C I 7;;o C]O

I I i I II FZ II III I 1 mV, III 13 11 (h II I

C7 m 71, 11up

4~ mII \LTl I

Z

u,I I I OUTED-tco O II ---r---

z

o~ oa cn II ii I

O cn c~;o II

u, mm I I uC3 II IIHOh II II cNOTE:m -T]\CL~ II IIr7 I- -II II THE AFT ENGINE MOUNT

II II BRACKETS MUST BEII I I I -I

REMOVED TO GAIN ACCESSIIII /zp TO THE FORWARD STEEL

110~ I 111 i I SIDE OF THE FIREWALLn II/ I I BULKHEAD ASSEMBLY

-I I FOR INSPECTION

PROCEDURES

MAXi..: JM A;ir3WABLE CRACK LENGTHS

F~REWALL

TYP.


j.50if CRACK I;USICATIONS ARE WITHIN THE MAXIMUM ALLOWABLE CRACK LENGTH

3.00 INCHES OUTBOARD

STEEL AND I OR ALUMINUM BULKHEADS

AS REFER TO TCAC .50 INCH TYPICAL INBOARD AND ORINSPECT BULKHEAD INSPECT BULKHEAD

b1068 i ASSY FOFZ OUTBOARD FROM THE LOWER TWO (#5)3.00 INCHES INBOARDMODIFI~ATION PROCEDURE ENGINE MOUNT ATTACHMENT HOLES

NOrr:

IF CRACK INDICATIONS EXTEND BE vOND

SPECIFIED LIMITS, DAMAGED PARTS MUST

BE REPLACED OR AN APPROVED REPAIR

INSTALLED


ACCOMPLISHMENT INSTRUCTIONS: (cont.)

26. Remove field fasteners from the firewall assembly and stringer #2 as required to allow installation of

K660001-3 -4 doublers, K660001-5 radius block and K660000-7 plate as indicated per 610681-1 ASSY.

27. Locate, drill cleco K660001-3 1 -4 doubler on aft side of firewall assembly and K660000-7 plate on forwardside of firewall assembly and match drill parts to existing fastener locations.

28. Approximately 1.00 inch excess material has been left on the K660001-3 1 -4 doubler and K660001-5 radiusblock parts to allow optimum fit. Trim inboard and outboard ends of the parts as required to maintain a

minimum of 2 x fastener diameter edge distance.

29. Locate, drill 8 cieco K660000-3 1 -4 angles, K660000-5 1 -6 angles, K660000-9 -10 clips, K660000-11 1 -12

and K660000-13 j -14 angles as indicated.

30.Sealant and finishes must be restored per recommended Aircraft Maintenance Manual practices after

inspections I modifications are completed.

NOTE:

FOR LOCAL TOUCH UP ON EXISTING STRUCTURE, CHROMATE PRIMER MAY BE USED. DO

NOT MIX CHROMATE AND POLYURETHANE PRIMERS ON THE SAME PART. ALL NEW PARTS

SUPPLIED FROM TCAC ARE POLYURETHANE PRIMED.

31. Prime all bare surfaces and apply sealer per TCAC Process Specification 260.8, install above parts and

fasteners as indicated per 610681-1.

32. Reinstall, reconnect and service components addressed in items 3) thru 20).

Fill out information on the Compliance Card and send to:


Attn.: SERVICE DEPARTMENT

19010 59’" DRIVE N. E.

ARLINGTON, WA. 98223

Page No. 8 of 9


ELECTRICAL LOAD:

No change

WEIGHT AND BALANCE:

No significant change

SPARES AFFECTED:

None

RECORD COMPLIANCE:

Make an appropriate entry in the Aircraft Maintenance Records as follows: Service Bulletin Na. 233, Dated

OCTOBER ?5, 2003, entitled "ENGINE NACELLE FIREWALL REINFORCEMENT", has been accomplished on

(DA TE).

Page No. 9 of 9

COMPLIANCE CARD


ENGINE NACELLE FIREWALL REINFORCEMENT

MODEL AIRPLANE S/N REG. NO. TOTAL TIME (Houns)

OWNER NAME

ADDRESS

TELEPHONE NO FAXNO


CRACKS FOUND: YES O NO O

IF YES, DESCRIPTION AND LOCATION OF CRACK(S):

DATE


(S IGNATU RE)

COMPANY

ADDRESS

TELEPHONE FAX

(D

ALERT

Service Bulletinrrw~U

AIRCRAFT CORPORATION

SERVICE BULLETIN No. 235 DATE: April 16, 2003

UPPER RUDDER STRUCTURAL INSPECTION

1. MODELS AFFECTED Model 685 all serial numbers

Model 690 all serial numbers

Mode1690A all serial numbers"

Model 690B all serial numbers"

Model 690C all serial numbers

Model 690D all serial numbers

Model 695 all serial numbers

Model 695A all serial numbers

Model 695B all serial numbers

Note: all serial numbers are equipped with the fiberglass composite Rudder Tipall serial numbers are equipped with the aluminum Rudder Tip

2. REASON FOR PUBLICATION:

2.1 Paragraph 9 titled Part A of this Bulletin defines a one-time inspection of the fiberglasscomposite rudder tip (P/N 420092-501, -503) which is common to each of the 685, 690,

690A, and 690B models.

2.2 Paragraph 10 titled Part 1B of this Bulletin defines a one-time inspection of the

aluminum rudder tip (P/N 420156-all dashes) which is common to each of the 690C,

690D, 695, 695A, and 6958 models.

2.3 In two recent events involving Twin Commander 690B aircraft the fiberglass compositerudder tip appears to have departed the aircraft in flight. In one event, the aircraft landed

safely; in the second event, the aircraft was lost. Neither rudder cap has been located,

nor has a determination been made as to the cause of either event.

2.4 Reports from the field indicate that some composite rudder tips have sustained unusual

wear of the leading edge (erosion, pitting and cracking) which could result in an overall

weakening of the attendant structural assembly. Reports from the field also indicate

evidence of cracking in welds and fasteners holes of some aluminum rudder tips. In

addition, Twin Commander has received reports of some fiberglass or aluminum repairsaffecting the balancing of the rudder being accomplished without the requiredadjustment to the mass balance in accordance with the aircraft Maintenance Manual

paragraph on Control Surface Balancing.page 1 of 8


2.5 This Service Bulletin defines the requirements for inspection of the rudder tip and

attendant structure.

2.5.~ If any damage to the fiberglass composite Rudder Tip is found, replace the

damaged Tip with the aluminum Rudder Tip P/N 420156-511 (available from anyTwin Commander Aircraft Corporation approved Service Center) per Paragraph 11

of this Service Bulletin.

2.5.2 If damage beyond standard repair is found to the aluminum Rudder Tip, replacethe damaged Rudder Tip with the aluminum Tip P/N 420156-511 (available from

any Twin Commander Aircraft Corporation approved Service Center) per

Paragraph 11 of this Service Bulletin.

2.5.3 If damage is found to structural parts other than the Rudder Tip, request advice

from Twin Commander Aircraft Corporation as to the appropriate action.

3. COMPLIANCE: Within 25 hours or 90 days, whichever comes first.

4. BY WHOM WORK WILL BE ACCOMPLISHED: A 8 P Mechanic or equivalent

5. APPROVAL: Engineering Design Aspects are FAA approved.

6. ESTIMATED MAN-HOURS: 10 hours

7. SPECIAL TOOLS: None

8. INSPECTION METHODS: Close Visual Inspection unless preliminary findings call for further

inspection by another method.

9. PART 1A: INSPECTION INSTRUCTIONS: (Fiber~lass Composite Rudder Tip, see Fia 1)

9.1 Install Rudder Gust Lock on Rudder to line up Rudder with Vertical Stabilizer. Verifythe alignment of the leading edge of the Rudder Tip with the leading edge of the Vertical

Stabilizer. Misalignment would be indicative of structural damage.

9.2 Remove Rudder from aircraft per applicable Maintenance Manual.

9.3 Remove Rudder Tip and perform Inspection of the Rudder Tip. Check for:

9.3.1 Leading edge erosion evidenced by chips, cracks, missing paint, leadingedge delamination (Coin Tap Test)

9.3.2 Previous Leading edge repairs degrading the original strength of the

Rudder Tip (Coin Tap Test).9.3.3 Elongated holes at lower attach screws, missing countersink fairing

washers, cracks around holes and in sidewalls

9.3.4 Proper adhesion of the three vertical stiffener ribs

page 2 of 8


9.3.5 Existing damage due to excessive sanding or exposure to paint strippercaused by the paint preparation process

9.3.6 Inspect for loose fasteners on second vertical stiffener rib web at the lightflasher installation

9.3.7 Delamination or debonding of the trailing edge

9.4 Inspect top Rudder Rib (2 Parts, forward and aft of Rudder Spar).

9.4.1 Inspect top rudder rib forward of rudder spar for cracks. Pay particularattention to the bend radius of rib flange, flange joggle area, and the area

around fastener holes.

9.4.2 Inspect counter weight attachment fasteners to rib (tight, corrosion free,

safetied). Note findings.9.4.3 Remove and Inspect Counter Weight

9.4.3.1 Inspect attach area for corrosion

9.4.3.2 Inspect for proper hardware

9.4.3.3 Inspect for cracks at weight attach holes in rib

9.4.3.4 CAUTION: If counterweight has raised Part Number or letters on

lower surface (surface in contact with rib web), file raised numbers

flush to surface and inspect rib web for damage. Replace Fwd Rib if

required9.4.4 Inspect top rib to rudder spar interconnection area, including splice plate

between Fwd and Aft Rib. Watch for loose fasteners and cracks in

aluminum sheet metal.

9.4.5 Inspect top rudder rib aft of rudder spar for cracks. Pay particular attention

to the bend radius of rib flange, flange joggle area, and the area around

fastener holes.

9.5 Inspect Forward Rudder Spar as follows:

9.5.1 Inspect forward side of Rudder Spar for cracks around fastener holes and in

bend radius, paying particular attention to the Spar area between the topHinge and the Top Rudder Rib

9.5.2 Inspect upper part of the Rudder Spar above Top Rudder Rib, payingparticular attention to the area of the joggle in the spar flange just above the

Top Rudder Rib

9.5.3 Inspect Rudder Hinges and their fasteners

9.6 If no damage is found, reinstall Counterweight, Rudder Tip, and perform Balancing of the

Rudder per applicable Maintenance Manual.

9.7 Touch up paint as required and return aircraft to service.

page 3 of 8


10. PART 1B: INSPECTION INSTRUCTIONS: (Aluminum Rudder Tip, see Figure 2)

10.1 Install Rudder Gust Lock on Rudder to line up Rudder with Vertical Stabilizer. Verifythe alignment of the leading edge of the Rudder Tip with the leading edge of the Vertical

Stabilizer. Misalignment would be indicative of structural damage.

10.2 Remove Rudder from aircraft per applicable Maintenance Manual.

10.3 Remove Rudder Tip and perform Inspection of the Rudder Tip. Check for:

10.3.1 Leading edge erosion or damage10.3.2 Previous sheet metal repairs degrading the originalstrength of the Rudder

Tip (non-standard or undocumented repairs) and/or affecting the balance

of the rudder

10.3.3 Elongated holes at lower attach screws, missing countersink fairingwashers, cracks around holes and cracks in the weld joining both tip halves

10.3.4 Proper assembly of the 2 (two) vertical stiffener ribs (some are riveted,some are spot welded), no cracks in weld area or loose rivets

10.3.5 Existing damage due to excessive sanding during the paint preparation10.3.6 Inspect counter weight attachment fasteners to first stiffener rib (tight,

corrosion free, safetied). Note findings.10.3.7 Inspect for loose fasteners on second vertical stiffener rib web at the light

flasher installation

10.4 Inspect top Rudder Rib (2 Parts, fwd and aft of Rudder Spar).

10.4.1 Inspect top rudder rib forward of rudder spar for cracks. Pay particularattention to the bend radius of rib fiange, flange joggle area, and the area

around fastener holes.

10.4.2 Inspect top rib to rudder spar interconnection area, including splice platebetween Fwd and Aft Rib. Watch for loose fasteners and cracks in

aluminum sheet metal

10.4.3 Inspect top rudder rib aft of rudder spar for cracks. Pay particular attention

to the bend radius of rib flange, flange joggle area, and the area around

fastener holes

90.5 Inspect Forward Rudder Spar as follows:

10.5.1 Inspect forward side of Rudder Spar for cracks around fastener holes and in

bend radius, paying particular attention to the Spar area between the topHinge and the Top Rudder Rib

10.5.2 Inspect upper part of the Rudder Spar above Top Rudder Rib, payingparticular attention to the area of the joggle in the spar flange just above the

Top Rudder Rib

page 4 of 8


10.5.3 Inspect Rudder Hinges and their fasteners

10.6 If no damage is found, reinstall Counterweight, Rudder Tip, and perform Balancingof the Rudder per applicable Maintenance Manual.

10.7 Touch up paint as required and return aircraft to service.

11. PART 2: MODIFICATION:

11.1 Fiber~lass Composite Rudder Tip: If the existing composite Rudder Tip is found to

be damaged, it should be replaced with Kit Number SB235-1 which includes a

replacement Rudder Tip in Aluminum with Installation Instructions and requiredHardware.

11.2 Aluminum Rudder Tip: If the existing aluminum Rudder Tip is found to be damagedbeyond standard repair, it should be replaced with Kit Number SB235-2 which includes

an aluminum replacement Rudder Tip with Installation Instructions and requiredHardware.

12. ELECTRICAL LOAD: No Change

13. WEIGHT AND BALANCE: Negligible

14. PUBLICATIONS AFFECTED: I P C

15. RECORD OF COMPLIANCE:

Make an entry in the airplane maintenance record as follows:

SERVICE BULLETIN NO 235, DATED ,TITLED "UPPER RUDDER

STRUCTURAL INSPECTION", ACCOMPLISHED

16. COMPLIANCE CARD:

Upon completion of all actions required under Service Bulletin 235, complete the attached

Compliance Card and mail (postage is prepaid) or FAX to Twin Commander Aircraft Corp. at

(360)435-1112.page 5 of 8


FIGURE COMPOSITE RUDDER TIP

up

AFT TOP RUDDER RIB

SPLICE PLA

FWD

COUNTERWEIGHT

RUDDER TIP

FORWARD TOP RUDDER R1

TOP HINGEj

RUDDER SPAR I

page 6 of 8


FIGURE 2 ALUMINUM RUDDER TIP

FWD I AFT TOP RUDDER RIB

SPLICE PLA

COUNTERWEIGHT

RUDDER TIP

~´•3

FORWARD TOP RUDDER R

TOP HINGE

RUDDER SPARi

page 7 of 8


UPPER RUDDER STRUCTURAL INSPECTION

COMPLIANCE CARD (p]ease mail this card to Twin Commander at the address shown on

the other side, or fax it to 360-435-1112)

AIRCRAFT MODEL SERIAL NUMBER

AIRCRAFT REGISTRATION TOTAL TIME (HOURS)

OWNER’S NAME AND ADDRESS:

TELEPHONE: FAX:

PARTS REPLACED:

WORK PERFORMED BY (NAME AND COMPANY NAME AND ADDRESS):

TELEPHONE: FAX:

DATE: SIGNATURE:

page 8 of 8


South Hill Drive 6AM-5PM PST M´•F

Brisbane, CA 94005 (800)227-4610


Twi n Commander A/C

695, 695A, 695B

SERVICE LE~TER

1) Applicable AD

2) Part Kit (1)



332 ENGINE FIRE DETECTOR 1)

05/19/1980 RELOCATION 2)

3)

4)100 HR IN SV

333 ENVIRONMENTAL CONTROL UNIT 1)

05/19/1980 (ECU) PRESSURE SWITCH 2) P/N SKA1820

RECALIBRATION OR REPLACEMENT 3) P/N P10M-58

4) 100 HR IN SV

334A ELECTRIC START SYSTEM MODIFI- 1)

03/1611981 CATION AND STARTER-GENERATOR 2)SEE ISSUE

GROUND BUS BAR REPLACEMENT 3)

4) W/I 100 HRS

335 CIRCUIT BREAKER PANEL ASSEMBLY 1)

08/2811980 MODIFICATION 2)SEE ISSUE

3)

4) NEXT 100 HRS

337 ENGINE MOUNT BRACKET 1)

11/21/1980 MODIFICATION 2)

3)

4)SEE ISSUE

338A AFT FUSELAGE THERMOSTAT 1)

03/13/1981 INSTALLATION 2)SEE ISSUE

3)

4) W/I 100 HRS


GC 0853 SI SL

1) Applicable AD

2) Part Kit (1)



339 BAGGAGE HEATER ANNUNCIATOR 1)

01/15/1981 LIGHT LENS REPLACEMENT 2) P/N ACR 11-3AL

3)

4)SEE ISSUE

340 INSTALLATION OF PLACARD FOR 1)

04/24/1981 USE OF ALTERNATE ENGINE OIL- 2)SEE ISSUE

ML-L-7808G 3)

4)SEE ISSUE

342 INSPECTION OF ENGINE MOUNT 1)

06/19/1981 CASTING BOLTS 2)SEE ISSUE

4)SEE ISSUE

343 HIGHER WATTAGE PITOT TUBES 1)

10/19/1981 2)SEE ISSUE

3)

4)SEE ISSUE

344 MAIN LANDING GEAR TORQUE LINK 1)

07/10/1981 SHAFT REPLACEMENT 2)SEE ISSUE

4)SEE ISSUE

345 R1 VERTICAL STABILIZER A~TACH 1)

05/21/1982 BOLT INSPECTION 2) SEE ISSUE

4)SEE ISSUE

346 R1 REPLACEMENT OF INNER 1)

06/23/1986 STRUCTURAL CABIN WINDOW GLASS 2)

3)

4)

347 REPLACEMENT OF INNER 1)

11/03/1981 STRUCTURAL CABIN WINDOW GLASS 2)SEE ISSUE

4) SEE ISSUE


GC 0853 SI SL

1) Applicable AD

2) Part Kit (1)



349A ELEVATOR PUSH-PULL TUBE 1)

02/24/1984 ASSEMBLY INSPECTION AND 2)SEE ISSUE

REPLACEMENT 3)

4)SEE ISSUE

350 COCKPIT INSULATION OVERHEAD 1)

04/15/1982 SWITCH PANEL 2)SEE ISSUE

3)

4)SEE ISSUE

351 PARKER HANNIFIN CORPORATION 1)

06/17/1982 PRODUCT REFERENCE MEMO (PRM) 2) SEE ISSUE

NO. 27 3)

4) SEE ISSUE

352 FUEL CELL INTERCONNECT HOSE 1)

07/30/1982 REPLACEMENT 2) SEE ISSUE

3)

4)SEE ISSUE

353 FLIGHT CONTROL CHAIN CONNECTOR 1)

09/03/1982 LINK INSPECTION 2)SEE ISSUE

3)

4)SEE ISSUE

354 MAIN LANDING GEAR WHEEL 1)

10/01/1982 BEARING AND AXLE HOUSING 2)SEE ISSUE

INSPECTION 3)

4)SEE ISSUE

355 FUSELAGE STATION 386.82 SCREW 1)

11/30/1982 TORQUE INSPECTION 2) SEE ISSUE

3)

4) SEE ISSUE

356 PNEUMATIC TUBE ASSEMBLY 1)

02/25/1983 INSPECTION 2)SEE ISSUE

3)

4)SEE ISSUE


GC 0853 SI SL

1) Applicable AD

2) Part Kit (1)



357A AILERON LEADING EDGE SKIN 1)


3)

4) 100 HR

358 TO ASSURE AUTOMATIC OXYGEN 1)

04/26/1983 MASK DEPLOYMENT 2) SEE ISSUE

3)

4) 100 HR

359 FUSELAGE STATION 386.82 FRAME 1)

06/17/1983 ASSEMBLY MODIFICATION 2)SEE ISSUE

3)

4) 100 HR

360 FLAP BRACKET INSPECTION 1)

08/01/1983 2)SEE ISSUE

3)

4)100 HR

361 TO ELIMINATE POSSIBLE 1)

11/04/1983 INTERFERENCE BETWEEN HYDRAULIC 2) SEE ISSUE

HODE ASSEMBLY AND ELECTRICAL 3)

WIRING 4) 100 HR

362 R1 INSPECTION AND/OR MODIFICATION 1)

05/02/ 1984 OF OBSERVER SEAT SHOULDER 2)

HARNESS STRUCTURE 3)

4)

363 FUEL DRAIN SYSTEM INSPECTION 1)

11/01/1983 2) SEE ISSUE

3)

4)SEE ISSUE

364 SERIES MODE ANNUNCIATOR LIGHT 1)

11/18/1983 TAPE REPLACEMENT 2)TC5003

3)

4)100 HR


GC 0853 SI SL

1) Applicable AD

2) Part Kit (1)



365 FUEL BOOST PUMP REPLACEMENT 1)

02/03/1984 2)SEE ISSUE

4)100 HRS

366A NOSE LANDING GEAR DRAG LINK 1)

03/22/1985 SUPPORT STRUCTURE MODIFICATION 2)SEE ISSUE

3)

4)SEE ISSUE

367 PARKER HANNIFIN CORP. PRODUCT 1)

01/04/1985 REFERENCE MEMO (PRM) NO.36 2)199-13000

(REV.A) (30-107 AND 30-1078 3)

BRAKE ASSEMBLIES) 4) SEE ISSUE

368 HEAVY DUTY NOSE LANDING GEAR 1)

01/04/1985 SPACER ASSEMBLY 2)SEE ISSUE

3)

4)SEE ISSUE

369 LANDING GEAR CONTROL ASSEMBLY 1)

01/11/1985 LUBRICATION 2)

3)

4)SEE ISSUE

370 FREON AIR CONDITIONER 1)

10/04/1985 COMPRESSOR BELT COVER ASSEMBLY 2) SEE ISSUE

INSTALLATION 3)

4) 100 HRS.

371 EXPAND TEMPERATURE RANGE OF 1)

04/24/1989 ENVIRO SYSTEM IN AUTO MODE 2) SEE ISSUE

3)

4) OPTIONAL

372 ENVIRO SYSTEM AMBIENT VALVE 1)

10/12/1989 REPLACEMENT 2)SEE ISSUE

3)

4)SEE ISSUE


GC 0853 SI SL

1) Applicable AD

2) Part Kit (1)



376 Inspection of main landing 1)

04/25/2000 gear clevis and drag brace 2) ED12758

installations 3) ED12526

4) Recommended

End of Index


GC 0853 SI SL

Service Letter Rockwell intemanonal

on~n,n*anomh

sml il*ma

SERVICE LETTER NO. 552

18 May 1881)

ENGINE FIRE DETECTOR RELOCATION

MODELS AFFECTED: MODEL BBOC, SERIAL NO’S 11800 THRU 11825 AND MODEL 085,SERIAL NO’S 85000 THRU 85005.

REASON FOR PUBLICATION: TO PREVENT POSSIBLE INTERFERENCE BETWEEN FIRE DETECTOR

AND LIP OF COWLINO AIR E]OT.

COMPLIANCE: WITH[N NEXT 100-HOURS TIME IN SERVICE.

*011

IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYINGWITH

THIS SERVICE LETTER, CONTACT YOUR NEAREST ROCKWELL

COMMANDER AIPPHORIZED SERVICE FACILITY.

BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EPUIVALENT.

APPROVAL: FAA DOA 8W-a Approved.

ESTIMATED MAN HOURS: ONE (1) HOUR.

PARTS DATA: 1 as. Compliance Card

SPECIAL NONE.


1. Remove upper ca-uling irom left and right engines.

2. Inspect air e~dl lip an ellglne oowllng and pt~ end of engine tire detector fcr any signs oi abrasion due

to interierenoe between fire detector and cowiing air e~dt lip.

3. Inspect for location ci Up d tire detector at tbe co~ullng air sdt.

*OTI

There should be a minimum clearance of 0.12-inch between air edt

Up and att end of fire detector.

4. 1l interierence or mmslocatlon I the airstream is evident, loosen clamps Ottachirg engine fire detectors

to upper strulaassmblles, relocate tire detectors and tighten clamps (see Figure 1,).

5. Relnstsll upper oaull~ on left and right engines.

8. Fill wt and mail Compllanoe Card.



8FARES AFFECTED: NO.


RECORD COMPLIANCE: Make an appropl?ate entry in airplane maintenance records as IoHows: Service

Letter No. 852, dated is May 1850, entitled "Engine Fire Detector Relocation", accomplished (date)

psp~lola

SERVICE LEITER NO. 592

yppeR COWLWO (REE)

CowLnro AIR

E~OTDUCT

~EF)

L _L$kJ1

*aTr

ENBURE A ~UM CLEARANCE OF

O.la-WCB BETWEEN FIRE DETECTORAND COWLWO AIR EXIT DUCT.

~FWD

F1RE DETECTOR ~EF)

f;

L -L BU-J1

UPPER STRUT A88Y ~EF)

TYPICAL INSTALLATION

Flsue 1.

Page a ol 2

COMPLIANCE CARD

From:

Service Bulletin No. 174 PARTIJ

Aimraft S/N

Complied with: Dare

Propeller (Mub) S/N: Left

Blade SIN

Propeller (Hub) S/N: Right

Blade S/N

Time on each propeller: Left Right

Complied with by:

Signaturerco ~r´•aol

osnaal ~risaon oaslon

SW1 Nonh Roctwsll Avsnu~

Belhany.OK73W81405)lsB´•M00

rwx: sla-B3o-ea7o RockwellInternational

May 15 1980 Reference 80 RDL 10 36 pdj

Dear Owner:

Service Letter Number 333 is attached for your information

and action,

Due to temporary availability difficulties, the P10M-58,

pressure switches, are extremely hard to come by.

Be request that you make every effort to comply with part

1 of this service letter, recalibration rather than

replacement, in order to help us through this difficulty.

Sincerely,

RDCKWELL INTEILNATIONAL

AVIATION DIVISION

R,Ron Laurence

ManagerCustomer Service

RDL:pdj

Attachment

Service Letter Rockwell intemsnonal

onnluwononw~nsml N~nh *nnu

8ERVICE LETTER NO. 999

18 May 1880

ENVIRONMENTAL CONTROL UNIT (ECU) PRESSURE SWITCH

RECALIBRATION OR REPLACEMENT

lEoTg

TIES SERVICE LETTER PROVIDES INSTRUCTIONS FOR RECALI-

BRATWO EXISTING P1OM-SS ECU PRESSURE S~TCH OR INBTALL-

nNG A NEW PRESSURE SWITCH (P/N P10M-68) TO A NEW PRESSURE

SETIING RECOMMENDED BY RMCKWELL INTERNATIONAL.

MODELS AFFECTED: MODEL 880C, 8ERVLL NO’S 11800 THRU 11890 AND MODEL 886,SERIAL NO’S 86001 THRU 85010.

REALXIN mR PUBLICA1?ON: TO PROVIDE A PRESSLIRE INDICATION FOR ENVIRONMENTAL

CONTROL UNIT PRESSURE REGULATOR WITH PRESSURE SETTING

DEVEU)PED TO ASSURE THAT "ECU PRESS" LIGHT ILLUMINATES

SHOULD AN OVERPRESSURE CONDITION OCCUR.

COMPLIANCE: WITHIN NEXT 100-HOURSTIME IN SERVICE.

98018

i IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH

THIS SERVICE LETTER, CONTACT YOUR NEAREST ROCKWELL


BYWHOM WORKWILL BE ACCOMPLISHED: A PMECHANIC OR EC~UIVALENT.

APPROVAL: FAA DOA 8W-2 Approved.

ESTIMATED MAN HOURS: PARTI RECALIBRATESWITCH TWO(I)HOURS.

PARTII REPLACESWITCH ONE (1)HOUR.

PARTS DATA: Parts required to comply with Part I of this Service Letter may be procured through your

nearest Rocksell Commander Authorleed Service Facility at no charge. Parts required for Part 1l may be

pracured for $141.80 and a credit of $141.80 will ire issued upon receipt of old pressure switch P/N P10M-SS,a properly executed Warranty CIaim and a Compllmce Card. Rsfsrenee this 8erlce Letter, aircraft model

and laCtory seriP number when ordering 8erviee Letter No. 188 hit consisting of the following:

Kit Na. 1 Partl

lilt Na. 2 Part II

Kit No.l Kit NO. 2

eTY PTY PART NO. DESCRIPTION

1 aa. bXAIBaO Labe~

1 ea. P1OM-S8 Switch

1 se. i ea. Compliance Card

1 ea. Iea. Service Lacer No. 989 Instructions

SPECIAL TOOLS: REGULATED PRESSURE SOURCE AND OHMMETER.

Page 1 of 4

Z

SERVICE LETTER NO. SSS


PART I RECALIBRATE ECU PRESSURE SWITCH

i. Cain access to ECU by removing air outlet duet access (avlonlcs access) cover which is Located on

bottom of an fuselage.

a. Remove BdsUng ECU pressure switch.

S. Recalibrate slddLog ECU pressure switch as follows:

Connect switch to a suitable pressure test set-up which has prodd~s for regulating or meter-

Ing the air pressure applied to the unit from 0 to 1(10 psl accurately indicating this applied

pressure d a psi or better) and connect pins A and B of pressure switch to ahmmeter.

b. Using an 0.080-lneh diameter B flute splined key (Brlebl P/N 8-080), remove locking setscrew

(ANSB5AC4L2). Then, insert key in adlustlng screw (ANWSACLII) and back-out screw oounter-

clockwise to lower setting.

ROTS

Setscrews may be type "H" sockets, in which case a standard

0.050 hex hay may be used.

Hen Socket Head FLuted Socket Head

o. AlterMtely back-out screw 1/4 turn and check trip points until switch actuates at 50 pslg on

increasing pressure. Once set, increase applied pressure to 100 psig, Ban recheolt setting.

d. Look setting adlustlng screw by applying 1 to a drops of Loetlte 2´•12 in hole and replacing

locking setscrew.

*OTT

Aiter.~adlustlng, space remaining above BdlusUng screw may be too

shallow to accept locking setscrew. In which case, omit locking set-

screw entirely and fill space xnth epoxy, Traeon Type 2101, 2128 or

equivsilent.

a. Mar completing above steps, apply bWL18aO Label on pressure switch.

4. ReinsDall edsting recalibrated pressure switch on ECU.

5. Rewire ECU pressure switch electrlosl connector as shown in Figure 2., and connect O ECU.

B. Assure no leaks are evident.

R8Lnstslll air outlet duct access cover.

8. Fill out and mail Compliance Card specifying that Part 1 has been accomplished.

2. Proceed to RECORD COMPLIANCE.

PARTn REPLACE ECU PRESSURE BWITCH

i. Ciain access to ECU by removing air outlet duct access (pvlonics access) cover which is located an

bottom of sit hselage.

2. Remove edalllll ECU pressure switch (see Figure i.).

Page 2 of 4

BERYICE LETTER NO. 553

P1OM-SI) BWPPCHENVIRONMENTAL CONTROL UNIT

(REF)

C~

Pipura i.

BEFORE CHANGE AFTER CHANGE

t--W"~2’

I)CCQPt

ii~ur´• 2.

Page 5 ol 4

IERYICE LETTER NO. )53

3. Install P1OM-18 switch on ECU (see Figure i.).

4. Rewire ECU pressure switch electrical connector as shown in Figure 2 and connect to ECU.

5. Assure no leaks are evident.

8. Reinstall dr outlet duct access cover.

Fill out and mail Compliance Card specifying that Part n has been accomplished.

ELECTRICAL I~AD: NO CHANGE.



PUBLICATIONS AFFECTED: The Airplane Maintenance Manual and illustrated Parts Catalog changes

required by this document will be incorporated at the ned scheduled

change/rsvialon

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service

Letter No. 533, dated 18 May 1880, entitled "Endronmsntal Control Unit (ECU) Pressure Switch

orI(eplaoament", Part Iaccompllshed (date) i PartII accompllshed_lda_t~L__´•

Page 4 014 4

COMPLIANCE CARD

Fmm:

Senrice Bulletin No. ’ln P~RT n

Alrwan SIN

Compliedrrim: Oate~: -sj------------*--cl--

Propeller (Hub) Srm: Lan

Blade S*l

Propeller IHub)S/N: Ri~ht

Blade SIN

Time on sad,pmpller: bft Riet

Complied with by:

Si~rmn,res i~´•so)

__

Sevvi~e Letter Culf~streamAmeriranCORPOR*TION

Cammads MullionSW1 Norm Aa;tnsll Avenue.Bam´•ny. OLlahoma 73008

SERVICE LETTER NO. 9S4A((llpersedes Servloe Letter No. 554, dated a0 June 1880, in its entlretg.)

16 Maroh 1881

ELECTRIC START SYSTEM MODIFICATION AND STARTER--GENERATOR

GROUND BUS BAR REPLACEMENT

MODELS AFFECTED: PART I MODEL BgOC, 8ERUAL NO’S 11601, 11605 THRU 11BM,1180$ TBRU 11815, 11615 TH(U 11818 AND 11621 ANDMOD1L 085, SERIAL NO’S 85001 THRU 85002.

PART n MODEL 680C, SERLAL NO’S 11801, 11805 THRU 11618,11821 THRU HBZB AND MODEL BsS, SERIAL NO’S85001 THRU 85004 AND 85006.

PART m- MODEL 680C, SERIAL NO’S 11600, 11802, 11820 AND11821 THRU llBSS AND MODEL 885, SERIAL NO’S

85000, 85005 AND 86001 THRU 85015.

PART IV MODEL 685, SERIAL NO’S 85000111RU 85055.

REASON FOR PUBLICATION: PART I TO PROVIDE SERIES BATTERY VOLTAGE FOR IGNITOR

UNIT, ENGINE FUEL VALVE AND START PRESSUREREGULATOR DURING 8ER1ES START AND PROVIDEIMPROVED BATTERY GROUND.

PART n- PROVIDE SERES BATTERY VOLTAGE FOR UNFEATII-ERINO PUMP, OIL VENT VALVE, ANTI-ICE LOCKOUT

VALVE, CENTERINSTRUMENT PANEL LIGAPINO, NTS

TEST AND BLEED NE VALVES DUIL1NG SERES START,PROVIDE AN ]MPRDVED STARTER-GENERATOR GROUNDBUS BAR AND INCREASE SERVICE LIFE OF GENERATORCONTROL UNITS (OCU) BY PROTECTING INTERNALTRANSISTOR FAILURES.

PART m- To INCREASE SERVICE LIFE OF GENERATOR CONTROLUNITE (OCU) BY PROTECTING INTERNAL TRANSISTORFAILURES.

PART IV TO ENSURE THE CAPABILITY OF PERFORMING 6E111E88TART8 WITHOUT TRIPPING CIRCUIT BREAKER.

COMPLIANCE: WITHIN NEXT 100-HOUR TIME RI 8ERVICE.

*011

COMPLIANCE WITR PARTS I, n, AND m, of SERVICE LETTER NO´•

554, DATED 20 JUNE 1860, A8 AMENDED BY RFVIblON 1 AM) 2,CONSTITUTES COMPLIANCE WITH PARTS I, n, AND m or THIS

(IERVICE LETTER.

PART IV 16 AN ADDITIONAL IMPROVEMENT, RE9UIRINO COMPLIANCE.

IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS8ERVICE LETTER, CONTACT YOUR NEAREST OULFSTREAM COMMAM)ER

AUTHORIZED BERVICENTER FACILITY.

Page 1 of 14

SERVICE LETTER NO. S3UL

BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC DR EQUIVALENT

WOll

DUE TO COMPLEXITY OF THIS SERVICE LETTER, IT L6 RECOMMENDED

THAT AN AUTHORIZED LIEHVICENTEH ACCOMPLISH THIS WOI(K´•


EST1MATED MAN HOURS: PART I ~X 16) HOURS.

PART n TWENTY (20) HOURS.

PART nI ONE (1) HOUR.

PART IV- THIRTY (80) MINUTES.

norr

Gulfstream American Corporation, Commander Division, will allow a

credit of six (6) hours for Part I, twenty (20) hours for Part n, one (1)hour far Part m and thirty()0) minutes for Part IV upon receipt of a

properly executed Warranty Claim with attached Compliance Card.

PARTS DATA: Parts required to comply with this Ber~oe Letter may be procured through your nearest

Oulfstream Commander Authorized ServlCenter Facility for: Kit No.l (BS.19, Kit No. a S?8. 58, KitNo. 3 $4.05 and Kit No.4 822.19. A lull credit will be issued upon receipt of a properly executed

4arran~y Claim and a Compliance Card. Reference this Service Letter, aircraft model and factory serialnumber when ordering Service Letter Nq´• 334A Rit(a) consisting of the following:

s.~ uai~l ~´•h´•nr ihauc nolir´•

Kit No. 1- PART I W011 Refer to airplane Seria~ Number eiectlldty ca~l-KitNo. 2 PART n out to determine which hit or hits are required.Kit No. 3 PART III

Kit No. 4 PART IV

Kit Kit I Kit I KitNo.l No.2 I No.S No.4

QTY QTY PTY 4TY PART NO. DESCRIPTION

1 ea. I I I 1 800522-1 Matntlng Strip2 ea. I I I I 800612-RE1 I Bus Bar

1 ea. I- I- I- I 800612-RE3 Cable

2 ea. I I I 1 93(1060~1 Clip Assy1 ea. I- I- I- I AOC-5 Fuse

1 ea. I- I- I- I AN4-5A I Bolt

2 ea. I I I I ANOBODIOL Washer

1 ea. I- I- I- I ANIIBODdlBL Washer2 ea. I I I I AN860D6 Washer

1 ea. I- I- I- ANO?O-( I Washer

8 ea. I I I 1 D-436-53 Splice1 ea. 1 ea. I I I HDJ-A Fuse Holder

2 ea. I I I I IN3209 I Diode

2 ea. I I I I M?8a8/1-LS Terminal

4 ea. I I I 1 M1826/1-22 Terminal

6 ea. I I I M1828/1-a4 Termina~

2 ea. I I I I M1B28/1-25 Termlnn~

2 ea. 2 ea.l I M1828/1-33 Terminal

I ea. 1 2 ea. I I I MS21a42L4 I Nut

2 ea. I I I I M8a1044NOB Nut

2 ea. I I I I MSalBlsDOB I Clamp2 ea. I I I 1 MS21058-1-08 1 Screw

2 ea. I I I 1 M835206-228 1 screw

Page 2 of 14

SERVICE LETTER NO. S9~A

1ait I 161L I- 1 M81044/8-18-8 Wireas ft I I 1 1810(4/13-22-8 Wire

IS ft 1S ft M81044/6´•a0-8 Wire2ea. I I I)OOB?a-ONI~O Cable Aesy2 ea. 8006?5-41 Bus Bar1 ea. 835058-1 Relay1 ea. AOC-?. 5 Fusea ea. ANI-UL Bolt2 ea. I I I AN86O-41BL WasherZea. MS11012L04 Nut8 ea. 2 ea.l I MSa5181-1 8utt Splicea ea. MSsS206-214 Screwlft I- I- I RNF 100 Tubing (Type I, 1-1/2"Ma.)4 ea. 8-5A2 Mode

I 1 ea. 1211-6-1-1/a- 12-501-81 Circuit Breaker1 ea. Il ea. 1 ea. 1 ea. Compliance Card

1 ea. 8erdee Latter No. SS1IA Wiring Magrams1 ea. 1 ea. 1 ea. 1 ea. Service Letter No. 334A instructions



PARTI

1. Gain access to batteries, located in aft fuselage, through baggage computmenl door.

2. Remove baggage compartment liner to gain access to batteries and Power Distribution Panel.

3. Disconnect and remove both batteries from airplane.

4. Drill and install 830080-1 clip assembly (a places) on aft angle of right battery support (see Figure i.).

5. Install one end of 800812-RES cable on left battery support using edsting hardware and insta~l otherend of cable on fuselage frame at Sta 212.00 using AN4- SA bolt, ANB?0-4 washer, AN860D41BLwasher, and MSZ1042L4 nut (see Figure 1.).

6. Install MS21818DG8 clamp (2 places) on 80067a-RES cable and attach to 830080-1 clip assemblies usingMSa?(lSg-I-08 screw and ANLIBOD1OL washer (see Figure i.).

1. Remove cover assembly from Power Mstributlon Panel.

8. Dsconnect wires No. 6, No. No. 8, No. g and No. 88 from CR-I diode, cutoff ring terminals andsplice wires No. B, No. No. 8, No. 8 and Na. 88 together using splice (see F~gure 2.).

*011

On Model 685, wire No. 239 should also be dlaconnected andspliced to the above listed wire numbers.

g. Disconnect wires No. 106, No. 101, No. 108, No. 109 and No. 198 from CR-2 mode, cutoff ringterminals and splice wires No. 106, No. 101, No. 108, No. 109 and No. las together using D4SB-53splice (see Figure 2.).

11011

On Model 685, wire No. 243 should also be disconnected andspliced to the above Usted wire numbers.

in. Install 800522-1 mounting strip, INS208 diode (2 places) and 800612-RE1 bus bar (2 places) on elatingCR-I and Cn-2 diodes. Clean mounting strips and bus bar for good continuity (see Figure 3.).

11. MssonMeot wire No. 4 from pin Aa of KS relay and connect wire O CR-I mode and diaeonneot wireNo. 104 from Fdn A2 of KB relay and connect wire to OR-a diode (see Figure 2.).

Page S of 14

SERVICE LETTER NO. 334A

la. Install wire No. 4A from CR-1 made bus bar to pin A2 of KS relay and Lnstlll wire No. 104A from Cf(-a

diode bus bar to Fdn A2 of K8 re~ay (see Figure a.).

13. Install wire No. 131A on CR-S and CR-4 diode and tnstsill wire No. 191 on CR-S diode and route to K25

relay on relay panel and connect to terminal B3 (see Figure a.).

14. Install wire No. 130C on 82 of g25 relay, r~Le wire i~ong edsdng wire bundle at to Start

Control Panel which is Located at of left battery and insta~l HDJ-A Bae holder (F41) (see Figure 2.).

15. Install Wire No. 13OA from WJ-A fuse holder (F41) to terminal 12 of K18 relay which is Located on

Start Control Panel (see Figure 2.).

YOlr

Fuse holder should be inst~lled within B-Lnches of terminal 12 of

K18 re~ay.

16. Install AOC-5 B.e in HDJ-A fuse holder (F(1) (see Figure a.).

W~SHER IUNDER NUTLaaelo´•4 wnstlsn (8EmEEN BOLTI(EI\D AND TERMINIIl)

INUT

0.2CI" DI* AND CLE*NMIZlglsD08CLIMP

SURFPICE AROUND BOTH llDE8MSnOJS´•laBMREW

OF HOLE TO ASPURE I\NgMIDIOL WPgHERAOOOD OAOUND PLSI

slooso.~ CLIP nsSY.

PLS)

RBATTERY

IRE Fl

CABLE

ExlsnNacnsrEslREFI

HaRDwnnE

Anouhlo BOTHSIOEF OF HOLEmAIURE AOOODOROUND

\Y´•

SyppOnT IREFI

Figura i.

Page 4 of 14

BERVICE LETTER NO. S94A

nurr ~t,curaa~b mwaur a

vl,c~ rr woru ur~a

T (nP RV 1! +~Y´•Sbr

dC~W)

m ~NI m BE M/´•i~>-l

3 nnufo DEUOIE

a bOllr, LIUCI DLYIVC U/P~ C

IIL~t---* Q41 wMw~

~YUIL (S rm~

9

L-~ib x~

ICI131~

xr

8r"/1

ca ~I0´•43853SPLICE

a -3

1 1´•´•~p’

I ooc r

w

re ~cr,

r"XIIIVI~

IIV mUINPL

~__m --~i;zn ihaL-----ln~n

a~ot

Oy.lmasm wnv

naureu~n

(1 IV ~69i0 ITCC)

IIIDLX.´•)

anms mpa

Q rurnur Mn.w~r

Fipur´• i.

Page 5 of 14


B008~2´•RE1 BUSB~R rZ PLS)

1’INJZOB DIODE

II1’

12 PLSL

rr-l

;L-..iI :F8 880522-1 MOUNTINGSTRIP

1IN32W DIODE (REFI

800672-661 BUSsnR IREFI

~uL

808522-1 MOUNTINGSTRIP IAEF1

POWER DISTRIBUTION P~EL IREF)

Fiour´• 3.

1? MsooMect wire No. 16 from CBBI series au~llary circuit breaker, wNch is located on Start Control

Panel, and connect wire to terminal 11 of K17 relay (see Figure 2.).

18. Install wire No. 76A from terminal 11 of K17 relay to termlna~ 11 of K18 relay (see Figure 2.).

18. Instill wire No. 130 from Lermlna~ 12 of K17 relay to terminal 12 of gig relay (see Figure 2.).

20. Install wire No. 130B from termin~ilii of K1? relay to CB61 series audl(ary circuit breaker (seeFigure 2.).

21. Retnstall batteries in airplane but do not connect battery Lermina~s. Fill out and mail Compliance Card

specifying that Part I has bean accomplished and proceed to step 5. of Part n.

PART II

11016

The following wire numbers in Part n are M81044/9´•2P8 (20 gauge) wire:No. 1A, No. 201, No. Z0?A, No. a018 and No. a0?C. Wire No. 210 and

No. 271 are M81044/9´•18-8 (18 gauge) anre. All other wires are M81044/12-21-8 (22 gauge) ~re.

1. Gain access to batteries, located in aft fuselage, through baggage compartment door.

2. Remove baggage compartment liner to gain access to batteries and Power Mstribution Panel.

3. MeeoMect battery terminate from batteries.

4. Remove cover from Power Distribution Panel.

Page 0 of 14

IERVICE LETTER NO. 934A

POWER DISTRIBUTION PANEL

9 cb-2

i j

r-\L´•i

13~

PUSE PANEL IREFI

FII FIZ F13 Flr 115

00000MSS9206-2146CREW

BPLS)

1175

0.30"

’i llr

SS:,oSP-l RELnvIMOUNT ON B*CK SIDEOEPANEL)

iiSure 4.

5. Locale, drill and install 853098-1 relay on fuse panel assembly wNch is Located on forward side of

Power Distribution Panel, using MSSS206-21( screw (2 places) and MSZ1042L04 nut (2 places) (see

Figure 4.).

B. install wire No. 1S1B from terminal B3 of K26 relay to terminal X1 of K?S relay (see Wiring Diagrams

No. 1 and No. 2).

11011

Reference to Wring Diagrams No. 1 UIN NO. 8 are U1B

vlrl~g diagrams included wiUl Ule kit.

Page 1 of 14

BERVICE LETTER NO. 394A

7. Install wire No. 1S1C from termlna~ X2 of K?5 relay to GND terminal of overvoltage sensor (see Wiring

Diagrams No. 1 and No. 2).

8. Disconnect wire No. 1 from termin~ B2 of K8 relay and connect to termina~ A9 of K15 relay (see

Wiring Diagrams No. 1 and No. a).

8. Install sire No. lA from termlnsl AZ of K?5 relay to terminal 81 of Kg relay (see Wiring Diagrams

No. 1 and No. 2).

10. Disconnect wire No. 101 from terminal B2 of KiO relay and connect to terminal BS of K?5 relay (see

Wiring Diagrams No. S and No. 4).

II. Insta~L wire No. 207B from Fdn A of P131 connector to terminal B1 of K?S relay (see Wiring Diagrams

No. 9 and No. 4).

12. Install wire No, 2O7C from terml~plB1 of K75 relay to terminal Al of K?S relay (see Wiring Diagrams

No. i, No. 2, No. S and No. 4).

13. Install wire No. 101A from terminal B2 of K?5 relay to terminal B2 of K10 relay (see Wiring Diagrams

No. 3 and No. 4).

14. Install wire No. 207, HDJ-A fuse holder (F42) and wire No. 207A. Wire No. 207 connects b terminal

A2 of K18 relay and to HDJ-A fuse holder and wire No. 20?A connects to pin A of J197 connector and

Lo HDJ-A fuse holder (see Wiring Diagrams No. 9 and No. 4).

WOll

The HDJ-A fuse holder is an inline fuse holder installed between

5137 conneclor and start control panel. Fuse holder should be

Installed within B-inches of termina~ A2 of K1B relay.

15. Install AOC-7.5 fuse in HDJ-A fuse holder (F42) (see Wiring Diagrams No. 3 and. No. 4).

18. Disconnect wire No. 12 from terminal L2 of CS-1 left generator field current sensor, splice wire

No. 270 to wire No. 12 with MS25181-1 bull splice andconnect wire No. 21(1 to terminal 24 of K1? relay

with M7828/1-53 terminal (see Figure 5.).

17. Disconnect wire No. 128 from termlna~ LZ of CS-I right generator field current sensor, splice wire

No. 271 to wire No. 128 with MS25181-1 butt splice and connect wire No. 211 to terminal 24 of K18 relay

with M1828/1-SS terminal (see Figure 5.)

18. On Model 680C, 8eria~lnumbers 11801, 11803 thru 11609, accomplish the following:

If Wire No. 203 is connected to terminal AS of K13 relay, disconnect from K1S relay and connect to

terminal A3 of Ka5 relay (see Figure 8).

*011

Wire No. 203 must be routed from Fdn V of 548 connector to terminal

AS of K25 relay´•

18. Lower overhead switch panel as follows:

a. Loosen alien screws on all tnobs on face of the electroluminescent panels and remove ~nobs.

b. Remove attaching screws secudng electroluminescent panels.

c. Carefully remove panels and, expose electroluminesoent panel wiring.

d. Grasp wires and gently pull down until quiok disconnect and airplane wiring are exposed.Disconnect electroluminescenl panel.

a. Remove atlaehl~ screws from top of metal plate of overhead switch panel and pull top of paneldown. Entire panel will hang in a vertical position suspended by the hinges.

Page 8 of 14


*12

REMOVE D~8HED WIRE REMOVE

L2

FROM L2FROM L? 1 155

55 IREF) I IIREF)

13 e ~alL__

I ~‘bsolaEn--r72 129

1 BUTT SPLICE Mn5181´•1 BUTT 8PLICE~P~DO NEW WIRE ~DD NEW WIRE

MlllLId18´•1&8

r T1 55 (REF1

3JTERMINn~

55 (REF1 1551REF)

I I _LI h!eg, ~-09

QP 25

M)92811J3 TERMIN~L

Pieu~s 5.

28. on Modej880C, rewire the overhead switch panel as follows:

a. Disconnect and dead end the following wires: (see wiring diagrams in Chapter 81 of the Airplane

Maintenance Manua~ for wire location):

(1) Wire No. 1E1Ba2 between terminal strip TB1B and pin P of P30 Connector. Dead and at

terminal strip TB16.

(2) Wire Na. 1E1C22 between pbnP of P3O Connector and terminal a of left NTB test switch.

Dead end at NTS test switch.

(3) Wire No. 2E1B22 between terminal strip TB8 and pin R of P30 Connector. Dead end at

tsrmlna~ strip TB8.

(4) Wire No. 2E1C22 between ~Ln R of P30 Connector and terminal 2 of right NTS test switch.

Dead end at NTS test switch.

b. install wire No. 1E28D22 from terminal 2 of Left NTS teet switch to termlnail 1 of Lan ITT

compensator test switch (see Wiring Diagram No. 5).

c. Instan wire No. 2328022 from terminal 2 of right NTS test switch to terminal 1 of right ITT

compensator test switch (see Wiring Diagram No. 5).

21. On Model 885, rewire the o~srhead switch panel as follows:

a. Disconnect and dead end the following wires (see wiring diagrams in Chapter 81 of the Airplane

Maintenance Manual for ire location):

(1) Wire No. 1E1Da2 between terminal 2 of left temperature compensator test switch and

terminal 2 of left talque limit control switch.

(2) Wire No. 211022 between terminal 2 of right temperature compensator test switch and

terminal 2 of right torclue limit control switch.

Page 8 of 14

SISRYICE LETTER NO. 994A

b. lnstail wire No. 1E2BF22 between terminals a and 5 of left temperature compensator test switch

(see Wiring Diagram No. B).

c, fnsta~lwire No. 2E2BF22 between terminals 2 and 5 of right temperature compensator test

switch (see Wiring Diagram Na. B).

22. Reinstail the overhead switch panel as follows:

cnurlon

When Insfs~lilg the overhead switch panel, ensure that all wires

and busses are properly secured and are not squeeled or chafingon airframe. This will prevent possible short circuits.

a. Swing overhead switch panel up and secure with attaching screws.

b. Connect electrolumlnescent panel wiring to airplane wiring and position panel for installation.

Stow excess wiring eneudnglhat it will not be pinched or crimped when panel is secured.

c. Secure electrolumlnesoent panels with attaching screws.

d. Relnstall aill knobs using existing alien screws.

2). Remove knobs from oil temperab~re control levers to facilitate rsmov~l of radar scope.

24. Remove and disconnect radar scope from center instrument panel.

25. Remove circuit breaker panel as follows:

a. Pull co~lot control wheel to full, aft position and secure.

b. Reach under and behind circuit breaker panel and disconnect electrical connector plugs and

wiring.

c. Remove attaching screws from front of panel and carefully remove circuit breaker panel

d. Remove backppate cover from circuit breaker panel to gain access to wiring.

28. Instsill S-SAI diode (2 places) on circuit breaker panel terminal board M (see Figure 8 and Wiring

Diagram No. 1).

OO tK%oo

TERMINAL BOARD "M’~ IREF)(LOCPITED ON CB PANELI

O o

ssAu DIODE

Fieura 6.

21. Disconnect wire No. 10 from pin A of 91 connector and connect to terminal 29 of terminal board M

(see Wiring Diagram No.

11015

When viewing the J1 connector, "A" appears as "a".

28. lnstail wire No. 10A from terminal 11 of terminal board M to pin Aof SI connector (eee Wlri~ Diagram

No.

Page IO of 14

BERMCE LETTER NO. 534A

28. Install wire Na. 1SZA from terminal 22 of Lennina~ board M to termmnail D2 of K20 relay (see Wiring

Diagrams No. 5, No. B and No.

SO. Reinsts~L baoltplate cover on circuit breaker panel.

51. The following wiring is located behind the center instrument panel:

a. Install wire No. PB1022 by iud splicing to existing wire No. L23E22 and install S-3A2 mode

(2 places) (see Wiring Diagram No. 8).

*011

Wire No. P61D22 and Wire No. L25Eaa are not to exceed B-lnches in length.

b. hst~l wire No. P5ICI0 on mode installed in step a. (see Wiring Diagrams No. 1, No. 2 and No. 8).

c. Disconnect wire No. PB1AIO from pin V_ of P? connector, install wire No. PB1BIO on pin Y ofP? connector and butt splice wire Nos.PB1AfO, P61B20 and PB1COO together (see WiringDiagram No. 8).

52. Reinstall radar scope on center instrument panel and reinstall knobs on oil temperature control levers.

55. Relnsla~l circuit breaker panel as follows:

a. Ensure that backplate cover is installed on circuit breaker panel.

b. Position circuit breaker panel close to its mounting position and connect electrical connector

plugs and wiring.

c. Position circuit breaker panel for installation and secure with existing attaching screws.

d. Release ooFdlot control wheel and allow it to move forward.

34. Remove upper cowling from left and right engines.

55. Disconnectwire Nos. 1PS5A4, 1P2?A2 and 1P28A2 from left and wire Nos. 2P55A4,2P21A2 and 2P28A2 from right starter-generator (see Figure and Wiring Diagrams No. 1, No. 2,No. 9 and No. 4).

56. Install RNF 100 (1.5-inch) tubing over wires, reconnect wires to starter-generator bus bar and slide

tubing over bus bar and sire terminals. Heat shrink tubing and secure with ty-raps (sse Figure 1.).

llOTI

Clean sill terminals prior to installing.

S1. Remove and discard existing starter-generator grmnd (OND) cable and existing ground cable bus bar

from left and right starter-generators.

58. Install 800615-4’1 bus bar on starter-generators using existing hardware and reconnect eldsdng wires

(see Figure

99. Install 800612-OND-0 cable assembly using slsting hardware and AN4-4A bolt, ANgBO-41BL washer

and M821042L4 nut (see Figure

40. Reinsta~l upper cowllng on left and right engines.

41. Relnstall cover assembly on Power Distribution Panel.

42. RecoMect battery terminals to batteries.

45. Assure that airplane electrical system is functioning properly.

44. Relnstilll baggage compartment liner.

45. Fill out and mall Compliance Card specifying that Part II has been accomplished.

Page 11 ol 14

BERYICE LETTER NO. SS4A

PART III

i. Gain acoess to bat~eries, located tn ait fuselage, Ulra~gh baggage conpartment door.

2. Remove baggage eomparDnent liner to gatn access to ba~terles and Powe. Mstribution Panel.

INSTALL IX´•´• ITERMINATION

LENGTH OF TUBINGTO BE I.W" PRIOR TO SHRINKING. POSITIONTUBING SO THAT BUS 8AR. TERMINAL TONGUES

MSZ10(2L4 NUT HABDWARE ARE COMPLETELY~N980dlBL WASHER

1N44~ BOLT

,TY´•RAP (REFL

80087547 BUS BAR o(EXISTINO WIRES NOT c

SHOWN FOR CLARITY)

BWB72´•ON00 CABLE ASSY IREF)

STARTER´•OENERATOR (REF)

~igurs 7.

illi--t~I I Brll

I--

LO(REF)7 X1*1

xl B2(REF)-----IBD(RTf)

il5:i

7slarF) ----1 q_

L_ v

1------~-----DISCONNECT DASHED WIRE AND CONNECTTO TERMINAL /u OF 126 RELAY qT IREF´•--( T

Jyb P4b

~i(lur´• B.

Page 12 of 14

SERYICE LETTER NO. 3S4A

3. Disconnect battery terminals from batteries.

4. Remove cover from Power Distribution Panel.

5. Disconnect wire No. 12 from termin~lL2 of CS-1 left generator field current sensor, splice wire

No. 210 to wire No. 12 with MSa5181-1 butt splice and connect wire No. 210 to terminal 24 of Fl?

relay with M?828/1-33 terminal (see Figure 5.).

8. Disconnect wire No. 128 from terminal L2 of CS-2 right generator field current sensor, splice wire

No. 211 to wire No. 129 with MS25181-1 butt splice and conned wire No. 2?L to terminal 24 of K18

relay with M?828/1-5S termina~ (Bee Figure 5.).

89. On Model 880C, Brlsil numbers llBDO and 11802, accomplish the folloHrlng:

If wire No. 205 is connected to terminal AS ofK1S relay, disconnect from K1S relay and connect to

terminal AS of Ka5 relay.

WOII

Wire No 203 must be routed from pin V of 548 connector to terminal

AS of K25 relay.

Reinstall cover on Power Distribution Panel.

8. ReooMecl battery terminals to batteries.

8. Assure that airplane electricail system 18 functioning properly

10. Reinstallbaggage compartment liner.

11. Fill wt and mail Compliance Card specifying that Part ill has been accomplished.

PART IY

i. Cain access to start control panel, located between batteries, in aft fuselage, by removing rear baggage

compartment liner.

2. Disconnect battery connectors from batteries.

3. Remove attaching nut and washer, seeuri~g circuit breaker, CB81, to Miscellaneous Start Panel (refer

to Figure 38~218, Chapter 30, of the Maintenance Manual).

noTr

Circuit breaker will drop out from panel,

4. Remove attaching screws for wiring connection and remove electrical wires.

5. Remove circuit breaker.

8. IoBta~l electrlca~ wiring to new circuit breaker, P/N 1211-5-1 1/a-12-501-61 with attaching screws.

Position circuit breaker in panel and secure with washer and nut.

B. Connect battery connectors to battery.

8. Ensure that airplr~ns electrical system is functioning properly

1(1. Instzll rear baggage oompartment liner.

ii. Fill out and mall Compliance Card specifying that Part IY of this Service Letter has been accomplished.

Page iS of 14

SERVICE LETTER NO 13U

ELECntICAL LOAD: WD CHANGE.

WEIOBT AND BALMCE: The sdght and balanee elnrge required by i~BUUatlon ol this Sernce Letter is as

folloars:

wna;ar nes) H-ARU mrBES) H-YOYEIF QN-LQs)

Fart I- ’2.M) t185.00 590.0

Fart n NO CHANGE.

Fart m No CHANGE.

PART TV NO CHANGE.


PIlDLlCAnDNS AFFECTED: The Munrenanee Manual and Illustrated Plnr Cabl~G c~n%esrequired by U1B document uill he ineorporated at the next scheduled

MOTE

Insert the Wiring Diagram chanb~es provided with this service I.cltsrIn the Airplane MaintenRnee Manual until the revised ulri~ dlayramslor the Maintenance Manual are available

RGCORD COMPLIANCE: Mate an c~ry is the ´•Irpl~p mslote~oce reeorde as lollovs: Service

Letter No. 3JU, dated 16 Yarrh 1981, entitled "Elect~e Start System YomBaUM and S~rter-Gcnmtor

Bus Bar RcplPeement". Part 1 Part n aeeomplished (dlte)Pilr(m aecompa´•beq_ (date] Part IV (dlte)

Rite 1I al II


WIRING DIAGRAMS

RETAIN THESE WIRING DIAGRAMS WITH

AIRPLANE MAINTENANCE MANUAL UNTIL

REVISION TO MAINTENANCE MANUAL IS

AVAILABLE.

Service Lettev Iponnlaru~mM´•mwnl NOrU R~*lll *mU

SERVICE LETI‘ER NO. 595

28 August lsBO

CIRCUIT BREAKER PANEL ASSEMBLY MODIFICATION

MODELS AFFECTED: MODEL 6800, SERIAL N0’S 11600 THRU 1189g AND MODEL 885,SERIAL NO’S 86(100 THRU 95024.

REASON FOR PUBLICATION: TO PREYENT P0SSlBLE CROSS CIRCUITING OF DISTR-I AND

RADIO-1 CONTROL CIRCUIT BREAKERS.

COMPLIANCE: WITHIN NEXT loO-HOUR8 TIME IN SERVICE.

11011

If ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYWG WITH

THIS SERVICE LETTER, YOUR NEAREST ROCKWELL


BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR


ESTIMATED MAN HOURS: TWO (a) HOURS.

PARTS DATA; Parts required to comply with this Service Letter may be procured through your nearest

Rochwell Commander AuUlori.ad Service FaelllLy for $4.12. Reference this 8arvtce Letter, aircraft model

and lacbrg serial number when ordering Service Letter No. 995 kit oandstlng of the following:

aauajnto~nn*inannorc

OTY PART NO. DESCI(IPTION

1 ea. 850618-5 Insulator

3 ea. MISB7-4-8 TLedown Strap

t ea. Compliance Card

1 ea. Service Letter No. 335 Instructions


ACCOMPLISBMENT INSTRUCTIONS:

i. Assure that bansry switch is in Ule OFF position.

a. Remove circuit breaker panel as lollo´•ua:

a. 111 copilot control wheel to b~U aft position and secure.

b. Reach under and behind circuit breaker panel and disconnect eleetriaal connector plugs and

wiring.

c. Remove attaching screws from front of panel and carehully remove circuit breaker panel.

d. Remove baokplate cover from circuit breaker panel to gain access to circuit breakers.

3. Install 850818-9 insulator between DISTR-a RESET circuit breaker and RADID1 REBET circuit

breaker using MSSSB1-~P-g tledown strap (9 places) (see Figure i.).

4. Reinstail bacbplnte cover on circuit breaker panel.

Page 1 of a


!O

’"~I’ r=´•´•´•´•~

ef~i´•

a

Es

io c

clRCurr BREAKER

PANEL (REF)olsw-a RESET (CB NO.S1)CIRCUIT BREAKER

850818-3 TNBULATOR

RADIO-I RESET (CB NO. 48)MSSSB1-4-9 TIEMIWN CIRCUIT BREAKER

STRAP (5 PL8)

I´•isur´• 1.

5. Reinstaillcircuit breaker panel as follows:

a. Position circuit breaker panel close to Ya mounting poldt(on and connect electrical connector

plugs and wiring.

b. Position circuit breaker panel for insta~latlan and secure wit easll~ attaching ser~ula.

c. Release copilot control wheel and aYow to move forward.

d. Check cbcuit breaker panel for operational integrity.

8. Fill out and mail Compttance Card.





RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as ioHove: Se~ee

Letter No. 555, dated 28 August 1980, entitled "Clrcult Breaker Panel Assembly Modilcatlon", accomplished(date)

PageaolZ

Rockwell internat~onsl

ev pnnaMlnoM´•a6W1 Nonh Ro~all *nnu

i

LITPIH NV. YY’I

91 NOVEMBER 1880

ENGINE MOUNT BRACKET MODIFICATION

MODELS AFFECTED: MODEL 690C, 8ERIAL NO’S 11681 THRU 11850 AND MODEL 696, SERIAL NO’S. 99018THRU 96035.

REASON FOR PUBLICATION: TO PROVIDE PROPER CLEARANCE BETWEEN ENGINE MOUNT BRACKET ANDOIL FILTER ADAPTER CLAMP PLATE WHEN INSTALLING MODIFIED OIL FILTER SWIVEL ADAPTER.

COMPLIANCE: WITHIN NEXT 100-HOURS TIME W SERVICE.

c.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS SERVICE LETTER, CONTACT YOURNEAREST ROCKWELL COMMANDER AUTHORIZED SERVICE FACILITY.

BY WHOM WORK WILL BE ACCOMPLISHED:_4 P MECHANIC OR EQUIVALENT.

APPROVAL: FAA DOA 8W-2 Approved.

ESTIMATED MAN HOURS: SIXTEEN (18) HOUR8:

Rockwell International, General Aviation Divieion.will allow a

credit of 16 hours upon receipt of a properly executed WarrantyClaim and a Compliance Card.

PARTS DATA: 1 ea. Compliance Card

SPECIAL TOOLS: PROPELLER SLING AND ENGINE HOIST


1. Remove upper and lower cowling from lelt and right engines.

2. Attach propeller sling to propeller blades and connect sling lift ring to engine hoist and asnure that engine is support-ed by sling and hoist.

S. Remove bolt attaching lan and right engine side mount brackets to mount isolators (see Figure 1.).

4. Remove bolt (4 places) attaching left inboard and right outboard mount brsclsts to engine (see Figure 1.). Thismount bracket is the one located below the oil filter.

6_ Remove mount brackets from anginas.

6. Modify existing left inboard and right outboard engine side mount brseleta by machining or filing bracketa in area

shown in Figure 1.

cnvrlow

DO NOT GRIND brackets se permanent damage to the heattreat may occur.

7. inbmud Md n.htoutba,.d. a´•iwnghard~´•Torque bolts 400 to 500 inch-pounds and safety wire (see Figure 1.).

:8. Reinstall edstiqhardware thatattacheslettand rightengine side mountbl.acketatomauntisolators. Torquebolt400 to 500 inch-pounds (aee Figure 1.).

Page 1 o12

SERYICE LETTER NO.351-;´•

LEFT INSTALLATION SHOWN1~ic~

RIG HT INSTALLATION OPPOSI~E

i

TOROUE BOLT 14 PLS)I iTOROUE BOLT 400 TO WO IN-L8S I j I

400 TO 500 IN--LRS j ANO SAFEN

fi:?,

0.03´•.o.l?’l.sa~

MDUNTBRICKETMAX M~X RADIUS

1´•

"-i-~ oREMOVE MATERIAL

FRoM SHADED AREA

VIEW LOOKING FWD

Figure i.

8. Reinatall upper and lower eowling on engines.


ELECTRICAL LOAD: NO CBANGE.

WEIGHT AND BALANCE: NO CHANDE.


PUBLIOlT1(INS AFIRCTaD: The Model BBOC.B. Olustraied Wrt. OLli.p ehi(oge re~uind bl.Qia doiument.ill i*incorporated at the next scheduled revision.

RECORD COMPLII\NCE: Make an appropriate entry in airplane maintenance records as follows: Berviee LetterNo. 331,dated 21 November 1880, entitled "Engine Mount Rraeket ModiBcatian", aeoomplished (date)

Page 2 of 2

Service Letter~II

CulfsrreamAmericanCL)RPOH*TII)N

Comnnndw Diuilion6801 North RocZwsll Avenue.Bsmeny, Otl´•hoM IJM8

SERVICE NO. 338ALSupereedes Service Letter No 388, dated 10 December 1980, in its entirety)

13 March 1981

AFT FUSELAGE TWERMOSTAT INSTALLATION

MODELS AFFECTED: PART I MODEL 690C, SERIAL NOS. 11600 THRU 11650 AND MODEL 695, SERIAL NOS.85000 THRU 95040. PART II MODEL 690C, SERIAL NOS. 11800 THRU 11662 AND MODEL 685, SERIAL NOS.96000 THRU 85058.

NOTE

IF BASIC SERVICE LETTER NO. 538 HAS BEEN COM-PLIED WITH, DISREGARD PART I ONLY OF THIS SER-VICE LETTER.

REASON FOR PUBLICATION: TO IMPROVE INDICATION OF ABNORMAL TEMPERATURES SHOULD THEYOCCUR IN THE AFI~ FUSELAGE AND ASSURE HOSES ARE PROPERLY INSTALLED ON ENVIRONMENTALCONTROLUNIT.

COMPLIANCE: WITHIN NEXT 100-HOURS TIME IN SERVICE.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILE COM-PLYING WITH THIS SERVICE LETPER, CONTACT YOURNEAREST DULWTREAM COMMANDER AUTHORIZEDEIERVICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A 8. P MECHANIC OR EQUIVALENT.

APPROVAL: FAA DOA SW-2 APPROVED,

ESTIMATED MI\N HOURS: PART I THREE (3) HOURS. PART 11- ONE (1) HOUR.

NOTE

GULFSTREAM AMERICAN CORPORATION, COMMAN-DER DIVISION, WILL ALLOW A CREDIT OF THREE (3)HOURS FOR PARTI AND ONE (1) HOUR FOR PART IIUPON BECEIP~T OF A PROPERLY EXECUTED WAR-RANTY CLAIM AND A COMPLIANCE CARD.

PARTS DI\TI\: PARTS REQUIRED TO COMPLY WITH PART I OF THIS SERVICE LETTER MAY RE PROCUREDTHROUGH YOUR NEAREST CULFSTREAM COMMANDER SERVICENTER FOR 866.58. A FULL CREDIT WILLBE ISSUED UPON REC%IPT OF A PROPERLY EXECUTED WARRANTY CLAIM AND A COMPLIANCE CARD.REFERENCE THIS SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERINGSERVICE LETI~ER NO. 338A KIT CONSISTING FOR THE FOLLOWING:

QTY PARTNO. DESCRIPTION

1 ea. 880661-35 Thermostat Aesy1 ea. M792811-15 RinpTerminal4 ft. Wire2 ea. MS26181-1 Butt Splice2 ea. Compliance Card1 as. Service Letter No. 338A instructiona

Pagelof6

SERYICE LETTER NO, 398*

SPECIALTOOLS: TORBUE WRENCH WITH 60 IN-LB CAPABILITIES.

ACCOIPUSHEBENT INSTRUCTIONS:

PARTI

1. Cain access to radio shelf and Environmental Control Unit, located in aft fuselage, through lower aft fuselage access

door.

2. Install M?B2811-15 ring terminal an ground lead of 880651-56 thermostat assembly.

3. Locate drill and install 880651-35 thermostat assembly an aft channel (Pi~ 831066´•19) of the radio shelf (refer to

Figure II.

NOTE

The radio shelf is laeated immediately above the Environmen-

tal Central Unit.

4. Connect the 880657-36 thermostat assembly to airplane electrical system by butt splicing new M8104419-12-9 wire

(W10G22) to existing thermostat using M526181-1 butt splice (refer to Figure 1).

NOTE

The existing thermostat is located an the forward channel (Pi

N 83106621) of the radio shelf.

5 Fill out and mail Compliance Card specifying that Pad I has been accomplished.

6. Proceed to step 2. of Part II.

PARTII

i. Cain access to Environmental Control Unit, located in aR fuselage, through lower aft fuselage access door.

2. Inspect Environmental Control Unit hose, located between heat exchanger and pressure regulator, to assure that

hose extends 0.2S-inch or more beyond both clamps (refel to Figure 3).

3. If hose extends O.PS´•ineh or more beyond both clamps and clamps are straight, proceed as follows:

a. With clamps and hose at ambient temperature, torque clamps to 60 IN-LBS (refer to Figure 3).

b. Proceed to step 6.

4. If hose does not extend O.OS-inch or more beyond clamps, proceed as follows:

a. Loosen clamps on hose and reposition hose on tube ends so that hose covers an equal distance over end of both

tubes (refer to Figure i).

b. Install clamps over hose, immediately behind tube beads, assuring that a minimum of 0.P5-inch of hose extends

beyond clamps.

c. With clamps and hose at ambient temperature. torque clamps to 60 IN-L88.


5. Assure that existing clamps on the other ECU hose, downstream of Pressure Regulator, are correctly installed with

rasped to tube beads. Retoque clamps (refer to Figure 3).

6. Reinstall accessdooron loweraftfuselage.

Provide a minimum of ons (1) hour oluninterrupted operation of the ECU either an the ground at 1008 RPM or

in the air. After.perstion of one (1) hour, allow the unit to cool down to an absolutely cool condition.

NOTE

The joint will retain its tightness as long as the temperatureis kept up and not allowed to cool down.

PagePofS

SER\I~CE LETTER ND. JSDA

880657-16 THERMOSTAT ASSY

-------------+_ -r-

AIRPLANE

83(088-19 RADIO SHELF

AFT CHANNEL (REFIMSZ~70AD3

RIYET 12 PLSI

VIEW LOOKING FWD

I

I.


m8104,9-222s wine

1----W1M22

WloF2z

MS25(81-1 BUTT SPLICE

12 PLSI

880657´•35

EXISTING FORWARD I THERMOSTAT~-

THERMOSTAT (861) ASSY

8’ M7828/1´•(SRINGi

EXISTING FORWAROTHERMOSTAT InE~l

TERMINAL

SERYICE LETTER NO. S38A

1,

TOROUE CLAMP

35 TO 40 IN´•LBS

PRESSURE REGULATORIREFI

B

Y

HEAT EXCHANGER(REFI

WITH CLAMPS AND HOSE PIT

*MBIENTTEMrEAATURE.TOROUE CLAMPS TO (10 IN´•LBI.

AFTER OPERATION OF ONE III

HOUR MINIMUM DURATION

ALLOW CLAMPS AND HOSE ENVIRONMENTAL CONTROL

TO RETURN TO AMBIENT I UNIT IREF)

TEMPERATURE AND RE´•

TOROVE CLAMPS BO IN´•LBS. ´•I TOROVE CLAMPS

16 TO Is INLBS

9HOSE

EXISTING I EXISTING

MS35842´•12 M515842´•12

CLAMP IREFI i CLAMP (REF)

CAUTMN

ASSURE THAT CLAMPSARE

INSTALLED BEHIND TUBE BEADS.

IF CLAMPS ARE NOT PROPERLYa2s´•´• I I I I INSTALLED. LEAKS COULD OCCUR.

MIN EXISTING 184(9 FLEXIBLEITYPI HOSEIREF)

\-cnwloN-MIN. I bO NOT PUT HOSE

CLAMPS ON TOP OF

TUBE BEAD.

ClCur´• 3.

Page lafS

SERVICE LETTER NO. SSBA

8. Remove lower aft fuselage access door to gain access ha Environmental Control Unit.

9. Apply a tightening torque to re-establish a 60 IN-LBB value to clamps originally to~qued in step 3e. or 4c. (refer to

Figure S).

NOTE

Do not loosen the clamps prior to performing step 9. It will

be necessary to comply with the intent of Part II of this Ser-

vice Letter whenever clamps are loosened for any mainte-

nance reason.

10. Rsinstall access door on lower aft fuselage.

11 Fill out and mail Compliance Card specifying that Part 1l has been acmmplished.

ELECTRICC.L LOAD: NO CHANCE


SPARES AFFECTED: NO

PUBIICI\TIONS AFFECTED: The Airplane Maintenance Manual change required by this document will be inrmpa-

rated at the nsrt scheduled revision.

RECORD COMPLI~NCE: Make an appropriate entry in Airplane Maintenance records as follows: lervice Letter No.

338A, dated 13 March 1981, entitled’.Aft Fuselage Thermostat Installation", Part I accomplished (date)

Part Il accomplished (datel

Page SofS

Service Letter I~sml ND~h R~dlll ImU

~lll´•n*.O*l*oMlfmB

Service Latter No. 339

15 January issl

BAGGAGE HEATER ANNUNCIATOR LIGHT LENS REPLACEMENT

MODELS AFFECTED: MODEL 680C, 8ERIAL NOS. 11620, 11621, 11623, 11628 THRU 11631, 11633, 11635,11638, 11639, 11642, 11646, 11661, THRU 11663. MODEL 685, SERIAL NO8. 85000, 95002, THRU 96005, 86009

THRU 96012, 95014 THRU 96018, 96020, 96022, 85023, 96026, 95026, 85026, 85029, 85031, 85033 THRU 85036, 86038,86041 THRU 85044, 85046, AND 96048.

REASONFORPUBLICATION: TO CHANGE BA(KiAOE HEATER ANNUNCIATOR LIGHT LENS FROM BLUE

TO AMBER.

COMPLIANCE: UPON RECEIPT OF THIS SERVICE AND AMBER ANNUNCIATOR LIGiRP LENS.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED COM-PLYING WITH THIS SERVICE LETPER YOUR

NEAREST ROCKWELL COMMANDER AUTHORIZED

SERVICE FACILITY.

BY WHOM WORK WILL BE ACCOMPLISHED: OWNER/OPERATOR OR A Be E MECHANIC OR EQUIVALENT.

APPROVAL: FAA DOA 8W-2 APPROVED

g9pI~TBOM*N HLlmYI: NEOIlOIBLB

PARTS DATA: Parts required to comply with this Service Letter are fumished at no charge, end consist of the follow-

ing:

cm PARTNO. DESCRIPTION

1 Ea. ACR ItSAL Cap1 Ea. Compliance Card

1 Ea. Service Letter No. 939 Instructions

8PEC1ALTOOL8: NONE

ACCOMPLISHMEPIP~INSTRUCTIONS:

1. Remove existing blue BAG HEAT FAILED light lens cap.

NOTE

BAC( HEAT FAILED annunciator light is located on top rightaide of center instrument panel and is removed by unscrewing.

2. Install amber light lens cap, P~ ACR It3AL. furnished with Wis 8eruiee Letter.

3. Fill out and mail CompianEn Card.

ELECT~UCAL LOAD: NO CHANCE

WEIGHTANDBALANCe: NO CHANCE

8PARES AFFECTED: NO

PUBLICATIONSAFFECTED NONE

RECORD COMPLIANCE: Make appropriate entry in airplane maintenance recerde as follows: Service Letter No. 998,dated 15 January, lsB1, entitled "Baggsge Heater Annunciator Light Lens Replacement", aceomplished (date~

Page 1 of 1

_

Ser~ee S-~tter CulFstreamAmericanCI)RPOH*TI(IN

ComMnda Divirion

6WI No~th Ralwsll bnuc.

Bamloy. OLI´•hDM 73008


24 April 1981

INSTALLATION OF PLACARD FOR USE OF ALTERNATE

ENGINE OIL MlL-L-78080

MODELS P.FFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11685 AND MODEL 695, SERIAL NOS. 95000

THRU 95059.

REASON FOR PUBLICATION: TO PROVIDE TEMPERATURE LIMITATIONS WHEN USING MIL-L-7808G OIL.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILE COM-

PLYING WITH THIS SERVICE LETI‘ER. CONTACT YOUR

NEAREST GULFSTREAM COMMANDER AUTHORIZED

SERVICENTER.

COMPLI~NCE: UPON OF THIS SERVICE

BY WHOM WORK WILL BE ACCOMPLISHED: OWNER/OPERATOR

APPROVAL: FAA DOA SW-2 APPROVED.

ESTIMATED MAN-HOURS: NOT APPLICABLE

PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LETI~ER ARE FURNISHED WITH THIS

SERVICE LE1TER AT NO CHARGE.

PART NO. DESCRI~TION

1 ea. 110185-685 Decal


1 ea. Service Letter No. S40 instructions

SPECIALTOOLS: NONE


1. Mount decal on center instrument panel 88 indicated in Figure 1.

2. Assure that Revision No. 6 (Model 690C) or Revision No. 4 (Model 685) has been incorporated in the Pilot’s

Operating Handbook.

3. Fill outand mail ComplianeeCa~d.

ELECTRICAL LOAD: NOCHANGE.

WE1OHT AND BALANCE: NO CHANGE.


PUBLICATIONS PIFFECT6D: The Airplane Maintenance Manual change required by this document will be incorpo-

rated at the nelt scheduled revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.

340, dated 24 April 1981, entitled "lnstallation of Placard for use of Altel?late Engine Oil MIL-L-18080", accomplished

Idate)

Page lofZ

1~1 u~’

i~

x

´•Service Lettev CulfstreamAmericanCORPOR*TION

eommandn DluLim

5001 Norm RoclrMII I\vsnus.Bsm´•ny. OXlahon~s 73005

SERVICE LETTER NO 342

18 June 1981

INSPECTION OF ENGINE MOUNT CASTING BOLTS

MODELS AFFECTED: MODELS 680, 69OA AND 69011, SERIAL NOS, 11001 THRU 11566, MODEL 690C, SERIAL

NOS, llM10 THRU 11630 AND MODEL 696, SERIAL NOS. 95000 THRU 95007, 86008 THI(U 95011.

REASON FOR PUBLICATION: TO ASSURE BOLT THREADS ARE NOT BOTM)MINO OUT DUE TO POSSIBLE

MISSINGWASHERS.

COLbPLIANCE: DURING NEXT 100-HOUR INSPECTION.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILE COM´•

PLYING WITH THIS SERVICE LETPER, CONTACT YOUR


BERVICENTER.

BY WHOM WORK WILL BE ACCOsPUSnED: A L P MECHANIC OR E$UIVALENT.

APPROVAL: FAA DOA SW2 APPROVED.

ESTIMATED MAN HOURS: INSPECT FOR WASHERS THIRTY (30) MINUTES: ADD WASHER FIFTEEN (15)

MINUTES EACH.

PARTS DATA: 1 EACH COMPLIANCE CARD,

NOTE

THE ANBeOC416 WASHERS, IF NEEDED, MAY BE PRQ

CURED LOCALLY.

SPECI*LTOOLS: TORBUE WRENCH.


1. Remove upper and lower cowling shells Ram len and right engines.

2. Inspect leR and right engine mount easting., on both engines, to assure that a washer is installed under each nut

(refer to Figure 1).

S. If a washer is installed under each nut on engine mount easting, reinstall upper and lower eowling shells on engines

and proeeed to step B.

4. If washer is net installed under each nut on engine mount easting, remove nut and install a AN860C416 washer

under nut and to~que 50 to 70 ineh-paunds (refer to Figure 1).

5. Reinstall upper and lower eowling shells on engines.

B. Fill outand mail Compliance Card.



Page 1 oIZ


LEFT INST*LLATION SHOWN

RIGHT INSTALLPITION TYPICAL

ENGINE MOUNTCASTING IREF)

i

ASSURE THAT AWASHER

IANSBOC41B) IB INST*LLEO

UNDER EACH NUT ON LEFT

I P,ND Rl(lnT ENGINE MOUNT

CP~TINOS

~rm

80LT6 SnDULO BE TOAOUED SD TO 70

INCH´•POUNDS

ENGINE MOUNT

CASTIN(I IAEF)

iigura i.

SPIRES AFFECTED: NO.

PUBLICP~TIONS AFFECTED: NONE

RECORD COMPLIINCE: Mate an appropriate entry in airplane maintenance records as bllows: Service I,etter No

:141. daud 19 dunr issl, entitled "lnspeetion of Engine Mount Casting Bolta~’ accomplished tdatedi

Pa:e 2 of i

Sevv~e Lettev CuHstreamAmericanCORWR*710N

Camm´•ndsr Dlrllion

IIW1 Norm Rm~wa(l I\vanua,8´•m´•ny, MII´•homs 73ma

SERVICE LETI‘ER NO. 343

18 October 1981

HIGHER WATTAGE PITOT TUBES

IOOELS ~FFECTED: MODEL 680C, SERIAL NOS. 11600 THRU 11685 AND 11109 AND MODEL 695, SERIAL

NOS. 95000 THRU 95055, 95051 THRU 95063.

REASON FOR PUBLICATION: FIELD SERVICE REPORTS INDICATE POSSIBLE FREEZE UP OF EXISTING

PITOT TUBES UNDER EXTREME ADVERSE WEATHER CONDITIONS CAUSING LOSS OF AIRSPEED

INDICATION.

COMPLIANCE: WITHIN NEXT 200 HOURS TIME IN SERVICE.

NOTE

IF ANY PROBLEMS AHE ENCOUNTERED WHILE

COMPLYING WITH THIS SI:RVICE LE~ER. CONTACT

YOUR NEAREST GULFSTREAM COMMANDER

AUTHORIZED SERVICENTER

BY WHOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR EQUIVAI.ENT


ESTIMATED MI\N HOURS: PART I (KIT NO. 1)- NINETEEN (19) HOURS

PART I (KIT NO. 2)- FOURTEEN I14)HOUKS.

PART II (KIT NO. 3)- THREE (3) HOURS

PART III (KIT NO 4)- TWO (2) HOURS

PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SE:RVI(:E LETTER MAY 8E PROCURED THROUGH

YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KIT NO 1 8406.93: KIT

NO. 2 -1588.10; KIT NO. 3 -8351.91; KIT NO. 4 8346.49. REFERENCE THIS SERVICE LETTER, AIRCRAFTMODEL AND FACTORY SERIAL NUMBER WHEN ORDERIFIO SERVICE LETTER NO. 343 KIT CONSISTING OF

THE FOLLOWING:

Kit No. 1 (Part I) Model 690C, Se~inlNos 11600 ttlru i ifif,o

Model 695. Serial Nos. 96000 thlu 9liil´•i0

Kit No. 2 (Part II Model 690C, SerialNoa 116:ii thnl I I G~:

Model 695. Serial No%. Y;)li~ll Illrii BBi;r:. !)5057 thru 95059

Kit No. 3 (Part II) Model 69t. Seriill 1Voa. BBi)ii(l thni ~Ti´•li´•:l

Mode1690C, Ba;ialNo ii_’iiY

Kit No. 4 (Ps~t III) Model 690C, Seriili Nou LICC: I;´•ld i I ~hi

Pa%e 1 of 14

SERVICE LET~ER NO. 545

KI1 ,il Kh

No.l No2 No.a No.4

aTu BTY BTY BTY PARTNO. DEGCRIPTION

1 ea 1 ea 110186-885 Decal

lea lee 110185~881 Decal

lea 833035-1 Relay1 sa 1 ea 1 ea. 1 se. PW11WRWLEFT PitotTube

1 ea 1 as 1 ea. 1 se. PH11W-RW-RIDHT PitotTube

lea lee 1 ea. 20TC4AK-a0 Circuit Breaker SWitCh

4aa 4Ba 820566 Buick Disconnect

ass 2 a. 1211-6-10-12501-61 Circuit Breaker

4ea 4 ea AN880C10L Washer

2 ea MSa1042L04 Nut

4ea 4sa M8210MN04 Nut

4ea 4ea MS21083C3 Nut

?sa 1.a MS26056-112 Terminal Lug2 ea 2 ea MS25056-164 Terminal Lug2 as 2 ea M8ZM136151 Terminal Lug3 as 2 ea MS25181-2 Butt Splice1 as 1 ea MS2121222 Terminal Board

4 se 2 ea MS96201-215 Screw

1 ea 1 ea MS9548811 Cmmmet

1 ea LRM16W-2 Connector Pin

248 248 M608612-129 Wire

lea M1828/1-16 Terminal Lug2ea 2 ea M7928/142 Terminal Lug?ea ?ea M1B2811-61 Terminal Lug26 it 26R 18104419-14-9 Wire

26 8 20R M8104U8-r6-9 Wire

1R M8104418-20-8 Wire

1R M8101U8-22-9 Wire

1 ea lee TA1SM04-2 Cover

1 as lee Iea 1 sa Compliance Card

1 se 1 ea 1 ea 1 ea Service Letter No. 543 Instrue6ans

SPECIPIL TOOLS: NONE.

*CCOMPLISHMENT INSTRUCTIONS;

PART I MODEL B80C, 8ERIAL NOS. 11600 THRU 11883 AND MODEL 696, SERIAL NOY. 85000 THRU 96055, 95051

THRU 85059.

CAUT1ON

oround Operation of the pitotiststic system for an extended

period of time (longer than 15-seeonds) may result in damageto the heating elements.

i. Turn eleetrical system and pitot/static system an and note magnetic compass heading

NOTE

A compass heading must be taken prior to mndi:: -iion Hnd

after modification of the pitot system to check ii; con,paau

deviation.

2. Cain aecesa to airplane batteries through baggage compartment door.

1 Remove baggagt cumpartmcnt liner to e~poio battsnas.

4. DisEonneettenninals fiom both batteries.

8. Remove copilot Best and bar.

P~e 2 of 14

i O 00 72176~10´•12C0781

i OQ8i _,,_

~m

O

(2 PLACE8L

10, q

I~ei o

COPILOT LOWER

CIRCUIT BREAKER PANEL

IREF)

(REF)

21

111111111111111111111111~

TERMINAL BOARD IN MIS AREA USINGM896208´•215 SCREWS AND MS21D14NM NUTS

7r1EW lXX)KING AFT

Figure i.

Pass 9 o( 14

BERVICE LETTER NO. 945

6. Remove right interior side panels to expose electrical wiring and terminal board that is located below emergencyexitwindow.

7. Remove right interior side panel forward of emergency exit window.

8. Remove panel from right eye brow window.

8. Remove cirruitbreakerpanel as follows:

a. Pull copilot control wheel to full aft position and secure,

b. Reach under and behind circuit breaker panel and disconnect electrical connector plugs and wiring

DAUTION

Mark plugs to assure they are reconnected to their respectivemating connector

c. Remove attaching screws from front of panel and carefully remove circuit breaker panel.

d Remove back plate cover from circuit breaker panel.

10. Drill two (2) 0.50 inch diameter holes in DC circuit breaker false panel st positions 30 and 61 to match existingholes in metal panel and install 7277-6-10-12-501-61 circuit breaker (2 places), 110185-895 decal and 110186-697decal (refer to Figure 11´•

CbUTION

Care should be taken so as not to damage false panel when

drilling holes.

WOTE

if positions 30 and 61 are in use, location is optional on rightside of circuit breaker panel.

11. Locate end drill a 0.621 inch diameter hole in circuit breaker back plate cover (refer to Figure i).

nOTE

This hole is for routing new wires through back plate cover.

12. Deburrhole andinstall MS36489-1l grommet.

L3. Locate, drill and install M527212-2-2 terminal board on an side of circuit breaker back plate cover using MS35206-215 screw (2 places) and MS21044N04 nut (2 places). Location should be near hole that was dnlled per step 11Hale size to be 0.113 inch to 0.116 inch diameter (refer to Figure 1)

14 Loweroverhead switch panel as follow.:

CAUTlOhl

When removing slectroluminesoent panels, be careful not to

dan,age or break electrical wiring and connectors. Do notallow panel to hang by the wiring. Panel has to be supportedor damage may occur.

a. Loosen alien screws on all knobs on face of the slactrolumines~ent panels and remove knobs.

b Remove attaching screws securing electrolumineseent panels.

c. Carefully remove panels to expose wiring.

d. Drasp wires and gently pull down until quid disconnect and airplane wiring are exposed, Disconnectelsetrolumineseenl panel

Page 4 of 14

L~RVICE LETTER NO. 549

BEFORE CHANGE

r

i i*ILI5L)*llOL

II II 1(

IUII CIUI LUI

I

,r T ´•I

,11101 1 ikl´• I.*IOI

~*ol´•

6 6

~ir

i..

a

MODEL 890C. YN (1BW THRU 11858 MODEL B9OC. BIN 11551 THRU 11sas

MODEL 885. SIN 85088 THRU 85858 MODEL 1195. SM 85041 THRU 85068

Z.

Page I of 14

BERVICE LETTER NO´• 549

e. Remove attaching acrsxa horn top of metal plate of overhead switch penal.

NOTE

Entire panel will hang in a vertical position and is suapendedby the hinges. This allows for easy access to circuit breakerswitches and electrical wiring.

15. Disconnect and coil and stow wire Nd. 1H26A~6 and wire No. 2H26A18 fmm overhead switch panel (refer to Figure2).

NOTE

Wire No. 1H26A16 is muted hem L PITOTISTATIC circuit

breaker switch (CB8S1) to shunt (811-5) and wire No.

2H25A16 is muted Rom R PITOT circuit breaker switch (CBS

52) to shunt (8116).

16. Remove existing L PITOTISTATIC (10 amp) and R P~OT (15 amp) circuit breaker switches. Discard L PITOTI

STATIC (10 amp) switch and retain R I)ITOT (16 amp) switch for reinstallation at step i?.

17. install existing 16 amp circuit breaker switch, removed in step 16, on overhead switch panel at position labeled L

PITOT1STATIC using existing hardware.

18. install 20TC4AK-20 circuit breaker switch on overhead switch panel at position labeled R ATOT using existinghardwent.

19. Disconnect wire No. 1H25B16 from shunt (SH-S) and disconnect wire No. 2H25B16 from shunt(SH-6). Coil and

stow both wires (refer to Figure 2).

20. Disconnect wire No. 8281\18 from TB 19 and wire No. H2BA18 fmm TB 10 of terminal board that is located below

emergency exitwindow (rafer a Figure 2).

21. Remove terminal lugs from wire No. H28A16 and wire No. H26A16 and install M815181-2 Butt Splices to both

wins (rsfer to Figure 8).

22. Disconnect pitot tube connector from both pitotheads and coil and stow (mfer to Figure 2)

23 Disconnect tube assemblies from left and right pitot tube fittings.

24. Remove four (4) screws attaching pitot tube to mount~ng bracket and remove pitot tubes.

25. Apply a bead of EC 1239 "82" sealant or an equivalent M1L-S-1602C sealant inside pitot tube mounting bracketsand also on new pitot tubes (refer to Figure 4). 6se sealing procedures, Chapter 20, in Airplane MaintenanceManual.

26 Install pitot tube and PW1100-RW-RIGHT pitot tube.

2?. Ensure that pitot tubes are properly sealed to prevent any pressurieation leaks.

18. Form tube an pitot tubes, as necessary, and connect to existing tube assemblies.

29 Install new M608612´•12-8 wire (12 gauge), M8104419-14-9 wire (1( gauge) and M8104418-16-9 wire (16 gauge) and

connect to airplane electrical system. Install 320566 quick disconnects on wires just outside of circuit breaker

panel back plate cover. Silver Solder wires to pitat tube connector using "Alloy C20" solder (refer to Figure 3).

NOTE

Connect wires M terminal board, installed in step 13, usingMS21083C3 nutr nnd AN960C10L washers. Route new

wires along existing wire bundles if possible.

30. Install TA1SM04-2 cover on terminal board installed at step 13.

Page 5 of 14

IERYICE LETTER NO. 545

ATTER CHANGE

IM926058164 LPITOTISTP~TIC RPITOT

TERMINAL LU(I HEATCONTROL HEAT CONTROL

M525038´•157

iCpll.,,,12 PLS1

(2PLS1

mls*ll

cul*1, au~

MIOIBII´•11-BWIREU6

t

M527212´•22 T´•BO~AD

MS152~8´•216 SCREWi~uclbr

sapn*n.

n. ran,´•~HEnrEn~4´•: I,

,,,,,,EnrERLPITOT

6WIRE 8

POWER WIRE PIPPROX

PITOT)

11 1(

;_g~___j_J oc cs PANELCIRCUITBREAI(ER

(2~LS) M81D14/8´•1B8WIRE

520580I(IUICK DISCONNECTC yll MSZ518(´•2 BUTT SPLICE

14 PLSI n

mnodale~lsswlnl

ms261n´•2 suTT 9PLICE I Hits

~xl

MB(OM/9´•22´•8WIRE

lUI

*1~(´•

4.8TATIC

PORT I

Ivrn C CIRloHn

*LLlq

-I´•_

OWO-10

,OT.I: "i ’I C(4 ´•V´•IIOLD’RW1"E’ IO ´•ImT

mNNerrOAI UIIIWO ´•´•~LLOY No.lo-.

HIIII*OTIHIIR*TYREOI-~LLOI NO. 10* (IOLDIR is ERE"P.

UIE LUO WITH (l(il\. WIRE

Uli. HJ2~OPI´•(IITLRMIN*L LV(Io* IHUNT I~Wbl

Y9E M310YI´•l(n TIRMIN*L LUO ON (HUNT l)n´•81 rO(iii iiMiC SIN I.´•.IU I(IRU 11RSOYIIE M1828116( TERMIN~L LYD WITH 110~´• WIRE

WODII i95 S/N BEOi;’; THAU 3M14(1Y~E LUD WIIH ((IGI\. WIRE

Ylil MIB?II1´•ll TER~INI\L LUB WITH 22 01\. WIRE

Page? of 14

BE~VICE LETTER NO. 543

AFTER CHANGE

~eTunaol iI~nroTipr*nE R PltOTM9280SB´•184TERMINAL LUO HEAT CONTROL HEAT CONTROL

MS2505B151TERMINAL LUO

rZPL8I

I*~L((

C *7111 51--~11 IYI

MS088/2´•12-gWIREWb

t

MS21212-2-2 T´•BOAAOM5)6206´•21JSCREW

M8104419´•(bg s~cror NUTEBI~NII

LPITOTII--~ rlll

R PITOT

HEATER ´•´•´•10 REATER

~(I) I rid

"8" ,I, ,ND WIRE&

WWER WIRE ~PPROX

12~’ ILILR PITOT)11

~zn´•6´•lol2´•smsl,CIRCUIT BREAKER

12 PLS) T

320588 (IUICI( DISCONNECT

I4PLS)

M810P~/8´•1SBWIRE

MSZ61812 8UTT

12 PLSI ,,I,, r*~u*,ol,,

\1 ~x,

-9,

ponr

IHlaHn

STATIC

ur~nni

ILEFTI

NOTL~: ´•661LVlR IIOLOIR WIRES TD ´•llOT

0686601056 USINI) IILLOY NO. Soil.

MIITINO TEMPERATURE OI´•´•*LLOY NO´• II´• (IOLDIR iS 56101.

UIE TIIMIN~L LYLI WIM 12 (I*. WIRT

UsE M125ml´•161 rrlMIN*L LUB ON SHUNT 16Hbl EFFECTIY1TYUlil MIIRP~´•1I TERMINIL LYO ON SHUNT (6HBI MODEL 8808 8/N 11851 THRU 11883USE MIB~/ldl TERMINI\L LYO WITH 110A´• WIRI MODEL BgS S/N 05041 THRU 85055USE Mle~llll2 TIRMINII LYO WITH (I (II\. WIRI

USE MIBIII1´•ll TIRMINI\L LU. WITH 11DA. WIRE AND 95051 THRU 85058

i:ipur~ i. IShn,, 2~1 2i

PPge B of 14

8ERYICE LETTER NO. 545

81. Reinstall circuitbreakerpanel asfollows:

a. Install back plate Fever and secure with attaching screws.

b. While supporting circuit breaker panel, close to its mounting position, connect electrical connector plugs and

mnng.

c. Position circuit breaker panel for installation and secure with attaching screws.

d. Release central wheel and allow it to move forward.

32 Reinstall overhead switch panel as follows:

CAUTION

When installing the overhead switch panel, ensure that all

wires and busses are properly secured and not squeezedtowards airframe. This will prevent possible short circuits,

a. Swing overhead switch panel up and secure with existing screws.

CAUTION

To prevent bending of panel, do not over-torque screws.

b. Connect electroluminescent panel wiring to airplane wiring and position panel for installation Stow any

excess wiring to ensure that it will not be pinched or crimped when panel is secured,

c. Secure electroluminescent panels with existing screws.

d. Reinstall all existing knobs and secure with existing alien screws.

33. On Model 690C, serial numbers 11661 thru 11665 and Model 695, serial numbers 96041 thru 95055, 95057 thru

95059, proceed to step 35.

34 On Model 680C, serial numbers 11600 thru 11650 and Model 695, serial numbers 95000 thru 95040, proceed as

follows:

a. Remove right baggage compartment liner to gain access to terminal board and P48 connector located just

forward of fuselage station 239.15 (refer to Figure 5).

b. Locate, drill and install 833038-1 relay on existing channel using MS35206-215 screw (2 places) and

M821040L04 nut (2 places) (refer to Figure 5).

c. Disconnect wire No. H26A16 from pin AA of P48 connector (refer to Figure 2).

d. Install new wire No. H26BB16 (M8104418-18-9) on pin AA of P48 connector using LPM16W-2 connector pin

and connect to AS of 855058-1 relay (K?a) (refer to Figure 5).

e. install new wire (MB10(4is´•18-9) an A2 of 853038-1 relay (K72) and hutt splice to existing wire No H26A16

using MS251812 butt splice (refer to Figure S).

Install new wire No. H26AA20 (M8104418-20-9) on 833038-3 relay (K721 from A2 to X1 (reLI to Figure 3).

g. Install new wire No. H??AZ2 (M81044~-22-9) ham X2 of 838038-1 relay (K72) to TA4 of terminal board (refer

to Figure 3).

h. Proceed to step 35.

35. Reconnect terminals tobatteries.

36. Functionally test pitot heat system.

Page 8 of 14


gL

FUSELAGE SKIN

(REFI

MOUNTING BRACKET

e, IREFI

O

SEAL WITH ECIPs’~82"SEALANT OR I\N EOUIVALENT

MIL-976(12C8EALANTO

ATTACHINGFURNISHEO WtTH

P1TOT TUBES

PHIIOORW-LE~T

PITOT TUBE ((1Br)

Fipura 1

Page 10 of 1(

SERYICE LETTER NO, 549

31. Pelfonn pibtststic system check as outlined in Chapter 84 of the Airplane Maintenance Manual to aesure there

are no leaks.

CAUTION

Omund operation of the pitatiatatie system for an extended

period of time (longet then 15-seconds) may result in damageto the heating elements.

SE. Turn electrical system and pitotistatie system on and note compass heeding. Note any deviation from originalheading, taken in step1., and note deviation on devialon card. Deviation shall not exceed 10 degrees. If

deviation exceeds 10 degrees, reswing magnetic compass as necessary.

58. Reinstall liner in baggage compartment.

10. Reinstall interior side panels andeyebrowpane.

41. Reinstall eopilotseat and bar.

42. Insert Figure 3. wiring diagrams in Airplane Maintenance Manual for troubleshooting purposes.

43 Fill out andmail Compliance Card.

44. Roceed to ELECTRICAL LOAD.

PIRT II Modal 880C, Serial No. H7W IND MODEL 885, SERUL NOS. 950%0 THRV 85083.

CAUTION

Dround operation of We pitotistatic system for an extended

period of time (longer than 1S´•aeconds) may result in damageto We heating elements.

1 Turn electrical system and pitotiststie system on and note magnetic compass heading

MOTE

A compass heading must be taken prior to molfication and

aRer modification of the pitot system to cheek for compassdeviation.

2. Loweroverhesdaviteh panel asfollows:

a. Ensure that electrical power is removed.

CAUTION

When removing slectmluminescent panels, be careful not to

damage or break electrical wiring or connectors. Do not

allow panel to hang by the wiring. Panel has to be supportedor damage may occur

b. laoaen alien screws on all knobs on face of the eletmluminescent panels and remove knoba

c. Remove attaching screws securing electroluminescent panels.

d. Carefully remove panels to expose winng

e. Orasp wires and gently pull down until quick disconnect and airplane wiring are exposed. Disconnect

electrolumineasent panel.

f Remove attaching screws from top of metal plate of overhead switch panel

page 110114


ALL 833038´•1 RELP~YEXISTING CHANNEL

EXISTING RELAYS

MSZIMILY

EXISTING CHI\NNEL

STArlNG

CONNECTOR IREFI

FW

FICnS.

NOTE

Entire panel will hang in a vertical position and is suspendedby the hinges. This allows for easy access to circuit breaker

switches and electrical wiring.

3. Remove existing L PITOTISTATIC (10 amp) and R PITOT (15 amp) circuit breaker switches Discard L PITOTI

STATIC (10 amp) switch and retain R PITOT(1S amp) switch for reinstallation at step(

4. Install existing 15 amp circuit breaker switch, removed in step a. on overhead switcii panel at petition labeled L

PITOTISTATIC using existing hardware.

5. Install 20TC4AK-10 circuit breaker switch on overhead switch panel at pouitioll inl;l´•iri( H 1’11‘01‘ using existinghardware.

6. Reinstall overhead switch panel as follows:

CAUTION

When installing the overhead switch panel. ensure that all

wires and busses are properly secured and not queeppdtowards airasme This will prevent possibir xholt ´•ireeir´•

a Swing overhead switch panel up and secure with existing screws

b. Connect eleetroluminaseent panel wiring to airplane wiring and positio,i pilnr! tbl in;i;ll;itli,n Stow any excess

wiring to ensure that it will not be pinched or crimped when panel is iruiireii

Page 12 of 14


c. 8eoure electmlumineaeent panels with exiatingaorews.

d. Reinstall all existing knobs and secure with existing alien screws.

Removeandraplace Isttendrightpit~ttube sssembliesasfollows:

a. Disconnect tube assemblies from left and right pitot tube Bttinga.

b. Remove four (4) screws attaching pitot tube to mounting bracket and remove pitot tube.

c. Apply a bead olEC 1238 "B2" sealant or an equivalent MIL-S-1602C sealant inside pitot tube mounting bracket

and also on new pitot tubes (refer to Figure 4). see sealing p100SdUIeel Chapter 20, in Airplane Maintenance

Manual.

d. Install PH1100-RW-LEFT pitot tube and PH1100RW-RIGHT pitot tube.

e. Ensure that pitot tub., are sealed properly to prevent any pressurization leaks.

r Form tube on pitot tubes, as necessary, and connect to existing tube assemblies.

8. Functionally test pitot heat system.

g. Perform pitatistatic system check as outlined in Chapter 34 ofthe Airplane Maintenance Manual to assure there are

no leaks.

CAUTION

Ground optation of the pitotistatic system for an extended

period of time (longer than fS-semnds) may result in damageto the heating elements.

10. Turn electrical system and pito~static system on and note compass heading. Note any deviation From original

heading, taken in step i., and note deviation on deviation card. Deviation shall not exceed 10 degrees. If

deviation exceeds 10 degrees, reswing magnetic compass as necessary.

11. Fill out and mail Compliance Card

12. Proceed to ELECTRICAL LOAD.

PART III- MODEL BgOC, SERIAL NOS. 11884 AND 11BBS.

CAUTION

Ground operation of the pitotistatic system for an extended

period of time (langer than 1S-sscondsl may result in damageto the heating elements.

1. Turn electrical system and pitotstatic system on and note magnetic compass heading.

NOTE

A eampsss heading must he taken prior to modiReation and

after modification of the yitot system to check for compass

de~iation.

2. Ensure that electrical pwer is removed

3. Remove and replace left and right pitot tube sssembljas as follows:

a. Diseonnect tube aane~nbliel from left and righl pitot tube Littings

b. Remove four (41 screws attaching pltot tube to mounting brael~et;l:ld remove pitot tube.

Page liul!a


c. Apply a bead of EC 1288 "B2" sealant or an equivalent MIL-S?SOZC sealant inside pitot tube mounting bracket

and also on new pitot tubes (refer to Figure 4). 8ee sealing prooedures, Chapter 20, in Airplane Maintenance

Manual,

d. Install PH1100-RW´•LEFT pitat tube and PH1100-RW-RIoHT pitot tube

e. Ensure that pitot tubes are sealed properly to prevent any pressurization leaks.

e Form tube on pitot tubes, as necessary, and connect to e~iating tube assemblies.

4. Functionally testpitot heat system.

5. Perform pitotistatic system cheek as 84 of the Airplane Maintenance Manual to assure th.re are

no leaks.

CAUTION

Ground operation of the pitotistatic system for an entended

period of time (longer than Ii-seconds) may result in damageto the heating elemente.

6. Turn eleetrical system and pitotistatic system on and note compass heading. Note any deviation from original

heading, taken in step 1., and note deviation on deviation card Deviation shall not exceed 10 degrees. If deviation

exceeds 10 degrees, reswing magnetic compass as necessary.

7 Fill outandmail ComplianceCard.

ELECTRICAL LOAD: PART I -18.4 AMPS

PART II -18.4 AMPS

PART 1I1 -18.4 AMPS

WEIGHT PINO BALANCE: NO CHANCE.

SPARES AFFECTED: NO,

PUBLICATIONS AFFECTED: The Pilot’s Operating Handbook, Ai~lane Maintenance Manual and Illustrated Parts

Catalog changes required by this document will be inmlpaeted at the next scheduled revision

RECORD CO~PLI*NCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.

343. dated 18 October 1051, entitled "Higher Wattage Pitot Tubes", Part I accomplished (date) Part II

accomplished (date) Pan III accomplished (date)

Page 14 of 14

Service Letter Gulfstream AmericanCORPORA~ION

Conmau(n Divbion1001 Norm Rak~wll I\uanu´•.Bathany. OLI´•hoM 13(108


10 July 1981

MAIN LANDING GEAR TORCIUE LINK SHAFT REPLACEMENT

YODELS AFFECTED: MODELS 680FL(P), 680’1, 630V AND 680W, SERIAL NOS. 1261 THRU 1854, MODEL 681, 6E´•

RIAL NOS, 6001 THRU 8012, MODEL 685, SERIAL NOS. 12000 THRU 12066, MODEL BgO, SERIAL NOS. 11001

THRU 11018. MODEL 8gOA, SERIAL NOS. 11100 THRU 11344, MODEL 680B, SERIAL NOS, 11560 THIRI 11666,MODEL 680C. SERIAL NOS, 11800 THRU 11816 AND MODEL 806, 8ERIAL NOS. 95000 THRU 850?5.

REASON FOR PUBLICATION: SHAFT FAIL~EI COULD RESULT M MAIN LANDING GEAR MALFUNCTION.

COMPLIANCE: NEXT 100-HOURS TIME W 8A~RVICE.

MOTE


PLYING WPTH TH1S SERVICE LETTER, CONTACT YOURNEAREST OULFSTREAM COMMANDER AUTHORIZED8ERVICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR EQUIVALENT.

APPROVAL: FAA DOA 8W-2 APPROVED.

ESTIMATED MAN HOURS: FOUR (4) HOURS.

PARTS DATA: REPLACEMENT ED12406-1 TORQUE LINK SHAFT, ED1S973-1 BUSHINGS, ES12106-1 TORQUELINK ASSEMBLY OR ED12452 THRUST RING MAY BE PROCURED THROUGH YOUR NEAREST GULESTREAM

COMMANDER AUTHORIZED SERVICENTER. ONE (1) EACH COMPLIANCE CARD 18 FURNISHED WITH THIS

SERVICE LETI~ER.

MOTE

MODEL B80FL(P) USES FF612-2 BUSHINGS INSTEAD OF

ED13313-1 BUSHINGS AND ES1O405 TORQUE LINK AS-SEMBLY INSTEAD OF ES12405-1 TORQUE LINK A88EM-BLY.



1. Jssk airplane as outlined in the applicable Airplane Maintenance Manual.

2. Reduce hydraulic pressure to zero by applying brakes or by actuating wing naps.

3. Remove bungee mads from left and right main landing gear strut lower pulleys.

4. Push up on drag brace and allow gear to go overcenter a facilitate removal of torque link shaft. Assure that gearis properly supported.

5. Remove safety wire from torque link shaft attaching bolt (refer to Figure 2).

Page 1 of 4

BERVICE LET~ER NO. S44

ED(1~2 THRUST RING

!REF1

Eol2´•oel ronoua

1LINK SH~FT IREF)

TOR(IUE LIWK

RuSHlNa (nEFI

LINK ~69Y

(REF)

t

LINK

gsusHINa IREF)

STRUTASSY IREF)

RLnt.

Page a of 4


FWD

TORQUE LINK SHI\FT IREF)AN4HIA

TOR(1UE LINK SHI\FT

RET*1NINO BOLT

TORQUE 50 TO 70 IN´•LBS.

BLEEDERPLUOIREFI

VIEW LOOKING DOWN ON MAM LANDING GEAR 8TRUT ASSY CTYP)

TOBOUE LINK SHAFT RETPIININO BOLT

MUGT BE (II\FETY WIRED *S SHOWN

TO PREVENT WIRE FROM 8LIPPIN(I

OVER TOP of BOLT HEnD nhlo OVER

TOP OF BLEEDER PLUO AND I\LLOWINB

BOLT I\NDIOR BLEEDER PLUO TO LOOSEN

FIWa 2.

Page 3 of 4

SERVICE LETTER NO, 5(4

6 Remove bolt that secures torque link shan (refer to Figure 2).

Remove torque link shaft and check for the following (mfer to Figure II:

a. Length of torque link shalt should be 4.18 inches. If shaft is not 4.18 inches in length, replace with new

ED12406-1 torque link shaft.

b if existing torque link shaft is 4.18 inches in length, inspect for straightness of shaft and wear at thrust ring

contact points Replace with new ED12(06-1 totque link shaft as necessary.

e. Cheek holes in thrust ring, through which torque link shah paste., for elongation. Replace with new ED12452

thrust ring as necessary.

d. Check bushings in to~ue link assembly for wear and possible cracks. Replace with new ED1S313-1 bushings

as necessary.

NOTE

Model 680FL(P) uses FF-612-2 Bushings.

e. Cheek existing torque link assembly for cracks end excessive wear. Replace with new ES12406-1 torque link

assembly as necessary.NOTE

Model 680FL(P) uses ES11IOS torque link assembly

e Assure that existing bolt (P~ AN4H4A) that secures torque link shaft is proper length as shown below.

1 17/32´•1 NOMIN~L

nN~Hdn BOLT

8. Install elisung or new ED12406-1 torque link shah through strut assembly and torque link assembly. Assure that

flat spot in center of shalt is aligned perpendicular to bolt hole (refer to Figure 2).

9. Ileinatall existing or new ANIH~A bolt to secure torque link shaft, torque 50 to ?0 inch-pounds and safety ulre

to bleeder plug (refer to Figure 2)

10. Remove support from main Lending gear and allow gear to go down and locked

Ii. Reinstall bungeecordson lowerpulleys.

12. Functionally check landing gear system as outlined in the applicable Airplane Maintenance Manual

13. Remove simlanejaeks.

14. Fillautandmail Compliance Card.


WEKIHT IND BALANCE: NO CHANDE.

SPIRES AFFECTED: YES

PUBUCPITIONS *FFECTED: The Illustrated Part. Catalog and Airplane Maintsnance Manual changes required by

this document will be incorporated at the next scheduled revision.


344, dated 10 July 1081, entitled "Main Landing Gear Torque Link Shaft Replaeement",aeEompliahed (date)

ppgedofd

SE RVICE PUB LI CATIONSGulfstreamAmerican

revision notice (-OHI´•OR*TII)N

Conlmanda Div*ion

~001 North Rakwsll /wsnus.

Bathsnyl Otlshoma 13008

SERVICE NO. 345

REVISION NO. 1

21 May 1882

VERTICAL STABILIZER ATTACH BOLT INSPECTION


Page 3 of g Figure 1. (9heet 1 of 2)

ADD: NOTE allowing use of nush head aorews to attach door.

~CCOMPLISHMENT INSTRUCTIONS- PART I

Page 5 of 9

CHANGE to reed: 8.e. If hale is damaged, it is acceptable to usa AN61 bolt (0.315"10.319" diameter hole) Ionly if an edge distance of 0.S6-inch or more can be maintained.

8.e. If it is determined, prior to reaming enisting hole, that an edge distance of 0.66-inch

or more can be maintained, ream damaged hole to 0.376"10.319" diameter and install

AN6-7 bolt, ANOBODBIG washer (under nut only) and M517825´•6 nut. Torque bolt 300 1to 330 inch-paunde by tightening nut to low side of torque range end, if necessary,

continue to tighten until a slot aligns with hole in bolt. Install M524665-134 cotter

pin (refer to Figure 3).

W07E

An additional AN960DB16 washer may be installed (under

nut only), if necessary to assure proper alignment of hole in

bolt with slete in nut.

P.CCOMPLISHMEKI INSTRUCTIONS- PART II

Page 8 of 9

CHANGE to read: 10.e if holes are damaged, it is acceptable to use AN6-? bolt (0.91S"i0.318.’ diameter holel I

only if an edge dists~nee of 0.56-ineh or more can be maintained.

lo.e. If it is determined, prior to reaming elisting hales, that an edge distance of 0.56-inch

or more can be maintained. ream damaged hale or holes to 0.575"10.379" diameter and

install ANB-? bolt, M880D616 washer (under nut only) and M811825-6 nut Torque Ibolt 900 to 330 inch-pounds by tightening nut to low aids of torque range and, if

necessary, cantinue to tighten until a slot aligns with hole in bolt. Install MS14865-

134 cotter pin (refer to Figure 3).

Page 1 of 2

Service Letter GulfsrreamAmericanL:ORPOR*TI(IN

Commndn Mvlon

6001 Norm Roc~well Avanus.Bamany, O*(´•hsM 73(*18

SERVICE LE1TER NO. 945

18 January 1882

VERTICAL STABILIZER ATTACH BOLTS INSPECTION

MODELS AFFECTED: PART I´• MODELS 690, 690A AND B90B, SERIAL NOS, 11001 THRU 11566. MODEL

690C, SERIAL NOS. 11800 THRU 11629 AND MODEL 695, SERIAL NOS. 95000

THRU 95010.

PART II MODEL 690C, SERIAL NOS llBSO THRU 11881 AND 11709 AND MODEL 695.

SERIAL NOS. 95011 THRU 95019.

REASON FOR PUBLICATION: A. TO CHECK FOR POSSIBLE IMPROPER WASHER INSTALLATION

RESULTING IN ERRONEOUS TOR9UE READINGS. IMPROPER

INSTALLATIONS CAN CAUSE CRACKS IN HORIZONTAL SPAR

B. REMOVAL OF TWELVE (12) MONTH OR 600 HOURS REPETITIVE

INSPECTION.


NOTE

INSTALLATION OF CASTELLATED NUTS PER THIS

SERVICE LETI~ER‘rYILL REMOVE THE RE$UIREMENTFOR TWELVE (121 MONTH OR 500 HOURS INSPECTION

OF THE VERTICA1, STABILIZER ATTACH BOLTS AT

FUSELAGE STATION 408.66 AS STATED IN THE

AIRPLANE MAINTENANCE MANUAL.


COMPLYING WITH THIS SERVICE LETTER, CONTACT


AUTHORIZED SERVICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A 8r P MECHANIC OR E9UIVALENT.


ESTIMP~TEDMANHOURS: PART I- FOURTEEN(ld)HOURS.PART II- FOURTEEN (14) HOURS.

PARTS DATA: PARTS REGLUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGH

YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: PART I 880.09: PART II

816.51. REFERENCE THIS SERVICE LE1TER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN

ORDERING SERVICE LETTER NO. 361 KIT CONSISTING OF THE FOLLOWING:

Page 1 ol 8


KF NO. 1- PART I

KB NO. 2 PART II

Kit No. 1 Kit No. 2

BTY qTY PART NO, DESCRIPTION

1 se, t as. 311011-9 Door

1 es. 1 ea. 511017-6 Doubler

1 ea. 1 ea. 511017-1 Angle1 ee. 1 as. 311011-9 Angle

1 ea. 1 ea. 311017-11 Doubler

1 ea. 1 as. 311011-19 Doubler

4 ea. AN5-6 Bolt

4ea. ANBBOD61B Washer

4es. MS11825-6 Nut

10ea. 10 as. MS2104?LS Nutplate4ea. M92(BBS´•1S2 Cotter Pin

10 ea. 10 ea. MS21098´•1-10 Screw

i ea. 1 ea. Compliance Card

1 ea. 1 ea, blvice Letter No. 546 Instructions

SPECULTOOLS: TORBUE WRENCH WITH 930 INCH-POUND CAPABILITY.

ACCOLbPLISHMENT INSTRUCT)ONS:

WOTI

Bolts to be inspected are located st fuselage station 408.66

and attach the vertical stabilizer to We horizontal stabilizer

front spar. Instructions are provided for installing an access

door, just aft of fuselage skin lap aft of station 396.82, to

provide easy access to empnnage attach bolts.

PARTI

1. Make a rough cutout (smaller then hole in 311011-6 doubler) in left side of aft fuselage, just ah of fuselage shin lapaft of station 386.82, for installation of an access door (refer to Figure i).

WOTE

Cutout is to be just large enough to insert 311011-5 doubler

through skin and enable mechanic to work through hole,

Cutout is to be enlarged to match cutout in 511011-6 doubler

after doubler is positioned in place for drilling per step 3. a.

Cutout is to be between longemns number 5 and number 7.

The top longeron (centerline of airplane) is longeron 0.

Longerona are numbered munterrlackwiss for the left side

while looking forward and are numbered O, 1, 2 and so forth.

Longeron number 6 does not extend past fuselage station

986.82.

2. Remove rivets through fuselage akin and Longemns, forward and aR of door cutout, as necessary to install 311011-6

doubler.

3. Locate, drill and install 311011-5 doubler, 311011-11 doubler, 811011-15 doubler, 911011-9 angle and 511011-7 angle

on sft fuselage as follows (refer to Figure 1):

a. Locate 311017-5 doubler on fuselage and drill all rivet attach holes and enlarge cutout in skin to match door

cutout in doubler. Drill the upper 8vs (5) nualate attach holes thmuQh skin and doubler. The lower five (6)

nutplates will not be attached through skin.

Page 2 of O

IERVICE LETTER NO. 545

6 LON(IERDN

31(0(7´•11 ~J _MS20170P~D4 RIVET OR MS200001\WW2 BLIND RIVET

DOUBLERNP~1097AD4 RIVET

511017´•5 DOUBLER

NO.S

LONOERON

311(1119 DOOR

7

0 DOOR311017´•11

IAEF)

CONSTANTMS2~10ADI

ORMS2OBWI\D4W2

RIVET

311017´•15 O.j7~’51(017´•7

ANGLE

NAS1D87ADI RIVET

NO. 7

VIEW AA

0.30LoNaEnON

MS20470AD4RIVET t

oRr

o~a´•´•Mszwaonplwl

BLIND

RIVETDOUBLER

IREF)DOUBLER

NI\BIOB~AW ~(1 (REF1RIVET ll(l i LON(IERON

VIEW CC

31101)´•´•8

ANGLE (REF) 3110179 DOUBLER

-I I-´•´•´•´•´•´•U´•MS28470nDI

RIVET

MIUWWPIYW2

BLIND !III illRIVET

7 DOUBLER ACCEPTABLE TO TRIM

NIU11081AW (REF) 5110176 DOUBLER TO

RIVET CLEAR RIVET ON

7 FUSELAGE ITYP~PL8)

LONGERON

VIEW BEFICn i. ism 1 ot 2)

PPge 4 d B


NOTE

Trim forward and aR ends of 511017-6 doubler, as necessary,a maximum of 0.GO-inch to prevent interference with rivets.

b, laeate 511011-7 angle, 311017-9 angle, 311011-11 doubler and 311017-13 doubler on fuselage and drill allattach holes.

c. Remove all parts from fuselage and deburr all holes.

d. Lightly countersink all holes in doubler that match original existing holes in fuselage skin to allow for dimplesin skin.

e. Install 311011-11 doubler and 511011-15 doubler on existing longerons (inboard nanges only) usingMS20470AD4 rivets or M820600AD4W2 rivets.

f Position 5110115 doubler in place, slide doubler up and install lower five (5) MS21047L3 nutplates on doublerusing M820426AD3 rivets.

g. Reposition 311011-6 doubler in place and install doubler, 311017-1 angle and 311017-9 angle usingNAS1097AD4 rivets.

h. Install upper five (5) MS21047L3 nutplates using M820426ADS rivets.

4. Remove left and right rudder central linkage access doors that are locatedjust aft of fuselage station 409.66.

5. Remove screws attaching tail cone.

6. Discanneet electrical wiring from tail position lights and remove tail cone.


8. Remove and replace existing ve~ical stabilizer attach bolt (4 places), one st a time. as follows (refer to ngure 2):

a. Remove bolt and inspect bolt hole for possible damage.

b. If hole is not damaged, install AN5-6 bolt, ANBB0D616 washer (under nut only) end M917826-5 nut. Torque bolt

160 to 200 inch-pounds by tightening nut to low side of torque range and, if necessary, continue to tighten untila slot aligns with hale in bolt. Install M824666-132 cotter pin (refer to Figure 3).

NOTE

An additional AN860DS16 washer may be installed (undernut only), if necessary, to assure proper alignment of hole in

halt with slete in nut.

c. If hale is damaged, it is acceptable to use ANG´•B bolt (0.915"m.319" diameter hole) only if an edge distance of0.5B-inch or more can be maintained.

d. If it is determined, prior to reaming existing hale, that an edge distance of 0.56inch or more cannot be

maintained, contact aulfstream American Corporation, Commander Division, Customer 8ervice Department,Bethany, Oklahoma 73008 far further instructions.

a. If it is determined, prior to reaming existing hole, that an edge distance 90.86-inch or more canbe maintained,ream damaged hole to 0.375"10.379" diameter and install ANB-B bolt, ANBBODB1B washer (under nut only) andM817826-8 nut. Torque bolt 500 to 330 inoh´•pounds by tightening nut to low side of tarque range and, if

necessary, continue to tighten until a slot aligns with hole in bolt. Install M824665-134 cotter pin (refar to

Figure S).

NOTE

An additional AN9B0D616 washer may be installed (undernut only), if a assure proper alignment of hole in

bolt with slots in nut.

Page 5 oIO

PIERVICE LETTER NO. 545

CONTROL LINKPIGE

ACCESS woR IREF)

VERTICAL ST*BILIIER

88/\0 IREFI

HORIZONT~L

8SnBILIZER

FRONT 88/(0

D goO [)Ooo~ O

o ooo

o.oD O

o. qo oD

O Ooo

o´•O 00

wnsHa8o

luNoER NVT ONLY)

Ms~lat6a*vr

o M924W8´•132 COTTER PIN

o o TOROUE 180 TO 280 IN-LBS

14 PL8)O O

0000

O 00 O

ooooo oo

NOTE

VIEW LOOKING FORWARD 00 NOT INSTP~LL ANY WASHERS

AT FUSELAGE STA. 409.56 05080 HEnO of BOLT

Flpura 2.

PngeBofB


I\DDITIONI\L WASHER MAY BE

USED IF REOVIRED TO ALIGN

HOLE IN BOLT WITH 8LOT IN NUT

VIEW SHOWIN(1 INCORRECT VIEW SHOWING CORRECT

ALI.NMENT OF HOLE IN BOLT ALIGNMENT OF HOLE IN BOLT

FIIPrs 3.

8. Raconnect electrical wiring to tail position lights and reinstall tail cone on airplane using existing hardware.

15. Reinstall left and right rudder control linkage access doons using existing hardware.

ii. Install 311017-8 door using MS21038-1-10 screw (10 places) (refer to Figure 1).

12. Touchup paint as necessary.


PART II

i. Make a rough cutout (amaller than hole in 311017-5 doubler) in left side sR fuselage, just aft of fuselage skin lap

aR of station 586.82, far installation of an access doar (refer to Figure 1).

NOTE

Cutout is to be just large enough to insert 311011-5 doubler

through skin and enable mechanic to work through hole.

Cutout is to be enlarged to match cutout in 311017-5 doubler

after doubler is positioned in place for drilling per step 3. a.

Cutout i. to be between longemna number 5 and number 7.

The tap langeron (centarline of airplane) is longeron 0.

Longerans are numbered counterclockwise forthe left side

while looking forward and are numbered O, i, 2 and so forth.

Longemn number 6 does not extend past fuselage station

388.82.

2. Remove rivet through fuselage akin and longsmns, forward and aft of door cutout, as necessary to install 511017-6

doubler.

3. Locate, drill and install 511011-6 doubler, 311017-11 doubler, 311011-15 doubler, 511011-8 angle and 511011-7 angle

on aft ti~aalage as follows (refsr to Figure 1):

a. Locate 811017-5 doubler on fuselage and drill all rivet attach holes and enlarge cutout in skin to match door

cutout in doubler. Drill the upper Eve (6) nutplats attach holes through skin and doubler. The Lower five (5)

nutplates be attached through akin.

NOTE

Rim forward and an ends of 51101’1-6 doubler, as necessary,

a maximum of 0.P0-inch to prevent interference wit rivete.

b, lacate I11(111-1 angle, 811011´•8 angle, 51101111 doubler and )11011´•11 doubler on fi~selage and drill all

attach holes.

Page? at 8


c. Remove all parts from fus.lage and deburr all holes,

d. Lightly countersink all holes in doubler that match original existing holes in fuselage skin to allow for dimples

in skin.

e. Install 311017-11 doubler and 511017-15 doubler on existing longerons (inboard Ranges only) using

MS20470AD4 rivets or MS20600AD4W2 rivets.

t position 311011-5 doubler in place, slide doubler up and install lower 8vs (5) MS21o4?L3 nutplates on doubler

using MS20(26AD3 rivets.

g. Reposition 511011-6 doubler in place and install doubler, 311017-1 angle and 311017-9 angle using

NASlOg7AD4 rivets.

h. Install upper Rye (5) MS21047LS nutplates using MS20426ADS rivets.

4 Remove left and nght rudder control linkage access doors that are locstedjust aft of fuselage station 409.56.

5. Remove screws attaching tail cone.

6. Disconnect electrical wiring from tail position lights and remove tail cone.


8. Inspect four (4) bolts attaching vertical stabilizer to front spar of horizontal stabilizer for presence of washer

under bolt heads (refer to Figure 2).

9. If there are no washers under bolt heads, proceed as follows:

a. Assure that nut. are secured properly with cotter pins (refer to Figure 3).

b. If nuts are not secured properly, remove cotter pin and nut, Install an additional AN960D616 washer (under nut

only), reinstall existing nut and torque 180 to 200 inch-pounds by tightening nut to Low side of torque range and,

if necessary, continue to tighten until a slot aligns with hole in bolt. Install existing or new M524665-132 cotter

pin.

c. Proceed to step 11.

10. If there are any washers under the bolt head, proceed as follows:

a. Remove bolts affected, one st a time, and inspect bolt holes for possible damage.

NOTE

Do not have more than one (1) bolt out at the same time.

b. If holes are not damaged, reinstall existing AN5-6 bolt. AN880D516 washer or washers (under out only) and

existing MS11825-S nut. Taque bolt 160 to 2W inch-pounds by tightening nut to low side of taque range and,

if necessary, continue to tighten until a slat aligns with hole in bolt. Install existing or newM824665-1S2 rotter

pin (refer to Figure 3).

c. If holes are damaged, it i. acceptable to use AN6-6 bolts (0.575"10.818" diameter hole) only if an edge distance

of 0.S6inch or more can be maintained.

d. If it is determined, prior to reaming existing holes, that an edge distance of 0.66-inch or more EBJI~ be

maintained, contact aulfstream American Corporation, Commander Division, Customer Service Department,

Bethany, Oklahoma 19008 for further instructions.

a. If it is determined, prior to reaming existing holes, that an edge distance of 0.B6-inch or more E~ebe maintained,

ream damaged hole or holes to O.S?S"/O.S?B" diameter and install ANB-B bolt, ANBBODB1B washer (under nut

only) and MB118256 nut. Torque bolt 900 to S90 inchpounds by tightening nut to low side ortorque range and,

if necessary, continue a tighten until a slot aligns with hole in bolt. Install M924BBS-1S~ cotter pin (refer to

Figure 3).

Page 5 of 8


NOTE

An additional ANOBODB1B washer may be installed (undernut only), if neosssa~y, to assure proper alignment of hale in

holt with slots in nut. The above listed hs~wsre is to be

procured locally.

11. Reconneet electrical wiring to tail position lights and reinstall tail cone on airplane using existing hardware.

12. Reinstall leR and right Ridder control linkage access doors using existing hardware.

13. Install 311017´•3 door using M821039-1-10 screw (10 places) (rsfer to Figure 1).

14. Touchup paint as neeessary.

15. Fill out and mail Compliance Card specifying that Part II has been accomplished.




PUBLICATIONS AFFECTED: The airplane Maintenance Manual changes required by this document will be


RECORD COMPLUNCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No,

345, dated 18 January 1982, entitled "Vertical Stabilizer Attach Bolte Inspection", Part I accomplished (date)

Part II acmmplished_l~.

Page BolB

,Service Letter a~llCulhsrresmAaospaeeCorpo~rion

$b"B~"a*lanornl ah. o* ahoml 73123

SERVICE LETPER NO. 346

REVISION NO. 1

23 JUNE 1986

REPLACEMENT OF INNER STRUCTURAL CABIN WINDOW GLASS

PIPPROVAL: ENOINEERINO DESIDN ASPECTS ARE FAA APPROVED.

This Revision N~tice is being issued to replace PIN 330113´•28 inside giase unth PBi 330115-33 inside glass and replacePIN 330367-55 inside glass with PIN 390367-19 inside glass.

Page 1 of 1

Y,, Service Letter GulfstreamAmericancoaPoa*´•rlon

i Commndn Dk~itlm

swl N~rm Rootr~ll IW~nus.I B´•m´•ny. OCllhoma 11009


t Septsmber 1881


NOTE

PILOT AND COPILOT SIDE WINDOWS, EYEBROW

WINDOWS AND WINDSHIELDS ARE NOT AFFECTED BY

THIS SERVICE LETTER.

1 UODILB IFFECTED: MODEL 690C, SERIAL NOS. 11664, l166B THRU 11610, 11612, 11819 AND 11108 AND

MODEL 685, SERIAL NOS, 96080 THRU 95088, 86085 THRU 98089, 88011 THRU 95018 AND 86016 (8EE NOTE

BELOW FOR ADDITIONAL MODELS THAT MAY SE APF&CTBD BY THIS SERVICE LETfER).

i NOTE

IF ANY O~ THE FOLLOWING MODELS HAVE

REPLACED ANY WINDOW SPACERS, BETWEEN 1L JANUARY 1881 AND 16 JUNE 1891, CONTACT

GULFSTREAM AMERICAN CORPORATION, CUSTOMER

R SERVICE DEPARTMENT, BETHANY, OKLAHOMA 18008

FORWBTRUCTIONS:

MODELS 68(1FL(P), BBOT, B80V AND 680W, 8ERL9L NOS.

1281 THRU 1854, MODEL 681, SERIAL NOS. 8001 THRUi 6012, MODEL 686, SERIAL NOS. 12000 THRU 12066,

MODELS 680, 680A AND 690B, SERIAL NOS. 11001 THRU

11566, MODEL 690C, SERIAL NO8. 11800 THRU 11863

AND MODEL 686. SERIAL NOS. 85000 THRU 95059.

REASON FOR PUBLICATION: THE INSIDE STRUCTURAL WINDOW PANES ARE SU&TECT TO CRAZWC

I´• AROUND BOLT HOLES DUE TO CATALYTIC REACTION OF COMPOUND MAKEUP IN SPACERS AND

OROMMETS.

NOTE

OUTER STRUCTURAL PANES, BEING OF DIFFERENT

COMPOSITION, HAVE NOT BEEN FOUND TO CRAZE.

COMPLIPINCE: WITHIN NEXT 10OHOURG TIME IN SERVICE.

NOTE




AUTHORIZED 8ERVICENTER.

BY WHOM WORK WILL BE PICCOMPLISHED: A P MECHANIC OR F,BUNALENT.

APPROVAL: PAA DOA 8W-2 APPROVED.

3


MAN HOUAS: TWENTY SIX (26) HOURS.

NOTE

DULFWREAM AMERICAN CORPORATION WILL ALLOW

A CREDIT OF TWENTY 81X (26) HOURS LABOR UPON

RECEIPf OF A PROPERLY EXECUTED WARRANTY

CLAIM, CUTOUT SECTION OF EACH WINDOW

ICONTAININCI THE PART NUMBERI, OLD GPACER8 ANDA COMPLIANCEC~D.

PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGH

YOUR NEAREST OULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 9601.58. A PULL CREDIT

WILL BE ISSUED UPON RECEIPT OF A PROPERLY EXECUTED WARRANTY CLAIM, CUTOUT SECTION OF

EACH WINDOW ICONTAININ(I THE PART NUMBER), OLD SPACERS AND A COMPLIANCE CARD.FACTORY SERIAL NUMBER WHEN ORDERING

SERVICE LETTER NO. 946 KIT CONSISTING OF THE FOLLOWING:

Prlw lub]oct to Ehan(ls dthoul not(oe,

BTY PART NO. DESCRIPflON

2ea. 580113-29 indde Glees8ee. 550115-51 Spacer1 ea. 580561-1 inside Classt as. 850361-8 inside Glass

2 as. 550361-66 Inside Glass

2 ea. 590561-65 Spacer2 ea. 850561-85 8pacer2 ea. 89056181 8paur2 ea. 330361-89 Space~z ea. 330361-11 8pacer2 ea. 330381-13 Spacer4sa. 830561-15 Spacer4 ea. 530361-11 Spacer8 ea. 861887´•35 Felt Pad

584 ea. WX)106621 Girommet

13 so. R. R411N yls Neoprenetmll Surgical Tape (514")1 ea. Compliance Card

1 se. Service Letter No. 546 instructions

SPECIALTOOLS: NONE.

~CCOMPLISHMENT INSTRUCTIONS:

CAUTION

WHEN PERFORMING THE FOLLOWING PROCEDURES,CARE SHOULD BE TAKEN SO AS NOT TO DAMAGE OR

SOIL ANY INTERIOR PANELS OR UPHOLSTERY.

1. Remove emergency exit window panel as follows (refer to Figure 1):

a. Remove emergency exit window from airplane.

b. Remove snaw (2 places) attaching emergency slit window release handle and remove handle.

c. Remove screw (4 places) attaching emergency exit window panel to window and remove panel.

1. Remove window penal from main cabin door as follows:

a. Remove screw attaching interior handle to door mechanism and remove interior handle.

b. Remove screws attaching center door panel to daor, disconnect wires from emergency door release switch and

remove center panel from doer. Mark wires to assure that switch will be rewired correctly after reassembly.

Page a of 11


81DE WINDOWTRIM EXTRVSION

EMERGENCY EXIT EMERGENCY EXIT PANEL

WINDOW PANEL RELEASE HANDLE ARMRESTPANEL

’i-r

meLE COVER

I

EMERGENCY EXIT

RELEASE HANDLE

EMER(IENCY EXIT

WINDOW PANEL

t;llun

Page 9 of 11


c. Remove channel that holds window panel in place.

d. Remove screw (2 places) that attaches window panel to door, pull down on window panel and remove panel from

door.

e. Remove lower acrew attaching forward bayonet rod assembly and remove rod assembly and bayonet from door.

NOTE

There i. a small spacer located at the lower clevis on the rod

assembly, Asaure that apacer is not dropped and lost when

rod assembly is removed.

3. Remove curtains locatedjust aft of main cabin door and emergency exit window.

4. Remove lan and right cabin aide window panels as follows (rsfer to Figure 1):

a. Pull top of table cover out and pull table up to expose screws attaching table guide O aide of table

b. Remove either forward or aft table guide from table and remove table.

c Remove two iZ) top screws attaching table cover to fuselage structure.

d Pull down on top of arm rest panels to expose screws that attach trim extrusion to fuselage structure.

e. Remove screws attaching trim extrusion to fuselage structure and remove trim extrusion.

f Loosen aft screws attaching panel over main cabin door to facilitate removal of left cabin side window panel

g Remove upper screws attaching cabin aide window panel to fuselage structure.

h. Assure that cabin side window panel, are not stuck to insulation prior to removal

i, Remove left cabin side window panel by pushing panel back to release forward portion of panel and then pull

panel dawn to clear headliner.

j Remove right cabin side panel by pulling down on panel to clear headliner.

5 Remove screws attaching all interior window glass (tintedl to emergency exit window, main cabin door and cabin

side windows and remove interior glass from airplane.

6 Remove inside and outside windows as follows (refer to Figure 21:

a Remove foam rubber insulation ~rom around window retainers.

b Remove interior clips, attached by screws, as necessary to facilitate removal of window retainers and windows.

Mark ail clips to assure they will be reinstalled in same location from which they were removed,

c Remove all screws attaching windows to fuselage skin.

d Remove window retainers and bumpers Mark top of retainers to assure they will be reinstalled in same

position from which they were removed.

NOTE

Pumpers are bonded to retainers.

e Remove windows

f Remove and discard, only if damaged, any neoprene (gasketfil bonded to interior of fuselage skin and on

retainers,

NOTE

Daskets are to be replaced only if they are damaged.

Page 4 of 11


8W1Mm

R911N 1118BROMMET

NranENr OLwlL.aasu .j

.m~.´•10.

BPnCER 14 PLSI

RI11N 1118is~ i -NEOPRENE

1- I’/

Or L cnNo

i CHI\NNEL

ka‘i´•

O ´•’I

lII ii

ExlsnNo

i OUTSIDE OLP~8S

INSIDE OL1\8(

L

EMEROENCYEXIT

WINDOW )I\NEL

INTERIOR (ILASS

CLIP

SE~L

REYEP~L

*illun 2 ishast 1 ot 3)

Page 5 of 11


gC0,

MAIN cnslhl ODORWINDOW PIZNELr REVEAL

CLIP

t; OIASSTINTED INTERIOR

GANG

CHANNEL

R(IIN 1118NEOPRENE

33011331SPACER 14 PLB

B~ n411N ins

NEOPRENE

CLIPY~1

RETAINER

r;;"550113´•28

OUTSIDE GLASS

800108´•527

GROMMET

Fllun, 2 ihast i of 91

Page B oI 11

SERYICE I.ETTER NO. 346

REYEI\LTINTED INTERIOR

CH~NNEL

OI\NO

OROMMET RI1IN 1116

U(UB7´•b3SPLICERII )L~CIS1

RIIIN lilB

~1.

BUMPER330361-51PACER I? PLSI

INBIDE OL*B prill jEXI(ITING

WTIIOE GL/\S5

IUSLLAOE SI(IN

eaalma,l

cnommET WINDOW PIINEL

BUMPER GI\NG

Cnl\NNEL

RI11N 1116 NIOPRENI

33035785 SPPICLR

J3a787d3SP*CEA

R411N 11(5 NEOPRENE

Ir h II: 1G

330357-61

SP~CLARCT

REVC~L

SP~CERTINTED

INTERIOR 330367

GLI\SS INS108 GL*SSFUSLLI\GE SI(IN

EXISTING

OUTSIDE GL~iS

33035)691 ´•I

PP~CER

~iCn Z IShs~t J ot O)

Page 7 of 11

SERYICE LETTER NO. 548

CAUTION

Protect all window glass, after removal, to prevent scratchingofglass.

g. Disassemble windows, cutout portion of inner glass (eontaining the part number) for return to Oulfstream

American Corporation with old spacers, and discard the gmmmets.

h. Cheek outside glass, around each bolt hole, for chips or distress. If found, contact your nearest Gulfstream

Commander serviCenter. If no cracks are found, retain outside glass for later reinatallation.

CAUTION

Care should be taken when assembling new inside glass to

existing outside glass to assure no contaminants are trappedbetween panes of glass and assure that glass is protected from

scratches.

7. Assemble new inside glass to existing outside glass se follows (refer to Figure 2):

NOTE

This procedure applies to all windows.

a. Clean both aides of inside glass and outside glass as outlined in Chapter 56 of the Airplane Maintenance

Manual.

b. Apply one (1) inch tape over all holes an outer surface of outside glass and turn glass over so that outer surface

is down.

NOTE

Outer surface of window is contaured. The tape is used to

hold grommets in place during assembly to inside glass and

outside glass.

c. Insert new 900106-621 grommete in outside glass holes.

d. Install new spacers over grommets.

NOTE

Square corners on spacers should be positioned adjacent to

edge of glass.

e. Assure that both inside glass and outside glass are clean and ready for assembly

f Place new inside glass on existing outside glass.

g. Apply one(l) inch tape over holes to prevent grommets from falling out.

h. Apply 314 inch surgical tape on all corners of glass (refer to Figure 3)

NOTE

Picture window will require one (1) piece of 314 inch surgicaltape an top and one (1) on bottom where spacers are joinedtogether.

8. If neoprene (gaskets) are to be replaced, thoroughly clean any damaged neoprene material from fuselage skin.

emergency elit window, main cabin door and all retainers as necessary.

9. Bond new R411N 1116 neoprene on fuselage skin, emergency exit window, main cabin door and on all retainers usingEC1~03 or an equivalent contact cement and trim as necessary (refer to Figure 21

Page 8 of 11


NOTE

To assure that the R411N 1118 neoprane is not wasted, layoutsites for each window prior to cutting. Cut one (1) inch stripsfor small windows and for all retainers. Cut two (2) inch

strips for picture windows.

10. Using a sharp tool, punch all holes in new neoprene.

11. Install all inside end outside windows on airplane as follows (refer to Figure 2):

a. Remove tepe, holding grommets, from both sides of glass.

b. Position window and retainers for installation on airplane and install existing screws. Assure that bumpersam bonded to retainers, if not, rebond bumpers to retainers using EC1403 or an equivalent contact cement,

E. Tighten all screws to the following torque value:

Main Cabin Door Window 12 to 15 inch-poundsEmergency Exit Window 12 a 15 inch-poundsPicture Window 20 to 25 ineh´•pounds8mall Cabin Windows 10 to 25 inch´•peunds

d. Ibinstall existing interior clip., removed in step 6.b., using existing hardware,

a. Bond 861881-53 felt pad on outboard side of picture window lower clip (4 places) on left and right side usingEC1´•IOS or an equivalent contact cement (refer to Figure 4).

NOTE

Allow contact cement to thoroughly dry before installinginteriorwindaws.

f Reinstall existing foam rubber insulation around all window retainers.

g. Assure that all glass is clean and then reinstall existing interior window glass (tinted glassl using existinghardware.

h. Reinstall emergency exit window on airplane.

CAVTlOhI

Assure that seal is not pinched when installing window.

12. Pressurieed cabin to maximum differential pressure to assure there are no leaks (refer to Chapter 21 of the

Airplane Maintenance Manual).

19. Reinstall existing left and right cabin side window panels as follows:

a. Position panel for installation and install upper screws and washers.

NOTE

On left aide panel, assure that forward edge of panel is tucked

under main cabin door panel.

b. Tighten aft screws that attach penal over main cabin doe;.

c install trim extrusion using existing hardware, Do not install two (2) serewa in area of table until arm rest

panels are tucked under trim extrusion.

d. Tuck arm rest panels under trim extrusion.

e. Install two (2) screws that attach table cover to fuselage.

Page B of 11

SERVICE LETTER NO. SE

IREF)

O914" SURGICAL TAPE OUTSIDE

GLASS IREF)O

INLIIDE GLASS

IREF)

O

SPACER IREFI

FipureS

PICTURE WINDOW

IRE Fl

BoND 8818875s FELT PAD

TOOUTBOIRD3DEOFLOWER CLIP (4 PLSI WITH

ECI403CONTACTCEMENT

L.PELT PAD

(REF)YIIYI LOOKING OUTBO~RDCLIP(REF)I\T RH SIDE LH SIDE OPPOSITE

YIEW~

Flpural.

Page 10 ol 11


f Position table for installation, reinstall table track on side of table and close table.

g Push in on tap of table cover.

14. Reinstall window panel on main cabin door as follows:

a. Reinatall forward bayonst rod assembly and bayonet on door using existing hardware and assure that bayonetis rigged properly

b. Position upper panel far installation on door and install existing hardware.

E. Reinstall existing channel under window panel using existing hardware.

d. Reconnect wires to emergency door release switch and install center panel on door using existing hardware.

e. Reinstall interior handle on bor using existing screw.

f Close cabin door and check to assure that red dots on bayonet inspection windows are centered over white disks,

g. Cheek electrical f~netian of door release system.

15. Reinstall emergency slit window panel as follows:

a, With emergency exit window release handle removed, position window panel for installation and installexisting hardware.

b. Reinstall emergency exit window release handle using existing hardware.

16. Reinstall curtaina,removedin step9., uaingexistinghardwsre.

17. Touch up paint, if necessary, on f\lselage.

18. Clean upholstery and side panels as necessary.

19 Fill out and mail Compliance Card, Warranty Claim, portion of glees (containing part number) and old spacers toDulfstream American Corporation, Commander Division, Bethany, Oklahoma 15008.

ELECTRICAL LOPID: NO CHANGE.

WEIGHT FIND 8*LANCE: NO CHANCE

SPARES AFFECTED: YES.

PUBIICATIONS AFFECTED: The Illustrated Parts Catalog changes required by this document will be incorporated at


RECORD COMPLIANCE: Make an appropriate entry in si~lsne maintenance records as follows: Service Letter No

346, dated 1 September IsB1, entitled "Replseement of inner Structural Cabin Window Glass", accomplishedtdafe)

Page 11 of 11

Service Letter GulfstreamAmericanuonpon*1´•ln*

Commanda Dirbion

6001 Norm Ra;kwsll Ausnua.Bsmany, Oklehem 13WB


3 November 1981


MODELS AFFECTED: MODEL 696A, SERIAL NOS. 96001, AND 96004 THRU 96001.

REASON FOR PUBLIC*TION: INSIDE STRUCTURAL WINDOWS ARE SUBJECT TO CRAZING AROUND BOLT

HOLES DUE TO INSTALLATION PRELOAD.

COMPLIP~NCE: WITHIN NEXT 100-HOURS TIME IN SERVICE.

NOTE





BY WHOM WORK WILL BE PICCOMPLISHED: A L P MECHANIC OR E9UIVALENT.


ESTIMATED MAN HOURS: FORTY-FOUR (44) HOURS.

NOTE

OULFSTREAM AMERICAN CORPORATION WILL ALLOW

A CREDIT OF FORIIYFOUR (44) HOURS LABOR UPON

RECEIPI~ OF A PROPERLY EXECUTED WARRANTY

CLAIM AND A COMPLIANCE CARD.


YOUR NEAREST DULP8TI~AM COMMANDER AUTHORIZED BERVICENTER MOR 6819.11. A FULL CREDIT

WILL BE ISSUED UPON RECEIPT OF A PROPERLY EXECUTED WARRANTY CLAIM AND A COMPLIANCE

CARD. REFERENCE THIS SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN

ORDERING SERVICE NO. 5117 KPT CONSISTING OF THE FOLLOWING.

pd, ..qsotlo~nllr


2 ea. 380381´•115 inside Glass

2 ea. 950581-114 inside Glass

1 ea. 950381´•115 inside Glass

1 as. 330881-116 inside Glass

1 ea. 330381-111 inside Glass

I as. 330881-118 Inside Glass

282 ea. 800106-627 Gmmmet

19.6 4´• ft. ~11N 1/8 Neoprene1 roll Sugieal Tape (2.0")


1 as, Serviee Letter No. 347 instructions

PagelolB


SPECIILTOOIS: NONE.


CAUTION

WHEN PERFORMIND THE FOLLOWING PROCEDURES.CARE SHOULD BE TAKEN SO AS NOT TO DAMAGE OR

SOIL ANY INTERIOR PANELIOB UPHOLSTERY.

1. Remove left and right cabin side window panels only.

NOTE

This rework does not apply to the cabin door, emergency slrit

or pilot and copilot windows.

2. Remove screws attaching cabin interior glass (tintedl to cabin side windows and remove interior glass from airplane.

3. Remove inside and outside glass as follows (refer to Figure 1):

a. Remove insulation from around window retainers.

b. Remove all screws attaching windows to fuselage skin.

c. Remove window retainers and bumpers, Mark top of retainers to assure they will be reinstalled in same positionRom which they were removed.

NOTE

Bumpers are bonded to retainers.

d. Remove windowsfrom airplane.

a. Remove and discard, only if damaged, any neoprene (gaskets) bonded to interior of fuselage akin and on

retainers.

NOTE

Gaskets are to be replaced only if they are damaged.

CAUTION

Protect all window glass, after removal, to prevent scratchingofglass.

f Disassemble windows and discard the inside glass and the grommets.

g. Cheek outside glass, around each bolt hole, for chips or distress. If found, contact your nearest Dulfstream

Commander ServiCenter. Ifno cracks are found, retain outside glass for later reinstallation.

CAUTION

Care should be taken when assemblying now inside glass to

eliating outside glass to assure no contaminants are trappedbetween panes of glass and assure that glass is protected from

scratches.

Assemble new inside glass to aliating outside glass as Follows (refer to Figure 1):

NOTE

This procedure applies to all windows.

a. Clean both sides of inside glass and outside glass as outlined in Chapter SE of the Airplane Maintenance Manual.

Page lolB


c.aN´•lo. i? Xa AI I

WINDOWPP~NEL EXISTING TINTED

Inrmlono~ass

EXISTING BUMPER

EXISTING GANG

RETAINER

R411N 1/3 NEDPRENE

39a981´•113 INSIDE GLASS

IINEOPAENE

´•i

Bb

EXISTINGSPPICERS

900108´•521(iROMMET

FUSELAGESKIN

EX18T1N(I OUT81DE

GLASS



Figqs 1. IShaat 1 of 21

Page3ofG

SERYICE LETTER NO. 541

LEFT INSTALLATION SHOWNExlSTlNG INTERIOR

PANELEXISTING TINTED


INTERIOR GLASS

EXISTING BUMPER

EXISTING GANG

CHANNEL

P41N id NEOPRENEO

J 23438(´•117GLASS

GROMMET

~II I)R411NllsNEOPRENE

I 8KIN

L r

EXIIITINO

EXISTING OUTSIDE

CAslN SIDE

WINDOWPANEL

EXIFTING TINTED

GLASS

EXlsTIN(IGAN(I

EXIBTIN(I BUMPERRII(NlnNEOPRENE

116 INSIDE GLASS

EXISTING OUTSIDE

EXISTING RETAINER~I- b

EXlsTlNa

800108´•527 (IROMWIET

ZIL~.L*B.SIINR411N 1/8

Filure 1. (Shaa 2 of 21

Page(olB

EIERVICE LETTER NOi 341

b. Apply one (1) inch tape over all holes on outer surface of outside glass and turn glass over so that outer surface

is down.

NOTE

Outer surface of window is contoured. The tape is used to hold

grommets in place during assembly of inside glass to outside

glass.

c. Insert new 900106-621 grommets in outside glass holes.

d Install existing spacers over grommets.

e. Assure that both inside glass and outside glass are clean and ready for assembly.

f Place new inside glass on existing outside glass.

NOTE

Contour of inside glass goes tothe inboard aids.

g. Apply ons (1) inch taps over holes to prevent prammsts from fallingout.

h Apply Z.O-inch surgical tape on all corners of glass (refer to Figure 2).

5. If oeoprene (gasksts) are to be replaced, remove any damaged neoprene material from fi~selage skin and all reta~nersas necessary.

6. Bond new R~11N 11 neoprene of fuselage skin and on all rsthmers using EC140S or an equivalent contact cement

and trim a. necessary. Allow cement to cure for thirty (90) minutes prior to accomplishing step 7 (refer to Figure 1).

Using a sharp tool, punch all screw holes in neoprene.

8. Install all inside and outside windows on airplane as follows (refer to Figure 1):

a. Remove tape, holding grommets, from bath sides of glass.

b. Position ~vlndow and retainers for installation on airplane and install existing screws. Assure that bumpers are

bonded to retainers, if not, rebond bumpers to retainers using EC1´•IOS or an equivalent contact cement.

c. Tighten all screws to a torque value of 20 to 26 inch-pounds.

d. Reinstall existing insulation around all window retainers.

e. Assure that all glass is clean and then install existing inner window glass (tinted glass) using existing hardware.

9. Pressurize cabin to a maximum differential pressure to assure Bare are no leaks (refer to Chapter 21 of AirplaneMaintenance Manual.)

10. Rsinstall left and right cabin side window panels using existing hardware.

11. Touch up paint, if necessary, on fuselage.

12. Clean upholstery and aide panels as necessary.


Page SalG


IAEFI

O2.0" 8UROICAL TAPE

OUTSIDE

INSIDE

iSPACER iff EFI

FlsureZ.


WEI~HT AND BALANCE: NO CHANGE.

SPARES AFFECTED: YES.

PUBLICATIONS AFFECTED: The Illustrated Parts Catalog changes required by this document will be incorporated atthe nsnt scheduled revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.941, dated 3 November 1981, Entitled "Rspl.cement of Inner Structural Cabin Side Window Glass", accomplished

(date)

PageBofB

Seavice e~ter GulfstreamAerospace


(8upersedes Service Letter No. 549 in its entirety)24 February 1984

ELEVATOR PUSH-PULL TUBE ASSEMBLY INSPECTION AND REPLACEMENT

NOTE

IF BASIC SERVICE LETTER NO. 548 HAS BEEN

COMPLIED WITH, COMPLIANCE WITH THIS SERVICE

LETTER IS NOT REQUIRED.

MODELS AFFECTED: MODELS BB0FL, 680FL(P), 680T, 680V AND 680W, SERIAL NOS. 1261 THRU 1854, MODEL

681, 8ERUL NOS. 6001 THRU 6072, MODEL 885, SERIAL NOS. 12000 THRU 12066,

MODELS 690, 690A AND 69OB, SERIAL NOS. 11001 THRU 11566, MODEL 690C, SERIAL

NOS. 11600 THRU 11718, MODEL 695, SERIAL NOS. 95000 THRU 95084 AND MODEL

695A, SERIAL NOS. 86001, 96008, 86006 THRU 96016 AND 96018.

REASON FOR PUBLICATION: POSSIBLE CRACKS IN ELEVATOR PUSH-PULL TUBE ASSEMBLIES IN BOTH

SWAGED ENDS.

COMPLIANCE: PART I- DURING NEXT 100-HOUR INSPECTION AND EVERY 200HOURs TIME 1N ISERVICE THEREAFTER UNTIL PART II OF THIS SERVICE LETTER HAS BEEN

C *cooMP~Hea

NOTE


COMPLYINCI WITH THIS SERVICE LE~ER, CONTACT


AUTHORIZED SERVIOENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A Be P MECHANIC OR EQUIVALENT.


ESTIMATED MAN HOURS: PART I INSPECTTUBE ASSEMBLIES:

MODEL BBSA FOUR a ONE-HALF (4.5) HOURS, ALL OTHER MODELS

-TWO (2) HOURS.

PART II REPLACE TORE ASSEMBLIES:MODEL BBBA 81X (6) HOURS. ALL OTHER MODELS FOURTEEN (14)

HOURS.

PARTS DATA: PARTS REQUIRED TO COMPLY WITH PART II OF THIS SERVICE LEWER MAY BE PROCURED

THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED BERVICENTER FOR 896.64.

REFERENCE THIS SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING

SERVICE LE?TER NO. 349A KIT CONSISTING OF THE FOLLOWIND:

Ilrl~ UIMIID nalo´•.

OTY PART NO. DESCRIPTION

2 ea. 590578-1 or 530578-81 Tube Assy

1 ea,

or630578-5CamplisnceCsrd

1 es. Service Letter No. 349A tnstructions

Page 1011

GF,RVICE LET~ER NO, 349A

S.ECIII~DOLB; N,N$´•


PART I INSPECT ELEVATOR PUSH-PULL TUBE ASSEMBLIES.

1. On Model 696A, proceed as follows:

a. Remove pilot seat, copilot Beat and bars.

b. Remove carpet, as necessary, to gain access to nwr panels in eaokpit area.

c. Remove left and right noor panels to gain access to elevator push-pull tube assemblies (refer to Figure


2. On all Models (excspt Model 696A31 prooeeda as follows:

a. Remove interior and carpet as necessary,just aR of pilot and copilot seats, to gain access to floor panels


b. Remove left and right access covers from noo~panels to gain access to aft end of elevator push-pull tube

assemblies (refer to Figure 1).

c. Remove access cover (2 places) from bottom of fuselage to gain access to forward end of elevator push-

pull tube assemblies (refer to Figure i).

d. Proceed to step i.

S. Visually inspect swaged ends of both elevator push-pull tube esaemblies for possible cracks (refsr to Figure 2).

I

6. If craets are found, proceed to Part II.

6. Reinstall acceea covers or noor panels an airplane.

7. On all Models (except Model 6BOFL and 69SA), reseal access covers on floor panels as outlined in the applicable

Airplane Maintenance Manual.

8. On Model 695A, reinstall carpet, pilot and copilot seats and bars.

9. On all other Medals, reinstall interiors and carpet.


PART II REPLACE ELEVATOR PUSH-PULL TUBE ASSEMBLIES.

1. On Model 696A, proceed as follows:

a. Remove pilot sent, copilot seat and bars.

b. Remove carpet, as necessary, to gain access to noor panels in mchpit area.

c. Remove left and right noor panels to gain access to elevator push-pull tube assemblies (refer to Figure

d. Remove bolts attaching left and right elevator push-pull tube assemblies to control columns and to

elevator torque tubs arms and remove tube assemblies (refer to Figure 2).

PBBeaol?

SERVICE LE1TER NO. 349A

REMOVE TH18 PANEL TO

C RI~HT PUSH´•PULL TUBE

AGEY

REMOVE TnlS PANEL TO

INSPECT AND AEPLACE

LEFT PUSH´•PULL TUBE

*sEY

MOOEI.B9SA

Fi(u~a i. IWm d 2)

Page S ol 1

SEKYICE LETTER NO. 349A

REMOVE THIII FLOOR PANEL

TO REPLACE RI(IHT PUW´•PULL

TUBE ASSY

OO

O

o o

oo o’´•´•.~ o

o

o

o

~JREMOVE THIS FLOOR PANELTO REPLACE LEFT PUGH´•PULLTUBE AgSY

REMOVE ACCESS COVER 12 PLS1TO INSPECT PUFH-PULL TUBE

~616

REMOVE ACCESS COVERSTO INSPECT AND REPLACE

PUW´•PULL TUBE ASSYS

O

o o o

o

VIEW LOOKING UP AT FUSELA(IE

ALL MODELSIEXCEPT MODEL 885*1

Fi~urs IShsat 2 ot 21

Page 4017

SERYICE LETTER NO. 348A

a Rsmoa aristmg md mds. Eb.knuts and Lay loeXa imm tub. Oipard alialins tubo

assemblies and retain rod ends, checknute and key looks for reinstallation.

f Install existing rod ends, checlrnuts.and key lacks on new 590578-1 or 530518´•S1 or 530518-5 tube Bassemblies and safety wire (refer to Figure 3).

g. Install new push-pull tube assemblies on control columns and on elevator torque tube arms using

existing hardware (refer to Figure 2).

h. Check a4iustment of elevator controls as outlined in the Airplane Maintenance Manual.

i Reinstall existing floor panels on airplane using existing hardware.

i. Rsinstall carpet, pilot and copilot seats end bars.

k. Proceed to step 3.

2. On all Model, (except Model 696A3, proceed as follows:

a. Remove interiors and carpet, as necsssary,just aft of pilot and copilot seats to gain access to floor panels

(refer to Figure i).

b. Remove rivets from left and right Roar panels, just aft of pilot and copilot seats, as necessary to facilitate

removal of elevator push-pull tubs assemblies (refer to Figure i).

Remove access cover (2 places) f~om bottom of fuselage to gain access to forward end of elevator puah-

pull tube assemblies (refer to Figure i).

d. Remove bolts attaching aft end of push-pull tube assemblies to elevator torque tube arm

a. Remove left and right arms ham elevator torque tubs to facilitate removal of push-pull tube assemblies

,,,,,,,~.2,

f Remove rad end, cheeltnut and key IDck from aft end of push-pull tube assemblies. Retain rod ends,

checknuts and key locks for reinstallation.

g. Remove bolts attaching push-pull tube asaemblies to control calumns and remove push-pull tube

assemblies.

h. Remove rod end, checknut and key lack from forward end of push-pull tube assemblies. Discard existing

tube assemblies and retain rod ends. checknuts and key lacks.

Install existing rod end, chsoltnut and key lock on forward end only of 630518-1 or 530578-51 or 530578-6 1tube assemblies and safety wire (refsr to Figure 3).

j. Position push-pull tubs assemblies in place and install forward end using existing hardware.

Reinstall existing arms on elevator torque tube using existing hardware.

i. Insl.l sristin. rod end, ihsrhnut and L.y lock on an end of.0678-1 or hPDS7B61 or 650618-5 rubs Iassembly. Do not safety wire until adjustment os elevator controls has been accomplished.

m. Check adjustment of elevator controls as outlined in applicable Airplane Maintenance Manual and then

safety wire aft rad end on push-pull tube assemblies.

n. Rsinstall existing access covers and floor panel. using existing screws, CR3243-4 or CR2249´•4 blind

rivets and CR9242-4 or CR2248-4 blind rivets.

NOTe

Rivet lengths to be determined on installation.

Page 5 of 7


ELEVATOR TOROUE

TUBE IREF)

/ARM IREFI

HDWE IREFI

CONTROL COLUMN

(REF~

IN6PECT SWABED EN08 FOR

PO8SI6LE CRACKS 14 PLSI

REMOVE EXISTIN(I PUSH´•PULL TUBE ASSY

*ND I~TALL 530678-1 OR 6SOhlBdl OR

5305186 TUBE ABEY (2 PLS)

EX18T(NO HDWE IREFL

FIBYrO 2.

ROD END.CHECKNUT I\ND KEY

LOCK 12 PL~I65(1578´•1 OR 530618´•SI OR630578´•6 TUBE ASSY SAFEN WIRE CHECK

31.12.. NUT USING MS2(lsBBC32

NOMINI\L IO.M2" OIA.1 CORROOION

RESISTANTSTEELWIRE

12 PLS1

FIIYn3´•

PageGol’l


C o Aa~aal and nmE isnsle ap outlun´•d in t~ lip~irsbls Alrpleoe Meint~N).i. Manull

NOTE

Model BSOFL dose not Rquire sealing.

p. Reinstall interiors and carpet.

3. Fill out and mail Compliance Card specifying that Part II has been accomplished Note ilany cracks were found

and where they were located.


WEIGHT ~ND BALANCE: NO CHANGE.

BPAREB AFFECTED: NO.

PUBLICATIONS AFFECTED: The Illustrated Parts Catalog Changes required by this document will be incorporated at

the nert scheduled revision.

RECORD COMPLIPINCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.

349A. dated 24 Bsbrusry 1984, entitled *EL8vator PushPull Tubs Assembly inspection end Replacement", Part I I

accomplished (date) Port II accomplished (date)

C

Page’lof?

~illService Letter Gulfst~amAmeriran

colPoln´•rlurr

Cammada Dirlon

BW1 Norm Roc~lall ~vsnua.(XIIhany. ~l´•homa 13006

8FIRVICE LETPER NO. 360

15 April 1982

COCKPIT INSULATION OVERHEAD SWITCH PANEL

PODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11?21.



MODEL BgM, 8ERIAL NOS. 88001 THRU 9BOS0.

REASON FOR PUBUCATION: INSULATION IMPROVEMENT TO CONTROL MOISTURE CONDENSATION

ABOVE OVERHEAD SWITCH PANEL.

COMPL]ANCE: WITHIN NEXT 100-HOURS TIME W SERVICE.

POTI


COMPLYIND WITH THIS SERVICE LET~R, CONTACT

YOUR NEAREST (IULFSTR~AM COMMANDER

AUTHORIZED SERVICENPER.

BY WHOP WORK WILL BE ACCOPPLISHEO: A d P MECHANIC OR EQUIVALENI.

APPROVAL: FAA DOA 8W´•2 APPROVED

ESTIPnTED MIN HOVRS: FnTE (6) HOURS.

WOTe

FOR AIRCRAFI 8TaL hi WARRANTY, aULPSPREAM

AMERICAN CORPORATION WILL ALLOW A CREDIT OF

FIVE (6) HOURS UPON RECEIPI OF A PROPERLY

EXECUTED WNUMNTY CLAIM AND A COMPLIANCE

CARD.

PARIS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE MAY BE PROCURED THROUDH

YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED 8ERt~CEPJTER FOR: KPT NO. 1 (46.81 OR KPT

NO. 2 -946.9?. FOE MICRAPP SPILL IN WNUMP~I, A FULL CREDIT WILL BE 18SUED UPON RECEIPI OF

A PROPERLY EX~CUTED WARRANTY CLAIM AND A COMPLIANCE CARD. REFERENCE THIS SERVICE

LE1TER. AIRCRAIT MODEL AND FACTORY 8ERML NUMBER WHEN ORDERING SERVICE LETPER NO. 350

KIT CONS1STINO OF THE FOLLOWING:

Page lolB

8ERVICE LETTER NO. SSo

KIT NO. 1- MODELSBSOC AND 895.

KIT NO. 2 MODELSBSOD AND 896A.

Kit Kit

No.l No.2

~TY BTY PARTNO DEBCRIPI~ION

lee. 860715-3 insulation

lea. 860175-4 insulation

Pea. 860115-6 Vinyl

sea. 860175-7 Insulation

1 se. 860175-9 Insulation

Zee. 860175´•11 insulation

2ea. 860115´•13 Insulation

lea. 862121-153 Insulation

las. 882121-154 insulation

2sa. 862121-156 Vinyl2ea. 882121-151 insulation

las. 882121-168 insulation

2ea. 862121-181 insulation

2ea. 862121-163 insulation

Iroll iroll #474 Tape(l")lee. lea. ComplianceCardiea, las. GervicsLetterNo.SSO Instructions

SPECI*LTOOLS: NONE.

ACCOMPLISHIENT INSTRVCTIONS:

i. Lower overhead switch panel as follows:

a. Ensure thatelectrical power is removed.

CAUTION

When removing eleetmlumin8seent panels, be careful not to

damage or break electrical wiring and connectors. De not allow

panel to hang by the wiring. Panel has to be supported or

damage may oocurto electroluminescent panels.

b. Loosen alien screwson allknabson face ofthe e*etmluminescent panels andremove knobs.

c. Remove attachingsorews securing electroluminescent panels.

d. Carefully remove panels sothatwiring forelectmlumineacsntpanelswill beexposed.

e. Grasp wires and gently pull dawn until quick disconnect end airplane wiring are enpased. Disconnect

electroluminss~entpanel.

r Remove attaehingsrrews from top ofmetalplate ofoverhead switchpanel.

g. Lower overhead switchpanel andallow(tto suspndbyths hinges.

2 Remove and discard any insulation that is installed on fuselage skin and frames in area above the overhead switch

panel.

3 Thoroughlyclean .u~faee where insulation istobe bonded usingToluene orlethylEthyl Ketone (MEK).

CAUTION

To prevent possible damage, care should be taken when usingsolvents in areaafelectrical equipmentand plasticmaterials.

Page 2 of 6


FUSELAGE SKIN IREF)

_B

880775-1

INSULATION

A

.iP 86077613 INSULATION

CANTEOFRAHE IAEFI

WINDSnlELd OVERnEI\D SWITCH PANEL IREF1FRAME IREFI

860775-8 INSULATION 880775-6 VINYL

VIEW LOOKING INBD FROM LEFT SIDE

880776-1( INSULATION E 880176-11 INSULATION

BOND WITH Ecluu CEMENT BOND WITH 501103 CEMENT

5597757 INSULATION

BOND WITH EC1403 CEMENTI--F-

8807)6-7 INSULATIONANDCUTOUT

BOND WITH EC1~103 CEMENT880771´•8 INSULATION

BOND WITH ECI(DJ CEMENTEXTEND TD FRAME

JUNCTIONITYP1 VIEW A-A

LOOKING FWD AT WINDSHIELD FRAME

SLIT PIS REOD FOR WIRE

on STRUCTURE ITYP) E 880776-11 INSULATION

IREFI

-i~-

~ct=-

86071515 INSULATIONBOND WITH ECII(U CEMENT

EXTEND TO FRAME

JUNCTIONITYPI VIEW B-8

LOOKING AFT AT CANTED FRAME

MODslS 690C *ND 695 FICln 2- IOhrt 1 st 21

Page 3 of 6

SERYICF.I.ETPERN0.3~O

800715-5 VINYL 8807764 INbULPlnON

880775-18 INIULATION

(REFI I 88077618 INSULATION

L

0507751 INsuLnnoN

660775-11 INsuLnnoNVSE NO. ale TAPE TO INSTALL

(REFI880775´•3 AND INSULATION

AND 860776´•5 YINYL 880775´•7 INSULATIONIAEFI

*011

TRIM AND IN~TALL INSVLATIDN WITH

SMOOTH fACE L~OI\INST SIIN.

ASSURE THAT N,suLoEs AnE )REKNT

VIEW C-C LOOKING UP AND FWD

Fiplrs 1´• Ihrf 2 ot 21

4 install new insulation on fuselage skin and frames in area above overhead Rwitch panel ~1Hine gC1403 Cement or

an equivalent Trun insulation upon instl,llatinn and assure no bulges are prelent (refer to Figure 1 or Figure 2)

Figure 1 is for Models 690C and 695 end Figure Z is for Models 6901) and 695A

5 HeinsLall overhead switch panel as follows:

CbUTION

I~en installing the overhead switch panel, ensure that all

wires and busaen are properly secured and iae not squoeledtowards airframe. This will prevent possible shortcircuita

a. Swingoverhead switch panel up and securewith exi~6ng attaching screws.

b Connect eleetrolumineacent panel wiring to airplane wiring and position penal for installation Stow excess

winng and ensure that wiring will net be pinched or crimped when panel is secured

c Secure electroluminercent panels with attaching screws. Tighten screws evenly to prevent warping of

panels

d Reinstall all eristingknobs and secure with existing ellen screws.

6 Fill out and mail Compliance Card

Page 1 of 6

8ERVICE LETTER NO. SIO

FUSELAGE SI(IN IREF)

NO. 414 TAPE

asn,lnaINSULATION

A

.CPCANTEDFR~MEIAEF)

8~2(21´•183 INSULATION

OVEHHPAD SWITCH PANEL (REF)WINDSHIELD

FRAME (REFI

882121´•159 INSULATION 88212(´•185 VINYL

VIEW LOOKING INBD FROM LEFT SIDE

882121-181 INSULATION802121181 INSULATION E BOND WITH 801483 CEMENT

BOND WITH rc~un CEMENT88211(´•181 INSULATION

BOND WITH 801403 CEMENT

TRIM TO MATCH FRPIME

882121´•157 INSULATION ANDCUTOUT

BOND WITH 501403 CEMENT8~2121´•188 INSULATION

BOND WITH 801403 CEMENTEXTEND TO FRPIIE

~UNCTIONITYP) VIEW A-A

LOOKING FWD AT WINDSHIELD FRAME

8LITASREODFORWIREOR STRUCTURE ITYP) e 882121181 INSULATION

(REFI

882(2(´•183 INSULATIONBOND WITH EC(~03 CEMENT

EXTEND TO FRAME

Juacnw(nPI VIEW B-B

LOOKING AFT AT CANTED FRAME

MODELS 6900 AND 695Pl Flgunl. (91rt 1 ot 21

ppge 6 916

__

8ERVICELETI~ERNO.SIO

BB21ZI´•ISSVINYL INSULATION

8~2121´•183 INSULATION(REF) 882121´•183 INSULATION

(REFI

88212(´•(63 INSULATION

882121´•18( INSULATIONUSE NO. 414 TAPE TO INSTALL IREFI

882121´•163 AND ´•184 INSULATIONAND8~2121´•(S6YINYL 882121´•(87 INSULATION

IREFI

NOTE

TRIM ANO INSTALL INSULATION WITH

SMOOTH FACE AGAINST FUSELAGE SI(IN.

ASSURE THAT NO BULGES ARE PRESENT.

VIEW C-C LOOKING UP AND FWD

Fplln 2. (9H*f at 2)

ELECTFIIOALLOAO: NOCHANGE.

WEIOHTANDBILP~NCE: NOCHANGE.

SPARESAFFECTED: NO.

PUBLICATIONSAFFECTED NONE.

RECORDCOMPLIANCE: Make and appropriate entry in eirplanemaintenanoereeords as follows: arvies Letter Na. SSO,

dated 15 April 1882, entitled"Cookpitlnsulation Overhead Switch Panel", aeeompliahod (date)

Page B ol 8

Service Lettev GulfstreamAmerican

Commanda DivironSW( North Roc~rmll nvsnua.Bethlny. OXlahoma 13M8


17 June 1882

PARKER HANNIFIN CORPORATK)N PRODVCT REFERENCE MEMO (PRM) NO. 27

MODELS AFFECTED: FACTORY APPROVED:MODEL 690A, SERIAL NOS. 11198 THRU 11944.MODEL 690B, SERIAL NOS. 11850 THRU 11566.MODEL 690C, SERIAL NOS. 11800 THRU 11667, 11689 THRU 11709.MODEL 69011, SERIAL NOS. 15001 THRU 15004 AND 15006.MODEL 696, 8ERUAL NOS. 80000 THRU 96049, 96051 THRU 98084.MODEL 695A, SERIAL NOS. 96001 THRU 96050 AND 98052.

STC APPROVED:MODELS 660F, 6808, 680FL(P), 680T, 680V AND 680W, SERIAL NOS. 871 THRU 1850.MODEL 681, SERIAL NOS. 6001 THRU 6012.MODELS 890 AND 690A, SERIAL NOS. 11001 THRU 11194.

NOTE

ALTHOUGH THE MODEL 690B 18 NOT LISTED ONPARKER HANNIFIN CORPORATION PRM NO. 21, IT ISRECOMMENDED THAT THE REWORK BEACCOMPLISHED ON THE MODEL BB0B.

THIS 8ERVICE LET~ER APPLIES TO CLEVELANDBRAKE ASSEMBLY Pi~ 50-107 AND SO-107A WITHMANUFACTURERS DATE PRIOR TO APRIL 1982.

REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH PARKER HANNIFIN CORPORATIONPRODUCT REFERENCE MEMO (PRM) NO. 21.


MOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE LE~ER, CONTACTYOUR NEAREW GULFSTREAM COMMANDERAUTHORIZED SERVICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A 8. P MECHANIC 08 E9UIVALENT.


ESTIMATED MAN HOURS: ONE(1)HOUR.

PARTS DATA: PARTS RE9UIRED TO COMPLY WITH THIS 8ERVICE LE1TER, FOR FACTORY APPROVEDINSTALLATIONS ONLY, MAY BE PROCURED THROUGH YOUR NEAREST OULFSTREAM COMMANDERAUTHORIZED SERVICENTER FOR 86.79. A FULL CREDIT WILL BE ISSUED UPON RECEIPT OF OLD FITI~INOPIN 104-0(1200,A PROPERLY EXECUTED WARRANTY CLAIM AND A COMPLIANCE CARD. REFERENCE THISSERVICE LETIER AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN OI(DERIND SERVICE LETI~ERNO. 911 KIT CONSWINO OF THE FOLLOWING:

Page 1 of 2


WOTE

PRIOR TO ORDERING PARTS, 8EE STEP (a) OF PRM NO.27. PARTS FOR 8TC APPROVED INSTALLATIONS MUSTBE PROCURED FROM PARKER HANNIFINCORPORATION, AIRCRAFT WHEEL AND BRAKE

DIVISION, P.O. BOX 158, AVON. OHIO 44011.

CITY PART NO. DESCRIPTION

2 ea 104´•04800 Fitting2ea. 101-24600 O-Ring1 ea. Compliance Card1 ea. Servioe Letter No. 961 Instructions

SPECIALTOOLSc NONE.

ACCONIPLISHMENT INSTRUCTIONS:

1. Comply with Parker HsnniF~n Corporation Roduet Reference Memo No. 21.

NOTE

If brake assembly nameplate is missing or date an nameplateis unreadable, it is reoommended that this rework be

aecomplished.

2. Fill aut and mail Compliance Card.


WEIGHT AND sALANCE: NO CHANGE.

SPARES AFFECTED: All SO-101 and 30-107A brake assemblies in spares.tock, wit nameplates dated prior to April1982, must be updated to comply with PRM No. 27 and so noted.

PUBLICATIONS AFFECTED: The Illustrated Parts Catalog ohange required by tbis dooument will be inoorporsted atthe neat aehsduled revision.

RECORD COMPLIINCE: Make an appropriate entry in airplane maintenance records as follows; Service Letter No.351, dated 1? June 1982, entitled "Parker HanniBn Corporation Product Referenos Memo (PRM) No. 21", aeeomplished

(date)

PageBofP

0)(0

PRM No. 27 L982

AIRCWLFT APPL’ICABILITY: Gulf stream American or Rockwell, CommanderModels: 560F, 680F, L80fL (P), 680’1, 680V,680W, 681, 690, 690A, 690C (840), 6900 (900),695 (980) 6 695A (1000); chose equipped withCleveland Brake aasembly 30-107 or 30-107A

Within the next 100 hours perform the following:

(a) Check each brake nameplate. If the manufacturing date is3-82 or earlier, proceed to (b). If the date is 4-82 or

later, the inspection is complete and no further serviceneed be performed per this PRM. (Make logbook entrystating such)

(b) Disconnect and cap hydraulic line at the brake inlet.

(c) Remove existing brake inlet fitting, part number 10460200.

(d) Install new inlet fitting, part number 104-04900 and o-ring(part number 101-24600 for 30-107 end parr number 101-23000for 30-107A). The new fitting is a straight thread to

flare tube end connector. Asau´•re that the straight threadland o-ring) is installed into the brake cylinder with theflare tube end out.

(e) Connect hydraulic line to the brake inlet.

(f) Bleed the brakes. While doing so, check for free flow

through the bleeder. (15 solid stream flow through the

bleeder cannot be reached, then disassemble that brake and

inspect for fluid passageway restrictions. Repair as

needed),

(g) Make a logbook entry showing compliance to PRM 1127.

Parker Hannifin CorporationPlircraft Wheel and Brake DivisionP.O. Box 158 Avon, Ohio 44011 USA

(216) 9345221

~AerospacePD((84´•618 iJj

~111Service letter CulfstreamAmeri~an

CDRMII*TION

Comm´•ndn Dhllon6001 NPllm Rm~*a(l ~vanus.Bsmany´• O*lah~ma 1)006


SO duly 1982

FUEL CELL INTERCONNECT HOSE REPLACEMENT

YODELS IFFECTED: THE FOLLOWING MODELS THAT HAVE FACTORY INSTALLED LONG RANGE FUEL

8YSTEM OR HAVE MODIFIED FUEL 8YSTEM PER CUSTOM KIT NO. 152:

MODEL 6W0C, SERIAL NOS. 116M) THRU 116&1, 11668 THRU 1168?, llBsB THRU 11703,11108 AND 11118 THRU 11?21.

MODELB80D, SERLAL NOS. 16002 THRU 15004, 16008, 15008, 16008, 15011 AND 15012.

MODEL 686, SERIAL NOS. B6WO THRU 85049 AND 86061 THRU 86084.

MODEL 886~, SERIAL NOS. 06001 THRU 86058, 86051, 86038 AND 86040.

REASON FOR P(IBLICATION: FUEL INTERCONNECT HOSE MAY BE SU&IECT TO EXCESSIVE SWELLING

AND EVENTUAL DETERIORATION.

COMPLIANCE: DURING NEXT lOO-HOUR INSPECTION.

IIOTe


COMPLYING WITH THIS 8EI(VICE LFFTER, CONTACT

YOUR NEAREST OULFSTREAM COMMANDER

AUTHORIZED SERVICECENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A 81 P MECHANIC OR EQUIVALEIIPP.

ESTIMATED MAN HOURS: UPON COMPLETION OQ AIRPLANE DEFUELINO, THE REWORK WILL TAKE

APPROXIMATELY ONE AND ONE-HALF (1.5) HOURS.

PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LF~1TER. MAY BE PROCURED

THROUDH YOUR NEAREST aULFSTREAM COMMANDER AIPDIORIZED SERVICENTER FOR (2.41.

REFERENCE THIS 8ERVICE LETTER,AIRCRAFI~ MODEL AND *ACTORY SERIAL NUMBER WHEN ORDERING

SERVICE LE~ER NO. 862 KIT CONSISTING OF THE FOLLOWING:

nlclllulusnmcHI~HlsvrmM*oma

cm PARTNO. DEBCRIPI~ION

2es. 880082-1 ~saket

2sa. 650384-81 H~ae

1 as. Compliancs Card

1 as. Service Iatte~ Ne. 552 Instruotiana

P~e 1~3

S´•u

8:

LIERVICE LETTER NO. 952 ip~i

d"

Remove mEsE

Bnccl~ooolr

CENTER WIN(I

24.00 (REP),,WS E FUEL CELL

AFT INBOARD ICFT FUEL CELLFUEL CELL (REF)

C‘j I ~i C::

INTERCONNECT489Y IREFI

INTERCONNECTPSSY IREF) ABSY IREF1 INTERCONNECT

ASSY (REr)(DOS8CIl NOSE IN~TALL 69038451 NOSE

USING EX18TIN(I CLL~MPS USING EXISTIN(I CLI\MPS

VIEW LOOKING DOWN AT FUEL CELLS

Fi~un i.

P´•galofS

BERVICE LETlEE NO. 362

SPECIAITOOL9: NONE.


1 Defuel airplane as outlined in Chapter 28 ofWe Airplane Maintenance Manual.

2. Remove leR and right inboard sR wing access doors to gain access to fuel interconnect hoses (refer to Figure

S. Remove and discard existing fuel plate gasket (Pn~ 6500821).

4. Remove damps and discard existing left and right hud intermnnect hoses (Pi~ 690584-55) (refer to Figure i).

6. Lubricate the new interconnect hose (Pi~ 65058451) with fuel or soap and water and install hose on

interconnect assemblies using existing clamps. Torque clamps to a value of 10 to 15 inch-pounds (refer to Figure

6 install new plate gasket (P~ 650082-1) and reinstall Be wing secess doom and seal with 880B-112 or equivalentMIL-9-8802 sealant per Chapter 51 of the Airplane Maintenance Manual.

7. Torque access door screws to a value of 20 to 26 inchpounds.

8. Refuel airplane as outlined in Chapter 12 of the Airplane Maintenance Manual.

g~ Fill out and mail Compliance Card.



SPARES AFFECTED: All hose P~ 85038455 mlaoL in color) must be removed from spares stock.

PUBLICI\TIONS AFFECTED: The Illustrated Parts Catalog change required by this document will be incorporated at

We next scheduled revision.


562, dated SO duly 1882, entitled "Fuel Cell interconnect Hose Replacement",

p~ 5 of S

Service Letter CulfstreamAmericanconroa*rl~,r

Commansr Divllion

5001 North Ausnu´•.

_

Bamnny. OLI´•Doma ~3W8

SERVICE LE?TER NO. 363

3 September 1982

FLIGHT CONTROL CHAIN CONNECTOR LINK INSPECTION

MODELS AFFECTED: MODELS 500, 600A, 600B, S00U, 520, 560, 560A 660E, 660F, 680, 680E, 680F, 680F(P),

680FL, 680FL(P), 680T, 680V, 880W AND 720, SERIAL NOS. 1 THRU 1354.

MODEL 6005, SERIAL NOS. 1166 THRU 1816 AND 5050 THRU 3323.

MODEL 681, SERIAL NOS. 6001 THRU 6072


MODELS 690, 690A AND 6908, SERIAL NOS. 11001 THRU 11566.

MODEL 680C SERIAL NOS. 11800 THRU 11127.



MODEL BgSA, SERIAL NOS. 86001 THRU 86042.

REASON FOR PUBLICATION: TO VERIFY INSTALLATION OF FLIGHT CONTROL CHAIN CONNECTOR LINK,

PLATE AND KEEPER.

COMPLIP.NCE: DURING NEXT 100´•HOUR INSPECTION´•

NOTE


COMPLYING WITH THIS SERVICE LET~R, CONTACT

YOUR NEAREST QULFSTREAM COMMANDER


BY WHDM WORK W(LL BE ACCOYPLISHED: A d P MECHANIC OR EQUIVALENT.

AFFROVAL: FAA DOA SW´•2 APPROVED.

ESTIBP;TED MAN HOURS: TWO (2) HOURS.

PARTS DATA: CHAIN CONNECTOR LINK PIN #35 (CONTROL COLUMN) AND PIN IYPS (gLEVATOR AND

RUI)I]ER TRIM) MAY BE PROCURED THROU(tH YOUR NEAREST OUL~STREAM COMMANDER AUTHORIZED

SERVICENTER AS RE~UIRED.

SPECIAL TOOLS: FLASHLIGHT AND INSPECTION MIRROR.

ACCOMFL!SHMENT INSTRUCTIONS:

1. R.´•aove tail cone and remove left and right inspenion panels, located on an fusalage just below horilontal

s~rbilieer, to gain access to rudder and elevator trim control aprockets irefer to Figure i).

2. Using a flashlight and an inspection mirror, inspect all chain to cable connections on Ridder and elevator trim

controls to assure that plates end "keeped’ me installed and properly secured on all chain master lin~s (refer

to Figure Il.

3. If"keepars" are secured properly, proceed to step 6.

Page 1 oft


RUDDER TR(M TI\B

RUDDER TRIM

TAB INOICATOR

RuooEn mlM rae

NO. 26 MASTER LINK.PLATE AND KEEPER I? PLS)

TURNBUCKLES

LINK I ELEVATOR

KEEPER

ELEVATORTRIM TAR

NO. 25 MASTER LINI(.PLATE I\ND KEEPER (2 PLSJ

ELEVATORTRIMTAB

TRIM TI\B

INDICATOR TRI\NIMIT(ER

Fir" 1´•

Page 2014

SERYICE LETTER ND. 553

NO. JS

MASTER LINK. PLATE

FIND KEEPER

MODELS.W. 6W*. 5880. 600U. 5055. 520. ~14PL8)586 5561\. 5806. S)OF. 880 6555, 6586.

COVER ASSY NO. 35

(REF) MASTER LINK. PLATE

ANO KEEPER 12 PL6)

N0.96MASTER LINK, PLATE

ANO KEEPER 12 PLSI

CONTROL COLUMNLINK IREFI

KEEPER

MODELS 1IBOFL. BBOFL(P1, 056T. BB(IV.BIIOW. 881, 685, 850. 850/\, 8508. 8550,

COVER ASSY

NO.55MASTER LINK.PLATE ANDKEEPER 12 PLSL

CONTROLCOLUMNIRE r)


5163111 INSTPILIPITION OPPOllrl

Fipm 2.

Page 3 of 4


4 IF any "keeper" is missing from chain master link, install new X21, chain link assembly with plate and "keeper"and proceed to step 8.

6. Reinstall tail cone and inspection panels using existing hardware.

6. Remove cover assemblies from pilot and copilot control columns, as necessary, to gain access to chain assemblies


NOTE

On Models 600, SWh 6008, 600U, 6008, 620, 660, 660A,

660E, 660F, 680, 680E, 680F, 680F(P) and ?20, it will be

necessary to remove carpet and noor panels to gain secess to

control column chains below fuselage floor.

Using a nashlight and inspection mirror. impact all chain master links to assure that plates and "keepers" are

installed and secured properly (refer to Figure 2).

8. Lf"keepra" ansecured properly, proceed to step 10.

g~ If any ’keeper" is missing from chain master link, install new YS6 chain link assembly with plate and "keeper"and proceed to step 10.

10. Reinstall all access panels, cover assemblies and ca~peting.

11. Pill out and mail Compliance Card.





RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Latter No.

858, dated 8 September 1882, entitled "Plight Control Chain Connector Link Inspection", accomplished (date)

page I of 4

Sewice Letter CulfstreamAmericanroRvoa*rloh

Commands DIrlIlon1001 Norm RDi*IWII AYLnYe,Bathany, 73008


1 October 1982

MAIN LANDING GEAR WHEEL BEARING AND AXLE HOUSING INSPECTION

MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11721, 11726 AND 11727.

MODEL 690D, SERIAL NOS. 16002 THRU 15004, 16W6, 15008. 15009, 15013, 15014 AND

15016.


MODEL 695A, SERIAL NOS. 96001 THRU 86055, 96037 AND 86039 THRU 96042

REASON FOR PUBLICATION: POSSIBLE CONTAMINATION OF AXLE GREASE WITH METAL SHAVINGS.

COMPLIANCE: DURING NEXT 100-HOUR INSPECTION.

NOTE



YOUR NEAREST CULFSTREAM COMMANDER


BY WHOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR E~UIVALENT.


ESTIMATED MAN HOURS: THREE (8) HOURS.

PARTS DATA: 1 EA. COMPLIANCE CARD.

SPECll\LTOOLS: NONE.


I. Jack si~lsne as outlined in Chapter 7 of the Airplane Maintenance Manual.

2. Remove left end right main landing gear wheels as outlined in Chapter 32 of the Airplane Maintenance Manual.

8. Thoroughly clean and inspect wheel hubs and wheel bearings as outlined in Chapter 32 of the AirplaneMaintenance Manual.

4. Assure that any contaminants are removed from inside the axle housing.

NOTE

The use of a magnetic probe and solvent Rush will facilitate

contaminant removal.

5. After assuring that wheel hubs, wheel bearings and anles are satisfactory, repack bearings and reinstall wheels

on airplane as outlined in Chapter 32 of the Airplane Maintenance Manual.

6 Fill out and mail Compliance Card.


WEIGHT IND BALANCE: NO CHANGE.

Page 1 of2

SERVICE LETI~ER NO. 364


PUBUCATIONS AFFECTED: NO.

RECORD COMPLI~NCE: Make an appropriate entry in airplane maintenanee reeords as follows: Service Letter No.

584, dated 1 October ~882, entitled "Main Landing Csar Wheel Bearing and A~le Inspection", aeeomplished

(date)

Page 2 of 2

Service Letter GulfstreamAerospace


SO November 1Bsa

FUSELAGE STATION 386.82 SCREW TORCUE INSPECTION

MODELS AFFEOTED: MODELS 880, 080A AND 8O0R, SERIAL NOS. 11001 THRU 11688.

MODEL 0800, SERIAL NOS. 11800 THRU 11?21, 11126 AND 1112?.

MODEL BBOD, SERIAL NO8. 18001 THRU 16004, 16008, 16008 THRU 16011 AND 16014.


MODEL OOOA, 8ERIAL NOS. 88001 THRU 8009? AND 88058 THRU BBOM

REASON FOR PUBLCAT1ON: TO ASSURE THAT SCREWS ATTI\CHINCI ANGLES TO FRAME ARE TORQUED.

COMPLIANCE: DURMQ NEXT 100-HOUR INSPECTION.

MOTE


COMPLYING W1TH THIS SERVICE LETI~R. CONTACT

YOUR NEAREW OULPEITREAM COMMANDER

AUTnORIZED81ERVICENT&R.

sY WHOM WORN WILL Be CICCO~PLISHED: A P MECHANIC OR

APPROVAL: ENGINEQRIND DEBION ASPECTS ARE: PILA APPROVED.

ESTIMATED BAN HOURS: MODEL11880, 080A AND 880B TWO (2) HOURS.

MODEL 880C, SERIAL NOS. 11800 THRU 11118 EIGHT (8) HOURS.

MODEL 885, SERIAL NO. 86000 THRU 96084 EIGHT (8) HOURS.

MODEL 685A, SERIAL NOS. 96001 THRU 88018 EIDIIT (8) HOURS.

MODEL BB0C; 8ERIAL NOS. 11118 THRU 11721 ONE (1) HOUR

MODEL 080D, SERIAL NOS. 16001 THRU 15014 ONE (1) HOUR.

MODEL 886A, SERIAL NOS. 88018 THRU 88048 ONE (1) HOUR,

PARTS DATA: 1 EACH COMPLIANCE CARD.

8PECIALTOOL9: TORqUE WRENCH.

ACCOMPLISHMENT INSTRUDTIONS:

I. Cain aacesa to fuselage ti~ams at station 880.82.

2. Assure that a ANBBO-1OL washer Is installed between the angle and fiane on both left and right lower inboanl

attaching screws (refer to Figure Il.

S. Tonpe existing four (4) lower screwsthat attach 8300a4´•16 and -18 angles to Rama to a torque value of 20 to

26 inch-pounds plus running torque (refer to Figure 1).

NOTC:

Running torque i the tonpa that is required to run the nut

upon the screw threads.

Page 1 of 2

BERVICE IET~R NO. 968

1. On Model BsOD and BRSA only, torque the hKo (2) upper anaws that attach 81M12C15 and -18 angles to irame

to a taque value ,f 50 to ?0 inch-pounds plus NMing torque (,r, t. Figure 1).

6. On all other models, torque the tare (2) upper screws that attach 810024-16 and -18 angles to Rama to a toqua

value of 20 a a6 inch-pounds plus running torque (rafar to Figure 1).


ILECTRICILLOID: NOCHANOE.

WEI(IH~ANDB*UNCE: NOCHANOE.

SFARIS AFFECTED: NO.

FUILICATK)NS AFFECTED: NONE.

RECORD COMPLI*NCE: MsLs an appropriate entry in airplane maintenance records as follows: Service Letter No.

556, dated 80 November 1882, entitled "Puwlaga Station 888.82 Screw Tor~Lue InapaWon´•’, acmmpliahsd

ronour: scnm sLS)(REFER m 8ssp nNo 6.1

ExlsnNa ad?c~snNGLE

ExlsnNo aoa2clsPINGLE IREF)

d

roBoUE 8cnEw*PLS)20 TO ?B IN´•LBS PLUSRUNNING TOA(IUE

PSSURE TnAT WgBa(OL WI\(UIERIs IN(ITI\LLED BETWEEN PNGLE

FIND FRPIME, P~LSPI\CER. FOR

THELIE mo (21 ihleonno scREws

FMELIPBE 8T~TION 38B82FAPIME PSSY

Fi~un

page 2 012

Service Lettev GulfstreamAerospace

SERVICE LE~TER NO. 356

25 Februarp 1983

PNEUMATIC TUBE ASSEMBLY INSPECTION

MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11721, 11723, 11126 AND 11727.

MODEL 690D. SERIAL NOS. 15001 THRU 15004, 150O6. 15008 THRU 16011, 15014, iSOiB,

16021 AND 1j022.

MODEL 695, SERIAL NOS 95000 THRU 95084.

MODEL 695r\. SERIAL NOS. 96001 THRU 96053

REASON FOR PUBLICATION: TO ASSURE THAT NO INTERFERENCE EXISTS BETWEEN PNEUMATIC TUBE

ASSEMBLY AND TOR9UE LIMITING TRANSDUCERIN RIGHT NACELLE

COMPLIANCE. WITH NEXT 100 HOURS TIME IN SERVICE.

NOTE

´•I:l´•i´•a´•: i

1F ANY PROBLEMS ARE ENCOUNTERED WHILE

COMPLYING WITH THIS SERVICE LETTER. CONTACT

YOUR NE*RTSP UULrSTREIM CoMMANDER

AUTHORIZED SERVICENTER

sY WHOM WORK WILL SE ACCOMPLISHED A P MECHANIC OR E~UIVALENT.

APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED

ESTIMATED MAN HOURS: INSPECT TUBE ASSEMBLY THIRTY (301 MINUTES

ROTATE TRANSDUCER ONE AND ONE-HALF(1 51 HOURS

:i-

PARTS DATA: i EACH COMPLIANCE CARD.

SPECIAL TOOLS: NONE


1 Remove forward access door from top of right nacelle to gain access to torque limiting transducer. The words

TOR~UE LIMITING should be stamped above tol´•que limiting transducer on engine fll´•ewall trefer to Figure ii.

2 inspect far possible interference between torque limiting tmnsducer and pneumatic tube 8´•~embt:

3. If no interference exists between torque limiting transducer and pneumatic tubs assembly, reinstall access door

on nacelle and proceed to step 5.

4. If interference exists between torque limiting transducer and pneumatic tube assembly, proceed as follows:

a. Remove upper cowling rom right engine.

b. Disconnect the pressure and vent lines from their respective Rttinga on the torque limiting transducer I

c. Disconnect electrical connector from transdueer

C d Remove nuts and washers that secure torque limiting transducer to engine fire\rall.

As Reecivod ByAIP j

,a~.._

...~_.,.i.

-C

SER\’ICE LETTER NO. 356

I cavnm~lCAUTION

Be careful not to damage threads on fittings when pullingtransducer through engine Brerall.

Remove tal.que limiting tran.ducer from engine firewall

F Slot torque limiting transducer mounting holes in engine firewall, as necessary, in order to rotate

tmnsdueer to clear pneumatic tube assembly

g Reinstall torque limiting transducer on engine Fnewali using enisting washers and nuts,

h. If any gaps are left in engine flrewali after transducer is reinstalled, seal around washers and nuts with

Pro-seal 700 firewall sealant or an equivalent sealant.

Reconnect pressure and vent lines to torque liwting transducer assuring that lines are connected to the

plaper Bttings.

j. Reconnect electrical connector to transdueer.

k StR1´•t right engine as outlined in Pilot Operating HandbooB and assure that no lealis are evident at

rorque limiting transducer connections,

I. Shut down right engine.

m Reinstall upper eowling an right engine

n ,instsll ar..aa do~i un nar~lla C5 Fill out and mail Compliance Card.

ELECTAICAL LOAD: NO CHANGE,

WEIOMT AND BALANCE: NOCHANGE.

SPARES nFFECTED: NO.

PUBLICATIONS PIFFECTED: NONE.

RECORD COMPLIANCE: Malre an appropriate entry in airplane maintenance records as follows: Service Letter No

356. dated 25 February 1983, entitled Tube Assembly inspection, accomplished Idate)

REMOVE THII MCESS

9DOOR TO EXWSE TOR(IUE

LIMITING TR~NSDUCER

COWLINO IREFI 8UPPER ENGINE

(REFINI\CELLE

As Roc,ived Byi A’" i:Bigure i.

’"5:

Page 2 of 3

1.._..~

I_

Senrice Letter CulfstreamAerospace

SERVICE LETTER NO. 3S7A

NoSI? mifa ´•ntu,m I4 November 1983

AILERON LEADING EDGE SKIN MODIFICATION

MOOELS AFFECTED: MODEL 890C, SERIAL NOS. 11800 THRU 11884 AND 11866 THRU 11721, 11723, 11726

AND 11127.(SEE NOTE).MODEL 69011, SERIAL NOS 15001 THRU 15006, 15008 THRU 15011, 16014, 16016 AND

15018

MODEL 695, SERIAL NOS. 95000 THRU 95084. (SEE NOTE).

MODEL 695A, SERIAL NOS. 86001 THRU 96037, 96039, 96040, 96042, 96044 THRU 96052.

NOTE

FOR MODEL 690C, SERIAL NOS. 11600 THRU 11666

AND MODEL 695, SERIAL NOS. 85000 THUR 95063,

SERVICE BULLETIN NO. 118A MUST BE ACCOM-

PLISHED LN CONJUNCTION WITH THIS SERVICE

LETTER IF NOT ALREADY ACCOMPLISHED

IF BASIC SERVICE LETTER NO, 557 HAS BEEN

ACCOMPLISHED, DISREGARD THIS SERVICE LET-

TER.

REASON FOR PUBLIC~TION: POSSIBLE CRACKS IN AILERON LEADING EDGE SKINS 1N AREA AROUND IN-

BOARD BALANCE WEIGHT ATPACHINO SCREW HOLES.


NOTE


COMPLYING WITH THIS SERVICE LETIER, CONTACT

YOUR NEAREST GULFSTREAM COMMANDER AU-

THORIZED SERVICENTER.

BY WHOM WORK WILL BE ACCOMPLlsHEO: A d P MECHANIC OR EqUIVALENT.


ESTIMATED MPIN HOURS: PART I INSTALL ANOLES- NINE (8) HOURS.

PART II INSTALL ANGLES AND DOUBLERS ELEVEN (11) HOURS.

PARTS DATA: PARTS RE~UIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGH

YU~ Ns*sE9P OULVCI.I.IU MM.~NWR IMrm~adD SBRYICINIBO FO~ ILB~ hlilillllNPli THI ISERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LETI~ER

NO 367A KIT CONSISTING OF THE FOLLOWING:

Page 1 of?

SERVICE LETTER NO 357A

qTY PART NO. DESCRIPI~ION

86 se. 250006´•RE3 Washer

1 ea. 2500(15-RE6 Doubler

1 ea. 2600(15-REll Doubler

2 ea. 260038-603 Angle1 as. Compliance Card

1 as. Service Letter No. 351A instructions

SPECIILTOOLS: HOLE FINDER

PICCOMPLISHMENT INSTRUCTIONS:

PART I

r EnurloN

When removing leR ailemn, oars should be taken to assure

that aileron trim tab actuator electrical cable is not broken

ordamaged.

i. Remove left and right ailerons as follows:

LIOTE

Do oot change the position of rad end an push-pull rod.

a. Disconnect aileron push-rod at aileron.

b Remove aileron hinge bolts and attaching herdwere.

c. While holding left sileron up, remove four screws that attach cannon plug secess plate to inboard end

of ailemn. Remove plate from aileron and disconnect trim tab actuator cannon plug.

d. Remove ailemn from airplane.

2 Remove inboard leading edge access doors from ailemns.

3. Inspect aileron leading edge skins in area around inboad balance weight attaohing screws. If no crac~s are found,

proceed to step 5.

4. If cracks are found in leading edge skins and are less than 0.50 inch long and a maximum of two (21 cracks per

hole, proceed to Part II. If cracks are longer than 0.50 inch and three (3) or more cracks per hole, contact

Gulfstream Commender ServiCenter, Bethany, Oklahoma before proceeding any further.

5. The following procedures apply to both left and right ailerons:

NQTF:

This modification dae~ not require rebalance oEailerons.

a. Remove screws attachinginboard balance weight to aileron leeding edge skin and remove balance

weight.

i

Page a of

8BRVICE LETTER NO. 35?A

alvrrll.rrsl

IN8laillsooosRr~wasNEnNnslnes4srlNo

UNDER SCREW HEAD U3 PLS1

Ij IOUTBD)12 E(1. SPACES

-tir 0.31´•´•

ACCESSOOOR

InEFI Ui~lLlt:t’:

I\ILERON

VIEW LOOKING DOWN R.H. AILERON-- ST"’gZ´•~

STA 115.31 EXISTING SCREWSIREFI EXISfINGGANG

CHANNEL IHEF)

WASHER IREFI

EXISTINGWEIGHT IREFI

260038803

NASIl3S84 BLIND

RIVET IREFIVIEW B-B

IF THIS ANGLE IS INSTALLED ON AlLERON,REFERTONDTEUNDEA8TEPSbOFPARTL

~II ne~dsDa)l

RIYET113 PLSI IREFIUNDER SCREW HEAD 143 PLSI

A

0.31´•´•-I- -I- f ´•i-+

AILERON VIEW LOOKING DOWN L.H. AILERON AILERON

STI\. 182.85 STA. 171´•31

EXISTING 8~LANCE SCREWS IREFI

WEIGHT IREF)

EXISTING GANG a WASHER IREFI

CHANNEL IREF)260039-6(15 ANGLE

VIEW A-A k NAS173BB4BLIND RIVET

IRE FI

IF THIS PINGLE IS INSTALLED ON A\ILERON,

REFER TO NOTE UNDER STEP S.b OF PART I´•

Figu~s i.

Page 3 of

SERYICE LE1TER NO 367A

b TsP~orarill iuefall s´•iatinp b.l´•nra ui.lht ad 210a8-~U3 angle on eilua~ ua~ng nia8n. nar~

and gang channel. Install a 250(105-RES washer under each screw head and tighten screws (refer to

Figure 1).

NOTE

If an angle has been added to aileron akin in area where

250039´•5~3 angle is to be riveted to akin, remove the angleand install 250039-509 angle with existing screws through

weight only. This angle was added to prevent oil canningon some ailerons. If edge of 260099-503 angle laps over any

one of the rivet holes in aileron skin more than half way,

trim nange of 260039-603 angle, assuring that an edgedistance of O.PSlnch can be maintained when riveting250039-605 angle to silsmn skin. Plug open holes usingNAS1738B4 blind riusta. If an edge distance cannot be

maintained, contact Culfstream Commander BsrviCenter

for further instructions.

c. Lacab and drill thirteen (13) 0.144 inch diameter holes through aileron skin and 250039-503 angles


d. Remove balance weight and 250039-503 angles from aiieran and deburr all drilled holes

a. Reinstall e.isting balance weight and 250099-503 angles on aileron using existing aerews and gang

Ie Attach 250039-603 angles to aileran skin using NA81738B4 blind rivet (13 places) irefer to Figure 1).

channel. Assure that a 260005´•RE3 washer is installed under each screw head (refer to Figure 1).

~m.us and runrsll oil s~vq onsate~ a remainin..ilaron landing algo balenta aslghta and

install a 25(1005´•RE3 washer under each screw head (refer to Figure 1).

h. Install a 250005-RE3 washer under each screw head on aileron access dam balance weight.

6. Touch up paint on ailerons as required

7. Rainatall left and right ailerons an airplane as follows:

a. On left aileron, reconnect trim tab actuator cannon plug and reinstall secess plate on inboad end of

aileron using existing hardware.

b. Position aileron for attaching to airplane.

c. Install aileron hinge bolts and attaching hardware.

d. Connect sileron pushpull rod at aileron.

e. If push-pull rod length has been altered, streamline trailing edge of opposite silemn with trailing edge

of wing and outboard nap and secure aileron.

f A4iust push-pull rad length to align attaching bolt hole with hole in aileron hinge fitting when aileran

is in neutral position.

3. Reinstall access doors on ailerons.

9. Operate the ailerons thru their full travel and check UI assure that no interference exists between screw heeds

on aileron leading edge and wing close out skins.

LO. Fill out and mail Compliance Card specifying that Part 1 haa been aeeompliahsd.

Page ´•1 ol7

BIRVICE LE~ER NO 367A

i. If cracks in aileron leading edge skin are less than 0.60 inch Long (marimum of two (2) cracks per hole). stop

drill cracks using a No. 40 drill bit.

2. The following procedures apply to both lan and right ailerona:

NOTE

This modification does not require rebaianoe of ailerons.

a. Remove screws attaching inboard balance weight to ailsron Leeding edge skin and remove balance

weight.

b. Temporarily install e.isting balance weight, 260006-RES doubler (Ieft aileron), 250006-REll doubler

(right ailemn) and 250099-503 angles on ailemns using existing screws and gang channel. Install a N

250005-RE3 washer under each screw head and tighten screws (refer to Figure 2).

NOTE

If an angle has been added to aileron skin in area where

250098-605 angle is to be riveted to skin, remove the angleand install 250099-605 angle with existing screws through

weight only. This angle was added to prevent oil canningon some ailerons. If edge of 250059´•505 angle laps over any

one of the rivet holes in aileron skin more than half way,

trim nange on 260019605 angle, assuring that an edgedistance of 0.25-inch can be maintained when riveting250039-603 angle to aileron skin. Plug open hole, usingNA81138B4 blind riveb. If an edge distance cannot be

maintained, contact Culfstream Commander serviaonter

c. Locate end drill 0.144 inch diameter holes through aileron skin, doubler end angle (refer to Figure 21.

d. Remove balance weight, doubler and angle Bom aileron and deburr all drilled holes.

a. Reinstall existing balance weight, 260005-RE5 and -RE11 doublers and 250058-603 angles an ailemn

using existing screws and gang channel. Assure that a 250005-RE3 washer is installed under each

screw head (refer to Figure 2).

f Attach 260005-RES and -RE11 doublers and 260038´•503 angles to ailerons skin using NAS173BB4

blind rivets (refer to Figure 2).

g. Remove and reinstall all screws, one.ta_tims, on remaining aileron leading edge balance weights and

install a 2500(15-RE3 washer underBsrh screw head (refer to Figure 2).

h. Install a 260006-RE3 washer under each.crew heed on aileron access door balance weight.

3. Touch up paint on ailerons as required.

4. Roinstall left and right ailerons on airplane as follows:

a. On left aileron, reconnect trim tab actuator cannon plug and reinstall access plate on inboard end of

aileron using existing hardware.

b. Position ailemn for attaching to airplane.

c. Install ailsmn hinge bolts and attsohinghardware.

Page 6 of 7


AILERON ZSWOS´•REII INSTALL 250005-853 WASHER

1~11141- ´°OUBLT. UNO.RSCR.LIYe~)llUII.I

IBE(1. r--o.eo´•´•

i~i STA 18285

F

P:CA(STU~NERIITYP’i

rolanoa?rrmi %Fi3 EO. SPS:RIVET

ACCESS DOOR

IREFI

VIEW LOOKING DOWN R.H. AILERONEXISTINGSCREWS ZS0005´•RE(( DOUBLER(REF)

BLIND RIVET IREF)

WASHER IREFIZbW39WIANOLE

EXISTING BALANCEWEIGHT IREF)

0.31~’

EXISTING GANG

NAS1138B4 BLINd I I\ CHANNEL IREFI VIEW A~A

RIVET (REFI

IF THIS ANGLE IS INSTALLED ON AILERON

REFER TO NOTE UNDER STEP 2.5 OF PART li´•

INSTALL 250006-853 WASHER I\ILEAON

UNDER SCREW HEAD (~J PLS) NAS113880 BLIND STA. 176.312501105´•RES RIVETDOUBLER

O.BO’~

15 EO.ACCESS DOOR

IREFI

GOYI~TRUE

-I- i- I- r t

PICK UP EXISTING3 EO. SP. I -I iti L FASTENERS ITYP

~0´•31´•´• 12 EO. TOP AND BOTTOM)

r

AILERON~-I VIEW LOOKING DOWN L.H. AILERON57/\. 182.85 EXISTING BALANCE

WEIGHTSCREWS IREF1

NI\S1138B4 BLIND 2600DS´•RE3WASHER IREFIRIVETIREF)

10005´•RES

DOUBLER IREFI 250038-S03~NGLEEXISTINGCHANNEL IREF)

VIEW 8-B

IF THIS ANGLE IS INSTALLED ON I\ILERON.BLIND RIVET

REFER TO NOTE UNDER STEP 2.5 OF FART II

I InaFI

FigYISZ´•

Fags O ol

BERYICE LET~ER NO. SS’iA

d Connect ailsmn pul´•pull rod at aiieron.

e´• If PUsh-PULI rod length has been altered, streamline trailing edge of opposite aileron with trailing edge

of wing and outboard nap and secure aileron.

f A~ust push-pull rad length to align attaching bolt hole with hole in aileron hinge fitting when aileron

is in neutral position.

5 Reinstsll secess doors on ailerone.

6. Operate the ailerons thru their full travel and check to assure that no interference exists between screw heads

an aileron leading edge and wing close out skins.

Fill out and mail Compliance Card specifying that Part II has been accomplished


WEILIHT AND 8*LANCE: NO CHANGE.

SPI\RES AFFECTED: NO.

PUBLICI\TIONS AFFECTED: NONE.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance record, as follows: Service Letter No.

357A, dated 4 November 1985, entitled "Aileron Leading Edge Skin Modification", Part 1 accomplished I

(dste) Part II accomplished (date)

Page 1 of 7

9 Service Letter CulfstreamAerospace


25 April 1883

OXYGEN MASK DISPENSER LID GASKET INSTALLATION

MODELS AFFECTED: MODEL 690C. SERIAL NOS. 11721 THRU 11?2?.

MODEL 690D, SERIAL NOS. 15001 THRU 16014, 15016, 15018, AND 15021.


REASON FOR PUBUCATION: TO ASSURE AUTOMATIC OXYGEN MASK DEPLOYMENT.


NOTE


COMPLYING WITH THIS SERVICE LE1TER CONTACT



BYWHO.W~RIWIU.E*CCOMPLIBHED: I\LPMECH~NLC oRB9UIVhLENT.

APPROVAL: ENGINEERING DESIGN ASPECTS ARE ~AA APPROVED.

ESTIMATED MI\N HOURS: TWO (2) HOURS.

PARTS DATA: MATERIAL RE~UIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED

THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR $12.80.REFERENCE THIS SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING

SERVICE LETTER NO. 358 KIT CONSISTING OF THE FOLLOWING:

P~´• ´•Ygl~ mllp´•lllh~yl n*i~´•

qTY PARTNO. DELICRIPI~ION

14 ft. 1/8" i~ l/d" Poiyfoam hesaure Sensitive Tape1 se. ComplianeeCard1 ea. Service Letter No. 358 instruotions



Tc~CAUTION

CARE SHOULD BE TAKEN TO PREVENT SOILING OF

VINYL FABRIC ON DISPENSER LIDS AND

HEADLINER WHILE ACCOMPLISHING THIS SERVICE

Page 1 of I


7

OXYGEN DISPENSER

(REFI

_t

O

iiINP)

1A"X 114~ WLYFO~MTAPE I’) PLI1

LID FOR DUAL

MASK DISPENSER

IREFL

_t

a.lr´•IrvPI

LIO~FR.NOL.

IREFI

VIEW A-A

Fisurs i.

Page a ol 6

8BRVICE LGTTER NO. 558

I YIIYIYO)Stow lanyzrd card and tubing so that neither one is entangled or

under any lanyard valve. latch mechanism or device within the

container that would prevent it from falling properly when de-

ployed.

MOTE

Remove lonyard pin before starting to told the mask to make It

easier to fold.

8TEP 1; RESERVOIR B~O´•FIAST FOLD 8TEP 2: RESERVOIR BAB´•SECOND FOLD

CLIP ATTACHMENT HOLE

3,

STEP 3; RESERVOIR BP~(1´• THIRD FOLD STEP 4; FOLD RESERVOIR BA0 AWAY FROMMASK SPRING CLIP ATTACHMENTnOLEINOOUBLEFOLD.

STEP 8: TURN MASK OPEN SIM UP AND STEP 8; BRING FOLDED REBEBVOIR Bn(lFOLD HEADSTRAP INTO FACE UP OVER 8108 OF FACE PIECE ANDPIECE. PLACE INSIDE IN DOUBLE FOLD.

wort

DO NOT I(INK THE TUBE WHEN FOLDINGFIEF I; WITH RE8ERVMR 81\0 FOLDED IT INTO MI\S~. ENSURE TUBE COIL MOE8

IN .i\er nscs, rmL maan ansv IN cllmNuoy. DIREETION PWM Y\.-TUBE ON FOLOED Bn(i. YARD VALVE OUTLET.

FILI?. IOhast(of 2)

Page 8 of 5


3AIRPLANES EOUIPPED WITH THE BENCH SEAT HAVE Pi DUAL MASK CONTAINER ABOVE THE BENCH. RESERVOIR BnOSSTORED IN DUAL CONTAINERS ARE FOLDED SAME ASIN G1NOLE MASK CONTAINER. NOTE ILLUSTRATION OF TUBEINSTALLATION IN SPRING RETAINERS.

g- ii

~i

STEP B; REINSERT LANYARD PIN

STEP g: PLACE MASK IN 8TORI\OE BOX WITH OPEN 811)6 OF Mn81( UP (TOWARDS IOP OF CABIN) ANO CLOSE LID.

ENSURE HINGE PINS ON BOX LID ARE EN(IA(IED 1N PIN RECEPTACLES ON BOX INNER SURFACE WHEN

INsmLLINa LID. TO CLOSE LID. PUSH FIRMLY ON LATCH SIDE AND, 81MULTI\NEOUSLY. USING A POINTEDOBIECTSUCH 1\6~ BALLPWINT PEN OR HEAVY PAPER CLIP INSERTED THROUGH THE EYELETTED

P~OY..N(YWINLI ,LL O.TE.TL

Fl~ura 2. (8haet? of 2)

i. Lower lids on all passenger oxygen mask dispensers by inserting a thin pointed metal objeet, such as a heavypaper clip, in lid hole and push up. Lid should drop.

2. Clean inside surfaoe of lid in area where tape is to be installed.

S. Cut and install VR-ineh polyfoam pressure sensitive tape on inside surface of lids (refer to Figure i).

4. Repack oxygen masks and close dispenser lids (refer to Figure 2).

6. Perform a pound cheek of the passenger oxygen distributing system as follows:

a. Passenger oxygen switch shoi~ld he in AUTO position. Passenger oxygen mask module doors should not

open.

b. Turn passenger oxygen switch to ON position.

NOTE

All passenger oxygen mask module doors should open and

masks should drop out, held suspended by the lanyerd card

andpin.

c. Turn passenger oxygen switch to OFF position.

a and pin m ane Daal t~ prruu~ In ly~am b nllm d.or I´•1Ei~B in b.

Pnee(ofl

SEIIJICF. I.gTTER NO 3~H

5. Rspnl ra~gsn Mll´• ´•d E~K dig.nl.r lids in~ to rllM 21

7. Fill eat and mail Compliance Card.

ELECSRICAL LOAD: NO CHANCE.

WEIGHT ANO BALANCE: NO CHANCE.


PUBLICPITIONS *FF~CTED: NONE.

RECORD COMPLIANCE: Make an appropriahe entry in airplane maintenanee records as follows: Service Letter No. 958,dated 26 April 1988, entitled "Oxysen Mask Dispense. Lid Casket installation’: accomplished (date)

C

Page 5 ol I

C~IIService Letter GulfstreamAerospace


17 June 1083

FUSELAGE STATION 386.82 FRAME ASSEMBLY MODIFICATION

MODELS AFFECTED: MODEL 690C. SERIAL NOS. 11600 THRU 11651 PtND 11633 THRU 11729.



MODEL 69SA SERIAL NOS. 98002 THRU 96055.

NOTE

IT IS RECOMMENDED THAT SERVICE LETI~ER NO.

355 BE ACCOMPLISHED IN CONJUNCTION WITH THIS

SERVICE LETTER.

REASON FOR PUBLICATION: POSSIBLE CRACK IN VERTICAL LEG OF BRACE IPIN 310024-63) THAT

ATTACHES TO FUSELAGE FRAME.


.arr



YOUR NEARESL~ DULFSTREAM COMMANDER


BY WHOM WORK WILL BE I\CCOMPLISHED: A Be P MECHANIC OR EQUIVALENT


ESTIMATED MAN HOURS: MODEL 690C, SERIAL NOS. 11600 THRU 11631 AND 11633 THRU 11718 TWELVE (12)

HOURS.MODEL 695, SERIAL NOS. 95000 THRU 95084 TWELVE (12) HOURS.

MODEL 695A, SERIAL NOS. 96002 THRU 93013 AND 96018 TWELVE (12) HOURS.

MODEL 690C, SERIAL NOS. 11119 THRU 11729 THREE (31 HOURS.

MODEL 690D, SERIAL NOS. 15001 THRU 15024 THREE (31 HOURS.

MODEL 69SA, SERIAL NOS. 96014 THRU 96017 AND 96019 THRU 96055 THREE (3)

HOURS

PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LE~I‘ER MAY BE PROCURED THROUGH

YOUR NEAREST DULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 86.40. REFERENCE THIS

SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LE1TER

NO 369 KIT CONSISTING OF THE FOLLOWING:

PRICI TcI WITHOUT NOIICI

9TY PART NO DESCRIPTION

2 os. 310024-103 Gusset

2 ea. 310024´•105 Shim

L ea Complionce Card

I ea Service Letter No. 359 instructions

Page 1 of 6

SERVICE NO. 359

AREAS TO BE INSPECTEDAND MODIFIED

/kExlmNo 310024´•53

BRACE IREF)

d

VIEW LOOKING AFT

AT FUSELAGE STATION 386.82

Fipur´•l.

Page 2 ol 5

SERVICE LE~ITER NO. 359

MODELS 690D AND 695*

EXISTINGWEBIREF)

C-‘s~

"p,

EXISTING HOLES

Ms2o47oaoe RIVETS I I-LPC MSzM7aaol RIVETon on

1*6173888 BLIND RIVETS I IIl V ~I NAS1738B~ BLIND RIVET

310024´•103(IUISET

f+INSPECT

EXISTING HOLESCRACKS

MS20470ADB RIVETSORNAS(738BB BLIND RIVETS

IIrvPI

NI\S1738BB BLIND RIVET

EXISTINE MS2MIO~DB RIVET

310024´•53 OR

BRACE

IREF)

310029´•(05 SHIN

t EXISTING HOLEMSZMIOPIDB RIVETOR

NAS173888 BLIND RIVET

EXISTING FRAME

IREFI

VIEW LOOKING FORWARD

LEFT SIDE SHOWNRIGHT SIDE OPPOSITE

Figure Z. ISlsst i ol 21

Page 3 al 5


MODELS 690C FIND 695

EXISTINOWEB

IRE Fl

510024´•105GUSSET

EXISTINOHOLESMSZM70nOSRIVETS

ORMSZ0170AD4 RIVET

N~S115885 BLIND RIVETSORNAhl738klBLIND RIVET

INSPECTCRACKS

+t~

ExlsnNo HOLESMS2MIOI\DB RIVETS

EXISTINGOR

310024´•53 310021´•105 FHIMNAS173BB8 BLIND RIVETS

BRACE

(REFI IIRIVETS

I)

1 ITYPIPPVO~; ~jlS113BBSBL(ND RIVETS

t IXIITIN6 ~R´•MI

IREFI


LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

El(Iura 2. laaat 2 af 2)

Page 4 of 5

SEAVICE LE~EK NO. 359

C EPECIIILTODLS: NONE.


1. Gain access to frame assembly at fuselage station 386.82.

2. Inspect left and right side of existing b~ame assembly brace (PIN 310024-53) for possible cracks in area oljoggleirefbr to Bigure 1).

3. If either end of brace is completely severed, inspect frame assembly $r any damage and contact GulBtreem

Aerospace ServiCenter, Bethany, Oklahoma before proceeding any further.

4 11 cracks ore found in brace but are not all the.way through brace, stop drill cracks using a No. 40 drill bit and

proceed to step 6.

5. 11 no cracks are found, proceed to step B.

6. Locate, drill and install 310024-103 gusset and 310024-105 ahim on left and right side of frame assembly (refer

to Figure 21.




SPARES AFFECTED: NONE.

PUBLICATIONS AFFECTED: The Illustrated Parts Catalog change required by this document will be incorporated at

the next scheduled revision

j RECORD COMPLmNCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.

359, dated 17 June 1983, entitled "Fuaelage Station 386.82 Frame Assembly accomplished tdate)

Page 5 of 5

V1

i Service Letter ~8Nd/lCulfstreamAerospace


1 August 1885

FLAP BRACKET INSPECTION

MODELS AFFECTED: MODEL 68011, SERIAL NOS. 15001 THRU 15018.

MODEL BSSA, SERIAL NOS. 88001 THRU 96050.

REASON FOR PUBLICATION: POSSIBLE OPEN DRILLED HOLES IN FLAP BRACKET CLIP.

COMPLIANCE: DURING NEXT 100´•HOUR INSPECTION.

NOTE

IF ANY.PROBLEMS ARE ENCOUNTERD WHILECOMPLYI~D WITH THIS SERVICE LETTER, CONTACT

YOUR NEAREST (IULFSTREAM COMMANDER

AUTHORIZED SERYICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT.

IPPROV~L:

ESTIMATED MAN HOURS: INSPECT FLAP BRACKET ONE (1) HOUR.

MODIFY FLAP BRACKET TEN (10) HOURS.

PARTS DATA: PARTS RE9UIREO TO COMPLY WITH THIS SERVICE LE1TER MAY BE PROCURED THROUGH

YOUR NEAREST OULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KB NO. 1-(26.00 or KIT NO.

2 525.00. REFERENCE THIS SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN

ORDERING SERVICE LETTER NO. 380 KIT CONSISTING OF THE FOLLOWING:

olo´• au,l´•a I~EnYlp´• Wln~ul HOll~

KIT NO. 1- LEET FLAP BRACKETKIT NO. 2 RIGHT FLAP BRACKET

Kit Kit

No. 1 No. 2

~TY PTY PART NO DESCRIPTION

L ea. 51o103-S1 DoublerLea. 510109-92 Doubler

L ee. 1 ea. 510109-83 Radius Block

1 es. 1 ea. 510103-S5 ClipL es. 1 ea. 5101(13-81 Shim

L ea. 510109-59 Doubler

1 an. 510103510 Doubler

lee. 1 ea. 510109-511 Tapered shim

L ea. 1 ea. Compliance Card

L se. 1 es. Service Letter No. 560 Instructions

p,, 1 of 6


FT~GHLIHT

PICCOMPLISHMENT INSTRUCTIONS:

i. Remove upper forward baggage compartment liner to gain access to left and right nap brackets that are located

above the fuselage lavatory oompartment.

2. Using a flashlight and an inspection mirror, inspect lower inboard clip and lower bracket on left and nght Oapbrackets for open drilled holes in clip and bracket (refer to Figure 1).

8. If no open drilled holes are located in lower flap brackets or clips, reinstall baggage compartment liner and

proceed to step 6.

4. If open drilled holes are located in lower napbraekets or clips, proceed as follows:

a. Disconnect and remove aileron servo and servo brackets to facilitate modilcation offlap brackets.

b. Disconnect and remove push-pull rod a88embly from nap bracket pulley assemblies.

o. Remove lavatory interior overhead panels and aft pressure bulkhead interior panels to expose aft

pressurebulkhead.

d. Trim lower end of existing clip and drill out upper two (2) existing rivets attaching clip to vertical angle(refer to Figure 2).

a. Drill and install 610103-51 doubler (leEt aide) andior 61010352 doubler (right side) and 510103-SS radiusblack on existing clip and vertical angle picking up rivet hole locations noted in step d. (refer to Figure9).

I. Locate, drill and install 51010556 clip, 510105´•57 shim, 610105-58 doubler (left side) andior 61010S-S10a~uulr iri61~ ~na ui´•~ (ron~ a Filu~ 31 C

J~IOH 1CAUTION

Drill holes in existing lower bracket first to assure proper

edge distance is maintained.

g. Reinstall push´•pull rod assembly on nap bracket pulley assemblies using existing hardware.

h. If necessary, trim SlolOS´•S1 andior -92 doublers and 51010S´•SS clip O clear push-pull rod assembly a

minimum of O.1B8´•inah and reprime with zinc chromate primer.

i. Reinstall ailemn servo brackets and aileron servo using existing hardware.

j. Check nap central rigging as outlined in Chapter 21 of the Airplane Maintenance Manual.

k. Check aileron cable tensions as outlined in Chapter 21 of the Airplane Maintenance Manual.

i. Using sealant conforming to Military Specification MIL´•6´•8802, seal rivet heads in iavatorycompartment overhead per procedures outlined in Chapter 20 of the Airplane Maintenance Manual.

Allow sealant to cure properly prior to installing lavatory upholstery panels.

m. Reinstall lavatory overhead panels and aft pressure bulkhead interior panels.

C

Page 2 of 6

SERVICE LETTER NO. 36(1

3YERTICI\LANaLE

t~ II i i~++

IREF)

ExlanNo CLIP

(REF)

jINSPECT ~FT ENO OF THIS

BRACKET P.ND CLIP FORLEFT FLAP sRnCKET

OPEN DRILLED HOLES(REF)

CVIEW LOOKING FORWARD

R.e.P*R

(REF)

AT REAR WING SPAR

VERTICI\L~NGLE

i r-i~bl,RE, EXISTIND CLIP

rL~ i(nEF,

-i-

INSPECT P~FT END OF THISRIGHT FLAP BRACKET

sAIICKET AND CLIP FOR

OPEN DRILLED HOLES (REF)

FlgUIB i.

Page 3 of 6

SEKVICE LE~ER NO. 380

(REF)

t -t- C CrlNBO

r--

i

Al I II;IJI A

DRILL OUT TOPTWO (1)

i

LEFT FLAP BRACKET

(REP)VIEW LOOKING FORWPIRD C

EXISTING CLIP TRIM LOWER END

(REF) ONLY 1.0" RADIUS

CLEAR 510103S1 DOUBLER)

f

DRILL OUT TOPTWO 12) RIVETS

THe~T A~*CH CLIP

TO VERTICI\L I\N(ILE

f

BULKHE~O

(REF) VIEW A-A ‘YERTIC*L PINGLE

(nER

LEFT INSTALLATION SHOWNRIGHT INSTALLATION OPPOSITE i

Fisure 2.

Paee 4 of 6

SERVICE LE1TgR NO. 360

REAR SPAR

Q~

(REF)

A III I IIA IA

LEFT FLAP BRACKET

cnEF, VIEW LOOKING FORWARDNAS1138R4 BLIND RIVETS 510103-61 DOUBLEROR M8Z0470AD4 RIVETS

510103979HIMPICK UP EXISTING HOLESIN WEB S~P103´•SB 510103´•88 DOUBLER

EYISTINO LOWER

BRACKET EXISTING WEB(REF) dgl (RER

NlnnasleuNonnr.rOR M92041011D4 RIVET 510103-911 TAPERED SHIM

(8 PLS)~5173(189 BLIND RIVET

88201704\04 RIVET

(4 PLS)I

VIEW B-B510103-911X TAPERED SHIM

I~ 51o103-9laHIM

\"h510109-81 CLIP

51010381DOUBLER DOUBLER NI\S17388B BLIND RIVETS

8\’ OR

MS204101\D5 RIVETS

B 510103´•83RADIUS BLOCK

o.ls´•´• MIN. +iI

PICK UP EXISTING HOLE VLRTIC*LPINOLE

VIEW A-A EX’ST’NG CLIP NAS1138B4 BLIND RIVET (888)cnEF,


Fleurs 3. RIGHT INSTALLATION OPPOSITE

Page 6 oE6


s ~inarsa linol C6. Fill out and mail Compliance Card.

ELECTRICPIL LOAD: NO CHANGE

WEIGHT AND SALANCE: NO CHANGE

SPPIREB AFFECTED: NO.


RECORD COMPLIP~NCE: Make an appropriate entry in airplane maintenance reeai´•dl as follows: SBNice Letter No.360, dated 1 August 1833. entitled "Flap Bracket Inspection". accomplished idatel

C

Paea 6 of 6

Service. .Letteu GulfstreamAerospace

SERVICE LETTER NO, 361

4 November 1983

HYDRAVLIC HOSE REPLACEMENT

MODELS AFFECTED: MODEL 690D, SERIAL NOS. 1SOPSTHRU 16029.

MODEL 896A, SERIAL NOS. 06066, 98058 THRU 96061, 98063 ANO 96069.

REASON FOR PUBLICATION: TO ELIMINATE POSSIBLE INTERFERENCE BETWEEN HYDRAULIC HOSE

ASSEMBLY AND ELECTRICAL WIRING.


NOTE

IF ANY PROBLEMS AP;E ENCOUNTERED WHILE

COMPLYING WPH THIS SERVICE LETTER, CONTACT

YOUR NEAREST CULFSTREAM COMMANDER


BY WHOM WORK WILL Be ACCOMPLlSHED: A 6r P MECHANIC OR E9UIVALENT.

APPROVAL: ENGINEERING DESIGN ASPECTS ARE BAA APPROVED.

ONE (1) HOUR.ESTIMATED MAN HOURS:

PARTS DATA: PARTS REqUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGHYOUR NEAREST GULFWREAM COMMANDER AUTHORIZED SERVICENTER FOR 513.00. REFERENCE THIS

SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LETI~ER

NO. 361 KIT CONSISTING OQ THE FOLLOWING:

~TY PARTNO. DESCRIPTION

1 ea. 790544-89 Hos~Assy3 R. U" (MIL-I-?´•4bl) Vinyl Tape3 ea. MS3S61-19 Tiedawn Strap1 se. Compliance Card

1 ee. Service Letter No. 961 Instructions


ACCOMPPLSHMEET INSTRUCTIONS:

1. Gain access to nap actuating cylinder through baggage compartment door.

2. Remove baggage compartment liner, as necessary, to expose nap actuating cylinder. The nap actuating cylinderis locatedjust forward and above the baggage compartment door.

3. Reduce airplane hydraulic system pressure to zero.

4. Remove and discard existing naps up hydraulic hose assembly (Pn~i 1905(4-81) from nap actuating cylinder (refer

C6. Install 190344-89 hose assembly (refer to Figure 1).

Page 1 of 2

SERYICE LE~ER NO. 381

a wrer uirr buhdb .ilh´•r lid. ov.r ho* ~th Yrul~h ringl inp aai ssiure ea.h end of

tape using MS9367´•18 tiedown straps (refer to Figure i).

Perform leak oheok of the nap actuating systee tb~’a maximum normal operating pressure of 1000 psi.

8. Reinstall baggage compartm.dliner:

9. Fill out end mail Compliance Card.

ELECTRICAL LOAD: NO

WEIGHT AND BALI\NCE: NO CHANDE.

SPI\RES AFFECTED: NO.

PUBLICATIONS AFFECTED: The Illustrated Pens Catalog change required by this document will be incorporated stthe nert scheduled revision.

RECORD COMPLIP~NCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.361, dated 4 November 1985, enwtled "Hydraulic Hose Replacement", accomplished (date)

FLPIPACTUATINOCYLINDER IREFL

REMOVE EXISTING HO8EA88Y AND IN8TI\LL78(1~4´•88 nOSE ASSY

WRAP EXIITINO WIREBUNDLE W1Tn 11’~ VINYLTAPE AND 880088 WITH

MS)SB7´•1´•8 TIEDOWNSTR*PI

VIIW LOOKING UP AND OUTED

AT EAOOAGE COMPARTMENTORIGINAL

Ffpm I.As Received By

ATP

Page 2 of 2

e~illC Culfstream

Aerospace

SERVICE LETIER NO. 362

Revision Na. 1

2 May 1884

INSPECTION AND/OR MODIFICATION OF OBSERVER SEAT

SHOULDER HARNESS STRUCTURE

~PPROYAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.

ACCOMPLISnMENT INSTRUCTIONS:

NOTE

IF OBSERVER SEAT SHOULDER HARNESS ATTACH

FPITING IS MOUNTED ON THE AFT SIDE OF FRAME

AT STATION 98.00 MODIFICATION IS NOT

NECESSARY. PROCEED TO 8TEP 17. AND NOTE ON

COMPLIANCE CARD THAT FI?TIND 18 MOUNTED ON

AFT 81DE FRAME.

THE OBSERVER SEAT 8HOULDER HARNESS ATTACH

FITTING TO BE MODIFIED IS JUST FORWARD OF

STATION BB.S0. TO DETERMINE LOCATION OF

FITTING AT STATION 98.50, MEASURE B.6INCHES

FORWARD OF AW END OF EMERGENCY EXIT

WINDOW UPHOLSTERY PANEL.

C

Page 1 ol 1

Service Lettev CulfsrreamAerospace

SRKYI(:% I.k:1’1´•RK NO.:16P

I?Nev~mhBI´• IOH:I

INSPEC71ON AND/OR MODIF1CATION OF OBSERVER SEAT

SHOULDER HARNESS STRUCTURE

MODELS AFFECTED: ’l’llI IIO[,I,OWIN(: MOI)R1.8’PHAT IIAVF: OI(SII(VF.I( YF.AT INSTAI.I.%I).

M(11)111. BOI)I), SRILIAI. NO8. 151)1)1 THKU 16(ISH.

MOl)l(ll ~(16A, 811~1AI. NOS. HS(IOI THKU 96(L61.9806:1. 111(11114, UB(168. BHI)?P ANII HfiO?:l.

MOTE

THE OI1SEHVIK YBA11 IS I.O(:ATBI) IIEHINI) TH~

UOPLT.OT YIAT

REASON FOR PUBLICATION: TO ASSUKB PKOPEH LNYTAI.IATION OF ORSIKVIK SRAT SHOUI.I)RI(

A1TA(:HMF.NT.

COMPLIANCE: WITHIN NIX’P IOII-HOUI~ TIMR IN SIIIVICB.

C rots

IP ANY PKOnI´•gM8 AHE EN(:OUNT%KRI) WHII.I

COMI’I.YIN(: WITII THIS YglLVICg IPITPIK. CONTACT

YOUIL NF.AHEW CUI.FYTRF~AM UOMMANI)%H

AU~PHOKIZRI) SEKVI(:ENTEK

BY WHOM WOR~ WILL BE ACCOMPLISHED: A L P MECHANIC 01( IYUIVALRNT.

APPROVAL: ~N(:LNlt:RKIN(: I)ESLON ASPR(:TS AKE FAA AP~’HOVII).

ESTIMATED MAN HOURS: r"OUI( (4) HOUHS.

PARTS DI\TPI: I’AKTS RR9UIKII) TO COMPI.Y WITH THIS SERVlcl I.En´•BH MAY ng I’ItOCUKEI) TRHOU(:H

YOUH NF.AHFST QUI.FSTII~AM UOMMANI)EH AUTHOKLEBI) YBHVLCENTBK FOK (20.0(1. KgFF.KRNUE TIIIY

SIIILVI(:g AIII(:KAPP MOI)BT. ANI) FAOTOHY SIKIAL NUMDOK WHEN OKI)EHLN(: I.F~1TRI1

NO.:lliP KI1‘ (:ONSIYTLN(: OF THR FOIII.OWIN(::

~m´•´•ua*nMI´•nl´• m~ul nohu.

cl’rv PAKT NO. DESCHLYPION

leu. 10U06X-81B Pbtr

leu. Hfil)?X:l-fi69 Plueurd

:leu. MS9(1~R´•I-UROh Huck Rlllt

:I cu. MS90:194-OHOS Huck Rolt

tau. Cumpliance Curd

Iril. Sttrvire Letter No. 361 inatructionn

SPECIAL TOOLS: HUCK (:UN ANI) HOI.FI FLNI)EH.

IICCO.PUS...NT INglllUenMIP;

I. Hemeve window ~sm airplanr

1. Hcmovr ilhxarvrr saut xhuuldar hilmexu.

Page 1 ol 4

I.IPPIIINO. :162

CEMERGENCY EXITWINWWOPENIN(I

IREFI

BEFORE CHANGE

EXISTING PLATE

(REF)

"1EXISTING FITT(NO 11?

II II

IREF) illREMOVE RIVETS

ANO INSPECT FOROF

INSPECT FOR BAP )I I L;/ I HOLES

ACCEPTABLE TO INSTALL THRU

+111

RIVETS

hcHOLE THAT WAS M)UNTERSUNK

IN BELOWPLATE

AFTER CHANGE

’I IACCEPTABLE TO USE N~S17SBB(lb

IIBLIND RIVETS IF NECESSARY)

II

h;

INSTALL IWOSIS1S PLATE WITH THREE 131MS9mSbOB05 MUCKS IFOR HOLES WITH MAXIMUM

NOOnP CLEANUP DIA. OF 0.202´•1 OR M990351-08~ MUCKS

ALLOWED IFOR HOLES WITH MAXIMUM CLEANUP oln. of8285"). ANY COMBINATION OF MS90J64 HUCI(SISACCEPTABLE.

NnS1ISBB~-S BLIND RIVETSII IACCEPTI~BLE TO USE NAS113888´•5

100058-515II BLIND RIVETS IF NECESSARY)

PLATE

VIEW LOOKING OVTBD

C

Pa~e 2 of 4

SII1V1(:l r.B~PTII( NO. :l(i2

I\

i,i

850783´•689

OBSERYER FE~T ITYP)IRE Fl

Fipura 2.

Pa~e 3 aI 4

SRI(VI(:R LRTTRK NO.:162

:I

n side rsscl illilt is isc;ltrd amar~enay exit windllw opening end side pilnel below wind~lw

illl.,iLllnol.alncy exit wincl.lw 1II explu;e ~,hlerver seat shoulder hurne*s iltt,lell litting

I(aml,va channel il’iN X6111:l(l-1281 th;,t is isci)lcd below the emergenmy exit window ~,psning.

6 inspecl ~ihl,ulclsr h;ll´•lloxx;llluch litting li,l’ it ~lp between lilting ilnd support plilte (rriir tcl I’igule 1).

7 i)lill ilut tll,´•ee I:11 i´•iwlr th,,t ilttiluh i,l,servsr aeilt sh~lulder hill´•ncsx;,tti,eh iilline xuppil,´•t plate ttl lunll;lgu lulmr

;11 st;ltilll, B(i611 irular t~l [iigure Il.

H. InLil’"’t thl´•se (:II holsn in ILlaii~Ee lismr li,r pllsaihle eillnpation IrrBI to PiFurr I)

L). 11´• 11(1181 in li´•ilml´• ;~l´•r nl,t elonhratrd and nl, Rap iX evidenl between littinl: and support plate. reill*tsll

exixtinl: auppslt plate usinl: NI\SI7:IRRS-5 blind rivets and prcneed to step il.lrelir tl, PiRura 1).

111 11’ h~llaa in Ib*rlilUe irilmu are elongnterl or ovenile or a ilap between litling imd support plate is evident. pn,crad

;I Oleunup elongated holes (reLr tn Fieure 1).

b. I)l´•ill out first two 12) rivet~ above and below support plate nttachinl! hnlrs irefer to Fihrurr 1)

c. Uxing a hale finder, locate. drill and install L000SR-S18 plate on fuselage frame Assure thilt no gap

axistu between ntting and plate ire~er to Figure i).

d I’*oeeed to step ii

Il ehunnel IPIN Rfi2030´•128) using cxistinb´• hardware.

it. ..ml .b Ransla uain, harduu~

I:I Keinxtilll observer seat hack.

14 KL´•inat;lll observer neat ahuuldar harness.

I(sinst;lll emer(!enov exit window

I(i Yuijr Eu*hion on observer sent and illstall 860?H3´•689 placard on top of front lip of seat base iroLI to i’igure 21

17 Fill out and mail Complinnee Card

ELECTRICAL LOAD: NO CW~NGP

WEIGHT AND BALANCE: NO CHAN~I%.



RECORD COMPLIANCE: Make an appropriate entry in airplane mnintonance re~ordJ as B,liowa: Servicr Letter No

:1~1, dated 17 November 1983, entitled "lnspsotion anPor Mndineatinn of Observer Seat Shoulder Ilnmeua Structure’~,;ec~lnlpli*hpd (date)

Page 4 of 4

dl


SERVICE LE~PTER NO. 383

1 November 1883

FUEL DRAIN-SYSTEM INSPECTION

MODELS AFFECTED: MODEL 69OC, SERIAL NOS. 116W THRU 11150.

MODEL 690D, 8ERIAL NOS. 15601 THRU 15029.

MODEL 696 SERIAL NOS. 85000 THRU 95084.

MODEL 695A. SERIAL NOS; B6W1 THRU 96061, 86065 THRU 96065, 96069, 96072, 88076

AND86018.

REASON FOR PUBLICATION: POSSIBLE BLOCKAGE OF FUEL DRAIN PATHS WITH SEALANT WHICH COULD

CAUSE UNDRAINABLEI[INU8ABLE FUEL TO INCREASE SLIGHTLY, INCREASE

CHANCE FOR BACTERIA GROWTH IN FUEL AND POTENTIAL WATER TRAPS

IN FUEL TANK AREA.

COMPLIANCE: AT NEXT SCHEDULED TWELVE (12) CALENDAR MONTH OR LOG-HOUR INSPECTION,WHICHEVER COMES FIRST.

NOTE


COMPLYING WITH THIS SERIVCE LETTER, CONTACT

YOUR NEAREST

BY WHOM WORK WILL BE I\CCOMPLISHED: A L P MECHANIC OR EQUIVALENT.


ESTIMATED MAN HOURS: THIRTY-FIVE (35) HOURS.


YOUR NEAREST CULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR (8.75. REFERENCE THIS

SERVICE LET~ER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LET~ER

NO. 365 KIT CONSISTING OF THE FOLLOWING:

Prl~´•um D aun* *Im~xllno~´•.


4 se. 690394-1 Gasket

1 ea. ComplianeeCard1 as. Service Letter No. 563 Instructions

SPECIALTOOLS: NONE.

ACCOMt´•LISHMENT INSTRUCTIONS:

1. Defuel airplane as outlined in Chapter 28 of the Airplane Maintenance Manual.

NOTE

Do not use booat pumps to off load fuel.

2. Remove upper aceee. doors, between wing station (WS) 141.0 to wing stntion 255.52, from left and right ~vlng

(refer to Figure I).

Page 1 of 6

..;I__..;

8ERYICE LETTER NO. SBS

BA-c, C-h D~h D

ii

sU-

:P,. O

oO

-r

G) ~dl

A~J Dcl Dt] DI-~i

VIEW LOOKING DOWN ON LH WINGRH WING OPPOSIPE

DONOTAEMOVEGE*L~NT AT WS 160.0

VIEW A-A

WS 160.0 AND WS 142.0

D INolcnrEsnnEnsro

iiFiaurs 1.1Shsat 1 ~t 0)

Page 2 ol B

SERV~CE LETTER NO. SBS

Inz.oONLY

142.0ONLY

VIEW B

C:

D

B INDICI\TESPIREAS TOWS 178.6

BE CLEAR OF SEALANT

F5urs i. IShsat of 3)

Page 3 ol B

SERVICE LETTER NO. S83

VIEW D-D

WS 197.3. WS 216.0 AND WS 234.6

I Y\D"B

VIEW E

SHOWING WS 216.0 SAME AS WS 234.6EXCEPT AS NOTED

88

BINDICATEII\REABTOBE CLEAR OF SE~LANT

VIEW F

SHOWING WS 197.3 SAME AS WS 216.0EXCEPT AS NOTED

Fieur´•l. (Shsat 3 of 3)

Page( olB


AREA TO BE CLEAREDOFSEALANTITYR

RIBASSY

REMOVE SEALANTFROM HOLES ITYPI

TYPICAL VIEWOF RIB CUTOUTSFOR MODEL 8800. SERIAL NOS. 11800THRU 11850 ANO MODEL 885. SERIALNOS. 85000 THRU 85038.

AREA TO BE CLEARED R?BSS"OF SEALANT ITYP)

CENTERLINE OF

CUTOUT

REMOVE SEALANT IN RIB CUTOUTSTO ALLOW A IlalNCH ROo TO PASSTHROU(IH CUTOUT. BE EXTREMELYCAREFUL SO AS NOT TO REMOVEEXCESSIVE SEALANT IN AREAS SHOWN

TYPICAL VIEW OF RIB CUTOUTS WHICH COULD CAUSE LEAKS. NO EXPOSEDFOR MODEL 8800. SERIAL NOS. 11851 METAL I\LLOWEO.IF NECESSARY. TOUCHUPTHRU 11730. MODEL 8800. SERIAL NOS. SEALANT:15001 THRU15028. MODEL 586. SERIALNOS. 85038 TnRU 85084 AND MODEL 885A.SERIAL NOS. 98001 THRU 88078.

Fieure 2.

Page 5 oI6


3 Hemove screws attaching outboard and mid-wing fuel transmitters to access doors and remove doors.

1 ma~act in i .b that ela~ i. n.~

5. If any area, noted in Figure 1., is blocked by sealant, remove excess sealant from that area to eliminate blockage.See Figure 2 for typical view of area to be cleared of sealant st cutouts and stringers.

NOTE

Place protective paper or cloth below all access door

openings prior to cleaning, sealant from periphery of

opening. Remove and discard before sealing doors.

8. Remove all sealant from wing access doors and access door openings. Care should be taken so as not to scratch

the metal surface.

7. To prevent contamination of fuel, assure that all fragments of sealant are removed from wet wine fuel area priorto installing wing access doors.

8. Apply alodine solution, as necessary, to bare metal on inner surface of access doors and outer surface of access

door openings in wing.

9. Reinstall existing fuel transmitters on wing access doors using existing hardware and new 630594-1 gaskets.Torque screw 20 to 25 inch-pounds.

LO. Reinstall and seal existing wing access doors as outlined in Chapter 67 of the Airplane Maintenance Manual

11. Perform fuel system pressure check as outlined in Chapter 28 of the Ai~lane Maintenance Manual.

12. Refuel airplane as outlined in Chapter 12 of the Airplane Maintenance Manual.

L3 T.u.hu~iulintssnsEPrsSI


ELECTRICAL LOAD: NO CRANGE.




RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance I´•ecords as follows: Service Letter No.

383, dated i November 1883, entitled "Fuel Drain System Inapection", accomplished (dnte)

Page 6 ofR



18 November 1983

SERIES MODE ANNUNCIATOR LIGHT TAPE REPLACEMENT

MOOBLS I\FFECTED: MODEL 690C, SERIAL NOS. 11750 AND 11152.

MODEL 680D,IERIAL NOS. 15025 THRU 15029.

MODEL 68SAl SERIAL NOS. 86068 THRU 96061, 96083 THRU 96065, 96069, 86012, 98016

AND 96078.

REPISON FOR PUBLICI\TION: STANDARDIZATION OF SERIES MODE ANNUNCIATOR LIGHT COLOR

BETWEEN ALL MODELS AND SERIAL NUMBER OF AIRPLANES.

COMPLIIANCE: DURING NEXT 100-HOUR INSPECTION.

NOTE


COMPLYING WPI~H THIS SERIVCE LETTER, CONTACT

YOUR NEAREST OULFP´•TREAM COMMANDER

AUTHORIZED8ERVICgNTER.

sYWHO.WORKWILL BEI\CCOHPLISHUI: ~WNWOPEh*TOB OR*6rP ~CRANIC OR eQUNALENT

I\PPROVP~L: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.

ESTIMI\TED MAN HOURS: THIRTY (80) MINUTES.

PARTS DATA: MATERIAL RE~UIRED TO COMPLY WITH THIS SERVICE LETI~ER IS FURNISHED WITH THIS

SERVICE LETTER AT NO CHARGE UNTIL 18 NOVEMBER 1984 AND CONS1STS OF THE FOLLOWING:

9TY PARTNO. DESCRIPTION

4 in. TCMIOB Chartpak Tape1 ea. Compliance Card

1 ea. Service Letter No. 364 Instructions

8PECIALTOOLS: NONE.

ICCOMPLISHMENT INSTRUCTIONS:

1. Remove two (2) aorews that attacb annuncintor face plate to annuneiator panel and remove face plate (refer to

Figure Il.

2. Remove e.isting amber tape behind’SERIES MODE" nomenclature and apply TC6009 blue tape (refer to FigureIi.

S. Re~netsll face plate on annunciator panel using existing ha~dware.


C

Page 1 of 2

´•j/


I\NNUNCI~TDR PI\NEL I\TT*CHIROSCREWC

(REF) IZPLSI

i IL~ eg YIL iiT X~ L a dr

~s0 i ´•I ´•IL*. Oe~L l~:a: .s..nr ~s ’D w ~ln n

Face pLnn REMOVE EXIST1N9 TI)PE(REF) BEHIND’´•S~RIES MOOE’´•

nND ~PPLY TCSOOJ BLVETI\PE

Flgura i.

ELECTTICI\L LO*D: NO CHANGE.

N~CHANCE


PUBLICATIONS AFFECTED: Pilot Operating Handbwlt change required by this document is furnished with this

Service Letter.

RECORD COMPLI~NCE: Make an appropriate entry in airplane maintenance recoids as follows: Service Letter Na. 564

dated 18 November 1983. entitled "leries Mode Annunciator Light Tape Replacement", accomplished (dstei

Pnge2ofB

-.__-.rm,lPILI-~,- _.l_l__-~IILi -..LIXIV-I i_- ii -i__L.._. i-:l.l;ii::;:.-__

~IIc Service Letter Gulfstream

Aerospace

SERVICE LeT~ER NO. 3663 February 1984

FUEL BOOST PUMP REPLACEMENT

MODELS AFFECTEO: MODEL BBOC, SERIAL NOS. ll?SO THRU 11132.


MODEL 685A, SERIAL NOS. 96058 THRU 96061, 96063 THRU 86069, 96012, 96075, 96018

AND 98085.

RMSON FOR PUBLIC~TION: TO PROVIDE FUEL 800ST PUMPS WITH IMPROVED RELIABILITY.


NOTE


COMPLYING WITH THIS 8&RVICE LE~ER, CONTACT



BYIYHOH BPMECH*NIC ORBqUIVILENT


ESTIMI\TED M*N HOURS: INSPECT BOOST PUMPS FOR MODEL NUMBER TEN (101 MINUTES

REPLACE BOOST PUMPS TWO (2) HOURS.

PARTS DATA: PARTS RE~UIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGH

YOUR NEAREST GULFSTREAM AUTHORIZED SERVICENTER FOR $1061.71 PER KB, h FULL

CREDIT WILL BE ISSUED UPON RECEIPT OF OLD Pn~T 630590-103 (VENDOR MODEL NO. 3B1´•1 OR 381-1A) FUEL

BOOST PUMPS, A PROPERLY EXECUTED CLAIM AND A COMPLIANCE CARD IF RECEIVED PRIOR

TO 3 FEBRUARY 1986. REFERENCE THIS SERVICE LETTER, AIRCRAIT MODEL AND FACTORY SERIAL

NUMBER WHEN ORDERING SERVICE LETTER NO. 365 KIT CONSISTING OF THE FOLLOWING:

NOTE

EACH KIT CONSISTS OF ONE (1) 630380-603 FUEL

BOOST PUMP AND TWO (2) S-OS10-912HT O-RINGS;THEREFORE, IT IS NECESSARY TO SPECIFY

qUANTITY OF KPPS RE~UIRED WHEN ORDERING.


1 se. 630390-509 (Model No. 981-4) Boost Pump2ea. S0310-912HT (L449´•80 Compound) O-Ring1 ea. Compliance Card1 ea. Service Letter No. 365 Instructions

C

Page 1 ol 1


sPw;laLrao~; NONE´•

ACCOMPIISHMENT INSTRUCTIONS:

I. Gain access to Left and right Fuel boost pumps, Located in nacelles, through main landing gear wheel well doors.

2. Check nameplate on fuel boost pumps for Model Numbers.

3. IfModel Number is 381-4, proceed to step 14.

4. If Model Number is not 311?-4, proceed to step 5.

5. Depress Battery switch to BA1TEBY position.

6. Turn FUEL-HYDR switch to EMER OFF position.

NOTI

This closes the main fuel shutoff valve.

Depress battery switch to OFF position.

8. Remove the left andior right fuel boost pumps as follows (refer to Figure i):

a. Completely drain the fuel lines to the fuel boost pumps by using the drain valves located just below the

fuel boost pumps.

b. Disconnect the electrical wiring and ground jumper cable from the fuel boost pumps and stow wires out

of the way so as not to damage wiring while removing boost pumps.

i ,sooMsl the drain dnin ´•slr~s

d. Disconnect the fuel supply line from the existing AN919-20D reducer.

e. Disconnect the fuel scavenge Line from the existing AN?83D12 tee.

f On the left boast pump, disconnect the existing M821919DG42 lower clamp, on the boost pump, from the

existing MS21919DG8 small clamp on the fuel scavenge line.

g. Disconnect the engine fuel supply line from the existing AN?83D12 tee.

h. Loosen the two (2) existing AN?S?TWLI1 clamps, attaching boost pump to boost pump bracket assembly,while supporting the boost pump.

i. Remove existing fuel boast pump, with flttings still installed on boost pump. from boost pump bracket

assembly.

j. Remove the fittings from the boost pump, as a unit (do not disassemble nttings), and note the number

of turns required to remove 8ttings from pump.

Install 8ttings, a. a unit, on the new 630380-503 (Madel No. 311?-4) boost pump using new S-0310´•glaHT

o-rings. Screw fittings into the boast pump the same number of turns noted in step j.

I. Install the new boost pump on the existing bracket assembly end finger tighten the existing AN?3?TW91

clamps.

m. Reconnect the existing fuel and drain lines 0 fuelboost pump and reposition boost pump on the bracket

assembly as required.

n. Tighten the edsting AN?B?TWg1 clamps on the boost pump.

a. On the lett boost pump, reinstall the existing M921819DG42 clamp an the boost pump and the e.is"np iMS21918D08 clamp on the fuel scavenge line using existing hardware.

Page a of 4

8ERVICE ~TTER NO. 985

8OO8TPUMPSUPPLY LINE

BR~CKETA88Y(REF1

OROVND JUMPER CAQLE n E~d EXISTING AN789D1Z TEEIREF) \/I (I I\ .IREFL

12 PLSIEXISTINO*NIIITWBI

FUEL SUPPLY LINEIREF)

FUEL SC~YENOE LINE

EXISTING U II (REFI

ANBlPEEG REDUCER

EXISTING M821818D(Y12CLAMP IREFI

030580603 (MODEL SBI~)FUEL 8008T PUMP

MS21818DOICLAMP (REF)

orul.uwrIREFI

EXISTING FITTINGSIRE Fl

FUEL DRAIN VALVE

INSTALL NEW 60310QllnT (REF)

O´•RINO 12 PLSI

LEFT INSTALLATION SHOWNFleurs i.

p. Remnnset the electrieal wiring to the fuel boost pump.

q. Reeonnect the existing ground jumper cable on top of boost pump.

9. Depress battery switch to BA1TERY position.

LO. Turn FUEL-HYDR switch counterclockwise to NORM position.

NOTE

This opens the fuel shutoff valve.

11. Depress battery switch to OFF position.

if. Cheek all connections for fuel lealage.

13. Functionally test the fuel boost pumps and t~el scavenge system as outlined in Chapter 28 of the AirplaneMaintenance Manual under paragraph labeled Low Fuel Scavenge Gystem

14. Fill out and mail Complianee Card.

Page 3 of 4


CELECTRICAL LOAD: NO CHANCE.

WB1GHT A.ND BALANCE: NO CHANGE.



RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance remrda as follows: Service Letter No.

385, dated 3 February 1884, entitled "Fuel Boost Pump Replaoement", accomplished (dato)

Page 4 of 4

´•II _I

,Seavide Letter CulfsrrssmAem~pereCo1Hnalion

on´•n~M a*, o*iah~ml loin

SERVICE LETTER NO. 366A 1(Supersedes Service Letter No. 366, dated November 2, 1984, in its entirety) I

22 March 1911

NOSE LANDING GEAR DRAG LINK SUPPORT STRUCTURE MODIFICATION


MODEL 680W, SERIAL NOS. 1121 THRU 1850.


MODEL 685, SERIAL NOS, 12000 THRU 12066.



MODEL 680B, SERIAL NOS. 11350 THRU 11566.OMODEL 690C, SERIAL NOS. 11600 THRU 11735.


NOTE

[F PART II OF SERVICE LETTER NO, 368 HAS BEEN

ACCOMPLISHED, DISREGARD THIS SERVICE

LETTER.

.E~S(I.FoRPUBLIC*TION: LOM P*l~-8 CAP~BILITY OF DRIO LINK SVPIORT

COMPLII\NCE PART I EACH loO-HOUR INSPECTION UNTIL PART 1l IS ACCOMPLISHED.

PART II AT OR BEFORE THE FIFTH 100´•HOUR INSPECTION (AFTER NOVEMBERB, 1984) OR EIWHEN PART I REVEALS ELONGATED HOLES OR CRACKS W SUPPORT STRUCTURE.

NOTE

UI’ANY PROBLEMSARE ENCOUNTERED WHILE


YOUR NEAREST´• GULFSTREAM COMMANDER


BY WHOM WORK WILL BE ACCOMPLISHED: A a p MECHANIC OR EqUIYALENT.

APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED. I

ESTIMATED MAN HOURS: SIXTEEN (16) HOURS,

PARTS DATA: PARTS RE~UIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED FROM

YOUR NEAREST OULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR $16.76. REFERENCE THIS

SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LETTERI

NO. 366A KIT CONSISTING OF THE FOLLOWING:

.Pagelof 7

SERVICE LETI~ER NO. BBBA

~n PARING. DESCILrPTION (I1 ea. 310054-RE3 Angle1 ea. 310054iRE4 Angle1 ea. 310054-RE5 Cha~nal1 ea. 31(0544-RE1 Strap4 ea. MS21044N3 Nut

4 ea. AN960-10L Washer4 ea. AN3-4A Bolt2 ea. Compliance Card

II 1 ea. Service Letter No. BBBA Instructions

SPECIALTOOLS: NONE.

ACCOMPL)SnMENT INSTRUCTIONB:

PART I INSPE~TION OF DRAG LINK SUPPORT.

I. Cain access to the nose landing gear drag link support structure through the access panel located on the rightaids of the airplane at FS -12.00.

NOTE

Loose bolts are to be suspected if a snap or popping sound

is detected in the nose landing gear attach area when the

tug begins the towing procedure.

2. Inspect nose landing gear drag link support far loose bolts which attach support channel to 310054-25 channel.If bolts are found to be loose, inspect Ear elongated holes in both channels (refer to Figure 1). If hales are not

dShtEn *lg. B*l.t ,I. p~.´•rri II ~f LU S.rvi~e

3. Inspect upper channel and lower channel at forward end for cracks in the radius of the bend adiacent to the

surface which attaches to the web (reler to Figure i). If cracks srs found proceed to Part II.

ii4. If no cracks or elongated hales are found, perform this inspection every 100-hours. Part II of this Service Letter

shall be accomplished at or before the~fth 100-hour inspection (after November 2, 1984) regardless ofthe link

support condition. Fill out and mail Compliance Card specifying thatPart I has been aeeompiished.´•

PART II MODIFICATION OF DRAG LINK SUPPORT.

NOTE

The following instructions modify the nose landing geardrag link support assembly with the drag link supportassembly installed on the airframe. An optional method Formodification is to remove the drag link support assemblyfrom the airframe.

1. Gain access to the nose landing gear drag link support structure through the nose wheel well and access panellocated on the right side of the airplane st FS -12.00.

2 Using a C10 bit, stop drill cracks in upper and lower channels.

3. Drill out the forward nine rivets which attach the existing upper channel to the existing web.

4. Perform step 3. for existing lower channel and web.

5. Dnll out the rivals which attach the cover to the upper and lower channels.

6. lour bolts, washers, and nuts which attach the upper and lower channels to the existing 310054-25

Page2of’i

SERVICE LET1’ER NO, 366A

7. Urill out the rivets at the forward end of the cover. These rivets attach the cover and clip to 510054-25 channel

Not. that the clip remains installed. Pry cover away from upper and lower channels. Use caution only to applyenough Fores to the cover to gain access to the interior parts of this assembly. Do not damage or sevel´•ely bend

cover. Place a screw driver or similar tool at the aft closure point of the cover and upper and lowel´• channels

to wedge the cover open at the forward end.

8. Remove the two bolt., washers and nuts which attach 310051-25 channel to the support channel. Remove aild

discard 310054-25 channel.

9. Position 310054-RE3 angle an upper channel as shown in Figure i, Detail B. Trim 310054-RE3 angle as

necessary to ensure a proper fit. Match drill rivet and bolt holes.

10. Locate and drill hales in 310054-RE3 and upper channel, follow drill pattern as shown an Figure i, Detail B.

ii. Attach 310054-RE3 angle to the upper channel and web using a NAS17S8B6 blind rivet or MS20470AD5 rivet

in the farward mast position and eight NAS1138BS blind rivets.

12. Attach 310054-RE3 to the upper channel with seven NAS1738B6 blind rivets.

13. Perform steps 9. thru 12. using 310064-RE4 and lower channel.

14 Remove wedge and secure cover to the lower and upper channels using NA91738B5 blind rivets.

15. Position 310064-RES channel between cover and support channel. Trim 310064-RE5 as necessary to ensure a

proper fit. Prior to match drilling assure that 310054-RES channel is a nush fit between caver and supportchannel. If a flush fit exists, proceed to step i?.

16. If 310064-RES channel does not fit Rush, fabricate and fit shim(s) made from 2024-T3 aluminum. A maximum

thickness of 0.010-inch shims are allowed between 310054-RE5 channel and support or channel cover.

17. Match drill 310054RE6 channel to cover and clip. Install four MS20470AD6 rivets or NAS1738B6 blind rivets

to attach channel to cover. clip and shim(s) as required,

18. Match drill 310054-RE6 channel to upper and iawer channels and install Four AN3-4A bolts, AN960-10L

washers and MS21o44N3 nuts to attach 310054RE6 to upper and lower channels. Inspect installation to ensure

that washers do not ride on radius of 310054-REB channel.

19. If washers ride on radius of 310054´•RE5 channel, remove washers and nuts. Fabricate a radius black to be

installed under both washers on the side affected. Install radius blocks, washers and nuts (next bolt grip lengthsize may be used if requiredl.

20. Trim 310054-RE1 strap as necessary to fit in forxerd side oFsupport channel.

21. Position 310064-RE1 strap on forward side of support channel. (See Figure 1. View D-D). Match drill holes in

strap,

22. Drill two 0.250 to 0.294-inch diameter holes in Si0054-BE5 channel to match location in support channel

23. Locate and drill eight holes in S10064´•RE1 strap and support channel, tSee Figure i, View D-D for rivet

pattern),

24. Attach 310054-RE7 strap to support channel using sight NAS1738B6 blind rivets or MS20410ADB rivets.

25. Secure 310064-RE5 channel to support channel, 310054-RE1 strap and shim(s), as required, with two ANI-SA

bolts, ANPB0-41B washers and MS21044N4 nuts.

26. Inspect AN4-6A bolt heeds installation to ensure that bolt heads do not ride on radius of310064RE5 channel.

27. If bolt heads ride an radius of 310054-RE5, remove bolta, washers and nuts. Fabricate a radius block to be

installed under bolt heads. Install radius blocks. bolts (next bolt pip length size may be used if required),washers and shim(s) (if required).

28. Fill out and mail Compliance Card. I

ELECTRICI\L LOAO: NO CHANGE.

Page 3 of 7

SERVICE LETTER NO. aBBA

EXIST1NB

SUPPORT

"JI

EX18TIN(I UPPER r

CHANNEL SHOWN PI

WITH nhlqLe prm

ExlsnNo LOWER3(W0eRESINSTALLED

CHANNEL SHOWN

WITH AN(ILE PIN~1DOW´•RII

INSTALLED

DET~II B(8haat? Dt

%SD~g,

ExlsnNoP

CHANNEL EXISTINB 8P~CER

IIP IN(ITAILEO)

9 Il Il IO

Oln a

oa

lo~-.- a

o,

EXISTIN(I

STRAP CDVER00 NOi

REMOVEEXISTIN(I OLO P/N CHANNEL

CLIP NEW PIN 3100MeRE6 CHANNEL

DETAIL A

FIWI~1. Nala Landinp Oasr Dng Lin~ Suppsn IShset 1 o( 3L

Page 4 ol 7

SERVICE LETTER NO. SBGA

0.16510.187" DIA HOLE

NAS1738BS BLIND RIVETS

OR RIVETS

PLSL3100J4´•RE3CHANNELSWOWN

31W54´•RE4 IOPPL

C~ I;i i+ta76.´•

ii O I t´• EXISTING SPACER0.35’~ 1 IIF INSTALLED)

0.78"

mpll II I t

’t CH~NNELISHOWN) ITYPI

COVER 1’EXISTING UPPER 0.35.:

LOWER CHANNEL

IOPPI

DETAIL E

VIEW LOOKING DOWN

o.las/o.la´•´• alA. HOLEDIA. HOLE NI\S1738B5 BLIND RIVET

NASI)JI1BS BLIND RIVETS (18 PLSITRIM FLAMIE

EXISTING UPPERTO MATCH CHANNEL 310054RE3

ANGLE CHANNELMSJOS53-05BLIND RIVET

laPLsl

~e -i- -.i-: I iiil+

D1A. HOLE tNAB171sBS f

BLIND RIVET

OR MS10470AO5RIVETS II 1 1111 1 1~1 C

I2PLS) II

L i i; i´• C C

TRIM FLANOE 310054RE4

TOMATCHCH~NNEL ANGLE EXISTING LOWER I

ITYPL CHANNEL

DO NOT REMOVE THESE

VIIW C.C RIVETSUNLESSDAAGLINK SUPPORT I\SSY IS

TO BE REMOVED AND

LOOKING OUTED MODIFIED ON THE BENCH

Figula i. Naa L~ndlna Osn Drse Lin* Suppo~ (Shwt Z of 31

PageDof7

SERYICE LETTER NO. QBBA

0.183W.189’~ DU. HOLE

ACCEPTABLE TO USE0.180/0.184" DIA. HOLE NASl73888 Is PLSI

BOLT

rl II\NBBO´•1OL WASHER

MS21044´•N3 NUT14PL4

1-c r! (.SD’´•

ANGLEIREFI

EXISTINGCOVER

IREF)ii

II

M82047P~DB

O

j AN4´•6P1 BOLT0.183/0.189" DI*. HOLE 0.250/0.254" OIA. HOLE

OR NI\S173888 0 0 I\NBBO~1R WASHER (21

I4PLS) MSZ1044´•N4 NUT12 PLS)

f

ANGLE I.ls" (np)IREFI

0/10"

INPI

VIEW D-D

LOOKING FWDE

lr31WSaRE6

CHANNEL

II,i

VIEW FOR

CLARITY ONLY

31W54´•RE7ITRI\P

II i\ SHIM IF RE(IUIREO BE~WEENII 310094´•REb CHANNEL ANO

31018521 CHANNEL OR 310054´•43COVER. FABRICATE SHIMI.I FROM

111 202473 IO´•MDII MAX. SnlM THlCI(NE8hILI ALLOWED1.

VIIW E´•E

LOOKING INBD

Filura(. Nora Llndln( Osar 014 Link Support rShast 3 ot 3)

Page sof7


WEIGHT AND BALPINCE: NEDI.IGIBLE.

SPPIRES AFFECTED: NO.I

PUBLICATIONS AFFECTED: The applicable Maintenance Manual and Illustrated Farts Catalog ehnnaes rcqoirrd by

this document will be incorporated at the nent scheduled i´•evision.

RECORD COMPLI*NCE: Make an appropriate entry in the airplane maintenance records as follows; Service i.t~tt*r INo. 366A, dated 22 March 1885, entitled "Nose Landing Gear Drag Link Support Structure ModiAeation". Pal´•t 1

accomplished (date) Part II accomplished (date)

Page’lof?

´•2*

$e~j@e ke~ter GulfstreamAerospace


4 January 1985

PARKER HANNIFIN CORP. PRODUCT REFERENCE MEMO (PRM) NO. 36 (REV. A)(30-107 and 30-1078 Brake Assemblies)

MODELS AFFECTED: FACTORY APPROVED:MODEL 680A, SERIAtNOS. 11195 THRU 11344.MODEL 690B, SERIAL NOS. 11350 THRU 11566.

MODELB90C. SERIAL NOS. 11600 THRU 11734.MODEL 690D. SERIAL NOS. 160U1 THRU 16033 AND 16035 THRU 15031.MODEL 695, SERIAL NOS. 95000 THRU 95084.MODEL 685A, SERIAL NOS. 96001 THRU 96061, 96069 THRU 96072. 96075, 96017, 96078,96082, 96085, 98088 AND 96089.

MODEL 595B, SERIAL NOS. 96201 AN1) 96202.

STC APPROVED:MODEL 690, SERIAL NOS. 11001 THRU 11019.MODEL 690A, SERIAL NOS. 11100 THRU 11194.

REASON FOR PUBLIC~TION: TO RECOMMEND COMPLIANCE WITH PARKER HANNIFIN CORP PRM NO. 36(REV. A) WHICH REDUCES BRAKE PISTON STROKE, THUS EXTENDING O-RING LIFg ADDS SELPAWUSTIND DRAKE FEATURE.

COMPLIANCE: PRIOR TO OR AT NEXT 100-HOUR INSPECTION

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE LETTER, CONTACTYOUR NEAREST CULFSTREAM COMMANDERAUTHORIZED SERVICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A 6L P MECHANIC OR EqUIVALENT.

APPROVAL: ENOINF.ERING DESIGN ASPECTS ARE FAA APPROVED.

ESTIMATED MAN HOURS: TWO (2) HOURS.

PARTS DATA: PARTS REQUIRED TO COMPLY WITII TIIIS SERVICE LE~PTER MAY BE PROCURED THROUGHYOUR NEAREST CULFSTREAM COMMANDER AUTHORIZED SILRVICENTER FOR (220.00. REFERENCE THISSERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LE1TgRNO. 361 KIT CONSISTING OF THE FOLLOWING:

Pd~ notla

BTY PART NO. DESCRIPTION

1 ea. 199-13000 Canveraion KitI ea. Complianee CardLee. ServiEe Letter Na. 567 Inntruetions

SPECI~LTOOLS: NONE.

Paselaf 3

SERVICE LE~EK NO. 367

INPTRUCTIONS: C-cnurloN

Cars must be taken and eye protection gear worn duringthis rework to avoid injury since we are dealing with

disassembly of a preloaded springstack.

Accomplish the following brake rework by installing Conversion Kit Pi~ 199-13000 as authorized by Parker Hannifin

Corp. PRM No. 36 (REV. A):

1. Chock main and nose wheel tires.

2. Apply a slight amount of pressure to brakes and set Parking Brako.

3. (WHILE WEARING SAFETY GLASSES) carefully Loosen the bolt which retains the enisting retract springs to

ibeback of the Hydraulic Pistons. (Typ. 8 places.) Remove and discard all parts.

4. Release Parking Brake

5. Remove Hydraulic feed line to Brake Assembly and cap.

6. Remove the 24 bolts which attach the beck plates to the Brake Cylinders, and remove brakes ham aircraft.

Screw one of the Back Plate attachment bolts into each piston in succession, and with hand pressure, pusheach

piston out of the Brake Cylinders. (MARK EACH PISTON AND BORE TO ENABLE~CT

REASSEMBLY.)

8. Remove O´•ril,Es from cylinder bores and pistons and discard.

9. clean eylinde~s and pistons using available solvent to aluminum.

10. Special attention should be given to the piston bores and pistons

A. Piston bores and "0" ring grooves should have foreign material loosened and Bushed from all surfaces,(The large diameter piston bore groove should not be polished with any abrasive material.)

8. The small diameter of the piston bore may be polished with steel wool or fine emery, but the finished

diameter shell not eroeed .565 min

C. The piston (lerge diameter) may be polished to remove shallow wear scratches andior nicks. The final

piston diameter, however, must be a minimum of 2.121.

D. Any prior rework to the above mentioned components which places them outside of the dimensionallimits defined, requires replacement of those components

11. Following cleaning and inspection of me cylinders anil pistons, instnll the new O-rings supplied in the Kit.

12. Lubricate the piston bares, O-rings and pistons with hydraulic nuld compatible with the aircraft system. Install

large O-ring in each cylinder groove and install small O-ring an each piston.

13. Lay the cylinder on a Rrm surface end insert piston into bore until the "0" rings prohibit further insertion. While

applying pressure with your thumbs, rotate the piston in a clockwise direction. After "O" ring squeeze is

overcome, the piston will slide freely into the bore. Push piston Bush to cylinder face. LRepeat 8 places.)

14. Install cylinders on aircraft

15. Install washers and cylinder tie bolts into cylinders and thru pressure plate. Typical 24 places.

16. Install (l)one insulator shim onto brake cylinder.

Page 2 of 3


CAUTION: (The brake may have had two (2) shima per cylinderinstalled at disassembly. Reassembly, however, with the

new retract mechanisms requires that only one shim be

used~. The additional shims may be saved and used as

future replacements should ons become damaged.

I?. Install back plates and tighten (24 each) cylinder tie bolts. (FINAL TOR~UE 85-90 IN-LBS.)

18. Reattach hydraulic feed line and bleed brakes.

19. Apply brakes to hold pistons from turning. Install new retract mechanism into the back of each piston. Screw in

by hand, making sure that the stud botrome on the piston tail surface. (FINA4TOK~UE 30-40 IN-LBS.)

(PEFER TO ENCLOSED DRAWING FOR CORRECT PART SEBUENCING.)

20. Safety wire studs.

21. Apply decals supplied in kit lane per brats assembly) for reidentifieat~on, remove old decal.

22. Functional check brake system to assure that it is operating properly.



WEIGHT AND BI\LANCE: NO CHANCE.

SPARES AFFECTED: SPARES TO STOCK PARTS ONLY FOR THE 30´•10?C BRAKE ASSEMBLY.

PUBLICATIONS AFFECTED: The Pilot Operating Handbooks, Airplane Maintenance Manuals and Illustrated Parts

C;ltalog changes required by this document will be incorporated at the next scheduledrevision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Istter No. 367,dated 4 January 1985, entitled "Pnrker Hnnninn Corp. Product Reference Memo (PRM) No. 96 (REY. Al", accomplished

(date)

page 9 of 3

Sevvice Letter Guifs~reamAerospace


4 January 1986

nEAVY DUTY NOSE LANDING GEAA SPACER ASSEMBLY

MODELS I\FFECrrD: MODEL 690C, SERIAL NOS. 11121 AND 11128 THRU 11734.

MODEL 690D, SERIAL NOS. 15021 THRU 15033, 15035, 15036 AND 15037.

MODEL 69SA, SERIAL NOS. 88063 THRU 96061, 96083 THRU 96012, 96075, 98071, 96078,96082, 96085 AND 86088.

MODEL 69511, SERIAL NOS. 86201 AND 96102.

REASON FOR PUBLICATION: STEEL SPACER ASSEMBLY REQUIRED DUE TO AUTOMATIC STEERINGSYSTEM REACTION TIME.

COMPLIANCE: DURING OR PRIOR TO NEXT 100-HOUR WSPECTION.

NOTE


COMPLYING WITH THIS SERVICE LETPER, CONTACT


CAUTHORIZED SERVICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A g P MECHANIC OR EQUIVALENT.

APPROVAL; ENGINEERING DESIGN ASPECTS ARE: FAA APPROVED.


PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGHYOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 916.13. REFERENCE THISSERVICE LETTER AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LETTERNO. 568 KB CONSISTING OF THE FOLLOWING:


1 as. 16W8o´•1 Spseer Aasy6 ea. ANI)GOD1OL Washer2 ea. MS21042-3 Nut

1 se. MS14865-132 Cotter Pin

2ea. NAS43DD3-12 Spaesr2 se. NAS464-3-24A Bolt1 an. Camplienee Card1 se. 6srvice Letter No. 368 hstruetians

SPEC(ALTOOLS: NONE.

Pegs 1olS

´•i

SERVICE LETTER NO. 9BB

C

MARK SPROCKET TOOTHAND CHAIN LINK TO RETAINPROPER *LI(INMENT

EXISTIN~ CRAINIREF)

NA~40DD3´•12 SPACER

12 PLSI

NOSE GEAR COLLARS M821WZ´•S NUT

IREF) 12 PLS)

WASnERce PLO

FOLLOWUPI r7

I Ir~nll´•nonl

IREFI

EXlsTlNB SHIMISIIREF) IAEF)

NAF480´•J´•24~ BOLTTOROUE 20-28 IN´•LBS SPACER ASSY

lS PLD

EXISTINGWASHER(S1(REF)

NUT(REF)

COTTER PIN

NOSE

STEERING CYLINDERIREF)

Fi~un

Page 2 of 2



1 Remove radome from fuselage nose.

2. Cain access to nose landing Bear spacer assembly through nose gear wheel well.

3. Remove existing spacer assembly from nose gear collars as follows:

NOTE

To assu,e that the nose gear steering system stays in

a~ustmsnt, do not turn nose gear during replacement of

spacer assembly.

a Mark chain and gear on follow-up potentiometer assembly sprocltet to assure that same gear tooth an

sprocket is isinstolled in same chain link from which it was removed.

b. Slip chain on sprocket and allow potentiometer arm assembly to rotate against nose gear strut.

c Remove and discard existing bolts, washers, spacers and nuts that attach existing follow-uppotentiomster assembly and nose gear spacer assembly to nose gear collars (reBr to Figure 1).

d. Remove follow-up potentiametor assembly from nose gear

a. Remove existing cotter pin, nut and washers (note location of washers) attaching nose gear steeringcylinder rod end to spacer assembly and remove and discard existing spacer assembly. Retain existingshims for reinstnllation (refer to Figure i).

f install 160080-1 spacer assembly and existing shims between nose gear collars and connect spacerassembly to nose gear steering cylinder rod end with existing washer(s) (reinstall in same location notedin step a.) (refer to Figure 1)

a´• ~ioatall arislmg s.lb,uy sa~mbly oil nea. gaer u´•ulg boil (Zplaces), ANBGOD1(IL washer (6 places), NAS43DD3´•12 spacer (2 places) and M821042-3 nut (2 places(refer to Figure 11 Torque bolts 20 to 26 inch´•pounds.

h. Rotate nose gear 450 left and right from center to assure that steering cylinder rod end does not bindon new spacer pin install washer(s) and nut, finger tighten, then back nut off one (1) castellation andthen install new MS24668-132 cotter pin.

i. Rotate follow-up potontiometer assembly and reconneot chain to sproctet assuring that mark on sproeketgear tooth aligns with mark an proper chain link.

4 Reinstall radome an fuselage nose using existing hardware. Burnish baltiattach ureas to assure radome isgrounded to airframe.

6. Functional check nose gear steering system as outlined in Chapter 32 of the Airplane Maintenance Manual.


ELECTRICIL LCAO: NO CHANGE.

WEIGHT ANO BALANCE: NO CHANGE.

SPIAES PIFFECTEO: NO.

PUBLICATIONS I\FFECTED: The Illustrated Par~8 Catalog change required by this document will be incorporated atthe next scheduled revision.

AECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.368, dated 4 January 1985, entitled "Heavy Duty Nose Landing Gear Spacer Assembly", accomplished (date)

Page 3 oTS

r´•.

~illService Letter Culfstream

Aerospace


11Janualy 1986

LANDING GEAR CONTROL ASSEMBLY LUBRICATION


MODEL 690, SERIAL NOS. 11001THRU 11079.MODEL BgOA, SERIAL NOS. 11100 THRU 11544.

MODEL B90B, SERIAL NOS. 11950 THRU 11566.

MODEL 590C, SERIAL NOS. 11600 THRU 11?29.



MODEL 69SA, SERIAL NOS. 96001 THRU 96055.

REASON FOR PUBLICATION: POSSIBLE HAND ZIP OF LEAF SPRING WHICH COULD RESULT IN LOSS OF

SAFETY LATCH FEATURE


NOTE

IF ANY PROBLEMS ARE ENCOUEF~ERED WHILECOMPLYING WITH TH1S SERVICE LETTER, CONTACTYOUR NEAREST GULFSTKEAM COMMANDERAUTHORIZED SERVICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR EqUIVALENT.


ESTIMATED MAN HOURS: ONE (1) HOUR.

PARTS DATA: MIL-G81322C GREASE MAY BE PROCURED LOCALLY.

SPECIALTOOLS: NONE.

PICCOMPL1SHMENT INSTRUCTIONS:

1. Jack airplane as outlined in the applicable Airplane Maintenance Manual.

2. Apply MIL-DdlS22C grease to not spring on landing gear control assembly. Grease is to be applied to the springsurface that comes in contact with the pin that actuates the spring (refer to Figure 1).

3. Cycle the landing gear control lever two (a) or three (S) times. After each cycle of the gear control lever, assure

that the safety locking mechanism on the landing gear control assembly functions properly. To assure that

Ianding gear control assembly is functioning properly, preeeed as follows:

a. Without touching or releasing the safety locking mechanism lever, try to pull up on the control lever.

b. If control lever will not go up without releasing safety locking mechanism, proceed to step 4.

o. If control lever will go up without releasing safety locking mechanism, cheek for correct grease

´•P’inb ´•nd rs~i´• lan(bll Br" mWI la~r ro UIU all.LI lai*.lnah´•nul. ill

landing gear control assembly is functioning properly. Safety locking lever must move freely without

Page 1 oft

ii

SERYICE LE~ER liP. S69

CENTER INSTRUMENTPANEL (REF)

~iPq

;lnY8e~I

A U!A4 4

TYPICAL GEAR CONTROL

SAFETY LOCKING I I LANDING GEAR

MECHAN18M LEVER I I CONTROL LEVER

(REF)\ I I /(REF)CENTER INSTRUMENT

PANEL (REF)

SPRING

(REF)

LUBRICATE WITHM~L-E81S22C GREASE O

0. a5" ABOVE AND BELOW PrN

pa ~EnO O

O O

VIEW A-A LANDING GEAR

LOOKING UP (REs)

rlsure i.

Page 2 ol S

SERVICE LE~ER NO. 369

d. If safety looking meehanism still does not function properly, replace existing landing gear control

aseembly with a new one.

4. After assuring that landing gear control assembly is functioning properly, removejacks from airplane.

5 Fill out and mail Compliance Card.


WEIGHT AND BI\L*NCE: NO CHANGE.

SPARES AFFECTED: All spare Lending Dear Control Assemblies (Part Numbers 640084-1, 540084-601 and 560013-1)must be pulled from shsl~staet lubricated and ehec~ed for proper operation

PUBLICPITIONS AFFECTED: The Airplane Maintenance Manual Interim Change Notice requiring lubrication of

lending gear control spring even twelve (12) months is included with this Service Letter.

RECORD COMPLIANCE: Malts an appropriate entry in airplane maintenance records as follows: Service Letter No. 369,dated 11January 1985, entitled "Landing Dear Control Lubrieetion", aeoomplishod (date)

Page 3 of 3

LettersoxCulFMlramAtms~eeCorporaIion

OXI´•blM E Nc O*lanoma 13123


4 October 1885

FREON AIR CONDITIONER COMPRESSOR BELT COVER ASSEMBLY INSTALLATION

MODELSAFFECTID: THE FOLLOWING AIRPLANES ARE AFFECTED IF FREON A~R CONDITIONING

INSTALLATION WAS PROCURED FROM THE FACTORY:

MODEL 69OC, SERIAL NOS. 11124 AND 11156

MODEL 890D, SERIAL NOS. 15006, 15010, 16011, 16019, 15025, 15025 AND 15051.

MODEL 895A, SERIAL NOS. 0802?, 98038, 98041, 96048, 96048, 98054, 98068, 98061, 96059,96061, 96065, 96088, 980?1, 98081, 96088, 98089, 8~(181, 98098, 98094 AND 98095.


PEASON FOR PUBUC~TION: TO PROVIDE A COMPRESSOR BELT COVER TO PROTECT TRIM TAB CONTROL

CABLES IF THE COMPRESSOR BELT SHOULD BREAK.

COMPLIANCE: NEXT 100HOUR9 TIME IN SERVICE.

NOTE

IF ANY PROBLEMS ARE ENCOUP~f(ED WHILE

Q: COMPLYWF 1IT~ THL8 BEBnCE IETTgR, COIYT*CT


AUTHORIZED SERVICX~ER

BY WHOM WORK WILL BE ACCOMPLISHED: A 8t P MECHANIC OR EQUIVALENT.

ESTIMP~TID MAN nOURS: ONE (1) HOUR.

IIPPROVAL: ENGIP~ERINC DESIGN ASPECTS ARE FAA APPROVED.

PARTS BATA: PARTS REQUIRED TO COMPLY THIS SERVICE LETTER MAY BE PROCURED

TIII~OUGH YOUR NEARE9T GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 819.26.

REFERENCE THIS SERVICE LE~ITER, AIRCIIAFT MODEL AM) FACTORY SERIAL NUMBER WHEN ORDERING

SERVICE LET~R NO. S10 KIT CONSISTING OF THE FOLLOWING:

Plkrual´•´•taa4´•~laMnn*-

BTY PART NO. DESCRIPTION1 as. K1250188 Cover Aaey Kit

lee Compliance Card1 ea. Service Letter No. 310 Inetructioee

SPEOIAL TOOLS: NONE.

Page 1 of 2


i. Gain access to Reon air conditioner compressor, located in aR fuselage, through baggage compartment door or

aff avionics access door.

2. Check Reon air conditioner compressor forinstallation of drive belt cover II cover is not installed, proceed to

step 3. If drive belt cover is installed, pmesad to step 4.

S. Install 1250iBB cover assembly on compressor as shown on kit drawing K12l01s0 dated November aB, 1984.


ILECTRICP~L LOAD: NO CIIANQE.

WEIGHT AND SALANCE: NO CHANDX.

SPARES I\FFECTIO: NO.

PUBLICI\TIONSAFPECTE0: NONE.

RECORD COMPLIANCE: Make an appropriate entry in ai~plans maintenance records as follows: Service Letter No.

3?0, dated 4 October 198B, entitled "Freon Air Conditioner Compressor Belt Cover Assembly Installation", accomplished(date)

C

page 2 of 2

~ervice Lettevwii* airwn

O*lahoin~ Ciry. OLI´•h.m´• .3123

SERVICE LE1TER NO. S11

24 April 1988

EXPAND TEMPERATURE RANGE OF ENVIRO SYSTEM IN AUTO MODE

MODELS AFFIOTED: MODEL 680C, SERIAL NO’S. ItBW THRU 11736MODEL 6W)D, SERIAL N(Y8. 15001 THRU 18042MODEL BBB, SERIAL NOB. 96000 THRU 86084MODEL 686A, SERIAL N(Y8. gB000 THRU 98100MODEL 68511, SERIAL NO’S. 86201 THRU 89208

REASON FOR PUBUCATION: TO EXPAM) UPPER TEMP&RATZTRE RANCE FOR MORE CABIN HEAT DURINGCOLD WEATHER OPERATIONS.

COMPLfAHCE: CUSTOMER OPmON.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILEPERFORMING THIS SERVICE LETTER CONTACT THEGULRSTREAM AEROSPACE TECHNOLOGIES SERVICE

CENTER, ?901 N.W. 50TH, BETHANY, OKLAHOMA 13008.

BY WHO* WORK WILL BE ACCOIPUSHED: A B P MECHANIC OR E9UIVALENT.

APPROVAL: ENGINEERING DESIGN ASPECTS ARE F.A.A. APPROVED.

ESTlMATED MAN HOURS: TWO (2) HOURS.

PARTS DATA: ONE (1) EACH COMPLIANCE CARD.


ACCOMPL)SHMENT INSTRUCTIONS:

1´• Remove Envim Control Panel (located below pilot’s in~trument penal) for Model Bg0C, Serial No’s. 11800 thru11?29, Model BW)D, Serial N~a. 16001 Lrulb024. Model 685; Serial Nb’n. 91000 thru 85084, Model BBM,8erial No’a. 88000 thru 98055: (lacated in center guadrant) for Model 680C, Serial No’s. ll?SO Wuu 11?96,Modal 89)D, Serial N~I1. 16026 Wru 16042, Mode! 885A, Serial Na’s. 98066 thru 98100, Model 886B, SerialNdB´• 86201 thru 88208 $BB RIBM 1)´•

a. Remove the two (2) 5.1 K Ohm ~-natt rralsters Ram the terminal of the temperature select pot Recormeetwires 8 and II to respective terminals oltampsrahua select pat (see Figure 2).

a. Reinstall Enviro Control Panel in the airplane.

4 F111 ontand mail Compliance Card.


WEI(IKC AND BAUANCE: NO CHANGE.

SPARES AFFeCTED: NO.

PUBLIC~ITION AFFECTED: The applicable Maintenance Manual Wiring Diagram and Illusbated Parts Catalogchanges required by this document will he ineolprated at neat scheduled revision.

RECORD COMPUANCI: MaLs an appmpriata entry in airplane maintenance records as follows: Service Letter Na.S?1, dated 28 April 1888, Entitled "Expanded Temperature Range .f Enviro System In Auto Mode" accomplished

(date)

Page 1012


U1SS

MWHwunL IHcn Mnx

*um 8608 LOW

MODEL 6500, SERIAL NO’S. 11800 TIIRU 11128,MODEL 8g0D, SERIAL NO’S. 16001 THRU 15024,MODEL BBB.(IERIAL NOS. BSOM) TIRU 85084,MODEL 685A, SERIAL NOB. 86000 TKRU 86055

ec=cm~

CI17~

MODEL8800, 8ERWINOB, ll?SO THRU 11155,MODEL 890D, SERIAL N0’8, leoas THRU 16042,MODEL 0g5Al SERIAL NOg. 88558 THRU 88100

MODEL 8S5B, SERIAL NO’S. 88201 THRU 88208

Plgun 1

BEFORE R8515mR REMOVALAPTERAe815TOR REMOVAL

151I II

111

i ip~n2

PagsaoPa

_ _

jService Letteroa,~ml cini, orlsnoma 73123

Service Letter No. SL312

12 Ostobsr 1989

ENVIRO SYSTEM AMBIENT VALVE REPLACEMENT

MODELS AFFECTED MODEL 690C SERIAL NOS. 11602. 11603. 11614. L1618. i 1620. 11614. 1L636. i 1638. 11640.11662, L16j6. 11663, 11664. 11669. 11613. 11676. ilBi9. 11681. 11682. 11683. L1685. 11687,11693.11101.11103. 11709, 11721.

MODEL 690D SERIAL NOS. 15004. 15006. 15007, 1IOLL. 15014. 15015. 15016. 15020. 15021,15025, 15026.15028.15032, 15039. 15042.MODEL 695 SERIAL NOS. 95003. 95006, 95008. 95016, 95022.95024, 95034. 9044. 95048. 1)5058,85060, 95061. 95(162. 95065, 95070, 95079, 95084.YODEL 69SA SERIAL NOS. 96012, 96013,96025, 96032. 96033. 96055. 95058. 96066MODEL 6968 SERIAL NOS. 96062 AND 96207

REASON FOR PUBLICAT1ON: TO IMPROVE HEATING DURING DROUND OPERATION AT LOW AMBIENTTEMPERATURES.

COMPLIANCE: WITHIN NEXT 100 HOURSTIME IN SERVICE.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYINGWITH THIS SERVICE LE1TER CONTACT THE OULFSTREAMAEROSPACE TECHNOLOGIES SERVICENTER, BETHANY.OKLAHOMA.

BY WHOM WOR~ WILL BE ACCOMPLISHED: A 81P MECHANIC OR EPUIYALENT

P~PPROVPIL: ENGINEERING DESIGN ASPECTS ARE F.A.A. APPROVED.

ESTIMATED MAN HOURS: ONE(1IHOUR.

FARTS DATA: REPLACEMENT AMBIENT VALVE MAY BE PURCHASED THROUGH YOUR NEARESTGULFSTREAM COMMANDER AUTHORIZED SERVICENTER TO OBTAIN A PARTS CREDIT.AMBIENT VALVE MUST BE RETURNED WITHIN 15 DAYS 130 DAYS INTERNATIONALLYI OFSHIPMENT DATE OF REPLACEMENT VALVE WITH A PROPERLY EXECUTED WARRANTYCLAIM AND A COMPLIANCE CARD. THIS OFFER EXPIRES 12 MONTHS FROM DATE OF THISSERVICE LETTER REFERENCE MODEL OF AIRPLANE AND SERIAL NUMBER WHENORDERING.

1 EACH PIN 1300470 AMBIENT VALVE1 EACH COMPLIANCE CARD

SPECIALTOOLS: NONE.

ACCOMPLISHMENTINSTRUCTIONS:

1. Gain aeeess to noweontrol velveaaaembly located leftofcenterline, top oPaft fuselage area through baggage door

2. Remove baggage compartmantoverheadand aR upholstery panels.

3. Remove clamp and ambient sir hose fmm Lhe noweontrol valve assembly.

4. Remove ambient air inlet iubei0nnge asrembly ileaeh 8-32 screwlsee Figure 1.

Page loE 3

SERVICELETTERNO.SL3?2

Icavno~ ICAVTION

Align mark check valve location and onentatlon between the ambient

valve and the now controlvalve. Location and orientation must not be

~hangadduringdiaassembly and reassembly.

5. Remove ambient vslvs((each 8-32screw) see Figure 1.

I CAUTION

Verify that the check valve location and orientation between theambient valve and the now control valve has not changed from

originallyaesembled.

B. Inlltall replacement ambient valve (4each 8-52 screw) seeFigure 1.Torque screws 12 to L8 inch-pounds.

Reinstall ambient air inlet tubeinanga assembly and motor support bracket to the flow control valve (4 each 8-32screw) see Figure i. Torquesrrews 12 to 15 inch-pounds.

8. Safety wire allscrews(8 each 8-32 screw)see Figure i.

9. Reinstall ambientair hose and damponthenow eontmlvalve.

10. Reinstail baggagecompartment aR andoverhead upholstsrypsnels.

11. Fill out andmail CompliancsCard.

ELECTRICALLOP.O: NOCHANGE.

WEIOHT*NDBALPIHCE: NOCHANGIE.

SPI\RESAFFECTED: NO.

PUBLIC*TIONS AFFECTED: NONE.

RECORD COMPLI*NCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.

SL372, dated _October, 1989, entitled "Envim System Ambient Valve ReplaesmenC’ accomplished(dste)

PagePoFS

SERVICELEWERNO.ILS?1

AMBIENT nlR INLET

TUBEFL~NOEASSY

O

i j

O

nMaENT vnLvs nssv

CIECKYALYE

Flplra i.

PageSofS

PN/N

COMMANDER

SERVICE LETTER~RLINOTON. WA 9823´•183:

PHONE i380) *559797 F*X(~BO)rJ5111:

SeF/ice Letter No. 376

April 25, 200(3

Inspection of Main Landing Gear Clevis and Drag Brace Installations

Models Affected: All Twin Commander Models except for Models 500, 520, 560,

560A, 560E, 680, 680E, 700 and 720

Reason for Reports from the field of cracks found in Clevis P/N ED12758

Publication: and ED12526, cracks or distortion of the mounting bosses on the

M.L.G. outer body and cracks in drag brace assembly P/N

ES12404.

Compliance: Inspection recommended prior to further flight ii the landing pear

has not undergone inspection within the last 500 Hours.

Re-inspect at 500-Hour intervals.

By whom work shall Visual and dimensional inspection to be pe(formed by ALP

be accomplished: Mechanic or equivalent. Magnetic Particle inspection and

Fluorescent Dye Penetrant inspection to be performed by a

Level II N.D.T. Inspector.

Estimated Man-hours: Estimate 8 Man hours per landing gear assembly

Parts Data: As Required: 1 ea. ED12758 and 1 ea. ED12526 per MLG Assy.

Special Tools: None

Accomplishment Instructions:

1. Jack the aircraft in accordance with the applicable Aircraft Maintenance Manual.

2. Reduce the hydraulic system pressure to zero and ensure the landing gear control lever

is in the Down position.

3. Reduce the pressure in the landing gear nitrogen blow down storage bottle to "O" PSI.

Cautionl

Do not attempt to disconnect either end of the hydraulic-pneumatic actuating

cylinders until the pressure in the landing gear nitrogen storage bottle hat been

reduced to "O" PSI.

Page 1 of 3

Service Letter No. 376

4. Disconnect the actuating cylinders from the devises on the strut and secure the cylinders

out of the way.

5. Remove the bolts that secure the clevis to the outer body and remove the clevis.

6. Replace the devises with New or perform a Magnetic Particle inspection per ASTME

1444 or equivalent.

7. Inspect the M.L.G. clevis attachment bass for obvious distortion or elongation of the

mounting hole.

8. Measure the diameter of the mounting hole and determine that it does not exceed 0.877".

9. Perform a Fluorescent Dye Penetrant inspection of the clevis mounting boss in the area

illustrated on Figure 1.

10. Perform a Fluorescent Dye Penetrant inspection of the main landing gear drag brace

assembly in the area illustrated on Figure 2.

Il.lf no defects are noted during this inspection, reassemble, rig and perform a landing gear

retraction test in accordance with the Aircraft Maintenance Manual.


13.if defects are found, contact Twin Commander Aircraft Corporation.

Electrical Load: No Change.

Weight and Balance: No Change.

Spares Affected: No

Publications Affected: No

Record Compliance: Make an appropriate entry in the airplane maintenance records

as follows:

"Ser/ice Letter No. 376, dated April 25, 2000, entitled inspection

of Main Landing Gear Clevis and Drag Brace Assembly

Installations" accomplished (Datel IAircraft Total Time) (Name)

(Cartiflcate No.~

Page 2 0(3

Service LettBi Nd. 376

Areas to be inspected i

Figure 1

Upper Brag Brace illustration

Area to Be Inspected

Figure 2

Page 3 of 3

COMPLIANCE RECORD


INSPECTION OF MAIN LANDING GEAR CLEVIS ANO DRAG BRACE

INSTALLATIONS

MODEL AIRPLANE S/N REG. NO. TOTAL TIME (HOURS)

OWNER NAME

ADDRESS

TELEPHONE NO FAx NO

COMPLIANCE WITH SERVICE LETTER 376:

DAMAGE (cRACKs, WEAR, ETC.) FOUND: YES O NO O

IF YES, DESCRIPTION AND LOCATION OF DAMAGE (CW\CKS, WEAR, ETC.) FOUND:

DATE


(SIGNATURE)

COMPANY

ADDRESS

TELEPHONE FAX



Brisbane, CA 94005 (800)227-4610


Twin Commander A/C

695, 695A, 6953

SERVICE INFORMATION

1) Applicable AD

2) Part Kit (1)



SI-11SB AUTOPILOT SERVO CLUTCH 1)

03/20/1980 SETTINGS AND APPLICABLE FLIGHT 2)SEE ISSUE

MANUAL SUPPLEMENTS 3)

4)SEE ISSUE

SI-165 VOLCANIC ASH HAZARDS 1)

06/04/1980 2)

3)

4) EXPOSURE

SI-166 AIRESEARCH MFG. CO. SERVICE 1)

10/31/1980 BULLETIN NO. 5-2288 2) 103570-5

3)

4)SEE ISSUE

SI-167 SUNDSTRAND AVIATION 1)

01/05/1981 MECHANICAL SERVICE BULLETIN 2) 724722-21-003

7247222-21-003 3)

4) SEE ISSUE

SI-170 AIRWORTHINESS DIRECTIVE 1)

02/27/1981 81-02-03, AMENDMENT 39-4017 2)SEE ISSUE

3)

4)SEE ISSUE

SI-172 POWER BRAKE VALVE ADJUSTMENT 1)

04/24/1981 2)SEE ISSUE

3)

4) SEE ISSUE


GC 0853 SI SF

1) Applicable AD

2) Part Kit (1)



SI-173 CABIN PRESSURE CONTROL SYSTEM 1)


3)

4)

SI-174 EXHAUST PIPE MOUNT REPLACEMENT 1)

07/15/1981 2)SEE ISSUE

3)

4)SEE ISSUE

SI-178 FLIGHT EQUIPMENT AND 1)

01/13/1982 ENGINEERING CORP. 2)SEE ISSUE

S.B. NO. 669-25-02 3)

4) SEE ISSUE

SI-179 PESTICIDE FUEL ADDITIVE 1)

02/01/1982 2)

3)

4) OPER DISCRET

SI-180A PARKER HANNIFIN CORPORATION 1)

06/17/1982 PRODUCT REFERENCE MEMO (PRM) 2)SEE ISSUE

NO. 25 (REVISION A) 3)

4)SEE ISSUE

SI-182 DOWTY ROTOL SE NO. 61-950 1)

06/01/1982 ALTERNATE GREASE (TEXACO LOW 2)SEE ISSUE

EP GREASE) FOR DOWTY ROTOL 3)

PROPS 4) SEE ISSUE

SI-183 IMPROVED AILERON SERVO 1)

07/09/1982 AUTHORITY -KFC 300 AUTOPILOT 2)SEE ISSUE

3)

070982 4)SEE ISSUE

SI-187 INSTALLATION AND/OR 1)

12/10/1982 MAINTENANCE OF ABRASION 2)

RESISTANT TAPE ON DOWTY-ROTOL 3)

PROPELLERS 4)


GC 0853 SI SF

1) Applicable AD

2) Part Kit (1)



SI-189B APPROVAL AND INSTALLATION OF 1)

02/24/1984 TPE331-10-511K ENGINES 2)

3)

4)0PTIONAL

SI-191 TERMINATION OF FACTORY 1)

05/27/1983 FINANCIAL PARTICIPATION ON 2)

PARTS AND/OR LABOR ALLOWANCES 3)

ON CERTAIN SERVICE PUBS. 4)

SI-193 OIL VENT HOSE ASSEMBLY 1)

08/03/1983 REPLACEMENT 2)SEE ISSUE

3)

4) DISCRETION

SI-195 DOWTY ROTOL SERVICE BULLETIN 1)

12/09/1983 61-A995 (REVISION 1) 2)SEE ISSUE

3)

4)SEE ISSUE

SI-196 SCOTT AVIATION CUSTOMER 1)

02/15/1984 SUPPORT SERVICE LETTER NO. 2)SEE ISSUE

893-SL-01 3)

4) SEE ISSUE

SI-197A AIRWORTHINESS DIRECTIVE 1)

06/15/1984 84-10-06, AMENDMENT 39-4867 2) SEE ISSUE

3)

4) SEE ISSUE

SI-199 FUSELAGE STATIONS 386.85 AND 1)

05/25/1984 409.56 PULLEY BRACKET 2)

MODIFICATION 3)

4) DISCRETION

SI-200 EXHAUST GAS TEMPERATURE (EGT) 1)

07/16/1984 INDICATOR ISOLATOR 2)SEE ISSUE

INSTALLATION 3)

4) SEE ISSUE


GC 0853 SI SF

1) Applicable AD

2) Part Kit (1)



SI-201 GARRETT SERVICE BULLETIN 1)

07/25/1984 TPE331- 73-0128 2) SEE ISSUE

3)

4) SEE ISSUE

SI-202 KING RADIO SERVICE MEMO 1)

02/14/1985 313, REVISION 1 2)

3)

4) SEE ISSUE

SI-203 INLINE PROTECTION FOR FUEL AND 1)

02/21/1985 OIL PRESSURE TRANSDUCERS 2)SEE ISSUE

3)

4) OPTIONAL

SI-204 R1 OVERBOARD ROUTING OF CABIN 1)

01/09/1987 EXHAUST AIR 2)

3)

4)

SI-205 EXHAUST STATIC PRESSURE HOSE 1)

04/08/1985 ASSEMBLY REPLACEMENT 2)SEE ISSUE

3)

4)SEE ISSUE

SI-206 NEGATIVE TORQUE SENSOR (NTS) 1)

04/12/1985 SWITCH RELOCATION 2) SEE ISSUE

3)

4)SEE ISSUE

SI-211 GARRETT TURBINE ENGINE 1) 87-24-07 R1

06/30/1986 COMPANY SERVICE BULLETIN NO. 2) SEE ISSUE

TPE/TSE331-74-0003 3)

4)SEE ISSUE

SI-212 GARRETT TURBINE ENGINE 1) 87-24-07 R1

06/30/1986 COMPANY SERVICE BULLETIN NO. 2) SEE ISSUE

TPE/TSE331-75-0004 3)

4) SEE ISSUE


GC 0853 SI SF

1) Applicable AD

2) Part Kit (1)



SI-214 EMERGENCY AIRWORTHINESS 1)

06/30/1986 DIRECTIVE NO. 86-12-02 (GTEC 2)SEE ISSUE

SERVICE BULLETIN NO. 3)

TPE331- 72-0530) 4)SEE ISSUE

SI-219 DOWTY ROTOL G.A. PROPELLER 1)

02/27/1987 DE-ICING SLIP RINGS 2)

3)

4)SEE ISSUE

SI-220 INFORMATION CONCERNING ECU 1)

03/31/1987 FAILURE 2)

3)

4)

SI-222 DOWTY ROTOL PROPELLERS 1)

04/13/1987 BLADE GROUP INTRODUCTION OF 2)SEE ISSUE

ESSO BEACON 325 GREASE 3)

MODIFICATION NO.(C)VP3179 4)RECOMMENDED

SI-223 MAIN LANDING GEAR TRUNNION PIN 1)

11/30/1987 ACCESS COVER 2)SEE ISSUE

3)

4) DISCRETION

SI-225 SUNDSTRAND ECU AIR CYCLE 1)

06/02/1987 MACHINE OIL REPLACEMENT 2)SEE ISSUE

3)

4)SEE ISSUE

SI-235 AEROQUIP AEROQUIP GENERAL 1)

08/24/1989 AVIATION ALERT NOTICE RECALL 2)SEE ISSUE

ON AEROQUIP 601 HOSE 3)

BULLETIN NO. 001 4) SEE ISSUE

SI-236 RA INSPECTION AND REPLACEMENT OF 1)

08/02/1995 FLUID LINES 2)

3)

4) RECOMMENDED


GC 0853 SI SF

1) Applicable AD

2) Part Kit (1)



SI-237 New production replacement 1)

04/14/1994 fuel cells 2)SEE ISSUE

3)

4)SEE ISSUE

SI-238 DEICER BOOT INSTALLATION 1)

01/16/1996 2)

3)

4) SEE ISSUE

SI-244 PROCEDURES FOR OPERATING IN 1)

01/27/1997 ICING CONDITIONS TO THE USE 2)

OF POWER SETTINGS BELOW FLIGHT 3)

IDLE FOR TURBOPROP AIRCRAFT 4) SEE ISSUE

SI-249 Installation of 300004-501 1)

05/18/2000 removable duct as part of SE 2)

214 3)

4) None Found

SI-251 PPG windshield moisture seal 1)

03/19/2001 installation and repair 2) CK163

procedure for installed Twin 3)

Commander Aircraft,contd. 4)See Issue

SI-252 Exhaust pipe seal installation 1)

04/03/2002 i ntructi ons 2) See Issue

3)

4) Recommended

SI-255 Picture window upper channel 1)

12/15/2003 inspection 2) 210-704-1

3) 310704-2

4) Recommended

SI-256 Main landing gear up-lock 1)

12/16/2003 assembly bolt 2)AN174C-21A

3)

4) See Issue

End of Index


GC 0853 SI SF

L --´•´•;ul-~-"1

JI? Rackweil intematlanal

Servic~ :1 ormMaaMnaml ~a na*nl *mm

m~m.gllmmlraB

ii

t’ 8~RV1CE INFORMATION NO. SI-119B

(SuprRedes 8ervtce information Na. 8I-110A dated 4 December 1918)20 March 1880

AUTOPILOT SERVO CLUTCH SETTINGS AND APPLICABLE FLIGHT MANUAL SUPPLEMENTS

MODELS AFFEF~ED!:;"’I’’I’(: MODEL 5005, SERIAL NO’S 3265 ATID rmBS., MODEL 680A, SERIAL NO’S

1lsos THRU 11348, MODEL 680B, SERIAL NO1S11350 AND SUBS., YODEL

880C, SERIAL NO’S 11BW AM) SUBS., MODEL 685, SERIAL NO’S 85000

AND SUBS., AND MODEL~OOI SERVUl)rO’S 7W01 AND 6UBS.

-38u::;;:-- r*´•-l:-: -Q:~:":-J--;.-´•-´•´•-´• ´•*´•-:--I1R´•~ rai?-( --´•~i;r;-

REASON FOR PUBLI~: TO PROVIDE A LLST OF SERVO CLIPI‘CH SETTINGS FOR AUTOMATIC

PILOTS INSTALLED ON ROCKWELL COMMANDER MODELS AFFECTED

AND THE REQUIRED FLIDHT MANUAL 8UPPLEMENTS.

COMPLIANCE: NOT APPLICABLE.

BY WHOM WORK WTLL BE ACCOMPLISHED: NOP APPLICABLE.

APPROVAL: NOT APPLICABLE.

e~TIMATED MAN HOURS: NONE.

PARTS DATA: NONE.


INSTRUCTIONS:

YO1I

The follo~ving autopllots and servo clutch settings are ~pmved:

MODEL FLT.MANUAL AUTOPILOT AILEIODN ELEVATOR RUDDER

SUPP_L_EMENI mr-lrs nN-itj)

seas a a,R.C. Apszoe 27 gs) 16 gal3 aoneg~uell H-14 (No Clutahes on H-ll)

885 4 Bend(x M-´•IC 40 g 5) 10 5) 185 (?16)(Trim) 20 (t 2)

10 Bend(x FCS-810 SO (."3) 30 (2 S)(Trlm) 30 d* 3)

a80A 1 s..mx M-4D 45 2) ~5 (iO, -4) 182 C 18)(Tdm) 20 a)

4 SIprry SPZ-100 (Electmnlo Torque Limited)7 or 8 Collins AP-106 (8ee Collins Service ~tter 11-14)

6 King KFC 300 54 C’ 4) 56 (.t 4) 135 d 13)(see KPN006-O081-01 Manual)

BOOB 5 Bendlx M-4D 45 C 21 45 -4) 182 C 18)c (Tam) to

1 Collins APIOB (8ee Collins Service Letter ii-14)

I King KFC 300 54 C 4) 95 r 4) 135 g 13)(Ses gPN000-(1081-01 Manual)

.Depenmna on FHght Director installed.

Page 1 ot 2

BERYICE INFORMATION NO. 81-1198

MOD~ FLT.MANUAL AIL~KUN

SUPPLEMENT -cii;-i:.iir

ssoc KLng KFC-500 )6 (I 10i 61 ii 6) 135 (f ii)(Tdm) 55~3)

8 Collins AP-1OB (see ColUns Service Publieatlon SIL 3-80)

(Trim136~ 13)095 1 King KFC-)OO 80 e to, 51

8 ColHne AP-1OB Lsee Collins 8ervica Publication SIL 3-80)

700 18 Collills AP-10? (8ee Calllna 8srvlce Lader AP-IO? 5-~B)

8 King KFC-aoo 32 (f 3) 46 r 5)

ELECTRICAL LOAD; NO CHANGE.

WEIOm Ir BALANCE: NO CHANGE.


RECORD COMPLIANCE: NOT APPLICABLE.

Pa~s 2 oi 2

i Rockwell intematlonal

i’ Stlrvjce onn*nNMol*wan

Mal Nonh *nnw

r SERVICE INFORMATION NO. 1-185:;4 June IsBO

VOLCANIC ASH HAZARDS

MODELS AFFECTED: ALL ROCKWELL INTERNATIONAL MODELS.

REASON FOR PUBLICATION: TO PROVIDE MAINTENANCE AND INSPECTION RECOMMENDATIONSFOR AIRCRAFT EXPOSED TO VOLCANIC ASH.

COMPLIANCE: UPON EXPOSURETO VOLCANIC ASH.

BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EpUIYALENT.


ESTIMATED MAN HOURS: AS REPUIRED.

PARTS DATA: AS REQVIRED FOR ROUTINE MAINTENANCE.



The following are excerpts from A1Resaarch Phoenlx Telex dated Map 25, 1880:

Until such time as sufficient information is gathered 0 permit more accurate assessment of the immediate and

long-term effects of operating the angina in an ash-laden environment the following recommendations shouldbe carefully considared in addition 0 those outlined in your routine maintenance program.

Recommendations

I. Whenever possible avcdd operation in known volcanic ash-laden environment. Exposure to tNs foreignmaterial Ln high concentrations or lesser concentration for prolonged periods La considered damaging tothe engine sind will likely result in increased cost of ownarship.

2. If operation in ash-Iaden regions cannot be avoided the following is recommended:

a. Engine oil filters should be examined more iraglent~y to Lnaure that abnormsil blockage is not

occurring. Would an unusupl amount of contaminate be observed in the the filter and

engine oil should be changed.

b. If oparallon in ash-ladan environment is fairly the engine oil change interval shouldbe shortensd to:

100 Hours for TPESS1/TSESS1150 Hours for TFE1S1

c. Fuel system filter should be more irequentlg examined to insure that blockage is not occurring.

d. Air fillers in pneumatic circuits associated with the AiResearch and Bendlx fuel control on

Turtdne Propulsion Engines /PS fLlter/ should be ewmined and cleaned as raguired afte. each

Right where ash was encountered.

a. Use of thrust reversing should be avoided where possible on ash-coated runways.

ri. In ash fallout areas, inlet and exhaust covers should be installed as Boon as engine cooling will

parmit. This is to ave6d introduction of ash into the static engine.

Page 1 of 4

iggRVICE NO. 8I-185

ffoTf!

Detrimental effect on the engine from volcanic ash will be

proportional to the concentration of the ash and the periodof exposure.

Relaxatlon of these recommendations in favor of more tyFdcal, routine maintenance should begoverned by

experience. The rate at which erosion is occurring within the engine may be estimated by careful examination

of tan/prop blade and compresaor blade leading edges. Thlnn(lg, sharpedllg or roughrmng of these surfaces

is indicative of accelerated erosion.

The following are Eleerp~s frdm OenerR1 Aviation Airworthiness Alerta AC Na. 45-l8:

i. Introduction. The purpose of this special alert Is to provide safety

LnformaCian and recommended actions to preclude possible airworthiness

problems associated with aircraft exgonure to volcanic ash either in the

atmosphere or on the ground. The following recommendations are based on

the best available information at this rine and will be amended as further

information and facts are gathered.

2. sac*ground. Volcanic ash from Mount st. nelens has been analysed to

contain abrasive and corrosive materials such as sulfuric acid and floride

and chloride salts and acids. Oependinq on the location of the volcanic

ash fallout. the particle sises range froma8 small as .5 microns to 100

microns. Most aircraft screens will filter out material down to 15

microns bur will pass particles that are smaller.

The ash will probably be encountered as a fine powder, li)ie talcum

powder, light grey in color. When dampened it has been reported to set

similar to concrete. Due to adhesive action of the sulfuric acid.^the

acid tends to adhere to the interface between the particles and the

aircraft structure causing corrosion. Although volcanic anh may oar be

visible on the structure, sulfuric acid may still exist causing corrosion

and it i. recommended that all aircraft that have been exposed to volcanic

fallout be given a rent to determine the acidity levels. This can be

accomplished by Ule application of nitraliine paper available from many

pharmacies. If the Ph factor is or below, it ill recommended that the

following correctlveactions be ra~en as soon as practicable.

i. Rirfranne.

(1) safety precautions including safety glasses. gloves and

protective clothing should be adhered tot

(2) ~ircrsfL should be cleaned in the following sequence;

a. The aircraft .anufaciurer’s maintenance manuals should be

followed regarding the protection of aircraft systems during the cleaning

process. The procedures recommended by the manufacturer for the

Inspection and cleaning or purging of pltot static aysr´•n~s. instruments

systems, etc., should be followed.

b. If there is any volcanic ash coating on the aircraft

structure, It should be removed by hand brushing, sir vacuum cleaning

prior to performing any washing actions. If the aircraft is washed before

removing ash, It will form a corrosive paste,

c. The aircraft should be thoroughly cleaned, inside and out,

before wanhing.

d. The aircraft should be rinsed thoroughly with freah water

without. scrubbing to ensure that all parts of the aircraft have been amplyrinsed.

e. The aircraft should be given a rest at the completion of each

wash cycle to ensure a Ph factor of above The Ph factor may be

performed by taping nitraelne paper strips on various parts of the

structure and wetting with distilled water.

Page a of 4

-i; ´•;;´•´•-´•ii-;´•;

(IERY~CE MFORMATION NO. SI-165

r. it may be necessary to repeat the wash procedures on

continuous basis in areas where fallout continues. To ensure rhaL the

sulfuric acid is neutraliled, complete the wash cycle using a petroleumbase solvent.

g. It is recommended that regardless ai the Ph factor, aircraft

exposed to volcanic ash be given a water wash as assurance againstcorrosion.

h´• Close inspection for external signs of damaged seals.

especially landing gear and landing gear actuators.

d. Systems. For all aircraft exposed to volcanic ash an the ground or

air, system checti should include LnspecLlon of piLot-staLic probes.static ports, air conditioning outflow valves and filters. generator

cooling tubes and filters, vacuum lines and filters, end externallymounted sensors, such as long wire antenna, and angle-of-attack sensors,

to remove any ash conLa.inatlon. precautionary inspection should be done

on a random basis of electronic equipment subject To cooling air co assure

need for equipment removal for removal of ash contaminaLion.

5.

(i) General. A. noted above the nature of the volcanic ash is that

it is both abrasive lin the form of fine powder) and corrosive iin the

form or acid content). Both and reciorocatinil engines may

be af~ecred. Compressor and Furbine blades suffer erosion by abrasive

particle impact. Lubrication and other fluid systems are subject to

conramination by solids and chemicals, while moving parts are subject to

abrasive wear.

The abrasive nature of the material causes rapid mechanical

damage La moving parts. Experience has shown that engines operated with

oil contaminated with the ash has caused them to fail in as few as ?O

nours after exposure.

The acids associated with the ash are soluble in ails and as such

attack engine parts resulting in rapid deteriocaiion. Engines can also be

at~acred externally by the corrosive action.

Maintenance. Engine. which have been operated or subjected to a

volcanic ash fallout need:

a. Thorough external cleaning.

b. Cleaning or changing of all oil, fuel, and other systemsscreens and/or filters and draining all sump.. Flushing and cleaning of

conLaminated fluid systems should be accomplished following the enginerecommended procedures.

c. Cleaning and scavenging of any open ranks where the ash or

cheini;al action could collect and EancentraLe.

d. Oil and fluid draining and change.

e. Close inspection for external signs of damaged seals.

f. Cleaning and inspection of accessaries and components for

contamination such as vacuum filters and regulators.

g. Following cleaning, inspection, end fluid changes the proper

operation of the engine should be verified by run-up. Frequent oil and

fluid changes should be scheduled. ouring subsequent operationtemperatures and pressures should be monitored closely far changes which

may signal problems.

h. Spectrographic oil analysis is an indicator of engine wear

and contaminarion. Comparison of analysis of early samples after cleaningwith previous analysis;eporrs can serve as an inicator of an engine’sstability.

PageSofl

IERYICE INFORMATION NO. 81-185

Recurrent inspections. Rircrafr ovners and aperalore are uigcd To

:iosely moniror aircrafi and engines. including systems. on a Continuingti16i5 and take action as deemed necessary for aircrait exposed to volcanic

csh as assurance against corrosion.

Hay 21, 1980

Right into volcaluc ash can damage windshields and aide windows by pitting due to sand blasting effect.




PUBLICATIONS AFFECTED: The Airplane Maintenance Manual changes required by this document will

be incorporated at a future date.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service

Information No. 81-165, dated( June 1888, entitled ’Yolcanic Ash Hazards", accomplished (date)

Page4o14

Rockwell internanonal

Service Information omlhnunonlm

sml hnh i~l*nll ~nu

SERVICE INFORMATION NO. 81-188

91 Ootober lsBO

AIRESEARCH MFO. CO. SERVICE BULLETIN NO. 5-2288

MODELS AFFECTED: MODELS 080A AND 500B, SEIIIAL NO’S. 11100 THRU 11688 THAT HAVEREPLACED OUTFIXIW/8AFETY VALVES BETWEEN 1 JANUARY 1880

AND 51 OCTOBER 1880, AM) MODEL 8g0C, BEIIIAL NO’S. 11800 THRU

11648, AND MODEL 585, SERIAL NO’S. 85000 THRu 85051, 85055 THRU

85035.

REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH AIRESEARCH MFO. CO. 8ERVICE

BULLETIN NO´• 5-2288.

COMPLIANCE: WITHIN NEXT 250 HOURS TIME IN SERVICE.

noT8

IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH

THIS SERVICE INFORMATION LETTER, CONTACT YOUR NEAREST

ROCKWELL COMMANDER AUTHORIZED SERVICE FACILlTY.

BY WHOM WORK WILL BE ACCOMPLISHED: A B P ME~C OR EQUIVALENT.

APPROVAL: SEE AIRESEARCH MFO. CO. SERVICE BULLETIN NO. 5-2288.

ESTIMATED MAN HOURS: INSPECT FOR DATES ONE (1) HOUR.

REPLACE OUTFLOW/SAFETY VALVE(S) S1X (5) HOURS.

PARTS DATA: Contact your nearest Rooltwell Commander AuUlodeed Facility for replacement hdnoul/8a(etyValve part number 105510-5. A credit will be issued, for each Outnow/Safetu Valve, upon receipt of old

Valve part number 1035?0-5, a properly executed Warranty Claim and a Compliance Card.

SPECIAL TOOLS: FLASHLIGHT AND INSPECTION MIRROR TO INSPECT OUTFLOW/SAFETY VALVES FOR DATE 8TAMPS.


i. Remove Flight Director and Course Indicator from left instrument pana~ to facilitate inepeelon of

Outflow/Safety Va~ves.

2. Comply dth AiReaearch Mfg. Co. Service Bulletin No. 6-2288.

WOT8

When replacing Oumow/SPieQ Valve, refer to Airplane Maintenance

Manual for bolt Lorqulng information.

3. RelnetaH Flight Director and Course Indicator an left instrument panel.





PUBLICATIONS AFFECTEDI NONE.

RECORD COMPLIANCE: Nlahre an appropriate entry in airplane maintenance recorda se follouls: Service

Information No. 81-108, dated 81 October 1BBO, entitled "1LlResearch Mfg. Co. Service Bulletin No. 5-2388,11accompllahed (date)

Pageloil

SERVICE BULLETIN

OUTFLOW/SAFETY VALVE Inspection for suspected faulty poppet

SECTION 1

PLANNING INFORMATION

A. Effectivity

This service bulletin is applicable to the 103570-5 Outflow/Safety Valvesused on GAO/Rockwell aircraft.

B. Reason

ALResearch has become aware of a potential problem which may be experiencedwith the outflow and safety valves listed in this service bulletin.

The problem area is centered around the outflow valve poppet assembly. It is

suspected that a small percentage of the poppet assemblies could fracture,and depending upon the type of fracture, could go as an undetected fault or

if a total fracture occurs it could lead to a valve failing closed.

Because of these circumstances, we are alerting our customers to perform an

inspection check of the outflow and safety valves as described in this servicebulletin.

C. Description

This service bulletin provides instructions for inspection of outflowlsafetyvalves for a suspected faulty poppet assembly. If valve has a functional testdate of 1 January 1980 through 91 August 1980 without a date stamp on poppet or

has a fracture of poppet, return valve to GAD/Roekue~l.

It is recommended that inspection of outflow safety valve be accomplishedwithin 250 flight hours after receipt of this service bulletin. Warrantyreplacement of outflow/safety valves under this service bulletin will ter-

minate as of 31 October 1981.

D. AF~roval

Governmental approval not required.

E. Manpower

Not determined.

Oct 1/BO Bulletin No. 5-2288Page 1 of 4

F. Materials Availability

Return outflow/safety valves to OAD/Rockvell through established channels.

G. Tooling Price and Availability

Not spplicsble´•

H. Weight and Balance

None

I. References

This service bulletin was prepared in accordance with ATA 100 requirements.

J. Other Publications Affected

None.

SECTION 2

ACCOMPLISHMENT INSTRUCTIONS

A. Access for Inspection

(1) Determined by Aircraft Manufacturer’s procedures.

B. Method of Valve Inspection

(1) Inspect all installed outflow/safety valves as follows:

(a) Visually check the functional test (FT) date appearing on cover of

outflow/safety valve (see figure 1) to determine if the ~T date falls

between 1 January 1980 through 31 August 1980´• If the FT date is

not within these dates and no pilysical damage is apparent, no further

action is required and outflow/safety valve is considered serviceable.

(b) If check of the FT date is between the specified date of 1 january

1980 and 31 August 1980, perform check of poppet assembly to determine

ii a date stamp appear, on surface of poppet (figure i), or ii poppet

is fractured. If poppet does not have a date stamp or is fractured,

remove and replace the outflovlsafety valve.

(c) If check of poppet assembly reveals a date stamp on poppet, regard-

less of an Ff date within 1 january 1980 through 31 August 1980 and

no physical damage is apparent, the poppet assembly is considered

serviceable and outflow/safety valve can remain in use.

Bulletin No. 5-2288 oct 1/80

Page 2 of 4

F T INK STAMPED DATE

WILL BE IN THIS AREA.

EXAMPLE: AUO 18 IsBO

I~

O

IDENTIF1CI\TION 01 F T DATE

Q

O

INI(STI\MPEO DATE WILL BE INPOPPET PART NO. MOLDED

THIS AREA NEXT TO POPPET PARTIN POPPET SURFACE

NO. OR WILL BE APPRoXIMATELY

1800 FROM POPPET PART NO.

EXAMPLE: APR1 lsBO

IOENTIFICATION 01´• POPPET DATE .II I´•.

Typical Outflow/Safety Valve

Figure 1

Oct 1/80 Bulletir. No. 5-2288 A´•PR"(´• nf L

Cc Reidentitication Instructions

None.

SECTION 3

MATERIPI~LINFORMATION

Not applicable.

Bulletin No. 5-2PBB oct 1/80

Page h of 4

oeneral Plviaum DM~n ROCkWBIIInternational

(405) 7886030

TWX: 8(08308810AB: *EROCOM

Cable: AEROCOM

-N OTICE

For Service Information No. SI-166, a credit of

one (1) hour will be issued for inspection of

Outflow/Safety Valves. If valve removal is required,

a credit of six (B) additional hours will be issued upon

receipt of a Warranty Claim form.

Rockwell internat~onal

Service Information an~l*mmoManrml Mnn aa;MI ~mua

BsnM( MUrmu nrB


6 JANUARY 1981

SUNDSTRAND SERVICE BVLLETIN NO. SE 724722-21´•003

MODELS AFFECTED: MODEL 690C; 8ERIAL NO’S. 11600 THRU 11663 (EXCEPT 11626 d 11651) AND MODEL

595, SERIAL NO’S. 86000 THRU 96044 (EXCEPT 95031).

REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH SUNDSTRAND SERVICE BULLETINNO. S8124722´•21-003

COMPLIANCE: WITHIN NEXT 100 FLIDHT HOURS (REFER TO SUNDSTRAND SERVICE BULLETIN NO.

88724122-21-009).

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILE COM-PLYING WITH THIS SERVICE INFORMATION LETI~ER,CONTACT YOUR NEAREST ROCKWELL COMMANDER

AUTHORIZED SERVICE FACILITY

BY WHOM WORK WILL BE ACCOMPLISHED: A dr P MECHANIC OR EQUIVALENT.

APPROVAL: REFER TO 8UNDSTRAND SERVICE BULLETIN NO. 88724722-21-003


NOTE

RaeLwsll International, General Aviation Division will allow

a credit of two (2) hours upon receipt of a properly enecuted

warranty claim and a compliance card while the airplane is

within the factory warranty period.

PARTS DATA: Contact your nearest Rockwell Commander Authoriled 8enica Facility furnishing them with the se-

rial number of the Enviromental Control unit installed in your airplane. Parts to comply with Sundstrand Service Bulle-

tin No. 88 724122´•11-003, will be supplied on a no charge basis until 31July 1981

NOTE

In order to furnish a matching unit data plate, the serial

number dthe ECU is essential and must be 1*mir8ed at time

oforderplacement.

SPECIALTOOLS: NONE


1. Gain access to Envimmental Control Unit, located in aft fuselage, through lower aff fuselage access door.

2. Comply with Sundstrand Service Bulletin No.SB 72472221-003.

3. Perform a prenight checkout of Envimmentsl Control System, Lrefer to Maintenance Manual, Chapter 21), ensuringsystem funotions properly and that there is no evidence of oil isalage.

4. Install acoess door on lower aft mselage.


Page 1o12


I


WEIGHTAND BALANCE: NO CHANGE

SPARES AFFECTED: NO

PUBLICATIONS AFFECTED: The airplane Maintenance Manual changes, and the Model 690C/695 Illustrated Parts

Catalog changes required by this document will be incorporated at the nert scheduled

revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Informs´•

tion No. 81-161, dated 5 January 1981, entitled "Sunstrand Service Bulletin No. S8124122´•

21-M)S, accomplished (date)

Papeaola

SUNDSTRAND AVIATION MECHANICALsuaom~auo

UN1I01 SUND8TRIND CORPOR~TION

4747 HIRRISON I\YENUL.ROC1(FORD. ILLINOIS 81101

SERVICE BULLETIN

Envirolm~ental Control Unit Replacement of Fluid Level

Sight Plug with Oil Pill Tube

SECTION I-PLANNING

i. Effectivity: Sundstrand Parr Number 7247221\ Environmental Control Unit

I Il~del ECU-II 7, serial olrmbers 001 theou8~0)6, and 101 through 179 used

on Rockwell 840/980 aircraft.

2. Reason: Field experience has shown that the present method of oil filling

causes excessive oil spillage and possible incomplete filling of the

air cycle machine.

3. Description: This service bullerin provides instructions for removal of

the presently installed fluid level sight plug and ~ring and in-

stallation of an oil fill tube. This modification will result in

improved serviceability of the environmental control unit.

i 1 4. Compliance: Within the next 100 hours of flight operation.

5. Approval: None required.

6. Plsnpover: Approximately 1 manhour will be required to perform this

replacement procedure.

7. ~steriel Cost and Availability: Contact your nearest authori~ed Rockwell

Service Center for parts availability. Parts will be supplied at no

charge until July 31, 1981.

8. Tooling Price and Availability: No additional tooling, other than that

required for normal aircraft maintenance, will be required for this

replacement procedure.

9. Weight and Balance: No change.

10. References: Sundsrralld Engineering Order 037350.

11. Other Publications Af fecred: None.

at islao 3B724722 ´•n´•003Nov 15/80 (Revfsion 1) Page 1/2 of 7

FLUIO LEVELSIGnT PLUG57915

iO-RING1832481~901

PARTS TD BEREYOVED

IIR CICLEUIZCHINE724950C 11 I I I-----

VEWB

LUBRltnTKXI PLATE DENTRICITIOI( PLATE

1002164 717704

OENVIRoNMENTnL OCONTROL uNIT

LUBRICATION NO

YIR .PNDILSPEC YFR S~RNOCIWCITI I (CU(TMIER PN I I

INSPECT I I

CHANGE 118

AVIATION SUNDSTRAND AVIPITION

DIV OF SUNDSTRAND CORPolv of SVNDSTRAND CORP

ROCKFORD, ILLINOISROCKFORD, ILLINOIS ~O us se zl-oO,

O

S8-2177-~

~aetallarion of Oil PiII Tube 731721

Figure 1 (Sheet 1 of 2)

oct 11/80 S8724722 ´•21´•003Nov 15/80 (Revision I) Page 4

-~Zon. FILL TUBE

731721

FITTING731722

O-RINGM83248-1-907

VIEW 1

TUBE PLUGLlS24404D6

LOOP CLIMPMS21919DG8 LLY WASTIER

AN960PDIOL

WASTIERSCREWN*S1351-~-10P

LOOP CLAMPU521919H20

NUTY521043-3

OIL FILL TUBE731721

VIEW B I191NCH BELOW

IND P~RBLLELTO BOTTOM OFMPT D(CWNGER

S8-2178

Inet´•ll´•fion of Oil Fill Tube 731721

Figure I (Sheet 2 of 2)

S8724722 ´•2\´•003oct 15/80 Page 5

1O. Reidentify environmental control unit as follows:

A. Remove old identification plate (717704) from environmental control

unit.

WARNING: METHYL ETHYL KETONE IS TOXIC AND PLAMMABI.E. W NOT BREATHE

VAPORS. USE IN WELL VENTILATED AREA FREE FROM SPARKS, FLAME,OR HOT SURFACES. WEAR SPLASH GOGGLES. SOLVENT-RESISTANT

GLOVES. AWD OTHER PROTECTIVE GW\R. IW CASE OF EYE CONTACT,PLUSH WITH WATER AND SEEK MEDICAL ATTENTION. IN CASE OF SKIN

CONTACT, WASH WITH SOAP AND WATER.

8. Remove old adhesive by cleaning surface, where identification plate

(717704) was located, with methyl ethyl ketone, Federal SpecificationTT-H-261.

C. Piece dauble-bacled, pressure-sensitive tape on back of identification

plate (717704), and position identification plate on environmental

control unit as shown in Figure I of this service bulletin.

Il. Check lubrication plate (5002164) for time between oil inspections. If the

number in the INSPECT block greater than 25, replace lubrication plate as

follows:

A. Remove old lubrication plate (5002164) from envirowental control unit.

WARNING: METHYL ETHYL KETONE IS TOXIC AND FLI\HHIIBLE. DO NOT BREATHE

VAPORS. USE II WELL VENTILATED AREA FREE PROH SPARKS, FLAME,OR HOT SURFACES. WEAR SPLASH GOGGLES, SOLVENT-RESISTANT

GLOVES. AND OTHER PROTECTIVE GEAR. IN CASE OF EYE CONTACT,PLUSH WITH WATER AND SEEK MEDICAL ATTENTION. IN CASE OF SKIN

CONTACT, WASH WITH SOAP AND WATER.

R. Remove old adhesive by cleaning surface, where lubrication plate(5002164) was located, with methyl ethyl ketone, Federal SpecificationTT-M-Z61.

C. Place double-backed, pressure-sensitive tepe on back of lubrication

plate (5002164), and position lubrication plate on environmental control

unit as shown in Figure I of this service bulletin.

act Lrlao S8724722 ´•n´•o 03Nov 15/80 (Revision 1) Page 6

SECTION III- MATERIALS INFORMATION

pty Unit

Per List DlspositionlNew P/N ECU Price Key Word Old e/N InstructionsNew P word

7247228 N/~ NIA Environmental 724722A Modify and

(Note 1) Control Unit identify

None 1 N/A Fluid Level 57915 Remove and

Sight Plug discard

Same 1 N/A ~ring M83248- Remove old.1-907 install new

731721 1 N/A Oil Fill Tube None install

731722 N/A Fitting None install

MS21919DG6 1 N/A Loop Clamp None Install

nSZ1919H20 1 N/A Loop Clamp None Install

HS24404D6 1 N/A Tube Plug None Install

NAS1351-3-10P 1 N/A Socket Head Cap None Install

Screw

AN960PD10L 2 N/A Flat Washer None Install

HS21043-3 1 N/A Self-locking Nut None Install

Same 1 N/A Identification 717704 Remove old,

Plate install new

Same I N/A Lubrication 5002164 Remove old.

(Note 2) Flare identify.install new

Note 1: Environmental control units retrofitted according to this bulletin

are identified by the identification plate marked with the symbol8821-003 and part number 7247228.

Note 2: If the number in the INSPECT block is greater than 25, lubrication

plate must be replaced. The lubrication plate will not be sent with

the oil fill tube end associated components. If a new lubrication

plate i. required. order through the nearest euthoriaed Rockvell

Service Center.

oct 15/8088724722 ´•21´•003

Nov 15/80 (Revision 1) Page 7

S

_ _

Service Information GulFstreamnmericanunarol*1´•loa

Cannmand´•r Dlrilia

M)01 Norm Rostwall Avsnus.B~many´• Otlahonu 73(138

SERVICE INFORMATION NO. SI-l?O

27 FebNary 1981

AIRWORTHINESS DIRECTIVE 81-02-03, AMENDMENT 39-4017

MODELS AFFECTED: MODEL 690A, AIRPLANE SERIAL NOS. 11249, 11269 THRU 11344. MODEL 690B,AIRPLANE SERIAL NOS. 11350 THRU 11546, MODEL 690C, AIRPLANE SERIAL NOS. 11800 THRU 11860 AND

MODEL 685, AIRPLANE SERIAL NOS. 95WO THRU 96040.

REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH AIRWORTHINESS DIRECTIVE 81-02-03.

(REFERENCE ZMR 151, PURITAN-BENNETI~OXYDEN MASK.)

COMPLIANCE: REFERTO AIRWORTHINESS DIRECTIVE 81-02-05.

MOTE


PLYING WITH THIS SERVICE INFORMATION CONTACT

YOUR NEAREST GULFWREAM COMMANDER AU-

THORIZED SERVICENTER FACILITY.

BY WHOM WORK WILL BE ICCOMPLISHED: REFER TO AIRWORTHINESS DIRECTIVE 81-02-05.

APPROVAL: REFERTO AIRWORTHINESS DIRECTIVE 81-02-03.

ESTIMATED MAN-HOURS: 81-02-03.

PARTS DATA: REFERTO AIRWORTHINESS DIRECTIVE 81-02-03.

SPECll\LTOOL%: REFERTO AIRWORTHINESS DIRECTIVE 81-0203.


I. Comply with Airworthiness Directive 81-02-03.


WEIGHT AND BALANCE: NO CHANCE

SPARES: REFERTOAIRWORTHINEIS DIRECTIVE 81-12-03.

PUBLICATIONS AFFECTED: NONE

RECORD COMPLIANCE: Make an appropriate entryin airplane maintenance records as follows: Airworthiness Di-

rective 81-02-05, Amendment 39-4011, effective 21 March 1981, accomplished (date)

Page lofl

PVRITANBENNEIT AERO SYSTEMS

Ain~orthinesP Dirretive

Vl,hale, IhII

81-02-0) PURITAN-BENNETT AERO SYSTEMS COMPANY; Amendment 39-4017. Applies to Puritan-Bennett Aero Systems Company oxygenmasks P/N 174039, 174010-01, 174010-03, and ZMR 100 series as

listed below.

for P 174039

S/N for P/N 174010-01 and 174010-03

146, 147. 109,00150 through 00194195 through 259

261 through 2’73

275 through 292

S/N for P/N 2?IR100 series

Compliance required as indicated, unless alreadyaccomplished

causing eitbeeTo prevent the regulator inlet valve from

leakage or positive pressure within the facecone, accomplishthe following;

(a) Within 120 days from the effective date of thisAirworthiness Directive, remove diaphragm assembly P/N F334-1001-1 and install diaphragm assembly P/N F334-1001-1 modifiedto include diaphragm and plate assembly P/N f334-1003-1.8evision E.

(b) After modification per paragraph (a) of this AD,permanently mark letter "M" at the end of or beneath the maskserial number. This serial number is located under the facecushion on the left-hand side of the hardshell on the 194039and ZMR100 series masks, and on the back surface of the headharness on the 174010-01 and 174010-03 masks.

(c) The modified diaphragm replacement of paragraph (a)of this no shall be accomplished by returning the mask to

Puritan-Bennett Aero Systems Company, 111 Penn Street, El

Segundo, California 90295. However, this replacement in theZMR100 series masks listed below may be accomplished in the

field in accordance with the following Puritan-Sennett Aero

Systems ATA Component Maintenance Manuals;

)5-10-25 for the ZMR1S0 mask

35-10-27 for the ZMR129 mask35-70-28 for the ZMR129-1 mask

35-10-29 for the ZMi~lls mask

Pagelofa

NOTE: Purftan-Bennett Aero Systems Company Service Bulletin

No. 1, dated April 15, 19801 pertains to the subject of this

Airworthiness Directive.

(d) Alternate inspections, modifications, or other

actions which provide an equivalent level of safety may be

used when approved by the Chief, Engineering and ManufacturingBranch, FRA western Region.

This amendment becomes effective March 20, 1981.

Page 2 of 2

.r

P~IIService

Commnndar Dlviuon6001 North Roe*wsll /Wsnu~.sathany. Oklahoma 73(3(18

SERVICE INFORMATION NO 51-172

i 24 April 1981

POWER BRAKE VALVE ADJUSTMENT

MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11800 THRU 11663 AND MODEL 695, SERIAL NOS. 95000

THRU 95051.

REASON FOR PUBLICATION: TO ASSURE PROPER ADJUSTMENT OF POWER BRAKE VALVES.


MOTE


PLYING WITH THIS SERVICE INFORMATION LET~ER.CONTACT YOUR NEAREST DULFSTREAM COMMAN-

DER AUTHORIZED SERVICENTER FACILITY.

BY WHOM WORK WILL BE ACCOMPUSHED: A 8~ P MECHANIC OR E9UIVALENT.

I\PPROYIL: NOTAPPLICABLE.

ESTIMPITED MAN HOURS: ONE AND ONE-HALF (1.6) HOURS.

PARTS DATA: 1 EA. COMPLIANCE CARD.

SPECIALTOOLS: TWO (2) HYDRAULIC PRESSURE CAGES WITH O TO 1000 PSI CAPABILITIES.


1. Reduce hydraulic system pressure to zero and disengage parking brakes.

2. Remove pressure cap from tee fitting installed on brake line above each main gear brake assembly (refer to Figure1).

3. Install a hydraulic pressure gage, with O to 1000 psi range, at each tee fitting.

4. Connect a 28 volt de e~tarnal power source to the airplane electrical system at the external power receptacle.

5. Place battery switch in BA1TERY position.

MOTE

The au~ilian hydraulic pump should operate and a hydraulicpressure of 615 to 606 psi should be indicated on instrument

panel hydraulic gage.

6. With brakes released, observe tee mounted hydraulic pressure gages. Pressure should indicate zero. If any pres-

sure is indicated st either gage, proceed to step 8.

7. If pressure is zero, with brakes released, operate brakes with normal toe pressure on brake pedals to obtain 615

to 605 psi on tee mounted pressure gages. Remove tee pressure from brake pedals and brake pressure should im-

mediately drop to zero. If gages indicate zero pressure, proceed to step 13., but if any pressure is indicated on tee

mounted pressure gages, after release olbrakes, proceed to step 8.

8. Check all castellated nuts on rudder pedal installation to assure that no binding occurs when pedals are released.

Page 1eIS

SERYICE LNFORMATION NO. 81-1?3

i-

;I’2

ail~

LANDING GEAR (RLFI

LEFT INSTALLATION SHOWNINSTI\LL HYDRP~ULIC

RIGHT INSTALLATION OPPOSITEPRESSVRE GAGE ON

THISTEE

Fipuie i.

g~ Remove access door, located on lower lan aide of nose section st f\lselage station d.50, to gain access to power brake

valves.

10. Loosen adjusting Checknuts on power brake valves and slowly turn pressure adjusting setscrews rountercloeltwiss

until indicated pressure on tee mounted pressure gages drops to sere. Turn pressure adjusting setscrews eounter-

clockwise one additional full turn and secure adjusting chrknuts (refer to Figure 2).

11. After adjustment, operate brake pedals using normal toe pressure. A brake pressure of 515 to 605 pi should be

observed. Removetae pressure from brake pedals and brake pressure should immediately drop to sere.

12. Reinstall access door.

18. place battery switch in OFF position.

page 2915

BERVICE INFORMATION NO. 81-112

PREhSUREADJUSnNOCHECKNUT (REF)

PRESSURE ~DJU1TINO

SETSCREW IREF)POWER BRAKE YALYE IREFI

figure 2.

14. Remove hydraulic pressure gages from each brake line and cap tee Bttings.

15. Assure that hydraulic system is functioning properly.



WEIGHT AND BPILINCE: NO CHANGE.

SPIRES AFFECTED: NO.

PVBLICATIONS P.FFECTED: NONE.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Information

No. 81-1?2. dated 24 April 1981. entitled "Power Blake Valve Adiustment", accomplished (date)

page )ofS

_

%er\8ice information Gulfsh´•eamAmericanCOIPOR*TION

DmmndrMvklm

6WI Nad, Ros~vall ~vsnul.Fnh´•ny, O*l´•h~ma IJms


16JulylsB1

CABIN PRESSURE CONTRM SYSTEM rODIFICATION

UM)ELS AFACTED: MODEL 8800, SERIAL NOS. 11880 THRU 11686 AND MODEL 886, SERIAL NOS. 86088

THRUssOB7.

RUSON FOR PVSLCPITION: TO DIMINISH CABIN RATE 8URGE UPON LANDING.

COMPLIANCE: AT OWNERS DLSCRETION.

*OTO

P ANY PROBLEMS ARE ENCOUNTERED WHILE COM-

PLYING WPPH THIS SERVICE INFORMATION, CONTACT

YOUR NEAREST GULLSBREAM COMMANDER AU-

THORIZED (IERVIC&NTER.

BY WHOM WORKWILLBE*CC(~PLISnED: A6L PMI~CHI\MC OREQUIVALENT.

APPROVAL: FAA DOA 8W-Z APPROVED.

ESTII~D MIN nOUR9: ONE (1) HOUR.

PARTS DITA: PART8 REqUIRED TO COMPLY WITH THIS SERVICE INRORMATION MAY BE PROCURED

THROUGH YOUR NEAREST OULFB~TREAM COMMANDER BERVICE~EI( AOR (20.88. REFERENCE THIS SER

VICE INFORMATION, AIRCRAIT MODEL AND FACTORY 8ERIIU. NUMBER WHEN ORDERING SERVICE

FORMI\1?ON NO. 81-118 KIT CONSI8TING OF THE AOLUIW~JO:

aTY PARTNO. DESCRIPTION

1 as. BOM)91´•LD?6 ResWetor

1 se. Compliana, Card

1 ea. 8ervi~a inf~nnation No. SI1?S inst~uction

SPE0IiL TOOLS: NONE.

Page 1 olJ

(IERVICE INFORMATION NO, 81-113

ACCOMPUSHMEM INSTRUCTIONS:

i. Push pilot’s seat as far aft as possible.

2 Push copilot’s seatas farforwardas possible.

3. Lean copilot’sseatback forward.

4. Pull pilot’s control wheel back and secure.

5. Cain secess to existing ANB164D nipple, looated under instrument panel on depressurieation control shutoff valve,by laying slang side of pilofs wat.

B. Disconnect existing tube assembly (Pi~ 880649´•33) from shutoff valve nipple (refer to Figure i).

Remove and discardexisting depressuri~ation control ahut~RValue nipple (P~ ANB18-4D1 (refer to Figure ii.

8. Apply tenon tape (3M No. 511 or eguivalent) to tapered threads of 8000S1´•(D-15 restrictor as follow.:

a. Place tenon tape two (2) threads in from end of tapered threads and hold tap firmly with thumb.

b. Stretch tap against threads and wind clockwise one (1) lap. Continue to hold tightly against threads until tapehas been broken.

NOTE

Do not attempt to tear tap sideways. Snap tape off in same

direction used for winding.

9. Install an ANB29-4 cap assembly (obtain locally) on end of 800037-4D-75 restrictar opposite tenan tape to facilitateinstallation of restrictor on existing shutoff valve,

10. Install 900037-41)´•76 restrictor on existing shutoff valve, remove AN929-4 cap assembly, malting sure that resCic-Dr doss not turn, and connect existing tube assembly to rnstrictor (refer to Figure i).

ii. Functionally check pressurieation system to assure there are no leaks.

12. Release pilot’s control wheel.



WEIGHT AND BAU\NCE: NO CHANDE.


PUBLICPITIONS AFFECTED: The Model B9OC/685 Illustrated Parts Catalog change required by this document will be


RECORD COMPUINCE: Make an appropriate entry in ai~lane maintenance records as follows: Service InformationNo. 81-113, dated 18 July 1981, entitled’%abin Pressure Control System Madifioation", accomplished (date)

Page 2 al S

BERVICE MFORMATION NO. 81-115

WTFLOW/S~CETY(REF1

I-r::: n BULKHEI\DIREF)

i: iRELIOVIEXI~IN.*NBI04D NIPPLEP~ND REPLI\CE WITHBWOa74D´•ll RESTRICTOR

‘B

DEPRhSSURIZATION -CC-L~ //YM)NTROLBHUTDFF

VI\LVE IREF)

EX18TIN08808)8JJTUBE ASSY IREF)

Flpra i.

Page S of S

~j"llService

CORPOR*TION

Csmmada aCr,lonMKII Norm Roo)irmll ~vsnus.Bsmany. Olshoma 13W8

SERVICE INFORMATION NO. SI-l?l16 July 1981

EXHAUST PIPE MOVNT REPLACE~ENT

MODELS AFFECTED: MODEL 880C, SERIAL NOS. 11BW THRU 11687 AND MODEL 886. SERIAL NOS. 86000

TWR~ 86028, 86080 THRU 06081.

MOTE

PI 18 RECOMMENDED THAT 8ERVICE INFORMATIONNO. 81-1?4 BE ACCOMPLISHED WHILE COMPLYING

WITH SERVICE BULLETIN NO. 188.

RIASON FOR PUBLICATION: TO REDUCE TAILPIPE VIBRATION BY PROVIDING BETTER ISOLATION

BETWEEN TAILPIPE AND AIRFRAME.

COMPUAHCE: A~041NERSD18CRETION.

MOTE


COMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST DUL~AM

COMMANDER AUTHORIZED 8ERVICENTER.

BY WHOM WORK WILL BE ~CCOHPUSHED: A dr P MECHANIC OR EQUIVALENT.

APFROVAL: FAA DOA SWZ APPROVED.

ESTlMATED MAN HOVRS: FOURTEEN (14) HOURS.

PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCURED

THROU(IH YOUR NEAREST CIULF8TRF~AM COMMANDER EIERVICENTER FOR: KIT NO. 1 8404.11 OR KPI~ NO.

2 -8484.11. REFERENCE THIS 8ERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER

WHEN ORDERING SERVICE INFORMATION NO. 81-114 KIT CONBIEITING OF THE FOLUIWINGI:

Kit Ne. 1 Model 680C

KitNo. 2 Model 886

Kit Kit

No.l Na.e

4TY BTY PARTNO. DEBCRIPI~ION

2es. 8I0B61-RES Channel Aasya as. 010a61-REs Channel Aasy

II ea. 4ss. B1~BB1-RE11 Washer

18ea. 16aa. BIOBS1-RE1B Pad

las, dsa. 810882-68 specsr8ea. 24U)B´•1 Mount

4ea. 4sa. AN4-l2A Bolt

Bea. 8sa. ANBBO-10 Waahar

Page 1 o( 6

SFRVICe INIDRMATION NO. 81-114

UPPER COWLIN(ISHELL

EXHAUST PIPE

EXTENSION ASSY

EXHAUSTPIPEASSEMBLY

d

FORWARDFAIRING

LOWER

NOSE RING COWLING

ASSEMBLY SHELL

EXHAUST

PIPE

ASSY

CLAMPS

ENGINEEXHAUST

PIPE

DlnPHRPI(IM

BOLT

DOLLAR

ENGINE

r: EXHAUSTSEAL

WASHER

NUT

PI~Zm 1.

PasaolB

5WVICE lNPORMATlON PSO. 81-174

4sa. 4ea. ANBBOCIIGL Washer

18 as. 16 as. ANI)?O´•8 Washer

4sa. 4 se. MS20500-428 Nut

8 ea. 8 as. M8205001032 Nut

8ea. 8aa. MS210SgC1-08 Screw

8 as. 6sa. M82103BC1-10 Screw

1 sa. 1 ea. Compliance Card

1 ea. 1 se. Service information No. 51-174 instructions

9PECI~LIOOL9: NONE.

PICCOMPLISWMENT INSTRUCTIONS:

1. Remove leR and right engine exhaust pips assembly as follows (refer to Figure 1):

a. Remove the fonuardfairing.

b. Remove upper end lower engine cowling shells.

c. Remove exhaust pipe extension assembly.

WOTB

There are four (4) screws, accessible from inside the main

landing gear wheel well, that secure the exhaust pipesxtension assembly to the engine nacelle.

d. Remove both clamps from seal and Bid seal aft towards the diaphragm.

a. Remove nuts, washers and bolts that secure the exhaust pipe assembly to the engine exhaust pipe´•

f Support exhaust pipe assembly and remove nut, washer, bolt and spacer ham channel that is located on aft

inboard side of exhaust pip asssmbly.

8´• Turn exhaust pipe assembly slowly and remove from aft side of diaphragm.

2. Drill out rivets attaching existing left and right exhaust pipe assembly attach channels to nacelles and mark

centerline on existing channel (refer to Figure 2).

3. Neat existing channel into new channel assembly so that centerline of sxlsting channel is on centerline of new

channel assembly, position forward end of existing channel flush with forward end of new channel assembly and

clamp channels together. Referenoe.oenterline of holes in existing channel must be 0.44 inch from sft end of new

channel assembly (refer to Figure 3).

WOTE

Centerline is marked on each end of new channel assembly.

4. Drill four (1) 0.192 (+0.002) inch diameter holes through hales in existing channel into new channel assembly (refer

to Figure 3).

5. Drill existing hole. in nacelle to 0.182 (r0.002) inch diameter and install 610651-RES channel assembly (Model

6g0C) or 610661-RES channel assembly (Model 886) on nacslle using MS27038C1-08 screw (4 places), AN960-10

washer (4 places) and MS206001032 out (4 places) (rsfer to Figure 4).

page 9 of B

IERVICE INE~DRMATION NO. 81-1’14

LEFT INITALLATION SHOWN

RIGHT lN9TALLATION OPPOSITE

EXISTING FRAME IREF)

EXHAUSTPIPEEXTENSION (REF)

ii’

-E

EXHAUST PIPE (REF1

MARK CENTERLINE ON

EXISTING CHANNEL

Pllun 2.

1 o,-

ASSURECHANNELSARE FLVSH I\T

MIS END

aleo~´•ro.l8l"om.HOLE U PLS)

EXISTING CHANNELBIM~I´•RIS CHANNEL ASSY

OR

B(~BI´•REI CHANNEL ASIY

FlpnS.

PsgelolB

BERVICE INFO~N NO. 81-114

LEFT INSTALLATIONSHOWN EXHAUST pl/’" FIPICELLE IREF)

RIGHT INSTALLATION OPPOSITE EXTENSION IREFI

MSnM8C1´•108CReW*NB1OSW~HER

BIOBS1´•REIBPAD

IONE PAD INSIDE AND ONE

VIEW kA PADOUTSIDEL(1 PLS)

AN87a3WkSHER

IBETWE~N PAO

ANO MOUNTING BRIZCIET)

EXISTING FRAME (REF)

EXHAUSTPIPE1\ EXTENSION IREF)

t~

~ii

EXHAUST PIPE (REFI

ATOROUE BOLTSI IN´•LB9 OVER

RUNNING TOROUE

OF NUTS_

NACELLE IREF)

MU-12ABOLT

EXHAUSTPIPE nOB~(-RE(( WASHER IUNDER BOLT HEAD)4111&( MOUNT 12 REED)

M1BBOUIIL WASHER (UNDER NUT)MS2MW428NUT

I)PLS)

VIEW B-ll DlA.HOLE

MRU EXISTING RIVET LOCI\TIONI M9nmBC1~088CREW

~NB(HI´•(O WASHER IUNDER NUTIMSMMlOlm2NUT

IIPLS)

BIOBII´•RES OHANNEL IMODEL BBOC)OR

BIOB~IIREICH*NNEL IMODEL BB(i)

Flpral

PsgelolB

BERVICE MPORMATION NO. 66-1?4

8. Reinstall exhaust pipe assembly on airplane as &:iuwi (raBr to Figure i):

a, insert exhaust pip assembly through diaphragm and position for attaching to engine exhaust pipe

b. Align holes in forward miler and exhaust pipe assembly with thane in the engine exhaust pip and install bolts,

washers and nuts.

NOTE

Washers and nuts are installed on Forward side of R~ant

miler. Use wedge between outer akin assembly and exhaust

pipe assembly sprevent turning or twisting of exhaust pipeassembly during installation procedures. Tighten mts to a

torque value of 60 inch-pounds.

c´• 8snne aRend of exhaust pipe assembly to near channel assembly using 610852´•59 spacer (2 placesl, ANb12A

bolt (2 plama), 8108B1-REI1 washer (2 places), 242881 mount (1 places), ANBBOC418L washer (2 places) and

M920S(X)-1032 nut (2 places) (rsfer to Figure 1).

d. Slide pip extension as~mbly over exhaust pip assembly end position for securing to engine nacelle.

a. Install MB21038C1-10 sorew (4 places), ANI?OJ washer (8 places) and B1OBSI´•RE19 pad (8 places) that secure

the exhaust pipe extension assembly (refer to Figure 4).

NOTE

The B1~BS1-RE1D pads are furnished ´•niW1 no screw blee.

Use sharp tool, as required, to open a hole in center of padmesh.

f Unfold seal and position over Rent collar and secure by installing clamps.

B´• Install forward fairing.

h. Install upprand lowersnSineeawlin~shdle.

Fill outand Mail Compliance Card.


WEIGHT AND BPILANCE: NO CHANGE.


PUBUCmONS IFFECTED: The Illustrated Parts Catalog changes required by this document will be inmrprated at


RECORD COMPLIINCE: Make an appropriate entry in airplane maintenance records as follows: 8ervice

No. 91-1?4, dated 16 July 1881, entitled’gxha~st Pipe Mount Replacement", accomplished (date)

Page Bol 0

Service Information GtdfstreamAmei,canEORI’ORITII)N

i6W1 Norm Roclwall ~usnue.

B~mlny´• O*l´•homa ’IJWB

SERVICE INFORMATION NO. SI´•178

13 January 1982

FLIGHT EOUIPMENT AND ENOINEERINO CORP. SERVICE BULLETIN NO. 669-25-02

MODELS P.FFECTED: MODEL 0gBA. SERIAL NOS. 86W1 THRU 8M)Z1.

REASON FOR FUBL(CATION: TO RECOMMEND COMPLIANCE WITH FLIGHT EQUIPMENT AND

ENGINEERING CORP. SERVICE BULLETIN NO. 668´•25-01.

COMFLIANCE: REFER TO FLIGHT EQUIPMENT AND ENGINEERING CORP. 8ERVICE BULLETIN

NO. 669-25-01.

BY WHOM WORK WILL BE PICCOMPLISHED: A L P MECHANIC OR EQUIVALENT.

APPROYAL: REFER TO FLIGHT EQUIPMENT AND ENGINEERING CORP. SERVICE BULLETIN NO. 668-25-02.

ESTIMATED MAN HOURS: 8M (6) HOURS.

NOTE

OULFSTREAM AMERICAN CORPORATION WILL ALLOW‘A CREDIT OF SIX (6) HOURS LABOR UPON RECEIPI~ OF

A PROPERLY EXECUTED WARRANTY CLAIM AND A

COMPLIANCE CARD.


THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED 8ERVICENTER FOR (100.00. A FULL

CREDIT WILL BE ISSUED UPON RECEI~T OF REMOVED ORIGINAL ROLLERS AND FITPWCS, A PROPERLY

EXECUTED WARRANTY CLAIM AND A COMPLIANCE CARD. REFERENCE THIS SERVICE INFORMATION,AIRCRAW MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING). SERVICE INFORMATION NO 81-1?8

KIT CONSISTING OF THE FOLLOWING:

NOTE

Parts are for crew seats only.

C3TY PART NO. DESCIUPI~ION

Id ea. 51245 Track Fitting52 as. 83425 Track Roller


1 ea. Service Information No. 81-118 instructions


NOTE

This modification applies only to the crew seats. Cockpitdividers must be removed in order to remove seats.

Pegslofi)

BERYICE INFORMATION NO. 81-118

i. Comply with Flight Equipment and Engineerng Corp. Serivee Bulletin No. 689-25´•02.

NOTE

Disregard step 3B. orService Bulletin No. 688-26-02.

2. Fill out and mail Compliance Card with Warranty Claim and all removed original rollers and fittings to Dulfstream

American Corporation, Commander Division, 5001 North RooLwell Avenue, Bethany, O~lahoms 13008.




PUBUCATIONS AFFECTED: NONE.

RECORD COHIPLI~NCE: Mslte an appropriate entry in airplane maintenance records as follows: Service Information

No. SI-118, dated 13 January 1982, entitled "Flight Equipment and Engineering Corp. Service Bulletin No. 669-26-02"

accomplished (dste)

Page i al 2 ~Y

F

-C~1. II. *s~u(11´• uL h´• 1.11 D*

SERVICE BUL LETIN

I M ODEL: 669_ ID nNo 669-if SINGLE PILOT SE ATS

NG: 6 6 9 -2 5 02 DATE Nov 16. Is a I

SUAJECT´• F -OOR TRACK FITTING AND

R OL L E R RE PL ACE MENT OF

r ORBG1S~IL 1As R@csived By

I. ATP i

669-25-02

PAGE I CF 4

FLIGHT EOUIPMENT

SERVICE BULLETIN1. planning Information

Elfec ti~i ty

The follo*ing 669-10 and 669-1B pilot seat assembliesare affected by this ser~ice bulletin modification,

nodel No. De a crip tion A ffe o ted se rial No

669-101 pilot Seat 22 576 thru 22589669-1DR Co-P ilot Seat 22609 thru 22622, 2353266P-1R. Pilot Salt 23372 thru 23380669-1FR Co-P ilo t Sea t 23L37 thru 23443

B. Reason

To eliminate interference betueen the bottom surface of.the seat base frame and the top surface of the aircraftfloor track.

C. Description

l~ha existing seat track iittlngs and rollers ire to De

replaced vith ~itting. and rollers that vill prc~idemore distance betueen the base frame and floor trick.4he nex fittines hr~s a thinner lip engaging the trackand the rollers are of a larger diameter.

D. Compliance

It is recommended that the vork outlined herein beaccomplished Pt the first opportunity Pinilpble.

E. blpro~P1

The only appro*al required and obtained, is the minimumPllovn~lt thickness of the seat track fitting 1ip tocomply vith required loads. Stress annlysis vas performedand Ppp~Cled by F´•l´•*´• D´•E´•R´•

F. nanpower

It is estimated that the time required to perform thismodification is 20 minutes per seat unit.

0. nnteriil

the sent trnck fittlnes and rollers vill be pro~ided byplight Equipment upon request at no charge.

F~il-llhL 1sa~. 16 19a1 As i-i~:ujvod By 669-25-02

L ATP i2

FLIGHT EOUIPMENT

SERVICE BULLETIN

Deli~cry dates after request far parts will be ppprox~-

mately three to Four weeks.

H. Tocline

No special tooling required.

I. Weight and balance

The affect to weight and balance is negligible,

2. A ccomplishmen4lnstru4´• tiona

A. It is recommended that the following modification be

accomplished during routine maintenance functions.

The sent unit is to be remored from the aircraft and

relocated at an appropriate work area.

Refer to Figure 1 for modification coordination,

i. the eristlnp track fittines, railers and

roller spacers by undoing the appropriate nuts

and withdrawing the sight cla~is bolts holdingthem tF the base Frame. Retain the steel spacers,

bolts, nuts and washers for reuse. Dispostion of

remo~ed fittinRs and rollers per section 3.1.

2. Install the new fittinps nnd rollers to the base

frame with the obo´•e retained spacers and hardware.

For identification purposes, the new fittinga hn~e

a lip thickness or .105/.110 inches and the new

rollers a diameter of .720/.?25 inches.

3. The assemblied sept unit should be checked in the

aircraft seat track to ensure smooth operation.With weight on the seat bottom cushion, loosen the

nuts holding the track fittinas slightly and re-

tighten firmly while the weight on the seat bottom

is mnintnincd.

3´• np terial Informati on

A. part Number Puan ti ty Das crirtion

312 L5 Pi ttin g- Tr ack

33L25 16 iloller- Track

As hec;jved ByNo~. 16 1911 ATP j 669-2 5-02

page 3ciz

FLIGHT EaUIPMENT

SERVICE BULLETIN

i. Disposition of Rernored Oprts

~11 rero´•e~ originrl rollers end flttings ´•ra to ~s

returned to Flieht E~ui´•.ent k Cnpinscring Core.

3915 I.U. PLth. Street, Hi´•mi, Flcride 331L2.

fi I;

ease FR~ncr

r BOLT

iROLLER LI~ND

THlc~

plLOT 5noWN

FIGURE I

1As Received By

Nn~. 1E 19EI ATP i 669-2 5-~2P´•ge L

Service Information CulFstreamAmericancoRpon*Tlonf 0ommae6n DlrWm

500( Nonh Auenus,_ Bamanv. O*l´•hama 73MS

SERVICE INFORMATION NO. SI´•~18

1 February 1982

PESTICIDE FUEL ADDITIVE

MODELS AFFBOTED: NODEL8 BgO. 890A, BBOB, BBOC, g96 AND 698A, W SERIAL IWMBERS.

REASON FOR PVBLICPITION: TO ALLOW THE ZiSE OF BIOBOR JP B~OCIDFI AS A FUEL ADDITIVE.

OOMPUANCE: AT OWNERS DISCRETION.


ESTIMPlleD MAN HOURS: NOTAPPLICABLE.

PARTS DATA: NOT APPLICABLE.

SPECIALTOOLS: NONE.

1. BIOBOR JF Biocide (Sehio or equivalent) 270 ppm maximum (2(1 ppm of elemental beron) may be added to the fuelfarpeaticidepurpoesa.

NOTE

me BrOBOR W must be premixed in La fuel prior a Rllingthe airplane Rtel tanks.

ELBCTR(CAL LOAD: NO CHANCE.

WEIGHT AND SALANCE: NO CHAN(IE.

SPARES AFFECTED: NO

PUBLICATIONS AFPEO7ED: The Pilot Operating Handbook, Airplane Flight Manual and Airplane MaintenanceManual Changes required by this document will be inaorporated at their next scheduled revision.

RICORDCOMPLIP~NCE: NOTAPPLICABLE.

Pagelell

Service Information CulfstreamAmericanconpon*TI~,N

Camnandsr Dlrllian

5001 North RocL~all Avanus.

Bsm´•ny´• O~lahorm l~ms

SERVICE INFORMATION NO. SI-1BOA

(8upersedes ServiFe Information No. 81-180, dated a February 1882, in is entirety)17 June 1882

PARKER nANNIFIN CORPORATION PRODUCT REFERENCE

MEMO (PRM) NO. 25 (RevlslOn A)

MODELS AFFECTEO: FACTORY APPROVED:

MODEL 8g0A, SERIAL NOS. 11186 THRU 11344.

MODEL 68011, SERIAL NO9. 11550 THRU 11566.

MODEL 680C, 8ERIAL NOS. 11600 THRU 11709.



ST: APPROVED:MODELS 680, SERIAL NOS. 11001 THRU 11079.

MODEL 680A. SERIAL NOS. 11100 THRU 11184.

NOTE

ALTHOIIOH THE MODEL 680A AND 680B ARE N(YI~

LLSTED ON PARKER HANNIFIN CORPORATION PRM

NO. 25 (REVISION A), 1T 18 RECOMMENDED THAT THE

REWORK BE ACCOMPLLFIHED ON THE MODEL 680A

AND 68(111.

THIS SERVICE INFORMATION APPLIES TO

CLEVELAND BRAKE ASSEMBLY P/N 50-107 WITH

MANUFACTURERS DATE PRIOR TO DECEMBER 1881.

IF BASIC 8ERVICE INFORMATION NO. 9I´•180, DATED 3

FEBRUARY 1882, HAS NOT BEEN ACCOMPLISHED,ONLY PART I OF THIS SERVICE INFORMATION

8HOULD BE ACCOMPLISHED. IF BASIC 8ERVICE

INFORMATION NO. 81-180, DATED 5 FEBRUARY 1982,HAS BEEN ACCOMPLISHED. ONLY PART II OF THIS

8ERVICE INFORMATION SHOULD BE ACCOMPLISHED.

REISON FOR PUILICATION: TO RECOMMEND COMPLIANCE WITH PARKER HANNIFIN CORPORATIONI

PRODUCT REFERENCE MEMO (PRM) NO. 26 (REVIION A).

COMPLIANCE: AT OWNERS DISCRETION.

NOTE


COMPLYWG WITH THIS 9ERVICE INFORMATION,CONTACT YOUR NEAREST CIULFSTREAM

COMMANDER AUTHORIZED SERVICE~ER.

BY WHOM WORK WILL BE *CCOMPLISHEO: A P MECHANIC OR IZ~UIVALENT.

APPROVIL: NOTAPPL1CABLE. I

HOURS: PART I-TWO(2) HOURS

PART II-TWO(2)HOURS I

Psee 1 ols

IERVICL WFORMATION NO. BI-1BOA

EX)STIN(I DISC

S~RINOI(REF1

TOROUE EXISTIN(I

STUD 10 TO ED IN´•LBS

TORDUE EXISIINO11ODtSOOSTUDI\SSY

INTO PISTON ASSY00 10 70 IN-LBS

PISTON PISW

IREFL

EXISTIN~ BR*I(EP~SSY IREFI

Figa i.

Page Z ol 9

BERVICE INFORMATION NO. SI-1BOA

PARTS DATA: PARTS REQUIRED TO COMPLY WITH PART I OF THIS SERVICE INFORMATION MAY BE

PROCURED THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR

888.21. REFERENCE THIS SERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER

WHEN ORDERING SERVICE INFORMATION NO, SI-18oA KIT CONSISTING OF THE FOLLOWING:

R*´•ulcalol;Nnpanoutnlla~.

qTY PART NO. DESCRIPTION

4 se. 068-03500 Insulator Shim

6 ee. 08616800 Dise Spring1 ea. PRM NO. 25 (Revision A) Instructions I1 ea. Compliance Card

1 as. Service Information Na. SI- 1BOA Instruction, I

SPECIALTOOLS: NONE.

ACCCOMLUSHMINT INSTRUCTIONS:

PARTI

1. Comply with Parker Hannifin Corporation Product Referense Memo No. 25, Rsvieion A. I

2. After rework has been accomplished identify brake aasemblies bystamping the date of rework (month and year)

with permanent ink.

3. Fill out and mail Compliance Card specifying that Pert I has been accomplished

PART II

C~UTION

Care must be taken and eye protection gear worn during this

reworkto avoid injury since we are dealing with disassemblyof a preloaded spring stack.

1. Apply a slight amount of pressure to the brake system and set parking brake. This will prevent piston rotation.

2. Loosen and slowly remove the stud assembly (Pi~ 110´•04900) from each piston (refer to Figure 1).

3. Slide existing fourteen (14) disc springs from each stud assembly. Placestud assembly in a vise and cheek

torque of ANIHSA bolt in stud assembly to assure that bolt has not loosened. If bolt has loosened, retorque bolt

in stud assembly 80 to 80 inch-pounds,

4. Slide dise springs back onto stud assembly and reattach stud assembly and springs to each piston. Torque stud

assemblies BO to 70 inch-pounds (refer to Figure 1).

5. Actuats brakes 2 to B times and visually inspect each assembly to assure that everything appears normal and

is seated properly.

6. Fill out and mail Compliance Card specifying that Part II has been accomplished


WEI(IHT FIND BALANCE: NO CHANGE.


PUBLICPITIONS AFFECTED: The Illustrated Parts Catalog change required by this daeument will be incorporated at


No, SI-1BOA, dated 1? June 1882, entitled "Park HanniT~n Corporation Product Reference Memo (PRMI No.~"IRECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service

A), Part I accomplished (date) Part II accomplished (date)

Page 9 ol 3

O)(o

Revision A 5/5/82

21. 1981

Page 1

SUBJECT: 30-107 BRAKE ASSEMBLY

INSTALLATION OF TWO (2) ADDITIONAL 068-03300

INSULATOR SHIMS AND FOUR (4) ADDITIONAL

095-16800 DISC SPRINGS PER BRAKE ASSEMBLY

AIRCRAFT

EFFECTIVITY: ROCKWELL INTERNATIONAL AND GULFSTREAM AMERICAN

690, 695, 840, 900, 980, 1000 SERIES AIRCRAFT

UTILIZING CLEVELAND WHEELS BRAKES ASSEMBLY

NO.’S 40-107/30-107

SCOPE: PRODUCT IMPROVEMENT TO THE 30-107 BRAKE ASSEMBLY

TO ELIMINATE LOW SPEED BRAKE CHATTER REPORTED BY

SOME OPERATORS IN THE FIELD

Product Improvement Sequence: (For reference, see sketch)

r. dt the next regularly scheduled maintenance period, performthe following:

A. Shim Installation (068-03300)

i. Block main wheel tires to prevent aircraft move-

ment and release parking brake

2. Loosen the twelve (12) 103-14500 bolts and remove

the four (4) 074-03900 back plate assemblies from

each brake assembly

3. Install one (1) additional 068-03300 insulator shim

on each brake cylinder

4. Reinstall 074-03900 back plate assemblies, tighten103-14500 bolts and torque to 85-90 in-lbs.

Parker Hannlfln CorpwatlonIlroraH Wheel end Brake Dlvlslon

P.O. Box 158. Avon, Ohio 44011 VSA

(215) 8345221

~Aerospace

d ponslsle

O)(o

Revision A 5/5/82

SpeRp:~pe;521, 1981

Page 2

SUBJECT: 30-107 BRAKE ASSEMBLY

INSTALLATION OF TWO (2) ADDITIONAL 068-03300INSULATOR SHIMS AND FOUR (4) ADDITIONAL

095-16800 DISC SPRINGS PER BRAKE ASSEMBLY

B. Disc Spring Installation (095-16800)

i. Caution must be taken and eye protection worn

during this phase to avoid injury since we are

dealing with disassembly of a preloaded springstack.

2. Apply a slight amount of pressure to the brake

system and set parking brake. This will preventpiston rotation.

´•vision~ 3. Loosen and slowly remove the stud assembly (110-04900)from each piston. Slide the existing thirteen (13)disc springs from each stud assembly. At this point,check to see if the AN4H-5A bolt in the stud assemblyhas loosened. If so, retighten the bolt into theguide stud at 80-90 in-lbs.

4. Slide the disc springs back onto the stud assembly,installing the one (1) additional spring in thelocation and position shown in the sketch.

O 5. Reattach the stud assembly and springs to each pistonas shown in the sketch. Torque the stud assembly at60-70 in-lbs.

6.´• Actuate brakes 2-3 times and visually inspect each

assembly to insure that everything appears normal

and seated properly,

Make a log book entry referene7. vi end

return aircraft to service.Alrcralt Wheel and Brake Dlvis(onP.O. Box 158. Avon, Ohio 44011 USA

(218) 9346221

5 pDl,sl´•a7s

Revision A 5/5/82

September 21. 1981

PRM No. 25

Page 3

Loosen 103-14500 bolts

per Pare I.A.2

Tighten and torque per install additional

Pare I.A.4 068-0~300 insulator

shim per Para ~.A.3

Existing 095-16800

disc spring stack

13 each typ. 4 p

per brake assenbly

110-04900

Scud AesamblyTighten perPare l.B. 5

5A bolt

095-15900’ 11flat washer

Parker HanniBn CorporationInstall per pare 1.8.4 st top of

Aircratl Wheel and Brake Divisionstack and positioned as shown (typ) P.O. Box 158, Avon. Ohio 44011 VSA4 pieces per brake assembly (216) B34´•5221

L P0118~´•6)P

Service Infoumationeammsnda Divilim6(101 North Rochwall Auanua.Bamany´• Otlahoma 75008

SERVICE INFORMATION NO SI-182

1 June 1982

DOWTY ROTOL SERVICE BULLETIN NO. 61-950ALTERNATE GREASE (TEXACO LOW TEMP EP GREASE) FOR DOWTY ROTOL PROPS

MODELS AFFECTED: MODELS 680C. 6B0D. 895 AND bSA.

NOTE

CHECK PROPELLER LOG BOOK FOR ENTRY OFMODIFICATION NO. (c) VP. 2989. IF THISMODIFICATION NUMBER HAS BEEN ENTERED INYOUR LOO BOOK. YOUR PROPELLERS HAVE BEENSERVICED WITH TEXACO LOW TEMP EP GREASE.

REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH DOWTY ROTOL SERVICE BULLETINNO. 61-950.

COMPLIANCE: REFER TO DOWTY ROTOL SERVICE BULLETIN NO. 81-950.

BY WHOM WORK WILL BE ACCOMPLISHED: A DOWTY ROTOL APPROVED PROPELLER SERVICE SHOP.

APPROVAL: REFER TO DOWTY ROTOL SERVICE BULLETIN NO. 61-950.

ESTIMATED MAN HOURS: NOT APPLICABLE.

PARTS DATA: REFER TO DOWTY ROTOL SERVICE BULLETIN NO. 61-9W.

SPECIALTOOLS: NONE.

~ZCCOMPLISHMEM INSTRUCIIONS:

1. Refer to Dawhr Rotol Service Bulletin No. 61-960.


WEIGHT FIND BIIPINCE: NO CHANGE.


PUBLICATIONS APPECTED: The Airplane Maintenance Manual changes required by this document will beincorporated at the next Kheduled revision.

RECORD COMPLIANCE: Refer to Dowty Rotol Service Bulletin No. 61-950.

Page 1 of 1

I%QWBYI

SERVI%E BULLETIH

PBOPBLLE8S 8LADE ORO~ IATROWCT~ON O8 TEXACO U)U Te~tP BP DRPISBAS Al.TERAATIVE TLI AEROSBELt 7

noorPxcnTroN ~D L~C)IP ´•2983

i. PI~NlllffD

Aircraft (f)Propaller

Duliaerca~ A´•sricao Co~msndcr R306/3-82-P/76900, Soon, 695, 6951\

g. Reason

(1) A requear has been made for pniisaia. to use an alternative

grease.

C. Description

(1) This modiricarion introduces Telsco lor Te~p BP grease as an

alrernntive to Aaroshell 7 for usa in Lha propellers listedin Para.l.A.

Mote Both greases are to specification DTD)598 (WIL-C-23827A)bur ire not ra be intemiled in use.

D.

(1) Bacolrended.

I. Apprc~al

(1) This bulletin is appro~ed under authoritJ of CM Appro~´•lao.nar/~ms/,s.

I. ELan Pover

C. Ilslcrill

Act: applicabls8. Tooling

I. Ueight and balance

Occober 6181 61-950March 9/82 (Revisicn 1) Page 1 of Z

L2.

IDQPl~iYI

SERYICE BULLETIW

J. aefereaces

(1) Coaunder 6900, 6900, 895, 699A Op~srhaul ~Lsnual 61-10-16.

r. Other Publications Affected

(1) None.

2´• IISTB~CPIONS

A. B´•bodlnaor instructions

(1) Vhcn servicing the prapalloF´•, Texaco Low Temp 00 greese IlaTbe used as an alrsroari~e to 7 where specified in

the rcla´•ranr overhaulmanual.

Note These greases lust not be intermixed in use.

B. Werhod of identification

(1) Record nod.No.(c)VP.2983 in the propeller log boob.

2. EU~TBI(UL

A´• ~oas.

61-990 October 6/81 i

Rage 2 (Ra~ision 1) ni~tch 9/82

Senrice fnformation CulfstreamAmericancc~npon*rloNCMmmdsrDivYaSM1 slam RartuFII Annu´•.

BaNny. Oll´•Don~ 13008

SERVICE INFORMATION NO. SI-1BS

9 July 1882

IMPROVED AILERON SERVO AUTHOR17Y KFC 300 AUTOPILOT

MODELS AFpEOTBD: THE FOLLOWING EQUIPPED WITH KFC 300 AUTOPILOT:MODEL 69(ID, SERIAL Nh9. 111001 THRU 11004, 18006 THRU 16012.

MODEL 696A, SERIAL N~. 88001 THRU 98039.

REIS80NFORUBLCATTON: TO MAKE AVAILASLE AN IMPROVEMENT TO KFC 300 AUTOPILOT

INSTALLATION.

COMPLI~NCE: AT OWNER’S DISCRETION.

mlTe

a ANY PROBLEMS ARE WHILE

COMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST GULFSTREAM


BY WHOM WORK WILL BE ICCOMPUSnED: KING RADIO CORPORATION AUTHORIZED SERVICE AGENCYOFCATEGORYVB.

APPROVAL: FAA DOW Sw-a APPROVED.

EST1MATED MW HOURS: FOUR (41 HOURS

PARTS DATA: AILERON SERVO P~ 066-0024-11 MAY BE PROCURED THROUGH YOUR NEAREST

AUTHORIZED KING RADIO CORPORATION DISTRIBUTOR OR SERVICE AGENCY. THE EXISTING AILERON

PFBVO PIN 066-0024-06 MAY BE MODIFIED TO A 0660024-11SEXVO BY KING RADIO CORPORATION.

9PECI*LTOOLO: NONE.

I\CCOMPUSHMENT1NSTRUmONS:

1. Gain access to ailsron servo, located just Eomard and above baggage Eompartment at fuselage station 223.98.through baggage compartmsnt doer.

2. Remove upperloruanl bsggage mmpartment liner to expose ailemn servo.

3. Disconnect electrical connector (irm an side oldlsmn servo.

a. Remove bolts that attach silemn servo and remove servo P/N (186-002408 (see Parts Data above).

6. Remove screws that altach cap to slip clutch and remove cap. Slip clutrh is located forward of silsmn servo

~splinedendofservo).

Page 1 of2

SERVICE INFORMATION NO. SI-lsS

6. Chanse slip setting 80(+ 10) inohpounda M 10) fReinstall cap on slip clutch using existing hardwsre.

g~ Instalt 0850024-11 aileron servo using existing hardware.

8. Remove wire Rom pin "C" on alleron servo c.nnaftori cap wire and ceil and stow wire.

10. Rsoonnect electrical connecter to new ailsmn servo.

11. Assure that Supplement No. 28 (Model 680D) or Supplement No. 32 (Model BgSA) is in the Pilot Operating

Handbook.

12. Check operation of new silemn servo as outlined in Normal Precednres of Pilot Operating Handbook

Supplement No. 28 (Model 680D) or SupplementNo. 82 ~Model 886A).

13. Reinstall baggage cempartment liner.


ELECTRIC*L LO*D: NO CHANGE.

Wel(lHT ANO 8*LI\NCB: NO CHANGE.

SPARES AFFECTIO: NO.

PUBLICI\TIONS I\*FECTEO: The Illustrsted Parts Catalog change ra~uired by this document will be incorporated at

We next ssheduled revision.

RECOR~ COIPLIANCE: Malts an appropriate entry in airplane maintenance records as follows: Service Morrnation

No. SI-183, dated g July 1882, entitled *Improvsd Ailema Servo Authority KFC 800 Autapila, accomplished 3(date)

i

Page 2 of 2

Service InformationCulfstreamAerospace

SERVICE INFORMATION NO. 81-18110 Decembsr 1882

INSTALLATION AND/OR MAINTENANCE OF ABRASIONRESISTANT TAPE ON DOWTY-ROTOL PROPELLERS

MODELS AFFECTED: 690C, SERIAL NOS. 11BM) THRU 11121 AND 11129 THRU 11?2?.MODEL 990D, SERIAL NO8. 15001 THRU 16018.MODEL 686, SERIAL NOS. 86000 THI(U 86084.MODEL B9SA, SERIAL NOS. 86001 THRU B60l9.

REASON FOR PUBLICPITION: TO REMIND OPERATORS OF IMPORTANCE OP PROPERLY INBTALLINO ANDMAINTAININ(I THE ABRASION RESISTANT TAPE ON DOWTY-ROTOLPROPELLERS

COMPLIANCE: NOTAPPLICABLE.

BY WHOM WORK WILL BE ACCOMPLISHED: NOT APPLICABLE.


ESTIMATED MAN HOURS: NOT APPLICABLE.

PARTS DATA: NOT APPLICABLE

SPECIAL TOOLS: NOTAPPLICABLE.

P~CCOMPLISHMENT INSTRUCTIONS:

Phis Service information is being issued to point out that abrasion resistant Ups was installed an the propeller blades

u, improve nbrasion resistance end ice shedding capabilities of Dowty-Rotol propeller. With the onset of winter, the

condition Jf this abrasion resistant taps should be closely monitored.

Service Bulletin Na. 189, entitled "Applicatian of Abrasion Resistant Tap on Dowty-Rot~ Propeller", was issued againstModel 690C. Serial Numbers 11600 thru 11118, Model 696, Serial Numbers 86000 Unu 86094 and Model 6861\, Serial

Numbers 96001 Lhru 96024- Operators of these aircraft should assure total compliance with Service Bulletin No. 188.

The operators of other affected PircraR should assure that the abrasion resistant taps is maintained per AirplaneMeintenanu, Manual Instructions

ELECTRIC*L LOAD: NOTAPPLICABLE.

WEICIHT AND BALANCE: NOT APPLICABLE.

SPARES AFFECTED: NOT APPLICABLE.

PUBLICATIONS AFFECTED: NOT APPLICABLE.

RECORD COMPLIAINCE: N(Y~ APPLICABLE.

Page 1

Service inf~rmatisnC~IIGulfsrreamAerospace

SERVICE INFORMATION NO. Sl-1898

(Supersedes Service Information No. SI-189A in its entiretyi24 February 1984

APPROVAL AND INSTALLATION OF TPE 331-10-511K ENGINES

MODELS AFFECTED: MODEL 695, SERIAL NOS. 95000 THRU 95084.sMODEL B95A, SERIAL NOS. 98001 THRU 96069.

NOTE

IT IS RECOMMENDED THAT SERVICE INFORMATIONNO. 81-193, ENTITLED "OIL VENT HOSE ASSEMBLY

REPLACEMENT", BE ACCOMPLISHED AT THIS TIME

(IFAPPLICABLE).

REI\GON FOR PUBLIC*TION: TO AUTHORIZE INSTALLATION OF TPE 331-10-6111 ENGINES AND PROVIDE

ELECTRICAL WIRING CHANGE REQUIRED WHEN INSTALLIND ENGINES.

COMPLUNCE: OWNER/OPERATOR OPTION. REFER TO GARRETT TURBINE ENGINE COMPANY SERVICE

BULLETIN TPE 331-72-0398

C No~a

IT IS ACCEPTABLE TO OPERATE AIRPLANE WITH A

TPE 951-10-501K ENGINE ON ONE SIDE AND A TPE

331-10-511K ENGINE ON THE OTHER SIDE.

IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST GULFSTREAMCOMMANDER AUTHORIZED SERVICENTER.

BY WHOM WORK WILL BE I\CCOMPLISHED: A L P MECHANIC OR EQUIVALENT. 8EE OARRE’IT TURBINE

ENGINE COMPANY SERVICE BULLETIN TPE 981´•72-0398.

APPROVAL: ENGINEERING DESIDN ASPECTS ARE FAA APPROVED.

ESTIMATEDM~HOURS: TWO (2) HOURS TO ACCOMPLISH THE MODIFICATION DESCRIBED IN STEPS 3

THROUGH 11 BELOW. SEE OARRET~ TURBINE ENGINE COMPANY SERVICE

BULLETIN TPE 331´•72´•0598 BOR ADDITIONAL INFORMATION

PARTS DATA: NO PARTS ARE REQUIRED TO COMPLY WITH STEPS S THROUGH 11 BELOW. INFORMATION

REGARDING PRICE AND AVAILABILITY OF PARTS PERTAINING TO THE ENGINE ITSELF MAY BE OBTAINEDFROM A CARRETT APPROVED SERVICE CENTER. INCLUDED WITH THIS SERVICE INFORMATION IS

ONE (li COMPLIANCE CARD.

SPECIALTOOLS: ENGINE LIFTING TOOL AND HOIST. SEE GARRETT TURBINE ENGINE COMPANY SERVICEBULLETIN TPE331-12-0398 FOR ADDITIONAL TOOLING REPUIREMENTS.


1. Remove elisting TPE 331-10-5018 sngine(s) and install TPE 331-10511K engine(s) as outlined in Chapter 71

of the Airplane Maintenanee Manual.

Page lofS

8ERYICE 1888

~-240-9 A2I3

7‘0---""e-215-in

AI

p~-´•i

~ISCONNECT WIRE NO. 233 FROMKS3-l\l I\ND RECONNECT WIRE I DISCONNECT WIRE NO. 238 FROMTO KS-AI AND RECONNECTWIRE

TO KB´•l\l

A3

1~-235

Al

LEFT ENGINE RIGHT ENGINE

*o´•rl

CASHED LINE INDICATES ORIGINAL I´•M1K ENGINE)

CONNECTION OF WIRE hlOS. 233*ND 238.

Filura i.

Page 2 of S

SERVICE MFORMATION NO. 189B

z M~tll ilunp pert oumi~ 81066360L a4~nl m Ula *md´• *&Ro P*RI‘ on the nov an.ins RaTsrto step (16) page 20 of Garrett Turbine Engine Company 8ervice~Bulletin TPE 331-72-0398

3. Gain secess to power distribution panel through baggage compartment door. The power distribution panel is

locatedjust aft of the baggage compartment door.

i. Remove baggage compartment liner, as necessary, to snpose power distribution panel.

5. Remove or lower power distribution panel cover.

NOTE

On Model 695A, serial numbers 96066 thru 96069, the cover IIon the power distribution panel is hinged to the panel and

may be lowered. The relays to be rewired on these airplanesare mounted on the cover.

If the TPE IS1-lO-SolK engine is not replaced by a TPE

331-l0-511K engine, do not rewire the relay for the side

that still has the -SO1K engine.

B. For the left engine, disconnect wire No. 259 from Al of KSS relay and reeonnect wire to Al of KS relay (referto Figure i).

7. For the right engine, disconnect wire No. 236 ham Al of KS4 relay and remnnect wire to Al of K6 relay (referto Figure i).

8. Reinstall or close the power distribution panel cover.

9. Reinstall baggage compartment liner.

10. Assure that revision No. 7 (Model 696) or revision No. 10 (Madel 695A) has been inserted in the Pilot’s OperatingHandbook.

11 Fill out and mail compliance card specifying if ons or bath engines have been converted to -611K. Record total

airframe and engine hours, slang with engine serial numbers on compliance card.


WEIGHT ~ND SALANCE: NO CHANGE.

SPARES ~FFECTED: THE TPE S31-10-611K ENGINE 18 THE SPARES REPLACEMENT FOR THE TPE 331-10-

60iK ENGINE. THE TPE 331´•10-601K ENGINE WILL NO LONGER BE AVAILABLE.

PUBL1CATIONS I\FFECTED: The Model 695 and 696A Pilot Operating Hendbw~ revision has already been furnishedand Airplane Maintenance Manual and Illustrated Parts Catalog changes required will be

incorporated at the nent scheduled revision.

RECORD COMPLI*NCE: Make an appropriate entry in airplane maintenance records as follows: Service InformationNo. S1´•1898, dated 24 February 1984, entitled "Approval and Installation of TPE331-10-511K Eogines~’. accomplished

(date)

Page S of S

Ikw~llSerwice information Gulfstream

Aerospace


21 May 1883

TERMINATION OF FACTORY FINANCIAL PARTICIPATION ON PARTS

AND/OR LABOR ALLOWANCES ON CERTAIN SERVICE PUBLICATIONS.

MODELS AFFECTED: MODELS 500, S00A, 5008, 520, 580, S80A, 1601, 580P, 880, B80E, 680F,688(F), 880FL, BLIOFL[P), 880T, 680V, 680W AND ?20, SERUALNOS. 1 TBRU

1854.


MODEL 885, SERIAL NaS. 12001 THRU 12068.

MODELS 680, 6B0A AND 680B, SERIAL NOi. 11001 THRU 11558.

MODEL 880C, SEIdAL NOS. 11880 THRU 11815 AND 11108.



MODEL 885A, SERIALNOS. 86001 THRU 86052.

MODEL ?00, SERIAL NOS. 10001 THRU ?0828.

REASON FOR PUBLICATION: TD ESTABLISH A TERMWATION DATE FOR FACTORY FINANCIAL

PARTICIPATION.

*9 os la~ n7. IlsJ. TAB sOLLaVn*C BER~CB POBLIOLTI(WB WIU PROYID. B*CTC~P

PARTICIPATION ONLY UNDER THE FOLLOWING CONDITIONS:

(3 IF COMPLIANCE IS ACCOMPLISHED WITHIN ONE (1) YEAR FROM THE DATE OF ISSUANCE,AS STATED ON EACH SERVICE PUBLICATION, OR,

(b) IF THE AfRCRAFT 1S COVERED BY OULWTREAM WARRANTY APPLICABLE FOR EACH

SERVICE PUBLICATION.

WOTE

THE PART PRICES 4UOTED ON THESE SERVICE PUBLICATIONS ARE SUBJECT

TO CHANGE WITHOUT PRIOR NOTICE IT IS RECOMMENDED THhT CURRENT

PRICING BE OBTAINED AT TIME OF ORDER PLACEMENT.

SERVICE BULLETINS

ISSUE

NO. TITLE DATE

25 Improved Catauretor Air Straightener 8-5-54

Suppl. 141 Replacement of Aileron Bellerank Castings at W~ Stations 188 5-a4-5751 MadWoation Flight Instrument Btatie System Piping 2-18-5852 Installation of Close Fitting Carburetor Air Box Shaft and Mmaball Rod Ends 2-15-6855 Replacement of Propeller Blade Split Rings 2-18-5851 Horizontal Stabilizer Modlflcatlon 3-11-5858 InsuMlon of the Hydraulle and Engine Oil Shutoil Valve CLreult Breaker 1-8-596(1 Corrosion Inspeetton Rudder Torque Tube 8-21-5881 Carburetor Air Bon Repair 8-21-58

70 Installation oi Improved Condenser in Bendin 280 Series and 800 Series Magnetos a-8-81

88 Replaeement of Main LandingGear Uploclt Cheek Vsilve 8-22-80

PagelofS

SERVICE INFORMATION NO. SI-lsl

BULLETINS ~CONTU)

NO. TITLE DATE

?1 installation of Fuel InJector Pump Ice Shield 2-13-8175A Replacement of Main Landing Gear Uplock Check Valve Assembly 12-1-8176A Replacement of Engine Induction Alternate Air Butterfly Valves and Mounting Shafts 2-5-6278 installation of Fuel Drain Lines for Engine Cage Units 5-16-6283A Main Landing Osar Piston Upper Bearing Look Pin Replacement 6-25-8589 Cable Retainer ALleron Cable Drum 10-21-8491 inspection and Possible Replacement of 4630068 Magnesium Fuel Sump Casting 4-28-6193 Replacement of Pilot and Copilot Windshields 11-11-6796 Inspection of DC Bus and Contactor Box Wiring 2-20-68105 Replacement of Emergency Door Release PLaea~d 5-2-11118 Sealing Engine Control Cables 2-25-73119 Engine Oil Pressure Rose Support 5-8-75120 De-leer Decal Installation 3-8-13121 Woodward Governor Modi~ioailon 3-16-73122 Thermostat Protection for Anti-Ice Heaters 3-27-1512SA Replacement of Unfeathering Pump Supply Line B-B-73134 Engine and Engine Installation Hardware Improvements 4-23-73191 Installation of Cabin M Pressure Light System 11-21-’15133 Engine Baffles 2-4-14

134 Replacement of Bleed Air Check Valves 2-6-1413?A Engine Gage Replacement 6-8-75139A (b~ygen Mask and Storage Provisions 7-21-75143 Replacement of Openable Pilot and Copilot Side Windows 8-10-14144 Yerticail Stabilizer Trailing Edge Modllication 10-4-14141 Bleed Air System 11-21-7(151 Replacement of Fuel Sump 4-11-15154 Hydraulic Pressure Line Replacement 5-21-15

11I InatULUion ai SE* ud BlmC´•l PlsOlld´• C158 Failure of Flap Control Bracket 8-27-15157A Flap Control Bracket Modification 5-29-19LSB Trim Annunciator Lamp Cap Replacement 10-9-15

162 Reduction in Electric Elevator Trim Speed 10-21-16

183 inspect and/Or Replace Wing Spar Cap Rivets 1-21-11

188 Copilot Airspeed Limitation Placard Installation 5-5-78

L?1 Unfeatherng Pump Supply Hose Replacement 4-8-80

175 Oil Filter Adapter Replacement and Engine Mount Retainer Modification 1-21-80178A Ailemn Access Door Inspection and Replacement 2-1-81

183 Exhaust Pipe Seal Replacement 1-7-81

189 Application of Abrasion Resistant Tape to Dowty-Rotol Propeller 3-12-82

190A Exhaust Pipe inspection and Modification 8-22-82

191 Nose Landing Gear Centering Cam Replacement 1-29-82

193 Passenger Oxygen Dispenser Modification 10-28-827-2 Throttle Control Cable Inspection and/or Replacement (Model 700) 8-27-19

SERVICE LETTERS

ISSUE

NO. TITLE DATE

44 Nose Landing Gear Cylinder Assembly Spacer Installation 2-3-5653 Addition of Stiffener Clips to Lower Cowllngs and Aft Nacelles 10-1-56

80 Battery Relay Terminal insulation 8-22-5983 Recommended Change of Carburetor Air Box Control Arms 11-18-59

83 Installation of improved Generator Drive Pulley Retaining Nut 12-8-60

04 Installation of Correctly Calibrated Oil Dipstick and Improvement of Weight and

Balance Data 2-8-6195 Installation of improved Engine Exhaust System 3-1-61

98 installation of Fuel Flow Gage Pitot Vent 4-12-81

112 Replacement of Tee Fitting in Vacuum Line Aft of Fuselage Station 165. 88 10-21-81C104 Horizontal Stabilizer Modification 8-15-61

118 Inspection and Replacement of Engine Exhaust Stack Assemblies 12-11-61

11? Replacement of Vacuum Air-Oil Separator 12-11-81

171A Main Cabin Door Modification 1-14-68

PaSe2of3

SERYICE INFORMATION NO, SI-181

C ssRITs LBTTEA8 ICONm)ISSUE

NO. TITLE DATE

184 mst2llatlan of Improved Cabin Pressure Differential Switch 31-4-68

IsS Modification of EGT System Pitot Static Hose Installation 11-20-68

186 Main Landing Gear Uplack Arm Modification 11-22-BE

189 Propeller Attach Bolts 12-23-68

190 Installation of Improved Roller Bushing Main Landing Gear Door Latch Assembly 12-29-BE

Ist Engine Cowllng Chafing Strip 1-18-67

182 Deflector Installation Nose Landing Gear 1-is-81

189 Modification of Engine Tail Pipe Molmtlng 5-14-81

241 Negative Torque Sense System Test Light 5-26-72

248 Quadrant Face Plate 8-6-72

286 ALResearch Heated Pr and Py Pneumatic Lines 8-16-73

257 Wire and Fuse Size Change far Heated Engine Prime 12-14-72

258 Fuel Quantity Indicator Deca~ 1-2-73

ZBO Quadrant Face Plate 1-5-15

262 Fuel Vent Check Valve insti~llatlan 2-1-15

aa? Cabin Temperature Control 4-18-75

269 Increased Landing Gear Ektend Speed 1-17-73

211 Increased Landing Gear Entend Speed 8-24-73

272 Bob Weight Modification 11-14-15

215 Oil Cooler Flange Reinforcement Installation 12-13-73

a?? Replacement of Governor Reversa~ Linkage 4-23-74

500 Installation of OTSIO-52O-K Engines 1-21-15

SOS Fuel Flow Indicator Modification 1-22-75

S1OA lent Headrest Spring Retainer installation 10-28-16

S15 Improved Operation of Start Pressure Regulator 1-12-17

524 Replacement of Center Fuel Quantity Transmitter Gasket 1-18-79

SSO Wing Fuel Cell Support Installation a-25-80

JJS KIIIMmold Unit IECU) P´•ssiiu.e Su~lilb Rsoa~UbE.tlon or Blmesms* S-18-BO

334A Electric Start System Modification and Starter-Generator Ground Bus Bar Replacement 3-18-81

SSB Inter Turbine Temperature (ITT) Indicator Replacement 10-11-80

357 Engine Mount Bracket Modification 11-21-80

938A Aft Fuselage Thermostat Installation 3-13-81

339 Baggage Heater Annunciator Light Lens Replacement 1-15-81

540 Datsillptlan of Placard for Use of Alternate Engine 011 MIL-L-1808G 4-24-81

548 Replacement of limer Structural Cabin Window Glass 9-1-81

547 Replacement of inner Structural Cabin Window Glass 11-5-81SJ1 Parker Hpnniltn Corporation Product Reference Memo (PRM) No. 21 8-17-82

?-1 Annunciator Circuit Modification and Throttle Switch Wire Replacement (Model 700) 5-18-79

SERVICE INFORMATION LETTERSISSUE

NO. TITLE DATE

SI-128 Goodyear Service Bulletin No. Aero Commander 690A-32-1 3-16-76

SI-118 Flight Equipment and Engineering Corp. Service Bulletin Na. 668-25-02 1-15-82

SPECIAL PRICING PUBLICATION

SERVICE BULLETIN

ISSUE

NO. TITLE DATE

174C Reverse Power Limitation and Propeller Inspection, Harteell HC-BSTN-S(L/LT10282 ()()+4 5-20-80

NOTE

For Service Bulletin No. 174C, Factory Financial Participation will apply if the

parts are o~dered prior to June 30, 1989 and installed prior to August S1, 1983.

Page 3of3

c Service informationCulfstreamAerospace

SERVICE INFORMATION NO. 8I´•183

3 August 1989

OIL VENT HOSE ASSEMBLY REPLACEMENT

MODELS AFFECTED: MODEL69(L, 8&RUAL NOS. 11001 THRU 11019.MODEL 690A, SERIAL NOS. 11100 THRU 11344.MODEL 680B, SERIAL NOS. 11510 THRU 11566.

MODEL B9OC, SERIAL NOS. 11800 THRU 11664, 11686 THRU 11684 AND 11681 THRU11730.

MODEL 690D, SERIAL NOS. 15001 THRU 16021 AND 16025 THRU 16029.MODEL 695, SERIAL NOS. 95000 THRU 85082 AND 95084.MODEL B95A, SERIAL NOS. 95001 THRU 06056 AND 86088 THRU 96061, AND 96063.

REASON FOR PUBLICI\TION: TO. INSTALL LONGER VENT HOSE ASSEMBLIES TO PREVENT POSSIBLEENGINE OIL VENTINO OVERBOARD AT ENGINE SHUTDOWN.

COMPLIANCE: AT OWNERS DISCRETI~N.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILE00~6PLYMO ~TH THIB SIERYIOB

CONTACT YOUR NEAREST CULF8TREAMCOMMANDER AUTHORIZED SERVICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A %i P MECHANIC OR EQUIVALENT.



PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCUREDTHROUGH YOUR NEAREST OULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 5314.14.REFERENCE THIS SERVICE INFORMATION, AIRCRAP~ MODEL AND FACTORY SERIAL NUMBER WHENORDERING SERVICE INFORMATION NO. 81-193 KIT CONSISTING OF THE FOLLOWING:

PAI(TNO. DESCRIPTION

2 ea. 5-0421B05-336 Hose Assy2 ea. AN960-10L Washer2 ea. MS21042L3 Nut2 as. MS21919H17 Clamp2 as. MSa1918H8 Clamp1 es. M821039-1-08 Screw1 ea. CamplianEe Card1 ea, srvioe Information No. 9I-1BS Instruetions

8PECIALTOOLS: NONE.

C *CWMPLISHLIEI~ INSTRUCTIOIIS:

1. Remove lower Eowling from left and right engines.

wee 1 or 4

SERVICE INFORMATION NO. SI-193

MODELS 690, 690A AND 6908cnurlo~

nSSURE TIIAT 91)921~109´•338 HOSE

A8SYOOESNOTCOMEINCONTACTWITH ENGINE AFTER IT HPIS BEEN MS21818H17 CLAMP

BECUREO WITH CLAMPS M821818H8CLI\MPMSZ1038´•1´•OB SCREWINBBO´•IDLW~sHER s´•0421H05-338

MS2((MZL3 NUT HOSE ASSY

~i

I ~wo>

i(_L!!

s a

c_

ATTACH ELBOW FITTING OIL TANK

MANIFOLD OAA1N ~SSYI IREF)MIVIIFOLD CRAIN

ASSY IREFI

VIEW LOO1(ING AT RIGHT SIDE of ENGINE (TYP)

Filura 1. Ihast 1 of 21

Page 2 oft

SERVICE INFORMATION NO. SI-1OS

MODELS 690C, 6900, 695 AND 695*

CAUTION

ASSURE THAT 80021H04´•338 HOSEnsSY WES NOT COME IN CONTACTWITH ENGINE AFTER II HA8 BEENSECUREPWITHCLP~MPS

EXISTINGMS2WBla88CReWAN911010LWA8HERM92(044N3NUT

Pis\ I ~M I ExlsnNa

MS?(BlsH12CLP~MP

Cii

EX~STIN(IMS21810nllCLAIP

r

TQOIL

OIL TANK(nEFI

80921H8IP18HOSE 1\89Y

M52l8(gH1ICLAMPM*NIFOLD DRAIN MSPIBIBHBCL*MP

Assv IREF) M92~(138´•1´•01SCREW~N880´•10LWnBHERM81101ZL3 NUT

VIEW LOOKING AT RIGHT SIDE OF ENGINE (TYP)

C

liica ~.(9lsst 2.1 21

Page 3 of 4

SERVICE INFORMATIOIV NO. SI´•193

Z Rrmo~ and Ixisnng oli rant hm that is routal tmm the oil tanX uanl i.rt to th. maniiold dFain Cassembly (refer to Figure 11.

NOTE

On Models 690C. 990D, 895 and 696A, retain eyistingclamps and hardware for reinstallation.

9. Install 8-04218(15´•336 hose assemblies on left and right engines and secure to engine using e.isting clamps and/or clamps furnished with this Service Information (reLr to Figure 1)

I CAUTION

To prevent heat damage to hose assemblies, assure thathose aaaemblies do not come in contact with engine sber

they are secured with clamps.

4. Reinstall lower cowling on left and right engines.



WEICIHT AND EALANCE: NO CHANGE.


PUBLICATIONS AFFECTED: The Illustrated Parts Catalog changes required by this document will be inro~oreted at

the nest scheduled revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service InformationNo. SI-1BS, dated 3 August 1985, entitled "Oil Vent Hose Assembly Replacement". accomplished tdate)

Page 4 of 4

~illc Service information GulFstream

Aerospace

Yk:I(VI(:R INI’ORMATION N(I SI´•I!IT,

Pl)r~ambar I On:I

DOWTY ROTOL SERVICE BULLETIN 61-A995 (Revision 1)

MODELS AFFECTED: MOl)ll. ((’III(:, HRHlnl. NOSr I IH(II) THHU 111:11.

MOl)~l:I. 69111), SEKI~I. NOY. 16(101 THKU Ih(llP. 161)11, 15016 I‘HKU 1601X, ANI) IOL)ZO

TnllU 15(111

MOl)lll. nlIF,, SERLAI. NOS, e601111THI(U YBOX4.

MOI)El.(iBSA. SF:KLAI. N08. UH(I(II, gB00a THKU 961)PI, !N(I)P:( ’PHHII ua,ss.

96(16:1, Rn064. 96089 ANI)H6012.

REASON FOR PUBLICATION: ’I´•0 IR(:OMMF.NI) (:OMI1I.IANCI: WITR I)OW’PY l(OPOI. Sgl(VI(:R HUI.I.E:’PIN (il-

nHBg (I1BVISION ii

COMPLIANCE: I(RPI’IK’PO IIOW’PY 1101‘0[. SRI(VI(:$ HUI.I.E’I~IN (il-hssllKRVISLON II.

MOTE

IF nNY I’KOTIIIIMY AIIR gN(:OUNTBKE:I) WHlllk:

(:OMI’I.YIN(: WITI( IIOWTY KOTOI. SPKVIUF:

IIUIITII:1´•IN LI-~re IKEYLqlON I) LDNThCT

NI(AKRS1‘ (:UI.ISTHBI\M (:OMMANI)RH nUTHOII%EII

SRI(VICRNTglL.

BY WHOM WORK WILL BE ACCOMPLISHED: A B I’ MECIIANIC 011 RUUIVIZI.RNT

APPROVAL: ItRP1IIHI‘O I)OWTY 1(0’1‘014 SBILVI(:R BU1.1.13TLN 61-A9U1II(F.VISION II.

ESTIMATED MI\N HOURS: 1(1(11~1:1(’1‘0 I)OW1’Y KOTOI, SEDVL(:F, IIIII.I.E1‘LN (il-ABOh IIIRVISION I I

PARTS DATA: I(I(PBI1TO I)OW’PY 1101‘01. SRI(VIC6 I(UI.I.RTLN 81-A9!)6(KF.VIS10N II.

SPECll\LTOOLS: NONR.


I. (:l,mllly wilh i)llwty 1~1011 Ssrvi.u i~ullutin 61-A0!)9 ilavilien I).

S L.*altx el’ illl Ehusks ixilti*llctl,ry ilncl alilurrx) ure ~I i,u rup,rten to ihr Pn~luet Bupl,.rt I)clwty Kotlll

I.imitl,d, 1:loua,at~!,´•, Rn.lsnd. I,y talul,hcmo 10491) 712421 or by telex 4:IBilfii7, yuotinl! thL. pn,p.llsr TYP"llUmIll?l., Sari,ll numbcl´•.’I´•Y.N,ilnd idsnti$inll tba *prina, i.a, insur ilr ilutcr. in tha avant I1I´•1I TaP(II´•tCd lililUle.

MOTE

Nl,rth ;Ind Cwntnd Amrricun Opsnltcll~ nl,suld rupllrtrnulta st i)llwty Kotol inol,rplll´•st*d by Clophene 111:(-4111-

R~:II) er i,y iclux XPOIH. Llulh Amurici,n OpunlClrx l~,uld

rapllrt rcnul(h II, I)llwty IlsC,I I.imitcd.

:1.

C

Pagelol2:

SI(KVI(:I LNF‘ORMA1’LON NO. YI-IHI

EL~CTRIC*L LO~D: N00tl*N(ilE CWEIGHT AND BA~ANCE: NO OHANOE.

BPARES nFFECTED: NO.

PVBLICI\TIONS *FFECTED: NONE.

RECORD COMPL(ANCE: Make im ,Ipp,´•opriilto cnlry in airplunr msintannnse racllnl* ax li,llowo: Y~I´•viea Inlilrm,lticln

NI,. SI-1!15. dalrd !I Ocecmbsl´• IOH:I, antillrd "I)owly i*hll Yarvies Bullatin gl´•AH06 illrvixisn II’~, neo,mplilh.dilnd i´•cli!r tl, I)owLy I(l,t~ll Yervicr ilulletin 61-A9H6 i~viuien II lilr I’n,pallrl´• Inlg ncx,k antry.

C

PaEe 2 of Z

D~QPli?ll ROTO L

iStRVICf BULUTI%

ALERT

PROPELLERS MALFUNCTION OF SPRINGS

i. PLANNING INFORMATION

A.

Aircraft (c) Propeller Types

Gulfstream Aerospace Comnander R306/3-82-F17

6900, 6900, 695 and 695A

Fairchild Aircraft SA-227AC (Metro II1) R321/4-82-F/8Fairchild Aircraft SA-227AT (Merlin IVC) R321/6-82-F/9Fairchild Aircraft SA-227TT (Merlin IITC) R324/4-82-F/9Jetstream 31 R333/4-82-F/12CASA 212 R334/4-82-F113

Note: Implement the instructions in this bulletin on all

propellers supplied during 1983 prior to and including

C Berlel No. ORG 61~7183 end on all propellers suppliedin previous years wiEh serial number suffixes /82 and

earlier.

B. Reason

(1) Two cases of feathering spring failures have occuired duringtesting end assembly of propellers at Ocvty Rotol Limited.

Such failure could result in inability to feather a propeller,hut is unlikely Co affect its normal operation. In order to

check that no undetected failures exist it is necessary to

carry out a featherinp check.

C. DescripCion

(1) This bulletin requires operators to carry ouC a groundfeethering check on installed propellers to ensure that the

feather position is achieved. Inability to feather is

recognised by a large angular error in the blade pitch.

n. Compliance

(1) STRONGLY insta lied propellers, within 200 hours or 1 month,RECDMMENDED whichever is the earlier, after receipt of this

bulletin.

uninscalled propellers, after fitmenr Co the

aircraft and prior to first flight.

Sapr. 14/53 61-A995

Nov ?1183 (Revision 1) Page 1 of 3

gBQPV~iill ROTOL

SE~RIICE BU:LLETI#ALERT

(1) This bullerin has been approved by the United ~inpdomCivil Aviation Authority. The technical

content. of the bulletin which affects airworthiness is

approved under the authority of C.A.A. Approval No. DAI/1O18/39.

F. nanpawer

(1) Approximately 15 minutes.

G. Material

(1) None.

H. Tooling

(1) None.

I; Weight

(I) None.

J. n.aerc.ceC

(1) Aircraft Operator’s Manual.

K. Other Publications Affected

(1) The above manual.

2. ACCOMPLISHMENT INSTRUCTIONS

A. Embodiment instrucrio_ns

Note: All engine operation Co be in accordance with aircraft

operating inatrucFians.

(1) Carry out a feathering Eheck in accordance with the following

procedure.

(a) With the aircraft stationary, start engine.

(b) Selectreverse pitch to disengage the starting latches.

(c) Position the power lever between ground idle and flightidle to allow engine conditions to normarise.

(d) Carry out a feather shuc down.

61-as95 Sept. 14/83

Page Nov 21/83 (Revision 1)

ROTOL

SERV~EE BULLETI#ALERT

(e) Note that the propeller blades move Co the feaeher

position.

(f) Operate the unfeather pump to re-engage the propellerstarting latches.

(2) Any propellers failing checks are to be investigaeed and

all springs replaced before

(3) Results of all checks (satisfactory and failures) are to be

reported eo the Prbduct Support Manager, Dowty Rotol Limited,

Gloucester, England, by telephone (0452) 712424 or by telex

43246/7, quoting the propeller Type number, Serial number,

T.S.N., and identifying the spring, i.e. inner or outer,

in the event of a reported failure.

Note: North and General American Operators should report

results to Dowey Rotol Incorporated by telephone703-450-5930 or by telex 824459. South American

Operators should report results to oowey Rotol Limited.

8. Method of Ideneification

(1) Record compliance with this bulletin in the Propeller Log Book.

3. MATERIAL INFORMATION

A. None.

Sepe. 14/83 61-A995

Nov 21/83 (Revision 1) Page 3

iwff~mation


15 February 1984

SCOTT AVIATION CUS’60NIER SUPPORT SERVICE LETTER NO. 893-SL-01

MODELS AFFECTED MODEL 690A, SERIAL NOS. 11249, 11268 THRU 11344.






REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH SCOTI~ AVIATION CUSTOMER SUPPORTSERVICE LETTER NO. 893-SL´•01.

COMPLIANCE: PRIOR TO NEXT FLIGHT AND DURING EACH PPIEFLIGHT INSPECTION UNTIL AFFECTED

MASKS ARE REPLACED.

CIF ANY PROBLEMS ARE ENCOUNTERED WHILE

NOTE

COMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST DULFSTREAM

COMMANDER AUTHORIZED SERVICENTEB.

BY WHOM WORK WILL BE ACCOMPLISHED: FLIGHT CREW ANDIOR A Bc P MECHANICOR

EQUIVALENT.


ESTIMATED MAN HOURS: TEN (10) MINUTES.

PARTS DATA: NEW Pi~ 893-16´•172 SERIES SCOTT MASKS REQUIRED TO COMPLY WITH SCOTT AVIATIONCUSTOMER SUPPORT SERVICE LE1TER NO. 893-81.-01 MAY ns PROCURED THROUGH YOUR NEARESTOULFSTREAM COMMANDER AUTIIORIZID SERVICENTER FOR $168.20 EACH. FOR AIRCRAFT WITHFACTORY EQUIPPED (AFFECTED) MASKS, A FULL CREDIT WILL BE ISSUED FOR MODEL 690C, SERIAL NOS.11651 THRU 11725, MODEL 690D, SERIAL NOS. 16001 THIIU ls0L2. MODel. 695, SERIAL NOS. 95041 THRU 96084AND MODEL 6g5A, SERIAI. NOS. 96Mli THRU 90041 UPON RECEIPI~ OP REMOVED ORIGINAL PIN R93´•16~172SERIES CREW MASK WITH BI.ACK PLASTIC PLOW INDICATOR. A PROPERLY EXECUTED WARRANTY CLAIMAND A COMPI.IANCE CARD LF RECEIVED PRIOR TO 15 FEBRUARY 1SsS.WHEN ORDERIND REPLACEMENT

MASK, ORDER SERVICE INFORMATION NO. 51´•196 I(IT.


I\CCOMPLIS*MENT INSTRUCTIONE:

L Comply with Scott Aviation Cuaronler Support Service Letter No 893´•SL-OL nnd refer to Fib~re L, for nowinrlicator.

Psge 1 of 2

SERVICE INFORMATION NO 51-196

2. Fill out and mail Complirnee Card.

CELECTRICAL LOAD: NO CHANGE.


SP*AEB AFFECTED: ALL AFFECTED CREW MASKS MUST BE REMOVED FROM SPARES STOCK ANTRETURNED TO OULFSTRGAM AEROSPACE CORPORATION.


RECORD COMPLII\NCE: Make an appropriate entry in airplane maintenance records as follows: Senrice Informatio~No. 51-196, dated 15 February 1984, entitled "Scott Aviation Customer Support Service Letter No. 89S-SL-01",accomplished~

FIOW INDICATOR (D,IREF1

-´•i-MASKS WITH SILVERIBL~CK COLORED

FLOW INDICATOR AND HOSE ~hCONNECTION CRIMP MARKS THAT AREPERPENDICULAR TO HOSE FIRE I\CCEPTABLE

OxvoEN MASKIREFI

FLOW INDICATOR

IREFI

MASKS WITHFLOW INDICATOR I\ND HOSECONNECTION CRIMP MARKSTHAT ARE PARALLEL TO NQTEHOSEARETOBEINSPECTE~AND REPLACED CHECK HOSE CONNECTIONS

AT PLUO´•IN END ALSO

FISUrO

Page 2 of 2

No. 893-SL-01November 8, 1983

SCOTT CUSTOMER SUPPORT SERVICE LETTER

Subject: Air Crew Oxygen Breathing System

Manufacturer: Scott Aviation225 Erie Street

Lancaster, New York 14086

Models: P/N 893 Series Air Crew Oxygen Breathing Systemsconsisting of a head harness, facepiece, mask mountedregulator and supply hose.

Applicabtlity: Assemblies manufactured prior to January 1982.

Reference: Sheet 89126-01 Operating and Maintenance Instructions,Air Crew Oxygen Breathing System, Series M893.

Background: There have been a number of reported field incidents of"broken flow indicators" and "hose seperatlons".

Certain environmental conditions experienced on theflight deel; of alrer~fr n~ay eauie dsgradatlan of

components at an accelerated rate. Bright sunlight,heat and ozone often take a toll beyond what would beconsidered "normal" wear and tear.

Discussion: Due to these factors, Scott Aviation is recommendingan inspection of earlier Model 893 Series MaskMounted Regulators to assure continued properfunctioning and service life.

Those 893 Series units having a black (plastic) flowIndicator and longitudinal (parallel to hose) crimpmarks on hose connection should be inspected prior tonext use and prior to each subsequent use untilreturned in exchange for current configuration masks.

Those units having a metal (silver colored) flowindicator and circumferential crimp marks on hoseconnections (Ferrules) Incorporate current methodsof manufacture. These units are not susceptible to

this environmental degradation.

SCOTT AvIATION A FIOGIE INTERNATIONAL COMPANYB225 Elis S1,8sl. Lancaatar. NY(4088 Tel: llBB83-51W Telex: 81-394

SERVICE LETTERi

PAGE 2

Supplier Action: Since indicator her been Cmade of metal and the hose ferrule crimping hasbeen circumferential.

Suggested OperatorAction:

Inspection Check List

i. Check black plastic flow indicator for signs ofcrazing, cracking or leakage.

2. Check all hose ferrules for signs of loosening,separation or leakage.

3. Perform a routine pre-flight test incorporatingdonning and breathing to assure proper overall systemfunction.

Service GulFstreamAerospace

SERVICE INFORMATION NO. SI-1O?A

(Supersedes Service Information Na. SI-197 in its entirety)15 June 1984

AIRWORTHINESS DIRECTIVE 84-10-06, AMENDMENT 39-4867

MODELS AFFECTED: MODEL 680T, 680V AND B8OW, SERIAL NOS. 1419 THRU 1850.


MODEL 690, 6BOA AND 69011, SERIAL NOS. 11001 THRU 11430, 11432 THRU 11542

CONVERTED FROM TPE331-S´•261K ENGINE TO TPESS1-6-252K ENGINE.

MODEL 690B, SERIAL NOS 11431 AND 11545 THRU 11566.


MODEL 690D, SERIAL NOS. 16001 THRU 15033 AND 15037.


MODEL 685A, SERIAL NOS. 96001 THRU 96061, 96063 THRU 96072, 96075, 96078, 86085

AND 96088.

REASON FOR PUBLICI\TION: TO RECOMMEND COMPLIANCE WITH AIRWORTHINESS DIRECTIVE 84-10-06,AMENDMENT 89´•4861.

COMPLI~NCE: REFER TO AIRWORTHINESS DIRECTIVE 84-10-08, AMENDMENT 39-4867.

BI WtlOM YIDRI( IILL BE I\CCONPUS*..: URWORTIIINESB DIRECTNB Bl-10d6, *MCNDMENT

ESTIMATED MAN HOURS: REFER TO AIRWORTHINESS DIRECTIVE 84´•10´•06, AMENDMENT 39´•4867.

PARTS DATA: REFER TO AIRWORTHINESS DIRECTIVE 84-10´•06, AMENDMENT 59´•4867.

SPECIAL TOOLS: REFER TO AIRWORTHINESS DIRECTIVE 84-10-06, AMENDMENT 39-4861.


NOTE

Carefully review requirements of Gsrrett Tu~bine EngineCo. Service Bulletin TPE331-13´•0121, Revision 2, if priorCompliance with original Service Bulletin TPE331-73-0121

has been accomplished.

1. Comply with Airworthiness Directive 84´•1(1-06, Amendment 39-4867.

2 Fill out and mail Compliilncs Card.


WEI(1WT AND BALI\NCE: NO CHANGE.


PUBLICATIONS AFFECTED: Refer to Airworthiness Directive 84-10-06, Amendment 39-4867

RECORD COMPLIP~NCE: Make an applopriab entry in nirplane maintenance records as follows: Service Information

No. SI´•1S?A, dated 15 June 1984. entitled "Aiwarthiness Directive 84-10-06, Amendment 39-4887". accomplished(date)

Pqeloll

Q AIRWORTHINESS DIRECTIVE

CUSDepamnent IVI*TIOH ITIN~LRDS.LTIOWIL nLD D(TrT

drronrpcnetan r.o. 21041M(UWDMI cml oruwou~ 11121

F~damtAvlatMn

Mrmnkhanon

anur~ i*I*I It* s~nrl Wlninunlia in ~h ih paril~l sal´•nl hn.((on R~LN´• Rn 3P.´•p~n I. rnI~ Wln~llnal.l*l~l´• nu ill´•r ix ih´• a~nhlnl Dl~nm ~nula ul´•l. ~n*rm~sluY11M xMEh r~in i~omali" nl´•sia

a~,,n illlalul,ia r~ rml nw* YI1IIEnll Ih*h U1*ICOnhllU I11 i´•aunn*nu ~llh´• hm*mhiru arrnmls*n

:wl,

84-10-06 GARRETT TURBINE ENFSNE COMPANY GTEC, formerl

RIRESEARCH MANUFACT’iiRIN~;CQMPANY OF ARIZONA): Amendment

~4sF;7. Aphlic~ble to;iT1 series of engine m~dels TPE331-25,-43, -47, -55, -1, -2, -3, -5, -6, -10 (except -10A), and -11

equipped with the following fuel pump assemblies:

P/N S/N

868531 7/-8 All.

869151-1/-3/-4/-5 All.

893573-1 through -7 All.

897380-1/-2/-3 series 1 2.

897380-4/-5 Series i, 2, 3.

897390-1/-2/-3/-4 Series 1 2.

897400-1/-2 Series 1 2.

897400-4 Series ii

Compliance is required as indicated unless alreadyaccomplished.

To prevent possible engine failure, accomplish the

following:(a) Inspect low-time engine fuel control/pump assembly to

determine drive shaft running torque as specified in Section

2.A.(2), "Accomplishment Instructions," of GTEC SE

TpE331-73-0121, Revision 2 dated April 18, 1984, or equivalentapproved by the Manager, Western Aircraft Certification Office,in accordance with the schedule below:

Fuel pump assembly time: since new or since last

as sembled; or engine total time since new or since last

overhauledi whichever is known to be least,

Hours Inspect not later than

Less than 200 the next 100 hours in service

200 or more, the next 200 hours in service

and less than 1,000

1,000 or more next fuel pump disassembly

NOTE; Engine Logbook Records should indicate if a new or

reassembled fuel pump assembly has been installed on the enginesince new or returned from overhaul.

Remove from further service fuel pump assemblies havingunsatisfactory running torque inspection results unless

2 84-10-06

modified as specified in Section 2, "Accomplishment~nstructions, in SE TPE331-73-0121, Revision 2, or equivalent

approved by the Manager, Western Aircraft Certification Office.

Fuel control/pump assemblies having satisfactory inspectionresults may he continued in service until fuel pump disassembly

per Paragraph (b) below.

(b) Upon clisassembly of fuel pump for any reason,

reassemble to an approved parts configuration as specified in

Section 2, "Accomplishment Instructions," of SE TPE331-73-0121,

Revision 2, or equivalent approved by the Manager, Western

Aircraft Certification Office.

(C) Special flight permits may be issued in accordance

with Federal Aviation Regulation FAR 21.197 and FAR 21.199 to

ferry aircraft to a maintenance base in order to comply with

the requirements of this AD.

(d) Alternative means of compliance providing an

equivalent level of safety may be used when approved by the

Manager, Western Aircraft Certification Office, FAA, Northwest

Mountain Region.(e) Upon request of the operator, an FAA Maintenance

Inspector, subject to prior approval of the Manager, Western

Aircraft Certification Office, FAA, Northwest Mountain Region,may adjust the compliance schedule specified in this AD to

permit compliance at an established inspection period of the

operator if the request contains substantiating data to justify

The manufacturer’s specifications and procedures identified ithe adjustment for that operator.

and described in this directive are incorporated herein and

made a part hereof pursuant to 5 U.S.C. 552(a)(1).All persons affected by this directive who have not already

receivedthis document from the manufacturer may obtain copies

upon request to Garrett Turbine Engine Company, 111 South 34th

St., P.O. Box 5217, Phoenix, Arizona 85010; telephone (602)231-1000. This document also may be examined at FAA Rules

Docket 83-ANE-29, New England Region, Office of the RegionalCounsel, 12 New England Executive Park, Burlington,Massachusetts 01803.

This amendment supersedes Amendment 39-4840 (49 FR 13487),AD 84-07-08.

This Amendment 39-4867 becomes effective May 30, 1984.

FOR FURTHER INFORMATION CONTACT:

Bob Liddiard, Aerospace Engineer, ANM-174W, Western

Aircraft Certification Office, Northwest Mountain Region, P.O.

Box 92007, Worldway Postal Center, Los Angeles, California

90009, telephone (213) 536-6380.

I~_ __

SerpliceGulfstreamAerospace


26 May 1984

FUSELAGE STATIONS 386.85 AND 409.56 PULLEY BRACKET MODIFICATION


MODEL 690, SERIAL NOS. 11001 THRU 11019MODEL 690A, SERIAL NOS. 11100 THRU 11349.MODEL 690B, SERIAL NOS. 11360 THRU 11566.MODEL B90C, SERIAL NOS. 11600 THRU 11732.MODEL 39011, SERIAL NOS. 15001 THRU 15025, 15029 THRU 16032 AND 16037.MODEL 695, SERIAL NOS. 86000 THRU 95084.MODEL 695A, SERIAL NOS. 98001 THRU 96055, 96059 THRU 96061, 96064, 96085 AND96012.

REASON FOR PUBLICATION: TO ELIMINATE THE REQUIREMENT FOR REPETITIVE INSPECTION OFRUDDER CABLES PER SERVICE BULLETIN NO. 195A.


NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST DULFSTREAMCOMMANDER AUTHORIZEO SERVICENTER.

BY WHOM WORK WILL BE ACCOMPLISHED: A L P MECHANIC OR EQUIVALENT.

APPROVAL: ENGINEERINC- DESIGN ASPECTS ARE FAA APPROVED.

ESTIMATED MAN HOURS: MODELS 685, 690, 690A AND 6908 THIRTY (30) HOURS.MODEL 6900, SERIAL NOS. 11600 THRU 11718 FORTY FIVE (45) HOURS.MODEL 690C, SERIAL NOS. 11119 THRU 11132 THIRTY (SO) HOURS.MODEL 690D THIRTY (30) HOURS.

MODEL 696 FORTY FIVE (46) HOURS.MODEL 695A, SERIAL NOS. 96001 THRU 96013 AND 96018 FORTY FIVE (46)HOURS.MODEL 695A, SERIAL NOS. 96014 THRU 96011 AND 96018 THRU 96012 THIRTY (30)HOURS.

PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION LETI‘ER MAY BEPROCURED THROUDH YOUR NEAREST CULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR(208.46. REFERENCE THIS SERVICE INFORMATION LE~PTER, AIRCRAFT MODEL AND FACTORY SERIALNUMBER WHEN ORDERIND SERVICE INFORMATION NO. 51-199 KIT CONSISTIND OF THE FOLLOWING:

prln lual´•a lo~h´•ny´• mtn~M notlu

Page 1 of 8

SERVICE INFORMATLON NO. 81-186


~USELAOE 5rPI. 386.85EXISTING ANGLES

ANGLES IVY/ IREFIIREFI lit~

c i"

M92456648 PULLEY

PULLEY ~iJ IAEPIIREF)

\C C

Gj~J, InEF1

EXISTINGWEB

c i -r- ExlsnNo WEB

h InEFI

530087´•REllDOUBLER

aBrREFI

BInEFI

IREF)LEFT INSTALLATION SHOWNRIGHT INSTALLATION OPPOSITE Fieura i.

CPUZ1LAOI STA. 386.85

De’lAll P. DImll B

EXISTING NAS427K11

GUARDPIN

InEFI

i i IREPI

HUCK BOLT i

t laPLsl (nsPI

i,TOOLTIOOB´•3.f DOUBLER

LOCATE AND DRILL

DII\.HOLE

´•I(0.211(1"/0.2172" DIA. HOLE

MS21044Nd NUTANBBOD41BWI\SHERI\N4´•llA BOLT

SHADED AREA

INDICATES AREA C-~ HLZZOPBBbPINTO BE REMOVED

i IHI SHEI\AI MS2QBB´•48 PULLEYTO INSTALL HLBJ-S COLLAR

PULLEY ANGLE0.2142"10.2112" DIA. HOLE

HL220PBB´•8 PINIREF)

0.2112"10.2112" DIA. HOLE (HI SHEARIHLZZOPBB´•SPIN ~NBBOOIOWASHER

(HI hHEAR) IUNDER HEAOInL83´•BCOLLPIR HLII´•B COLLAR

VIEW LOOKING AFT

Figure

Page 2 of B

SERVICE INFOIIMATION NO. 91-399

$TY PART NO. DESCRIPTION

4 ea. ANB-4A Bolt

2 ea. AN(´•11A Bolt

2 ea. AN6-22A Bolt6 ea. AN960D10 Washer8 ea. AN960D416 Washer4 ea. AN860´•616 Washer

6 ea HL220PBG-5 Pin6 ea. HL93-6 Collar4 ea. MS2104JN3 Nut

2 ea. MS21044N4 Nut2 en. MS21044N6 Nut2 ea. MS21051L3 Nutplate6 ea. M621256-1 Turnbarrsl Locking Clip2 ea. MS24566-4B Pulley2 ea. MSP(SB6-SB Pulley2 ea. MS35207-265 Screw

12 ea. NAS1080-6 Collar

12 ea. NAS1465-S Huckbolt2ea. NAS43DD6-60 Spacer1 ea. 53(1481-RE6 Anglei ea. 530481-RE6 Angle1 se. 530487-REll Doubler

1 ea. 530487-RE12 Doubler2 ea. 530487-BE19 Spacer2 ea. 530487-B316 Spacer1 se TS0063 Drill Template1 se. Compliance Card1 ea Service Information No. 9I´•lsD instructions

SPECIAL TOOLS: HUCK GUN AND TS006´•9 DRILL TEMPLATE.

ACCOMPUSHMENT INSTRUCTIONS:

I. Gain secess to rudder pulley brackets, located at fuselage stations 386.85 and 409.56, through aft fuselage access

doors or through baggage eompartment door.

2. Remove tail cans and remove left and right inspection panels, located on aft fuselage just below horizontal

stabilizer, to gain access to rudder and elevator control cables.

1 caurmtlEAUTION

Clamp cables forward of station 386.85 to prevent cables

From slipping alforward pulleys or cable drums. Stow and

protect cables from kinking or bending damage while

accomplishing this modifieatian.

3. ~Disconnelt left and right rudder cables st tumbarrsls or at rudder horn assembly.

1. Disconnect leR and right elevator cables at turnbarrels or st elevator idler tube link assemblies to facilitate

modification of rudder pulley bracket aslemblies.

5. Modify left and right pulley bracket assemblies at fhselage station 386.85 as follows:

a Remove and discard existing left and right pulleys and attaching hardware. Retain existing NAS427Kllcable guard pins far inter reinstallation (refer to Figures 1 and 2).

h. Using 530481-HEll and 530487-AEll doublers as templates, mark and lengthen existing pulley cutoutsin existing same web to four ii) inches (refer to Detailk, Figure 2).

Page 9 of 8

SEBVICE INFORMATION No. SI-189

,UIII*Ol 11*´•

EXISTINGCABLE ounnr, PIN

IREPI LEFT INSTALLATION SHOWNRIGHT INSTALLATION OPPOSITE

ExlsrlNaPULLEY D

EXISTINGCABLE GUARO

PIN BRACKET

IREF)

BEFORE CHANGE

figure 3.

O408.68

VERTICAL BRACKETIREFL

C,

REMOVE PER --r V

srEPa.~.

1.501’ ,8´•´•

HORIZONTALBRACKET

IREFI

VIEW LOOKING DOWN

Pigu,s 4.

Page 4 or B

SEIIVICE INFORMATION NO. S1-189

CAUTION

Care should be taken when drilling out rivets in pulleyangles to prevent elongating holes in brace, web andangles if proper hole sizes and minimum 1.5 edge distancecriteria cannot be maintained in brace, web and angles,replafement of Chase parts may he required.

c. Carefully drill out and remove nine existing rivets that attach existing.‘pulley angles (refer to DetailA. Figure 2).

d. Locate, drill and install 530487-REll doubler (leR side), 630481-8112 doubler (rightside), 530487´•RE13

spacers and 530487-8115 spacers using NAS1(65-5 huckbolta, NAS1OBO collars. HL220PB6´•6 pins,AN860D10 washer and nL93-B collars(refer to Detail A, Figure 21.

a. Using TS006-3 drill template, line drill 0252 (10.002) inch diameBr hale through existing angles (I´•eBrto Detail 8, Figure 2).

NOTE

Use end of tool with short drill bushing that is markedyr383.

f Deburr holes and touchup paint with zinc chromate primer,

g. Install MS24566´•4B pulley, on left and right side using ANI-11A bolt. ANSM)D4L6 washer and

i MS21044N4 nut (I´•eB1´• to Detail B, Figure 2).

6. Modify i~rt right pulley bracket assemblies at fuselage station 40966 as follows:

a, Remove and discard existing NAS427K12 cable guard pins irefer to Figure 51.

b. Remove and discnl´•d existing left and i´•ipill pulleys and attaching hurdwal´•e ircLI to Figure 3).

c. Drill out rivets and discard existing cable guard pin bracket irerer to Figure 3).

d. Trim forward nange on existing left and i.ight horizontal brackets os shown on Figure 4 and deburl´•edges of

e Using TS006´•3 drill teml,lote, drill 0.3111~0.002) inch diameter irole through left and right verticalbrackets IreWr to Figure 51.

NOTE

Use rad of tool with long drill buslling that is markedY=409.

f Clamp 530481-KIC, angle tlelt aide) ond 530187-llB6 angle (rigbt sider to bottom side of existingbol´•i~ontal h´•oekets and,ncrk hole location on angles (refer to Pigul.e 51.

g Measure vertical dimonsio,~ on angle, ol,tained in step 1:, and transfer ciimensios to opposite end of angleand drill 0.377 it0.002) inch diameter hole in 530487-R&5 and 53U487-HE6 angles (re~8r to Pigulr 51.

h. Touchup paint on brackets and angles with zinc chromate primer

Install MS210511.3 nutplnte over existing cable guard hole in vel.ticai bracket (I.rLI to Figure 61.

Page 5 of 8

IERYICE INFORMATION NO. SI-199

*poslnoN OF ANGLE ASSHOWN 18VERTICAL BRACKET FOR OBTAINING VERTICAL DIMENSION(REFI OF HOLE LOCATION. ANGLE WILL BE

TURNED AROUND 1800 ON FINAL INSTALLATION

HORIZONTAL 3RPICKET

(REF)VERTICAL BRACKET

HORIZONTAL BRI\CKET

53M87´•RES ANGLE

POSITION ANGLE APPROXIMATELY

TO LOCATE VERTICAL

DIMENSION ON ANGLE

i. USING TSOOBJDR(LL TEMPLATE.LOCATE AND DRILL P.3711/~´•379´•´•DIA. HOLE THRU VERTICALBRACKET PER STEP 8.a.

2. CL~MPS30(s7´•RES AND ´•REB

ANGLES ON HORIZONTAL BRACKETS

AND MARK HOLE LOCATION ON

ANGLES PER STEP 6.1.

TS00830R(LLTEMPLATE VIEW LOOKING INBD

0.375" DIA. HOLE WILL FALL ON EDGE

OF HORIZONTAL BRACKET FLANGE

TRANSFER THIS MEASURED

DIMENSION TO OTHER ENDANO DRILL HOLE AS SHOWN.

53M87-RE6fl.o´•´• FLANGE

ANGLE i.

0.375"10.379" DIA.HOLE

DIMENSION MARK

MADE PER STEP 8.1.

PiBurs 5.

Page a ot 8

SEAYICE INFORMATION NO. SI-188

CHOLESINBRACKET

ACCEPTAQLE

L’/d *N ADDITION OF ONE Ill WASHER

MAY BE INSTALLED UNDER BOLTHEAD OR NUT PROVIDED P,MINIMUMOF ONE lijfjiREl\O EXTENDSTHROUGHTHENUT.

630181-866 ANGLEIREF)

MS21044N8 NUT. ANBBOB1BWASHER

EXISTING HOLE

IREFI

AFTER CHANGE

M82468868

FiYCC-I-----; liZO.ls0’7o.194’~ DII\.

HOLE

ANJ-~BOLTANBBOOIOWASHER

ANB-22ABOIT’ 1 111 MS21041N3 NUT

12 PLSI0.50~

EXISTING HOLE

MSZ1D61L3 NUTPLPITEMSJ6207286SCREW

WITH MS20PIOAD3 RIVET

I? PLSI

-O- o\

M824SBBaBPULLEY iIREFI

IF INTERFERENCE EXISTS BETWEENRIVET AND ANIBO´•BIB WASHER. REPLACE

RIVET WITH RIVET II\CCEPTABLETO USE MSZ04ZBAOS RIVET AND SHAVE

HEAD OF RIVETI.

630dBI´•RES PINGLE


RIG HT I NSTALLATIO N OPPOSITE

sm.

~oe.se

Figure 6.

Page 1 of 8

SERVICE INFORMATLON NO SI-199

i ineisll M6a(86-Ln lulby ~ind 590(87´•1116 ´•Wlo (Idt aids), 69D~87REB allgle inght aid.) ulin~ ~N6´•22A bolt, NAS4SDD6-60 spacer, AN960´•616 washer (2 places) and MS21044N6 nut il´•efer to Figure 6)

NOTE

Do not drill hulea in 0.75-inch nange ofangle Far attachingangle to hori2ontal bracket at this time. Holes will bedrilled after assurance alprapsr alignment of pulleys.

k. Reconnect left and right rudder cables at turnbarreis or at rudder ham assembly and apply slighttension on cables to assist in alignment.

i. Assure that pulley is properly aligned to allow cable to operate smoothly over pulley. This can heobtained by positioning ofangle Clamp angle into place end drill two 0.192 I+OU02) inch diameterholes through horizontal bracket and angle (refer to Figure 6).

NOTE

Use pilot hole in aft end of angle for ah fastener and Locateforward fastener from existing tooling hole in horizontalbracket.

m. Attach angle to horizontal bracket using AN9-4A bolts, AN960D10 washers and MSa1044N3 nuts (reiel.to Figure 6).

n. install MS35a01-265 screw (used as cable guard) in nutpiate installed in step i. (rsfer to Figure 6)

7. Reconnect left and right elevator cables at turnbarrels or at elevator idler tubs link assemblies

8. ReinataB guard .ins at hualsls 386

9 Check rigging and tension of rudder and elevator controls as outlined in the applicable Airplane MaintenanceManual and functional check system.

10 Reinstail tail cone and inspection panels on airplane.

11. Fill nut and mail Compliance Card.




PUBLICATIONS AFFECTED: The Illustrated parts Catalog Changes required by this document will be incorporated atthe next scheduled revisisan.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service InformationNo. SI-199, dated 25 May 1884, entitled "lluselage Stations 386.85 and 409.56 Pulley Bracket Modification.., accomplished

(date) Note in maintenance records that repetitive inspection per Service Bulletin No. 195A is herebywaived.

Page 8 of B

I __

Service inlf~rmation GulfstreamAerospace

SERVICE INFORMATION NO. SI-20016 July 1884

EXnAUST GAS TEMPERPITURE (EOT) INDICATOR ISOLATOR INSTALLATION

MODELS AFFECTED: MODEL 695, SERIAL NOS. 95000 THRU 96084.MODEL BSSA, SERIAL NOS. 96001 THRU 96061, 46065 THRU 96072, 96015. 96078, 96088AND 96088.

REASON FOR PUBLICATION: AS THE EGT HARNESS AGES, IT BECOMES SUSCEPTIBLE TO BREAKDOWN OFINSULATION BETWEEN THE THERMOCOUPLES AND THE OUTSIDESHIELDING OF THE HARNESS. THE ISOLATOR WILL ELECTRICALLY ISOLATETHE HARNESS FROM THE INDICATOR AND PREVENT ERROR CAUSED BY THEBREAKDOWN.


NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYINCI WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST GULF8TREAMCONM*NOER hmBORIZED BERVICENTER

BY WHOM WORI( WILL sE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT

APPROVAL: ENGlNEdRINO DESIGN ASPECTS ARE FAA APPROVED.

ESTIMATED MAN HOURS: THIRTY (801 MINUTES.

PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCUREDTHROUDH YOUR NEAREST DULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR $888.60.REFERENCE THIS SERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIAI. NUMBER WHENOHIIEKINC´• SERVICE INFORMATION NO SI-200 KA CONSISTIND OF THE FOLI.OWIND:

n~Un

~TY PART NO. DESCRIPTION

2 ea. 400188´•5 tMaricopa Controls) Isolator1 as Compliance Card1 ea. Service Inlormstion No. SI-200 Instructions


L. Loosen screws attaching EGT indicator to center instrument panel and pull EGT indicator out.

2. Disconnect electrical connector Emm ECT indicator and connect 400266´•3 isolator to EDT indicator (re~er toFigure 1).

3 Connect airplane electrical connector to 400288´•5 isolator (reBr to Figure 1).

Page 1 oE2

FIERYICE INFOHMATION NO. SI´•200

4. Insert isolator thru panel and reinstall EGT indicators on center instrument panel and lighten sorews.

Ci. Assure that EGT indicators are functional and working properly.

B. Fill out and mail Compliance Card.


EXIGTINB I\IRPLANEELECIRICAL COIINECTOR

(REF1

EXI~TINO IXHAUST (11\8

TEMPERATURE IND1CI\TORIREPI

Am ´•I.

WBIOHT AND BILANCE: The weight and balance change resulting Rom installation of this Service information is as

follows:

WEIOHT(LBS) H´•ARM (INDHES) H-MOMENT IIN-LBS)+l.ls ?0.0 +81.0

SPAAES AFFECTED: NO.

PUBLICATIONS AFFECTED: The illustrated Parts Catalog change re~uired by this document will be incorporated at

the next soheduled revision.

RECOAD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Information

No. 61-200, dated 16 July 1984, entitled "llhsust Oas Temperature (EDT) Indicator lsalator Installation", accomplished(datel

L

2 of 2

c Service informationGulfstreamAerospace

SERVICE INFORMATION NO. 81-20126 July 1984

OARRETT SERVICE BULLETIN TPE331-73-0128

MODELS AFFECTED: MODEL 695, WITI-I ESOINE SERIAL NUMBERS PRIOR TO P58962.MODEL 69SA, WITil ENDINE SERIAL NUMBERS PRIOR TO P39552.

NOTE

Regardless of engine serial number, verification of fuelmanifold part number should be accomplished. (Refer toDarrett Service Bulletin TPE331-13-0128, paragraph2.A.(2).)

REASON FOR PUBLIC~TION: TO RECOMMEND COMPLIANCE WITH GARRETT SERVICE BULLETIN TPE331-19-0128.

COMPLIANCE: REFER TO OARRETT SERVICE BULLETIN TFE991-13:0128.

BY WHOM WORK WILL BE ACCOMPLISHED: A B P MECHANIC OR EQUIVALENT.

C/ EBTIM~TED.IIN nouns; ~eR TO UANR.~ SERVICE BOLl~eTIII TP&991-?SoL1B DIITED is NOVEMBER

PARTS DATA: ONE EACH DUPLICATE CERTIFICATE OF COMPLIANCE

SPEICALTOOLS: NONE.

~CCOMPLISHMENT INSTRUCTIONS:

NOTE

Carefully review the requirements and thoroughlyunderstand the procedures outlined in Garrett ServiceBulletin TPE931-13-0128.

1. Comply with Garrett Service Bulletin TPE331-7S´•0128.

2. Fill out and mail the CERTIFICATE OF COMPLIANCE and DUPLICATE Certificate of Compliance.

ELECTRICAL LOAD: NO CHANCE


SPARESAFFECTED: REFER TO DARREW SERYICE BULLETIN TPE391-13-0118, MATERIAL INFORMATION,FOR SPARE PARTS REqUIRED,

PUBLICATIONS AFFECTED: REFER TO OARRETT SERVICE BULLETIN TPESS1-13-0128.

RECORD COMPLIANCE: Make an appropriate entry in the airplane maintenance records as follows: ServiceSlao~, d´•t~ P6 duly LBBC sntillai .O.mtl Sar*iE´• BullsLm TPE881´•n~ll(i.. n~mpllahid

Page 1 of 1

/~3 SEaaylGE IULLETBNGARRETT TURBINE ENGINE COMPANY

.CINF rUFL (WD (OHTR~L DLITRIBUTION In~pecr hi.l Naniiold~ far iealage

i. Planning Information

A. Effectivity

This service bulletin is applicable to the following turboprop aircraftengines.

Prior toPart No. Model No. Serial No. Application

3101470-1 TPE331-8-401S Conquest II3102510-1 TPE331-8-4025 Conquest II3102510-2 TPE331-8-403S Conquest II3101470-2 TPE331-8-404S Conquest II3102170-1/-2 TPE331-10-501C CASA 212-2003102190-1 TPE331-1O-501K Jetprop

Commander 695/980 JetpropCommander

695/1/10003102180-1 TPE331-10-501M Mltsubishl

Marquise/solitaire

3102170-5 TPE331-10-511C CASA 212-2003102190-2 TPE331-10-511K Jetprop

Commander 695/980 JetpropCommander

695A/10003102180-2 TPE331-10-511M Mftsublshl

Marqulse/Solitaire

3102170-3 TPE331-10R-501C CASA 212-2003102170-4 TPE331-10R-502C CASA 212-2003102170-6 TPE331-10R-511C CASA 212-2003102170-7 TPE331-10R-512C CASA 212-2003103090-1 TPE331-10U-501E No Current

Application3102050-1/-2 TPE331-10U-501G Merlin IIIB3102050-3 TPE331-1OU-502G Merl in IIIB3102940-1 TPE331-10U-5036 Merlin IIIC3102050-4 tPE331-10U-511G Merlin IIIB3102050-5 TPE331-10U-512G Merlin IIIB3102940-2 TPE331-10U-5136 Merlin IIIC3103230-2 TPE331-10UA-501G Metro II3103230-1 TPE331-10UA-511G Metro II3102600-1 TPE331-1OUF-501H Jetstream 313102600-2 TPE331-10UF-511H Jetstream 313102540-1 TPE331-llU-601G Metro III/i Merlin IVC

Nov 18/83 TPE331-73-0128

Page 1 of 8Copyright 1983 by The Garrett Corporation

[F~ SEW?IIGE BULLETIIa

GARRETT TURBINE ENGINE COMPANY

Prior toPart No. Model No. Serial No, Apollcation

3102540-2 TPE331-llU-6026 Metro III/Merlin IYC

3102540-3 TPE331-11U-611G Metro III/Merlin IVC

3102540-4 TPE331´•llU-612G Metro III/Merlin IVC

3102920-1 TPE331-11UA-601W Pucara 1A-663102920-2 TPE331-llUA-611W Pucara IA-66

*Effectlvity may be determined by visually checking the manufacturer’spart number on fuel manifolds,

8. Reason

To inspect fuel manifolds that have shown a potential to leak at weldedjoints.

C. Descriptfon

This service bulletin provides instructions for inspection of andreplacement (if needed) of Manifold Assemblies, Part No. 3102469-1

1.0. Tag, Pdrt No. 28882).

D. Compliance

Recommended. Garrett recommends that this service bulletin be accom-

plished at next exposure of affected part and every 100 hours (if noleakage occurs) until fuel manifold is replaced with a manifold whichhas a manufacturer’s part number other than Part No. 28881. InspectionIs no longer required following replacement of fuel manifold.

E, Approval

The inspection authorized by this service bulletin has been found tocomply with applicable Federal Aviation Regulations and is FAA approved.

F. Manhour Requirements

An estimated one manhour is required to accomplish this inspection afteraccess to part is obtained.

G. Material Price and Availability

Information regarding price and availability of parts may be obtainedfrom a Garrett authorized Servf ce Center or the aircraft manufacturer’sappointed service factllty. (Refer to Service Information Letter(S.I.i.) P331-27 far a complete listing of these f~cllities.)

Nov 18/83 TPE331-73-0128

Page 2

I~ilti 5EXM36~ BULEETPMGARRETT TURBINE ENGINE COMPANY

CH. Tooling Price and Availability

No special tooling required except that already listed in referenced

manual(s).

I. Weight and Dalance

No change.

J. Publications References

The sources of information used in the preparation of this service bul-letin include Garrett engineering documentation and the followingpubiication(s).

IllustratedPart/ Overhaul Maintenance PartsModel No. Manual Manual Catalog

TPE331-8-401S NA *72-00-13 72-00-11TPE331-8-402S NA "72-00-13 72-00-11TPE331-8-4035 NA *72-00-13 72-00-11TPE331-8-404S NA f72-00-13 72-00-11TPE331-1O-501C NA "72-00-28 72-00-21

C TPE331-10-101K NEI ’12-00-29 1P-00-21TPE331-1O-501M NA *72-00-27 72-00-21TPE331-1O-511C NA *72-00-28 72-00-21TPE331-10-511K NA *72-00-29 72-00-21TPE331-10-511M NA *72-00-27 72-00-21TPE331-1OR-501C NA *72-00-28 72-00-21TPE331-10A-502C NA *72-00-28 72-00-21TPE331-10R-511C NA *72-00-28 72-00-21TPE331-10R-S12C NA *72-00-28 72-00-21TPE331-10U-501E NA *72-00-42 72-00-41TPE331-10U-501G NA *72-00-23 72-00-21TPE331-10U-502G NA *72-00-23 72-00-21TPE331-10U-503G NA *72-00-30 72-00-21TPE331-1OU-511G NA *72-00-23 72-00-21TPE331-10U-512G NA *72-00-23 72-00-21TPE331-10U-513G NA *72-00-30 72-00-21TPE331-10UA-501G NA *72-00-45 72-00-44TPE331-1OUA-511G NA X72-00-45 72-00-44TPE331-1OUF-501H NA *72-00-42 72-00-41TPE331-10UF-511H NA *72-00-42 72-00-41TPE331-11U-601G NA *72-00-25 72-00-24TPE331-1lU-602G NA *72-00-25 72-00-24TPE331-llU-611G NA *72-00-25 72-00-24TPE331-llU-612G NA "72-00-25 72-00-24TPE331-llUA-601W NA *72-00-25 72-00-24TPE331-ilUA-611W NA *72-00-25 72-00-24

*Affected Chapter/Sectlon/Subject 73-10-09.

Nov 18/83 TPE331-73-0128

Page 3

$ERVICE BULLETI~GARRETT TURBINE ENGINE COMPANY

K. 9,,,,, Bullefin CNone.

L. Other Publ~catlans Affected

Same as those listed under ’Publlcatlons References’.

Nov 18/83 iPE331-73-0128

Page 4

SE~VICEB


i. Accomolishment Instructions

NOTE: Manuals listed in Section 1 provide applicable disassembly,cleaning, inspection, reassembly, and testing instructionsand shall be referred to during the accomplishment of thefollowing instructions.

Paragraph A provides instructions for inspection of fuelmanifold assemblies, Paragraph B provides instructions for

removing and replacing of fuel manifold.

Inspection is applicable to only those Fuel Manifolds, PartNo. 3102459-1, that I.D. tag indicates Manufacturer’s PartNo. 28881.

A. Inspect Fuel Manifolds, Part No. 3102469-1 for Leakage

NOTE: Do not remove any items that would prevent engineoperation. Engine to be operated in performance offuel manifold leak check.

(1) Remove aircraft mounted equipment to gain access to affected partIn accordance with Aircraft Maintenance Manual.

(2) Check I.O. tag an fuel manifolds far manufacturer’s Part No. 28881.If I.D. number is not 28881, no additional action is required,proceed to step (6).

(3) Start and operate engine at propeller governing mode in accordancewith Engine Maintenance Manual. Observe fuel manifolds duringstart, if leakage is noted, abort start.

(4) Inspect fuel manifolds for leakage, paying particular attention towelded areas.

jSJ If no leakage is noted, reassemble aircraft mounted equipment inaccordance with Aircraft Maintenance Manual. if any leakage isnoted, replace fuel manifolds. Refer to Paragraph B for replace-ment instructions.

(6) Upon completion of aircraft reassembly, check and ensure proper en-

gine operation in accordance with Aircraft Flight Manual.

(7) Upon completion, make entry in engine log book noting engine oper-ating time land serial number of installed component if applicable)and compliance with this service bulletin land service bulletinrevision number if applicable).

(8! Reidentification of equipment not required.

(9) Complete attached Compliance Certificate and mail.

Nov 18/83 TPE331-73-0128

Page 5

SEWVB@E BULIE’BI~P

O\RREST TURBINE ENGINE COMPANY

NOTE: Return removed fuel manifolds to Garrett TurbineEngine Company, Phoenix, Arllona for exchange.

8. Remove and Replace Fuel Manifolds, Part No. 3102469-1

(1) Disassemble engine as needed to gain access to and remove affectedpart in accordance with Engine Maintenance Manual.

(2) Install and leak check replacement fuel manifold, which has a

manufacturer’s part number other than Part No. 28881, in accordancewith Engine Maintenance Manual.

(3) Reassemble engine in accordance with Engine Maintenance Manual.

Nov 18/83 TPE331-73-0128

Page 5

SERIB@EGARRETT TURBINE ENGINE COMPANY

3. Material Information

NOTE: Applicable illustrated parts catalogs and spare parts bul-letins dated later than the original issue date of thisservice bulletin may introduce different parts forinstallation, Refer to these documents before orderingparts.

Expendable parts discarded in gaining access to the af-fected area of the equipment are not included.

The following parts are required to accomplish the instructions outlined inthis service bulletin.

Unit

List instructfuns-New PN Ouantltv Price" Key Ward Old PN Disposition

a3102469-1 1 or 2 Fuel Manifold #3102469-1 0, T

Disposition Code O. New part is available on exchange basis. Contact your ser-vice agency for details.

Ol.llorit~on C~de T. Return Part to barrett Phoenix, Ar(lona far exchange.

bWith manufacturer’s Part No. 28881

~With manufacturer’s part number other than Part No. 28881

*Refer to Section 1, Paragraph G for information regarding price and availabil-fty of parts.

Nov 18/83TPE331-73-0128

Page 7/a

DUPLICATE

Certificate of Compliance

To: Operator Dr SeNice Center Pslforming Modification.

Upon modification of equipment, pleare fill in the information requertsd below, then fold, ~taple, end drop the

completed certificate into the mail.

Owner/Operator

Engins/squipmsnt Part No. Model No.

Serial Na.

No. 1 Na. 2 Na. 3 No. 4

TSN/TSO

No. 2 Na. 3 No. 4

Cycler

No. 1 No. 2 No. 3 No. 4

I certify that the above engine/equipment her been modified in accordance with the following Service Bulletin(l).

SE No. Rev No. SE No. Rev No.

SE No. Rev No. 33 No. Rev No.

SE No. Rev No. Ss No. Rev No.

Signature Dare

Title

CulfJlream AemspareCorpontion

clots i,´•al) q

~IService informationGulfstreamAerospace

SERVICE INFORMATION NO. 81-20214 February 1986

KING RADIO SER\IICE MEMO #319, REVISION 1

MODELS PIFFECTED: THE FOLWWING MODELS, IF EqUIPPED, WITH KING KFC 200, KFC 260 OR KFC 300AUTOPILOT SYSTEM INCORPORATING KSA 570, KSA 571 OR KSA 312 AUTOPILOTSERVO’S:

MODEL B90A, SERIAL NOS. 11100 THRU 11544.MODEL BgDB, SERIAL NOS. 11560 THRU 11566.MODEL 690C, SERIAL NOS. 11600 THRU 11734.MODEL 690D, SERIAL NOS. 15001 THRU 16033 AND 16086 THRU 18057.MODEL 695, SERIAL N0S. 86000 THRU 95064.MODEL 69SA, SERIAL NOS. 96001 THRU 96081, 96084 THRU 86068, 96070 THRU 96073,96011, 86092, 96088 THRU g90B1 AND 98095.MODEL 700, SERIAL NOS. 10001 THRU 70092.

REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH KIND RADIO SERVICE MEMO #313,REVISION 1 DATED DECEMBER 6, 1984.

COMPLIANCE: REFER TO KING RADIO SERVICE MEMO #513, REVISION 1 DATED DECEMBER B, 1884(ATTACHED).

WOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING. WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST WLFSTREAMCOMMANDER AUTHORIZED SERVICENTER.

BY WHOM WORK WILL BE ICCOMPLISHED: A p MECHANIC 08 EPUIYALENT.

ESTIMATED MAN HOURS: REFER TO KIND RADIO SERVICE MEMO #313. REVISION t DATED DECEMBER B.1984.

PARTS DATA: REFERTO KING RADIO SERVICE MEMO *S1S. REVISION 1 DATED DECEMBER 9, 1984.



1. Cain access to King Autopilot servos la.sted in aR fuselags.

2. Comply with King Radio Service Memo #513, Revision 1 dated Dseember 6, 1984.

3. Fill out and mail Complianee Card.

ELECTRICAL LOAD: NOCHANGE.

WEIOHTAND BALANCE: NO CHANGE.

SPARES P.FFTCTED: ALL KSA 310, KSA 311 AND KSA 512 SERVOS MUST BE PULLED FROM 8PARES SHELFBTOCK *NO INSPBCPEO PER KI~NO R*DiO SBBYICI: LL&MO XSLS, 8&YISION 1 D*TEDDECEMBER B, 1984.

Page 1 01 2

-----´•---´•--i-´•------´•- ------´•----´•--i- --´•-´•i

I’ EIERVICE INFORMA~ION NO. 9I-202

PUBLICITIONS AFFECTED: NONE.

RECORD COIPLII\NCE: Make an appropriate entry in airplane maintenance records as follows: Servioe InformationNo. SI,2D2, dated 14 Wbruary 1985, entitled "King- Radio Service Memo #S1S, Revision i", complied with or not

applicable (date)

Fake 2 of 2

SERVICE MEMOC: 7RADIO

saav,ceSILES SERVICIJ neMO 1313 Revised

SUBJECTI Improper Assembly of IISA 370, RSA 371, end

RSA 372 Clutch Assemblies

R possibility exists that improperly assembled clutch assemblies

of ~SR 370, RSA 371, and RSA 372 Servos will not allow the servo

to disengage. The result will be an increase in the frictionforces the pilot has to overcome when manually controlling the

aircraft. The serial numbers of the affected servos are detailed

on Service ~emo t313 Addendum Revised, RPN 600-8313-51.

To eliminate the possibility of improper assembly in the future,the clutch has been improved. Service Fulletins KSA 370-5,55A 371-3, and RSA 372-1 identify the change to the clutch

assembly.

Ring desires to replace all servos which may he improperlyfrom the i date of thissssembleb. ver ninety (90) E;li; pay_rg~olYA c~ir(bta]letion. andservice memo revision, Ring

freight charges for exchanging gpy´•qt~ybmE serial number

appears on the serial in Service nemo (313

C Iddendu. Revised. Gre~iun freight charges one-rayand normal surf bel or eouivelent) freight chargesfor the return Ring will also cover the cost of inspectingan aircraft to determine if any of the listed servos are installedsubject to the following constraints;

A. The aircraft must have been delivered from the manufacturer or

field installaticn completed after August 31, 1981, and haveRSA 370, ISA 371, or nSA 372 Servos installed.

oR

The aircraft must have undergone maintenance and had a

RSA 370, RSA 371. or RSA 312 Servo changed out after

August 31, 1981.

R. inspection must take place within ninety (90) days from dateof issuance of this service memo revision.

To ensure payment for an inspeCtion (including servo removal 4odinstallation as required), submit the following:

i. Proof of new aircraft delivery from the manufacturer or fieldinstallation after August 31, 1981.

on

Proof that replacement servos were installed after

August 31, 1981 (log hook entry or shop order).

Date: 1982 Sn )313 Rev.i. December 5, 1904

SM0007-13 KPN 600-8313-01 Page: 1 of 2

2. An Ae~ standard warranty claim which indicates:r:

a. Peasonable actual time to accomplish inspection (includingremoval end installation as required).

b. Aircraft serial number end registration number.

c. Serial number of all servos inspected.

3. Copy of log book entry detailing the inspection or servo

replacement.

King will not pay for both an inspection and then an additional

labor charge to remove and reinstall the servos at a later date.

This offer to exchange servos and accomplish inspection expiresninety (90) days from the date of issuance of this service.memorevision. King will replace the affected serial number servos at

no charge after ninety days but labor charges will not be paid.

Date; Cay 14. 1982 SC 1313 ~ev.

Pev. i. December 6. 1989

Sn0007-13 leN 600-8313-01 Pager 2 of 2

4

SE RVICE MEIVIOC \Rnoio

SERVICE

SnLEs/ SERVICE neno No: 313 aadenaum aevisea

SVeJECT: Servo Serial Number Gist

KSA 370 RSA 371 8SA 372

3331 2031 1093 11823337 2032 1094 11833339 2043 1117 1184

3343 2044 1120 11853348 2045 1121 11863369 2046 1123 1187

3373 2047 1124 11903376 2048 1126 11923377 2049 1128 11943381 2050 1133 11953383 2051 1134 11983388 2061 1136 11993389 2063 1138 12053391 2064 1139 12083393 2073 1140 19103414 2083 1142 12153(11 2087 1147 12183424 2089 1152 12223427 2092 1158 12263429 2103 1159 12273438 2109 1160 12313445 2111 lie) 12333449 2113 1164 12373498 2134 1165 1238

2137 1166 12411174 12611177 12641179 1265

Date: Hey 14. 1982 Sn 1)13 rdnendum PevisedPev. i. Decembec 6. 1984

Sn0007-15 RPN 600-8313-51 Page; 1 of 1

5

)P"9~

s~-

ServiceGulfstreamAerospace

SERIVCE INFORMATION NO. 81-203

i: 21 February 1885

INLINE PROTECTION FOR FUEL AND OIL PRESSURE TRANSDUCERS

MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11800 THRU 11?36.MODEL B90D, SERIAL NOS. 16001 THRU 15042.MODEL 696, SERIAL NOS. 96000 THRU 95084.MODEL BBSA, SERIAL NOS. 96001 THRU 86100.MODEL 6858, SERIAL NOS. 93063, 96069, 960?5, 960?8, 88085 AND 96201 THRU 96201.

REASON FOR PUBLICATION: SNUBBING OF FUEL AND OIL PRESSURE TRANSDUCERS, CONDUCIVE TOLONGER TP\ANSDUCER LIFE.

COMPLIANCE: AT OWNERS OPTION.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE INFORMATION.CONTACT YOUR NEAREST GULFSTREAMCOMM*NI)ER I\UTHORISEDSERYICEKSER

sv WHOM WORK WILL Bf ACCOMPLISHEO: A g.P MECHANIC OR EQUIVALENT.



PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCUREDTHROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR (8~0.15.REFERENCE THIS SERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHENORDERING SERVICE INFORMATION NO. 81-203 KIT CONSISTING OF THE FOLLOWING:

&TY PART NO. DESCRIP~ION

1 an. AC-1E Snubber4 se. 8-0421g02-116 Haee Asay2ea. S-0d21E08´•116 Bose Assy2 ea. 8-0421308-352 Hose Aasy18 in. 840005 (Code 3719200) Fuel Pressure IdentiBoation Tepe18 in. .940006 (Cede 311931(3) Oil Pleasure Identification Tape1 ea. ComplianceCard1 ea. Servi~e Information No. 81-203 Instructions



1. Remove upper eowling from left and right engines.

Pagsloi4

8ERVICE INFORMATION NO. 81-205

-4-´• ;i’

i-- (j-0421E08-580C:,on. PRESSURE BOSE A89Y

;I

EXISTING 8-042lE0B-243f~ ,FUEL PRESBURE ROSE A88Y

i... (ReF)

j;´•

!7~.-ii

iii:i´•l--´•i:. ii´•~a;´•

WGr;i,.

alli

r

8

~UEL PRESSURE BOSE ASSY

BEFORE CHANGE.;,.,...i

:´•i:´•;L i:

S-- r

OIL PRESSURE BOSE A8SY

8-0421308-380

(RLF);isZ:.

’iL

4h~-lh i~d

i

~I´•

ic~"

,i

LEFT ENGINE SHOWNi R~i

RIGHT ENGINE TYPICAL

Figure 1.

Page 2 ol 4

:r-----´•----´•I--´•´•--;-´•´• ´•-i-.-i~l _,._~.

(IERYICE INFORMATION NO. 81-a09

a -0sa1E0e -Ile AL~-IE 8NOBBERFUEL PRESSURE 8-0411103-138

ROSE ASSY OIL PRESSURE HOSE ABSY

s-o*zlsoz-llas -o,21sas-aszOIL PRESSURE FUEL PRESSURE HOSE ASSEMBLY

ROBE

:j )APPLy 840005 OIL PRESSUREIDENTIBICATION TAPE

i´•: IDENTIFICATION TAPEAPPLY840005 PUBL PRESSURE

r´• (2 PLS)

iiit

i;(i)i:4s-a421Eo8-lle

’’‘e’´• FUEL PRESSURE-’IHOSE k58Y

s-o4alEos-a5zOIL PRESSURE

ROSE ASBY

AFTER CHANGE

o´•

dz~76 n

li-´•

4x,:.iiz~i;

LEFT ENGINE SHOWN

RIGHT fN G IN E TYPICAL i~_.

Figure 2.

Page Sell


a Rrnlur..nd dia.aFd pliami. oil ho´•s aumbl" (RN 90121EM980) rod fu. prsa~uls hose ouambl~(PIN 5-0421E08-2431 from left and right engines (refer to Figure 1).

8 Install AC-1E snubber between S-0421E02-116 hose assembly and S´•0421E08-116 hose assembly. Connect theothe,´• end of 5-0421102-116 hose assembly to fuel pressure transdueer fitting on engine firewali assembly andconnect the other end of 5-0421E08-116 hose assembly to fitting an engine (refer to Figure 2).

4. Install AC-IE snubber between S-0421E02-116 hose assembly and 5-0421108-252 hose assembly. Connect theothel´• end of 5-0421302-116 hase assembly to ail pressure transducer fitting on engine Arewall assembly andconnect the othel´• end of 8-0421808-262 hose assembly to fitting on engine. Use existing clamps and hardwareto secure hose assemblies (refer to Figure 2)

5 Apply 940005 fuel pressure identification tape to both ends of applicable 5´•0421102-116 fuel pressure hoseassemblies (refer to Figure 2).

6. Apply 0~10005 ail pressure identification tape 0 both end. of applicable 5-0421302-116 oil pressure hoseassemblies irefer to Figure 21.

7 Functional check to assure no leaks are evident.

8. Reinstall upper cowling´• on left and right engine..


ELECTRICI\L LOAD: NO CHANGE

WEIGHT AND BP.LANCE: NO CHANGE.

SPARESAFFECTED: SPARES TO PROVIDE NEW HOSE ASSEMBLIES IN LIEU OF 5´•0421B08-245 AND/ORS-0421E08-380 HOSE AISEMBLIES.

PUBLICllnON6 LlfEDIED: Tbs *i~iane Neinteoan.a ibsnu.l .od illusbotsd Pehs Ontol~ chansal .a~juind bgthis document will be incorporated at the next scheduled revision.

RECORD COMPLI*NCE: Make an appropriate entry in airplane maintenance record. as follows: Se.vice InformationNa. SI´•203, dated 21 February 1985. entitled "lnline Protection for Fuel and Oil Pressure Transducers", accomplished

(date)

Page40f4

SE RVICE PUB LI CATIONS

YeVISlOn notice Gulfs~reamAerospace

SERVICE INFORMAT?ON NO. 8I´•20´•1REVISION NO. 1

8 January 1881

OVERBOARD ROUTING OF CABIN EXHAUST AIR

This Revision Notice i. being isausd to delete Model B90C, 8erial Nos. 118(10 thru 11111 and Model 685, Serial Nos.95000 thru 85084. Model and Serial No, ef~ectivities are changed to read as follows:

IODELSIFFECTED: MODEL 6900, SERIAL NO8. 11112 THRU 11?55.MODEL 690D, SERIAL NOS. 15W1 THRU 15042.MODEL 696A, SERIAL NO8. 98001 TEED 98100.MODEL 6968, SERIAL N0S. 96063 96069, 96016, 960?8, 88085 AND 86201 THRU 96205.

Page 1 of 1

_´•

Service informationGuffstreamAerospace


July 7, 1986

OVERBOARD ROUTING OF CABIN EXHAUST AIR

MOOELS ~FFECTEO: MODEL 690C, SERIAL NOS. 11600 THRU 11136.MODEL BBOD, SERIAL N0S. 16001 THRU 15042.MODEL 695, SERIAL NOS. 86000 THRU 95084.MODEL 696A, SERIAL NOS. 88001 THRU 96100.MODEL BgSB. SERIAL NOS. BBO03, 8069, 95075, 96078, 96085 AND 96201 THRU 96203.

REI\SON FOR PUBLICI\TION: TO ROUTE AIR FROM CABIN OUTFLOW VALVES DIRECTLY OVERBOARD ANDELIMINATE HUMIDITY, FROM CABIN, FORMING FROST ON ELECTRONICEQUIPMENT LOCATED ON UPPER NOSE DECK.

COMPLIPINCE: AT OWNER’S OPTION RECOMMENDED FOR AIRPLANES BASED IN OR FREPUENTINGHIGH HUMIDITY AREAS.

NOTI

IT )ih~ PROBL&LaB *RS BNCLIUNTBRFD WHaECOMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST OULFSTREAMCOMMANDER AUTHORIZED SERVICENTER.

BY WHOM WORK WILL BE ACCOMPUSnEO: A L P MECHANIC OR EQUIVALENT,

PIPPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.

ESTIMITEO MIN HOURS: THIRTY-FIVE (55) HOURS.

PARTS D*TA: PARTS REQUIRED TO COMPLY WITH THIS SERV1CE INFORMATION MAY BE PROCUREDTHROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR )820.04REFERENCE THIS SERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHENORDERING SERVICE INFORMATION NO. SI´•204 KIT CONSISTNNI OFTHE FOLLOWING:

qTY PART NO. DESCRIPTION

2 ea. ANI-SA Bolt4 ea. AN?S’ITW10? Clamp

12 ea. AN960D06 Washer2 ea. AN860D10 Washer2 ea. MSZ1047L3 Nutplste6 ea. MS21069L06K Nutplats

I~ra MS96206-229 Sc~ewI se. NCllS´•13-29-4 DuelI as. NC225´•13-52´•4 Duet

C

Page 1 of 11


Is.. Doubler*~y C1 se. 310181-126 Doubler

1 ea. 830156-11 Strip Assy1 se. 880018-503 Vent

1 as. 880113-5 Doubler

2 se, 880114-3 Shroud HalfAssy2 ea. 880714-5 Shroud Half Assy1 se. 8801165 Shroud Assy1 se. Compliance Card

1 ea. Service Information No. SI-204 Instructions

SPECllLTOOLS: NONE,

nCCOMPLISHMENT lNSTRtlCTlONS:

I CIYII.N~IC*VTION

Care should be taken so as not to damage outnow valves

and hoses when performing this modification.

i. Remove upper door assembly from fuselage nose section to gain secess to outnow valves located on forward

pressure bulkhead (rsfar to Figure i).

i. Remove left side and left lower aeeeas doom from fuselage nose section and remove duct to facilitate installation

of e~hauat vent (refer to Figure 1).

i. RBm~YD LR lond"p llsht nsl´• as ~uilm*i in Ch´•pts SS ~Lh´• AliplnnL Msintanaors ManualRemoval of landing light is to facilitate installation of 880113-3 doubler.

4. Remove outnow valves as outlined in Chapter 21 of the Airplane Maintenance Manual.

5. Disconnect flex duct from ram air check valve and remove flen duct from fuselage nose section.

6. Locate and make a cutout in lower left fuselage nose shin for installation of 880113-3 doubler, 510944-13 doubler

assembly and 880018-603 vent. Cutout for vent and doublers is to match enisting vent and doubler cutout on

lower nght side offuselage nose (refer to Figure 1).

7. Locate and drill 880115-3 doubler, 310944-13 doubler assembly and 880018503 vent on lower left fuselage nose

skin (refer to Figure 2).

8. Dimple fuselage akin, 880115-3 doubler, 510944-13 doubler assembly and 880018´•503 vent to acceptMS20426AD4 rivet heads (refer to Figure a).

9. Install 880113-3 doubler, 310944-13 doubler assembly and 880018-603 vent on lower fuselage nose skin usingMS20426AD4 rivets (reBr to Figure 2).

C

page 2 of 11

SERYICE INFORMATION NO, 51-204

(-1 10. Ii rlprso Dwr unit is inltdlaiun nEsa dsi* in una uhers 31nls1-121 dmbl~r i´• to to in.tailpd, r.l~ile

s~e,ra power unit as shown in Figure 3.

NOTE

It is aceeptable to leave the original stereo power unit

attaching holes open in nose deck.

11. Remove existing rivets in area where 810181-126 doubler is to be installed (reEer to Figure 4).

12. Relocate 0.250-inch diameter hole in nose deck for routing landing light wire (refer to Figure 6).

13 Position 31[)181-125 doubler on nose deck, locate and make a cutout in left side of upper nose deck (refer to

Figure 41.

14. Drill and install MS2104?L3 nualate (2 plaees) on leR side of upper nose deck. Holes for nutplates are to matchholes in 310181-125 doubler (refer to Figure 5).

15 Locate, drill and install 310181-125 doubler on left aide of upper nose deck (refsr to Figure 51

16. Locate, drill and install M821o89LoBK nutplate (8 places) on aEt side of forward pressure bulkhead. Brush coat

seal around rivets and nutplates using sealant and sealing procedures outlined in Chapter 20 of the AirplaneMaintenance Manual (refer to Figure 6).

17. Reinstall out0ow valves as outlined in Chapter 21 of the Airplane Maintenance Manual.

18. Functional check outnow valves as outlined in Chapter 21 olthe Airplane Maintenance Manual.

19 Touch up paint on nose deck, as necessary, using zinc chromate primer.

to. Instail 880714-5 ahmud ball aaasmbly is pls~rsi end 881116 ahraud hall ssssmbly IZ jllBF~S) Un FDFWBFd

pressure bulkhead using M535206´•229 screw (12 places) and AN9jOD06 washer (12 places) (refer to Figure 7).

21. install 880116-3 shroud assembly on left side of upper nose deck using AN3-6A bolt (2 placesi and AN960D10washer (2 places) (reEer to Figure 7).

22. install NC22S´•13-29-4 duet and NC22S´•13´•52-4 duet on shroud assemblies using AN737TW107 clamps (reEer to

Figure 7).

23. Reinstall left landing light on fuseless nose as outlined in Chapter 33 of the Airplane Maintenance Manual.

24. Reinstall hex duet on ram air check valve and lower left secess door using existing hardware.

25. Reinstall left side and left lower access doers an fuselage nose section using existing hardware

26. Reinstall upper door aa~iembly on fuselage nose section using existing hardware.

27. Touchup paint on fuselage nose section as necessary.


C

Page 3 of 11


REMOVE THISDOOR ~gsy

-"9

LOWER LEFT

J

ACCESS DOOROPENIN(I IREFI

REMOVE THESEACCESSDOORS

AFTEDOEOFFUSELPIOE SKIN

~n C_

’a.so´•´•

CUTOUT IN SKIN TOMATCH CUTOUT IN b~ssmls´•s DOUBLER I ~J I

’’L´•,

TRUE DIMENSIONALONGCONTOUROF FUSELP~(IE SKIN

’7.75"

STA STALOWER EDGE OF 5.50

VIEW LOOKING UP SKIN

AT FUSELAGE NOSE

Fieurs 1.

PaCe 4 of 11


C a-~

--i-´•,

Osr,´•4.W S.BO

MSZOIZBPIM RIVET880713´•3 DOUBLER I3JPLs)(TRIM AS NECESSARY)

;I -t- c t´•1.26"

_

880010603 VENT

t- f(I 31(Wd4´•13DOUBLERAS8Y

rl CI_I+

I-; f \’Rt

;I+ c+III-’-

MF2042B~D4 RIVET118 PLSL

c~Y´•

ExlsnNo HOLEMSzol28aon nlvET

I1PLSI j.

NOII

THE 880713-1 DOUBLER IS

CVIIW LOOKINGDOWN LIFTZIOE INSTALLED ON THE INSIDE

AT LOWER FUSELAGE 5KINSURFACE OF THE SKIN

Filule 3

Page 5 of 11


r.

STA

~t6.50´•1 -1 830135´•11 STRIP

~lil s.la .y/ aJo~NOSE DECK

IRE FI

EXISTING STEREOWWER UNIT

(REFI

-I---

i’ InEFI

Lt~CTc~++

LEFT NOSE SEAM

ASSY FI\STENERSIREF)

B li~in

VIEW LOOKING DOWN

ON NOSE DECK

Fieura 3.

Page 6 of 11

SERVICE INFORMATION NO. 51´•204

sra´•12.0

EDGEOFCUTOUT ~1I7IREFI

t t+FUIELAOE

t h +5 t f ~kOES:IOECKEDGE OF I I A\)CCUTOUT +T~

o.85´•´•n

+iIREFI

:i EOGEOFCUTOUT

iIREFI

Jilt3.15~´•

f llJ C,

C’ 310101-121t ;i i IREFIOOUsLER

-VS5- X

310181´•126 DOUBLER

iEOOEDFCUTOUTIAEF1

C VIEW LOOKING DOWN

ON NOSE DECK

VIEW A-AFi(lur´• 1.

Page 7 of 11

SERVICE INFORMATION NO. 81-?04

-\eVIEW LOOKING DOWN

ON NOSE DECK

’~I,IF FLITE PHONE iS

O INSTALLED PICKUP EXISTINGHOLE AND DELETE EXISTINGSPACER AT THIS LOCATION

STI\ QFusELaaE

´•tz.a

NOSE DECKIREFI

MS20428A04RIVET i

f ~Ba a

a

´•Ilcl.m6.751´•

el L I I J.o.lse~o.zololn HOLE

f NOSE DECK

Q a PLSL

a

a

aTHIS HOLE IN

NOSE DECK 2.5(1" AFTnhlo aN sAmE suTr

LINE IRL1 AS EXISTING

MS204281\D4 RIVET 0.2~0´•´• DIA HOLE

FLUSH HEAD IN NOSEi. ILANDIN(I LIGHT WIRE

DECK ITHESE TWO tnOLEl

EXISTING RIVETS DO ZNOT PICKUP DOUBLERI

Icll~310181-125 DOUBLER

LEGEND: flNDIC~TE)EXISTINOHOLE IMU*IO~D4 RIVET)EXCEPT AS NOTED.

O IF THIS RIVET HOLE INTERFERES~L INDICATES ADDED WITH LANDING LIGHT WIRE HOLE.

MS?W281\04 RIVETS FLUSH PLUG HOLE IN DOUBLER

I\NO RELOCATE HOLE. MI\INTI\INja INDICATES ADDED EDGE DISTANCE OF 1 x Dll\.

MS20470~D1 RIYETS- OF RIVET PLUS O.DB’~.

Figure 5.

pago 8 of 11

SERVICE INFORMATION NO. SI-2U4

AtRcnnFT

I)IA. HOLE

MSZIOBBLOBK NUTPL*TEoN *FT SIDE OF BULKHEAD

(3 PLSI

6~"’ I.ss´•´•

c 1-I-UPPER OUTFLOWAAFETYYALVE HOLE LREFI

0

LOWER OUTFLOWISAFETYVI\LVE HOLE IREFI

C:, r/-3´•16 O

~.g´•´•Ij

r%

D1A. HOLEMSZIOBBLOBK NUTPLATE

ON AFT SIDE OF BULKHEAD

C VIEW L001(ING AFT AT LEFT

SIDE OF FWD PRESSVRE BULI(HEAD

Figure 6.

Page 9 of 11

SERVICE INFORMATION NO SI-204

SIOl(a38HROUDHALF ASFY

880114´•SSWROUDAN737M1107 CLAMP I HALF A9SY

PPLSI

FWDPRESSUAEBULKHEAD

IRBF1

NC228´•13-28´•4

DUCT

i ~C I~-’ 880714´•3 SHROUDHALFASSY

i ,,,,,,,,,,,,,,.s3szoa´•22escREwNC22S´•13-S211DUCT

r

I11PLSI

i880715-39HROUDASEY

I\N3´•S~ BOLTi\NBB0010WAIHER I I FUSELAOB NOSE

(2 PLB) I DECK IREFI

Fi(lYn 7.

Pnge 10 of II


j EL.CTRICIL LD~O: NO CH*NDE.

WEIGHT AND IPIL~NCE: The weight and balance ehanpe due to instailation olthia Se~vice information is as Follows:

WOICIHT (LR8) H´•ARM (INCHESI II-MOMENT+6.19 48.96 264.0

SP*RES AFFECTED: NO

PUBLICATION8 AFFECTED: The Illustrated Parts Catalog change required by this document will be incorporated atthe nert scheduled revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Ssrvice InformationNo. SI-204, dated July 1986, entitled "Overbaard Routing of Cabin Exhaust ae~ompliJhed (date)

i

Paec 11 or ii

Service InformationC

SERVICE INFORMATION NO. Sb106

8April 1985

EXHAUST STATIC PRESSURE nOSE ASSEMBLY REPLACEMENT


MODEL 8964 SERIAL NOS. 98001 THRU 96200.

MODEL BB~B SERUALNOS. 96063, 96069, 96075, 96018, WW)66, 96201 THRU 96999.

REASON FOR PUBLICATION: TO REDUCE THE POSSIBLE FAILURE OF TAE EXHAUST STATIC PRESSURE

HOSE ASSEMBLIES DUE TO HEAT HARDENWG.

COMPLIANCE: AT OWNER’S DISCRETION.

NOTE

[F ANY PROBLEMS ARE ENCOUNTERED

COMPLYING WITH THIS SERVICE INFORMATION,CONTA~T YOUR NEAREST GULFSTREAM

BY WnOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR EQUIVALENT.

APPROVAL: ENOINEERINO DESIGN ASPECTS ARE FAA APPROVED.

ESTIMATED MAN FIOURS: TWO (2) HOURS.


TMROUOH YOUR NEAREST OUI.FSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 8187.74.

REFERENCE THIS SERVICE INFORMATION, AIRCRMT MODEL AND FACTORY SERIAL NUJIBER WHEN

ORDERING SERVICE INFORMATION NO. S1a05 KIT CONSIST~O OP THE FOLLOWWO:


2 se. 830378´•653 Tube Aaay2 ea. AN818~41 Union

4 se. ANSBO-1OL Washer

4ea MS21WW Nut

(es. MSa1919H4 Ckmp4 ea. MSa1819812 Clamp4 ea. M911039CI´•o8 Scnwa ea. s-otnmoz´•oao Aasy1 ea. Card

1 ea. S´•rvies Informstioll No. SI-a(M InsPueti~os

(a

PaSe1 of 1

Clly..

SERVICE INFORMATION NO. SI-Z05

BEFORE CHANGE

F1REW~LL

HOSEaFsY (REFI

REMOVE EXISTIN(ISW21EOBQn EXHPIUSISTATICHOSE ASSY

EN(IINE TUBEASSY (REF)

TEMPERATURECONTROL (REF)

VIEW LOOKING AT LEFT SIDE

TYPICAL BOTH ENGINES

Figure 1. (2hes)l~( 2)

P~e 2 d 4

SERVICE INPORMAT~ON NO. 8b205

AFTER CHANGE

FlnEwaLL IREF,

S0421E02´•080HOSE ASPY

L~n) cLnw cs

~N9BO´•1OL WPSHER

M821042L3 NUT

nOSE489Y IREFL

P1N81841 UNION

80376883 TUBE ~SSY

ENOINBTUBE~ISY(RBFL

IEMPERI\NReCONTROL IRIFI

VIEW LOOKING AT LEFT SIDE

Ms2181sn4 CLaMP (21~ TYPICAL BOTH ENGINESM927~9C1´•08SCREW*NgBOIOLW1\8HeRMta1042WNUT

Fipur´• 1.(5h´•´•t2 or 2)

Pnge3~14

EIERVICEINPORMATION NO. 91-205


INSSRUCTIONS:

1. Remove upper and right side cowling from leR and right engines.

2. Remove and discard existing left and right e~hauat static pressure hose assemblies PIN 9-0421308-211 (rsPer to

Figure 1, Sheet I of z).

5. Install C04alE02-080 hose assembly, AN816U uniah and 650516883 tube assembly on left and right engines(refer to Figure 1, Sheet 2 of 2).

4. Secure the 9´•0821301´•080 hole assembly to the existing pitot hose assembly using MS2191PH12 clamp (2

places), M8210S8C1-08 screw, ANBGO-1OL washer and MSZ10112LS nut (refer to Figure 1, Sheet 2 of 2).

5. Secure the 650578-858 tube alsembly to existing engine tubs assembly using M821919B4 clamp (2 places),M921098C1-08 screw, ANOBQ1OL waahsr andM821042LS nut (refer to Figure 1, Sheet 2 of 2).

6. Functional cheek for leaks.

Reinstall upper and right side Eowling on left and right engines.



WEILIHT FIND BALANCE: NO CHANGE.

9PI\Re9 AFFECTBO: NO.

PUBLICATIONS AIPECTEED: The Illustrated Parte Catalog change rsquirsd by this document will be incorporated at


RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service information

No. 91205, dated 8 April 1958, entitled Exhaust-Static Pressure Hose Aesembiy Replacement", accomplished(dats)

Page 4 of 4

’r. r-

~SllService :Infovmation Culfslream Rerospaee Corpanrion

OLUnom CiN. OXlbhMu 73121

SERVICE INFORMATION NO. SI-10612 April 1985

NEGATIVE TORQUE SENSOR (NTS) SWITCH RELOCATION

MODELS AFFECTED: MODEL 880, SERIAL NOS. 11001 THRU 110?9.



MODEL 590C, SERIAL NOS, 11800 THRU 11999.




MODEL 6968, SERIAL NOB. 96063, 96059, 96015, 96018, 96088 AND 96201 THRU 95999.

REASON FOR PUBLICATION: TO RELOCATE NTS SWITCH TO A MORE SECURE AREA PREVENTINGPOSSIBLE SWITCH WIRE FAILURE.


NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST GULFSTREAMCOMMANDER AUTHORIZED SERVICENTER.

BY WHOM WORK WILL Be ~CCOMPLISHED: A B P MECHANIC OR EPUIVALENT.

APPROYAL: ENGINEERING DESIGN ASPECTS ARE RAA APPROVED.

ESTIMATED MAN HOURS: FOUR(B) HOURS.

PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCUREDTHROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICEESPE~R FOR: KIT NO. 1 1281.46OR KIT NO. 2 5358.49. REFERENCE THIS SERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIALNUMBER WHEN ORDERING INFORMATION NO. SbloB KIT CONSISTING OF THE FOLLOWING:

hla ~vllmmn

Kit Na. 1- Models 880, 6g0A:snd 690B,Kit No. 2 Models 590C, 890D, BgB.-BgbA end 69511.

Kit Kit

No. 1 N~.,2BTY QTY PART NO. DESCRIPaON2 ea. a os. 6305’16-851 Tube Assy2 ea. 2 os. 800040-415 Restrictor2 ea. 2 ea. ANB288*L Nut2 os. 2 os, AN785~-4 Tee

2 ea. 2 os. AN8t14 Plug8 ea. 8 ea. SOS10904T O´•RingZ ea. 2 os. 80811-804 Backup Ring2 so. 8104961E1 Hose Artsy

2 ea. 80421306244 Hose Asuy1 ea. 1 ea. Compliance Ca~d1 os. 1 os. Se~iea IDlonnation No. 51´•206 Instructions

Pi~e t oi 4

SEILVICE INFORMAT?ON NO. 91´•206

d LEFT ´•INSTALLATION 9HOWNRIGHT INSTALLATION TYPICAL

laslrloa soxEXlsTINoIRIP)

a

i

rvplcnLEN(IINB I\SPY

(ReFI

ehlalNE EXISTING

"*"’:k9~9 ’6C/

MODELS 890. 690AAND 6909

EXISTING BETAPRESSURISWITCH

IREF)eXlsTINo otLIUPPLYHOSE(dePi

ExmlNoloNlnoN BOX

IREFI

EN(IINE MI\NIPOLD(REF)

eXlsTINOANB2aBd NUT

fRNPFIBWOBZ´•445 RfSTRICTOR

EXISTING~N81Sd UNION

(ReFIExlsnNa sernPnEsnuRa swncHIRePI

exlSrINo olL EXlsnNoQUPPLY WOSE ~N84(d ELBOW

IREP) IRfiF)

MODELS 6900. BgOD. 695. 695AAND 8958BEFORE CHANGE

Pl(iure i.

PageDol(

SERVICE INFORMATION NO. SI-POB


RIGHT TYPICnL

bi

i ’R""

TYPICALENIIINB A8SY

L;

d.

aEN(IINE MANIFOLDIRE Fl

EXI8TIN(IBOX

IREFI

SaS1DB04TORINOISAFETY WIRE PLU(II

~311´•BM 840KUP RIN(I9(100404´•71 RESTRICT~R

ANBZ88´•4 NUTBOI10´•BMTO´•RING

83MB´•861TUBE A85Y

Om(DB04TO´•RIN(iEX1STINB NTS SWITCH

(SAFETY WIRE SWITCH)

EX18TIN(I BETAAN714 PRESSURE SWITCH

ISAFETY WIAE SWITCHI

810484RE~1 HOSE ASSY(MODELSBBO. BBO*, AND BBOB)

gW21EO~´•244 HOSE A89YIMODELS 8800. 8900. 889. 896* AND 8888)

ALL MODELS

AFTER CHANGE

iieurs 2.

Psga3o14

SERVICE INFORMATION NO. SI´•208


ACCOMPLISHMENT INSTRUCSIONS:

i. Remove lower cowling from left and right engines.

2. Disconnect electrical connectors ham NT9 switch and Beta Pressure switch (refer to Figure i).

S. Remove and discard existing oil supply hose assembly (refer to Figure i).

4. Remove existing NTS switch and Beta Pressure switch and retain both switches for reinstallation (refer to Figurei).

5. On Models 6B0C, 680D, 895, 696A and 685B, remove and discard existing elbow (P/N AN941-4), restrictor (PIN

900092416) and nut (P~ ANB289-4) fi´•om engine manifold (refer to Figure ii.

B. Remove and discard existing union (PIN AN811~4) from engine manifold (refer to Figure i).

7. Discard existing aringll and ring(sl.

8. install ANB144 plug and SoS10904T a´•ring in engine manifold port that NTS switch was originally installed

in. Safety wire plug (refer to Figure 2).

9. Install AN?83´•4 tee, S-031090PT o-ring, 90911904 backup ring and ANBls9-4 nut on engine manifold. Position

"branch" of tee facing forward along ignition box (refer to Figure 2).

10. Install existing NTS switch and S0310-904T oring in AN?83´•4 tee and safety wire switch (refer to Figure 2).

11. Install 800040-475 restrictor and S0910-804T oring on engine manifold (refer to Figure 2).

12. Install 830518-667 tube assembly on 800040-418 restrictor (refer to Figure 2).

13. Install existing Beta Pressure switch on 830378667 tube assembly and safety wire switch (refer to Figure 2).

14. Install 810494-RE1 hose assembly (Models 690, BgoA and 6808) or 5-0421105´•244 hose assembly (Models 890C,

690D, 885i 696A and 695B) and secure hose assemblies with existing dames and hardware (reEsr to Figure 2).

15. Reconnect existing electrical connectors to NT8 switch and Beta Pressure switch and safety wire connectors.

NOTE

Due 0 relocation of NTS switch, NTS switch connector may

not reach switch. Butt spliced extension of electrical wiringis acceptable.

16. Cheek installation far leaks by running anginas.

17. Function check both NTS and Beta systems,

18. Reinstall lower cowling on left and right engines.


ELICTRICAL LOAD: NO CHANCE.

WEIGHT AND B~WNCE: NO CHANGE.


PUBLICATIONS APPECTED: The Airplane Maintenance Manual and Illustrated Parts Catalog changes required bythis document will be incorporated at the next scheduled revision.

RecORD COMPLI*NCE: Make an appropriate entry in airplane maintenance records as follows; Service information

No. SI-208, dated 12 April 1986, entitled "Negative Torgue Sensor (NT9) Switch Reiocation", accomplishedidate)

ppgsdoi(

Service InformationGulfstreamC: Aerospace

SERVICE INFORMATION NO. 8I-211

30 June 1886

GARRm TURBINE ENGINE COMPANY SERVICE BULLETIN NO. TPETTSE331´•74-0003

MODELS AFFECTED: MODELS 680T, 680V AND 880W, SERIAL NOS. 1413 THRU 1850.

MODEL 681, SERIAL NOS. 8001 THRU 60?2.

MODELS 690, 690A AND BBOB, SERIAL NOS. 11(101 THRU 11868.

MODEL 69OC, SERIAL NOS. 11600 THRU 11?36.




MODEL 695B, SERIAL NOS. 88201 THRU 86208.

REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH DARRET~ TURBINE ENGINE COMPANY

(OTEC) SERVICE BULLETIN NO. TPEITSE831-740003.

COMPLIANCE: REFER TO CTEC SERVICE BULLETIN NO. TPEiT8E9S1-14-oo03.

BY WHOM WORK WILL BE ACCOMPLISHED: REFER TO GTEC SERVICE BULLETIN NO. TPE~8E331-?(-0003.

*PP.W*L: RaPBRTOGTBC SERYICE BULLETM NU.TPEnsEIll-?ld00S-

ESTIMATED MPIN HOURS: REFER TO GTEC SERVICE BULLETIN NO. TPEiT8E931-14-000S.

PARTS DATA: REFER TO GTEC SERVICE BULLETIN NO. TPE11~9E331-14-0003.

SPECIAL TOOLS: REFER TO (ITEC SERVICE BULLETIN NO. TPEi~SE331-14-000S.


1 Comply with Garrett Turbine Engine Company Service Bulletin No. TPEI~SE331-?il-0003.






RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Senriee InformationNo. SL-2I1. dated 30 June 1986, entitled "Garrett Turbine Engine Company Service Bulletin No. TPEPI~SE331-14-0003,"

accomplished (date)

i

Page 1 of 1

I~ SERVICE BULLETI#1,


REVISION TRANSMITTAL SHEET

This sheet transmits Revision 3 to Service Bulletin No. TPE/TSE331-74-0003titled ENGINE IGNITION Replace Ignition Unit.

This is a COMPLETE revf sion. This bulletin has been reprinted in its entirety.Please remove and discard all pages of prior issues and replace with pages ofthis revision.

Reason for Revision:

NOTE: Equipment modified in accordance with a previousissue of this service bulletin does not requirefurther rework.

This service bulletin is revised to add duty cycle information, toadd engine models and to update format.

Section 1

Paragraph A is revised to reflect latest engine applications.C

Paragraph B is revised to reflect latest duty cycle limits.

Paragraph C through L are revised to reflect latest fo~mat.

Paragraph J is revised to add engine models.

Section 2

Accompl i shment Instructions are revl sed to reflect latestformat.

Section 3

Material infolmatlon is revised to reflect latest prices andformat.

.ist

oate oate

1 ~lar 24/06 6 Mar 24/062 Mar 24/86 7 Mar 24/863 Mar 24/86 8 Blank4 Mar 24/86 9 Mar 24/865 Mar 24/86 10 Blank

C

Mar 24/86 TPE/TSE331-74-0003

Page 1 of 2Copyright 1986 by The Garrett Corporation

2´•

SERVICE BULLEBIWGARRETT TURBINE ENGINE COMPANY

Plsulour Revirlonr:

Revision 1 dated June 22/82Revision 2 dated Dec 2/82

Ma r 24/86 TPE/TSE331-74-0003

Page 2 of 2

I~ SERVICE BULLB~WWIGARRETT TURBINE ENGINE COMPANY

CENGINE IGNITION Replace Ignition Unit

NOTE_: This Service Bulletin is revised to add duty cycle information.

A. Ef fectl vl ty

This service bulletin is applicable to the following turboprop aircraftengines.

Prior to

Part No. Model No. Serial No. ~eplicatlon

R 865912-1A-61 TPE331-25AA Mitsublshl MU-LB-1A-7/-1A-8/-1A-9

R 865912-10-51 TPE331-25DA Falrchlld Porter PC-6/-10-6/-10-71 C-n2-10-8

R 865912-1F-51 TPE331-25FA Porter/Volpar-1F-6/-1F-71

-1F-8R 867940-1-41 TPE331-43A Turbo Commander 680T

R 867970-1-5/ TPE331-47A Turbo 18

-1-7 680V

-1-6/-1-7/-1-8

R 893290-1-1/ TPE331-25AB Mitsubishi MU-2B/-2D-1-2

R 893310-1-1/ TPE331-2508 Fairchlld Porter-1-2

R 893270-1-1/ TPE331-43BL Turbo Commander 680W i

-1-3/-1-4/ 581-1-5

R 893330-1-1/ TPE331-55B Jetllner 600 (Oove)-1-2

R 893130-1-1/ TPE331-1-100F *14003 Pilatus Porter

R 893400-1-1/ TPE331-1-1O18 *93073 Turbo 18/-2 Turbollner

R 894120-1-1/ TPE331-1-101E *95005 Jetliner-2 600 (Oove)

896760-1/-2/ TPE331-1-lOlF *98042 Peacemaker-3/-4

R 3101850-1 TPE331-1-101Z *34032 S2R TurboR Thrush/MarshR Turbo Ag Cat

893250-1-1/ TPE331-1-151A "93258 Mitsubishi-2 MU-20P/-2F/-2G

C R 869595-1-1/ TPE331-1-151G *91198 Merlin IIB-2

Apr 14/82 TPE/TSE331-74-0003Revision 3, Mar 24/86 Page 1 of 10Copyright 1986 by The Garrett Corporation

/~ISEWVICE BULLETBWGARRETT TURBINE ENGINE COMPANY

Prior toPart No. Model No. Seria~. Application

3101260-1/ iPE331-1-151K *26102 Century Turbo-2 Commander

R 869480-1-1/ TPE331-2-201A *90373 Skyvan

894820-1-1/ TPE331-2-201C *08024 CASA 212

R 894980-1/-2 TPE331-2UA-203D *97004 GooseR 894040-1/-2 TPE331-3U-303G *03451 Merlin III/

or or

895880-1/-2 TPE331-3UW-303G *05067 IVA/Metro/Metro II/Metro IIA

3101800-1 TPE331-3U-303V *32015 CenturyJetstream III

R 3102550-1! TPE331-3U-304G f03743 Merlin III/R -2/-3/-4

IVA/Metro/Metro II/Metro IIA

R 894870-1/-2! TSE331-3U-303N +07024 Helitec CorpR -3/-4 S55T

815950-1-1/ TPE331-5-251C *22370 CASA 212-100-2/-3

R 895720-1/ TPE331-5-251K *40101 Jetprop Commander-2/-3 690/590A/6908

3102200-1 TPE331-S-252D *39011 Dornler 228R 3102520-1 TPE331-5-252K *40461 Jetprop Canmander’

690A/69083101840-1 TPE331-5-252M *33092 Mitsublshi

MU-2N/-2PR 3102520-2/-3 TPE331-5-254K "40393 Jetprop Commander

iR 6900/6900R 895720-4 TPE331-5-255K "40101 Jetprop CommanderR 690/690A/690B

896150-1/ TPE331-6-251M *20602 Mltsubishi-3/-5 MU-2J/-2K/-2L/-2M

3101630-1 TPE331-6-2528 *27263 Beech 81003101300-2 TPE331-6-252M *30048 Mltsublshl

MU-2J/-2K/-2L/-2M3102450-1 TPE331-6A-251M *44250 Mitsublshi

MU-2J/-2K/-2L/-2M3101300-3 TPE331-6A-252M *30066 Mitsubishi

MU-2J/-2K/-2L/-2MR 3101470-1/-3 TPE331-8-401S *31705 Conquest iIR 3102510-1/-5 TPE331-8-402S *31604 Conquest iIR 3102510-2/-9 TPE331-8-403S *31604 Conquest IIR 3101470-2/-4 TPE331-8-404S *31705 Conquest II

3102170-1/-2 TPE331-10-501C *37160 CASA 212-200 i

Apr 14/82 TPE/iSE331-74-0003Revision 3, Mar 24/86 Page 2 4

Ib~ SERYICE BUUE~#GARRETT TURBINE ENGINE COMPANY

Prior to

Part No. Model No. Serial No. Application

R 3102190-1 TPE331-10-501K *38220 Jetprop CommanderR 695/695A/6958

3102180-1 TPE331-10-501M *36393 Mitsubishi

Marqui se/Solitaire

R 3102170-5 TPE331-10-511C *37160 CASA 212-200R 3102190-2 TPE331-10-511K *38220 Jetprop CommanderR 695/695W6958R 3102180-2 TPE331-1O-511M *36393 Mitsubishi MarquiselR SolltareR 3102050-1/ TPE331-10U-501G *35250 Merl in IIIB

R 3102050-3 TPE331-10U-502G *35250 Merl in IIIBR 3102050-4 TPE331-10U-511G *35250 Merlin IIIBR 3102050-5 TPE331-10U-512G *35250 Merl in IIIB

R 3102500-1 TPE331-10UF-501H *42007 Jetstream 313102600-2 TPE331-10UF-511H *35250 Jetztream 313102600-5 TPE331-10UF-512H *35250 Jetstream 31

3102600-6 TPE331-10UF-513H *35250 Jetstream 313102600-7 TPE331-10UR-513H *35250 Jetstream 313102920-1 TPE331-llUA-601W *47011 Pucara IA-66

*Praduction incorporation Point.

R **Improvements provided by this service bulletin are optional and haveR not been incorporated into production units.

8. Reason

(1) Problem: The present ignition unit duty cycle is limited in ac-

cordance with the aircraft flight manual based on vendor

recommendations.

(2) Background: Ilhen the aircraft flight manual limits are exceeded,the ignition unit is subject to failure.

(3) Action: A new ignition unit has been developed with an extended

du ty eye le.

R (a) Above +50F (~10C) ambient temperature, the ignition unit maybe operated up to one hour continous duty. The total time"on" shall not exceed one hour without one hour "off". The

R one hour "on" may be either continuous or intermittent.

R (b) Below ~50 (~iOC) ambient temperature, the ignition unit may beR as required without limitation provided service bul-R n TPE331-75-0004 has been complied with.

i.

Apr 14/82 TPE/TSE331-74-0003Revision 3, Mar 24/56 Page 3

I~j SEWIIIGEv


C. ption

This service bulletin provides instructions for installation of IgnitionUnit, Part No. 868962-3 which has a longer continuous duty cycle.

D. Compliance

Optional. Thi a service bul leti n may be accompl i shed at operator’soption.

E. Approval

The change to the engine type design authorized by this service bulletinR complies with applicable Federal Aviation Regulations and is FAA

approved.


No additional manhours are required to accomplish this change when aR maintenance action necessitates access to the affected part.


Information regarding availability of parts may be obtained from a Gar-R rett authorized Service Center or the aircraft manufacturer’s appointed

rervice fadllt)i. iiiefer to Service Infor~nation Letter (S.I.L.)P331-27for a complete listing of these facilities.)

Refer to Section 3 for information regarding price of parts required toaccomplish this bulletin.

H. Tool i ng Price and Availabili ty

R No special tooling is required except that already listed in publica-R tlons referenced in Paragraph J.

I. Weight and Balance

No change.


The sources of infonnation used in the preparation of this service bul-letin include Garrett engineering documentation and the following.


Ic~iSERVICE BULL~IWGARRETT TURBINE ENGINE COMPANY

Illustrated

Part/ Overhaul Maintenance Parts

Model No. Manual Manual Catal oq

TPE331-25AA NA *72-00-85 72-00-84

TPE331-250A NA *72-00-85 72-00-84

TPE331-25FA NA *72-00-85 72-00-84

TPE331-43A NA *72-00-85 72-00-84

TPE331-47A NA *72-00-85 72-00-84

TPE331-25AB NA *72-00-88 72-00-87

TPE331-250B NA "72-00-88 72-00-87

TPE331-438L NA *72-00-88 72-00-87

TPE331-558 NA *72-00-88 72-00-87

TPE331-1-10OF NA *72-00-92 72-00-91

TPE331-1-1018 NA *72-00-92 72-00-91

TPE331-1-101E NA *72-00-92 72-00-91

TPE331-1-1O1F NA "72-00-92 72-00-91

TPE331-1-101Z NA *72-00-92 72-00-91

TPE331-1-151A NA *72-00-92 72-00-91

TPE331-1-151G NA "72-00-92 72-00-91

TPE331-1-151K NA *72-00-92 72-00-91

TPE331-2-201A NA *72-00-92 72-00-91

TPE331-2-201C NA *72-00-92 72-00-91

TPE331-2UA-203D NA *72-00-92 72-00-91

TPE311-3U-3r)30 NR *12-00-98 12-00-91

TPE331-3UW-303G NA *72-00-98 72-0~-97

TPE331-3U-303V NA *72-00-98 72-00-97

TPE331-3U-304G NA *72-00-98 72-00-97

TSE331-3U-303N NA *72-00-98 72-00-97

TPE331-5-251C NA *72-00-95 72-00-94

TPE331-5-251K NA *72-00-95 72-00-94

TPE331-5-252D NA *72-00-95 72-00-94

TPE331-5-252K NA f72-00-95 72-00-94

TPE331-5-252M NA *72-00-95 72-00-94

TPE331-5-254K NA *72-00-95 72-00-94

R TPE331-5-255K NA *72-00-95 72-00-94

TPE331-6-251M NA *72-00-95 72-00-94

TPE331-6-2528 NA *72-00-95 72-00-94

TPE331-6-252M NA *72-00-95 72-00-94

TPE331-SA-251M NA *72-00-95 72-00-94

TPE331-6A-252M NA *72-00-95 72-00-94

R TPE331-8-401S NA *72-00-13 72-00-11

R TPE331-8-4025 NA *72-00-13 72-00-11

R TPE331-8-403S NA *72-00-13 72-00-11

R TPE331-R-404S NA *72-00-13 72-00-11

R TPE331-10-501C NA *72-00-28 72-01-17

R TPE331-10-501K NA *72-00-29 72-01-18

R iPE331-10-501M NA *72-00-27 72-01-16

R TPE331-10-511C NA *72-00-28 72-01-17

R TPE331-10-511K NA *72-00-27 72-01-18

j R TPE331-10-511M NA *72-00-27 72-01-16


SEIVICE BULLETI#GARRETT TURBINE ENGINE COMPANY

IllustratedPart/ Overhaul Maintenance PartsModel No. Manual Manual Catalpg

R TPE331-1OU-501G NA *72-00-23 72-01-15R TPE331-1OU-5O2G NA *72-00-23 72-01-15R TPE331-10U-511G NA *72-00-23 72-01-15R TPE331-10U-512G NA *72-00-23 72-01-15

TPE331-10UF-501H NA *72-00-42 72-00-41R TPE331-1OUF-511H NA *72-00-42 72-00-41R TPE331-1OUF-512H NA *72-00-42 72-00-41R TPE331-1OUF-513H NA *72-00-42 72-00-41R TPE331-10UR-513H NA *72-00-42 72-00-41

TPE331-llUA-601W NA *72-00-25 72-00-24

*Affected Chapte r/Secti on/Subject 74-10-01.

K. Service Bulletin References

R The following shall be accomplished prior to or concurrent with thisR service bulletin. The accomplishment instructions outlined in each ser-R vice bulletin stand alone; therefore compliance with this service bul-R letln doer not indicate compliance with any other service bulletin.

Service 8ulletln No. Service Bulletin Title

R TPE/TSE75-0004 ENGINE AIR SYSTEM COMPONENTSR Rework Anti-Ice Shield Assembly

L. Other Publications Affected

Same as those listed under "Publlcations References".

Apr 14/82TPE/iSE331-74-0003

Revision 3, Mar 24/a6Page 6

SERVICE BULLETINGARRETT TURBINE ENGINE COMPANY

2. inrtructlonr

R NOTE_: Publ i cations ii sted in Section 1 provide applicable di sassembly,R cleaning, inspection, reassembly, and testing instructions and shallR be referred to during the accomplishment of the followingR instructions.

R A. Replace Ignitron Unit as Follows

R (1) Gain access to and remove Ignition Unit, Part No. 868962-2 in ac-

cordance with Engine Maintenance Manual.

(2) Install replacement Ignition Unit, Part No. 868962-3 in accordancewith Engine Maintenance Manual.

R (3) Reassemble engine in accordance with Engine Maintenance Manual.

R (4) Check and ensure proper engine operation in accordance with Air-R craft Flight Manual and/or appropriate aircraft documents.

R (5) Make entry in engine log book noting engine operating time landserial number of installed canponent if applicable) and compliancewith this service bulletin land service bulletin revision number if

applicable).

R (6) Reidentiiicatlon of equiprrnt net reguired.

R (7) Complete Compl i ance Certificate fo rm and ma ii. Contact local Gar-R rett authorized service center to obtain forms, if required.

i

Apr 14/82 TPE/TSE331-74-0003Revision 3, Mar 24/86 Page 7/8

I~ SER\IIICIE Blllhl~TI#GARRETT TURBINE ENGINE COMPANY

3. Mater~al infarmatlan

R The fol lowing parts are requi red to accomplish the 1 nstructf ons outl i ned i n

R this service bulletin.

R NOTE: Applicable illustrated parts catalogs and spare parts bul-R letlns dated later than the original issue date of thisR service bulletin may introduce different parts farR installation. Refer to these documents before orderingR parts.

R Expendable parts discarded in gaining access to the af-R fected area of the equipment are not included.

R The following parts are required to accomplish the instructions outlined inR this service bul letin. The Unf t Net Price applies to Canmerci al Ai rllnesR only.

Unit

List Instructlons-New PN Ouantity Pri ce Key Word Old PN Disposition

R 868962-3 1 82,6 28.00 Ignition 868962-2 F

Unit

R Di EPOZltion Code F. Dispose of old part according to company practices; replaceR with like part.

Disposition Code K. Old and new parts are interchangeable.

*Thfs price is F.O.B. Garrett Phoenlx, Arrzona and will remain fl~m throughR September 17, 1986.

Refer to Section 1, Paragraph G for information regarding availability of parts.

Apr 14/82 TPE/TSE331-74-0003Revision 3, Mar 24/86 Page 9/10

II

Service snformatisn GulfstreamAerospace


30 June 1986

GARRETT TURBINE ENGINE COMPANY SERVICE BULLETIN NO. TPETTSEBJ1-75-0004

MODELS AFFECTED: MODELS 690, 690A AND 690B, 8ERIAL NOS. 11001 THRU 11566.

MODEL 690C, SERIAL NOS. 11600 THRU 11?35.





REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH GARKF.TT TURBINE ENGINE COMPANY

(rrTECI SERVICE BULLETIN NO TPEiTSES31-75-4004,

COMPLI~NCE: REFER TO GTEC SERVICE BULLETIN NO. TPEPI~SE331-75´•0004.

BY WHOM WORK WILL BE ACCOMPLISHEO: REFER TO GTEC SERVICE BULLETIN NO. TPEITSE331-76-0004.

APPROVAL: REFER TO GTEC SERVICE BULLETIN NO. TPEiTSES31-76-0004.

ESTIMATED MAN HOURS: REFER TO GTEC SERVICE BUI.I.ETIN NO. TPEiTSE331-75-0004.

PARTS DATA: REFER TO GTEC SERVICE BULLETIN NO. TPERSE381-75-0004.

SPECIAL TOOLS: REFER TO GTEC SERVICE BULLETIN NO. TPEiTSE331-75-0004


I Comply with Garrett Turbine Engine Company Service Bulletin Na. TPERSE~1-76´•00011.

a. Fill out and mail Compliance Card.




PUsLICPITIONS AFFECTED: NONE.

RECORD COMPLIANCE: Mabe an appropriate entry in airplane maintenance records as follows: Service Information

No. SI´•P12. dated 30 June 1986, entilled’~Garrett Turbine Engine Company Service Bulletin No. TPEiTSES31-15-0004,’’

nci:limi,lishod tdate)

C

Page i of 1

SERYICE BULLETINGARRETT TURBINE ENGINE COMPANY

CREVISION TRANSMITTAL SHEET

This sheet transmits Revlsf on 1 to Service Bulletin No. TPE/TSE331-75-0004,

This is a COMPLETE revision. This bulletin has been reprinted in its entirety.Please remove and discard all pages of prior issues and replace with pages ofthis revision.

Reason for Revision:

NOTE: Equipment modl ff ed in accordance with a previous issue of thisservice bulletin doer not require further rework.

This service bulletin is revised to provide additional optional rework procedureto allow the use of rivets to plug holes and to add engine models.

Section 1

Title is revised to delete part numbers.

C Paragraphs R and J are reviled to add Engine Models IPE331-1-100Fj-10LIF-512H/-lo~F-513H/-lauR-513H.

Paragraph 0 is revised to add Part No. 895298-5.

Paragraph K is revised to add service bulletin compliance requirement.

Section 2

Accomplishment instructions are revised to add optional rework procedure.

Step 2.A. Is revised to delete reference to Part No. 868780-1 and addPart Nd. 896298-5.

Step 2.A.(3) provides for location of rework area.

Step 1.A.(4) provides optional rework procedure using rivets.

Step 2.A.(5) provides rework procedure by welding.

Step 2.A.(6) provides for inspection of rework.

Step 2.A.(7) provides far reldentlflcation of Part No. 868780-2 to868780-3.

Section 3

C Material information (r revised to add unit prldng infarmatl.n.

Jan 14/85 TPE/TSE331-75-0004Page 1 of 2 2Copyright 1985 by The Garrett Corporation

´•SEWCE BULLIE’BINGARRETT INE ENGINE COMPANY

List of Effective Pages:

Page No. Date Page No. Date

1 Jan 14/85 7 Jan 14/852 Jan 14/85 8 Jan 14/853 Jan 14/85 9 Jan 14/854 Jan 14/85 10 Jan 14/855 Jan 14/85 11 Jan 19/856 Jan 14/85 12 Blank

Previous Revisions:

None

Jan 14/85 TPE/TSE331-75-0004 14o,,, ,f

j~ SEP\IIGE BULUETIIGARRETT TURBINE ENGINE COMPANY

R ENGINE AIR SYSTEM COMPONENTS Rework Anti-Ice Shield Assembly

1. Planni nq Informa ti on

A. Effectivi ty

This service bulletin is applicable to the following turboprop aircraft

engines.

Prior to

Part No. Model Na. Serial Na. Application

R 893130-1-1/-2 TPE331-1-100F **Not Avail Pilatus Porter

893400-1-1/ TPE331-1-1O1B **Not Avail Turbo 18/Turbollner

894120-1-1/ TPE331-1-101E **Not Avail Jetliner 600 (Dave)

896760-1 TPE331-1-1O1F **Not Avail Peacemaker

thru -4

3101850-1 TPE331-1-101Z **Not Avail S2R Turbo Thrush/Turbo Ag Cat

893250-1-1/ TPE331-1-151A **Nat Avail Mitsublshl

-2 MU-2DP/2F/2G

869:85-1-1/ iPE931-1-1510 **N~t Avail Meil(n LIE

3101260-1/ TPE331-1-151K **Not Avail Century Turbo

Commander

869480-1-1/ TPE331-2-201A **Not Avail SLyvan-2

894820-1-1/ TPE331-2-201C **Not Avail CASA 212

-2

894980-1/-2 TPE331-2UA-203D **Not Avail Goose

894040-1/-2 TPE331-3U-303G **Not Avail

or or IV/IVA/Metro/895880-1/-2 TpE331-3UW-303C **Nat Avail Metro II/

Metro IIA

3101800-1 TPE331-3U-303V **Not Avail CenturyJetstream III

3102550-1/-2 TPE331-3U-3040 **Not Ava ii

IV/IYA/Metro/Metro 1I1Metro IIA

894870-1 TSE331-3U-303N **Not Avail Helltec Corp S55T

thru -4

896950-1-1/ TPE331-5-251C **Nat Avail CASA 212-100

-2/-3895720-1/ TPE331-5-251K **Not Avail Jetprop Commander

-2/-3 690/690A/69083102200-1 TPE331-5-2520 **Not Avail Oornier 228

i 3Ln2520-L rPE331-5-252K ’´•NOt Avail

Feb 28/84 TPE/TSE331-75-0004Revision 1, Jan 14/85 Page 1 of 12

Copyright 1985 by The Garrett Corporation

I~ SEIVICE BUUEBBMGARRETT TURBINE ENGINE COMPANY

Prior to

Part No. Model No. Serial No. Application

3101840-1 TPE331-5-252M **Not Avail Mitsubishi

MU-2N/2P3102520-2/-3 TPE331-5-254K **Not Avail Jetprop Commander

6900/6900895720-4 TPE331-5-255K **Not Avail Jetprop Commander

690/690A/6908896160-1/ TPE331-6-251M **Nat Avail Mltsublshl

-3/-5 MU-2J/2K/2L/2M3101630-1 TPE331-6-252B **Not Avail Beech 8100

3101300-2 TPE331-6-252M **Not Avail Mltsubishl

MU-2J/2K/2L/2M3102450-1 TPE331-6A-251M **Not Avail Mitsubfshi

MU-2J/2K/2L/2M3101300-3 TPE331-6A-252M **Not Avail Mltsubishi

MU-2J/2K/2L/2M3101470-1 TPE331-8-4015 **Not Avail Conquest II

3102510-1 TPE331-8-402S **Not Avail Conquest II

3102510-2 TPE331-8-403S *"Not Avail Conquest II

3101470-2 TPE331-8-404S **Not Avail Conquest II

3102170-1/-2 TPE331-10-501C **Not Avail CASA 212-200

3102190-1 TPE331-10-501K "*Not Avail Jetprop Commander

69515’15A/695B3102180-1 TPE331-10-501M *"Not Avail Mitsubishi

Marquise/Solitaire

3102170-5 iPE331-10-511C **Not Avail CASA 212-200

3102190-2 TPE331-10-511K **Not Avail Jetprop Commander

695/695A/69583102180-2 TPE331-10-511M **Not Avail Mitsuhlshi

MarqulselSolitaire

3102170-3 TPE331-10R-501C **Not Avail CASA 212-200

3102170-4 TPE331-10R-502C **No t Ava 1 1 CASA 212- 200



3103090-1 TPE331-10U-501E **Not Avail No Current

Application3102050-1/-2 TPE331-10U-501G **Nat Avail Merlin IIIB

3102050-3 TPE331-10U-502G **Not Avail Merlin IIIB

3102940-1 TPE331-10U-503G **Not Avail Merlin IIIC

3102050-4 iPE331-10U-511G **Not Avail Merlin IIIB

3102050-5 TPE331-10U-512G **Not Avail Merlin IIIB

3102940-2 iPE331-10U-513G **Not Avail Ilerlin IIIC

3103230-2 TPE331-10UA-501G **Not Avail Metro II

3103230-1 TPE331-10UA-511G **Not Avail Metro II

3102600-1 TPE331-10UF-501H **Not Avail Jetstream 31

3102600-2 TPE331-10UF-511H **Not Avail Jetstream 31

R 3102600-5 TPE331-10UF-512H **Not Avail Jetstream 31 jR 3102600-6 iPE331-10UF-513H **Not Avail Jetztream 31R 3102600-7 TPE331-10VR-513H **Not Avail Jntstream 31

Feb 28/84 TPE/TSE331-75-0004Revision 1, Jan 14/85 Page 2

~j SEWYICE BUILLETIRGARRETT TURBINE ENGINE COMPANY

Prior toPart No. Model No. Serial No. Application

3102540-1 TPE331-l1U-601G **Nat Avail Metro III/Merlin IVC

3102540-2 TPE331-llU-602G **Not Avail Metro III/Merlin IVC

3102540-3 TPE331-l1U-611G **Not Avail Metro III/Merlin IYC

3102540-4 TPE331-llU-612G **Not Avail Metro III/Merlin IVC

3102920-1 TPE331-llUA-601W **Not Avail Pucara IA-663102920-2 TPE331-llUA-611W **Not Avail Pucara IA-66

**Improvements provided by this service bulletin have been approved fornew production and existing units. Serial number effectivity will beprovided when determined by production schedules.

B. Reason

(1) Problem: Engines have experienced overheating of the ignition unitduring engine anti-ice system operation.

12) Rction: Reworl the anti-l~e shield to ell.lnate anti-ice rynte.air from impinging on ignition unit during anti-ice systemopel’ation.

C. Description

This service bulletin provides necessary procedures far the rework ofR Anti-ice Shield Assembly, Part No. 868780-1/-2 or 896298-1 through -5.

D. Compliance

Recommended. Garrett recommends that this service bulletin be accom-

plished at the operator’s convenience but not later than the next accessof affected parts.

E. Approval

The change to engine components authorl2ed by this service has beenfound to comply with applicable Federal Aviation Regulations and is FAAapproved.


An estimated two manhours are required for this change when accomplishedat the maintenance level.

C

Feb 28/84 TPE/TSE331-75-0004Revision 1, Jan 14/85 Pin.

(O

SERIIIGE BULLETINGARRETT TURBINE ENGINE COMPANY


Information regarding availability of parts may be obtained from a

Garrett authorired Service Center or the aircraft manufacturer’s ap-pointed service facilf ty. Refer to Service informatf on Letter (S.I.L.)P331-27 for a complete listing of these facilities.)

Refer to Section 3 for information regarding price of parts required to

accomplish this bulletin.

H. Tooling Price and Ava ilabfl i ty

No special tooling required except that already listed in referenced

manual(s).

I. Weight and Balance

No change.


The sources of information used in the preparation of this service bul-

letin include Garrett engineering documentation and the followingpubllcatlon(s).

Illustrated

Part/ Overhaul Maintenance PartsModel No. Manual Manual Catalos

R TPE331-1-100F NA *72-00-92 72-00-91TPE331-1-101B NA *72-00-92 72-00-91TPE331-1-101E NA *72-00-92 72-00-91

TPE331-1-101F NA *72-00-92 72-00-91TPE331-1-101Z NA *72-00-92 72-00-91

TPE331-1-151A NA *72-00-92 72-00-91

TPE331-1-151G NA *72-00-92 72-00-91IPE331-1-151K NA *72-00-92 72-00-91

TPE331-2-201A NA *72-00-92 72-00-91

TPE331-2-201C NA *72-00-92 72-00-91TPE331-2UA-2030 NA *72-00-92 72-00-91TPE331-3U-303G NA *72-00-98 72-00-97

TPE331-3UW-303G NA *72-00-98 72-00-97

TPE331-3U-303V NA *72-00-98 72-00-97

TPE331-3U-304G NA *72-00-98 72-00-97TSE331-3U-303N NA *72-00-98 72-00-97TPE331-5-251C NA *72-00-95 72-00-94

TPE331-5-251K NA *72-00-95 72-00-94TPE331-5-252D NA *72-00-95 72-00-94TPE331-5-252K NA *72-00-95 72-00-94

TPE331-5-252M NA *72-00-95 72-00-94

iPE331-5-254K NA *72-00-95 72-00-94TPE331-5-255K NA *72-00-95 72-00-94

TPE331-6-251M NA *72-00-95 72-00-94TPE331-6-252B NA *72-00-95 72-00-94

Feb 28/84 TPE/TSE331-75-0004Revision i, Jan 14/85 Page 4

I~ SELIIICE BULLETINGRRRETT NRBIIE FNOINf COPIPANI

IllustratedPart/ Overhaul Maintenance PartsModel No. Manual Manual Catalqg

TPE331-6-252M NA *72-00-95 72-00-94TPE331-6A-251M NA *72-00-95 72-00-94TPE331-6A-252M NA *72-00-95 72-00-94TPE331-8-401S NA *72-00-13 72-00-11TPE331-8-4025 NA "72-00-13 72-00-11TPE331-8-403S NA *72-00-13 72-00-11TPE331-8-404S NA *72-00-13 72-00-11TPE331-10-501C NA *72-00-23 72-00-21TPE331-10-501K NA *72-00-23 72-00-21TPE331-1D-501M NA *72-00-23 72-00-21TPE331-1O-511C NA *72-00-28 72-00-21TPE331-10-511K NA *72-00-29 72-00-21TPE331-10-511M NA *72-00-27 72-00-21TPE331-10R-501C NA f72-00-23 72-00-21TPE331-10R-502C NA *72-00-23 72-00-21TPE331-10R-511C NA *72-00-28 72-00-21TPE331-10R-512C NA *72-00-28 72-00-21TPE331-10U-501E NA *72-00-42 72-00-41TPE331-10U-501G NA *72-00-23 72-00-21TPE331-10U-50ZG NA "12-00-23 72-00-21TPE331-10U-503G NA *72-00-23 72-00-21TPE331-10U-511G NA *72-00-23 72-00-21TPE331-10U-512G NA *72-00-23 72-00-21TPE331-10U-513G NA *72-00-30 72-00-21TPE331-10UA-501G NA *72-00-45 72-00-44TPE331-10UA-511G NA *72-00-45 72-00-44TPE331-10UF-501H NA *72-00-42 72-00-41TPE331-~OUF-511H NA *72-00-42 72-00-41

R TPE331-10UF-512H NA *72-00-42 72-00-41R TPE331-iOVF-513H NA *72-00-42 72-00-41R TPE331-10UR-513H NA *72-00-42 72-00-41

TPE331-llU-601G NA *72-00-25 72-00-24TPE331-llU-602G NA *72-00-25 72-00-24TPE331-llU-611G NA *72-00-25 72-00-24TPE331-ilU-612G NA *72-00-25 72-00-24TPE331-llUA-601W NA *72-00-25 72-00-24TPE331-liUA-611W NA *72-00-25 72-00-24

*Affected Chapter/Sectian/Subject 75-10-02.

Feb 20/84 TPE/TSE331-75-0004Revision i, Jan 14/85 Page 5

SERVIClOi BULLETINGARRETT TURBINE ENGINE COMPANY

CK. Service Bulleti n References

R (Anti-Ice Shield Assembly, Part No. 868780-1) The following serviceR bulletin shall be accomplished prior to or concurrent with thisR bulletin. The accomplishment instructions outlined in each bulletinR stand alone, therefore compliance with this bulletin does not indicateR compliance with any other bulletin.

Service Bulletin No. Service Bulletin Title

72-0323 ENGINE ANTI-ICE SHIELO ASSEMBLY

Replace/Rework Anti-Ice Shield As-

sembly

R The following service bul letf n(s) should be revf ewed by the operator forR possible incorporation at this time.

R Service Bulletin No. Service Bulletin Title

R 75-0005 AIR ENGINE ANTI-ICING Rework or

R Replace Antl-Ici Shield Assembly,R Part No. 896298-2tlth -6, Part No.R 896298-3 with -7, and Part No.R 896298-4 with -8

L. Other PublicaTlanr Rfiectpd

Same as those listed under "Publlcatlons References".

Feb 28/84 TPE/TSE331-75-0004RevlElon i. Jan 1(/85 Page 6 j?

14~ SERVICE BULLE’BINGARRETT TURBINE ENGINE COMPANY

2. Accomp1 i shment Instru cti ons

NOTE: Manuals listed in Section 1 provide applicable disassemhly,cleaning, inspection, reassembly, and testing instructions

and shall be referred to during the accomplishment of the

following instructions.

Table 1. Materials and Compounds

Material or Compound Manufacturer

NOTE: Equivalent substitutes may be used for listed items.

Enamel, light green epoxy Grlggs Paint, Subsidiary of Domcom Cist,(Type L, Class A) 3602 S 16th Place. Phoenix, AZ 85040

(With Catalyst C1178)

Filler rod (4043) Cabot Corp, Stellite 01v, 1020 West Park

Ave, P.O. Box 746, Kokomo, IN 46901

C Powder (Irldlte no. 11-2) Rlehardron Chen~ieai Co. Rllied KeliteProducts Dlv, 400 Mldland Ave, HighlandPark, MI 48203

Primer, glass green epoxy Grlggs Paint, Subsidiary of Domcom Cist,

(Type I, Class A) 3602 S 16th Place, Phoenix, AZ 85040

(Wlth Catalyst C1178)

l,l,l-Trichlaraethane Commercially available

(M1L-T-81533)

R A. Rework Anti-Ice Shield Assembly, Part Na. 868780-2 or 896298-1 ThroughR -5

(1) Clsassemble engine as required to gain access to anti-ice shield

assembly in accordance with Engine Maintenance Manual.

(2) Remove anti-ice shield assembly in accordance with Engine Mainten-

ance Manual.

R (3) Locate and identify three 1/8 inch diJlneter holes to be reworked.R (See figure 1.)

Feb 28/84 TPE/TSE331-75-0004Revision 1. Jan 14/85 Pace 7 iD

I~ SER\IIGE BULLETINGARRETT TURBINE ENGINE COMPANY

e, o

THRsl 1/B INCII DlhMBIRHOLEIIO 81 WI1OID OP

RIVnlD

vlw

R

o O

Omnlr 1/8 INCH

DIIIMITIR HOLII

TO III WI1DID OR

O o,lv,,,

vim B18-5625

View A PN 868700-2View B PN 896298-1 thru -5

Rework Anti-Ice Shield AssemblyFeb 28/83 Figure 1 TPE/TSE331-75-0004Revision 1, Jan 14/85 Page 8

BULL~BINGARRETT TURBINE ENGINE COMPANY

R NOTE: Anti-ice shf eld assembly may be reworked by in-

R stalling rivets in holes, or by welding holer

R closed.

R (4) Rework anti-ice shield assembly using rivets as follows.

R cpurIo_N_: ENSURE THREE 1/8 INCH DIAMETER HOLES TO BE

R REWORKED ARE LOCATED BETWEEN ~TWO PARGE HOLES AS

R SHOWN IN FIGURE 1.

R (a) Install Blind Rivets, Part No. 627-510-9420 or Solid Rivets,

R Part No. MSZ0470A4-4 in holes shown in Figure i, with formed

R heads of rivets on outboard surface of anti-ice shield

R assembly.

R (b) Upset rivets in accordance with standard shop practices.

R (5) Rework anti-ice shield assembly by welding as follows.

(a) Remove gaskets from anti-ice shield assembly in accordance

with Engine Maintenance Manual to prevent damage duringrework.

C (b) weld ~rea ia clean and remove pdlnt prior ta

CAUTION: ENSURE THREE 1/8 INCH DIAMETER HOLES

WELDED ARE LOCATED BETWEEN TWO LARGE HOLES

AS INDICATED IN FIGURE 1.

(c) Puddle weld to fill three 1/8 inch diameter holes in accord-

ance with AMS4190 using aluminum filler rod (4043).

(d) Hand finish to blend weld areas smoothly to adjacent surfaces

both inside and outside of anti-ice shield assembly.

(e) Prepare chromate conversion coating solution as follows,

NOTE: Prepare chromate conversion coating solution

in small batches. Use only freshly preparedsolutions.

1 Dissolve one ounce of powder (Irldlte 14-2) In each quartof distilled or de-ironized water.

2 Maintain solution at 21 to 27C (70 to 80F).

(f) Coat bare areas with chromate conversion coating solution.

Allow area to remain wet for one minute.

(g) Rinse parts with water at 27 to 430 (80 to llOF). Blow off

excess water with low pressure air (20 pslg maximum), then dryin oven at a temperature not to exceed i1C (160F).

Feb 28/84 TPE/TSE331-75-00041 In,aE p~,. q

SIERVICE BUU~TINGARRETT TURBINE ENGINE COMPANY

L-(h) perform fluorescent penetrant inspection in a~cordance with

MIL-I-6866.

(1) Thoroughly clean area for paint touch-up using 1,1,1-Trfchloroethane (MIL-T-81533).

(j) If anti-ice shield has been previously painted. touch-up paintusing gloss green epoxy primer and light green epov.y enamel in

accordance with Engine Maintenance Manual.

(k) Relnstall gaskets on anti-fee shield assembly in accordance

with Engine Maintenance Manual.

R (6) Inspect rework.

R (7) Reidentlfy Anti-Ice Shield, Part No. 868780-2 to Part No, 868780-3

R by removing -2 (868780-2) and entering a -3 (868780-3) using an ink

R stamp or stencil.

(8) Install reworked anti-ice shield assembly in accordance with EngineMaintenance Manual.

(9) Reassemble engine in accordance with Engine Maintenance Manual.

(10) Upon completion of engine reassembly, check and ensure proper en-

gine operation in accordance with Aircraft Flight Manual.

(11) Upon co~npletion of this rework, make entry in engine log book not-

ing engine operating time tend serial number of installed componentIf applicable) and compliance with this service bulletin land ser-

vice bulletin revision number if applicable).

(12) Reidentlflc~tion of equipment not required.

(13) Complete Compliance Certificate form and mail. Contact local Gar-

rett authoriled service center to obtain forms, if required.

Feb 28/84 ~PE/TSE331-75-0004Revision i, Jan 14/85 Page 10

13

F~jlSERVICE BULLELlPIj


R 3. Material !nPo~atlon

R NOTE: Applicable illustrated parts catalogs and spare parts bul-

R letlns dated later than the original issue date of this

R service bulletin may introduce different parts for

R installation. Refer to these documents before orderingR parts.

R Expendable parts discarded in gaining access to the af-

R fected area of the equipment are not included.

R The following parts are required to accomplish the instructions outlined in

R this service bulletin.

R Unit

R List Instructlons-

R New PN Quantity Prlce* Key Word Old PN Olspositfon

R NOTE: Rivets are not required if reworl is accomplished by welding.

R MS20470A4-4 3 ~0.08 Rivet

R or

R 627-510-9420 3 2.10 Rivet

CR *Thls price is F.O.B. Garrett Phoen(x, Arizona and will remain fins throughR May 14, 1985.

R Refer to Section 1, Paragraph G for information regarding availability of parts.

Feb 28/84 TPE/TSE331-75-W04Revision i, Jan 14/85 Page 11/12 \’i-

Sevvice Informaftie4n GulfstreamAerospace


30 June 1986

EMERGENCY AIRWORTHINESS DIRECTIVE NO. 86-12-02

(OTEC Service Bulletin No. TPE331-72-0630)

MODELS AFFECTED: MODELS 680T, 680V AND 680W, SERIAL NOS. 1413 THRU 18501

MODEL 681, SERIAL NOS. 60(11 THRU 6072.

MODELS 690, 690A AND 6908, SERIAL NOS. 11001THRU 11566.




MODEL BB5A, SERIAL NOS. 96000 THRU 96100


REASON FOR PUBLIC~ITION: TO RECOMMEND COMPLIANCE WITH EMERGENCY AIRWORTHINESS

DIRECTIVE NO. 86´•12-02.

COMPLIANCE: REFER TO EMERGENCY AIRWORTHINESS DIRECTIVE NO. 86´•12-02.

BY WHOM WORK WILL BE I\CCOMPLISHEO: A a p MECHANIC OK EQUIVALENT AND AN APPROVED TPE331

O1L AND FILTER ANALYSIS FACILITY.

REFER TO GTEC SERVICE INFORMATION LETTER P331-97,

REVISION 5 DATED MAY 23, 1986, FOR APPROVED TPE931 OIL

AND FILTER ANALYSIS FACILITIES.

APPROVAL: REFER TO OTEC SERVICE BULLETIN NO. TPES31-72-0630

ESTIMATED MAN HOURS: REFER TO OTEC SERVICE BULLETIN NO. TPES31-72-0530

PARTS DATA: REFER TO GTEC SERVICE BULLETIN NO. TPE331-72-0630

SPECI~LTOOLS: REFER TO GTEC SERVICE BULLETIN NO. TPE331 -12-0630


1. Comply with Emergency Airworthiness Directive No. 86-12-02

NOTE

Darrett Turbine Engine Company Service Bulletin Nos. TPE331-72-

0533 and TPE331´•72-0534, referenced in Service Dulletin No. TPE331-

72-0530, may be obtsined from Garrett Turbine Engine Company. P O.

29003, Phoonix, Arizona 85038.





C PUBLIC/ITIONS*FFECTED: NONE

RECORD COMPLIANCE: Make an approprinte entry in oi~lsne maintenance records as follows: Servior Information

No. 5I-214, dated 30 June 1986, entiiled’~Emergeney Airworthiness Directive No 86´•12-02," aceompliahed(dnte)

Page 1 of]

Q EMERGENCY AIRWORTBINESS DIRECTIVE

uSDeoortmenl

dTnm~atatm :VdlT~: ~PIRDI 1(ITION11 A(LO~ OITICT

~sd´•rm ~iv*mon MUIMIIL CIT( MiUrrml 1111~

Mm(n(~fmtMn

"is en´•cqency priority letter airworthiness directive86-12-02 applicable to operators of Garrett Turbine Engine

c;npany :~ode?s TPE33: :5RA. -:5AB, -25DR, -25D6, -25FA, -43A,-47A, -558, -1, -2, -:UA, -3U, -iUW, -5, -6, -6R, -8,

-:UC, -1OR, -10U, -?OVA, -10UF, -1OUG, -:OUGR, -10UR,-11UR, -ii, and TSE331-3U turboprop and turSoshaft

engines is effective immediately upon receipt of this priority:etter. This priority letter AD is required to preventpossible failure of the beryllium-copper nut on the turbine endof the tiebolt shouldered shaft and resultant major damage tothe engine. This priority letter AD requires accomplishing aspectrometric analysis of oil samples collected in accordancewith a schedule as provided herein after receipt of thisletter.

Pursuant to the authority of the Federal Aviation Act of 1958,delegated to me by the Administrator, the following priorityletter AD is issued.

86-12-02 GARRETT TVRBINE ENGINE COMPANY: Letter issued June6, 1986. Applies to Garrett Turbine Engine Company ModelsTPE331-25 AA, -25 AB, -25DA, -25 DB, -25 FA, -43A, -4 3BL, -47A,-558, -1, -2, -ZUA, -3U, -3UW, -5; -6, -6A, -8; --IU; -IDG;

OR, -iOJ. -10UA, -1OUF, -10UG, -10UGR, -1OUR, -11U, -11UA,-12, and TSE331-3U turboprop and turboshaft engines.Compliance required as indicated unless alreadyaccomplished.To prevent the failure of the beryllium-copper nut on the

turbine end of the tiebolt shouldered shaft and resultant majordamage to the engine, accomplish the following:(a) Engines with less than 100 engine operating hours

since new or since installation of a turbine oil scavenge pumpassembly for any reason are to have an initial oil sample takenand processed in accordance with the instr uc t ions provided inparagraph i of Garrett Service Bulletin No. TPE331-7 2-0530,dated May 9, 1986, (SB 0530) or FAA approved equivalent. ThisIs to he accomplished at not less than 20 hours or more than 25hours since new or after the installation of that pumpassembli´•, or within 5 engine operatinci hours after receipt ofI~is priority letter AD, whiche ve; occurs later unless;ragraph (e) below has been accomplished. Additional oil.~illnlcs are to he taken and processed at not note than 25

hour intervals therea:ter until a total or 1ODoperating hourS has been accumulated since new or sinceins~allztion of that pump assembly or until paragraph (e) belownas been accomplished.

ibi Enginei with :UO or moie, ilut less iban 500 eng;neoperating hours since new or since installation of a turbinesil scav-nge pump assemblY for any reason on the date of

DIRECTIVE

RECEIVED gy bhT$

ri I b? L R I fl R

V Y ~u s l\al-4k As

RECEIVED svbh7P1 86-12-02

receipt of this priority letter AD, are to have an oil sampletaken and processed in accordance with the instructions

provided in paragraph i of SE 0530 within the next 50 engine

sps:ating hours after receipt of this priority letter AD. This

i-joastion is not required if paragraph (e) below has been

?i;bmplis~ed.IIOTE: Garrett recomnends chat oil samples continue to be

tJken at Leaulac intervals after accomplishment of this

prioritl: letter RD in accordance with the Spectrometric Oil

Ana;vsij Trogran (SOAl) described in Garrett Service

Information Setter No. P3)1-97. While the FAA encourages these

programs, thev are not mandatory per this priority letter AD.

ic) if oil sample analysis indicates beryllium content of

oil is in excess of O.; (two-tenths) parts per million,

accomplish paragraph (e) before further flight.(d) if oil sample analysis indicates beryllium content of

oil is in excess of 0.1 tone tenth) parts per million, but

equal to or less than 0 i (two-tenths) parts per million,:thin the next five engine operatingaccomplish paragraph (e) wi

hours.

(e) Engines which exceed the limits for beryllium content

in the~engine oil are to have the torsion shaft inspected, the

turbine oil scavenge pump r ewo r k ed or r epl ac ed the

beryllium-copper nut replaced, the turbine oil scavenge pump Cdrive spur gear shaft assembly inspected, and the engine oil

and filter changed in accordance with paragraph Z of SE 0530 or

FXx approved equivalent approved by the Manager, Western

Aircraft Certification Office. The inspection of the torsion

shaft does not apply to the following engine models which have

"strain-gage" torque sensors:

TPE331-10G TPE-331-10UG TPE331-1OUGR

TPE331-lLU TPE331-llUA TPE331-12

Aircraft may he ferried in accordance with the provisionsoi Federal Aviation Regulations (FARs) 21.197 and 21.199 to a

base where the AD can be accomplished. Upon request, an

ecuivalent means of compliance with the requirements of this hD

Ray be approved by the Manager, Western Aircraft Certification

ofiice, P.O. Box 92007, Worldway Postal Center, Los Angeles,California 90009-2007. Upon submission of substantiating data

Sy an owner or operator, through an FRA ~aintenance :nspector,

~ne !I.anager, Western Aircaet Certification Office may adjust

tne compliance time speciried in this Ao.

priority latter RD i; effective innediately upon

r´•ceipt.

?Ua-gER COLSACT:

Mr 3ili MorinS, Propuljion Sec.ion, j9?007, :as Xnoeles. Ciii:-´•:niaC-rtification Oe:i;e. ?.O. 90n

9C603-:007, telep~oni (:1?1 ;9T-l?a:.

BULLETI#GARRETT TURBINE ENGINE COMPANY

FNGIIII I.eanp)lih i*-rial Berllliu. S~ecironrlR c Oil b´•lairFrog ran (SOAP) In s pect 1 on

I. Planni no I nformat i on

A. Effectivity

NOTE: This service bulletin is no longer applicable to the followingturboprop aircraft engines when Service Bulletins, TPE331-72-0533

and TPE331-72-0534 have been complied with.

Service Bulletin TPE331-72-0534 is NOT applicable to enginesIdentified with an asterisk

This service bulletin is applicable to the following turboprop aircraft

engines.

PRIOR TO

PART NO. MOOEL NO. SERIAL NO. APPLICATION

865912-1A-6/-1A-71- 1A-8/ TPE331-25AA Al 1 Mi tsubl r hi M]-2B

-1A-9

893290-1-1/-2 TPE331125A8 Al 1 Mi tsubl s hi MU-ZB/-2Ds65912-lo-5/-lo-6/-10-7/ TPE331-250A All Falrchild Porter PC-6/

-1D-s C-H2

893310-1-1/-2 TPE331-250B All Fairchlld Porter

865912-1F-5/-1F-6/- 1F-7/ TPE331-25FA All Porter/Vol par-1F-8

867940-1-4/-1-7 TPE331-43A All Turbo Commander 680T/680\r

89327 O- 1-1/-1- 3/- 1-4/ TPE331-438L All Turbo Commander 680W/-1-5 681

867970-1-5/-1-6/-1-7/ TPE331-47A All Turbo 18

-1-8

893330-1-1/-2 TPE331-558 All Jetllner 600 (Dove)893130-1-1/-2 TPE331-1-100F All Pllatus Porter

893400-1-1/-2 TPE331-1-101B All Turbo 18/Turboliner894120-1-1/-2 TPE331-1-101E All Jetliner 600 (Dove)896760-1/-2/-3/-4 TPE331-1-1O1F All Peacemaker3101850-1 TPE331-1-101Z All S2R Turbo Thrush/

Turbo Ag Cat

893250-1-1/-2 TPE331-1-151A All Mltsublshi MU-Z0P/-2 F/-26

869595-1-1/-2 TPE331-1-151G All Merlin 1IB

3101260-1/-2 TP E3 31-1- 151K Al i. Century Tu rbo

Ccmmander869480- 1- 1/-2 TPE331-2-201A All Skyvan89482 O- 1-11- 2 TPE331-2-201C Al 1 CASA 212

894980-1/-2 TPE331-2UA-2030 All Goose

894040-1/-2 TPE331-3U-303G AllIVA/Metro/Metro II/

ORle; IMAL. ns

Metro III

May 9/86 RECFI\’Fr 1\´• BTP TPE331-72-0j30

Page 1 of 1?

Copyii~ht 1986 by TPC Gdrrett Corporation

le~ SERIIICE BULLE’BBHGARRETT IURBINE ENGINE COMPANY

PRIOR TO

PART NO. MODECO. _SSBIAL_NP. APPLICATION

3101800-1 TPE331-3U-303V All Century Jetstream III

3102250-1/-2/-3/-4 TPE331-3U-304G All

IVA/MetrO/Metro IIMetro IIA

895880-1/-2 TPE331-3UW-303G All

IVA/Metro/Metro II

Metro IIA

894870-1/-2/-3/-4 TSE331-3U-)03N All Helitec Corp 555T

896950-1-1/-2/-3 TPE331-5-251C All CASA 212-10089572 0-1/-2/-3 TPE331-5-251K Al 1 Jetprop Commander 690/

690A/690B3102200-1 TPE331-5-252D WP-39244 Oornler 228

3103330-1 TPE331-5A-252D #P-640O3 Darnler 228

3102520-1 TPE331-5-252K All Jetprap CaniMnder

690A/69083101840-1 TPE331-5-252M All Mitsubishi MU-2N/-2P3102520-2/-3 TPE331-5-254K All Jetprop Commander

6900/6900895720-4 TPE331-5-255K All Jetprop Commander 690/

690A/690B896160-1/-3/-5 TPE331-6-251M All Mitsubirhl MU-ZJ/-2h/

-2L/-2M3101630-1 TPE331-&2528 All Beech 8100

3103300-1 TPE331-6-252L All Merlin IIB3101300-2 TPE331-S-252M All Mi tsubi shi MU-2J/-2 K/

-2L/-2M3103340-1 TPE331-6-252T All Skyvan3101630-2 TPE331-6-253B All 8eech 8100

3102450-1 TPE331-6A-251M All Mltrubishl MU-2J/-ZK/-2L/-2M

3101300-3 TPE331-6A-252M All Mitsubishi MU-2J/-2K/-2L/-2M

3101470-1/-3 TPE331-8-401S All Conquest II



3101470-2/-4 TPE33I-8-404S All Conquest II3102510-4 TPE331-8-406S All Conquest II

3102170-1/-2 TPE331-1O-501C Al 1 CASA 212-2 003102190-1 TPE331-10-501K All Jetprop Ccmr~nder 695/

695A/69583102180-1 TPE331-10-501M Al 1 Mi tsubi shl Ma rqul se/

Solitaire3102170-5 TPE331-10-511C All CASA 212-200

3102190-2 TPE331-la-511K Al 1 Jetprop Comma nder 695/695A/6958

3102180-2 TPE331-1O-511M All Mi tsubi shi Ma rqu i s e/Solitaire

’3103440-1 TPE331-10G-5115 All Na Current Application3102170-3 TPE331-10R-501C All CASA 212-200 j3102170-4 TPE331-10R-502C All CASA 212-2003102170-6 TPE331-10R-511C All CASA 212-200

TPE331-72-0530

May 9/86 Page 29

I~14 SERYICE BULLETINGARRETT TURBINE ENGINE COMPANY

C

PRIOR TO

PART NO. MODEL NO. SERIAL NO. APPLICATION

3102 17 0- 7 TPE 331- 1 OR- 5 12 C #P-37513 CASA 2 12-2 00

3102170-8 TPE331-10R-513C All CASA 212-200

3102050-1/-2 TPE331-10U-501G All Merlin 1118

3102050-3 TPE331-10U-5026 All Merlin IIIB

3102940-1 TPE331-10U-503G All Merlin IIIC

3102050-4 TPE331-10U-511G All Merlin IIIB

3102050-5 TPE331-10U-512G All Merlin IIIB

3102940-2 TPE331-1OU-513G All Merlin IIIC

3103230-2 TPE331-10UA-501G All


)103230-1 TPE331-10UR-511G All


3102600-1 TPE331-1OUF-501H All Jetstream 31

3102600-2 TPE331-10UF-511H All Jetstream 31

3102600-5 TPE331-10UF-512H All Jetstream 31

3102500-6 TPE331-10UF-513H bP-42150 JetZtream 31

*3103310-1 TPE331-10UG-513H #P-63123 Jetstream 31

TPE331-IOUGR-513H R11 Jetrtrea. 31

3102600-7 TPE331-10UR-513H All Jetstream 31

*3102540-1 TPE331-1lU-601G All Metro III/Merlin IVC

*3102540-2 TPE33r-11U-602C All Metro III/Merlin IVC

*3102540-3 TPE331-llU-611G 6~-44486 Metro III/Merlin IYC

’3102540-4 TPE331-llU-612G #P-44470 Metro III/Merlin IVC

"3102540-6 TPE331-llU-612G #P-44474 Metro III/Merlin IVC

*3102920-1 TPE331-11UA-601W All Pucara IA-66

’3102920-2 TPE331-11UA-611W Al 1 Puca ra 1A-66

’3103400-1 TPE331-128-701A #P-65003 No Current Appl i catf on

t8roduction Incorporation Point

8. Reason

(1) Problem: Under certain adverse conditions cavitation of oil in the

turbine hearing support assembly can cause erosion pittlng of the

Beryllium Copper nut on the turbine end of the shouldered shaft.

Excessive plttfng may cause failure of the 8eryllium Copper nut and

can result in major damage to the engine.

(2) BacLground: Tm, recent Beryllium Copper nut failures were at-

tributed to erasion pitting. Both failures occurred at less than

100 operating hours since overhaul and/or hat section inspection.

(3) Action: Erosion pitting of the Beryllium Capper nut can be detected

C by accomplishing a zpectron~tric analysis of oil sampler collectedIn accordance with the Engine Maintenance Manual at an acceleratedschedule as detailed in this service bulletin.

TPE331-72-053n

~nv 0/~5 P~o" 3[p

SERYICE BULLIETIHGRRRETT TVRBINE ENGINE COMPANY

C.. Descrr pti on

This service bulletin provides an inspection schedule for accomplishingan accelerated spectroo~tric oil analysis program.

D. Compliance

NOTE: Canpllance with this service bulletin is no longer required when

Service Bulletin, TPE331-72-0533 and TPE331-72-0534 have been

compiled with.

Service Bulletin TPE331-72-0534 is NOT applicable to enginesidentified with an asterisk in Paragraph A.

Recommended. Garrett recommends that this service bulletin be acccm-

pllshed in accordance with the following schedule.

(1) Less than 20 engine operating hours time since new, overhaul, or

any maintenance to turbine bearing support area, initial sampleshall be taken at 25 engine operating hours; and at 25 engine oper-

ating hour intervals thereafter until 100 engine operating hours

a re accumu la ted. Resume normal SOAP schedule after 100 engineoperating hours.

(2) n.re than 20 engine operatrng hour. and le~r than 100 engine oper- Cating hours time since new, overhaul, or any maintenance to turbinL

beanng support area; initial sample shall be taken within five en-

gine operating hours of receipt of this service bulletin; and at 25

engine operating hour intervals thereafter until 100 engine operat-

ing hours are accumulated. Resume normal SOAP schedule after 100

engine operating hours.

(3) More than 100 engine operating hours and less than 500 engine oper-

ating hours time since new, overhaul, or any rraintenance to turbine

bearing support area; a sample shall be taken within 50 engineoperating hours of receipt of this service bulletin.

E. Approval

FAA a pproved.


An estimated 15 minutes are required to obtain and package each oil

sample.

6. Material Price and Availability

Information regarding price and availability of parts may be obtained

from the Garrett General Aviation Services Company, Oistribution Center,

2340 East University, Phoenix, AZ 85038.

TPE331-72-0530

~ay 9/86 paoe 7

SERVICE BULLEVIHGARRETT TURBINE ENGINE COMPANY

H. Tooling Price and Availability

No special tooling is required except that already listed in publica-tionr referenced in Paragraph J.

i. Weight and Balance

No change.


The sources of information used in the preparation of this service bul-

letin include Garrett engineering docunentation and the folloving.

Engine Engine Illustrated

Partl Overhaul Maintenance Parts

Model No. Manual Manual Catalaq

TPE331-25AA NA 72-00-85 72-00-84

TPE331-25AB NA 72-00-88 72-00-87

TPE331-250A NA 72-0~85 72-00-84

TPE331-25D8 NA 72-00-88 72-00-87

TPE131-25FA NI\ 72-00-85 72-00-84

CTPE331-43A NA 72-00-85 72-00-84

TPE331-43BL NA 72-00-88 72-00-87

TPE331-47A NA 72-00-85 72-00-84

TPE331-55B NA 72-00-88 72-00-87

TPE331-1-100F NA 72-00-92 72-00-91

TPi331-1-101B NA 72-00-92 72-00-91

TPE331-1-101E NA 72-00-92 72-00-91

TPE331-1-10~F NA 72-00-92 72-00-91

TPE331-1-101Z NA 72-00-92 72-00-91

TPE331- 1-151A NA 72-00-92 72-0~sl

TPE331-1-151G NA 72-00-92 72-00-91

TPE331-1-?51K NA 72-01~92 72-00-91

TPE331-2-201F, HA 72-00-92 72-00-91

TPE331-2-201C NA 72-00´•92 72-0~91

TPE331-2UA-2030 NA 72-00-92 72-00-91

TPE331-3V-303G NA 72-00-98 72-00-97

TPE331-3U-303Y NA 72-00-98 72-00-97

TPE3)1-3U-304G NA 72-00-98 72-00-97

TPE331-3UW-303G NA 72-00-98 72-00-97

TSE331-3U-303N NA 72-00-90 72-00-17

TPE331-5-251C NA 72-00-95 72-00-94

iPE331-5-251K NA 72-00-95 72-00-94

TPE331-5-2520 NA 72-00-95 72-00-94

TPE331-5A-2520 NA NA NPI

TPE33!-5-252K NA 72-00-95 72-00-94

TPE331-5-252M NR 72-0~95 72-00-91

TPE331-5-254K HA 72-00-95 72-0rr9i

TPE331-5-25SK NA 72-00-95 72-0~94

TPE331-6-251H NA 72-00-95 72-00-94

TPE331-6-252[1 NR 12-0~45 12-ii0-95

TPED3i-S-2j2L NA 72-01-95 72-C1-9’

11":331-72-053’

9!P~ i

’i

I~ SERVICE BULIETIRGARRETT TUABINE ENGINE COMPANY

Engine Engine lilurtrated IPart/ Overhaul Maintenance PartsModel Na. nanual Manvai ~TTPE331-6-25ZM NR 72-00-95

TPE331-6-252T NA 72-01-95 72-01-94TPE331-6-253B NA 72-00-95 72-00-94TPE331-6A-251M NA 72-00-95 72-00-94TPE331-6A-252M NA 72-00-95 72-00-94~PE331-8´•4015 NA 72-00-13 72-00-11iPE331-8-4025 NR 72-00-13 72-00-11TPE331-8-4035 NA 72-00-13 72-00-11TPE331-8-404S NA 72-00-13 72-00-11TPE331-8-406S NA 72-00-13 72-00-11iPE331-1O-501C NA 72-00-28 72-01-17TPE331-10-501K NA 72-00-29 72-01-18TPE331-10-501M NA 72-00-27 72-01-15TPE331-10-511C NA 72-00-28 72-01-17TPE331-1O-511K NA 72-00-29 72-01-18TPE331-10-511M NA 72-00-27 72-01-15TPE331-10G-511S NR 72-00-48 72-00-47TPE331-10R-501C NA 72-00-28 72-01-17iPE331-1OR-502C NA 72-00-28 72-01-17TPE331-10R-511t NA 72-00-28 72-01-17TPE331-10R-512C NA 72-00-28 72-01-17TPE331-10R-513C NA 72-00-28 72-01-17TPE331-10U-501G NA 72-00-23 72-01-15iPE331-10U-502G NA 72-00-23 72-01-15TPE331-10U-5036 NA 72-00-30 72-01-19TPE331-10U-511G NA 72-00-23 72-01-15TPE331-1OU-512G NA 72-00-23 72-01-15TPE331-1OU-513G NA 72-00-30 72-01-19TPE331-1OUA-5016 NA 72-00-45 72-00-44TPE331-10UA-511C NA 72-00-45 72-00-41

TPE331-10UF-501H NA 72-00-42 72-00-41iPE331-10UF-511H NA 72-00-42 72-00-41TPE331-10UF-512H NA 72-00´•42 72-00´•41TPE331-10UF-513H NA 72-00-42 72-00-41TPE331-10UG-513H NA 72-00-42 72-00-41TPE331-~OUGR-513H NA 72-00-42 72-00-41

rPE331-10UR-513H NA 72-00´•42 72-00-41TPE331-llU-601G NA 72-00-25 72-00-24T PE 331-1 1U- 6 026 NR 72-00-25 72-00-24TPE331-llU-611G NA 72-00-25 72-00-24TPE331-1lU-612G NA 72-00-25 72-00-24TPE331-llUA-601W NA 72-06-25 72-00-24

TPE331-llUA-611W NA 72-00-25 72-00-24

TPE331-128-701A NR NA NA

iPE331-72-0j30

I~lay 9/86 Pnge 6

9

i~ SERVICE BULLEBIWGRRRETT TURBINE ENGINE COMPANY

K. Service Bulletin References

Review of the following should be accomplished by the operator for poss-ible incorporation at the tirn~ this service bulletin is accomplished.

Service BulletinNQ. Service Bulletin Title

72-0533 ENGINE TURBINE SECTION Replaceor Rework 011 Scavenge Pump Assembly

72-0534 ENGINE REDUCTION GEAR AND SHAFTSECTION Inspect Torsion Shaft

L. Other Publications Affected

Same as those listed under "Publications References".

C

May 9/86 TPE331-72-0530

Pa?e 718

Ir,

I~ SEIUICE BULLETIRIGARRETT TURBINE ENGINE COMPRNY

CA. Obtain’Oil Sample for Analysis

N91E: Do C(O_I submit engine oil filter with oil samples for this service

bulletin.

(1) Obtain an oil sample for SORP analysis in accordance with EngineMaintenance Manual using container provided in Kit, Part No.

831022-1.

(2) Fill out data sheet provi ded wi th Ki t, Pa rt No. 831022- i.

(3) Package the oil sample to prevent leakage in accordance with EngineMaintenance Manual.

(4) Forward oil sample and data sheet to Garrett Turbine Engine Com-

pany, P.O. Box 5217, Phoenix, AZ 85010 (Attn: S.O.R.P. Program, SB#

72-0530) for analysis, or any Garrett authorl~ed laboratory capableof detecting Berylllum in the oil.

(5) If the result of the S.O.A.P. analysis is 0.1 to 0.2 PPM Beryllium,accanpllsh the following within five engine operating hours of

receipt of analysis results. If the result of the S.O.A.P.

analysis is more than 0.2 PPM Beryllium, accanpllsh the followingprior to the next flight.

(a) Contact Customer Support Department of Ga rrett General Avia-

ti on Servi ces Conpa ny. (Telephone 602-225-25903

(b) Inspect torsion shaft in accordance with Service Bulletin,TPE331-72-0534.

(c) Rework or replace scavenge pump in accordance with Service

Bullerin, 72-0533.

(d) Inspect spur gearshaft assembly (scavenge pump drive) as

fol lows.

1 Visually inspect for evidence of damage to spllnes or gearteeth. Damage is not acceptable.

2 Visually inspect for evidence of wear on the scavenge pump

end of the gearshaft. Wear is not acceptable.

2 Measure gearshaft for corrett length.

May 9/86 TPE331-72-0530

Page 9

SERVI@IE BULLEBH#GARRETT TURBINE ENGINE COMPANY

Shpit Length

TPE331-25AA 4.21 to 4.24 inch (Used with 865046-2

scavenge pump only)TPE331-25DA 4.21 to 4.24 inch (Used with 865046-2

scavenge pump only)iPE331-25FA 4.21 to 4.24 in ch (Used wi th 865046-2

scavenge pump only)TPE331-43A 4.21 to 4.24 inch (Used with 865046-2

scavenge pump only)TPE331-25AA 4.11 to 4.14 inch

TPE331-25AB 4.11 to 4.14 inch

TPE331-250A 4.11 to 4.14 inch

TPE331-25DB 4.11 to 4.14 inch

TPE331-25FR 4.11 to 4.14 inch

TPE331-43A 4.11 to 4.14 inch

TPE331-43BL 4.11 to 4.14 inch

TPE331-47A 4.11 to 4.14 inch

TPE331-55B 4.11 to 4.14 inch

TPE331-1 4.11 to 4.14 inch

TPE331-Z 4.11 to 4.14 inch

TPE331-3 4.11 to 4.14 inch

TPE331-5 4.11 to 4.14 inch

TPE331-5A 4.78 to 4.82 inch

TPE331-6 4.11 to 4.14 inch

TPE331-8 ´•1.11 to 4.11 inch

(Ured vith hydraulicTPE331-10 (Pre 72-0466) 4.71 to 4.74 inch

torque sensor)TPE331-~OUA (Pre 72-0466) 4.71 to 4.74 inch (Used with hydraulic

torque sensor)TPE331-10 (Post 72-0466) 4.67 to 4.70 inch (Used with hydraulic

torque sensor)TPE331-10UA (Post 72-0466) 4.67 to 4.70 inch (Used with hydraulic

torque sensor)TPE331-10UG (Pre 72-0466) 4.78 to 4.82 inch (Used with torque ring)TPE331-1OUGR (Pre 72-0466) 4.78 to 4.82 inch (Used with torque ring)TPE331-ll (Pre 72-0466) 4.78 to 4.82 inch (Used with torque ring)TPE331-ilU (Pre 72-04661 4.78 to 4´•82 inch Ured u(th toryue ringiTPE331-10UG IPort 12-04~61 4.111 to 4.18 inch Ured w~th torque ring

TPE331-10GR Post 72-0466 4.74 to 4.78 inch Used with torque ring)TPE331-11 (Pos t 72-0466) 4.74 to 4.78 inch (Used with torque ring)TPE331-llU (Port 12-0466) 4.111 to 4.18 inch (Ured with torque ringiTPE331-12B-701A 4.74 to 4.78 inch (Used with torque ring

4 If spur gears’lft assembly fails.any of the precedingsteps, replace in accordance with Engine Maintenance

Manual.

Mav 9/86 TPE331-72-0530

Page 10

SEWVICE BULkEllstBGARRETT TURBINE ENGINE COMPANY

I "p’acE Beryllium Cap.er nut in ac~ardance vifh EngineMaintenance Manual.

(e) Change engine oil and filter in accordance with Engine Main-

tenance Manual.

(6) After each special oil sample cycle is canpleted, enter compliancewith this service bulletin in engine log book noting engine opera-

tion time and compliance with this service bulletin.

(7) Refdentiffcatlon of equipment is not required.

(8) Complete Compliance Certificate form and mail. Contact local Gar-

rett authorized service center to obtain forms, if required.

C

May 9/86 :PE3?1-72-05jn

Page i!

18

~ilSE"VleE BULLETIRGARRE~T TURBINE ENGINE COMPANY

C3. Ma teri a 1 informatl on

Unit

List Instru~tions-New PN Ouantity price" Key Uord Old PN Oisposition

831022-1 AR 112.00 Kit

’Refer to Sectron 1, Paragraph G for information regarding price and availabil-ity of parts.

May 9/86 TPE331-72-0530

Page 12 ILt

~illService InformationGulfstreamAerospace


21 February 1987

DOWTY ROTOL SERVICE LETTER NO. E.123 REV. 2

MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11?35.




MODEL 69SB. SERIAL NOS. 96062, 96063, 96069, 96015, 96018, 96085 AND 96201 THRU

96208.

REASON FOR PUBLICATION TO RECOMMEND COMPLIANCE WITH DOWTY ROTOL SERVICE LEWER NO.

E.12S REV. 2.

COMPLIANCE: REFER TO DOWTY ROTOL SERVICE LEITER NO. E.123 REV. 2.

BY WHOM WORl( WILL BE ACCOMPLISHED: A P MECHANIC OR EqUIVALENT.


PARTS DATA: NONE.


ACCOMPLISHMEM INSTRUCTIONS:

1 Comply with Dowty Rotol Service Letter No. E. 113 REV. 2.

2. Fill out and moil Compliance Card.




PUBLIC~TIONS AFFECTED: The Airplane Maintenance Manual chenge required by this document will be

incorporated st the next seheduied revision.

RECORD COMPLIANCE: Make an appropriate entry in airplans maintenance records as Follows: Service Informntion

No. 51´•219, dated 27 February 1981, entitled "Dowty Ratol Service Letter No. E. 125 REV. 2,~ accomplished(date)

Pale I ot 1

LIMIISD

K()~fOI.

SERVICE 1ETTER

SERVICE LETTER NO: E.123 REV.L.

DATED: 14TH JANUARY,1987.

ATTENTION: CHIEF INSPECTOR.

SUBJECT: G.A.PROPELLEROE-ICING SLIP RINGS.

PROPELLER TYPES: R.306 OULFSTREAM COMMANDERR.321) FAIRCHILD METROR1324) 6 MERLIN.R.333 BAE JETSTREAM 31R.334 CASA 212

R.339) PIPER CHEYENNER.341)R.352 FOKKER F5OR.354 SAAB SF.340.

Because of the problems brought about by lubricant contamin-ation of slip ring feces, this Service Letter is issued toadvise Operators of the necessity to clean Frequently thisitem, as fallowa:-

i.

For aircraft in regular ’Normal’ service, at wee~lyintervals, clean slip rings by rubbing vigorously with aclean lint-free cloth moistened with Arklone. M.E.K. orToluene. If slip rings are very dirty or pitted, polishlightly with a fine grade silicone carbide paper or glasspaper.

/cont’d...

2.

IBQW~ILIMITID

SE RV ICE 1E TT ERPACE 2 No. E.1~3 REV.E.

2.

After cleaning slip rings as necessary, proceed as follows:

A. Using a clean linen cloth apply ’Cramolin CleaningFluid’ to the slip ringe. Where necessary, rub for

approximately 1 minute to allow the oxides to become

saturated.

B. Leave surface for a further 30 seconds to complete

the saturation process.

NOTE: After applying ’Cramolin Cleaning Fluid’

the surface may turn green. This is normal

and is not the result of corrosion but

indicates that oxides are being dissolved.

C. Wipe the slip ring surface with a clean linen cloth

until it is clean and shiny,

D. Using a clean linen cloth, apply a thin film of

’Cramolin Special’ to the slip rings.

E. ’Cramalin Cleaning Fluid’ and ’Cramolin Special’ may

be obtained from:-

CAIG LABORATORIES INC.,

P.O.BOX J,1175-0 INDUSTRIAL AVENUE,

ESCONDIDO,CALIFORNIA 92025.

Telephone No. 619-745-4341.

Thi s Letter should read i n conjunl´•ti on w i th Arcrn rl

Maintenance Manual .1026, tl-1(-30, pages 304-n04/1

issued by: SERVICE MANAGER,DOWTY ROTOL LIMITED,

CHELTENHAM ROAD,GLOUCESTER GLE 99H.

r Ser~iceGulfstreamAerospace

’SERVICE INFO~IATION NO. 81-220S1 March 1881

INFORMATION CONCERNING ECU FAILURE

MODELSPIPFECTEL): MODEL 880C, 8ERIAL NOS. 11800 THRU 11’195.MODEL 880D, SERVLL NO9. 15001 THRU 11042.MODEL 888, SERIAL NOS. 85000 TXRU 81084. n

MODEL 885A, SERIAL NOS. 98001 THRU 86100.MODEL 88511, SERIAL N08´• 88082, 88069, 98088,880?5, 880?8, 88085 AND 88201 THRU 88208.

REASON FOR PVBLICAIION: SEVERAL RECENT ECU FAILURES HAVE DEMONSTRATED A NEED TO~i?""/ REEMPHASIZE THE 8YMPTOhIS OP AN ECU AILURE AND THE APPROi

i PRUTE ACTION BY THE PILOT AS SHOWN hi THE APPLICABLE APM/POA.

COMPLIANCE: N(YI´• APPLICABLE.

BY WHOM WORK WILL BE *CCOMPLISHED: NOT APPLICABLE.

APPROVAL: ENGhTEERINO DESUIN ASPECTS ARE FAA APPROVED.

~1N HOUAS: Nor *PPLIC*BLB.

PARTS DATA: NOT APPLICABLE.

SPECIALTOOLS: NONE.


The following provides a brief description of the symptoms which may accompany a mechanical failure ofthe Environmental Control Unit (ECU). Also listed are typical procedures that may be used in the eventof a mechanical failure of the ECU which will allowsale handling of the airplane. This document ispublished to bring to the attentlan of the pilot the type of information an this sublfft that is avall8ble inthe Pilot’s Operating Handboo~ and does not override the speclllo data in the Pilot’s Operating Handboor.

ENVIRONMENTAL C~TROL UNIT FAILURE

A mechanical lailure of the ECU will result in a complete loss of cabin temperature control. The cabinpreslrieatlon system will continue to Operate; however, cabin temperature will increase significantly.An ECU failure may be accompanied by an odOr of hot oil and hot air ducts, followed shortly thcrea(terby light smoke from Uls airoutlets. A noticeable increase in cabin temperature will occur. Il.theseindications are observed,check the airflow from an overhead outlet. Hot air coming from an overheadoutlet indicates a failure of the ECU, since only cool or cold air comes from the overhead outlets during.normal operation.

If an ECU failure occurs and it is deemed necessary to daprseeurlae, proceed as follows:i. PASS OXY Switch ON, if carrying passengers in any sent other than Ni cockpit seat.2. Oxygen Masks DON. Verify all occupants are receiving oxygen.S. ENVIR MASTER Switch ENVIR MASTER position to close ECU shutoff valve. Cabin willaapressuri~e when valve closes.4. Valve YERIPY CLOS~D by checking for airflow from environmental outlets. U.irflow

5. Bleed Air Selector IIOTH CLOSED. Bafh valve lights illuminated.

ORIGIINBLL As

RECEIYED 8Y ATP P´•pr LIZ

BERYICE INFORMATION NO. SI-220

*0´•r CPlacing Bleed Air Selector to BDTH CLOSED will renderthe alrdriven artillclal horieon and the wing and empe-nnage delcer boots inoperative.

B. Desoent- INPTIATE bbelow 12,0Wleet, ilpossible.

Ram air va~ves will open when cabin depres~urleasl This will aid in clearing the cab~n of smoka andfumes and will reduce cabin temperature.

Do not attempt to use ECU until mallunclion has been corrected.


WEIQHT AND BALANCE: NOCHANOE.


PUBUCAnONSIFPeCTeD: ~I-NONE.

RECORD COMPLI\NCE: NOT APPLICABLE.

"I.I

C

Pnce 2 of 2

iD:´•

A~space

LIERVICE-IN~ORMATION Npi 51222

IRApril 18X5

ooWTv RCTOt SERVICE BULLETIN 61-1d49(6140066408026 QnlB)

i.

MODEL~FFECTED: MODFIL BBOC, SERI~L´•NOS_11BW THRU 11156;

:XgX~t´• 08811;~I,NOt~awl TNRUIIWL

MODEL B8SA,R86B18ERIA4 ~$gBOBL-gBOB4 88008,886?6: 96~8,:BOOR6 A~ 90201 THRII

86206.

84806 FOR PUBUCI\TION: T1PqS~COMMEND OOMPLIANCB:WITH:~ BVLLETIN 6i

~TO DO~ ROTOL

Bv W~lwonK WILL Be *C~PHEDI A 4 08 EQUIVALFINI:

appRovari REFERTO:DOWTY-ROT04 BERVICEBULLWIN 81´•1048´•

´•_ :EsnMarEo 11411 nOuAs: DOUrpy ROTOL BIRVICPE OVLLETIN 81-1048.,1:

:~i:: pARTS:Dlml DOWTY ROTOL BBKVIGk BULLERN B1-i~g.

N~

ii ServioelBullet(n 81´•1048.

2, i ~il out and mail Campli.nee Card.in

eLEcrRlcaL Loaa: NO CW~N(IB.

WEBMTIND:BAL*NEB: NO CHANOB.

BNO.

PueLlcnnons AFFECTID: Th. Alrplsne: Maintonn~oe MqnuAl hb.~ rrqulrrd by this document will hrincorporated at tke nout sohbduled revl.lan.

RECORO;OOMPLIP~NCE: MBkS nn appmprlata Bntrvrn slrplsne ~ee insmaliollNo. 81-222’,´•dsted 15 April 1BB1. entitled IDowty Rati;l Servioe Ra116tln B1;1MBZmawnplish;d ´•.::(date):’:

oR8csg~atAs RBcojued Ry

ATPi

i i

IDQPilT~I’I ROTOL

StRVICt BULL[IIN

OF ESSO BEACON 325 GREASE

MOULFICATION No.(c)VP3179

1. PLANNING INFORMATION

A. Effectivity

Ai rcraft (c)Propeller

Gulf stream Aerospace Commander R306/3-82-F/7Fairchild A/C Corp. Metro III Merlin IVC R321/4-82-F/8Fairchild A/C Corp. Merlin IILC R324/4-82-F/9FMA IA66 R316/4-82-F/6jetstream 31 R333/4-82-F/12CASA 212 R334/4-82-F/13Embraer Xingu 111 R338/4-82-F/14

B. Reason

(1) Evaluation of Esso Beacon 325 grease has produced evidence thatit is far less susceptible to oil separation than Aeroshell 7and is therefore less likely to leaL during service.

C. Oescription

(1) This modification introduces Esso Beacon 325 grease to bestocked and used as a preferred alternative to Aeroshell 7 andTexaco Low Temperature EP grease.

NOTE Esso Beacon 325, Aerosheil 7 and Texaco Low TemperatureEP grease are not to be intermixed.

O. Compliance

(1) Recommended at next overhaul or repair.

E. Approval

(1) The modification to which this bulletin relates has beenapproved by the United Kingdom Civil Aviation Authority. Thetechnical content of this bulletin is approved under theauthority of CAA Approval No.DA1/1018/39.

F.

(1) Normal time.

Feb 10/8761-1049

Page 1 of 3

BD~TiYI ROTOt

S[RV~Clt´• :IIHflll

G. Material

(1) No modification kit is issued. The grease should be purchasedas and when required.

H. iaolinq

(1) None.

i. Weight

(1) None.

3. References

(1) Dowty Rotol Component Maintenance Manual 61-10-16.




(5) Dowty Rotal Component Maintenance Manual 61-10-25.


(7) Oowty Rotol Maintenance Manual Publication No. 1002.

(8) Dowty Rotol Maintenance Manual Publication No. 1008.

(9) Dowty Rotol Maintenance ManUal Publication Na. 1009.


(111 Dowty Rotol Maintenance Manual Publication No. 1014.


K. Other Publications Affected

(11 The above manuals.

til-lO49 Feb 10/87Page 2

IBQIFlfYI ROTOL

StRYICI BULLtllN

ACCOMPLISHMENT INSTRUCTIONS

A. Embodiment Instructions

(1) On build of blade group use E550 Beacon 325 grease for all loca-tions illustrated in the component maintenance manual with theexception of the blade mating faces of the blade bearings bottomraces. At these locations the grease detailed in the componentmaintenance manual is to continue in use.

Method of identification

(1) Record Mod. No. (c)VP3179 in the propeller log book.

3. MAIERIAL INFORMATION

A. The modification will be embodied in future production by the manu-

facturer. Stocks of pre-modification greases will not be maintained.

New List Old InstructionsPart No. qty. Price Keyword Part No.

Esso Beacon A/R N/A Grease Aeroshell 7 or

325 Texaco Low

Temperature EP

Feb 10/87 61-1049

Page 3

Li

~IIi.

Infoi mationCa ´•~Gulfstream

~1:"´•-´•

;-~iERVICE INFORMATION NO. 51-223

90 November 1981

E;inlN LANDING GEAR TRUNNION PIN ACCESS COVER..-´•´•i,;-

MODELS AFFECTED: MODELS 880T, 680V AND 88(1W, SERIAL NOS. 1418 THRU 1R~O.

MODEL 681, SERIAL NOS. 6001 THRU 6072. gjMODELS 690, fiSOA AND 89011, SERIAL NOS. 11001TIIRU 11548, 11550 THRU 11586.

"MonnL s~ac, aRlhr NOS. IIBODTIIRU 11195

MODEL 6I)OD, SERIAL NOS. 15002 TIIRU 16042.

MODEL 695, SERIAI. NO9. 9500L) THRU 95084.

MODEL B(IBh, SERIAL NOS. 04001 THRU 96100.

MODEL 695R, SERTAI,’NOS. 96062, 96063, 98069, 98075, 96078, 96088 AND 96201 TIIRU

86208.

REASOu FOR PUBLIC;TION: TO PROVIDE AN ACbESS HOLE 1N .NDINE NACEWIE FOR EASIER REMOVAL

OF MLD TRUNNTON PIN.´• THIS WILT, ALLOW rOR REMOVAL OF MAW GEAR

WITHOUT LOWERING ENQINE NACELLE WHEN COMPLYIND WITH TIIE FIVE

(5) YEAR OMR I~NSPEFPION.


al~l NOTE

IF ANY PROBLEMS hPE ENCOUNTERED WHaB COMPLYING

WITH THIS SERVICE INFORMATION, CONTACT YOUR

NEAREST CULFSTREAM COMMANDER AUTHORIZED

SERVICENTgR.

BY WHOM WORK WILL BE PICCOMPLISHED: A P MECHANIC OR E4UIVAI;ENT.

APPROVAL: F,NDINgERING DESICrN ASPECTS ARE F~h APPROVED.

ESTIMATED MAN HOURS: MODELS 680T, BR0V, 680W, G81, 690, 690A AND 690n TWELVE (12) H01~R9.MODEL 690C, SERIAL NOS. 11800 THRU 1168?- TEN (10) HOURS.

MODEL 695, SERIAL NOS. 85000 THRU 95081- TEN (10) HOURS.

MODEL B9Bn, SERIAL NOS. 96001 THRU 88003 TEN (10) HOURS.

MODEL 890C, SERIAL NOS, 11688 THRU 11135 FIVE (5) HOIIRS.

MODEL 890D FIVE (6) HOURS.

MODEL 695, SERIAL NOS. 85082 THRU 95084 FIVE (5) HOURS.

MODEL 095A, SERIAL NOS, 96004 THRU 86100 FIVE L5) HOURS.

MODEL 695B FIVE (6) HOURS.

PARTS DATA: PARTS REQUIRED TO COMPrlY WITH THIS SERVICE INFORMATION ARE TO BE

PADRICATED LOCALLY. TB8 NAS13981vm-2 BLIND RIVETS ARE TO BE PROCURED LOCAIlLY.


ORIOIMqlL 1

C As Racdivsd ByAIP i

-::1;::

iSERVICE INFORMATION NO. SI-22S

~s;"´•l-"e*;i~s‘a´•V´•

i ")Odl-’´•i

:iom

:::::-;l-riiLP 1; i ´•II´• liBO’Ci~i-’i´• i;,;il

CUT 2.0" Dln. HOLE IN NPICELLESKIN. HOLE TO BE IN´•LINE WITH

MAIN LI\NOING GEAR TRUNNIONPIN I\LLOWINO ACCESS FOR REMOVALAND REPLACEMENT

NP~S1388MI´•2 BLIND

;XRIVET 18 PLSI SEAL ACCESS COVERWITH PRC l000 IORE(IUIVPILENTI FIREWPILL

J.sa ola, ACCESS COYER~ .8EALANTMAKE FROM 0.016" TYPE

521 ~MS6610 CRES STEEL

IIN FLI\TI

I’J.

iy´•

a*o´•´•TYP

2.76´•’appnax.or:SKIN

APPROX.

FROM EDGE

N~CELLE SKIN IREFI

LEFT INSTALLATION SHOWNRIGHT INSTALLATION OPPOSITE

---:i CW.

i;

SERVICE INFoRMATION NO. SI´•223

CCaMPLISHMENT INSTRUCTIONS:

1 Fahricate a B.BO´•inch diametsr access cover using O.O1B-inoh type 321 AMS5510 corrosion resistant steel sheet stock

Lreter to Figure 1).

2. Remove lan and right engine exhaust pipe aasembliea as outlined in the Airplane Maintenance Manual.

t C*(nlON

The main landinggear trunnion pin is very close B We nacelle

akin; therefore, caution should be taken to prevent damaging the

trunnim pin when cutting hole in nacelle.

S. Cut a a.0-inch diameter hole in outbaard side dleR and right naeelle as shown in Figure 1.

i. Locate, form and drill access rovar, fabricated in step 1., on angina nacelle (re9er to Figure i).

5. Apply PRC1000 flrswall sealant or an aluivalant sealant between access cover and nacelle skin and installaccess cover on nacelle using NA81SgsM4-a blind rivet (8 places)(refer to Figure i).

B. Reinatall left and right engine exhaust pipe assemblies asoutlined in the Airplane Maintenance Manual.

7. Fill out end mail Compliance Card.


WEIGHT AND BAL~NCE: NO CHANGE.

PPI\RES AFFECTED: NO.

C´•Ir UBLICATIONS AFFECTED: NONE.

RECORD CD*PLUNCE: Make an appmpri´•te entry in airplane maintenance records as follows: Service InformationNo. SI-225, dated SO 188?, entitled "Main Landing Oear TNnnion Pm Access Cover." accomplished

(date)

ORIGINALAs Reii~ived By

A;I~P 1

PageSofS

~I:Service information Culhnr~mAnospPaCarpmrim

"dla%~

SERVICE INFORMATION NO. SI´•n6a dune 1987

SUNDSTRAND ECU AIR CYCLE MACHINE OIL REPLACEMENT

YODELS IFFECTID: MODEL BW~, SERIAL NOS. 11809, 11815, 11829, 11840, 11876, 11871, 11879 AND 11709.

MODEL 89011, 8EIUAL NOS. 15002, 15021, 16056 AND 16087.


MODEL BgSA. SERIAL NOS. 98001, 90020, 98089, 88098 AND 98100.

MODEL 8958, SERIAL NOS. 98075, 98078, 98085, 98208 AM) 98205.

REASON FOR PVBUCA7H)N: THE ECU AIR CYCLE MACHINE WAS SERVICED WITH THE ~NCORRECT TYPE

OF OIL BY LIZTNDSTI~AM) CORPORATION. THIS 8ERVICE INFORMATION IS

BEING ISSUED TO ENSURE THAT THE CORRECT TYPE: OP OIL IS USED IN THE

AIR CYCLE MACMNE.

COHPLI~NCI WITHIN 1IWTY (SO) DAYS AFTER RECEIP~ OF THIS SERVICE INFORMATION LET~ER.

BY WIOOM WORN WILL Be A P KECHANIC OR EQZTIVALENT.

APPROVIL: ENDINEER~N(I DESIGN ASPECTS ARE RAA APPROVED.

d .9M11760 Y** .OYRI: IbRO~RS.

NOTE

A credit of SSO.M) rill be laaued to We author~ad OuVstraam

Commander Se~iCsntar. Wat performs the aorL, upon reosip~ of a

properly sllaoutad Warrenty Claim and a completed ComplianceCard, provided Wat Wa Warranty Claim and Compliance Card an,

sent in ~ithln seven (7) mrling days aRar We aork has been

aemmplishsd

PP~RTS DATA: The MIhil Jet 254 oil (appmximately 7.8 ounEee or apprrlmatoly 220 E´•E´•) may be procured IOFd~ly´•

SPECllLTOOLS: NONE.

~CCOIPUWMENT INSTRVCTIONS:

1. Cain access to ECU Air Cycle Machine LACM) located in aR fi~aelage.

2. Chwk for aerial number of Air Cycle Maddne on Ah Cycle Machine identi8cation plate.

a. If aerial number of ACM matches aerial number, noted in Figure 1., lor your airplane model and aerial number,proceed to step 5.

4. Ifaerial number of ACM does not match aerial number, noted in Flaue 1., for your airplane modal and serial

number, fill out and mail Compliance Card noting aerial number of ACM inatalled on your airplane. Proceedto Record Compliance.

Page lofS


ACM I MODEL 5WH: MODEL 89oD MODEL Bg5 I MODEL BS5A MODEL 89611S~ SM 8/N 9/N 9/N SRJ

151 11809

642 11615

296 11629

292 11816

AS05 lien

206 11679

207 11109

671 15002

285 16021

149 16056

220 15037

887 96054I

245 95065

196 98001

487 1 I I 1 98020

1BB 98095

567 98100

300 98076

188 98078

149 98086

118 98203

652 88206

281 in Dapartmsnt of Astatian Auatralls Stook

Fl9un(.

Pogo 2 of 3


5 Drain and replace existing oil in Air Cycle Machine with iMobii Jet 294 oil lapproximately 7.5 ounces or

approximately 220 c.c.1 as outlined in Chapter 21 of the Airplane Maintenance Manual.

NOTE

The oil pan on the ACM is accessible while the unit is still

installed on the airplane.

B. Fill out and mail Compliance Card.

ELECTRICAL LOAD: 110 CHANGE.

WEIGHT AND BALANCE: NO CIWNOE,



RECORD COMPLIANCE: Malts an appropriate entry in airplane maintenance records as follows: Service InformauonNa. SI-229, dated 2 June 1987, entitled "Sundstrand ECU Air Cycle Machine Oil Replacement." accomplished

tdate,

Page 3 of 3

Q~IIService Information Whnmnaoapreffhmcqlin

Service Information No. 56255

14 AuguM 1089

AEROQUIP GENERAL AVIATION ALERT NOTICERECALL ON AEROQUIP 601 nOSE

BVLLmN NO.W1

UODeLSAPPECTED: Models 590 WOA. BOqS. 90111, 9dOE, 9806, 880, 8906, 6896. 8506(6). BBOFL.8sopun, 680r, and ?a0 Serial Nos. 291 thrn 189cl, Model 9008 Serial Nos. 3090

thru 3529, M~del 886 8alpl Nos. 1Mol thru 12068, M~dela 890. 890A. 890B. BWKC Serial Nos.

11W1 Uua 11156. Model BgOD Serial Noa 18001 thru 15W2, Models 895, BSSA 605B Serial

Nos. 89990 thN 98909.

REASON FOR PUBUCIT~ON: TO COMPLIANCE lRIIH AWOQUIP GENERAL AVIATION ALERTNOTICE. RECALL ON AEROQI~ 601 HOSE, BULL&IW NO. 901.

NOTICI

INVICSI~OATION REVEAL AEROPIRP 801 HOSE

INSTALLATION ON ABOVE LISTED OULFSTREAM

COMMANDER THEREFORE AEROQUIPGENERAL AVIATION ALERT NOTICE RECALL ON AEROQZIIP801 HOSE BULLETIN NO. 901 OOBS APPLY

couFulNce: REFER TO AEROOUIP GENERAL AVIATION ALERT NOTICE RECALL ON AEROqULP 801

HOSE. BULLEIW NO. 991.

BY wnor worts Mu BE A p MECHANIC OR EQUIVALEPIT.

APFROYIL: REFER TO AEROPUIP GENERAL AVIATION ALERT NOTICE RECALL ON AEROQUIP 801 HOSE,BULLETIN NO. 901.

ESTBlATEDUANi(OVRSl REFER TO AEB09~ GENERAL AVIATION ALERT NOTICE RECALL ON

AEROPUIP 601 HOSE, NO. 001.

PIRTSDATA: REFER TO MROQUIP GENERAL AVIATION ALERT NOTICE RECALL ON AEROQUIP 601

HOSE. BZTLLETINNO. 901.

SPeCllLT00~5: REFER TO AEROQUIP GENERAL AVIATION ALERT NOTICE RECALL ON AEXOSUIP 801

HOSE, BULLETIN NO. 901.

*CCOUPUSnMan INSTRVCTK)IIS:

I. CMopb ´•rith As~ulp aswral Aviation Ale~ Notice Recall on Aemquip 801 Hwe, Bulletin No. 901.

a. Fill rutend mail Compliance Card.

ELECIRICIL IOAD: Nochange.

welo~ AND BAWnCEr Nochangs.

SPARES No.

PUBWWITMN8 IFFeCTrD: None

ReCORD Mate an appropriate aRJ in ahpns maintenance roarda as Ulas: Servloa InmrmaHon No.

SI-aS8 dated al Auguat. 1889 entitled IAsmlulp (isneral Aviation AlertNotice Recall on Aemquip 801 Hose, Bdlatin

Ne 001" aecompllahsd (dete)

Page 1 of 1

Como,´•l~n sullatlnM1(4\1´•10(10´•11 D1II´•IPn

*ugusl 1888~´•o´•on Flint

JmSoumE´•~l*r´•nu~´•d´•on. M1(9205´•19~2nhone 517´•7818121IU 517´•387-~118I´•m: 711412

~Li\eroquip

GENERAL AVIATION ALERT NOTICE

RECALL ON AEROQUIP 601 HOSE

Aarogulp is pre´•ently recslllns COltaln PPBC’lied 601 hose iTha 601 type nose assemblies could be IdBntlfled

a´•.emller Tne suspect hose aosamblles cOnslslof /L.l.quip Mth one 01 the following Aeroquip part numbers.

80( hose with rubber cure dates from 1084 inrough 3087.

Thl. hose could have been installed on any General Aviation or601WOI´•´•III 00112(1-´•-Ui´• ~201(1-i-UI´•

experlmsnlal aircraft from Plpnl 1984 throush May 1988.B0l00li´•´•´•1´• 601113´•´•´•´•´• ~ZO(1Z´•´•´•xii´•

~01002´•s´•´•n ~OttsO´•-´•i´•i OZOttJ´•´•´•uui

6010031-1111 00tl~(´•´•´•´•u´•

60100611111 L101371´•I´•´•´•~I

´•I sa~mz..,..

60101911111 601´•8’1´•´•´•´•1 ~10((1´•´•11´•´•

gnl* n´•lna oolon~ losl´•ll ~10100´•´•´•u´•I ~10119´•1´•11´•1

401040-1-1111 020102´•´•-´•´•´•´• ~ZMm-I´•uu´•

Aerooulo requsas that any aircraft ownersloperatorr wno ~01011´•´•´•´•´•´•´• 620(031´•´•1´• ~20121´•´•´•´•1´•´•

have ´•n.lalmd hoses durtnp the aboveldcntlfi.d time LHriod (120101~1-u´•´• (120122.1.1´•11

601064.1.lu11 IPO(D6´•´•-llII 820113´•´•´•´•LI´•notna loll-ulno

.0(01.1´•´•´•´• ´•I010L1´•1´•11 62012.´•1´•1´•´•´•

´•ImmOdl**l~ inrFre’ ´•"e aircraft for sly 4arwulp hoses .0106~´•´•´•u´•I LW~?)´•´•´•r´•´•´•

/\erooulp.orOouced *o)e assemblies are identified with a 601067.1.1111 ~10101)-´•.1´•´•´• 620126.1.1111

metal idantlt;sallon b,nd IIO(W(i´•´•´•´•´•´•l 620109´•´•´•´•´•´•´• 620(~L-´•´•´•I´•1

00(0(1,´•´•´•111 620110´•´•11´•´•

IWnfdladwlmsnAE701´•i´•lu

part number are nor suspect and mould nor be removed´•’"O"V’´•

´•´•.´•m´• unless. U.M1 inrpection and/or performance ot routineloll Isr-

u~n X LDCulol maintenanee. a problem with the hose io identi(ied.

´•’´•´•*Y’""´•)t the hose assembly has no bandor it is illapibla aM’L’´•’’’’ 81´•´•´•´•1-´•11´•

10*1-I 1I1´•´• can be Y.ntai.d.O an Aaroqulp ness. the hose snam-

bly should be removed and replaeed if it was installed

9YsRE9 ´•´•´•´•P~- from ~pnl 1984 througn May 1988

(11IIII.UII ´•This notica does nor apply to Oulhtrsam Alroaft. pell

H.liCDgt.r 01 MCDonneII Dougla. nelicooter Model 600.

Separate ~´•Nica bulletins will )´•.asuad for operators of

OuHmwmAircish doll WEmsrsnd McL~nndl DouglasHOIIEW101 Model 900.

´•AnV *srogun 601 type hose assambliasthat are identified

with 1 094 throu0h 3(187 hosefula date are suspeCt endWhen the suspect hose aeeembltes have been IdenlltiW.

should be removed The cure dates may be rhowncontact one of the authorilad Aeroquip distributors idantlfied

CD1084 through CD3C187on the reverse side of ih~ A).n Notice. and prwids that

ed the hose cure data. are Mt Ihom. then AHoguip Aaoquip distnbuutw unfh ihtollouing iotorm´•lion:

801 type hope assemblias identified with an assembly Ownar.. Name

date of A208q throuan A2(18B should be removed. It Address:

assambty date I. shown m month and year. remove all phone Number:

assemblies with assembly date A.rl 1984 throu0h May ACE,sh R´•gkn´•lion Number:1988. Nose Assembly. part Number a Description:

Can~ou´•d

IIIIIUIOVI OOMPINI

a

The sulh~rilad*sralu,p d,rtributor will send vou reolecernent it there are any qus~tion´• or it vou are uns~k toconfecf one olho´•e susmblin. Complete in´•tructien~ ln(ormin0 you how 1c the wthoriled *aroqui. dinributn´•, then eonfaft *´•roqulp st

return the suspect hose lotheAeroquip di´•tributor 19095411888will he included with the replacement h~´• w~´•mMUI. You

~III n´• ~rl.b.or b. m~ m*am´•m hu

´•~tsmblis´• snd ~YDleqbCnlly Ered1te6 (O( the lull amount

when the dl,tribulor rK´•lv´•l the removed IueoectIkie otter tor nocherge reoles´•mant hoee n.smbllsl

asaembller.

AEROQUIP HOSE SHOPS

Asro Hardware 8 Supply. Inc. Herbe,AIrcratt Service. Inc. Vsr(la EOtsrprisso. Inc

4301 NW. 3816 Street 124 Center Street 2350 South Aimon skd.

Miami Springp. FL 33( 86 El Sagundo. CA 90245 Chandler. At 89249

Phone: 305-888-2411( Phone: 213´•322´•9575 Phone: 802´•883´•8936

Plimano Hosal Unlimited. inc. Nals~n´•Dunn. Inc.

5801 wan Harry 818 Dooll* Drive 940 South Vail Avenue

P.D. Box 12370 San Laandro. CA 94577 Monabell~. C* 90840

Wlohits. I(S 87277 Phone: 415-832-4177 Phone: 212´•724-3’105

Phone: 3189432377

Piedmont Aviation Supply Alama Accelawin. Inc.

FDurnier Rubbsc~ B SuWh Com~sny 3820 North Libnty Street t08UV´•nd´•la

1341 Nonon Avenue Win´•t~nS´•l´•m. NC 27102 San Antanio. TX 78218

P.D. Box 285 Phone: 919´•~87´•8993 Phone:

Columbua. OH 43218

Phone. 814´•294´•8S43 Superior Air Pane. Inc.

oll´•r rX 76244

Phone: 800-84&4873

j

~I ~´•lr

Service Information CIIRC~*FT COePOR*TIONno. Bac 9369

Aaetaa, WA 88PJTel: (2oB1CFr8T87 Far:(206)4351112

Service information number 236, rev A

August 2, 1995

INSPECTION AND REPLACEMENT OF FLUID LINES

Models affected: All Twin Commander airplanes

Reason for publication: To recommend replacement of all hoses installed in enginecompartment after a maximum of 10 years time in service and to recommend inspection of ail

other fluid hoses and lines annually.

Compliance: Twin Commander Aircraft Corporation recommends the part replacement and

inspection intervals stated in this publication.

By whom work will be accomplished: A P mechanic or equivalent

Approval: This Service information is FAA approved.

Estimated man hours: 2 hours per side

Special tools: None

Accomplishment Instructions:

Replace all engine compartment hoses with new hoses after a maximum of 10 years in

service. This applies to all hoses’installed forward of the engine compartment firewall. Inspectall tubing and tittings. Replace or repair any wom, damaged, or corroded fittings and tubes.

Inspect all fuel, oil, and hydraulic hoses, tubes, and fittings in the airplane at every annual

inspection. Replace any worn or damaged hoses, regardless of age. Replace or repair any

worn, damaged, or corroded frttingr*and tubes.

Note: Replacement hoses may differ in construction and outside diameter from originalhoses. Be sure that clamps properly secure the hoses. It may be necessary to change to

different size clamps.

Electrical load: No change

Weight end balance: No change

Spares affected: No

Record compliance: Make an entry in the airplane maintenance records as follows: "All

engine compartment hoses replaced date i in accordance with SI-236A, dated 8-2-95".

Senrice information *IRCRIFT CORPOR*TION

P. O. B~xS3aJ

~lneton, WA 88223 Tsl: ~06)4358797 Fax:

SERVICE INFORMATION NO. Sl-237

14 Fsbruaryl984

NEN PRODUCTION REPLACEMENT FUEL CELLS

"PERMAFLM"m~

MODELS AFFECTED: All models of Twin Commander aircraft. except Models 520. 560. and 700

REASON FOR PUBLICATION: To provide aircraft owners and maintainers with pad numbers for use when

ordering new and improved Twin Commander PERMAFLEXTM Factory Authorl2ed

fuel cells to replace obsolete Engineered Fabrics fuel cells.

COMPLIANCE: When replacement of existing fuel cells becomes necessary.

BY WHOM WORK WILL 8E A P mechanic or equivalent.ACCOMPLISHED:

APPROVAL: Not applicable.

ESTIMATE MAN HOURS: Not applicable.

WEIGHT BAL4NCE: When installing new fuel cells, calculate the fuel system weight change using the

values stenciled on the fuel ce~ls. If the weight change exceeds 5 tbs., incorporatethe weight change in the weight and balance section of the aircraft flight manual.

NOTE: IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS SERVICE INFORMATION, CONTACT

YOUR NEAREST FACTORY AUTHORIZED SERVICE CENTER.

NEW rM FUEL CELL REPLACEMENT PART NUMBERS:

OLD NEW OLD NEW

Tcne P/N Tcne P/N 1%AC P/N Tcne P/N

630069-501/ ;502 511/-512 630302-1/ -2 -503/ -504

63ooaa´•so7 -508 -509 i 610 630302601 -502 -505 j -506

630061-5011 -502 -511/-512 63o3a4-1/ -2 -503/ -504

630061-507/ -508 ´•509/ -510 630304-501/ -502 -505/ -506

630082-507 -511 630307-11 -2 ´•5011502630063-501/ -502 -511/-512 630308-1/ -2 -501/602630063-507/ ´•508 ´•509/ ´•510 630353-1/ -2 -505/ ´•506

630084501/ 502 ´•515/ -516 630353-503/ 504 -507/ -508

830064-507/ -508 5111-512 630354-1 -503

630064-509/ -510 513/-514 630354-501 -505

630204-501 -503 630355-1/ -2 ´•5031 -504

630296-1/ -2 -503/ -504 630355-501/ -502 -5051 -506

630296-501/ -502 -505/ -506 630356-1/ -2 -501/ -502

6303011 i -2 -503 -504 630393601 -502 -503 j 604

630301-5011 -502 -5051 -506 630397-1/ -2 -5031 -504

63a397-so1! ’502 -5051-506

NOTE: FOR FUTURE REFERENCE WHEN ORDERING AND REPLACING EXISTING FUEL CELLS WITHNEW ’PERMAFLEX"rM FUEL CELLS. PLEASE PLACE A COPY OF THIS DOCUMENT IN THE FRONT OF YOURILLUSTRATED PARTS MANUAL AND YOUR MAINTENANCE MANUAL.

jr~w

Service I nfbrmation AIRCRAFT CORPORAT~ION

P.O. Box 3388, Arlington, WA 98223435-8797 fax1360)435-1112

Service information 238

January 18, 1996

DEICER 8007 INSTALLATION

Models affected: all airplanes with deice boots.

Summary: This information updates the maintenance manual instructions for installing deiceboots.

Compliance: When deice boots are replaced.

By whom work will be accomplished: A 8 P mechanic.

Approval: This Service information is FAA approved.

Instructions:

Follow the instructions in the maintenance manual when installing deice boots, with the

following updates and clarifications.

1) Cement 1300L is equivalent to EC-1403 and may be used in its place.2) Toluol may be used anyplace that MEK is called for.

3) ProSeal 890 may be used in place of EC1031 and EC801 fillers.

4) Boots manufactured by Aerazur do not require leer or conductive paint.5) It is important that the mounting surface of the boots and the airplane be thoroughly

cleaned.

a) It is important that the curing times and temperatures be observed: 24 hours at

temperatures of BO"F and above, or 72 hours at temperatures below BOOF.

7) Boots on the right side of the airplane must be the same, except for being opposite, as the

corresponding boots on the left. In particular, they must have been made by the same

manufacturer.

8) It is recommended that when a boot on one side of the airplane is replaced that the boot

on the other side be replaced at the same time.

Page lbl

~s TW/N

COMMANDERSERVICE IN FORMATION

teolo asM DR NE

ARLINGTON. WA 98213-7832

PHONE (380) 435-8797 FAX (350)4351112

Service Information No, 244

January 27, 1997

PROCEDURES FOR OPERATING IN ICING CONDITIONS

AND TO THE USE OF POWER SETTINGS BELOW FLIGHT IDLE

FOR TURBOPROP AIRCRAFT

MODELS AFFECTED: Models 680T, 680V, 680W, 661, B90, 690A, 690B, 690C.690D,695,695A,895B

REASON FOR PUBLICATION: To provice aircraft owners and operators with the FlightManual/Pilot’s Operating Handbook insertion regardingprocedures for operating in icing conditions and to the use

of power settings below flight idle.

COMPLIANCE: Prior to next flight.

BY WHOM WORK WILL BE ACCOMPLISHED: Owner/Operator/Flight Crew

APPROVAL: Flight Manual/Pilot’s Operating Handbook revision is FAA

approved.


i. Removal of obsolete pages and insertion of revised Flight Manual/Pilot’s Operating Handbook

material in appropriate sections of manual.

2. Complete attached postage paid Compliance Card and return to Twin Commander Aircraft

Corporation.

Page 1 at 1

COMPLIANCE RECORD

SERVICE INFORMATION NO. 244

PROCEDURES FOR OPERATING IN ICING CONDITIONS

AND TO THE USE OF POWER SETnNOS BELOW FLIGHT IDLEEOR TURBOPROP AIRCRAFT

MODEL AIRPLANE SIN REO. NO. TOTAL TIME IHOURS)

OWNER NAME

ADDRESS

TELEPHONE NO FAX NO

COMPLIANCE WITH SERVICE INFORMATION NO. 244

Please fill in date below that revisions were filed in appropriate Flight ManuaNPilot’s

Operating Handbook.

DATE

WORK PERFORMED BY IPRINTED)

ISIGNATURE)

COMPANY

ADDRESS

TELEPHONE FAX

Z

TW/N

SERVICE INFORMATION A/RCR4FTCORPOR4T~’/ONARLINGToFI AIRPORT

f 9010 59TH DR. N.E.

ARLINGTON, WA 98223-7832

PHONE (360) 435-9797 FAX(360)435-11~2

Service information No. 249

May 18,2000

Installation of 300004-501 Removable Duct as Part of SE 214

Airplanes Affected: Those airplanes for which Service Bulletin 214 is required.(690D and 695A: all serial numbers except 15037, 15041, 15042,96064, 96072, 96088.

6958: serial numbers 96063, 96069,96075, 96078, 96085, and

96204 through 96208.)

Twin Commander Aircraft recommends that the Removable Duct, 300004-501, be installed

at the time of the first inspection that is done in accordance with item r~l on Service Bulletin

214. Inspection item on pages 7, 8, 9, and 10, refers to figure 25 on page 59 and is requiredat or before 7500 hours of operation. Making the duct removable will simplify future re-occurringinspections.

Kit SB214-4-501 contains the parts and drawings for this installation. It can be ordered from anyfactory-authorized Twin Commander Service Center.

HTW/N

CO~MIMANDERSERVICE INFORNIATION A/RCR4FTCORPOR4T~’/ON19010 59TH DR NE


PHoNE(360)435-9797 FAX(360)435-1112

Service information 251

March 19, 2001

PPG Windshield Moisture Seal Installation and Repair Procedure for Installed Twin

Commander Aircraft Corp. Windshields

Models Affected: 690A/B/C/D, 695, 695A/B With Part Number 360043-1/-2, -3/-4, -7/-8,-11/-12, -11SS/-12SS Windshields

Reason for Publication: To Insure Maximization of Windshield Service Life by Installation of

Moisture Seal (Hump Seal) per Twin Commander Aircraft Corp.Custom Kit No. 163

Compliance: At next Scheduled Inspection.

Who Will Accomplish Work: A&P Mechanic or equivalent.

Approval: Engineering design aspects of Custom Kit No. 163 are FAA approved.

Estimated Manlhours: 12 Man Hours

Parts Data: Custom Kit No. 163 is available from authorized Twin Commander Aircraft Corp.Service Centers. Order Kit Part No. CK163

Record of Compliance: Make an appropriate entry in the Aircraft maintenance records as

follows:

Custom Kit No. 163 Moisture Seal Installation dated August 4, 1998

Accomplished _(date)

Complete Service Information Letter No. 251 Compliance Form and return to Twin Commander

Aircraft Corp.

COMPLIANCE RECORD

SERVICE INFORMATION 251

PPG WINDSHIELD MOISTURE SEAL INSTALLATION AND REPAIR PROCEDURE FOR

INSTALLED TWIN COMMANDERIAIRCRAFT CORP. WINDSHIELDS

MODEL AIRPLANE S/N REG. NO. TOTALTIME (HOURS)

OWNER NAME

ADDRESS

TELEPHONENO FAX NO


MOISTURE SEAL INSTALLED YES O NO B

DATE


COMPANY

ADDRESS

TELEPHONE FAX

*L

M~N

COIMIMANDERSERVICE INFORMATION A/RC~9AFTCORPOR4TIONi 9010 59TH DR NE


PHONE (360) 435-9797 FAX(360)435-1112

Service Information No. SI-252

April 3, 2002

Exhaust Pipe Seal Installation Instructions

Models Affected: 690A, 690B, 690C and 690D Ecluipped With TPE 331-10T Engines.695, 695A and 695B

Reason For ]Pubiication: To provide detailed instruction for the replacement of exhaust pipe seals.

Compliance: Recommended Procedure

Approval: Twin Commander AircraR Corp.

By Whom Work Shall

Be Accomplished: A&P Mechanic or Equivalent

Parts Data: 1 ea. 144-01-10045-01 Seal

18 ea. MS24693C26 Screw

18 ea. MS21046C06 Nut

18 ea. NAS1169C6 Washer

Special Tools: None

Instructions:

1. Remove Exhaust Pipe from the Aircraft.

2. Remove Old Seal and Scrap.3. Remove any burrs or sharp edges fkom the interior of the exhaust stack seal area.

4. Remove any burrs or sharp edges from the exterior surface of the exhaust stack seal area and from the

aft edge of the -65 Flange assembly.5. Clean the surfaces in the area of seal (items 3&4 above) with an abrasive pad or emery cloth. Remove

dust with a cloth wetted with isopropyl alcohol or methanol.

6. Locate the split in the metal insert in the tail of the New Seal and mark the end locations with ink, soR

pencil or equivalent.7. Fit the New Seal inside the exhaust pipe with the tail end of the seal oriented forward. (ref. Figure 1)8. Position the seal so that it is even with the forward edge of the exhaust pipe. (ref. Fi~re 1)9. Position the seal so that the split in the metal insert of the seal (ref. Item 6 above) is about ’/2" from an

existing fastener hole.

10. Clamp the seal to the exhaust pipe using padded clamps spaced between some of the existing fastener

holes.

Page lof3

rw/N

COIMIMANDER

SERVICE INFORMATION14010-59THDRNE


PHONE(360)435-9797 FAX(360)435-1112

Service Information No. SI-252

April 3, 2002

Caution i

Do Not Clamp Bulbed Section of the Seal!

Exercise Care to Prevent Damage to the Seal or Exhaust Pipe!

1 1. Verifjr that the forward edge of the tail side of the seal is even with the forward edge of the pipe and that

the metal insert is Centered over the existing fastener holes.

12. Drill through existing fastener holes, seal and seal metal insert using a 9/64" or .140" drill bit.

13. Add one new hole to secure the other end of the seal metal insert. Locate the hole .20 to .25" in from the

edge of the pipe and about ~z" from the end of the metal insert.

14. Secure the seal to the exhaust pipe using MS24693C29 Screws, NAS1169C6 Washers and

MS21046C06 Nuts with screw heads and washers inside of the pipe at each hole location. (ref. Figure-i)15. Apply "Fel Pro C5A" or Silicone #5 grease to the seal and sealing surface of the -65 Flange Assembly.16. CarefUlly fit the exhaust pipe over the flan,oe assembly by applying forward force while simultaneously

rocking the pipe side to side and up and down.

17. Secure the exhaust pipe to the nacelle. 2 Places)

Note: If the exhaust pipe has been re-polished while it was removed for the seal replacement, pleaseobserve the following recommendations.

In order to preserve the shiny polished appearance of the pipe precautions must be taken to ensure that the

surface is not exposed to contamination.

Twin Commander Aircraft Corp. recommends that the pipe be handled with clean cotton gloves and that the

polished surfaces be masked with a protective covering during the fit and installation process.

Work surfaces that may come in contact with the pipe should be clean and dry.

When the exhaust stack is installed and any cleaning activity adjacent to the pipe has been completed the

protective covering may be removed.

Prior to the first engine run after installation the pipe should be thoroughly cleaned with Isopropyl Alcohol

or Methyl Ethyl Ketone.

The Key to Maintaining the Polished Surface Begins at Installation!

Arllv Contamination Present On The Surface At The First Ex~osure To Heat Will Degrade The

Annearance Of The Exhaust Stack Over Time

Page 2 of3

I_

TWIN

COMMA IVDERS E RVICE I N FORMATI ON

ARLINGTON. WA 98223;1832PHONE (360) 435-9797 FAX(380)435-1112

Service leformntion No. SI-252

April 3, 2002

Exhaust Pipe Seal Instnllntion

onIaINaLAr sv

arp Figure 1

Forward Edse of Exhaust Pipe I Tail ofBulb Seal

MS24693C26 Screw NAS1169C6 Washer MS21046C06 Nut(l8 Places)

Page 3 oT3

~--e L-- I I I I_

I

TW/AI

NDERSERVICE INFORMATION A/RCRAF;TCORPOR4TIO19010

SSTH DR NE


PHONE(360)435-9797 FAX(360)435-1112II I

Service Information No. Sl-255

December15,2003

Picture Window Upper Channel Inspection

Models Affected: 690, 690A, 690B, 690C and 695

Reason for Publication: Reports of cracking in the 310704-1 and -2 Upper Frame Channel discovered duringtrouble shooting pressurization leaks or window replacement.

Compliance: External visual inspection is recommended at the next 100/150 Hour Inspection and

each 100/150 Hours thereafter.

Internal detailed visual inspection recommended at window replacement, while area is

accessed for compliance with Service Bulletin No. 223, window replacement or when

troubleshooting pressurization leakage at the wing root area.

Approval: Twin Commander Aircraft Corporation

By Whom Work Shall A&P Mechanic or EquivalentBe Accomplished:

Parts Data: New 310704-1 and -2 Channels are available through Twin Commander Aircraft

Corporation Authorized Service Centers. The new channels are manufactured from

.063" thick material with a specified grain direction to improve fatigue life.

Instructions: External Visual Inspection:

Visually inspect the external skin lap directly above the picture windows for evidence

of working fasteners or gaps in the skin lap. If evidence of working rivets or gaps are

found, proceed to the internal detailed visual inspection.

Internal detailed visual inspection:

Remove interior panels as necessary to gain access to the channel through the

lightning holes and removable door of the inner skin. Visually inspect the outboard

flange radius of the channel for cracks. This will require the removal of accumulated

sealant in an area of limited access. Cracks typically occur between rivets on the

outboard flange of the channel.

Caution!

Care shall be exercised during sealant removal to ensure that no damageoccurs to surrounding structure. It may be necessary to remove inner skin

panels to facilitate sealant removal.

If damage is noted in the area accessed above, remove inner skin sections as

required to inspect the full length of the channel.

Remove and replace the channel if any damage is noted.

I’age 1 of I

-~C ´•r LI I _I

~nN

COMMANDERSERVICE INFORMATION

19010 59TH DR NE

ARLIN GTON, WA 98223-7832

PHONE (360) 435-9797 FAX(360)435-1112I I~I

Service Information No. Sl-256

December I~, 2CH)3

Main Landing Gear Up-lock Assembly Bolt

Models Affected: SO0/A/B/U/S, 560F, GSOF/FWFLP/FP, 680T/V/W, 681, 685, 690/A/I)/C/L) and 695/1\/1~

Reason for Publication: Recent field reports have indicated failures of the AN174C-21A Uolt installed at the pivot

point of the up-lock arm. Refer to Item 10 of the illustration below. Rilurc of the bolt

result in the landing gear not achieving or maintaining an up and locked position with a

landing gear unsafe indication.

a 134

I? ~cp&s

´•1

SL~ a A

It 10

Compliance: At the next scheduled inspection and at 5 Years or 3000 Hours thereafter, perform an

inspection of the bolt.

Approval: Twin Commander Aircraft Corporation

By Whom Work Shall

Be Accomplished: ASrP Mechanic or Equivalent.

Parts Data: Replacement Rolts may be procured locally (P/N AN174C-21A).

Instructions: Remove the left and right main landing gear up-lock bolts and inspect for cracb, L~OITOSi011

and straightness. Tile inspection method (Magnetic Particle, Fluorescent I’enctranl, clc.) sll:lll

be determined by the inspection personnel performing the inspection. if the holt is acccpla\,lf,reinstall and verify proper up-lock operation. If the bolt fails to pass inspection, replate tile

bolt, verify proper up-lock operation and notify Twin Commander Aircraft Corporation.Please provide the aircraft serial number and time in service of the bolt. If you are unable to

determine the time in service of the bolt, provide the aircraft total time.

Record of Compliance: Make an appropriate entry in the aircraft maintenance records referencing Service

Information No. SI-256 compliance.

Pnge I of I



Brisbane, CA 94005 (800)227-4610


Twi n Commander A/C

695, 695A, 695B

SERVICE ALERT

1) Applicable AD

2) Part Kit (1)

Issue Number 3) Part Kit (2)Issue Date Issue Description 4) Compliance Time

4/19/94 FLIGHT CONTROL SYSTEM RIGGING 1)

04/19/1994 AND TRIM TAB FREE PLAY CHECK 2)

3)

4)SEE ISSUE

End of Index


GC 0853 SI VA

jrC~w’wtrlllYAYIIAI~

CIIA F T C O R P O ~d TIO NSERVICE ALERT

1991 1Revised; April 19, 1994

FLTOHT CONTROL 8YSTEM RTOOTNC AND TRII TAB FREE PLAY CHECI.

NOTE: This Service Alert supercedes the January 4, 1994 Service Alert.

Changes have been made to this service Alert regarding control surface balance.Also, references to Section 3? of the applicable Maintenance Manual have been

added. Revised text is identified by a black line in Ehe right hand margin.

MODELS AFFBCTEDI 685, 690, 5901, 6908, 690C, 6900, 695, 6951L, 6951

REASON WR PWLlCCATTONI Reports have been recently received from the field

concerning aileron trim tab free play in excess of Ehe established service

limits. Service Bulletin 186, which was issued 23 December 1981, defined

~he actions required to assure that no excessive free play exists on aileron,eleva~or and rudder trim tabs.

Excessive trimtab free play can cause vibrations which can lead to structural

damage and possibly to loss or the airplane. Also, it is equally importantthat the entire flight control system be kept adjusted within the limits

specified by the applicable Airplane Maintenance Manual.

This Service Alert is being issued to re-emphasire the importance of ensuringthat trim tab free play on each control surface is within limits specified bythe applicable Airplane Maintenance Manual. Also, a complete check of the

flight control system rigging is required.

COMPLTANCEr

Initially; within the next 50 flight hours or six months time in service,whichever comes first.

Repetitive; At each annual or other scheduled inspection, except for

checking control system balance. Balancing needs to be

accomplished when any change is made which may affect the

control surface balance, such as painting or repair.

BY wHOM WORE l8lLL BE ACCOMlPLTSREDI R&P Mechanic or s~uivalenC.

APPROVAL: N/A

9PBC~AL TOOLS i As nOEsd in the applicable Maintenance Manual.

RELATED

1) Airplane Maintenance Manual applicable to each airplane model.

2) Service Bulletin No. 186, dated 23 December 1981, Trim Tab Free

Play Measurement.

ACCOMPLISHMEPP~ i

Conduct a complete inspection of the flight control system rigging in accordance

with Section Vrr or Section 27 of the applicable Maintenance Manual. Give

particular attention to control surface balance, cable tension, control surface

movement limits, and trim tab movsmen~ limits.

Comply with the inetruetions outlined in the section "Control Surf~ce ITrim Tab Free Play" in Sec~ion VII or Section 27 of the applicable Maintenance

Manual.

IWIHCOMUIIIDER ~IRCA*PTCORPORI\TIO 1WXI)-SO11( 01. N.E. Irllnglon. WI\ 98113 Talqnons(2PO) 436811 F´•x No. (208) P3Cll(a


South Hill Drive 6AM-5PM PST M-F

Brisbane, CA 94005 (800)227-4610


Twi n Commander A/C

695, 695A, 6958

CUSTOM KIT

1) Applicable AD

2) Part Kit (1)Issue Number 3) Part Kit (2)


132 R1 ENTENDED RANGE FUEL SYSTEM 1)


3)

4) SEE ISSUE

133 IMPROVED SIDE WINDOW DEFOG 1)

09/15/1981 SYSTEM 2)SEE ISSUE

3)

4) SEE ISSUE

134 IMPROVED INLET AIR SUPPLY 1)

01/11/1982 SYSTEM FOR YOUR JETPROP 2)SEE ISSUE

ENVIRONMENTAL CONTROL UNIT 3)

4)SEE ISSUE

135 COMMANDER AURAL MACH OVERSPEED 1)

09/29/1982 WARNING SYSTEM 2) SEE ISSUE

3)

4)SEE ISSUE

136 IMPROVED TAIL LIGHT/STROBE 1)

1111511984 LIGHT SYSTEM 2) 310052- 509

3)

4) SEE ISSUE

137 WINDSHIELD ANTI-FOG SYSTEM FOR 1)

01/18/1985 YOUR GULFSTREAM COMMANDER 2) SEE ISSUE

JETPROP 3)

4)SEE ISSUE


GC 0853 SI CK

1) Applicable AD

2) Part Kit (1)



138 R1 AUTOMATIC ENGINE IGNITION 1)

06 14i 1987 SYSTEM 2)SEE ISSUE

3)

4) DISCRETION

140 R1 NOSE GEAR STEERING 1)


3)

4) DISCRETION

141 ENVIRO AIR CONDITIONING AND 1)

07/17/1992 PRESSURIZATION SYSTEM 2)SEE ISSUE

INSTALLATION 3)

4) DISCRETION

158 ADDITION OF INBOARD DE-ICE 1)

01/08/1996 BOOTS 2) CK158-501

3) CK158-1

4) DISCRETION

163 PPG windshield moisture seal 1)

08/04/1999 installation and repair 2) CK163

procedure for installed Twin 3)

Commander windshields 4)See Issue

End of Index


GC 0853 SI CK

SERVICE PUBL1CATIONSCulfstrramnmerican

revision notice Coamandar Divi~ien6001 N~rh R~cLwall Avsnus.Bsfhany. OLI´•horm 13008

CUSTOM I(IT NO. 152

REVISION NO. 1

19 ~uly 1981

EXTENDED RANGE FUELSYSTEM MODIFICATION KIT

APPROY*L: FAA DOA 8W-2 APPROVED.

Page 2 at 20 PARTS DATA

CBANGE: Part Number of Hose

WA8: 650584-35 Aose

NOW: 650384-31 Hose

Page 1 of 1

tB 118´•~L sljslC~mmnda,Oirilion

CUSTOM KIT NO. 192 2 MARCH 1981

RN EXTENDED RRNGE FUEL S’bSTEM MODIFICA-

TION KIT FOR YOUR GULFSTREAM COMMRNDER

J~TPROPS.

Olncreases usable fuel capacity from 425 gallonsto 474 gallons for a range increase of approxi-mately 240 nautical miles.

EFFECTIVITY: MODEL’890C (EIOHT FORTY), SERIAL NUMBERS 11800 THRU 11999

MODEL 895 (NINE EIGHTY), SERIAL NUMBERS 95000 THRU 95040

Obtain this kit and tull details trom your nearest Dulfstream Commander SetvlCenter.Price: $8500.00, plus insfallation

Pd~s ´•uWnf ~ifhoulnolra

C

ORIGINALAS RECEIVED BY ATP. COPY ON ORDER

4

L

Udfucrcnlnnmrricn,

9 ATi~A/’ s,~ ~sen/

OOSiYlM KIT NO. 1822 Mnneb 1981

EXTeNDED RANGE FUEL SYSTEM MODIFICATION KIT

MODELS *RECTED: MODKL SS(lO, SERIAL NO~ 1IMLO THRU 11989 AND MDDEL 696, SERIAL N05. 96000

THRV 85MO.

REASON FDR PUBUCATION: M PXOVIDB MCREAB&0 PUELOAFAClTY.

COMPLII\NCI?: AT OWNEW D18CR6T10N.

NOTE:

a´• ANY PROBLRMII ARE ENCOUNTERED WHILE

~FPALLINO TH18 CVBT(IM KPI~. YOUR

NEAREST OULFSTR&~M COMMNYDBR ~IITHOHIZBO~LERVLCeNTERPACnPI"I.

BY WHOY WORK: WILL BE A k P MeCHANIC OR EPUrVAI.ENT.

*PPROVAL: PM DOA aw-a APPROVER.

eSTlmnm~MANHOuRs: FORTY SeVEN (II) HOUR8 (USINC´• WFF CILIBRA.I\IOK PROCED~LE) TWU(1.Y TWO

(821 HOURS (U8WC DRY CALLBRATION PROCEDIIR&)

PARIS DATI\: PaN rsollired to install Wia Custom Kit may ha pmursd thruuEh your ncare~l CulIdrrsm Connan-

d~r SuviC´•ocar Farlligl Tor 88580.00.

Oultom KIC No. 132-1 Model 590C Airplana, uial n~a 11008 thru 11853 and hloCI 096 Airpl´•nw. ari´•l n~s 88800

Ulru85MO.

Oosrom KtlNo. 199-2 Madsl sfloc Ai~lanlq wrial no’s 11861thN IlsPg.

Rdmlrr the ´•ppliuble eulllom kl~ n(daM) model and ractary rrial oumbrr v~hsn ord*rine Curlorm Kif No. 1~P´•l or

111-2, eun~l(lnlt ortho rollowing:

K~NrlSa-I

PTY OTY PAWTNO. DESCRIP1ION

1 u. 1 as. 110156-060 DEcnl

)c´• 2 ea. 6300821

2nl. 1.4´• 69MSl´•b01 OnrhetZoa. 1 e´•. 860082505 Gasket

II En 2~u. b30821´•M)1 P)aLI

)sC 2,. 630310-1 Tulr1 sn, lea, 630351.1 (:EIIIUI FIIII CCII1Ln. 8311931L101 Csncar Flrl Cell

AS2 se. Zen. Rl(lY58´•S Piller illnck

b a3o3aa´•s(IECEIVED HY Aq´•p

lan. lull. 6309688 Filler ill~rk

11L 1 r´•. 630368-7 Filler (Ila~L1 cn. len. 6311358-8 Filler Hl~sL

1 el. )pU. 530JJB-18 Fill*r nLrk ~i ’i

CLIS1~M 101NO. 1SZ

(177 Q1’Y P*IO.NO´•Kit h’~ 132-1 KilNo 132-2

1 I´•. la. 630965-80 Pil*r Black

I.a. 1 nn. 83(IS6BgS Filler Black

1n. lee, g~a96e9( sillar Black

Pea 2c´•. 630568-96 Flll.rBlak

Jar. 6 an. 830969-80 Fillsr Black

2s´• 690309-609 Pu´•l 9u´•n~iB Monitrr

2an. 2 sc. 630972-501 TmnsmitUr

II. 2sn. 630913-601 Tr´•namilLer

241- 2re. 590370-001 Tube *ay2 er. Pa. 890976809 Tuba hs~y2 an. 2ca. 690376-606 ~btl Asalee. 1 a. 69091&121 InUrconnr(

I I´•, lee. 6801)78-522 b~rrnnnnal

lu´• 1 ca. b30518619 inta~onnat

t a. I a. 030378-654 IntcrmnnaclI a. 61~880´•680 IntElronn~(

Is´•. I a. 630950-550 incarrannac~

lot. I se. 8110980-Mn lnlcmonnace

1 01. 1 a. BIlh980´•6SB Lnhrronnrl

2oa. Pa. RYOBR0~519 intamnnad

a ´•o, aaa. BBOBMd6 Bore

630583-501 lusl Call

lu. 650588502 Fuel Call

(aR Rannle-l a

030416-305 Valva Arsy2a. 2on. 690416-601 a

6904161606 VIIV(I

lan. 090417-8 l\daptarAayt a. 690417-16 Block

20´• a M´• 6YM1&? Sernn AsoyI.a. 1 a. 65041829 Aq

I´•a. 1 a.. 650116-24 Angle hney1 a. 630119-5 RracLst

1 let BJM1B-li ORIGINAL 1

loe 050410-15 Ang´•l* ~Asly As Received BYlee. 111l 68WLB-19 Ane~s AayZ~a. Pat W0l9Bl14 Clump ATP2an, esa. AN8C8A &.h jsla. 32laa MI4HBA Bait

244. Pa ANla7TW30 Clamp4sa. AN787TWJ8 Clamp

2an. Pa. M81~-4D Unia,

(LU´• I a. AISBOCBL H’aahar

RUI. 544. ~N9BbDR6ss. 944. AN86~CIOL Wanlar

a.. O~l´•m*C nJlaa. YBsa. ANSBOL’II(I Walhor

418. 1~- MS95´•8)6-eP8 kmx~ RSBsl. Bsn. Myss2062cs AECr~

-i i riP6crr g~. ´•MSl~l(n´•?B1 Scnnr2 a. Pen. MSS64RO-1P Ommm~t

(e´•. 1´•´•. MSBO2J-01 Clamp91a. 844. S0310al?HT O´•R)nRIle´• 12 a. Vrlrm Pile (2"12’1

Ipt. 1 pi. MILS´•~983 Cement.

lroll I mil T.p. BST ’lapa (Ztrido a U.UII~ Ihictl

IOR. 10 R. Clen. Yl(s(l Wire (0.01Z~I

1*´•. 630351 HlurprinlIn. Ian. 690968 larprinllee lan. 680381 Rlllllrit,~

Isa BWJLI~ Ulucprinl1 ca 630(11 i(lllcplilll

CU(I’POM KI1‘ 110. 131

i(iINe 1~2-1 HI( No. I)PY

qru OT1 YnlllNO- UI:.CAJI?I(IN

lee 1 na 6J0C18 Blue~int

1 ea. B~DI1B BlueprilaIna. 1 MI. 800706 Bluapin(I M- 1 U1´• 890120 Blueprint

1 os. 800612 Blueprint (!’~sL16b 15.1)

IRe* AS1

Isa 1 cc. 851055 BlueprintLcn. Custom KitNo. 139 Inptrudiurl;

SPECII\L TODLS: NOh´•e

ACCWPL15I1MEMmsTRVCT)(INS;

Ihli~el.irpl.n. as nutlined in Chnptor is orthe Airplane M*(nLanan~e i~nll´•l

CPIUTIOM

Do nut uu airplane hal boo~r nump to drain bel mnn

airplane llacommend use of s´•tarn´•lly au~erad pump to

prevent possible damage to airplane pump.

i llemove ruael.~e hood doors that are lo~nted on top ollu.clage and ilnn,dlolcdl:. o*sr wine area.

9. Rrmurs asoeudeora fmm wtsr wingaren.

Romnvs roru;ard and aR i.bosd Turl UnL i~r dears hom (aft and right ~inr.´•

5. Hsmove lorrml and in oulla´•rd ~ualUnk nceeaa doers hem ieh and right clnl

(Ba 8. Rernara and diacord existing leg and right aR inbosrd fuel tranamitrun (Plh’ 531131211 II.ILI to Figllrr Il

7 and dl~nrd erIs(ing idt.nd right lomard autlunrd 11101 LranrmiUan tPIN 838373-11 tmler Lu FipM ii.

5. Remorr and dinurd (u)ldllp illel tank int´•rmnnat ~4 ad´•ple’ tP~ 830117´•51 and rsl´•W harduard trolw to

AgunSI.

9. Runova and dluud uhtinl IeR inboa´•d all NIIIP IUeI CoI) iWN BSOSOS-ll´• right inbonrd aft ´•unlp M loll tPIPI

690985-21. oni´•tin. gmmmcta and valve .ea.mbliar (Ph’ 690561´•9011 (rrl.r to Figure 2). Bump i\Iei

r.lls. Pnv RBOB93´•W11-M12 do Mt have to be removed.

NOZ5

RrBr 1.Ch.lua~ 28 o( the Airplane Maintenana ~u.ull rm

Rmavnl o(luol~dll.

to. Remove and di~rd erirting plupr 11~1! s´•0116-111~m laR and right loru´•ad in)a.rd LII nllr ImT´•r to Fieun 21.

L1. Rcmnv. and dix´•rd Lri´•ting tube aamb(ln IPm’ 690375-589. -585. -585. ´•587 and -5581. wrren uaemblin (Plh’

590(18-9 and ´•II and related to Figure 31.

NOTE

II is not Dla!´•anry to remove tuha..lamhlial P;S 8989)8-589.

.585. ´•1B(i. and ~n asremhiies pIF183Mltl´•3. -4 and related

hard*;areat this time however. there parts nholllcl he rc-

Il,uvad u~h.nav.r arI.rsr to the I~w´•rd inhanrd and nuthnard

assemblies P L ti)eSi6-IB?. ´•JI(B

and rrl*~rd ilntdl*ra murt he r*ll,av~d during this

Q 64~-´• h- AS

RET1..´•TP 4 j

(:I)SIOH l(lT NO- JZ

STEPS 6 AND 7 a~abd, n

O a

:i-

B

l_e

r,

EXISTING LEFI INSTALLnTIOFI SI-IOWN

EX IS TIN G R I G I-1T IN 5 TA LI.A T I O N O PPO SITE

r I

1:115 ITIM KJ’I NO. 132

SI’EPS 8. 9 AND 10

EXISTING RIGHT IMSTALLATIOH OPPOSI~E

EXISTING I.~FI INZTALLATION 4nOWRI

I‘-

´•-r

-~S a

~e

i. CVVLPI)

1( 2. I´•P151(A ROL~II

St~II. (iJU111´•l HOIE. LH

0*~a

II

5. 63Mll-ll H(lkE. RHe, owl ~s ne cLnmr. ou~au

I.NMII´•5*D/U´•IIRtJOm(-MI V~CVF I~FI

~5’I1.61UW~IIIN RIICONHECT12 ~IJr’lW CIIINNIL

I~ LIICONNICT

f:~ Ib.l;)(ll!Bl 1:(ILL CTLL. 1.11h)l\)llllllFI nI´•ll. Hn

R-b ASIC. S O(lli110~ :IVII((IR OI(I)MML:III-C(JT~ll(l!i IIIIOIICR (:HUMMET

III, nulunn il()L I

RE(:iil.i-i´• ~Y P~P .I*.n:?:ln WIISIEH

1?. -01161 PI illi 7 i\T(

cvsmhl KIT NO. 152

STEP 11

1. sJmlbscn rust nMa mseoz~s CLnUp

i. ~Nlm* BOLTANBWCIOLWI*WEA

6 6330178~511181 ~JY.LHmm16YC´• TUBE AIEY. AH

/BBIDln~WI´•Un.LnQ(UISML8 TUDL A6n. RH

>1

E

I,yr~,Z´•-\C~\j

4)

(3P

,i 8~r 15 NOT N(CF6SARY TO REI1IOVti

ITLMI i. 2.4 I)NO 6 UNI1L I\CCEII

EXISTING LEFT (NIWLIATION ZIIOWN(IUI’ROIRD CELLS II RE(IUIRBD:

EYI~TINO IPISIALIAIION OP)OIRE

CIIS’IDM ~aT NO. 131

12 in*tilll B~OlL7´•9 aulnpm. u*,mbly in(rr II n(lue II ´•nd 83041715 blue~ p.r (Illleprill 630117, nun(a 5. 6 ´•nd 7.

eB, I~ 6~0119-1( hr..l.l´•umhll. Cs.(l(llJ und. n´•uml,b and 83~411-1.lnll.

14. Inntall 830358 8llur bloeks and i-inch Valrro Pile pada mr r´•nt´•r wing fi~al coils nor hluepnnl 630958

16 IluUII hlSZL2R84h’gmmmstl parblurprint 630384.

NOTE

rrs MSI11BBBN rsplnca Le Nbkr gromm´•b that

wore remaWd in ~P O´•

Id in~nll MLi96UIB?1 LPOm*n´•( nor blueprintS30581, ulne 8.

17 Vlho.ump ~ual eJl. ware mmonnI ira~r La step 8), install 8S0998-M)L and 690303-502 sump i~d E.lla..nd 63051~-

I nnd R9a964´•W1 ~ucll cslla par blu3rln( 630384, Shco(2, 68Lhru 42.

HOIL

Ibtrr to Chrplsr 26 o~ L0 Al~lnnr MainPnNlcu Manu´•l BI

fn´•Ullntion alLel esllo.

Is. inNlfl 640978 830388 630416 valve alunnblies. p´•ske( and F~Oa216M

plate par bleop*lnt 630984 (rrl~ to Piauna 51,

ID. Install 830919-1 tuhr and AN~STPWS(I ellmp parhluqrinl 690381, ~ona 6 (r~r8r fa Ffpn: 51.

20. Install 6W~97680L. -803 and -W16 Cube urmblin. ANB:OID unions, 69011R1 rmn aremblin and 850(18~a3

.nd.a4 an81e na~mblies per biueorlnt 690418. Mnen 19 nlld 90 (rrTer to iFLguro 81.

21. 630372-501 (nntmilton linhon.d nnl and RI~P17S-MI Llnntmillen loutboyd (amald) per blusluint 690362

96441 S,~nea 4 th~u 3 (r~ar to FiRurs 61.

norE

A sdunnatic o(Ur oxtdndsd M n/nul,n it IlludraLsd in Fil-

urr 7.

22. Ibnuve nPhaletan su ncmauuy Login H*aa 10 ~Wn. tirl quantity monitors Uul are mounted on tba

21. Ranuva md dlsOud ~Wns lird quan(ifdt m0nl(orn~m Fillurr 41.

24. I~utslll 830989-808 luel OurnlilY monitor (P plsco´•) nor bluo~rlo( 800708

26. Relostali r0caudamon nn~nruinl.

28 f~(nd\ll nEFessdOora.

27. Rsin´•hll fue(tank aoeeuJoora.

28. InlUIII th*.ut out pnrtlnn of~ IIOLBJ´•BBII drsl on axllinll quanmnl console dacnl IrsOlo Fipln 6).

Rc~v(lr e.*t(ng Rrl tr.n´•rsr pumpB no’ Uu´•p’i"t 500679, Sh*ct 15.1 IRFFlninn A91

OR:’ "e As

~3, .i,oRECEIVi

q7

CVSglTnM l(lT NO. 152

c..ranr~.o6RIWHT

FUII CF;LL

eLeCFRIUILCONNECmRCL~M(´•

rPUEL INTEACONNECTVI\LYE

LIFT/I CENTER W1NO

PVELCeLL

OR’N"

d

4

Figur´•

90. Calibmt. lual 9uaotih system udng the wet method or the dn method. To c.llsm(s the Tuel luMtlN systemuulne the wet method. pmcaed an bll.wa:

Jack airplane in acmrdnno8 vlth ploeeduras outlined in Ch.ptar nrth. ~Lrplln. Mainlcnnna ~nudf, p*hing isleraplng (pllsLnml under tail rsctinr. ofelrplsne.

NOIB

Whun aidano is placed MLUL´• sad elaelnEal power i. Oh.,the h.urmlEter wfll np*mta. To pmvant operation at~hourme´•tar. trip the ap~mpri(o circuit breaker.

b.

M~d;lrplana, both h.ri~ntolly end lon~hldlnnlly,.´• aullincd la ChnpteT 8 Oltha i~irpl.ne L(olntnnnnEc

c. Oblain a m~ane b d.brmine the weight(ln naundH)ol the fuel put into and tnk.n out olthe.irplsw.

NOTE

Wright nTli~el added or t´•smuvsd .holl be accurals vilhint2.6 iba. Rm~rd q,lanrlty in pnunds. fuel *R,psro~urr indr(lrers hhrcnhal(, hnd epeelne gnvity olLsl used

En.u´•o(L* Tuclinl.runlul .slni.duad ~aR´•nllriUO(O1Ble- I;:iis\k ns

h´• irpnFolil ~tlnE oyy~*"dRECEIYEn aY MTP IOfuc.i for (Ipl´°"e irvlol (o Chapl;l 12 of the Aill,lp.~ ~*inlr

CIIS?DM KI’1‘ NO. 139

8RILIHTEENrER WINGFUEL CELL

VILVE

h~mM´•lLERCINIERW(N~FVELCELL

--P-

NYING n~ CHE(X

VNVE

c~JBPaTJ~W11601AFT INBOARDCELL

FWo FLEX TUQLINBOARD ~´•7clA i VPZr con~ulcron

CELL~--RZ// ITYPICALI

Oapr

wnaanD

VENT CELL

INTERCWNECTLINES

DLU*P NBE

CONNECTOI(

PWD

;NT.ACONNLCTLINI

LINE VENTLINL

NI~ILLE

FUELL FELL

Oarcl i ~L,LEFT INSTALLATION SI-(OWN

Lj IMIGHT INSTALLATION OPPOSITE

COS?DM ICITIIO. 191

~i69p~NEL IHEF)

O WMOV~ EXIPITIN(I NEL OUANTIN MJNlmA Ar‘.)

(NS+*LL (9~88605 PVIL QUnNnTY MDM1TOR

d

~f3

IlfiX1II3rZil

i ~7f i~/m´•

00(r7

~un EYISTINCI ~CREIH"’~’1 00 (HEF)

EX1S~T1NOOEW\L--IRLF) CUIOUT THAT WRTION

O, oe uEEn~*N ito,asaoAli aoanrro. AEMWEscnew 4ND SFCURE

CUTOUI POATION OF

DLC*L VSINO CONIACT

CEMINT.REINSTALL

___U~F..:.._..i scRla.

il-... ..-_...14

CIIS’R)M 107 NO. IS1

d ilrmova nl)er eRpa Bust linl( Ue~r nnd add 290 W.llun´• (194 lautldl ulB 1 ihrig.li arluo) to sach L´•nk.

lora

ITalrplanu fuel tnnka luva boom dmiMd n(bo~, unllubla end

undrainabla 0141 (6.2 pllans -3(.89 pounds st 6.1 IWnl),maurs UI´•l l.a.all.ns (8 peunde at 6.1 ibdbd) is added to

each tonk bdon add)ylaD ilallon. par LML

s´• Walt 15 Mnutn nnd drain W until 16 B.llan. (LO?.a lbsnt 6.7 ibsignl) pr tn,lk is ranlosd. Wait on addl-

GanJ 16 n(nute~ and eheck h.l indle´•lon Tor ism (0) indieotion 1+O. -5 ibn). Alu.l empty sdiuotment

KIOW on c0ntlol monitor boxn.nd rare the Twl quan~ty Lndlcawnl La Eara (a)(* 0, 6 iba) ii r4ulm3-

NOTE

Amount olruil romnining in ea.h Rrl tonk is equiv´•lcnt to

unlulable.nd undrplnsblo fual (5.2 plloas) per LanL.

I. FLU Unka to loll st top dnllcr nook (pdn(

NOTE

To nll wilt W1. nn ´•rers~c.lZ1’1.0 gnlbn. or 1681.0

polmds ollual (wLight o(kel 8.1 pounds per gallcn).

II´• ndjun lull ´•~iudmcnr wrow in mnMI monitor bores so (haL Tusl qusntl(y indicstors (ndicet+ or illsl

rddod (poulldn).

NOTE

During the allowing poowiuree. do not nske neuaunane of

Be amply or Tull ´•9iustmone sfrrv´• on Uls mnlml monitor

CnUTION

Do not ula ´•Irdulr bal boost prnp to drsin lusl fmm

´•irllDM´• Rcmmmend use ol*x(amdly pl~orrd pump to

prsvonI p~ibls d´•rnaRo to oirplans pump.

h. Drain tirsl i)om dthnr side, drainintl to on even (ncremnnt (i.n. 1687.8 dnin´•d to IWO). Continuo to d~h in

100 pounb inmaaentU raoFd(ng .Q111 iraibhsdrainad md (nnlcat~r raadinR´•.

NOTE

Plot Ura dllFnnMs between ladlsscor matinn nsirut notus(

Lsl pounds rsmo*ed on cnlibm(ion eh´•rt (rtBr to PiRura 91.

Lf the dil~rrnee between indlretor reedlnga and rclusl fuel

pound´• is greeter thou the i(n\la ntnblilhod M ~nlibr´•tinn

rberl. II is raoommcnded th´•t t´•nL be tilled end ml(bmlion

pmoadunn steMd Oom the beginning. ICarmr is indicltd

in uppr h.l(or H obert, ndju´•t U1o LII

mant serov in Control monitor bor M as to ´•Y´•IARB LhC

OR F (T1 n F d) L ,i. ´•hauld brios indr´•Ur (h limiu

oltba Lalibn~on rhm. LI the some indic´•tion aeun spin.

LL t,l !IYP B PU indirntr elsctric´•l wiring nr Can´•mlttsr )roba mal-

RECU\r~ tunaion. Iln(ore pmned(ns ~rUler, hadl uinn´• ~untinuih

end trannmitcar probs´•, rrpairing or rrpl´•ring os mluirad.n.pant nll ann dro)n pmrrdurm.

i. Drain Tual to level where ~uel low level w.minp light illuminntn. fitnp rcrurli.g Rnn racurd ilcuud welyhldroinEd and i,ldicp~,r reading.

NOTE

b ah.ll~ )sB puundl IraO Uund´• or anu.l 14

j to dcRcl until rl,lpy by rciulll iS 2 r.~n*ininl: In I.nL Ilnllrlil~:lhlr ~´•´•d ~louahlr hll´•l, ihr

indi~.lor rcadinl:!:l1.111 lil´• III I II

(:IIS1UI( K17 NO 131:

)I)LL ru~u

3:iiUto ~Iz I :i.

oI :::I i:

oul i:i1; i

8

g

liii

rit iii::

iliii illii

o:

I~o i ~i´• ~t-

ACTUAL FUEL POUNDSla0(t~olb) ~snai

R(lun O.

NOtL

R.xuru th´•~ Uc indi~ator rn,din~.re within La

oul)ilud in rtop i..nd It Ilo~ rap*l 611 .nd dtrin pmne

dun~ u.Lrl indiulor laadinp on v((hin lallral~ce

L Alid lu,pn~nd´• ~hd t.the tide Q´•t hn betn ulibr´•Ud

HOT´•

.nlc ndditio. al hlol vill nlin~li.h c)lr low irvrl ualnisl

lila. ,1L AsH~L atcp´• h. (hnlj LI th~ clllllr ~!d´•

(31~r\kt´•´•‘

tn. H..(wl.irplnnr.´• ~ullilled in n,.pler I% ´•ITDle Mntl~tmn*oo L(;~nu*l. RECEIV~o BY ATPQ

11 nirpl;lnn rrunl I;I’L1; x´•i.ullillt.n il,l.l.;ll,(.rr I ol 11,1´• hirl.l;ln~. M:lll~l´•iiililll´• hllllll.l.

I.. I(( (111 1/111111 illr:llnr \1)II.II ;´•ilJI!´•´•ll 11 (11)1)11 1:111111)11

C(IO’1´•OM KII’ NO. 1]2

1, Il)ry Melhudl. (H*lrr y Pil.l~!a 1U d II) Turulibr´•t~cUlekol 9Y""Llly ay

wm, ymroed u* lullu~.

(11 Test Gcluipnlen~ The Bllmuil~ itellu .IlasltpuipnPnl art rcqulrrd when tasting or dallbra(ln(l tho Tuel gual

Uly syslcm and its eonlpananta:

(sl Pu* pur.lW Tcsi Sat- GTli-l or GTF-a 4 Gull Airhorno LNwman~. Inc.),or s~uivelenl

(bl Calibration harneasoa

Ici 28 vdo ne plwcr supply

NO~t:

The *a may ha shop bhrluted in aa~ord´•ncl with

illustrations in Fylra 12.

(2) (IloRr to Pipuma 11612~ To

pralorman as rosovr:

I´•~ nl´•mnn~.irpl.na hirna Tmm Uu,lan mntml mon)(ol lo~ anJ the h*mak

(bl Cnnnnct Coax hand irona mnLlol monitor has to eoa. urnln´•l (261 .f MDICATOR ´•´•~ion an DTP~B (taat

´•9ulpmo~O-

(r) CMNet aoax A isa´•l from ulrplnn´• uirinp to co~. A t´•rminal (21) ol*IRCiAPP TI\NK UWPIS udlol on

DTP-Z((ssta(u(pmcno.

(d~ CMM* UN911 land liom mnLlol mmli(m ban to Uh´•SH Larndn´•I (281 ol INDICAmR IHtion on GL1U

(Ms~uipmenl).

~S1CcaMfl. UWH B land fmn ´•trplsM ~irillp 14 UNSH B annln.l (12) oTAtRCR~FT TANE UNITS racUa,

on OTF´•a (Lartcquipmsnt)´•

WOTC:

Ensure that eovor on Lha roccpt.rle INDICATOR

COfrIP 1241 is inutnllcd The proter*lm mrar hns a nonnledpin ´•rbim ipaund( the unuead ampansncl,. ´•rrtioll to din(-

nptaany etmy PIJIYP "h" not in Ene.

(II Sd D18RAY rwitch (9) to IIES tM&01 position nnd sat RANGE tMBQI avitrh ~1SI to lW-Kpaaitioo.

(B) SdR&SLSTAN~E FUNCRDN sr)tsh 11211a A;B lai(ion nnd than to AOND paitla.

nora

Ro.dinn~.n dlgltnl O(lplay ´•houm not ha (eee th;ln IW

msgahms

(hl 9ct CAPADI~ANCE YUN~ION sd~h (2) to NC TE8T ZNSH ~lriliun on ant DISI’W\Y SglleCT swlloh

(81 to CAP (PFI pmtloo.

HQTn

Digital airpl.r (8) should (nd(cpU latcrrn M W pl and 88.88

p~

(il Apply 28 vn116 DC p~war to Tucl quantity

01 Sat (:APACl.PANCE FI1WCnON ´•uillh 12) to SL~N SET )’)(OUI~ ju,´•.rion anil ´•djul SI~UIJI10)( tPR

~ROR6 nno .djualmmnttonn.rol 1151 nlld rut didul diapl´•~ B,r C*).( D~

t;s´•i L. ns 17

rF

(:USTOM KI‘P NO. 13P

tF~warrnao

I´•UIL (IAVOIHO

FUEL e~Y

PROBES

Xv 14200

wer wlNo aurso

-xnl~l.w

ruc~anvolNunAHNESLDUTBD

FOELeELLOIWINO

I1*RNEBII INBO

FL~L D(IELLO

IYETWINO INBD OcoNNecraR

nrrrsrssunfceara~rvlaaFUEL

-GCELL IN80

MNNECtOn

FUEL O*UalN(IH*RNETtCENTII(

6

~q !7

C’UG~DM t(IT NO. IPZ

I I

OwvkelrAm:r RELilliTANCE

i,,,Ynoa CJ I C1II*~ I rnaCno*

IVX S(MULAmRO IPF)

Il~x´• F(mER

WII( C~*l U*YII CO*I P~ac cl*x clI u*n*r eo~´• CDvE

Battnn

1_ AS

TFSI SE~ 6$s

RECE~IEU BY W~ P Fieu´•a n.

ILI Jrsk rirplan~´•in amordanea viL pmeedurrs outlinad in Chnpta. 1 ol the Ai~plnne Mainbnanm Manual,placin6 tsluroeing La)latand under tail aobi.o oEairplane

nOre

When airplane isplsnd on ICCL4 and sleQTcal porer is ON,the hounnelar will npnDde. T. prsvanl o~sratia. dhourmc´•tar,tllp Us appmprlste olrrult breaker.

0) Ia,velnirplano, buW1 huriwnWlly and lunyihldinally, nn.uUinad in Chantor 6 at tbs Ai~nlnna h(nintonanreManual.

rml Rcmn~s nllsra~pa bum winl tanks and add 20.0 ilnll.na (1SI plunds at 6.7 ibs/ljsl) allilal B a´•ch tank.

HO+B

IT ~lrphne Lnl tanks have been drained or hath unllsable andundrsin~blsrua) (6.9snI)au -5(.84 pMmd´•ntS.7 ibsipnl),ansoro Uat 1.1 galIe,(a 01 pounds at 8.1 IhslOaIl is added W

eseh mnk haare addlnl! 80 gslLna ~BI tank.

(nl ~dt 16 minuter and drain RrLI Ilnitl IR 8aIIons(lO?.a ihn at. R.? IhUgall lur IRd is ranluvad W.L an

additional 15 tnino(os and theek lupl indicators (or ~m (01 indiwliun(+0. -6 ib.l Adjnn( cmp~ .diull-men~ on control monitor bolar and rcro Uc Lrl qurntily indientnra to u:m (O) (+O, -6 ib´•l ii nt-

~Yiird 6Here

i~,nnunl.( nl*I ~,IIRillinb ill ulnk is clui~aluoc I, Ilnu*.bls ~2.0*´•a IIL~J (i?l!.~llmX)

F’

CUR’POM KI~P NO. IJ1.

reor~drarra

yl*aa~M1 ymna*ru*ln~O 000

RO-5(IUCOAX25110N(1

;~u INcrualNomaaEctoR

9 fl f tim~RnANEWIR1NC

HI\RNE~S; M~Otdlt-IWPER MIL´•WQO~ DR HIIDU~OBPIR h(lLrrBIDL~ ~IPrRnX 26*´•’ L(I.

86M)IXNnIh~OP

OONNecmR

0 P

E E

It It

H H

roooNnia AlronlR*LaNEMONITOR ~IIUNB

B~

~1 1, ~C3B2RBNE/i´• o

UNSHO

h,KoabrPsm:

~ca4czlRNe

00NNECtOn OONNECIOR

CONNECTOR

%k nsFieur´• 12 i-0

Ht~

(0) CAPACITANCR FVNCTION muitch (8) to IND T~8T A~posl(icm.

Ip) ~iUIIIL EMI?´•Y pnrm~l.metar an control inon(tar box for O Ibu: indlr~tlan on (uJ quatlry indicator, for ion

fbeltank, locaccn a yudastlt mnMI penal.

(yl Set Ch~hCITnNCE PONCTION Nribh ca, to INT’12ST nC rrtoee yl.u imrl~ion.

rr) Adlnat the PULL poten(i.mltsr an ~untrol mol´•itol b.r Tar fWn ILa indicrtian on fuCI yu.n(iB indie.lor.

far ioftlunt Lnnk.

(a~ RPPClr atnps to) thru bl us(il no funhor adjurtnlcl,lr are mluirnd

QiP n,, *I lh, ul.~ .I.,. 1.,1 lh, at ru, laollr e,~

52 Ilrin.LIII llllIloIPlery- 2´•\ 17

33. I(n:lsl´•~ Lllcl´•o ~rr s~l il´•;lk i ill 1)11´• Ri.´•l :´•~:lr´•li

CUS~POM KI’P NO. 161

HEmn*a nllplo"e rmmjnckl or aullinud *I Ch*pbr ul L)Ia A(rpl.ne Mnlnlannreo Mn.uol.

IICCRICI~ LOla

WBOH~ I\NO BALINCE: nM w*pbt snd b´•lma cha~y n~qulnd du+ (D (ns(allst(~l orthi´• Cu~m Kit at Dllau~:

WEI(IHTO;BS) H´•ARMtINCWF~O HMOMENTLW-LBSI+98.*0 +216.85 85118

8PARE8 AFFECTEO: NO

PURLICI\T1ON *FPECrET): ThL M~del B9OC nnd 896 nirplnn. Mlintsnan~e Mnnual. and Ls g9UC1696 illuat.s*dPart´• Cnlab. ch´•nlel mlulml by thlr documsne uill be (nmrpor´•Ud st Wlb na.L abrlulcd nvi´•ion.

ACKIRD COM~UANCB: MaLa an ´•pp~pr(´•U entry in ´•irpl´•n. Minm.nse rrcord. u T.lla´•n;: Cuacor. Kit Na.166. dlW 2 M~rch tO9L. ~nn8´•d "enended Rnd (lyalen, Modltlcall.o RLt´•.

f) 6a i G i Al, As

RECEIVED BY aTPZ Z

~IICulfstreamAmerican

coal*,u*noa

ComMndw Divilion

6WI North RIX;*UII ~´•nYI.8´•m~ny. OLI´•honu 75001

CUSTOM KIT NO. 133 15 SEPTEMBER 1981

Update Your Commander Jetprop NOW With

An Improved Side Window Defog System

a Utilizes Conditioned Air To Prevent Pilot and Copilot Side

Window From Fogging.

a Provides Pilot and Copilot Removable Inner Windows Which

Eliminate Cold Air On The Crew’s Shoulder.

Etfeotlvlty: Nit No. 1 ModeIe 6801 end 6908, 8eriai Noe. 11288 Thru H586.

Nit No. 2 Model 600C (8lpht Porty), 8´•rl´•I No´•. 11800 Thru HBJO end Model 695

(Nlne Eighty), serial Not. 91000 Thru 85040 Not Equipped With Pilot

end Copilot Inner Wlndowe.

Nit No. 3 Model 88(IC (Elpht Porty), 8erlei Noe. 11600 Thru 11(60 end Model 685

(Nlne Eighty), 8´•rlal Noe. 96008 Thru 86010 EquippedWith Pilot end

Copilot Inner Wlndowe

Old´•r thl´• kit org6t tuN d´•NIII´• Imm your ns´•n´•1 Oun´•lnem Commender ServlCen(sr

Prloe: Kit No. 1 -)828.L18, pine in~tallltlon.

Kit No. 2 Y38.43.~plu´• Inetellatlon.

Kit No. 3 -8321.34, plue In´•tall*lon.

-I

GubtreamAmericancoawa*~lo*

)W1 Norm Raxnll

B´•mlny. O*l´•honu IJW8

CUSTOM KIT NO. 133

15 September 1881

IMPROVED SIDE WINDOW DEFOO SYSTEM

MODELS AFFECTED: MODELS 690A AND 6908, SERIAL NOS. 11269 THRU 11566, MODEL B9OC. SERIAL NOS.

11600 THRU 11650 AND MODEL 695, SERIAL NOS. 95W0 THRU 96040.

REASON FOR PUsLICATION: TO PROVIDE IMPROVED SIDE WINDOW DEFOO CAPABILITY


wore


INSTALLING THIS CUSTOM KIT, CONTACT YOUR

NEAREST DULFSTREAM COMMANDER AUTHORIZED

SERVICENTER.

sY WnOM WORK WILL BE ACCOMPLI.HED: A Bi P MECHANIC OR E9UIVALENT.


ESTIMATEO MAN nOURS: KIT NO. 1 TWENTY (20) HOURS.

KIT NO. 2 SIXTEEN (18) HOURS.

KIT NO. 3 FIFI~EEN (15) HOURS.

PARTS DATA: PARTS REQUIRED FOR INSTALLATION OF THIS CUSTOM KIT MAY BE PROCURED THROUGH

YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KIT NO. 1 5828.86: KIT

NO. 2 -8438.43 KIT NO. S 9321.34. REFERENCE THIS CUSTOM KIT, AIRCRAFI~ MODEL AND FACTORY

SERIAL NUMsdR WHEN ORDERIND CUSTOM KIT NO. 139 CONSISTING OF THE FOLLOWIND:

Kit No. 1 Models 6BoA and 690B.

Kit No. 2 Models 690C and 696 not equipped with pilot and copilot inner windows.

Kit No. 9 Medals 690C and 896 Equipped with pilot and copilot inner windows.

Kit Kit Kit

No. 1 No. Z No. 3

~TY qTY 9TY PART NO. DESCRIPTION

1 ea. 1 se. 1 se. 510390-81 Channel

1 ea. 1 ea. 1 ea. 310380-82 Channel

2%s. 8818046 Bumper1 ea. 862058-451 Frame Assy1 ea. 882058´•462 Rama Assy1 ea. 1 ea. 862058-3 Inner Window

1 ea. 1 ea. 862058-4 InnerWindow

2 as. 8880585 Escutehaon

2 as. 2 ea. 2sa. 880183-39 Nipple Assyt as. 1 se, f se. 880616´•1 Plenum Assy1 os. 1 se. 1 se. 880816-2 Plenum Assy1 se. 1 ea 1 ea. 880616-1 Tube Assy1 as. 1 se. 1 ea. 880816-2 Tube Assy2 os. 2 ea. 2 ea. 8808801 Tubs Plug

1 se. ADSIABS Pop Rivet

ppe0ldla

CUSTOM KIT NO. 191

RIGHT INSTALLATION SHOWN


roplLon

9106 WINDOW

3~IREF)

64 i´• EXISTINGHARDWARE

1(REF)

I ~i,.INTERIOR

9106 PANEL

IRE FL

EXISTING 898869-1

HEATER AsSY

(REF)

EXISTING 8W)575´•2EXISTING W7Slm08 C#IX PLENUM 1\8SY

CLAMPS rPLB y IREF)(REF)

EXISTING 980676681

DUCT ASSY

(REF)

ELECTRICAL WIRING

u,,,,,,, i i EXISTINGNTa34´•(1 HOSE HARDWARE(REFL

MODEL 6908 SERIAL NOS.

(1617 THRU 11888 AND

dMODELS Bsoc AND 896

EX(mN01N757TW48CLAMP12PLI)

IREF! /V ‘EXISTIN.880676´•2 PLENVM ASSY

(REF1

EXISTING

9906781 DUCT ASSY

IREF)

EXISTINGNT30Cn HOSE

IREFI

MODEUI~90A AND 6808 FILn i.SERIAL N09. 11298 THRU 1(818

ppgs 2 of 12

CU8TDM KIT NO. 133

4 as. 4es. 4 ea. AN860D6 Washer

2 ea. 2 as. 2 ea. AN737TW46 Clamp4 ea. 4es. tea. MS21042L06 Nut

4 ea. 4ea. MS21180-A26 Rivnut

4 se. 4ea. 4 ea. MSSS206-228 &rew3 ea. B ea. 8 ea. HL86-5 Collar

6 se. 6ea. 6 ea. HL2[1-6-4 Pin

2ea. 2 ea. 2 ea HLPO-S-S Pin

2 ea. Z ea. 2 ea NT3S-4-11 Hose

2sa. 2 ea. 2 ea. NW2W28-4-68-6 Duct

4 ea. 4 se. TFP-1006 (Itud

4aa. 4 ea. TFS-1OB Button

1 ea. 1 ea. 1 ea. Compliance Card

1 ea. 1 ea. 1 ea. Custom Kit No. 133 Instructions

SPECIALTOOLS: RIVNUTPULLER.

C.CCOMPLISHYENT INSTRUCT)ONS:

i. Remove pilot’s seat, WPiJO~B Beat and ham from the airplane. It may be neoessary to remove the levetory seat.

2. Remove leR and right ca;~pit interior side panels and sound proofmg to gain access to pilot and copilot side window

defog system.

3. Remove interior window frames from pilot and copilot aide windows.

4. On Models 680A and 6g0B, serial numbers 11289 thru 11616, proceed as follows (lafer to Figure 1):

i a. Remove end discard existing leR and right hoses (P~ NTS3-4-21).

NOTE

Retain existing clamps (Pn~ AN?9?TU016) for later

installation at step 1S, or step 14.

b. Remove and discard existing leR and right duet sssembliea (P/N 880616-1) and plug duet attaching holes (2

places) with MS20410AD4 rivets.

c. Remove and discard existing lan plenum assembly (P~ 880515-1) and right plenum assembly (P~ 880515-2).

NOTE

Retain Plenum assembly attaching hardware for new plenumassembly installation at step 12.


5. On Model 880B, serial numbers 11611 thru 11686 end Models 680C and 685, proceed as follows (refer to Figure 1):

a. Remove and discard existing left and right hoses (Pn~ NTS3-411).

NOTE

Retain existing clamps (Pn~ AN?S?TW48) for laterinstallation at step iS. or step 14.

b. Remove and discard existing heater assemblies (P~ 880662-1).

Page 3 of la

KIT NO. 1SS

0.128" DIA. HOLE

(I PLS)1.OB" DIA. HOLE

lb0" DIA.

TYPLI

B.2a´•´•1

ExisnNo INTEncosmLIREF)

88019359 NIPPLE ~S8Y

N~S113B82 BLIND

RIVET. UPLS)

PR12Z1 TYPE ´•´•B" OR

ATY 183 GEALANT BETWEEN

NIPPLE ASSY AND INTERCOSTAL

coplLora aln

VALVE IREF)

AlR BOX AS(rY

IREFI

L´•--~.6

8TA\ I 8T"

23.50VIEW LOOKING OVTBD

RIGHT INSTALLATION SHOWN

LEFT INSTALLAIION OPPOSITE

Fkura 2.

Pass 1 01 12

CUWOM KfT NO. 195

c. Assure that wire ends are individually capped, coiled and secured.

d. Remove and discard existing lan and right duet assemblies (PIN 880516-501) and plug duct attaching holes (2places) with MS1OI?0ADI rivets.

e. Remove and discard existing left plenum assembly (P~ 880575-1) and right plenum assembly (Pn~ 880575-21.

NOTE

Retain plenum assembly attaching hardware for new plenumassembly installation at step 12.

f Remove interior upholstery fiom aft pressure bulkhead to expose terminal board located on right side ofbulkhead.

8´• On Model 690B, remove fuse "F33" and on Models 690C and 685, remove fuse "F24".

h. Proceed to step 6.

6. Cut a 1.06 inch diameter hole in existing leR and light intereostals (refer to Figure 2).

NOTE

Intereostals are located on top of pilot’s and copilot’s sir boxassemblies.

7. laeate and drill 0.128 inch diameter hole (4 places) in left and right intermstale for installation of 880183-39 nippleassembly (refer to Figure 2).

8. Install 880183-39 nipple assembly on left and right interoostals using NA81198B2 blind rivets. Seal betweenintermstal and nipple assembly with PR 1221 Type "B" sealant or RTV 182 sealant (refer to Figure 2).

9. Remove rivets as necessary to nest 310590-81 and -82 channels in existing left and right frames at fuselage station37.00. Using 51038081 and -82 channels as templates, merit 1.03 inch diameter hales on leR and light framesand drill eight (8) attaching holes using a No. 50 drill bit. Remove Ohannels and out 1.03 inch diameter holes inframes (refer to Figure 3).

10. Install 910590´•81 channel on left tiame and 110880-82 channel on right fiame st station 31.00 using rivets, Hi-Lok

pine and collars. 8eal coat outboard Range of channels prior to nestling in frame and seal around channels, framesand rivete per sealing procedures outlined in the appliosble Maintenance Manual (rsfer to Figure 3).

11 Drill and install 880876-1 tube assembly on left frame end 880618-a tube assembly on right frame at station 31.00

using screws, washers and nuts (refer to Figure 4).

12. Install 880516-1 plenum assembly on pilot’s aide Rod 8806162 plenum assembly on copilots side using existingscrews, washers and nuts. 8eal around Range of plenum assembly with PR 1221 Type "B" sealant or RTY 162sealant (refer to Figure 4).

13. Install NW2WZS´•4-Bg6 duct using existing or new AN?9?TW46 clamp (2 places) (refer a Figure 4).

14. At left and right fuselage station 25.50, where existing duct runs through Rama, install NT33-4-l1 hose and880680-1 tube plug on existing duct using existing or new AN?3?TW46 clamp (2 places) (refer to Figure 4).

NOTE

Install hose between 880680-1 tube plug and existing duct

through f~ame.

15. Assure that defog system is functioning properly and no leaks are evident.

16. Reinstall existingsoundpmoSng material.

I?. Far Models BBOA and 690B, proceed to step 20.

Page 5 of 19

CU8TOkl X~T NO. 199

RIO HT INSTALLATION SHOW N


21.60

STA31.00

EXTERIOR SKINIRE Fl

EXlsTIN(I (IUSSET mszt~,aaoa RIVETSIREFI

_ THRU 83IN AND FRAME

DEAL PER MAINTENANCE0.18W´•´•10.1825’´• DIA. HOLE -1\ a ,MlvrunLI

HL2089 rlN

HLBB6 COLLAR

f

~.60´•´•

0.1(100"10.(826" DIA. HOLEnL20M PIN iW

HLB85 COLLAR m\ ~L APPLY 8E~LI\NT TO OUTED

t FLANOE OF CHANNEL PRIOR

TO IN8TALLINO IPER SEALINGPROCEDURES OUTLINED IN

AIRPLANE MAINTENANCE MANUALL.

t 1.03" DIAHOLE

MS2010AD4

RIVET 18 PLS)

31098082CHANNEL

VIEW LOOKING FWD AT

FRAME STA. 37.00

npas.

Pnga 9 ol 12

CU8TOM KIT NO. 1SS

880575´•2 PLENUM nsSYSEAL ALL AROUND

WITH PRlnl TYPE "8’~

OR RTV 182 SE~LPINT87/12S.M)

EXISTING DUCTNTU´•4´•II HOSE AIREFL

880(180-1PLUD

EXISTING HARDWARE(REFL

8808~8´•2

TUBE ASSY

srA\ Ism87.001 \52.67

RIGHT INSTALLATION SHOWNMN137TWOB CLAMP

(2 LEFT INSTALLATION OPPOSITENwzw2ssaaa

DUCT AFTER CHANGEAJR BOX ASSY

IREFIVIEW LOOKING OUTBOARD

PIT RlOnT SIDE

B(M8DB2 CHANNEL

(REF)8197"m.l52" DIA. HOLE

MS(52W´•228 8CREW

IN9BOW WASHERM8210~2LOB NUT

.PLSL

8808782 TUBE

f nssv inen

B

VIEW A-A

Fl~ula 4.

P~e? a) 12

CUSTOM KIT NO´• 133

Is. For Models 690C and 895 equipped with factory installed inner windows, reinstall elisting window frames and

inner windows and proceed to step 21

19. For Models 890C and 686 not equipped with factory installed inner windows, modify existing left and right window

frames by installing inner windows as follows (refer to Figure 5):

a Position 862058-3 left inner window and 862058-4 right inner window frames and scribe lines for 0.40-inch

wide by 6.20-inches long slot in tap of framee.

NOTE

Spot laced area on lower holes of inner window should be

positioned on the outboard side (toward outer window).

b. Cut 0.40-inch wide by B.20-inches long slot in top of window frames.

c. Install 862058´•6 escutcheon on window frame using AD34ABS pop rivet (1 places) and EC1403 or an

equivalent contact cement.

d. Install existing left and right modified window frames on airplane using existing hardware.

a. Position 862068-3 left inner window and 862058-4 right inner window in existing window frames and mark

center of lower holes in inner windows on window frames for inetallation of MS27130-A25 rivnuts.

f Drill 0.253 (t0.003) inch diameter holes, marked in step e., in lower corners of window frames and install

MS27130-A25 rivnut (2 places).

g install TFP-1006dudin rivnuts

h. Unscrew net portion of TFS106 button and install button (2 places) on inner windows.

i. Install innerwindows inwindowframes.

i. Proceedto step 21

20 On Models BgOA and B90B, proceed as follows:

a. Rim and fit, as required, 882068-451 and 862058-452 frame assemblies on airplane (refer to Figure 6)

NOTE

Usa existing frame assemblies as models for trimming and

fitting new Rsme assemblies.

b. Install 861904-6 bumper on 862058-451 and 882068-462 frame assemblies using EC1403 or an equivalentcontact cement (refer to Figure 6).

c install 862068-461 and 862088452 frame assemblies on airplane picking up existing attach points and usingexisting hardware. Assure that 880515-1 and 880616-2 plenum assembly outlets are not restricted or covered

by installation of frame assemblies.

d. Position 862068-5 left inner window and 862058-4 right inner window in new window frames and mark center

of lower holes of inner windows on window frames for installation of MS27130-A25 rirnuts (refer to Figure 5).

a. Drill 0.259 (+0.00S) inch diameter holes, marked in step d., in lower corners of window frames and install

MS21130A25 rivnut (2 places) (refer to Figure 5).

f Install TFP-100Bstud inriMute(rsfertoFigure 5).

g. Unscrew net portion of TFS-1OB button and install button (2 places) on inner windows. (refer to Figure 6).

b. Install inner windows in window frames (refer to Figure 6).

Page 8 of 12

CU8TOM KIT NO. 1.88

VIEW LOOKING OUTED AT LEFT SIDE0820686 ESCUTCHEON

RIGHT SIDE OPPOSITE

AD3UI8s POP RIVET

BBMS8´•J INNERWINDOW

MIRRI CENTER OF INNER WINDOW

ON FRAME ASSY (2 PLS1

A

A

882088481 FRAME

0.280"/0.268" olA. HOLE new (REF)

MSnlS~A28 RIVNUTSTUD

12 PLS) 862058´•3 INNER

WINDOW IREF)

TFS1L~ BUTTON

Ba~soob BUMPER rVli~llL, ~12 PLS)

OUTER WINDOW IREF)

882068451

FRAME ASSY (REF)

-18.00

A-A

FCn 6. IRrt 1 ot 2)

Page 8 ol 12

CUGITOM KIT NO. ISS

881801´•5 BVMPER

INSTALLS ON FLPIN(IE OF

FRAME PIS?IY IALL AROUNDIWITH ECUO~ OR AN

EaUIVALENT CONTACT

CEMENT

E~rmBUMPER SHOULD 6EI\L

AGAINST WINDOW

WHEN INSTALLED

PICK VP ALL

EXISTING ATTACHPOINTS

TRIM EXCESS MATERIAL FROM

mts FLAN(IE (ILlL AROUND)FOR PROPER FIT pg REOUIRED

882058462 FRAME ASSY ISIIOWNI882058451 FRAME ASSY IOPPOSITEI

ACn B.

Psge H ol I2

CU8TOM KIT NO. 133

21. Reinstall interior side panels.

22. Reinstall pilot and copilot seats and bars and iavatory seat (if removedi.

23. Fill outandlllail ComplianceCard.

ELECTRICAL LOAD: Models 690A and 690B, Serial Numbers 11269 thru 11516 -NoChange. Model 690B, Serial

Number. 11517 thru 11566 and Models 680C and 695 Reduced by 10 Amps.



PUBUCATIONS AFFECTED: The Pilot’s Operating Handbook, Airplane Maintenance Manual and illustrated Parts

Catalog changes requiredby this document will be incoporated at the nert scheduled revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No

183, dated 15 September 1981, entitled "lmproved Side Window Defeg System", accomplished (date)

Page 12 of 12

Culfst~amAmericanCORPOR*TIDN

ConMndn Md~n

M~I Norm Awnu´•.t~mlny. MI´•hw 13008

CUSTOM KIT NO. 134 11 JANUARY 1982

IMPROVED INLET AIR SUPPLY SYSTEM FOR YOUR

IETPROP ENVIRONMENTAL CONTROL UNIT.

C

Improves Efficiency Of Environmental Control Unit By

Ducting Only Outside Air Across Heat Exchanger.

EFFECTIVITY:

MODEL 880C (EIOHT FORTY), SERIAL NOS. 11800 THRU 11718

MODEL095 (NINE EIGHTY), SERIAL NUMBERB 95000THRU85086

Order thle kit from your nearest Oul(atream Commander Authorl~ed ServlCenter

Prlee: 8187.82, plus in~tsllatlon

~3"11GulfstreamAmerican

coaPon*TloN

Commanda Mrl~aSW1 North Ratwall Auenua,Bamany, OLlahoma 13W8

CUSTOMKITNO.1SI

11Januarylss2

IMPROVED INLET AIR SUPPLY FOR ENVIRONMENTAL CONTROL UNIT

MODELI*FFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11118 AND MODEL 695, SERIAL NOS. 95000 THRU

95086.

REASON FOR PUBLICPIT(ON: TO IMPROVE EFFICIENCY OF ENVIRONMENTAL CONTROL UNIT (ECU) BY

DUCTWGONLY OUTSIDE AIRACROSEL HEATTXCCANNEER

COMPLI*NCE: ATOWNERDISCRETION.

NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILE INSTAL-

LlNG THIS CUSTOM KIT, CONTACT YOUR NEAREST

GULFSTREAM COMMANDER AUTHORIZED SERVI-

CENTER.

BY WHOM WORK WILL BE PICCOMPLISHED: A&PMECHANICOREQUIVALENT.

APPROVAL: FAADOASW-BAPPROVED.

ESTIM*T.DM**.OUR.: SEVEN(1)HOUAS

FARTSDATA: PARTSRE9UIRED TO INSTALL THIS CUSTOM KIT MAY BE PROCUREDTHROUDH YOURNEAR-

EST GULFSTREAM COMMANDER AUTHORIZED SERV1CENTER FOR 818?.62. REFERENCE THIS CUSTOM KIT,AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING CUSTOM KIT NO. 134 CONSISTING OF

THEFOLLOWING:

QTY PARTNO DESCRIPTION

tea. 310968-A3 GrillAssylea 880682-3 ClosureAssytea. 880682-1 ShroudAssytea. 880682-15 Angletea. 880682´•19 SealAssy8ea. AN9-3A Bolt

32ea. CR9248-4-3 Rivet

8ea. ANS60D10L Washer

2ea. MS21042L3 Nut

lea. ComplianeeCardLee. CustomKitNolS4 InstNotions

SPECIALTOOLS: NONE.

ACCOMPLISHMENTINSTRUCTIONS:

1. Ren~ve loweraftfuaalage aecessdoorto gainaccessto EnvimmentalControl Unit (ECU).

2. Remove baggage eompartment liner, as necessary, to facilitate inatellation of 880682-3 closure assemhly on ECU

heatexchanger.

Page IdS

CUSTOM KIT NO, 194

S. Remove and discard existing ECU air intake grill assembly that is located on right side of fuselage just aR of

station 290.0.

4. Enlarge existing cutout in fuselage skin and drill holes for installation of 310966-AS grill assembly (refer to

Figure i).

NOTE

Use 310966-A3 grill assembly as template to locate cutout.

5. Remove two (2) screws from top of heat Exchanger that secure pressure switch and tube assembly to heat

exchanger.

6. Temporarily install 880682-3 closure assembly on ECUheat exchanger picking up two (2) existing holes on topof heat exchanger and using existing hardware (refer to Figure a).

NOTE

If holes in 880682-3 closure assembly do not match holes in

heat exchanger, it may be necessary to drill new holes. Assure

that proper edge distance is maintained.

7. Temporally install 880682-7 shroud assembly on 880882-3 closure assembly with AN3´•3A bolt (2 places) and

AN960D10L washer (2 places) (refer to Figure 2).

8. Temporarily install 880682-15 angle using ANI-BA bolt (4 places) and ANSB0D10L washer (4 places) and assure

of proper alignment of assemblies (refer to Figure 2).

9. Drill two (2) 0.199 inch to 0.204 inch diameter holes in heat exchanger to match two (2) lower holes in 880681-3

doauraasarmbly(r~LrtonWre21

10. Remove 880682-15 angle, 880682-1 shroud assembly and 880682-3 closure assembly.

11. Install 880882-19 seel assembly on fuselage frame at station 280.0 using EC140S or an equivalent contact

cement (refer to FiBure a).

12. Install 880682-3 closure assembly on ECU heat exchanger using existing hardware, AN3-3A bolt (2 places),AN9B0D1OL washer (2 places) and MS21042L3 nut (2 places) (refer to Figure 2).

13. Install 880682-1 shroud assembly on 880682-5 closure assembly using AN3-3A bolt (2 places) and AN960D10L

washer (2 places) (refer to Figure 2).

14. Install 880682-16 angle using AN3-3A bolt (4 places) and AN960D10L washer (4 places) (refer to Figure 2).

15. Clean 880682-1 shroud assembly, fuselage skin and lonpmns in area of shroud assembly, in preparation for

sealing, in accordance with procedures outlined in Chapter 20 oPAirplane Maintenance Manual.

NOTE

pay particular attention to the WARNING with regards to

use of solvents.

16. Seal around longemns and 880682-1 assembly with Pro-Seal 700 or equivalent sealant in accordance with

procedures outlined in Chapter 20 of the Airplane Maintenance Manual (refer to Figure 2).

17. install 310968A3 grill assembly on fuselage skin using (3B2248-4-3 blind rivet (80 places) (refer to Figure 1).


19. Reinstall lower alt fuselage access door.

to Ca,

Pasezats

CU8TOM KIT NO. 134

B

00

29412

1.67"

IIOB1~B/U(IRILL ~8SY I I FUSELA(IE SKIN (REF1

FI+ t +~;tLi

_t_--- E AlR INTAKE

DASH LINE INDICATESt +-+++t-"’

PIFT END OF ORIOIN~L

CUTOUT

FUSEL~(IE SKIN IREF). ~C L 0´•ZBI IPIP)

CR22484J BLIND RIVET

(SOPLI1VIEW LOOKING OUTED

AT RIGHT SIDE

nosaa´•A3aRILL

IREF)

VIEW CC

ngun i.

Pnee S of 5

CUSTOM KIT NO. 134

~oso

NO. BLON(IERON

IREFI880882´•7 SHROUD I\S6Y

.U~LaoE.K1W amaa~s*NaLL

ANIJABOLTANBBODIOLWASHER

880682´•7 1 X R (4 PL9SHROUDASSY

1 nN33nsoLI

(RlFI 0.188’´•10´•2~´•´• DIA´• HOLEINECUnEATEXCnANOERTO MATCH 81~823 CLOSURE A8SY

ANBBOD(()L WASHER1 B LON(IERON MS21042L3 NUT

IREFL 880BBZSCLOSURE

NEST LOWER FLAN(IE OF W U nN3~ BOLT880882-7 SHROUD nSSY 1 llANBSODIBLWASHER

TUBE iSSY IREFIBENYEEN FUSELAGE SKIN IIPLS)

\ECU HEAT EXCHANGERAND NO. 10 LONOERON AND

TO ALLOW FOR MOISTURE

DRAINAGEDO NOT

880882´•18 SEAL ASSYI

_mrrli I II iN0.10

VIEW 8-8SWITCH IREFI

EXISTING HDWE (REFI0.199’~0.204" DIA. HOLE IN

ECU HEAT EXCHANGER TO

VIEW LOOKING DOWN MATCH 8880823 CLOSURE AS5Y

I\N35*80LT~NBBOD1IILWA8HER

MS21042L3 NUT

0.76’~9000

NO. 8 LONOERON

IREFI /i I asoea2ns SEAL AssvBOND TO FRAME AS8Y

IVITH 001403 CONTACTCEMENT

FRAME ASFY IREF)

NO.8

(0801

8008827 SHROUD ASSY

(REFI

VIEW A-A ~i ,´•.fVIEW LOOKING AFT AT STA 290.0

Fisun 2.

PagalofS

CU8TOM MT NO. 134


WBOHT FIND BALANCE: NO CHANGE.

SPARES AFFECTED: NO

PUsLICATIONS AFFECTED: The Illustrated Parts Catalog changes required by this document will be incorporated at


RECORD COMPLII\NCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No 134,

dated 11 January 1882, entitled ‘~Improved Inlet Air Eiupply for Environmental Control Unit", accomplished(date)

Page 5 of 5

C~IIB~ GulfB.reamAemspaceCoI)aaran

1001 NP´•th Roi*wsll Balhiiny. OLlilhoms 13008

C~mm´•nd´•rO*ilion

CUSTOM KIT NO. 135 29 SEPTEMBER 1982

AN AURAL MACH OIIERSPEED WARNING SYSTEM

FOR YOOR COMMANDER JETPROP

The Commander Aural Meeh Warning System is a fully automatio airspeed moni-

taring system.

The system compares airplane pitot pressure and pressure altitude. The sense

s~vitch is pre-set to aurally alert the pilot of airspeeds exceeding 243 KIAS.

n This system, which provides a warning in the event of an inadvertent

overspeed of the airplane, is an additional safety feature introduced to

offset the low drag feature that allows the Commander Jetprops to

easily increase airspeed during letdown.

U This system has been incorporated in our Model Bg5A (One Thousandl

C and all other L98 nodsi´• e´• a iland´•~ instdMlon.

EFFECTIVITY:

Kit No. 1.- Madel690,SeriolNos 11001thru 110?9.

Model BSL)A, Serial Nos. 11100 thru 11344.

Model 89011, SerialNos. 11360 thru 11566

Kit No 2.- Model 690C, Srriol Nos. 11600 thru 11709

Model 696, Serial Nos. 95000 thru 95084.

Order this kit Rom your nearelt Dulfstreom Commnnder Authorized ServiCenter.

Price: Kit No. 1- $11411.69 plus (nstallation

Kit Na 2 (1?66.49 plus installation

Pd~´• (IY11´•n To ohilosD Wllh~Y(

8Gulfstream Aerospace Corporation

6001 N~nh Bllhlnyl OLlan~m´• l~ms

CUSTOM KIT NO. 136

29 September 1882

COMMANDER AURAL MACH OVERSPEED WARNING SYSTEM

MODELS *FFECTED: MODEL 690, SERIAL NOS, 11001 THRU 11079.


MODEL 690B, SERIAL NOS, 11350 THRU 11566.



REASON FOR PUBLICATION: TO PROVIDE AN hURAL MACH OVERSPEED WARNING SYSTEM.


NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILE IN-

STALLING THIS CUSTOM KIT, CONTACT YOUR NEAR

EST GULFSTREAM COMMANDER AUTHORIZED SER-VICENTER.

BY WHOM WORK WILL 88 I\CCOMPLISWED: A 8r P MECHANIC OR EqUIVALENT.

I\PPR~VI\L: ENDINGWND DESION*SPBCTS *RB FI*~PPROYEO

ESTIMATED MAH HOURS: KIT NO, 1- TWENTY (20) HOURS.

KIT NO. 2 THIRTEEN (13) HOURS.

PARTS DATA: PARTS RE9UIRED TO COMPLY WITH THIS CUSTOM KIT MAY DE PROCURED THROUGH

YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERYICENTER FOR: KIT NO. 1-)1.144.69 OR KIT

NO. 2 )1766.49. REFERENCE THIS CUSTOM KIT, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN

ORDERING CUSTOM KIT NO, 136 CONSISTING OF THE FOLLOWING:

RIO´• nOllC´•´•

Kit No. 1- Models 690, 690A and 69011.

Kit Na. Z Madols 690C and 695.

Kit Kit

No.l No.2

lyru 9TY PART NO. DESCRIPPION

1 ea. 1 ea. 800144-3 Bracket Assy1 ea. 800144-1 Tube Aasy1 ea. 800744-11 Tube Assy1 se. 800744-15 Tube Assy1 es. 800144-11 Tube Assy

1 se. 1 ea. K800759-K7 Aural Annunciator Unit

1 ea. 1 ea. K800159-K3 Deeal

1 os. AN804-4D Tee

1 se. 1 ea. AN815-4D Union

1 ea. AN815-5D Union

1 ea. AN824-4D Tee

1 ea. AN824-5D Tee

Page 1 ol 20

CUSTOM KIT NO. 195

Kit Kit

OTY BTY PART NO. DESCRIPTION

No. 1 No. 2

2 ea. AN831-4D Elbow

1 ea AN919-3D Reducer

2 ea. AN924-40 Nut

1 ea AN929-4 Cap AssyLea. AN929-5 Cap Assy

2 ea. AN960D716L Washer2 ea. 2 ea. AN960D8L Washer

1 ea. 1 ea. DRA45C-45 Switch (Sense)1 ea 1 ea. M792811-13 Terminal

2 ea. 2 ea. M792811-15 Terminal38 R. 38 ft. M8104419-22-9 Wire

9 ft. M1L-H-6593-4 Hose

2 ea. 2 ea. MS25181-2 Butt Splice8 ea. MS214o4´•4D Fitting1 ea. 1 ea. MS3106E14S-SS Connector

20 ea. 10 ea. MS3367-1-9 Tiedown Strap2 se, a ea. MS35206-257 Screw

Lea. 1 ea. MS35489-1 Grommet1 ea. 1 ea. PB-126 (White) Switch (Test)1 ea. 1 ea. 5´•0309-804 O-RingLea. 1 ea. 5-0309-905 O´•Ring4 es. 4 ea 320555 quick Disconnect

2 ea. 4RBX-D Tee

6 in. 6 in #6 Yinyl Sleeve1 ea. 1 ea. Compliance Card

1 ea. 1 ea. Custom Kit No. 135 Instructions

SPECIALTOOLS: TUBE BENDING E4UIPMENT AND TUBE FLARING TOOLS FOR KIT NO 2

nCCOMPLisHMENT INSTRUCTIONS:

To install the Aural Mach Overspeed Warning System, follow the installation procedures for your airplane model and

serial number.

I. The following procedures are applicable to Models 690, 690A and 690B (refer to Figure i):

a. Remove bar behind copilot seat (ifinstalled) and remove copilot seat.

b. Remove nose compartment access door to gain secess to forward side of forward pressure bulkhead

c. Remove insulation banded to aft side of forward pressure bulkhead in area where holes for routing pitotline, static line and electrical wiring are to be drilled. Remove only enough insulation as necessary to

expose area where holes are to be drilled.

NOTE

Eleetrical wiring required with this installation may bemuted through forward pressure bullhead with any

existing wire bundle rather than drilling an additional hole

as outlined in step e, below.

i ´•´•-OK1CAUTION

Install a stop on drill bit in order to penetrate the bulkheadbut not the insulation. This will prevent damage to any

equipment on aft side of bullhead.

Page 2 of 20

CUSTOM KIT NO. 135

d Drill two (2) 0.47´•ineh diameter holes in forward pressure bulkhead for instullntian at AW897-4D

plba~w.

e. Drill a 0.25-inch diameter hole in forward pressure bulkhead far routing of electrical wiring lif

required).

L Using pilot hales in 8(10144´•3 bracket assembly as a template, Locate and drill four (4) O 1l0-inch

diameter holes in bracket assembly and forward pressure bulkhead for installation of bracket assembly

NOTE

To prevent interference with any equipment that may be

located on nose deck, it may be necessary to locate bracket

assembly to the left or right of area shown in Figure i.

g Apply sealant, conforming to Military Specification MIL-S-88o2, between bracket assembly nanges and

forward pressure bulkhead and install 800744-3 bracket assembly using NA1738B4 blind rivets Cover

heads of rivets with sealant after rivets have been pulled

NOTE

The following sealants conform to Military SpecificationMIL-S-8802, Class A brushable sealants:

Company Part No.

Products Research Co. PR1422 81 PR1440

Chem Seal CS3240

3M Corporation EC1675

Coast Pro Seal 890

Sealing shall be accomplished in accordance with proceduresC

outlined in Section Il of Model 690 and 690A/B Maintenance

Manuals.

h. Install DRA46C´•45 mach warning switch on bracket assembly using M836206-247 screw (2 places) and

AN960D8L washer (2 places).

i. Install AN919-3D reducer and S-0309-905 a-ring on static port of mach warning switch

j. Install ANB16´•ID union and S-0309-904 o-ring on pitot port of mach warning switch,

Place an AN9601)716L washer on each of the AN831-4D elbows and insert elbows in O 47-inch dianietei

holes that were drilled in step d, in forward pressure bulkhead. Washers are to be on Eorwnl´•d side of

bulkhead.

I. Apply MIL´•S-8802 sealant around AN924-4D nuts andsecure AN837-4D elbows to forward pressure

bulkhead with nuts, Orient elbows upward towards mach warning switch,

I~auno. 1CAUTION

Routing of pitot and static lines is optional: however, ensure

that no sumps exist after hoses are installed, System shall

be installed to ensure proper drainage. Condensation will

collect in a sump area and will not drain. The water may

freeze causing aural mach overspeed warning system to

malfunction and indicate erroneous readings.

Page 4 of 20

CUSTOM KIT NO. 1S5

c;F~t

ASSEMBLY INSTRUCTIONS

To install MS27404-4D end fitilngs an MIL-H-5593-4 hose, proceedas follows:

i. Cut hose to Length required and assure both ends are square

and then insert hose into socket and ensure that hose bottoms

up against recess in socket.

WOll

lberal application of soapy water to hose end

makes insertion of hose into socket easier.

2. Install mandrelinto igl~ nut through nipple and Lubricate inside

diameter of hose, threads of both socket and nipple with oil.

nOTI!

If mandrei is not ava~lable, install a bulkhead fittinginto "B" nut.

3. Screw Ripple into secret and hose. Tighten nipple and leave a

gap (1/3i-inch manmum) between socket and "B" nut so that

nut will swivel.

4. Remove mandrel or bulkhead fitting ir~m "B" nut.

FiBY" 2.

Page 5 of 20

CUSTOM KIT NO. 135

m. Cut two (2) hoses, to route from mach warning switch to elbows on forward pressure bulkhead, Elom

~MLenll to desired isogth iOusrall length la(ui´•sd mmun ona (li in.h to allor for

n. Install MS27404-4D Flttinga on hoses (refer to Figure 2).

a. Clean hose assemblies of all contaminants.

p. Connect fabncated hose assemblies to mach warning switch and to elbows on forward side of pressurebulkhead. Tighten hose assembly connections to a torque value oi40 to 65 inoh´•pounds while holdingswitch flttings and bulkhead elbows.

q. Install MS35489-1 grommet in 025-inch diameter hole (if drilled for wire routing) in forward pressurebulkhead

NOTE

If electrical wiring is to be muted with an existing wire

bundle, one (1) of the MS35489-1 grommets, furnished withthis kit, is not required.

2 The following procedures are applicable to Model 690, serial numbers 11001 thru 11079 and Models 690A and

690B, serial numbers 11100 thru 11521 that have not installed the pitot-static modification per Service Letter

No. 323A, dated 13 November 1980 (refer to Figure 3):

a. Disconnect existing copilot interconnect pitot tube assembly (Pi~ 850430-17) from tee fitting on rightpitot tube assembly, push the tube assembly upward and install 4R6X-D tee on top of existing tee.

b. Reconnect existing copilot interconnect pitot tube assembly (PIN 850430-17) to top of 4R6X-D tee.

c. Remove existing AN929-4 cap assembly from copilot static system that is located on top of the nose wheel

well closure and install 4R6X-D tee an top of existing tee.

d. Reinstall existing AN929-4 cap assembly on tap of 4R6X-D tee installed in step c.

cnurloN

Routing of pitot and static lines is optional; however, ensure

that no sumps exist after hoses are installed. System shallbe installed to ensure proper drainage. Condensation willcollect in a sump area and will not drain. The water mayfreeze causing aural mach warning system to malfunctionand indicate erroneous readings.

e. Cut two (2) hoses, to route from pitot and static tees to elbows on aft side of forward pressure bulkhead,from MIL-H-5593-4 hose material to desired lengths (Overall length required minus one (1) inch toallow for both end Bttinps).

f install M527404-40 fittings on hoses (refer to Figure 2).

IclunoNCAUIION

Assure that pitot and static hoses are connected properly.The top elbow on the forward pressure bulkhead is thestatic connection and the bottom elbow is the pitoteonneetion. incorrect connections could result in damage to

the system

Page 6 al 20

CUSTOM KPT NO´• 195

Q LENGTH OF HOSES TO BE DETERMINED

ON INSTALLATION. ROUTING IS OPTIONAL

WITH THE ONLY REQUIREMENT BehlG

THAT HO~S ARE ROUTED SUCH THAT

NO SUMPS EXIST.

I\EXISTING P~OT TUBE

ASSY (P/N 850430-17)

4RBX.D TEE

\EXblTINGICAPEXISTING TEEASSY (REF)

~IL-H-558S-4 PIIOT HOSE 17 ~4RBX-D TEEMS27404-4D FITTING (2 REQD)

TORQUE 40 TO 85 IN~LBS I

sPr,’r Q MIL-H-559S´•4 STATIC HOSO

M82~404´•40 FITTING (2 RFQD)TORQUE 40 TO BS IN-LBS

DRA1ISC-(S SW~PCH

(REF)

NOSE WHEEL WELL

CLOSURE (REF)

FORWARD PRESSUREBULKHEAD (REF)

MODELS BgO, 880A AND 880B, S/N 11001

THRU 11521 THAT HAYE NOT COMPLIED

WITH SERYICE LETTER NO. SaSA

Figure 9.

Page? ol 20

CUSTOM KIT NO 195

ha. Ma.mblias Ch. Connect one (1) fabricated hose assembly to new tee installed on right pitot tube assembly and to Elbow

on aft aide of forward pressure bulkhead. Tighten hose assembly connections to a torque value of 40

to 65 inch-pounds.

Connect the other fabricated hose assembly to new tee installed on copilot static system tee on nose wlieei

well closure and to elbow on aft side of forward pressure bulkhead Tighten hose assembly connections

to a torque value of 40 to 66 inch-pounds.

sOTe

Use MS3367-1-9 tiedown straps to secure hose assemblies to

eliminate the possibility of sumps in pitot and static lines.

i. Proceed to step 6.

3. The following procedures are applicable to Models 690A and 690B, serial numbers 11100 thru 11451 that have

installed the pitot-static system modification per Service Letter No. 323A, dated 13 November 1980 (refer to

Figure 4):

a. Remove and discard existing AN929-4 cap assembly from tee on right pitot tube assembly.

b. Disconnect instrument static line from tee on copilot static drain tee and install 4R6X-D tee on drain

tee.

c. Reconnect instrument static line to top of(RBX-D tee.

cnurlou

Routing of pitot and static lines is optional; however, ensure

that no sumps exist after hoses are installed. System shall

be installed to ensure proper drainage. Condensation will

collect in a sump area and will not drain. The water may

freeze causing aural mach warning system to malfunction

and indicate erroneous readings.

d. Cut two (2) hoses. to route from pitot and static tees to elbows on aft side of LMiard pressure bulkhead,hem MIL-H-659S-4 hose material to desired lengths (Overall length required minus one (1) inch to

allow for bath end fittings.)

e. Install MS214o4´•4D Bttings on hoses (refer to Figure 2).

I CI\UTIONCAUTION

Assure that pitot and static hoses are connected properly.The top elbow on the forward pressure bulkhead is the

static connection end the bottom elbow is the pitotconnection. Incorrect connections could result in damage to

the system.

Page 8 of 20

CUSTOM RPI NO. 135

Q U;NDTH OF MUSES To BE DETERMINBOON INSTALLATION. BOUTWG LS OPTIONALWITH THE ONLY REQUIRE~PENT DEING THATHOSES AI1E ROUTED SUCH THAT NO SUMPS

EXIST.

EXISTMO P~OT

HOSE ASSY (PIEF)

EXWTING CAP

ASSY (REB)

4R6X-D TEE

ExeTwo TEE (REF)

MIL-H-5593´•4 PITOT HOSE QMS21404-4D FPTING (2 RE~D)

TORBUE 40 TO 65 IN-LBS I~ II II COPULOT INSTRUMENT

STATIC LINE (REF)

4R6X-D TEE

EXLSTINO COPIL(YI~

STATIC DRAW TEE

(REF)

Q MIL-H-5598-4 STATIC HOSE

M821404-40 FBTWO (2 REQD)TOR&UE 40 TO 65 W-LBB

DRA45C-45 SWITCH

(REF)

FORWARD PRESSURE

BULKHEAD (REF)

MODELS 890A AND 6908, S/N 111UO

THRU 11451 THAT HAYE COMPLIEDWITH SFRVICE LETTER NO. 323A

Pilurs i.

Page 9 of 20

CUSTOM KIT NO 135

i Clean h´•s slssmblie,~f 11I

g. Connect one (1) fabricated hose assembly to existing tee on nght pitot tube assembly and to elbow (pitatconnection) on aft side of forward pressure bulkhead. Tighten hose assembly connections to a torquevalue of 40 to 65 ineh-paunds.

h Connect the other fabricated hose assembly to new tee installed on copilot static drain tee and to elbow

(stntic connection) an aft side of forward pressure bulkhead. Tighten hose assembly connections to a

torque value of 40 to 66 inch-pounds.

NOIE

Use MS3367-1-9 tiedown straps to secure hose assemblies to

eliminate the possibility oEsumpssumps in pitot and static lines.

Proceed to step 6.

4. The following procedures are applicable to Model 690B, serial numbers 11452 thru 11521 that have installed

the pitot-static system modification per Service Letter No. 323A, dated 13 November 1980 and for Model 69011,serial numbers 11522 thru 11566 (refer to Figure 5):

a. Remove and discard existing AN929-4 cap assembly from tee on right pitot tube assembly.

b. Remove upholstery panel on copilot’s side to gain access to secondary static lines at fuselage station

1250.

c. Disconnect existing copilot rate´•of-elimb hose assembly (P~ 850503-95) from elbow on frame at

fuselage station 12.50.

d. Remove and discard existing elbow from frame at fuseiagestation 12.50 and install ANB04-4D tee at

that position using existing hardware.

a. Recannect existing copilot rate-of-climb hose assembly (PIN 850503-95) to new tee at fuselage station

12.60.

f Cut two (2) hoses, to route from pitot and static tees to elbows on aft side of forward pressure bulthead,from MIL-H´•5593-4 hose material to desired lengths (Overall length required minus one (1) inch to

allow for bath end Bttings).

s´• Install M527404-4D flttings on hoses (refer to Figure 2).

cnurlo~

Assure that pitot and static hoses are connected properlyThe top elbow on the forward pressure bulkhead is the

static connection and the bottom elbow is the pitotconnection. Incorrect connections could result in damage to

the system.

h Clean hose assemblies ofall eontaminants.

Connect on. (1) fabricated hose assembly to top of existing tee on right pitot tube assembly and to elbow

(pitot connection) on an side of forward pressure bulkhead. Tighten hose assembly connections to a

torque value of 40 to 66 inch-pounds.

j. Connect the other fabricated hose assembly to new tee that is installed an frame at fuselage station

12.50 and to elbow (static connection) on aft side of forward pressure bulkhead. Tighten hose assemblyconnections to a torque value of 40 to 65 inch-pounds.

Page 10 of 20

CUSTOM KFP NO´• 135

o LENGTH OF HOSES TO BE DETERMINED

ON INSTALLATION. ROUTING IS OPTIONAL

WITH THE ONLY REQUIREMENT BEING

THAT HOSES ARE ROUTED SUCH THAT

NO SUMPS EXIST.

COPILOT RATE-OF-CLIMB

INDICATOR (REF)

EXISTING 850503-85

HOSE ASSY (REF)

EXISTING P~OT

HOSE ASSY (REF)

EXISTING TEE

(REF)

MIL-H-5583-4 PITOT HOSE 0 ~3

MSzl4oa-4o FITTING (2 REQD)TORQUE 40 TO 85 IN-LBS (UII EXISTING STATIC

TUBE ASSY (REF)

REh(OYE

ELBOW AND INSTALL

CO Mn-H-558S-4 STATIC HOSE

MS27a04-4D FITTING (2 RE9D)TORQUE 40 TO 65 IN-LBS

STA 12. 50

DRA45C-45 SWITCH

(REF)

PRESSUREBULKHEAD (REF)

MODEL 680B, S/N 11452 THRU 11521 THAT HAVE

COMPLIED WITH SERVICE LETTER NO. 323/1 AND

MODEL 680B, S/N 11522 THRU 11588 WITH FACTORY

INSTALLED SPLIT PITOT-STATIC SYSTEM.

Figula

Page 11 ol 20

CUSTOM KIT NO. 195

N.T.

Use M53367-1-9 tiedown straps to secure hose assemblies to

eliminate the possibility olsumps in pitot and static lines

k P,´•oceed to Jteg 6.

5. The following procedures are applicable to Models 690C and 695 irefer to Figure 6):

a. Remove bar behind copilot seat (ifinstalled) and remove copilot seat.

b. Remove nose compnrtment access door to gain access to forward side of forward pressure bulkhead,

c. Remove insulation, bonded on aft side offorward pressure bulkhead, in area where hole is to be drilledLr routing oleiedrieai wiring,

NOTE

Electrical wiring required with this installation may be

routed through forward pressure bulkhead with any

existing wire bundle rather than drilling an additional hole

as outlined in step d, below,

I?au~loNcnurlow

install a stop on drill bit in order to penetrate the bulkhead

but not the insulation. This will prsvsnt to any

equipment on aft side of bulkhead.

d. Drill a 0.25´•inch diameter hole in forward pressure bullhead (if required) above existing static Rttingand install MS35489-1 grommet in hole.

NOTE

If electrical wiring is to be routed with an existing wire

bundle, one (11 of the MS35489´•1 grommets, furnished with

this kit, is not required,

e. Install AN815-6D union and S´•0309-905 o-ring an static port of mach warning switch Torque union 86

to 160 inch-pounds.

L install AN811´•4D union and 5-0309-904 o-ring on pitot port of mach warning switch. Torque union 70

to 120 inch-pounds.

g. Instaii DRA45C-45 mach warning switch on bracket assembly using MS35206-247 screw (2 places) and

AN960D8L washer (2 places),

h. If existing pitot and static fittings. located on right side of forward pressm´•e buiklichd, are unused

(capped). proceed as follows:

(11 Remove existing cap assemblies from pitot and static fittings and retain for inter

reinstallation.

(2) Install 800744-11 tube assembly an static fitting and tighten "B" nut to a torque value of 60

to 80 inch-pounds,

Page 12 of 20

CUSTOM KIT NO. 135

(3) Install 800744-7 tube assembly an pitot fitting and tighten nut to a torque value of 40 to

66 inch-pounds.

(41 install AN824-5D tee on 800744´•11 tube assembly and tighten "B" nut to a torque value of 60

to 80 inch-pounds,

(5) Install AN824-4D tee on 800144-7 tube assembly and tighten nut to a torque value of 40

to 65 inch-pounds.

(6) Install existing cap assemblies, removed in step (1), on new pitot and static tees.

17) Connect 800744-17 tube assembly to static port on mach warning switch and to static tee atForward pressure bulkhead and tighten "B" nuts an tube assembly to a torque value of 60 to80 inch-pounds while holding union an switch secure.

(8) Connect 8(10744´•15 tubs assembly to pitat port ofmach warning switch and to pitot tee at

forward pressure bulkhead and tighten "B" nuts on tube assembly to a torque value of 40 to66 inch-pounds while holding union on switch secure.

If existing pitot and static fittings, located on right side of fonvard pressure bulkhead, have tubeassemblies connected to them, proceed as follows:

(1) Disconnect existing tube assemblies from pitot and static fittings on forward pressurebulkhead.

(2) Install 800744´•11 tube assembly on static fitting and tighten "B~’ nut to a torque value of 60to 80 inch-pounds.

(3) install 800744´•7 tube assembly on pitot fitting and tighten "B" nut to a torque value of 40 to

(4) Install AN824-5D tee on 800744-11 tube assembly and tighten "B" nut to a torque value o160

65 ineh´•pounds

to Bo inch-pounda.

(5) Install AN824´•4D tee on 800144-1 tube assembly and tighten "B" nut to a torque value of 40to 65 inch-pounds.

(6) Cut existing tube assemblies, diaconneoted in step (1), to Length required to connect to new

pitot and static tees. Install existing sleeves and "B" nuts on tube assemblies and dare tubing

NOTE

If bends in existing static line prevent cutting to new lengthand prevent flaring of static line, it may be necessary to

fabricate a new static line.

(7) Connect existing tube assemblies to piMt and static tees. Tighten "B’~ nut on static tee to a

torque value of 60 to 80 inch-pounds and tighten "B’~ nut on pitot tee to a torque value of 40to 65 inch-pounds.

j. With tube assemblies connected to switch assembly and using pilot holes in 80[)744´•3 bracket assemblyas a template, locate and drill four (4) O.llO-inch diameter holes in bracket assembly and forward

pressure bulkhead for installation of bracket assembly.

k. Apply sealant, conforming to Military Speeineation MIL-S-8802, between bracket assembly nanges andforward pressure bulkhead and install 800744-9 bracket assembly using NAS1138B4 blind rivets.Cover rivet heads with sealant after rivets are pulled.

Page 14 of 20

CUSTOM KIT NO. 195

K800158-KS DECAL

M/CI(

WARN

O. 250" DIA. HOLEpa-lzs (WH~E) SWITCH

PTT

LEFT INSTRUMENT PANEL(REF) 8O0 o ´•00

NOIB

LOCATION OF PB-126 (WHITE) SWITCH ONLEFT INSTRUMENT PANEL iS OPTIONAL.

Figure 7

Page 15 oL 20

CUSTOM KIT NO. 135

UOTB

The following sealants conform to Military SpeciBcationMIL-S-8802. Class A brushable sealants:

Company Part No.

Products Research Co. PR1422 PR1440

Cilem Seal C53240

3M Corporation ECi615

Coast Pro Seal 590

Sealing shall be accomplished in accardance with

procedures outlined in Chapter 20 of the AirplaneMaintenance Manual

6. On all madels, proceed as foilaws:

a. Locate and drill a o.250-inch diameter hole in left instrument panel for installation of PB´•126 Lwhitoi

switch (refer to Figure 7)

NOTE

Location of switch an left instrument panel is optional.

b. Install K800159-K3 decai on left instrument panel (refer to Figure 7).

c. install PB-126 (white) switch on left instrument panel (reEer to Figure 7).

d. Remove copilot’s side panel.

e. Cut a 11s-inch diameter hole in capiiat side panel and install K80o7fi9-K1 aural annunciator unit on

panel. Insulation may be cut and removed in area to clear annunciator unit. Apply Y-9082 thermal

insulation tape (or equivsient) on fuselage skin behind annunciator unit (reEer to Figure 8).

f Connect aural mnch overspeed warning system to airplane electrical system as shown on Figure 9

NOTE

Use MS3361-1-9 tiedown straps to secure electrical wiringas necessary

g Reinrtiill col,ilot’s upholstery side panrl.

7. Seal around grommet, rivets and electrical wiring an both sides of forward pressm´•e bulkhead with MII.-S-RROP

sealant.

8. Rebond insulation to forward pressure bulkhead using EC1103 cement.

9. Perform a leak check of Primary ipilatl and Secondary (copilot) pitot-static system individually as follows:

a Assure that all instruments are connected to their respective pitot-rtatie systems

b. Seal static ports an each side of airplane fuselage and pitot drain hales

c. Connect a vacuum source at static drain fitting and pitot tube assembly such that same vacuum is

applied simuitaneously to each paint

d Adlust altimeter to ~ero

e. Apply vacuum slowly until altimeter indicates 12.600 feet

Page 18 of 20

CUSTOM KIT NO. 135

BCUT 1.181’ DIA. HOLE W COPILOT

4SIDE PANEL IN THIS AREA DENOTED37.00

BY CROSS-HATCHING AND INSTALL

K800758-K7 AURAL ANNUNCIATOR UNIT.

n

nlJ

IjVIEW LOOKING OUTBOARD AT COPILOT SIDE

COPILOT SIDE PANEL II h FUSELAGE SKIN

(REF)~ I I II (REF)

Y-0052 THERMAL INSULATION

K800159-K7 AURAL I nlrl TAPE OR EQUTYALENT

ANNUNCIATOR UNIT

(REF)

INSULATIONI I I VIEW A~A(REF)

Pigura 8.

Page 17 ol 20

CUSTOM KII NO. 165

ON MODEL 680, CONNECT THIS WIRE TO TBS (CONTROLLED BY

LEFT ENGINE INDICATOR BREAKER) OR CONNECT TO

TB4 (CONTROLLED BY R2GHT ENGINE INDICATOR CIRCUIT

BREAKER) FOR POWER SUPPLY.

ON MODELS B80A, 690B, 690C AND 695, CC~JNECT THL4 WIRE TO

AVIONICS TERMINAL AVB (LOCATED BELOW fHE EMERGENCY

EXITDOOR) FOR POWER SUPPLY AND VERIFY THAT ANNUNCULTOR

3 CIRCUIT BREAKER CONTROLS THIS CIRCUTT.

1815181-2 BUTT

SPLICE

POWER

SOURCE

M1Ba8/1-13 TERMINAL 1 COVER SOLDER CONNECTIONS

WITH #6 VINYL SLEEVE

(2 PLS)

(4 PLS)PB-128 (WHITE)

320555 PUICKDISCONNECT

SWITCH (REF)

Mwnsna CGN’D~Ct)-MW4A22

KB(IO?SI)-K1

AURAL C:W

M?828/1-15TERMINALA f

I

(2 PLS) IIM81044/8-22-8 WIRE

(TYP)

MSS1OBE1QG-SI

CONNECTOR

B CD AE

DRA45C-45

MACH

SWITCH

WIR ING DIAGRAM

FIIYIP 9´•

Page 18 ol 20

CUSTOM KIT NO, 135

*mL

When applying vacuum, do not exceed range of Rate-oE-

Climb indicator.

f Shut off vacuum and hold for one (1) minute.

g. Observe altimeter for indication of leakage. Altimeter drop in Indicated Altitude shall not exceed 250

feet.

NOTE

Tap altimeter lightly before taking a reading.

h. Release vacuum slowly and then remove static port sealing material.

NOTE:

releasing vacuum, do not exceed range of Rste´•of-

Climb indicator.

Connect a clean, dry air pressure source to pitot tube.

j, Apply pressure to pitot slowly until Airspeed indicator indicates 130 knots.

k. Shut off pressure and observe for ons (1) minute.

i. Observe Airspeed indicator for indication of leakage. Leakage shall not exceed an indicated drop of 8.5

NOTE

Tap Airspeed Indicator lightly before taking a reading.

m. Release pressure slowly and remove test pressure source.

10. To functionally check the completed instellatian, proceed as follows:

a. Airplane Power ON.

b Mach-Warn Test Switch PUSH TO TEST.

Aural Warn Alert should pulse approximately 8 times per second at 2900 HZ.

NOTE

If system does not operate, check all electrical connectionsand venfy power source. The Aural Mach Warning Switch

has no field udjustments and is factory set.

Airplane Power OFF.

11. To functionally ground check system operation, proceed as follows:

System SpeeiBeations:

Actuate (Increasing Speed):243 ii B, -O) KIAS Seal i.evei to 18,700 Pt. Alt.

.52 ii.01.-00)MACW Above 18,700 Ft. Alt.

Page 19 of 20

CUSTOM KIT NO 196

a. *Place a tight fitting eix (6) foot length of surgical tubing over right pitot head.

NOTE

If Service Letter No. 323A has not been complied with, the

left pitot tube must be seeled.

b Airplane Power ON.

c. Double tubing over and grip tubing until airspeed indicator reads 243 (t6,-0) KIAS.

hural Warn Alert should sound a pulsing tone.

d. Airplane Power OFF.

a. Remove tubing from right pitat heed.

f Remove seal from left pitot head.

If a Pitot-Static System leak cheeker is used, follow the manufacturers instructions.

12. Reinstsli nose equipment cempartment access door.

13. Reinstall copilot seat and bar.


WEIGHT AND BALANCE: The weight and balance change resulting from installation of this Custom Kit is as follows:

WEIGHT (LBS) H-ARM (INCHES) H-MOMENT (IN-LBS)

ta.88 62´•60 CKit No. 2 1.80 82.50 112.5


PUBLICATIONS AFFECTED: The Airplane Maintenance Manual and illustrated Parta Catalog changes required bythis document will be incorporated at their naitt revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenonce records as follows: Custom Kit Na.

135, dated 29 September 1982, entitled, "Commander Aural Mach Overspeed Warning System’~, accomplished(date)

Page 2U of 20

OGulfstream

Custom Kit No. 136

15 November 1984

IMPROVED TAIL LIGHT STROBE LIGHT SYSTEM

MODELS AFFECTED: MODEL 690B, SERIAL NOS. 11541 THRU 11566.

MODEL 690C. SERIAL NOS. 11600 THRU 11999.

MODEL 690D. SERIAL NOS. 15001 THRU 15041.

MODEL 695. SERIAL NOS. 95000 THRU 95999.

MODEL 695h SEIAL NOS. 96001 THRU 96200.

REASON FOR PUBLICATION: TO PROVIDE AN IMPROVED TAIL LIGHT i STROBE LIGHT INSTALLATION

WITH LONGER RATED BULB LIFE.


NOTE




SERVICENTER.

sY WHOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR EQUIYALENT.

C *PPWY~L: &NODUGBRWO DBiiION WPSCTS *R6 APPROVIID.

ESTIMATED MAN HOURS: FOUR AND ONE´•HALF (4.5) HOURS,

PARTS DATA: PARTS REqUIRED TO COMPLY WITH THIS CUSTOM KIT MAY BE PROCURED THROUGH

YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR (262.21. REFERENCE THIS

CUSTOM KIT, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING CUSTOM KIT NO. 136

CONSISTING OF THE FOLLOWING:

Prr´• BYbl´•O1 T~ Eh´•4´• Wim~ut


1 se. 310062-609 Light Assy1 en. Complianee Card

1 ea. Custom Kit No, 136 Inatructioss

SPECIAL TOOLS: NONE

i_-Paee 1 of 3

’I

CUSTOM KIT NO. 136


1 RLmouP s.EBr. atldEh~nglail .ons to .mlans, diaronnot.lsUilal mnne..rs and remo*. tall mao

2. Remove screws and washers attaching tail cone lens to tail cone. Retain screws and washers for installing310062-509 light assembly.

3. Remove and discard existing tail cone lens.

4. Remove screws attaching existing tail i strobe light asaembly to tail cane.

5. Remove and discard existing tail i strobe light assembly.

6. Drill out rivets attaching existing nutplates and doubler to tail cone.

7. Remove and disca~d existing nutplates and doubler.

8. Make cutouts in tail cone for installation of new tail light i strobe light assembly (reEer to Figure i).

9 install 310052-509 tail light i strobe light assembly on tail cone using existing screws and washers removed

in step 2.

10 Connect 310052-509 tail light i strobe light assembly to existing electrical connectors.

Il. Reinstall existing tail cone on aft fuselage using existing hardware.

12. Functional check strobe light system to assure system is operating correctly.



WEIGHT AND BI\II\NCE: NO CHANGE.

SPARES AFFECTED: SPARES TO STOCK BOTH CONFIGURATIONS OF TAIL LIGHT i STROBE LIGHTS. CPUBLICI\TIONS AFFECTED: The Airplane Maintenance Manual and illustrated Parts Catalog changes required by

this document will be incorporated at the next scheduled revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No. 136,dated 15 November 19811, entitled "lmprovsd Tail Light i Strobe Light Systsm*, accomplished (dated)

Page 2 of 3

CUSTOM KIT NO. 136

C0.375" DIA. x 0.75" LONGSLOTS (4 PLS)

NOTE

ACCEPTABLE TO USE THIS

ILLUSTRATION AS A TEM-PLATE SINCE IT IS SHOWN

ACTUAL SIZE.0.88"

1´•-" tt -t

3~rf-- I ‘1.´•13´•´•Dln. HOLE 2.98"

pkl-nBLENDSMOOTH

1.75" E

HOLE

I

EXISTING 1.37" DIA. HOLE

(REF)

EXISTINGTAIL CONE

(REF)DISCARD EXISTING

F. DOUBLER

TAILCONE


AT TAIL CONE

Figure 1.

Pnge B of 3

QGulfstreamAerospace

CUSTOM KIT NO 136 15 November 1984

AN IMPROVED TAIL LIGHT STROBE LIGHT ASSEMBLY

FOR YOUR GULFSTREAM COMMANDER JETPROP....

O Provides individual strobe light and individual tail light

O More economical to maintain with longer rated bulb life

EFFECTIVITY:

MODEL 690B. SERIAL NOS. 11541 THRU 11566

MODEL 690C (EIGHT FORTY), SERIAL NOS 11600 THRU 11999

MODEL 690D (NINE HUNDRED). SERIAL NOS. 15001 THRU 15041

MODEL 695 (NINE EIGHTY). SERIAL NOS. 95000 THRU 95999

MODEL 695* (ONE THOUSAND), SERIAL NOS. 96001 THRU 56200

Order this kil irom your nearssl Oulfstieam Cammandsr

Authoriled ServiCenter

Price: (282.21. Plus installation

PII~´• Cn´•nl´• WI(IIOYI NnlT´•

OGulFstreamAerospace

CUSTOM KIT NO.137 18 JANUARY 1985

WINDSHIIELD ANTI-FOG SYSTEIVI FOR YOURGULFSTREAM COIVIMANDER JETPROP

O An electrically heated film is applied to the upperportion of the Pilot and Copilot windshields tomaintain a temperature sufficient to prevent fogformation.

O The heated film heats automatically with selectionof windshield heat.

C::: O Upon descent and landing a~roaeh, the heated filmreduces moisture accumulation which precludes water

dripping.

O The gold tinted film also acts as a sunscreen.

EFFECTIVITY:

Model 690, Serial Nos. 11001 thru 11079

Model 690A, Serial Nos. 11100 thru 11349

Model 690B, Serial Nos. 11350 thru 11566

Model 690C, Serial Nos. 11600 thru 11999Model 690D, Serial Nos. 16001 thru 15999Model 695, Serial Nos. 95000 thru 95999Model 695A, Serial Nos. 96001 thru 96200Model 6958, Serial Nos. 96201 thru 96999

Order this kit from your nearest Gulfstream Commander Authorized ServiCenter

Price: $486.00, plus installation

PRICE SUBJECT TO CHPINGE WIIHOUT NOTICE

ci~l,~m Nw, wlh wilov po~l aio~rl

PO Bor 22SWO*l´•homo CiN. 73123

CUSTOM KIT NO. 131

is January 1985

WINDSHIELD ANTI-F00 SYSTEM

MODELS AFFECTED: MODEL 690, SERIAL NOS 11O(I1THRU 11079.

MODEL 69DA, SERIAL NOS. 11100 THRU 11349.

MODEL 69DB, SERIAL NOS. 11350 THRU 11566.

MODEI. 680C, SERIAL NOS. 11600 THRU 11999.

MODEL 690L), SERIAL NOS. 16001 THRU 15999.


MODEL 695A, SERIAL NOS. 86001 THRU 98200.MODEL 695B. SERIAL NO9. 96201 THRU 96999.

REASON FOR PUBLICATION: ELIMINATES INTERNAL FOGGIND OF WINDSHIELDS AND SUBSEqUENTMOISTURE PROBLEMS.

COMPLII\NCE: AT OWNERS OPTION

NOTE




SERVICENTEB.

BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EQUIYALENT.


ESTIMI\TED MAN HOURS: THREE (3) HOURS.

PARTS DATA: PARTS REqUIKED TO INSTALL THIS CUSTOM KIT MAY BE PROCURED THROUGH YOURNEAREST OULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR (486.00. REFERENCE THIS CUSTOMKIT. AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING CUSTOM KIT NO 137CONSISTING OF THE FOLLOWING.

BTY PARPNO. OESCRlmION

1 en. 511800 Left Heater AssyI ea. 511900 Right Heater Assy1 en Compliance Card1 en. Custom Kit No. 137 instructions

SPECI~LTOOLS: NONE.

Page lolS

CUSTOM KIT NO. 13?

I\CCOMPLISHMENT INSTRUCTIONS:

8CAUTION

UNDER NO CIRCUMSTANCES ARE HEATERASSEMBLIES TO BE FLEXED, TWISTED. FOLDED ORSPINDLED. CLEAN, LINT FREE, SOFT COTTONCLOVES SHOULD BE WORN WHILE HANDLING ANDINSTALLING HEATER ASSEMBLIES. AVOID HIGHWIND CONDITIONS THAT MAY ALLOW DIRT AND

GRIT TO BECOME EMBEDDED IN THE HEATERASSEMBLY ADHESIVE. DO NOT APPLY HEATERASSEMBLY TO A HOT WINDSHIELD.

I Remove left and right sunvisors from windshields.

2 Apply 511800 heater assembly to left windshield and 611900 heater assembly to right windshield as follows:

a. Prepare inside surface ofleR and right windshields by cleaning them with a solution ofleopmpyl Alcoholand water (SOC solution).

b. Remove the protective caaung from adhesive side of heater assemblies. This will elpoee the gold costingon the heater assemblies; themfore, elttreme caution should be erereised so as not to scratch surface ofheaterassemblies.

c. Position heater assemblies and tack to windshields using masking tape as shown in Figure 1. Maintainone (1) inch constant dimension between upper edge of windshield heating element and heaterassemblies. To help maintain this dimension, one (1) inch masking tape may be used.

d. Strip away release paper fmm adhesive along longest vertiesl saga Gnao~nl ´•d~i orhasUr as

C~shown in Figure 2.

a. Using a hand miler, apply even pressure across the width of the adhesive as shown in Figure 3.

f Strip away release paper along top and bottom of heater assembly as shown in Figure 4.

g. Hold adhesive away from windshield until miler can press adhesive onto glass and then use the handmiler to apply even pmssum across the width of the adhesive.

Cars should be taken so that Link. or wrinkles am not

intmduced into haster assembly,

h. Altsmstely work top and bottom adhesive strips with roller veN slowly.

Remove the release paper fmm adhesive strip along shortest edge (outboard edge) of heater assembly andsecure adhesive to windshield using hand miler very slowly.

i. Remove masking tape and clean inside surface of windshield where masking taps was applied using a

solution oflsopropyl Alcohol and water (S09b solution).

i Lower overhead switch panel.

4. Route wires above heater assembly to overhead switch panel and connect heater assembly wires to airplanewindshield eleftncal system. Secum heater assembly wires to e~isting wire bundles as rrquired (refer to Figure5)

6 Assure that electrical wiring is clear of panel and then close overhead switch panel.

Page a of 5

CUSTOM KIT NO. 131

CROSS HATCHING INDICATES

RLACKEO OUT AREA OF

WINOSHIELDLEFT WINDSHIELD RIOM WINDSHIELD

IREFI I IREFI

611866 HEATER ASSY 611860 HEATER ASSY

IREF) IREFL

t I II ´•I.o´•´• CONSTANT1.0" CONSTANT

j

UPPER EDGE WINDSHIELD UPPER ED(IE WINDSH1ELD

HEATING ELEMENT IREF1 HEATIN(I ELEMENT (REF)

VIEW LOOKING FW D

1118W HEATER ASSY rREFI

~Ti

B11BW HEATER ASBY (REF)PEEL OFF AOHESIVERELEASE PAPER

i aiWINoSHIELD IREF)

Figure i.

k---I--

MASKlNO TAPE TO HOLD

HEATER ASSY IN WSITION

LEFT W1NDSHIELD IREFI

Fig u re 2.

PageSolS

CUSTOM KIT NO. 157

Csllano HEATER 511500 HEATER

A55Y IREFI ASSY IREFI

MI\IIINO TAPE (REFI

HAND

ROLLER

PEEL OFF RELEASE

PAPER TOP ANDLEFT WINDSHIELD IREFI LEFT WINDSHIELD IREF) BOTTOM

Figure 3. Figure 4.

2 51 LEFT WINDSHIELD RI(IHT WINDSHIELD 15 5

WITCH (REFI SWITCH InEFI

Illh Ill^s I 5_14 _31 1)

HI I I; I ILO LO I I I\ I HI

OVERHEAD SWITCH PANEL

wo´•reOYo OND

CONNECT ONE HEATER ASSEMBLY LE~O

WIRE TO WINDSHIELD 6WITCH AND THE

OTHER LEAD WIRE TO (IROUND

LEFT I I RIGHTWINDSHIELD I I WINDSHIELDHEATER I\SEY I I HEATER ASSY

(P/N 51(5WI I I IP/N 611800)

Figure 5. i

Pape4ofS

CUSTOM KIT NO. 131

5 ohpc~ xlinhhlald in f~r ihori~ople, spplunbls ilrpl´•n. M8int~n.nEp Manual

NDT6

Due to characteristics of low wattage anti-fog heater

operation. a positive functional test cannot be verf~ed on the

ground. Functional vsri8cation will be absence of foglh~oetbuildup at altitude.

7 Reinstall left and right sunvisors on windshields using eristing hardware.

S. Fill out and mail Compliance Card.

ELECTRICAL LOAD: +0.22 WA1TS PER SBUARE INCH (2.2 AMPS TOTAL).

WEIGHT ARO BAUINCE: NO CHANGE.

SPARES PIFFECTED: NO.

PUQLICATIONG AFFECTED: The Airplane Maintenance Manual and Illustrated Parts Catalog change. required bythis document will be incorporated at the ne.t scheduled revision.

RECORD COMPU*NCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No. 131,dated 18 January 1485, entitled "Windshield Anti-Fag System", accomplished: (date)

C

Page SofS

Custom Kiti Gulfstream

Aerospace

CUSTOM KIT NO. 138

Revision No. 1

14 June 198?

AUTOMATIC ENGINE IGNITION SYSTEM

APPROVAL: ENOINEERWC DESIGN ASPECTS ARE FAA APPROVED.


Pogo of 9

ADD Note to Figure 4:

NOTE

ON MODEL 690C, SN ~1BW THRU ll?ag AND MODEL690D. S~ 15001 THRU 16024, WIRE NO. 2K2?A22CONNECTED TO SOB SPEED SWPCH IS REPLACEDBY WIRE NO. (W22) 114 AWD WIRE NO. 2K13A22

C CONNBCPED TD laa spEnD SWPrCH 18 R8PL~OEDBY WIRE NO. (W22) 111 PER AIRPLANE WIRINGDIAGRAM MANUAL.

Page 8 of 9

ADD Note to Figure 5:

NOTE

ON MODEL 690C, S(N 11800 THRU 11128 AND MODEL

690D, Si~ 15001 THRU 15084 WIRE NO. iK27A22CONNECTED TO 60+ SPEED SWITCH IS REPLACEDBY WIRE NO. (W22) 14 AND WIRE NO. 1K1SA22CONNECTED TO 109b SPEED SWITCH 18 REPLACEDBY WIRE NO. (W22) 11 PER AIRPLANE WIRINGDIAGRAM MANUAL.

Wgslofl

C~IIGulfstreamAerospace

CUSTOM KIT NO. 13815 April 1987

AUTOMATIC ENGINE IGNITION SYSTEM

MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11135.MODEL 690D, SERIAL NOS. IbOOl THRU 15049.MODEL 695, SERIAL NOS. 95000 THRU 95084.MODEL 695A, SERIAL NOS. 86001 THRU 96061, 96064 THRU 96068, 96070 THRU 96074,96016 THRU 96071, 96019 THRU 96084 AND 66086 THRU 96100.MODEL 695B. SERIAL NOS 96062, 96065, 96069, 9607, 96018, 96085 AND 96P01 THRU96208.

REASON FOR PUBLICI\TION: To provide Automatic Ignition for bath engines in ease of engine namsout duringtakeoff and landing on wet runways and during nights in icing conditions. AutomaticIgnition is not limited to only these conditions. Automatic ignition is ovailableanytime the engine RPM is above 60 percent.

NOTE

Installation of this Automatic Ignition System meets therequirements of Part (b) of AD 86-24-12.

COMPLUNCE: AT OWNER’S DISCRETION.

NOTE

IF ANY PIIOIILEMS ARE ENCOUNTERED WHILEINSTALLING THIS CUSTOM KIT, CONTACT YOUR NEARESTGULFSTREAM COMMANDER AUTHORIZED SERYICECENTER.

BY WHOM WORK WILL BE I\CCOMPLISHEO: A B PMECHANIC OR EQUIYALENT.

I\PPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROYED.

ESTIMATED MnN HOURS: TWENTY (20) HOURS.

PARTS DATA: PARTS R68UIRED TO INSTALL THIS CUSTOM glT ON TWO ENGINES MAY BE PROCUREDTHROUGH YOUR NEARESP GULPSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KIT NO. 162660.00 OR KIT NO. 2 12650.00. REFERENCE THIS CUSTOM KIT, AIRCRAET MODEL AND FACTORY SERIALNUMBER WHEN ORDERING) CUSTOM KIT NO. 138 CONSISTING OF THE FOLLOWING:

Kit No. 1 Models 690C and 695Kit No. 2 Models 690D, 69511 and 69SB

Page 1 of 9

CUSTOM KIT NO. 138

Kit Kit

No.l No.2

BTY BTY PART NO. DESCRIPIIION

1 en. 1 ea. 800814-15 ComponentAssy1 ea. 800814-11 Angle Assy1 os. 800814-19 Angle Assy

1 ea. 800814-21 Angle Assy1 ea. 800814-23 Angle Assy

2 ea 2 ea. 800814-29 Tube AssyI ea. 1 ea. 83(1516-1159 Placard

2 ea. 2 ea. AN894-43 Bushing8 as. 8 ea. AN960D8L Washer

40 ft. 40 R. M22159Rl-20-9 Wire

50 ft. 50 it. M8104419-229 Wire

4 ea. 4 as. llLS21042L08 Nut

2 ea. 2 ea. MS26036-102 Terminal

4 se. 4 ea. M525214-2 End Cap4 ea. 4 ea. MS21039-0807 Screw

4 se. 4 ea. MS210S0081S Screw

2 ea. 2 ea. MS310BE1OSlr3S Connector

1 se. 1 ea. MS35059-21 switch

4 ea. 4 ea. NAS4SDD3-21 Spacer2 ea. 2 ea. 211C119´•115 Pressure Switch

4 se. 4 ea. 53A2 Diode

2 ea. 2 ea. S-0310-804T O´•R(ng2 ea. 2 ea. 3RBX-s or 6602-3 Swivel Tee

8 ea. 8 ea. 320555 Terminal

20 es 20 ea. 820658

Z ea. 2 es. 320562 Tenninal

4 ea. 4ea. M?92811-13 Terminal

2 ea. 2 ea. M?9as/1-22 Terminal

1 ea. 1 ea. Compliance Card

1 ea. 1 ea. Custom Kit No. 138 Instructions

SPEC1AL TOOLS: NONE.


1. Remove baggage wmpartment liner, as necessary, to facilitate installation of th~s Custom Kit.

2. Disconnect airplane batteries.

3. Remove upper and lower cowling from left and right engines.

4. Remove acoes: doors from tap of engine nacellss, as neceseary, to facilitate installation of electrical wiring.

6. Disconnect existing engine torque oil pressure hose assembly from oil preaaure port on engine torque preasuretransducer (refer to Figure i).

6. Install SRGX-S or 6602-3 swivel tee on engine torque pressure transducer (refer to Figure i).

Install 800814-29 tube assembly, AN894-CS buehin[l, S-03109904T ~ing and 211C119-115 pressure switch


8. Remove left and right inboard flaps as ontlined in Airplane Maintenance Manual.

g~ Remove left and right inboard wing closeout skins to gain access to electrical wire bundles.

Page 2 of g

CUGTOM KIT NO. 1SB

TYPICAL ENGINE PISSY.

dTYPICAL BOTH LEFT AND RIGHT ENG(NE

~J

THANSDVDER (REF)EXISTING TOROUE

ENGINEU FIREW*LL

IREF)

EXISTING ENGINE TOROUE011 PRESSURE HOSE ASM.

3RSXS TEE OR B(W129 TEEIREFI

SPOB14-29 TUBE AFSY

s´•031010dTO-RINO

2((C118´•(78 PRESSURE SWITCH

msJloellosL´•JsCoNNECroR

1.

Page 8 of 9

CUSTOM KIT NO. 138

0.1341~ Dll\. HOLE

MSJM168´•27SWITCHLEFTORCENTERINSTRUMENTPANEL

AUTO leN RELIOHT I I ILOCATION OPTIONI\LI

830516´•1168~-L 1 TEST

PLACARD

LEFT I I RI(IHT

Fi(uraZ.

10. Remove seats and lower right upholstery panels to gain secess to electrical wire bundles.

ii. Loeate, drill and install MS35059-21 switch on left or center instrument panel. Location of switeh is optional(refer to Figure 2).

12. Install 830515-1159 placard on instrument panel (reler to Figure 2).

13. On airplanes that have Service Buletin No. 194A accomplished, remove existing 800788-5 component assemblyand replace existing angles with 800814-11 and 800814-19 angle assemblies (Models 690C and 695) or 800814-21and 800814-23 angle assemblies (Models 69011 and 695A) using existing hardware. Rein3all existing 800188-3

component assembly using existing hardware (refer to Figure 3).

NOTE

Service Bulletin No 194A applies to Model 690C, serialnos. 11600

thru ll?a?. Model 69011, serial nos. 16001 thru 15018, Model 695,serial nos. 86000 thru 96084 and Model 69SA, serial nos. 96001

thru 96049.

14. If Service Bulletin Na. 194A is not applicable or has not been aocompliahed, locate, drill and install 800814-11and 800814-19 angle assernbliea (Models 690C and BgS) or 80081´•1´•21 and 800814-23 angle assemblies IModels690D 695A and 69511) using MS21039-0813 sorew 14 places), ANB60D8L washer (4 places), NAS43DD3´•24

spacer (4 places) and Ms21042L08 out (4 places) (reler O Figure 31

16. Install 800814-16 component assembly an angle assamblies, installed in step 14., using MSZ1039-0801 screw 14

places) and ANSBODBL washer (4 places) (refer to Figure S).

page loi9

CUSTOM KIT NO. 138

ACFT

BAGGAGE COMPPIRTMENT 14.MI..STRUCTURE IREFI

STA

THIS IS STI\. ZBO.O FORI\IRPLI\NESWITHOUT I i ‘BAO(I~OE COMP*RTMENTEXTENDED BAOOAOE

COMP~RTMENTSTRUCTURE

IREFL800814´•15VIEW LOOKING DOWN eOMPONENTnssv

IREF1

IC 2

8.67

oCOMP~RTMENT

B smucruallREFI

0.173~10´•(77´•1 Dl/i. HOLE

MSn099081JSCREWNI\S4JDDO´•24SPP1CERAN980OSLWASHER

MS21D41L08 NUT

I4PLS)

EXISTING OR

800114´•17ANGLE ASSY

EXISTING OR8W814´•18ANGLE ASSY

MOUNTING HOLE 14 PLS1/ I´•´•;i;´•´•nFOR 80078843 COMPONENT

ASSY (IF INSTALLED) PERSERVICE BULLETIN NO. (8d~

I ,II nit COMPONENTASSvANsSODSLWASHER

(4 PLS)

a c

e 7.36´•´•


MODELS 8900 I\ND 885

FiSurs S. Ishwt( of 2)

PaReSafS

CUSTOM KIT NO. 1SB

RCFT

ST*

STRUCTURE

InEFIBaosl4-lsVIEW LOOKING DOWN CMPohlENTnssY

(REFI

´•BAl

BAGGAGE COMPARTMENTBnOOAOE COMPARTMENT

STRUCTURE rREF)‘I,.BO´•´•TYP

0.1731´•10.111~´• DIA. HOLEMSn038´•0813SCREW

~NBMD8LWASnER

/J MS21042LOBNUT14 PLS)

EXISTING OR Ii I i II EX(STINO OR

malc2~ --II I I I II awncaANGLE nsn II I i I I ANOLEASSY

MOUNTING HOLE (4 PLSIFOR 8m7BS4SCOMPONENT

pgSy (IF INSTALLED) PER

SERVICE BULLETIN NO. (84A

saos~l´•tsCOmwONENTAssv

Ms2lossoao7scnEwaNsmosLwnsHER

’4PLS’ CI´•CI

*orr

FOR SOME MODELS. ITWILL 88 NECESSARY TOTRIM ANGLE ASSEMBLIES.AS NECESSARY. FORPROPER FIT.

D.S5~TYP O.IO’~

WP


MODELS 8800. 6851\ AND 8988

Flers 3. IShast 2 of 21

Page Bois

CUSTOM KIT NO. 138

16. Install 83A2 diode (4 places) and connect auto-ignition system to airplane electrical system as shown in Figures4 and 6. Route new wires along elisting wire bundles.

NOTE

Use M2216918´•20-9 wire fonuard of engine Brewall and use

M8L044/9-20-9 wire and M81044~-22-9 wire aR of engine flrewalland in an fuselage.

1?. Reinstall upper and lower cowling on engines.

is. Reinstall access doom On engine nacelles.

19. Reinstall left and right inboard wing closeout skins.

20. Reinetall left and right inhoard naps as outlined in the Airplane Maintenance Manual.

21. Reinstall interior upholstery panels and seats.

22. Reconnect airplane batteries.


24. Check rigging ofinboard naps ae outlined in the Airplane Maintenance Manual.

26. Check auto-ignition system as follows:

a. Battery Switch ON.

b. press AUTO-IGN RELICIIT test swish to the lan L-ION lightshall illuminate.

c. Press AUTO-ION RELIGHT teet switch to the right RION light shall illuminate.

d. Bsuen~ Switch OFF.

26. If annunciator lights do not illuminate while performing step 25., check to assure that annunciator lights are

not burned out end recheek wiring pr Figures 4 and 6.

27. Assure that Pilot’s Operating Handbook has revision dated 9 April 198? pertaining to Automatic Ignition System.



WE(GHT AND BALANCE; The weight and balance change resulting from installation of this Custom Kit is as follows:

WEIQHT (LBS) H´•ARM (INCHE8) HMOMENT(IN-LBS)

Kit Na. 1- +3.63 +284.1 +1031

Kit No. 2 +3.63 +284.1 +1031


PUBLICATIONS AFFECTED: The Airplane Maintenance Manual and illus~ated Parts Catalog changes required bythis document will be incorporated at the nest scheduled change/revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No. 188,dated 16 April 193’1 entitled "Automatic Engine Ignition System," accomplished (data)

Page 9 of 9

~ICustom KitCulfstreamAerospace

cvSroM KIT NO. 140

Revision 1

18 May 1988

NOSE GEAR STEERIFNG MODIFICAT~ON

APPROYI\L: ENCINBERING DESIGN ASPECTS N(L? FAB APPROVED.

Page 1 of 14 MAN HOURS:

Change to reed: TWENTY (20) HOURS.

RIRa 1 of 1

Custom KitCulfstreamAerospace

CUSTOM KB NO. 140

BNovember 1881

NOSE WHEEL STEERING MODIFICATION

MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11727, 11129 THRU 11755.


MODEL 695A, SERIAL NOS. 96055 THRU 86082 AND 96084 THRU 96100.

MODEL 6988, SERIAL NOS. 96062, 96063, 96069, 96075, 96078, 98085 AND 96201 THRU98208.

NOTE

FOR AIRPLANES THAT ARE APPLICABLE, SERVICE LETTER

NO. 367, ENTITLED "PARKER HANNIFIN CORP. PRODUCTREFERENCE MEMO (PRM) NO. 56 (REV A)" SHOULD BE

ACCOMPLISHED IN CONJUNCTION WITH THIS CUSTOM KIT.

CHECK YOUR AIRPLANE LOC BOOK TO ASSURE THAT

SERVICE LETTER NO. 167 HAS BEEN ACCOMPLISHED IF IT

IS APPLICABLE.

REASON FOR PUBLICATION: TO PROVIDE FOR THE REMOVAL OF ELECTRICALLY CONTROLLEDHYDRAULIC SERVO VALVE NOSE WHEEL STEERING SYSTEM AND THE

INSTALLATION OF BRAKE PEDAL CONTROLLED HYDRAULICALLYACTUATED NOSE WHEEL STEERING SYSTEM.


NOTE

IF ANY PROBLEMS ARE ENCOUNTERED WHILEINSTALLING THIS CUSTOM KIT, CONTACT YOUR NEAREST

GULFSTREAM COMMANDER AUTHORIZED SERVICENTER.

BY WHOM WORI( WILL BE ACCOMPLISHED: A d P MECHANIC OR E~UIYALENT.


EsnMnrEo Man HOURS: TWELVE (12) HOURS.

PARTS DATA: PARTS RE9UIRED TO INSTALL THIS CUSTOM KIT MAY BE PROCURED THROUGH YOURNEAREST OULFsTREAM COMMANDER AUTHORIZED 8ERVICEN*ER. REFERENCE THIS CUSTOM KIT,AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING CUSTOM KIT NO. 140 CONSISTINGOF THE FOLLOWING:

Pase1of14

CU8TOM KIT NO. 140

BTY PART NO. DEBCRmTION1 ea. 310181-13 Covet

1 ea. 79032D17 Rad Assy1 ea. 19054361 Tubs Assy1 as. 190343-65 Tube Aaey1 se. 190343-69 Hose Aesy1 ea. 180343-11 Nose Assy1 se. 862089-610 Plate1 as. AN5-4A Bolt

1 ea. AN3-6A Bolt1 se. AN3-14A Bolt

4 ea. AN3-21A Bolt4 ea. ANS-24A Bolt2 ea. AN929-4 Cap Assy8 ea. ANI)GO-1OL Washer2 ea. ANSBOD1OL WasherI ea. ANO6OPD10 Washer1 ea. AN960PD10L Washer1 ea. M8a0382-2Cll Pin4 ea. M521042-5 Nut5 ea. M821044NS Nut

2 ea. MSa108SN4 Nut2 as. MS21919D04 Clamp2 se. MS21919D08 Clamp1 es. M824665-134 CotterPin1 ea. MSO?9?5-4 Clevia End1 se. NA843DD3-10 Spacer4 ea. NA845DD9-40 Spacer4 as. NA94SDD3-58 spacer1 as. NAs43HT8-9 Spacer1ea. NAS43HTS-32 Spacer2 ea. NAS484-3-1BA Bolt1 se. REBSN Bearing1 as. BSSlObl Plug Button1 se. V-102 Valve Asey1 ea. Compliance Card1 ea. Custom Kit No. 140 Instructions

SPECULTOOLS: NONE.

~CCOMPLISHMENT (NSTRUCTIONS:

i. Jack airplane as outlined in Chapter 1 of the Airplane Maintenance Manual.

2. Reduce hydraulic system pressure to aero by applying brakes or actuating wing flaps

5. Cain access to airplane battery through baggage compamnent.

4. Remove baggage compartment liner to e.pose airplane batteries.

5. Disconnect airplane batteries.

6. Remove upper nose mmpartment access dear.

7. Cain access to nose gear steering command patentiometer, located in right fuselage nose section, through lowerforward nose access doer (refer to Figure i).

8. Remove and disoard petentiorneter, clamp assembly and bracket assembly (refsr to Figure 1).

5. Cap and staw potentiometer electrical wires N3dA22 (refer to Figure a).

Paseaof1d

O

CUSTOhl KIT NO. 140

AEHoVETnl~CCES8DWRTO(IIUN*CCEIIS

TO COMMIND POTELIIIOMETER

I´• REMOVE AND DISCARDITEMS 1 TnRU B

REINSTALL ITEM ION EXIST1N(I NUTPLATE

11I1PLS)

m

"---~---I II I I II U 1

I1PLSJ

I i i’

i:´•,ij, i~LI

i NOSE LA\DDNNO

IREF)

FieYra I´•

Page S or 14

CUSTOM KIT NO. 140

r

Bi

T 1

pms

CONTROL MODULE

I I i+ I "´•I

t

J -tn I I ´•´•U´•

mllaL,*,

F~un).

Page 4 of 14

CUSTOM KIT NO. 140

10. Remove and discard followup potentiometer installation from nose Landing gear (refer to Figure 3).

11 Replace existing hardware on nose gear collar assembly with NAS464´•9-18A bolt (2 places), ANSB0D1OL washer

(2 places) and M521042-3 nut (2 places). Toque bolt heads 20 to 25 inch-pounds (refer to Figure 3).

12. Cap and staw followup potentiometer electrical wires NS6AaZ (refer to Figure 2).

13. Remove hydraulic nose wheel steering manifold cover, manifold assembly and related fittings and a-rings (refer

to Figure 4).

14. Cap and stow nose gear steering manifold assembly electncal connectors P140, P141, and P142 Cap and stow

electrical wires NS17C22 and NS28A22 (refer to Figure 2).

16 Remove and replace existing cover assembly on fuselage nose deck with 310181´•15 cover using existing

hardware irefer to Figure 4).

16. Seal cover, installed in step 15., with Pro Seal 706 or equivalent MIL-S-8184 sealant as outlined in Chapter20 of the Airplane Maintenance Manual.

17 Remove existing hose assemblies on nose gear a~ambly and tube assemblies that were attached to the existing

nose wheel steering manifold assembly. Seal tube assembly clamp support holes in nose wheel well with Pro

Seal 880112 or an equivalent MIL-8-88~2 sealant as autlinsd in Chapter 20 of the Airplane Maintenance Manual

(refer to Figures 4 and 5).

18. Install AN929-4 cap assembly (2 places i on existing tees where tube assemblies were removed from in step 1?


18. Remove existing AN929-4 cap assemblies from right side of parking brake valve (refer to Figure 5).

cnurlo~

When drilling holes for V-1O2 valve assembly, in step 20., care

should be taken so as not to drill into any equipment installed on

nose deck.

20. Rack drill 0.180"10.194" diameter hole (4 places) through existing holes in channel and through nose deck.

Channel is installed on lower side of nose deck. Cain access to channel through wheel well (refer to Figure 6).

21. Install V-102 valve assembly, 190322-11 rad assembly, REBSN bearing end MS2?B75-4 clevis end (refer to

Figure 6).

22. Install 190545-69 Lan brake hose assembly, 790343-71 right brake hose asaembly, 180349-61 left brake tube

assembly and 7908(363 right brake tube assembly. Use existing clamps and attaching hardware or new

hardware furnished with this Custom Kit to suppo~ hose and tube assemblies (refer to Figures 6 and 7).

23. Remove and discard existing switch plate on pilafs control wheel.

24. Remove and discard existing ND 9TR switch from pilo~a control wheel and cap and stow electrical wires (refer

to Figure 2).

25. Install 862055-510 switch plate on pilot’s control wheel using existing hardware.

26. Remove and discard existing TAXI PARK switch cap, switch, lamp bulb and switch bezel. Cap and stow

electrical wires NS4C22. NS4A2a, NS8B2a, NsBC22,N8SB22 and N89BA1Z (reler to Figure 2).

27. Remove Dose steering circuit breaker from lett circuit breaker panel, cap and staw electrical wires and install

8861061 plug button in circuit breaker hole.

28. Remove STR INOP, TAXI and PARK lamp bulbs from annunciator panel.

29. Cain access to annunciator coupler, located on cockpit noor forward of control pedestal, and disconnect connector

plugs P189 and P170. Cap and stow wires NSa?Baa, NBSB22, NS6822, and D30C22 (refer to Figure 8).

90. Reconnect connector plugs P169 and P110 to annunciator coupler.

Page 5 of 14

CU8TOM KIT ND. 140

BEFORE CHANGE

NOblE LANDINDDEAR (REF)

1~

.j

i. REMOVE AND DISCARD ITEMS I

2. REPL~CEITEM1BATTACHINO1TRRU II

15 sHARDWAREWITH:

I\NWODIOLWASHERNasoea,lsn BOLT

rala~rauvr 1 ’71Ji I

ronoursoLTHEno2a TO ta IN´•LBS IZPLS)

~8SURE 6~ME NUMBER 1~ ,iOF SHIMS ARE REINSTI\LLEO OIN SAME LOCATION FROMWHICH THEY WERE REMOVED.

II

Figul´•5.

PageBof1d

CU6TOM KIT NO. 110

VIEW LOOKING AT

FUSELAGE NOSE DECK

1. REMOVE AND DISCARDITEMS 1 THRU 12

2. REMOVE AND REPLACE ITEM13 WITH 310181-13 COVER

3. REMOVE I\ND DISCARD ITEMS

id THRU 18 ISAME AS ITEMLII.3 AM)4 ON F1OURE 51 WHERE

SUPWRT HARDWARE WASREMOVED. SEAL HOLES

I?~81

i11

2 "ii,

Fllursd.

PaSa? of 14

CUSTOM KIT NO. 140

SEE FIGIUREI

1, I

i. REMOVE AND DISCARD ITEMSITHRUI

REMOVE EXISTING CAP ABIY12 PLSL FROM RIGHT HAND SIDEOF PARKING BRAKE VALVE()TEM 51

3. INSTALL *N828´•4 CAPASSY ONTEES IITEMS B AND II WHEREITEMS3 AND 4 WERE REMOVED

i. SEAL HOLE WHERE CLAMPSWERE INSTALLED IITEM 8)

Flgurali.

p,, 8 of 14

CUSTOM KIT NO. 140

AIRPLANE

Q nNsl4nsoLT A;nAS43HT132 SPACER i

1LnaDINo

Mp(044N3NUT

i oEnR cnEFI

I

ExlsrlNaBELLCRANK

IRE FI

~80922´•17ROD ASY

(REF)

780549´•61TUBE A88Y

IREFI

7em49a8HOSE ASSYIAEF)

IREFL Y´•IDZ YALVEAMY

EX18TIN0310527´•J

IREF) CHANNEL IMODEL BBOCII OR

o.lso´•~. lss- OIA 1111 1 It EXIBTINOS10889´•8

HOLE 14 PLS) CHANNEL IMODELS 880D.BACK DRILL THRU B86AAND8JSB)

HOLES IN EXISTINGCHANNEL

iii

I ----f-7em43´•7~ HOSE A6SYIREF)

STA

~IFWD

leasos~u TUBE AMY

InEFI

VIEW LOOKING DOWN ON NOSE DECK

Flp~O´•(SM(012)

Page 8 of 14

CUSTOM KIT NO. 1PO

REBSN BWRINO

NOSE LANDING (IEARIREF) "Y

EXISTING BELLCRANK

IREF)

Inl IMS210B3N9NUT

II

190522´•17ROO AS9Y

PUSELI\OE NOSE DECK

IREF)

0] i I ,MS27879d CLEVIS END

MS?IOBBN4NUT

EXISTING CHANNELIRE Fl

IN WWN POSITION

M~INTI\IN 109 FROM VERTICALFOR VALVE ARM

M9M382´•2el( PIN~N980´•IOLWI\SHERMS21~6(3(COTTEA PIN

AN3-21A BOLT (MODEL B90C1 i N~S4SnTSIJSPI\CER

I\NPZ4A BOLT IOTHER MODELSLANBBDlDL WASHER 12 REB’D) I i bl V´•(02

MS210MNINUT ii i VALVE A8SY

NAF4SDD3~0 SPACER (MODEL BBOC)NA~9De968sPnCER

IOTOER MODELSIUPLS1

VIEW A-A

LOOKING OVTBOARD

FIIYI. L (8h~M? 01 2)

Page 10 01 14

CUSTOM KIT NO. 1(0

MSlslBDOB CLAMP 12 REO’D)ANJBnBOLTNAUIDDJ´•IOSPACER MSZ(BIID(II CLAMP 12 REO’DIANB1IOPD1PLWI\SHER ANSI~BOITMPlOd2jNUT I\NBBOPDIOWASHERINSTALL SPACER BETWEEN MS(W2~3 NUTCLAMPS AND NOSE DECK

780343 -81 TUBE ASSV

V-102 VALVE

ASPY (REF) 1 780343´•89 TUBE ASSY

NOSE LANDINGOEAB (BEFI

EXISTING IBM0(7CLAMP

leouu;71 HOSE ASSY

NOSE GEAR /I EXISTING MS21818D08 CLAMPSSTEERINOCYLINDER IA ANS~A BOLT

MSZ1M2-S NUT

7803119´•88 ROSE ASSY

~1

r~CAUTION

CARE SHOULD BE TAKEN TO PREYENT*NY DAMI\(IE TO EOUIPMENT ON NOSEDECK WHEN DRILLING HOSE AND TUBECLAMPATTACHING HOLES IN NOSE DECK.

Fioursl.

Page 11 o~ 14

CUSI~OM KI~ NO. 1´•10

P189P111

INOP-1121CWAB1\22 E6--N97822----L

141 [z~U E---Nslsn----,

san.~lel il~--M8822---C

*NNUNCI*TORM~STERCnUT1ON

UNIT

029/\22

030822 0281\22---)

FilYns.

Page 12 of 14

CUSTOM KIT NO. 140

31. Reconnect airplane batteries.

32. Bleed nose wheel steering system as follows:

a. Fill hydraulic reselyoir with hydraulic nuid conforming to Military Specification MIL´•H-89282 as

outlined in Chapter 12 of the Airplane Maintenance Manual.

b. Loosen hydraulic line at forward side of nose wheel steering cylinder enough to allow nuid to seep out.

Apply slight presaure to left rudder brake pedal and hold pressure until fluid seepage is free of air.

Tighten forward hydraulic line before releasing pressure on rudder brake pedal.c. Loosen aft hydraulic line of nose wheel steering cylinder and apply alight pressure to right rudder brake

pedal and hold pressure until nuid seepage is free of sir, Tighten aft hydraulic line before releasingpressure on rudder brake pedal.

d Refill hydraulic reservoir with hydraulic fluid as outlined in Chapter 12 of the Airplane Maintenance

Manual.

SS. Bleed brake system as outlined in ChapterS~ of the Airplane Maintenance Manual

34. Functional check the nose wheel steering centering pin as follows:

a. With airplane an jacks, attach weighted tailstand as outlined in Chapter 7 ofthe Airplane Maintenance

Manual.

b. Ensure Bat nose gear strut is fully extended.

c. Turn nose wheel 450 to left by hand, releaee end allow nose wheel to center. Turn nose wheel 46’ to

right by hand, release and allow nose wheel to center.

NOTE

Should nose wheel fail to center, remove centering pin and check

far wear. Centering pin may be rotated 180D, providing a new

weanng surface.

I I*.RNINO IWbRWINO

If centenng pin is to be removed, nose gear strut pressure must be

reduced to zero prior to removing centering pin. Failure to do so

will result in pin becoming a projectile which may result in injuryto personnel.

d. Reduce hydraulic pressure to zero by applying brakes.

e. Using auxiliary hydraulic pump only, apply toe pressure to left and right rudder pedals. Nose wheel

should remain centered.

NOTE

If nose wheel turns to left or right, remove centering pin and check

for weer. Centering pin may be rotated 1800, providing a new

wearing surface.

I UIIRNIN. IW~RNINB

If centering pin is to be removed, nose gear strut pressure must bereduced to zero prior to removing centering pin. Failure to do so

will result in pin becoming a projsetile which may result in injuryto personnel.

page 13 of 14

CUSMM KIT NO. 140

35. Functional check nose gear retraction to assure no interference exists.

36. Reinstell baggage compartment liner.

31. Reinstall upper nose compartment access door.

38. Reinstall lower forward nose access door.

39. Remove jacks and weighted tailstand as outlined in Chapter of the Airplane Maintenance Manual.

40. Assure that the Pilot Operating Handbook has the revision addressing Custom Kit No. 140 mserted.


ELECTRICP.L LOAD: -20 Amperes.

WEIGHT FIND BALANCE: The weight and balance change resulting fiom installation olthis Custom Kit is as follows:

WEIGHT (LBS) H-ARM (INCHES) H-MOMENT (IN-LBS)t2.64 35.52 +88.0

-6.62 28.40 -195.0

SPARES IFFECTED: NO

PUQUCATIONS AFFECTED: The Ai~lane Maintenance Manual and illustrated Parts Catalog changes required bythis document will be incorporated at the next scheduled revision.

RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No. 140,dated 8 November 188?, entitled "Nose Wheel 8tesring Modlttcptlon," accomplished (date)

Page 14 of 14

Custom Kit A IR CRI FT CORPORI nON

P.O. Bm: 3889

AdnJbn. WA 88223

at: (208) 435´•978~ FsX:(208) 435-1112

CUSTOM KIT NO. i 41 JULY 17, 1992

ENVIRO AIR CONDITIONING AND PRESS~_RIZATIONSYSTEM_INSTALLATION

******’*’*TO PROVIDE AN ALTERNATIVE AIR CONDITIONING SYSTEM"’"""

Fan can be used for air circulation at any altitude

MODEL 690C(EIOBT mRm) SERTRI´• NUMBERS 11600 TBRV 11’135

MODEL 695(NINE ElcBrY) IERTRL NUMBERS 91000 TBRU 95084

obtain this kit and rull details from p~ournearest ~win Commander service Center.

Custem Kit *LRCR*FT

r0 8~´• UIII

*Ilinglsn. Wi\ IliD

n: is´•enr Fu; ilObl 131´•11(2

CUSTOM KIT NO. 141

JULY 17, 1992

ENVIRO AIR CONDITI(ININD AND PBESBURIZATION BYSTEM INSTALLATION

MODELS AFFECTED 690C Serial Numbers 11600 thru 11735

695 Serial Numbers 95000 thru 95084

that have not previously complied with earlier modification to

Gulfstream Dwg.880718 (Environmental system installation).

Reason for publication: To provide an alternative air

conditioning system.

Complianoe: At owner’s discretion.

NOTE:

IF ANY PROBLEMS ARE ENCOUNTERED WHILE INSTALLING THIS

CUSTOM KIT CONTACT TWIN COMMANDER A/C CORP.

By whom work will be accomplished: A P Mechanic or equivalent.

Approval. Engineering aspects are FAA approved

Estimated man hours: 375 hours for-I kit two evaporator at rear

pressure bulkhead; 385 hours for -2 6 -3 kits with one evaporatorat rear bulkhead and one evaporator forward.

NOTE:

TIME DOES NOT INCLUDE RECTIFICATION OF PRESSURIZATION

LEAKS, PAINTING OR WEIGHT AND BALANCE.

PARTS DATA: A PACKAGE OF DRAWINGS PERTAINING TO CK 141

INSTALLATION IS PROVIDED AS ADDENDUM A.

NOTE:

CUSTOM KIT 134, IMPROVED INLET AIR SUPPLY SYSTEM, MUST BE

ACCOMPLISHED AT THIS TIME IF NOT PREVIOUSLY INSTALLED.

SEE STEP 35. PARTS LIST DOES NOT INCLUDE FASTENERS

WHICH SHOULD BE PROCURED LOCALLY. OTHER PARTS REQUIREDTO INSTALL THIS CUSTOM KIT MAY BE PROCURED THROUGH YOUR

NEAREST TWIN COMMANDER SERVICE CENTER. REFERENCE

AIRPLANE S/N WHEN ORDERING CK141-1, CX141-2, CK141-3

CONSISTING OF THE FOLLOWING:

CX141-1 a Evaporator at rear pressure bulkhead.

CK141-2 1 Evaporator at rear pressure bulkhead and 1 Evaporatorinside sideways seat (only possible if A/C does not have

an electrical lavatory).

CX141-3 1 Evaporator at rear pressure bulkhead and

L Evaporator inside R/H bar.

Page 1

PARTS DATA (1)

All installations will require the following parts:

ITEM NO QTY PART NUMBER DESCRIPTION

1 1 1-48028)-0 PLUG

2 2 1-4803 05-0 CONNECTOR

3 2 110134-229 STATIC DECAL

4 1 110134-271 DECAL. EXT PWR

5 1 1250400-22 COMPRESSOR

6 1 1300)50 CABIN TEMP CONTR

7 1 1)00360 FLOW CONTROLLER

8 1 130 044 0-1 CABIN TEMP SENSOR

9 1 1300450 TEMP SENSOR

10 1 1300464 FLOW SENSOR

11 1 1300520-1 MUFFLER

12 1 1588-00-1 VALVE

13 30 205050-1 SOCKET

14 12 26838-5 STUD

15 1 310868-55 DOUBLER

16 Z 310868-57 COVER

17 5 5466 NIPPLE

18 7 60619-1 SOCKET

19 6 60620-1 PIN

20 1 62065-3/8X3/8X)/8 TEE

21 4 640903-1 PIN-RECEPTACLE

22 20 640905-1 TERMINAL

23 3 7277-i-2-12-507-61 CIRCUIT BREAKER

24 1 800655-501 BRACKET ASSY

25 1 800697-511 BUS BAR

26 1 800812-1 DOUBLER

27 1 800816-17 PANEL ASSY

28 1 800816-3 PLACARD

29 1 800816-5 PLACARD

)O 1 800816-7 PLACARD

31 1 800816-9000-1 AFTWIRE BUNDLE

32 1 800816-9000-2 2 EVAP WIRES BDL

33 1 8)3038-1 RELAY

34 1 862064-501 ESCUTCHEON

35 1 880647-11 DOUBLER

36 2 880697-13 DOUBLER

37 1 880647-5 GRILL ASSY

38 2 880701-11 BRACKET

39 1 880701-9 SPACER

40 1 880708-11 CHANNEL

41 1 880708-13 CHANNEL

42 1 880708-15 WEB

43 1 880708-19 SHIM

44 1 880708-21 PAN ASSY

45 1 880708-27 ANGLE46 2 880708-29 DRAIN TUBE ASSY

47 2 880708-3 CHANNEL

48 1 880708-35 HOSE

49 2 880708-37 HOSE, DRAIN

50 4 8807CS-49 ANGLE

51 1 880708-5 CHANNEL

ITEM NO. QTY PART NUMBER DESCRIPTION

52 1 880708-7 CHANNEL

53 1 880709-17 ANGLE ASSY

54 1 880709-413 SHROUD ASSY

55 1 880709-9 TAB

56 1 880718-17 TUBE ASSY

57 1 880718-19 TUBE

58 1 880718-23 POTENTIOMETER

59 1 880718-39 HOSE

60 1 880718-41 HOSE

61 1 880718-43 HOSE

62 1 880718-5 TUBE

63 1 880718-63 HT EXC/DUCT ASSY

64 1 880718-65 ANGLE ASSY

65 1 880718-69 ANGLE ASSY

66 1 880718-7 TUBE

67 1 880718-73 PANEL ASSY

68 1 880718-79 MODULATING VALVE

69 1 880718-81 FLOW/TEMP CNTR

70 1 880718-9 TUBE

71 1 880722-505 ANGLE ASSY

72 1 880722-507 ANGLE

73 1 880722-508 ANGLE

74 1 880722-509 ANGLE

75 1 880722-510 ANGLE

76 1 880723-1 COVER ASSY

77 1 880723-503 BAFFLE ASSY

78 1 880723-515 TUBE ASSY79 1 880723-529 CHANNEL ASSY

80 2 880724-19 LONGERN DOUBLER81 1 880724-3 TUBE ASSY

82 1 880725-25 DUCT ASSY

83 1 880726-1 TUBE ASSY

84 1 880727-501 BOX ASSY-LOWER

85 1 880727-j02 BOX ASSY-LOUVER

86 1 880728-3 SUPPORT ASSY

87 1 880728-5 TEE ASSY

88 1 880728-7 TEE ASSY

89 2 880730-11 MOUNTING PLATE

90 1 880730-7 COVER

91 1 880730-9 COVER

92 1 880732-19 HOSE ASSY

93 1 880732-21 HOSE ASSY

94 1 880732-25 HOSE ASSY

95 1 880732-29 HOSE ASSY

96 1 880734-3 TUBE ASSY

97 1 880734-9 PLACARD

98 1 880735-3 BRACKET AS SY

99 1 880735-7 ANGLE

100 16 900129-58 CLAMP

101 2 900129-66 CLAMP

102 4 930060-1 CLIP ASSY

103 16 AD34ABS POP RIVET



105 20 AD44A8S POP RIVET

106 1 AGC-1 FUSE

107 45 AN3-3A BOLT

108 1 AN3-4A BOLT

109 13 AN3-5A BOLT

110 2 AN4-22A BOLT

111 4 AN4-5A BOLT

112 4 AN503-6-8 SCREW

113 10 AN737TWZZ CLAMP

114 2 AN737TW48 CLAMP

115 1 AN804D6 TEE

116 1 AN804D8 TEE

117 2 AN818-6D NUT

118 1 AN924-6D NUT

119 1 AN924-8D NUT

120 66 AN960D10 WASHER

121 14 AN960D10L WASHER

122 1 AN960D1216 WASHER




126 5 AN960D6L WASHER

127 1 AN96~D916 WASHER

128 20 D100-00 SLEEVE SOLDER

129 24 D101-00 SLEEVE SOLDER

130 24 D436-36 SPLICE

131 )O D436-37 SPLICE

132 30 D436-38 SPLICE

133 1 ECARD COMPARISON CARD

134 1 FELT 1/16X1 BLK FELT (BLACK)135 20 FT FLEXGUARD 1/2" DIA. WIRE BUNDLE SLEEVING 135

136 1 ADJA FUSE HOLDER

137 4 M7928/1-22 RING TERMINAL



140 1 M7 9 Z 8 /1-42 RING TERMINAL

141 2 M7928/1-50 RING ERMINAL

142 2 MS21042-) NUT

143 2 MSZ1042L06 NUT

144 50 MS21042L3 NUT

145 4 MSZ1042L4 NUT

146 2 MS21071L06 NUTPLATE

147 2 MS21073-L06 NUTPLATE

148 12 MS21266-1N GROMMET

149 1 MSZ1266-3N GROMMET

150 1 MSZ1919DG10 CLAMP

151 5 MS21919DG13 CLAMP

152 B MS21919DG28 CLAMP

153 1 MS21919 DG34 CLAMP

154 1 MS24166-D1 RELAY

155 6 MS24621-15 SCREW

156 4 MS24621-18 SCREW

ITEM NO. PTY PART NUMBER DESCRIPTION

157 9 MS25036-103 TERT.INAL

158 5 MS25036-108 TER~INAL

159 5 M525036-123 TFREIINAL

160 2 3S25036-125 TER~INAL

161 1 MS25036-132 TERI~INAL

162 1 1S25036-133 TERMINAL

163 1 lS25036-154 TERMINAL

164 4 MS25171-1S NIPPLE

165 2 MS25171-3S NIPPLE

166 4 MS27039-1-08 SCREW

167 3 MS27039-1-09 SCREW

168 4 MS27039-4-04 SCREW

169 1 MS3126E10-6S CONNECTOR

170 15 MS3192A-20A CONTACT PIN

171 15 MS3193A20A CONTACT SOCKET

172 50 MS3367-1-9 TYRAP

173 50 MS3367-2-9 TY~P

174 4 MS35206-216 SCREW

175 5 M535206-229 SCREW

176 4 MS35206-230 SCREW

177 12 MS35206-231 SCREW

178 6 MS35207-265 SCREW

179 1 MS35207-267 SCREW

180 2 MS35842-15 CLAMP

181 2 NAS1564D6-4 REDUCER

182 1 NAS43DD3-32 SPACER



185 1 NC22S16-50-6 DUCT

186 2 412 PANEL BOX BLACK

187 1 NWZW2S-5-102-4 DUCT

188 2 PT06CE-8-4S CONNECTOR

189 1 RB-67-1-SK-7-M KNOB

190 1 RNF10O 3/4 HEAT SHRINK TUBE

191 2 RNF100-2IN-TY1 TUBE RED SHRINK

192 3 RNF100-31N-TY1 TUBE RED SHRINK

193 2 RNF100-4IN-TY1 TUBE RED SHRINK

194 2 RPC2300-W FELT INSULATION

195 4 S0333A6-20C SCREW

196 8 S0335A8-4 SCREW

197 1 50-370-501 JUMPER

198 3 S3A2 DIODE

199 1 SEC07C12 CONE SEAL

200 2 SECo7C16 CONE SEAL

201 3 SEC07C24 SEAL

202 8 ST3333-6-12 TUBE

203 1 9T3333-7-12 TUBE

204 1 TAPE 622 DUCT TAPE 2"

205 Z TIGLS1-1CWHC SWITCH

206 1 WTTY CARD WARRANTY CARD

207 1 YAEV4CL3 TERE:INAL

208 2 X6687 DUCT

PARTS DATA (2)

Please refer to airplane nodel and serial number and type of

installation for additional parts required.

CK141-1-1

Airplane Models 690C and 695 Serial Numbers 11600-11718 and

95000-95087, two evaporators at rear pressure bulkhead.

ITEM NO. BTY PART NUMBER DESCRIJTION

1 1 800816-9501 WIRE SET (2 EV)2 1 850618-501 PANEL

3 1 880697-29 GRILL ASSY

4 1 880697-31 DOUBLER

5 1 88 0701-413 WIRED SW PANEL

6 1 880718-101 ANGLE

7 2 880723-531 COVER

8 2 880728-15 EVAP ASSY

9 1 880732-23 HOSE ASSY

10 1 880732-27 HOSE ASSY

11 1 880741-1 HZO DEFLECTOR

12 1 AN821-8D ELBOW

13 4 MS24621-18 SCREW

14 6 MS27039-1-1l SCREW

15 2 M527039-1-20 SCREW

16 1 TIGLS1-1CWHC SWZTCA

CKI41-1-509

Airplane Models 690C Serial Numbers 11719-11729, two evaporatorsat rear pressure bulkhead.


1 1 800675-501 BRACKET ASSY

2 1 800816-9501 WIRE SET (2 EV)3 1 850618-501 PANEL

4 1 880697-5 INLET GRILL

5 1 880701-413 WIRED SF PANEL

6 2 880723-531 COVER

7 2 880728-15 EVAP ASSY

8 1 880732-23 HOSE ASSY

9 1 880732-27 HOSE ASSY

10 2 AN821-8D ELBOW

11 4 MS27039-1-11 SCREW

12 6 MS27039-1-20 SCREW

13 1 TIGLS1-1C-WHC SWITCH

CK141-1-511

Airplane Models 690C Serial Numbers 11730-11735, two evaporatorsat rear pressure bulkhead.


1 1 8 008 16-9 503 WIRE SET (2 EV)2 1 850665-513 PANEL

3 1 880697-5 GRILL ASSY

4 1 880701-413 WIRED SW PANEL

5 1 880718-55 PANEL

6 1 880718-57 PANEL

7 1 880718-61 PANEL

8 2 880723-531 COVER

9 Z 880728-15 EVAP ASSY

10 1 880732-23 HOSE ASSY

11 1 880732-27 HOSE ASSY

12 2 AN821-8D ELBOW

13 4 AT405B CAP SWITCH

14 3 MLW3022 SWITCH

15 1 MLW3028 SWITCH

16 4 MS27039-1-l1 SCREW

17 Z MS27039-1-20 SCREW

CKf41-2-525

Airplane Models 690C and 695 Serial Nunbers 11600-11718 and

95000-95084, one evaporator at rear pressure bulkhead and one

evaporator inside sideways facing observer seat.

ITEM NO. PTY PART NUMBER DESCRIPTION

1 11FT 1/2ID-X-3/BWALL #ZARMAFLEX INSL

2 1 1250340 SPLIT EVAP ASSY

3 1 3708 VENT

4 1 800816-9501 WIRE SET (2 EV)

5 1 850618-501 PANEL

6 1 862064-501 ESCUTCHEON

7 1 880697-29 GRILL ASSY

8 i 880697-31 DOUBLER

9 1 880700-75 TUBE ASSY

10 2 880701-11 BRRCKET

11 1 880701-17 SW PLATE ASSY

12 1 880701-9 SPACER

13 1 880718-101 ANGLE

14 Z 880723-531 COVER

15 1 880728-19 EVAP ASSY DUAL

16 1 880732-37 HOSE ASSY

17 1 880732-39 TUBE ASSY

18 1 880712-41 HOSE ASSY

19 1 880732-43 HOSE ASSY

20 1 880737-11 SCREEN

21 1 880737-13 BRACKET

22 1 880737-15 NAMEPLATE

23 1 880737-3 ANGLE

24 1 880737-7 ANGLE

25 1 880737-9 ANGLE

26 1 880741-1 HZO DEFLECTOR




30 1 AN81j-8D UNION FLARE

31 2 AN821-8D ELBOW

32 4 MS24621-18 SCREW

33 3 MS27039-0812 SCREW

34 6 MS27039-1-11 SCREW

35 2 MS27039-1-20 SCREW

36 1 NW2W2S12-72-6 DUCT

37 1 NW21v’2S14- 72-6 DUCT

38 4 S0333A6-20C SCREW

39 1 VZZOOD4 SOCKET WIGGINS

40 1 VZZOjD4 NIPPLE WIGGLNS

41 1 VEC2OOD8 SOCKET WIGGINS

42 1 VEC205D8 NIPPLE WIGGINS

CKI4I-Z-535

Airplane Models 690C Serial Numbers 11719-11729, one evaporatorat rear pressure bulkhead and one evaporator inside sidewaysfacing observer seat.


1 11FT 1/2ID-X-3/8 WALL bZARMAFLEX INSL

2 1 1250340 SPLIT EVAP ASSY

3 1 370B VENT

4 1 800612-1 DOUBLER

5 1 800816-9501 WIRE SET (2 EV)6 1 850618-501 PANEL

7 1 862064-501 ESCUTCHEON

8 1 880697-5 INLET GRILL

9 1 880700-75 TUBE ASSY

10 1 880701-9 SPACER

11 2 880701-11 BRACKET

12 1 880701-17 PLATE

13 2 880723-531 COVER

14 1 880728-19 EVAP ASSY

15 1 880732-37 HOSE ASSY

16 1 880732-39 TUBE ASSY

17 1 880712-41 HOSE ASSY

18 1 880732-43 HOSE ASSY

19 1 880737-11 SCREEN

20 1 880737-13 BRACKET

21 1 880737-501 PLACARD

22 1 880737-7 ANGLE

23 1 880737-9 ANGLE

24 1 80737-15 NAMEPLATE




28 2 AN821-8D ELBOW

29 3 MS27039-0812 SCREW

30 4 MS27039-1-l1 SCREW

31 6 M527039-1-20 SCREW

32 1 NW2W2S12-72-6 DUCT WIRE REINFORCED

33 1 NW2W2S14-72-6 DUCT WIRE REINFORCED

34 4 S0333A6-20C SCREW

35 1 TIGLS1-1CWHC SWITCH

36 1 V2200D4 SOCKET WIGGINS

37 1 V2205D4 NIPPLE WIGGINS

38 1 VEC200D8 SOCKET WIGGINS


CK141-2-537

Airplane Models 690C Serial Numbers 11730-11735, one evaporator

at rear pressure bulkhead and one evaporator inside sideways facingobserver seat.


11FT 1/2ID-X-3/8 WALL #ZARMA FLEX

2 1 1250340 EVAP ASSY

3 1 3708 VENT

4 1 800816-9503 WIRE SET (2 EV)5 1 850665-513 PANEL

B 1 862064-501 ESCUTCHEON

7 1 880697-5 GRILL ASSY

8 1 880700-75 TUBE ASSY

9 2 880701-11 BRACKET

10 1 880701-17 SW PLATE ASSY

11 1 880701-413 WIRED SW PANEL

12 1 880701-9 SPACER

13 1 880718-55 PANEL

14 1 880718-57 PANEL

15 1 880718-61 PANEL

16 2 880723-531 COVER

17 1 880728-19 EVAP ASSY

18 1 880732-37 HOSE ASSY

19 1 880732-39 TUBE ASSY

20 1 880732-41 HOSE ASSY

21 1 880732-43 HOSE ASSY

22 1 880737-11 SCREEN

23 1 880737-13 BRACKET

24 1 880737-15 NAMEPLATE

25 1 880737-7 ANGLE

26 1 880737-9 ANGLE


28 3 AN73 7TW107 CLAMP

29 1 AN73 7TW114 CLAMP

30 a AN821-8D ELBOW

31 4 AT4058 CAP SWITCH

32 3 MLW9022 SWITCH

33 1 MLW3028 SWIICH

34 3 MS27039-0812 SCREW

35 4 MS27039-1-11 SCREW

36 2 M527039-1-20 SCREW

37 1 NW2W2S12-72-6 REINFORCED DUCT


39 4 S0333A6-20C SCREW





II

CK141-3-541

Airplane Models 690C and 695 Serial Numbers 11600-11735 and

95000-95079, one evaporator at rear pressure bulkhead and one

evaporator inside R/H bar.


r 11FT I/2ID-X-3/8 WALL #ZARMA FLEX

2 1 125 0200-31 EVAPORATOR ASSY

3 1 3708 VENT

4 1 800816-9501 WIRE SET (2 EV)5 1 850618-501 PANEL

6 1 862064-501 ESCUTCAEON

7 1 880697-29 GRILL ASSY

8 1 880698-47 PLATE. EVAP MTNG

9 1 880700-67 HOSE ASSY

10 1 880700-69 TUBE ASSY

11 1 880700-71 TUBE ASSY

12 2 880701-11 BRACKET

13 1 880701-17 PLATE

14 1 880701-9 SPACER

15 1 880718-101 ANGLE

16 1 880723-531 COVER

17 1 880728-19 EVAP ASSY DUAL

18 1 880732-37 HOSE ASSY

19 1 880732-45 TUBE ASSY

20 1 880732-47 HOSE ASSY

21 1 880737-11 SCREEN

22 1 880737-13 BRACKET

23 1 880737-15 PLACARD

24 1 880737-3 ANGLE

25 1 880737-7 ANGLE

26 1 880737-9 ANGLE

27 1 880741-1 H2O DEFLECTOR




31 1 AN815-8D UNION FLARE

32 4 AN821-8D ELBOW

33 4 MS24621-18 SCREW

34 6 MS27039-1-11 SCREW

35 2 MS27039-1-20 SCREW


37 1 S0333A6-20C SCREW

38 1 TIGL51-1CWHC SWITCH





special tools: Enviro System test box (800816 test box)Freon system charging equipmentGround pressurization test cart

Micro shaver and sheet metal riveting tools

Digital Temperature meter 0-2000C

Electrical connector insertion/extraction tools

and crimping tools

P/N 32447(SANKYO) dipstick

NOTE:

PERsoNNEL uHo ARE NOT FAMILIAR WITH THE ENVIRO AIR CONDTTIONINO SYSTEM ARE

ADVISED TO REAO THE RELEVANT PAGES IN CHAPTER 21 OF THE AIRPLANE MAINTENANcE

MANUAL TO FAMlLTARIZE THEMSELVES PRIOR TO cOMMENOEMENT OP THIS MoOIEIcATIoN.

IN ADDITToN, PLEASE ENSURE THAT REFERENCZ: TS MAGE TO THE DRAWTNDS PRoVLDEO

FOR SPECTFTED TORC~UE VALUES WHEN ASSEMBLING THE NEW COMPONENTS.

Accom~lishmant InstructionsPrior to commencement of this kit it is strongly recommended that

the modification center obtains a list of existing discrepanciesfrom the flight crew. These discrepancies should be identified

by the maintenance personnel prior to flight crew departure.Airplane should be weighed prior to commencement of modification

to obtain a base line. Pressure check cabin as follows prior to

removal of cabin interior or Sundstrand unit.

(a) Remove static line from cabin pressure controller and

cap off port on controller. Attach a gauge calibrated in

inches of water to the static line to read cabin

pressure. Set rats selector knob on cabin pressurecontroller full clockwise position.

(b) Connect ground pressurization test cart to recirculationair duct in empennage.

(c) Remove sound proofing from R/H side wall of baggagecompartment to gain access to pneumatic system manifold.

(d) Connect an external air pressure source regulated to

18 +/-1 PSI to the inlet side of the cross

containing the overpressure switch.

NOTE;

THIS AIR SOURCE IS TO INFLATE THE DOOR SEAL.

WARNING:IT IS IMPRACTICAL TO SECURE THE PA88ENaERICREsr DOOR 80 THAT IT

CANNOT BE OPENED FROM THE OUTSIDE. Tr 58 RECOMMENDED THAT WHILEPERFORMINa GROUND PRESSMIZATION CHECKS THAT LIAFEOVRRDB BE TAKEN TO

PREVENT SOMEONE FROM OPENING THE MAIN CABIN DOOR. OPENINe DOOR WITH

CABIN PRESSZRRISED. TO ANY DEGREE. WILL CAUSE CONSIDERABLE BODILYHARM AND DESTRUCTION TO EOUIPMENT. PLACE SIGNS AROUND THE AIRPLANE.

PUT TAPE ACROSS DOOR HANDLE. SEAtINO HANDLE IN CLOSED POSITION.

HAVE PRESSURIZATXON CONTROL PERSONNEL INSIDE THE AIRPLANE AND ENSUREELECTRICAL POWER 18 8ELECTED ON AND THAT DOOR LOCK/UNLOCK SWITCH

LOCATED ON OVERHEAD SWITCH PANEL TS DEPRESSED TO THE DOOR LOCK

POSITION.

(e) Set cabin altitude knob full Cow.

(f) Close and secure the cabin door.

YIARNINO:

DO NOT EXCEED MAX ALLOWABLE

DIFFERENTIAL PRESSURE (5.4P9ID Model 695 9

690C) OTXERWISE STRUCTURAL DAMAGE AND

POBBIBLY INJURY 80 PERSONNEL COrrLD OCCUR

(g) slowly increase the pressure on the pressurization cart

until the flow rate reads 100-110 SCFM.

CAUTION:

DO NOT EXCEED 2000 FEET PER MIN OR DAMAGE CAN OCCO~R TO

PRESSURIBATION CONTROLLER.

(h) Record max cabin pressure.

(i) Set flow meter reading to 124 SCFM.

(j) Record max cabin pressure

(k) Record all cabin leaks. Pay particular attention to the

door seal, wing roots,windshields, pitot heads, rudder

pedal boots, control column boots, cabin floor access

panels, rear pressure bulkhead and Top mounted antennae.

CAosXON;

DO NOT EXCEED 2000 FT PER MINUTE OR DAMAGE CAN OCCOR TO

PRESSURIZATION CONTROLLER.

(1) Slowly decrease the pressure on pressurization cart.

(m) Depressurize the aircraft. Do not exceed 2000 ft perminute or damage can occur to pressurization controller.

open cabin door.

(n) Seal all cabin leaks and repeat test until maximum

differential of 5.4 PSID is achieved at 110 SCFM.

(0) Disconnect all test equipment

Alternate method if a pressurization cart is not available

perform pressurization test using bleed air from R/H enginerunning at 90-95% RPM.

(a) Disconnect the static air line at the cabin pressurecontroller and install a needle valve and a piece of

hose in series with the static air line and reconnect

to the controller. See Figure 1.

ENSURE NEEDLE VALVE IS FULLY OPEN

P(rTJ ~ReDBU*O

a,n

WAI

i~LENOID VALVE

1~3

~71

TrP~ROLLBR Ic~sl*

~ermRe

r pl~reR

NOTE: CHECK VA LVE NPT

INSTi~LLED ON MPDEL b90D I I

ANO bj;A AIRPLANEI.

NE30~E VA LVE

FIGURE 1

WARNING

PRE88rmIBA~ION SYBTEM CANNOT BE CONTROLLED ELECTRICALLY

(b) Close and secure cabin door

(c) Start R/H engine and set rpm to 90-95% using normal

starting procedures in P.O.H.

(d) Disconnect ground power unit.

(e) Turn on R/B generator h cabin bus.

(f) Trip cabin depress circuit breaker.

(g) Set cabin rate knob fully clockwise altitude select

knob fully counter clockwise.

(h) Set max flow switch to off.

(i) Select bleed air switch to L/H closed and environmentalmaster switch to on.

(j) Close needle valva slowly, pressurize cabin to max

differential.

CAUTION:

Do NOT EXCEED 2000 FT PER MTII OR ORMAOE CRN OCCUR To

CONTROLLBR´•

(k) Record differential pressure.

(1) Set max flow switch to on. Pressurize cabin to max

differential. Record max differential.

(m) Record all cabin leaks. Pay particular attention to

the following areas, door seal,emergency exit seal,wing roots, windshields, pitot heads, rudder pedalboots, control column boots, cabin floor access panels,rear pressure bulkhead, top mounted antennae.

(n) Open needle valve slowly daprassurize cabin at a

comfortable rate.

CAUTION:

Do NOT EXCEED Z000 rr PER YTNUTE OR DRMRCE CRN OCCUR TO

PRLSIURTZ~LTTON CONTROLZER´•

(O) When cabin altitude is close to field elevation reset

cabin depress circuit breaker.

(p) Verify cabin pressure is zero.

(q) shut down engine using normal procedures.

(r) At completion of pressure test seal all cabin leaks and

repeat test until cabin maximum differential is

obtained using the specified engi~e rpm of 90-95%.

(s) Remove needle valve and reconnect static line to the

cabin pressure controller.

(t) Set cabin rate and altitude knobs back to normal.

NOTE:

If you are unable to obtain max cabin differential then

check the pressure setting or the pressure regulatorshut off valve utilieing procedures found in chapter 21

of the airplane the Maintenance Manual.

In addition check calibrate the cabin differential pressureindicator.

Once cabin sealing integrity is established proceed as follows:

i. Fix weighted tailstand to empennage tie-down.

z. Disconnect remove both A/C bat_eries. Label GPU

socket "do not attach electrical power.

3. Remove all cabin cockpit seats, L/H R/Hcabinets, R/H table if fitted. Retain for re-

installation.

4. Remove cabin cockpit floor carpets. Retain for re-

installation.

5. Remove all trim from rear pressure bulkhead. Retain

for re-work and re-installation.

6. Remove both L/H and R/H cabin head linings. Retain for

re-installation.

7. Remove R/H lower cabin and cockpit side trim. Retain

for re-installation.

8. Remove baggage compartment trim from rear pressurebulkhead, from overhead from R/H sidewall if not

previously removed and retain for re-installation.

9. Remove plenum assy complete with the mixing valve.

Retain for re-work.

10. Working from belly access hatch and through baggagecompartment remove complete Sunds-,rand ECU and its

mountings. Remove baggage compar:ment trim. Supportstructure as required to facilitare easy removal.

11. Disconnect and remove main electrical junction box

assembly. Ensure that all wires are marked to facilitate

re-installation. Disconnect both generator control unit

connectors and remove pin D with its shielded wire intact

from the GCU connectors. Wires to be left in A/C for re-

installation. Utilize correct extraction tool for this

task. Retain electrical junction box for rework and re-

installation.

12. Remove air conditioning muffler and its brackets from

frame Y290; duct from muffler to rear cabin floor 8

discard.

Remove ECU "air in" metal shroud assy from R/H side of

fuselage discard. Leave P/N 880682-7 sealed to fuselageskin. (If CK 134 is already accomplished.)

14. Remove overhead duct transfer tube from beneath baggagefloor and discard.

15. Remove GCU’s, speed switches, prop de-ice timer retain

for re-installation,

16. Disconnect and remove ground power relay, ground power

connector, and over voltage relay. Retain for rework

and re-installation.

17. Remove inverters if location will interfere with L/Hskin doubler installation refer to Dwg.880697, Sheet

#2. Retain for re-installation.

18. Remove bleed air pipe P/N 880656-1 from ECU back to

junction of L/H and R/H engine bleed air pipes. Discard.

19. Place crawling boards across frames to facilitate re-

work in baggage area.

20. (Model 690C only) Remove propeller syncronizationcontrol box mounting plate from rear pressure bulkhead

structure. Do not disconnect electrical wires.

CAUTION;

DO N0T DRILL FASTENERS COBPLETELY OUT-DRILL OFF READS

AND PUNCX OUT 8HANKS.

21. Drill off fasteners in rear cabin floor duct transition

assembly for re-circulation air and cold air for cabin

overhead ducts and remove assemblies discard.

22. Disconnect and remove DC circuit breaker panelassembly(ies). Retain for rework and reinstallation.

23. Disconnect and remove air conditioning control panelassembly. Retain for re-work and reinstallation.

24. Remove L/H cockpit side trim up to side window lower

edge. Retain for re-work and reinstallation.

25. Remove lower flex cold air duct from Y piece at rear

pressure bulkhead and discard.

26. Remove Y piece cold air duct assy and discard.

NOTE i

RETATN UPPER TWO COLD AIR DUCTS IOR RE-WORR AND Re-TNSTWRTION.

27. Sand down L/A fuselage skin between F.S.Y254 F.S.Y310,#5 longeron 6 #9 longeron to reveal fasteners. Use 120 gritsand paper orbital sander. See Figure 2 for location.

28. Remove GPU socket relay bracket assy, 805008 doubler 6

hinge from L/H side of fuselage skin. Drill off heads of

fasteners and punch out shanks. Retain 3ea screws for later

use.

CAOTION:

DD NOT DRILL FASTENERS COMPLETELY GOT-DRILL OFF READS

AND POhlCR OUT 8KANK6.

29. Drill off fastener heads to release fuselage skin

between Y254 Y310, 65 longeron 6 89 longeron as

required to facilitate 880697 -11 doubler

installation. Refer to figure for typical area.

30. (a) Working from leading edge of fuselage skin carefullyinsert 880697-11 doubler between skin stringers and frames.

(b) Position 880697-11 doubler in accordance with Dwg.

880697, Sheet #2. Ensure that 20 edge distance an all

fasteners is maintained throughout.

(c) Mark grill cut out on fuselage skin using 880697-11

doubler cutout as a pattern.

(d) Mark GPU socket cut out on 880697-11 doubler to match

cut out in 800812-1 doubler and fuselage skin. Refer

to Dwg. 880718, Sheet 3, Zone 30A/B.

CAUTION:

ENBURE THAT ZD EDDE DISTMCE ON ALL FABTENERS I8

MAI~TAINED TBROUDWO~I!.

(e) Drill 880697-11 doubler fastener pattern usingfuselage skin existing fastener pattern.

(f) Drill 880697-11 doubler and fuselage skin in accordance

with Dwg.880697, sheet P2.

(g) Drill fuselage skin h 800812-1 GPU socket doubler in

accordance with Dwg. 880718, Sheet Zone 30A/B

(h) Remove 800812-1 GPU socket doubler from airframe.

(i) Remove 880697-11 doubler from airframe.

(j) Open out all holes for rivet pattern as shown on

Dwg’s.880718, Sheet 83, Zone 30A/B and 880697, Sheet

62, In 880697-11 doubler and fuselage skin De-burr all

holes and remove swarf from rear of fuselage skin,stringers and frames.

(k) cold dimple all fastener holes in 800812-1 GPU socket

doubler.

(1) Using a router bit cut fuselage skin grill cut out

where previously marked and smooth edge of cut out.

(m) Using a router bit cut 880697-11 doubler CPU socket

cut out where previously marked. Clean up cut out.

(n) Cold dimple all fastener holes in 880697-11 doubler.

to) cold dimple all new holes in fuselage skin.

(p) Position 880697-13 longeron doublers I.A.W. Dwg. 880697,Sheet B1. Drill off fasteners pattern and remove-13

doublers.

(q) Position 880697-11 doubler between fuselage skin,stringers and frames I.A.W. Dwg.880697-1l, Sheet #2.

Cold Dimple 880697-13 doublers.

(s) Position 880697-13 doublers I.A.W. Dwg.880697,Sheet 81.

(t) Postion 800812-1 doublers I.A.W. Dwg.880718, Sheet g3.Zones 30A/B, zone 29A/B and zone 28A/B.

(u) Install rivets to fuselage shin, 880697-13, 800812-1

880697-13 doublers I.A.w. Dwgs. 880697, Sheet #1 and

Sheet 62, 880718 Sheet 63 zones 28, 29 30A/B.Ensure that 0.12 die hole thru fuselage skin 880697-

11 doubler is left open for drainage purposes see

Dwg.880697, Sheet Il for location adjacent to F.S.

Y272.00.

(v) Install 880697-5 grill assy I.A.W. Dwg. 880697, Sheet bl.

(w) Build up 800675-501 bracket assy with componetsremoved from old GPU socket bracket assy. TogetherWith new bus bar 800697-511 I.A.W. Dwg. 880718, Sheet

63, Zone 32 A/B.

(X) Install GPU socket access door hinge and associated springs.

(y) Install built up 800675-501 bracket assembly I.A.W.

Dwg.B80718, Sheet I), zone 28, 29, 30 A/B. Utilize

previously removed 3ea attaching screws.

31. Install 880709-13 shroud assy to inside of L/Hfuselage skin between F.S. Y272 Y290 I.A.W. Dwg.880709, Sheet 12. Seal all edges of shroud assy to

structure using coast proseal 890 or equivalent two partsealer to obtain good water tight seal.

32. Fit 880708-35 hose to 880709-13 shroud assy utilizingAN737TW22 clamp. Install AN737TW22 clamp to other end

of hose for later installation to 880708-21 pan assy.See Dwg.880708, Sheet B1, Zone 3E.

33. (a) Make cut out in fuselage skin at F.S. Y259 2-9.65 on

R/H side of fuselage I.A.W. Dwg. 880734, Sheet 81.

(b) Install 880734-3 Tube assy I.A.W. Dwg.880734,Sheet II.

(c) Install 880734-9 Placard I.A.W. Dwg.880734, Sheet bl.

34. Gain access to R/H side of fuselage skin between

F.S. Y272.00 Y290.00 6 betveen #’s 9 10

longerons.

Turn off Ozbottle at bottle and purge system by operating02 masks in cockpit.

CAUTTON:

OXY(IEII L~NE Is LOCRTED TN IDNBERON´• DO NOT DAMAGE OXYGEN

LTNE WHTLE: DRTW.INO OR RIYETTNO.

(a) Make skin cut out using a router I.A.W. Dwg.880724,Sheet BZ.

(b) Install 880724-1 flush scoop assembly I.A.W. Dwg.880724, Sheet #2. All fastener locations to be

cold dimpled prior to installation. It is permissibleto use BB4 in lieu of LZ4 rivets.

(c) Install 880724-19 longeron doublers inside longerons#’s 9 Io I.A.W. DWg.880724, Sheet 62.

~a´•:

a-

I--´•´•,

ORIGINALAs Received By

ATp

PHOTO 1

23

35. Ascertain if Custom Kit 134, improved inlet air supplysystem, has been accomplished on aircraft model

690C Serial Numbers 11600 thru 11718 model 695

serial Numbers 95000 thru 95084. If C.K. 134

has been accomplished on your aircraft or serial

number is not affected than disregard this step and

proceed to step 36. If CK-134 is to be accomplishedproceed as follows.

(a) Follow instructions on page 2 of C.K. 134 steps 3, 4

11, 13 (but only install 880682-7 shroud assy to

fuselage skin. e~ not install 880682-3 closure or

880682-15 as these are reguired). Step 15,

16 8 17. Refer to CK-134 Figures 1 2.

NOIE:

IT IS PEIUIISSIBLI TO USE BB4 IN LIEU 01 CR22~8-4-) BLTND

RIVETS

36. Airplane model 690C Serial no’s 11600 thru 11718 model

695 serial numbers 95000 thru 95084 only, modify3)0387 Avionics lower access door as follows:

(a) Make cut out in door skin to match 880697-)1 doubler

I.A.W. Dwg.880697, Sheet t5.

C~LIITION:

ENBURE TKAF 8RORT VERTICAL PORTION OF 880741-1 WATER

REFLECTOR Is FAClEO FORI~ARDB.

(b) Attach grill and doubler assy together with 880741-1

water deflector assy to inside of 330387 access door

I.A.W. Dwg.880697, Sheet 65 and Engineering Order 880697

ADV R Sheet #2 and 880741 Dwg.

(c) Trim away portion of 330387 Avionic access door to 0.95

2.60 dimensions as shown on Dwg.880725, Sheet P1, Zone 4,5 6 A/B.

(d) Install MS21266-1N grommet using EC1403 adhesive or

equivalent 1.A.W. Dwg.880725, Sheet B1, Zone 4, 5 6

A/B. Retain door for later installation.

37. Airplane model 690C serial no’s 11719 thru 11735

modify rear avionic lower access door 310957-35 as

follows:

(a) Make cut out in 310957-35 door assy I.X.W. Dwg.880697, Sheet 83.

(b) Install 880697-5 grill assy I.A.W. Dwg.880697, Sheet

3.

~ea

o...,

IEB tYILTjI11 nacesl

mn~ue Bp I~LBS

ijjji

muraoLT~uruESiX)ROUE 5e’10 IKLBS

YODULEUOUHTINO PL4TPORU

dIFT ~O*leR CUIEL

R´•monl M ImDl~a ot Uod~

FIGCRE

25

NOTE:

4164 FUSEBLOCK SHOWN ON DWG. 880708, SHEET ~1 HAS BEEN

SUPERCEDED BY CIRCUIT BREAKER PANEL 860816-17 SHOWN ON

PHOTOGRAPH 62 AND SHOULD BE INSTALLED IN PLACE OF THE

FUSE BLOCK.

,s. (a) Build up Freon compressor shelf in accordance with

Dwg.880708, Sheet bl h photograph. See Dwg. 800816

Sheet #1 for C.B. panel build up.

NOTE:

PRY PARTICULAR ATTENTION TO VIEW CC,DD ZONE 90 OF

DWD 880708.

(b) Place built up freon compressor shelf assy into rear

of airplane. Install at L/H side of fuselage between

fuselage stations Y272 Y290 I.A.W. Dwg.880708, Sheet

#r.

(c) Install 880708-35 hose using AN737TW22 clamp to 880708-

21 drip pan I.A.w. Dwg.880708, Sheet B~1, Zone 3F.

(d) Install compressor 1250400-15 Rev H or subsequenton built up shelf assy I.A.W. Dwg.880708, Sheet

#1, Zone 22D 23C. Torque mounting bolts to 50-

70 inch ibs

NOTE i

IT WILL BE NECESSARY TO REMOVE THE BOLTS AND REFIT TBEH

TO THE LTDHTENED wee 880708-15 IN oRDER To INSTALL

COMPRESSOR CONDENSOR MODULE ASSY. TORPUE WEB BOLTS TO

20-25 IN LBs. SEE FIDURE 3.

(e) Check oil level of Compressor as follows: (See Figurea)

Dipstick P/N 32447 (SANKYO) or equivalent, will be requiredto check the oil level in the compressor. If oil leak is

noted, check compressor oil level as follows:

NOTE:

THE COMPRESSOR iS SHIPPED TO TWIN COMMANDER FULLY CHARGED WITH

THE CORRECT PUANTTTY OF SUNISO NO. 5GS OIL; THEREFORE, NO OTL

LEVEL CHECK IS REPUTRED UNLESS THERE IS A NOTICEABLE OIL LEAK FROM

THE COMPRESSOR AND/OR AIRPLANE SYSTEM.

NOTE:

STEPS F THROUGH H BELOW ARE NECESSARY IN ORDER TO CLEAR THE

DTPSTTCK OF INTERNAL PARTS ANO ALLOW TTS INSERTION To FULL DEPTH.

(f) Remove the oil filler plug. Look through the oil

filler plug hole and rotate the clutch front plateto position the internal parts as shown in figure 4.

______ ____ __ __

OIL PILLER‘Im*uw mmesoo *ora wm*n~ aumcsoR

uourmla *NOLE LEFTDUNTINO INOLE IICHT

~OD BI~LL

aoo

isnn SDCXFF OW

I’

saLL9DOxEIONnurEiPurr KINar n*ra

orraesson(TO~VIEII)

*aamm imaa atom uxlmn~i Lnrnmw r~slmi Nnal nmen rnane unal

OIL PILLERm3LE

a

c~ oil ha

FIGURE 4

17

(g) Compressor mounted to the right (facing clutch).Center the parts as they are moving to the rear of

the compressor (discharge stroke).

(h) Compressor mounted to left (facing clutch).Center the parts as they are moving to the front

of the compressor (suction stroke).

(i) Insert the dipstick (P/N )2447) to its stop position.The stop is the angle near the top of the dipstick.

NOTE:

OIL LEVEL SHALL BE BETWEEN DTPSTTCK INCREMENTS 4 AND 6.

(j) Remove dipstick and note increments of oil on

dipstick.

(k) Service compressor, as required, with SUNISO No.

5GS or Texaco Capella E Oil (500 viscosity).

(1) Install oil filler plug.

39. Place previously removed electrical main junction box

into position. Check to see if circular relay K1,clears recently installed compressor-condenser module

support. If relay X1 does clear the support remove

main electrical junction box once more. If relay K1,does not clear support then remove Main electrical

junction box and modify as follows:

(a) Remove K1 relay from relay base

NOTE:

DO NOT DISCONNECT ELECTRICAL WIRES.

(b) Remove K1 relay base from side of junction box.

(c) Install new relay angle P/N 880718-101 inside main

junction box r.n.W. Dwg.880718, Sheet #3, Zone 30E.

(d) Cut Tywraps as necessary from electrical bundle and

relocate relay base for relay K1 to -101 angle.

(e) Install relay K1.

NOTE:

1. EXISTING WIRING 15 SHOWN AND NEW WIRING WITH A

SoLrD LINE. WIRING AND TERMINAL ENDS ARE PROVIDED IN DARTS KIT.

2. AIRPLANE SERIAL NUMBERS 11616~ 11617, 95022, 95023,

95024, 95025, INSTALL K39A K40A 833038-505 RELAYS, AS

SHOWN ON DWG.800816, SHEET 14, ZONE 7, AND 8AB.

(f) Modify main electrical junction box wiring I.A.W.

Dwg.800816, Sheet #4, Zones 4D, 5D.

(g) Re-install main electrical junction box using retained

hardware. Reconnect all disconnected wires.

(h) Re-install Generator control unit panel below main

junction box. Install shielded wires into Pin 0 (usecorrect insertion tool for this task) of both L/H and

R/H control unit connectors. Ensure L/H and R/Hconnectors receive correct wires. Refer to relevant

schematic in wiring diagram manual. Re-install all

connectors and wires to panel.

40. (a) Connect wires from main electrical junction box to

External Power Control panel and to Compressor module

circuit breaker panel, I.A.W Dwg.B00816, Sheet #4,Zones 3, 4, 5, c D.

(b) Connect wires between Compressor Condenser module

and circuit breaker panel mounted on CompressorCondenser module structure.

(c) Connect ground wire from Compressor ground stud to

frame at F.S. Y290.

NOPE:

RETAIN WIRES X52R22 AND H52B22 PRoH REGULATOR SHUT OI‘B

VALVE AND ENVIRONMENTAL SWTTCW PRNEL FOR LATER USAGE.

a. cut back wires from duct tamp sensor and dead end

close to rear pressure bulkhead.

b. Remove cabin temp sensor controller from above

emergency exit. Cap and stow connector. Remove temp

sensor/controller from trim panel and discard. Refit

trim panel.

41. Remove relays KY36 and K46 located L/H side of center

line between F.S. 272 and 290 cut back wiring as close

to rear pressure bulkhead as practical and dead and.

Remove wiring from relay K46 and Temp control valva.

42. Install channel assy 880722-505 between F.S. Y290.00

and F.S. Y308 I.A.W. Dwg.880718, Sheet #2, Zones 9 10

A. Thru F views BE CE and zone 20 D, E F. Make

certain that anchor nut plates for KRA relay are

positioned towards rear of aircraft as shown in zone

20E of Dwg.B80718.

NOTE;

PORTION OF TUBE TO BE REMOVED BY CUTTING IT OFF FLUSH.

43. Modify previously removed 880653 plenum assy I.A.W.

Dwg.880726, Sheet bl.

(a) Install 880723-515 tube assy I.A.W. Dwg.880718, Sheet

#2, Zone 19, 20 C D. Use sealant RTV red high tampor equivalent between joints.

(b) Remove 5.62" of L/H side tube and drill holes I.A.W.

DWg.880726, Sheet 81.

(c) Install 880723-1 blank I.A.w. Dwg.880718, Sheet #2,Zone 19C, 11C view JJ. Use sealant RTV Red high tempor equivalent between joints.

(d) Retain modified plenum assy for later installation.

NOFE;

ENSURE 0001) ELECTRICAL BOND BETWEEN AIRCRAFT STRUCTURE AND

BRACKET ASSY BY BURNTSHTNO THE MATING SURFACES AND APPLYING A

sRrrsH COAT OF ALOOINE 600. USE BONDING BRUSH TO BURNISH

EPUIPHENT MOUNTING HOLES.

44. (a) Install 880735-3 Bracket Assy between F.S. Y29000 and

Y308 on L/H side of fuselage I.A.W. Dwg.880735, Sheet 82.

45. Models 690C s/n’s 11600-11729 695 s/n’s 95000-95084

proceed as follows:

(a) Disassemble removed circuit breaker panel to

provide access. Remove 5 amp circuit breaker

identified as TEMP AUTO and replace it with 2 ampcircuit breaker P/N 7277-5-2-12-507-61 provided.Install 800816-7 Placard marked ECS BLD AIR over

circuit breaker.

(b) Remove 5 amp circuit breaker marked TEMP OVRRD and

replace it with 2 amp circuit breaker P/N 7277-5-2-12-

507-61 provided. Install 800816-5 Placard marked TEMP

CONTROL over circuit breaker.

NOTE:

IT TS PREFERABLE TO CONNECT CTRCUTT BREAKER DIRECTLY TO blDrsTnrsvTlon BUS BAR. HOWEVER IF A SPARE LOCATION IS NOT

AVAILABLE TO ACHIEVE THIS THEN USE 80370-501 JUMPER TO CONNECT

CB TO DISTRIBUTION bl BUS ERR.

(c) Find any unused (open) circuit breaker position and

install 2 amp circuit breaker P/N 7277-5-2-12-507-61

provided. Circuit breaker must be connected to

Distribution B1 bus bar.

(d) Connect other side of circuit breaker to any unused

pin in connector P7 CB1 using 20 guage wire. Install

800816-3 placard marked FLOW CONTROL over circuit

breaker.

(e) Install cabin temp sensor 1300440-1 I.A.W.

Dwg.880718, Sheet #3, Zone 40 CB.

(f) Reassemble circuit breaker panel and place aside for

later installation.

46. Model 690C S/Ns 11730 thru 11735 find previouslyremoved L/H and R/w cB panels.

(a) Disassemble L/H circuit breaker panel as required to

gain access. Locate CB labelled temp AUTO. Remove 5

amp CB and install 2 amp circuit breaker. Install

800816-7 placard over circuit breaker.

(b) Install 7277-5-2-12-507-612 amp circuit breaker in

any spare location and connect to Distributor #1 bus

bar. Vtilize 50370-501 jumper if necessary to connect

CB to correct bus bar. wire r.A.W. Dwg.800816, Sheet

#2, Zone 6D. Install placard TEMP CONT. P/N 800816-5

over circuit breakers.

(c) Dissassemble R/H circuit breaker panel as necessaryto gain access. Locate CB labelled Temp OVRD. Remove

CB and replace with 2 amp cB P/N 7277-5-2-12-61.~nsta11

placard 800816-3 over circuit breaker.

(d) Install cabin temp sensor 1300440-1 I.A.W. Dwg.880718, Sheet g3, Zone 40 CB.

(e) Install cabin temp sensor on lower surface of R/Hcircuit breaker penal I.A.W. Dwg.880718, Sheat 83,Zone 40 DE.

(f) Reassemble circuit breaker panels and place aside for

future installation.

NOTE:

VALVE ASSY IS INSTALLED ON AFT SUPPORT CHANNEL

AT F.S. Y290.00.

47. Mount 880718-79 assy which includes 1300330

modulating Y valva to Compressor Condenser supportstructure I.A.W. Dwg.880718, Sheet #2, Zone 13 EF,and Dwg.880718, Sheet 65, Zone 61-69.

BOTE:

VALVE IS INSTALLED ON OVERHEAD FRAMES.

48. (a) Install 1300490 Flow Control valve between F.S. Y254

and F.S. Y272 I.A.W. Dwg.880718, Sheet ~5, Zones 66-

68.

(b) Connect up NW2W2S-5-102-4 duct to valve and 880734-1

tube I.A.W. Dwg.880718, Sheet 82, Zones 19, 20, 21, AB.

~I

Received ByAfP

PHOTO 2

32

NOTE:

SEE ZONE 7 6 15 FOR TYPICRL INSTAL;ATTON. USE EXISTING CLAMPS

AND HAROWRRE FOR INSTRLLRTI~ON.

49. Refer to Dwg.880726, Sheet %1. Install 880656-3 tube

assembly insulate tube assembly joints with ~PC2300-

WFELT and cover insulation with heat shrink tubing I.A.W.

Owg.880657, Sheet BL. Use existing clamps and hardware for

installation.

50. (a) Install bleed air shut off valve P/N 1588-00-1.

Connect valve to 880656-3 tube assy installed in step49.

(b) Install 880718-17 tube assy between shut off valve and

1300490 flow control valve I.A.W. Dwg.880718, Sheet 52,Zone 18, 19, AB. Insulate valve with RPC2300-W FELT.

cover insulation with heat shrink tubing T.A.W.

Dwg.880657, Sheet 63, Zone 45 and sheet 81, Zone 15 for

typical installation.

51. (a) Install tube assy 813333-6-12 between 1300490 flowcontrol valve and 880718-5 (or -25 as applicable) tubes

I.A.W. Dwg.880718, Sheet ~2, Zone 19 CD.

(b) Install ST3333-6-12 tube to other end of 880718-5 (or25 as applicable) and connect to 1300330 temp modulatingvalve T.A.W., Dwg.880718, Sheet 82, Zone 13FG.

52. Install 880722-1 angle assy at F.S. Y290.00. Use

existing hardware I.A.W. Dwg. 880718, Sheet 62, Zone

1), 14 C and 18-20 D.

53. (a) Install 813333-6-12 tubes on ends of muffler P/N1300520-1 using clamps I.A.W. Dwg.880718, Sheet #2,Zones 19, 20 D-F. Place muffler in position thru F.S.

Yzs0 from lightning hole ready for connection to heat

exchanger and temp modulating valve.

(b) Build up heat exchanger ground blower assy I.A.w.

DWg.880718, Sheet IZ and photograph 12 opposite.

(c) Install heat exchanger ground blower support structure

I.A.W. Dwg.880718, Sheet #2 Zone 11-21.

54. (a) Install ground blower/heat exchanger duct assemblybetween F.S. Y290.00 and F.S. Y308. Use mounting boltsand washers provided (4 each) I.A.W. Dwg.880718, Sheet

#2, Zones 11 thru 21 and Figure 5.

(b) Connect 880718-9 tube between temp modulator Y valve

and muffler 1300520-1 I.A.W. Dwg.880718, Sheet #2, Zone

14 19, 20 D.

’´•H) NUT ~ND ZE~L-FORaVe NUI ItPBYm

(NLLIS*NU ~FETI WIAE1NO FITTINB

CUYP

mA(IUE1Cp

CLIYP UISBROW 1 IKLBS(PPLSInose

NBE EUUPTOROUE(I-?2

INLBS(1PLS)CUUP

~e SCRCIYINOLOCKWISHEA

~YCT NBE ~s"*usenr~m

eree~*ln m YOOUL*TIHaYILVEN8E O

EXI(IYSIOVIRBO.

TORaUE 30~0 I,LIIS 12 PL~I

OUCTHase~ \Y~HOSEr2PLS,

CULIPronoUElcn~ ~nhrm r4~ V _CL)IUPIrc~escaPrs,, II ru8e ronous~a.n

IbLas(~prs)

OUCTISS’IH09E Y IY H09E

NBE

NBEIJSICLIYP

CUUP(ZPLBJ TOR~UB (622

IKL89(2PLS~UUFFLER

RIYIIRSCOOP .I ;UBE CUUP HEITEXOHINOERTOR(IUE(bl~IKLBS(ZPLS)

UBIH*(RDISTRIBMONPLEHUy

TeYPeRINAe9eN90R

FIGUIIE 5

51

(c) Connect 880718-19 tube between aft end of 1300520-1

muffler and heat exchanger cutlet T using 5T3333-6-12

tube and clamps I.A.W. Dwg.880718, Sheet 62, Zone 19F.

(d) Connect 880718-7 tube to tamp modulating valve and heat

exchanger using 513333-6-12 tubes and clamps route -7

tube thru opening in compressor/condenser module drippan l.R.w. Dwg.B80718, Sheet 82, Zone 19.

(e) Connect duct NC22S16-50-6 between 880724-1 scoop and

ground blower heat exchange assembly I.A.W. Dwg.88o718,Sheet #2, Zone 15.

(f) Install KIIA relay MS24166-D1 to 880722-505 channel withbolts and washers provided I.A.W. Dwg.880718, Sheet #2,Zones 20, 21 E.

(g) connect up red wire from ground blower to KT(A relayand black wire to ground on frame F.S. Y308 I.A.W.

Dwg.800816, Sheet #4, Zones 3, 4 8. Utilize red rubberterminal protectors.

55. (a) Install previously modified cabin air distribution

plenum assy 880653 with 4 bolts previously removed.See Figure 5 (21-60-01 202) Model 690C or695 MM.

(b) Connect up lower cabin air ducts (2 each) to plenumusing existing hardware.

(c) Install 1300450 duct sensor provided in same locationas old duct sensor on plenum assembly. Utilize sealantRTV Red nigh Temp or equivalent between plenum and ductsensor to ensure a gas tight joint.

(d) Install 880718-11 tube assembly between heat exchangeroutlet T and plenum assembly using ST5333-6-12 tube and823333-7-12 tube and clamps I.A.W. Dwg.880718, Sheet

#2, Zone 17 GH and zone 19, z0. Install mounting clampMS2~919-DG38 I.A.W. Dwg.880718, Sheet X2, Zone 11 H and

Zone 20 D. Move avionic wire bundle outboard toward

R/H side of fuselage to facilitate tube installation if

necessary.

56. Cut hole in rear pressure bulkhead I.A.W. Dwg.800816,Sheet bl, Zone 4C for new wire bundle. Cut hole in310868-57 cover to match hole in rear pressure bulkhead.cut hole in 310868-55 nut plate doubler I.A.W. Dwg.800816,Sheet #3, Zone 4C. Assemble doublers to pressure bulkheadwith MS35206-230 screws provided. Install MSZ1266-3N

grommet as shown on Dwg.800816, Sheet #1, Zone 4C.

57. (a) Cut two holes in rear pressure bulkhead for freon hose

fittings I.A.W. Dwg.880732, Sheet 84, Zone 6, 7D.

(b) Install tee fittings in rear pressure bulkhead as

called out on Dwg.880732, Sheet #4, Zone 7B. Do not

tighten tee fittings at this stage as they must be

sealed and oriented to suit later installation of

evaporators.

(c) Install 880732-19 and -zl hose assemblies between Tee

fittings on rear pressure bulkhead and freon compressorI.A.W. Dwg.880732, Sheet 64, Zone 4, 5 AB and views 8,C D. Hose assemblies between compressor and clamps at

FS Y272 frame may be marriage Ty-wrapped in place(To any convenient structure or bracketing). Hoses are

routed overhead to R/H side of fuselage and then alongfuselage side to rear pressure bulkhead.

(d) Lightly coat flares at compressor end with refrigerantoil and apply a small amount of thread sealant to

fitting and install fittings on compressor receiver

dryer assembly. (stay clear of first 2-3 threads).Torque fittings to 160-200 inch ibs.

(e) position tee fittings at rear pressure bulkhead to

facilitate easy installation of evaporator hoses on

forward side of rear pressure bulkhead. Tighten T

fitting nuts on rear side of rear pressure bulkhead and

seal around fittings to prevent cabin pressure loss.

Use coast pro-seal 890 or equivalent.

(f) Install hoses 880732-19 21 to T fittings at rear side

of rear pressure bulkhead. Lightly coat flares with

refrigerant ail and apply a small amount of thread

sealant to fitting threads (stay clear of first 2-3

threads).

NOTE:

ENSURE THAT A 0000 ELECTRTCAL BOND EXTSTS BETWEEN CONTROLLER AND

MOUNTTNO BRACKET.

58. (a) Install mass flow controller 1300360 an bracket

assembly L/LI side of fuselage between F.S. Y290.00

and Y308. NE. Mass flow controller is fitted forward

of cabin temp controller refer to Dwg.880735, Sheet #2.

Utilize MS35206-231 screws and AN960-6 washers

provided.NOTE:

TEMP CONTROLLER TS MOUNTED AFT 01 MASS FLOW CONTROLLER. ENSURE A

DOOD ELECTRICAL 8oND EXISTS BETWEEN CONTROLLER AND BRACKET

ASSEMBLY. UTTLTZE MS35206--23L SCREWS AND AN960D6 WASHER

PROVTOED. REFER TO DW0.880735~ SWEET 82.

(b) Install cabin temp controller 1300350 on left hand side

of fuselage between F.S.Y 290.00 and Y 308.00.

NOTE:

ENSURE R GOOD ELECTRICAL BOND EXISTS BETWEEN FLOW SENSOR

AND BRACKET ASSEMBLY. ORIENTATE CONNECTOR TO REAR OF A/C.

(c) Install mars flow sensor 1300464 to bracket assemblyL/H side of fuselage between F.S. Y290.00 and Y308 aft

of cabin temp controller utilize M935206-231 screws and

AN960-6 washers provided.

CAVTION:

Use EXTREME CAUTION WHenr INSTWTNO PROBE´• DO NOT BEND´•

(8) Route flow sensor wires along avoinics shelf lower

support and install flow sensor probe in 880718-11 tube

assembly I.A.W. Dwg.880718, Sheet 62, Zones 20 DE and E

and View EE, Zone 24. Ensure that red protective cover

is removed. Utilize AN503-6-8 screws and AN960-D6

washers. Seal between faces with RTV red high tempsealer RTV KD 492 or equivalent.

NOTE:

IT TS PERMISSIBLE TO UTILIZE PSEVIoUSLY RETAINED WIRES CODED

H52A22 AND H52B22 FOR ENVIRONMENTAL SHUT OFF VALVE OR TO

UTTLIZE NEW WIRING PROVTDED. ROUTE WIRING CLEAR OF CONTROL

CABLES AND BLEED ATR DUCTS. UTILIZE TYWRRP STRAPPING AS REPUIRED.

TIE WIRE BUNDLE ALONG AVIONICS SHELF WITH AVTONTCS WIRING BUNGLE

AND ROUTE ALONG R\H SIDE OP FUSELAGE WITH AVIONICS WIRING TO REAR

PRESURE BULKHEAD T.A.W. AC43.13.1A. REFER TO DWG.800816,SHEET 3 FOR MODELS 690C S/N 11600 THRU 11729 AND 695 S/N95000 THRU 95084. REFER TO OWG.800816, SHEET #2 FOR MODEL

690C S/N 11730 THRU 11735.

ENSURE THAT TEMP AND FLOW CONTROLLER RND FLOW SENSOR SHIELDING

GRouND WIRES ARE CONNECTED I.A.W. NOTE 10 ON DWG.880816,SHEET #2 OR ~3 AS APPLICABLE. CONNECT ENVTRO WIRING TO CB

PANEL AND ENVIRONMENTAL CONTROL PANEL AND ANNUNCIATOR PANEL

CoNNECToRS I.A.W.RELEVENT DWG.800816. ANY EXTSTTND WIRES

WHICH HAVE TO BE REMOVED FROM CONNECTORS SHOULD BE REMOVED

COEIPLETELY FROM THE A/P OR TERMINATED AT BOTH ENDS WITH

WIRE CAPS AND STOWED.

59. (a) Install enviro wire bundles thru rear pressure bulkhead.

Utilize hole installed in step 57. Feed wire bundle from

rear of pressure bulkhead forward with connectors for

controllers and valves aft of pressure bulkhead. Connect

up wiring to temp and flow controllers, Duct temp sensor,

temp modulating valve, mass flow sensor, mass flow valve,and environmental shut off valva.

(b) Install wire AC12C14 between KRA relay Al terminal

(ground blower relay) and 20 amp R/A circuit breaker on

800816-17 panel mounted on compressor/condensor module

structure I.A.W. Dwg.8008L6, Sheet 14.

37

(c) Install wire ACLA2O between KRA relay Terminal X2 and

Terminal strip TA4 located R/H side of baggagecompartment behind trim. Install S~A2 diode between

wire AC1A2O and TA4 I.A.W. Dwg.800816, Sheet 64.

(d) Install Diode S3A2 across terminals XI, X2 of KRA relayas shown on Dw9.800816, Sheet P4.

(e) Install wire AC2A to terminal X1 of KRA relay and placethru rear pressure bulkhead with wire bundle I.A.W.

Dwg.800816, Sheet 14.

(f) Install wire AC1OA from compressor power relay mounted

on compressor shelf and Terminal 11 of X39 inside main

junction box I.A.W. Dwg.80oQ16, Sheet 64.

(g) Install wire AC4C16 to lo-press switch on compressorcondenser module and thru rear pressure bulkhead hole

I.A.W. Dwg.800816, Sheet #4.

(h) Install wire AC9B16 to 15 amp EB circuit breaker on

800866-17 panel mounted on compressor/condensor module

support structure route wire thru hole in rear pressurebulkhead.

(i) Install bus feeder wire between main bus bar inside

main electrical junction box and lOSamp circuit breaker

mounted on 800816-17 panel I.A.W. Dwg.800816, Sheet#4.

(j) Install wire AC3A14 to K66 relay A2 terminal and 15 ampcircuit breaker mounted on 800816-17 panel I.A.W.

Dwg.800816, Sheet 64.

(k) Install wire AC1OBZO to K39 relay terminal 11 and K88

terminal nZ external PWR control relay I.A.W.

Dwg. 800816, Sheet R~4.

Seal wire bundle thru rear pressure bulkhead with Coast

Pro-seal 890 or equivalent.

60. (a) Take previously removed environmental control panel and

re-wire I.A.W. Dwg.800816, Sheet 83, for Models 690C

S/N’s 11600 thru 11729 and 695 S/N’s 95000 thru 95087.

Utilize existing switches, new switches and potentiometerprovided. For Model 690C S/N’s 11730 thru 11799 re-

wire I.A.W. Dwg.800816, Sheet #2. Refer to new facia

panel for location of switches. See sketch for

clarification.

BLgTCH IS DRRWN VTEIYED IFROM REAR WITB TOP OP PANEL

DOWMIRRDS

ENVIRO CABIN 5 MASS

MASTER DEPRESS 6 15 MANUAL TNCR FLOW

OFF OFF OFF SPRTNG OFF

LOADEO

CENTEI(

OFF

ON ON POTENTTOMETER ON ON

NORMAL AUTO OEC8 LOW

22 1 10 I 11 16 1 1 I ONL

14 1 8 17 11 I 1 12 30

Il 11 13 f 1 GND 1

x Terminal with a wire1 Terminal not used

(b) Remove switch guard from old overlay panel and install

on new overlay panel in same location.

61. Remove master annunciator panel front and remove lampbulb from position labelled ECU press. Refit panelfront.

62. Cut hole on L/H side of cockpit side wall trim for

freon control panel I.A.W. Dwg.880701, Sheat 82. -503,-507 installation. Ensure that top edge of PNL assy

aligns with AC circuit breaker panel top edge. Do not

fit panel assy at this stage. See step 75 later.

63. (a) Install 880708-29 drain assembly I.A.W. Dwg.880718,Sheet #3, Zones 38, 39, ABC to fuselage lower skin on

center line at F.S. Y175.8.

(b) Install 0.56 Dia hole thru floor at F.S. Y175.8 on

canter line.

(c) Install 850718-43 hose to drain assembly and thru 0.56

dia hole. Seal around hole with coat pro-seal 890 or

equivalent.

64. For those airplanes that are to receive 2 evaporatorsmounted at rear pressure bulkhead proceed as follows:

(a) Install 880730-7 and 880730-9 covers in place of floorduct assemblies previously removed at F.S. Y178 I.A.W.

Dwg.880730, Sheet /1, Zones 13,14, I5.A. Seal between

-7 and -9 covers with coast Pro-Seal 890 or equivalent.

39

NOTE:

CENTER OF L/H EVRPOIULTOR IS INSTALLED ON CENTER LTNE OF THE

R~RPLANE.

(b) Install 880728-5 and 880728-7 evaporator support Tee’s

I.A.W. Dwg.880728, Sheet II.

(c) Install evaporators to 880728-5 and 880728 Tee’s I.A.W.

Dwg.880728, Sheet ~1, and Dwg.880730, Sheet P1, Zone

13-15 A/B. Utilize screws MS27039-1-08 and AN 9600

blOL washers.

CAUTION;

USE REPRTOgRANT OTL ONLY ON IITT~N(IS. DO NOT USE PILRAFTN

BRSE O~L OR OIIERSE´•

(d) Connect up freon hoses to rear pressure bulkhead Tee

fitting and evaporators I.A.w. Dwg .880732, Sheet 84.

(e) Connect up drain hoses I.A.W. Dwg.880718, Sheet 13,Zones 37, 38, ABC.

(f) Install Prop sync control box to side of R/H evaporatorI.A.W. Dwg.880730, Sheet P1, Zones 15, 16, 17b.

Relocate wires on adjacent ground block as required to

facilitate installation. (Model 690C only)

(g) Connect up evaporator fan wiring to connectors 1-

480305-0 (2 each) I.A.W. Dwg.800816, Sheet #4, Zone 4

A/B. Find wires AC9A16, GND1B (2 each) AC8A16, AC7A16,AC6A16. connect these wires to plugs 1-480303-0

which mate with connectors 1-480305-0 I.A.W. Dwg.800816, Sheet 84, Zone 4 A/B.

(h) Install wire AZA20 to cabin bus bar at rear pressure bulkhead

R/H side. Utilize any spare location. Install 1 amp fuse

provided. See Dwg.800816, Sheet 4, Zone 6D.

65. Models 690C S/N’s 11600-11718 and 695 S\N’S 95000 thru

95084 proceed as follows:

(a) Make cut outs in upholstery and mirror at rear pressurebulkhead I.A.W. Dwg.880730, Sheat i, Zones 6-9 F/G and

view B Zone 4, 5, 6, C, D, E.

(b) Install 880727-501 and -502 louvre boxes I.A.W.

Dwg.880730, Sheet bl, Zone 6-9 F/G and view B Zone

5/6C, D, E.

(c) Connect ducts X6687 between evaporators and louvre

boxes installed in step b/ I.A.W. Dwg.880730, Sheet B1,Zones 13, 14.

(d) Inspect L/H and R/H overhead cabin panels for air

system integrity. Repair or replace any damaged ducts

or air transition units prior to installation. Ensure

air system is leak free.

(e) Shorten existing l/h and r/h overhead cabin panel ducts

to mate with new louvre box outlets I.A.W. Dwg.880730,Sheet P1, Zones lo, 11, F/G.

66. (a) For Model 690C S/N’s 11719 thru 11735, make cut outs in

upholstery and mirror at rear pressure bulkhead I.A.W.

Dwg.880730, Sheet bl, zones 12-15 and view ’A’ Zones 7-

10 A, B 8 C.

(b) Install 880727-501 502 louvre boxes I.A.W.Dwg.880730,Sheet 81, Zone 12-15 FG view ’A’ Zone 7-10 ABC.

(c) Connect ducts X6687 between evaporators and louvre

boxes installed in step b/ I.A.w. Dwg.880730, Sheet #1,Zone 13 &14.

(d) Inspect L/H and R/H overhead cabin panels for air

supply system integrity. Repair or replace any damagedducts or transition units prior to installation.

Ensure air system is leak free.

(e) Shorten existing L/H and R/H overhead cabin panel ducts

to mate with new louvre box outlets I.A.W. Dwg.880730,sheet Il, Zones 10/11 F G.

67. Airplanes which install a single evaporator at the

rear pressure bulkhead proceed in accordance with

Dwg.880730, Sheet R1, Zone 11 12 for difference

from a evaporators at rear pressure bulkhead. In

addition, steps 66 or 67 as applicable by model and

serial number should be embodied.

BOTE;

DTFWRENCE FOI1 2 EVAPORATOR TNSTALLATToN AND SINGLE EVAPoRRToR

INSTRLLATION

68. Modify previously removed 860988 rear pressure bulkhead

lower equipment cover I.A.W. Dwg.880730, Sheet 82: Zone

30-32 A, B C. Retain cover far later installation.

69. Airplanes which are to install an evaporator inside the

sideways facing observer seat opposite the main cabin

door proceed as follows:

(a) Modify previously removed observer seat I.A.W

Dwg.880737 Sheet #1. Follow instructions for -501

installation.

(b) Install 880694-23 drain assy I.A.W. Dwg.880694engineering order S, Sheet II, for location and

Dwg.880694, Sheet Il, Zone 7A view B. Seal around

880694-63 drain hose at floor with coast pro-seal 890

or equivalent.

CAUTION:

Do NOT UBE PRRRPIN BASED GRERSE OR OIL ON PTTTINDS´•

USE ONT~Y RBP~RTDERENT OIL. BLANK OP~r FORWRRD FTTTINDS.

(c) Route freon hose assemblies from rear pressure bulkhead

tee connections forward along R/B side of fuselage to

sideways facing seat location I.A.W. Dwg.880700, Sheet

#9. Connect up hoses at rear pressure bulkhead Tees.

70. (a) Route electrical wire bundle from inside rear pressurebulkhead forward along R/H side of fuselage to cockpitinstrument panel. Tyrap wire bundle as required to

provide support. I.A.W. AC43-13-1A Refer to

bwg.8008l6, Sheet #3 for Models 690C S/N’s 11600 thru

11729 and 695 S\N’s 95000 thru 95084. Refer to

Dwg.800816, Sheet g2 for Model 690C S/N’s 11730 thru

11735.

(b) Identify from relevant sheat of Dwg.80o816 wires to be

connected to P27 connector which is for the

environmental control panel. Route wires in 1/2’flexguard behind instrument panel. Removal of the

radar indicator will assist with routing. Route wires

to circuit breaker panel connectors I.A.W. Dwg.800816relevant sheet.

(c) For Models 690C S/N’s 11600 thru 11729 and 695 S/N’s95000 thru 95084 proceed as follows:

Find wire H62A22 from pin 22 of connector P14 of

annunciator panel. Join new wire H62A22 to this

existing wire and connect other end of wire to

pin L of P27 environmental control panel connector

I.A.W. Dwg.800816, Sheet 63.

(d) Model 690C S/N’s 11730 thru 11735 find wire H62AZZ in

P170 Pin 12 of annunciator Master caution unit. Join

new wire H62AZZ to this existing wire and connect other

end of wire to pin L of P27 environmental control panelconnector I.A.W. Dwg.800816, Sheat #2.

71. Connect fwd cabin temp sensor connector PT06CE-8-45 to

wires from digital temperature computer pins 14 and 34

and ground wire I.R.W. DWg.800816, Sheet BZ or Sheet #3

as applicable by Medal and serial number. Connect wire

H39sii from circuit breaker connector to fwd cabin

temperature connector I.A.W. Dwg.800816, Sheet 62 or #3

as applicable by Model and serial number.

72. (a) Find wires AC9A16, AC8A16, AC7A16, AC6A16 previouslyconnected to evaporator fans at rear pressure bulkhead

route wires along R/H side of fuselage behind

instrument panel to freon system control panel on L/Hside of cockpit install wires into plug 1-48 0283-0 as

shown on Dwg.800816, Sheet g4, Zone 5, ABC.

(b) Find wire AC9B16 and install into plug 1-480283-0

I.A.W. Dwg.80o816, Sheet P4, Zone 5, 6 CD.

(c) Find wire AC4C16 and install into plug 1-48028)-0

I.A.W. Dwg.8o0816, Sheet 64, Zone 48.

(d) Connect all ground wires for control panel and

evaporators I.A.W. Dwg.800816, Sheet %4.

73. (a) Airplanes with dual split evaporator system install

wires AC7A16, AC6A16 from aft evaporator fwd to ACI

plug I.A.W. Dwg.800816, Sheet 14, Zone 4A.

(b) Find wires AC9A16, AC8A16 and install into ACI plugI.A.W. Dwg.800816, Sheet 64, zone 4A. Route wires

behind instrument panel, along R/H side of fuselage to

forward evaporator location. Connect wires to 1-

480303-0 plug.

(c) Carry out steps 73.b/ and c/ for control panel and

evaporators. Connect all GND wires for control paneland evaporators as on Dwg.800816, Sheat P4.

74. Install freon control panel to L/H cockpit sidewall

I.A.W. Dwg.880701, Sheet 61 view AA 507 or -511 as

applicable and shown on Dwg.880701, Sheets B1 and

12 and Dwg.880718, Sheet 53, Zone 39, 40 GH when 3rd

evaporator is installed.

75. Install all upholstery previously removed from cabin area.

76. (a) Install drain assembly I.A.W. Dwg.88od9, Sheet B1 and

E.O. ADV’S’.

(b) Install co-pilots seat before installing bar assembly.

(c) Airplanes which are to install a fwd evaporator inthe R/H bar behind co-pilots seat proceed as follows:

Modify bar assembly I.A.W. Dwg.880698, Sheet ~6.

Install evaporator unit inside bar I.A.W. Dwg.880698,Sheet #6.

CnvTloru:

Do NO~ USE PlU(RPIN BRSeD OIL OR (IRERSe ON FITTTN(ls~ USE

ReFRT(IERRNT OTL ONLY.

(d) Install bar assembly in aircraft and connect upelectrical connector and freon hoses I.A.W. Dwg.800816,Sheet #4 or P6 as applicable and Dwg.880732, Sheet 86

515 installation. Connect up drain assy I.A.w.

Dwg.88 0694, Sheet bl.

77. Airplanes with forward evaporator inside sidewaysfacing lavatory seat proceed as follows:

CAUTION:

Do NOT USE PRRAPIN BRSeD ~RERSe OR OIL ON FITTINDSI USE

REFRToERANT OIT´• ONLY.

(a) Install lav seat assembly in A/P. Connect up

electrical connector and freon hoses I.A.W. Dwg.800816,Sheet #4 or #6 as applicable and Dw9.880732, Sheet P6

511 installation. Connect up drain assembly I.n.W.

Dwg.880694 Engineering order ADV’S’.

78. Install previously modified environmental control paneleither beneath pilots instrument panel or in center

console as applicable. Connect up electrical connector

P27.

79. Model 690C 11600 thru 11729 and 695 95000 thru 95084 proceedas follows:

(a) Install circuit breaker panel beneath cc-pilotsinstrument panel and connect up all electrical

connectors.

(b) Model 690C 11730 thru 11735 proceed as follows:

Install both L/H and R/H circuit breaker panels and

connect up all electrical connectors.

80. Re-install radar indicator if previously removed for

access.

81. Modify baggage compartment structure and ski storagearea I.A.W. Dwg.880718, Sheet #4, Zones 41 thru 49. If

A/P does not have ski-storage area modify only as

directed. Refit baggage compartment floor and carpetall sides and overhead trim.

(a) Install head liner assemblies L/H and R/H. Connect upto ducts at rear of headliner.

82. Install aircraft batteries and function test all

electrical systems. Correct any discrepancies.

83. Install ground power and function test. Correct any

discrepancies.

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NOTE:

PERFoRM STEPS 85 ~ZND 86 CONCURRENTLY

84. Charging Freon Air Conditioning System. (Refer to

Figure 6). The following tools and/or equipment are

required to charge the refrigerant system:

1. small hand tools and socket set.

2. Vacuum pump (0 to 30 In. Hg.)3. R-12 refrigerant (1 Lb cans)4. Charging manifold assembly with gauges and hose.

(Robin air P/N 40153 or equivalent).5. Thermometer (O to 1500F)6. Ground Power Unit.

7. Adjustable inspection mirror.

8. Service light or flashlight.

To charge the freon air conditioning system, proceed as follows:

(a) Verify that airplane and/or external power is OFF.

(b) Remove aft panel from baggage compartment.

NOTE:

WHEN CONNECTING CHARGING MANIFOLD TO COMPRESSOR, THE RED(HIGHPRESSURE) HOSE MUST BE CONNECTED 20 THE PORT MARKED ’D’

(DTSCHARCE) AND THE BLUE (LOW PRESSURE) HOSE MUST BE CONNECTED

TO THE PORT MARKED ’S’ (SUCTION). TO CONNECT OTHERWTSE MAY

RESULT IN DAMROE TO THE LOW SIDE PRESSURE GAUGE.

(c) Connect charging manifold to compressor service ports.

(d) Connect manifold inlet service hose to suction side of

vacuum pump.

(e) Turn pump on, open manifold service valves and evacuate

system for 30 minutes. System should read 25-27 In.

Hg. after 10 minutes.

(f) Close manifold service valves and shutoff vacuum pump.Remove manifold service hose from vacuum pump and

connect to R-12 refrigerant can.

(g) open refrigerant can valve and crack hose fitting at

manifold to purge hose. Open both manifold valves and

charge system with refrigerant until internal system

pressure reaches 10-15 psig. Close manifold gauge

valves and refrigerant valve.

CAUTION:

8YSTEM MUST BE VENTED SLOWLY TO ASSURE THAT TIIE REIRIOE~ANT

OIL TS NOT VENTED OVERBORRD´• EYE AND HAND PROTECTION ~U8a

BE WORN DURING THIS PROCEDURE.

(h) Remove R-12 can from service hose and slowly open both

manifold valves and slowly vent system to zero.

(i) Close manifold valves and reconnect service hose to

vacuum pump.

(j) Start pump and open manifold valves. Run vacuum systemfor a minimum of 45 minutes. System vacuum should read

25 to 27 In. Hg. after 10 minutes operation.

(k) Close manifold valves and shut off vacuum pump. Remove

service hose and connect to a one (l) pound refrigerantcan.

(1) Observe vacuum gauge for 5 minutes to assure no leaks

or no excessive moisture is in system.

NOZ~E:

If loss of vacuum is noted, a system leak check or

re-evacuation will be required. If the systempassed the leak check, the only reason for vacuum

change would be excessive moisture in the system.Repeat steps a/ thru 1/.

(m) If there is no change in vacuum, connect the manifoldservice hose to a one (1) pound refrigerant can and

open the valve.

(n) Crack service hose fitting to purge air out of hose,turn can to position with outlet pointed to the groundand open both manifold valves. Allow liquid contents

of can to enter system and repeat this step until two

(2) cans of refrigerant have been consumed or systempressure is stabilized.

NOTE

IT TS IMPORTANT AT THIS POINT TO KNOW THE EXACT PIIANT~TY OF REFRIGERANT

FOR EACH AIRPLANE SYSTEM TO ASSURE THAT AN "OVE8 CHARGE" CONDTTION GOES

NOT OCCUR OR THE SYSTEM SHOULO BE CHARGED ON R HOT OAY (90-1050F) TO

ASSURE a PROPER PVANTTTY WITHOUT OVER CHAI(OT~NG.

(O) Close manifold valves and verify system pressure is

greater than 50 psig. Record, at this time, the number

of one (1) pound cans of refrigerant consumed.

(p) verify that system electrical controls are in the OFF

position. Connect a ground power unit capable of 28

V.D.C. and 200 Amp capacity to airplane electrical

system.

(q) Turn GPU power ON, place evaporator blower speed to

high and turn system power ON.

(r) With system operating, observe the suction and

discharge pressures and refrigerant condition in

receiver-dryer sight glass. Excessive bubbles

indicate low refrigerant level.

(s) With new refrigerant can connected to the manifold

service hose, slowly open the suction (blue) manifold

valve and allow refrigerant to enter system through

compressor

NOTE:

AS REFRIGERANT ENTERS COMPRESSOR, TRE SUCTION PRESSURE WILL

TNCREI\SE AND A SLIGHT INCREASE IN DISCHARGE WILL BE NOTED.

COMPRESSOR SPEED WILL BE REDUCED SLIGHTLY ALSO.

(t] Continue to add one (1) pound cans of R-12 refrigerantper above procedures until the required system chargeis loaded or until the receiver-dryer sight glass is

clear of excessive bubbles.

(u) Let the system operate for 5 to 10 minutes and observe

sight glass. If excessive bubbles appear, add a slightquantity of refrigerant until clear. Close suction side

manifold hose (blue) and close refrigerant can valve.

HAND RND EYE PROTECTION SHOULD Be WORN DURING Tars

OPERATION DUE TO HI(IH PRESSURE REFRIGERANT vENTTNG RT

veRY COLD TEMPERRTURBS´• BLIN RNm EYEB MUST BE

(v) Slowly vent service hose from can and remove from can.

(w) Allow system to operate for a minimum of is minutes

and observe compressor suction and discharge pressures.

Typical values at various ambient temperatures are

shown below:

SUCTION DISCHARGE

O.A.T. PRESSURE (PSIG) PRESSURE (PSIGI

Selow 800F 29 140-150

800F z8 (c/-2) 195 (c/-10)

900F 32 215

l00OF 34 230

(x) Check evaporator air inlet and outlet temperatures to

determine proper refrigerant distribution. The

evaporators must be balanced to obtain equalperformance. To balance the evaporators, refer to

balancing procedures as outlined in Step 88.

(y) cover both compressor service valves with shop rag and

quickly remove both suction and discharge hoses.

Disconnect charging manifold from compressor.

(z) Disconnect GPU from airplane.

NOTE:

IF NECESSARY PERFORM LEAK CHECK I.A.W. STEP 87.

85. Balancing Evaporator Module. The following equipmentwill he required to balance evaporator modules:

Ground power unit capable of 28 VDC and 200 Ampcapacity.

2. Service manifold with gauges and hoses.

3. Thermometer O to 1500 F.

To balance evaporator modules, proceed as follows:

(a) Connect a ground power unit capable of 28 VDC and 200

Amp capacity.

(b) Verify that system leak check and refrigerant charginghas been performed and system is operating within

typical values as outlined in System Chargingprocedures in this chapter.

(c) Remove all covers from evaporator modules. Each

evaporator module expansion valve must be accessiblefor this operation.

(d) Remove evaporator module blower outlet ducting and

expansion valve protective cap.

(e) Verify that evaporator coil inlet is free of

contamination or debris which could reduce air flow.

(f) verify blower speed switch is in "high" position.

(g) Verify service manifold gauges and hoses are connected

to compressor-condensor module and system is operatingnormally.

(h) Place air conditioner switch to AIR COND. Verify Ac

light illuminates.

(i) Close cabin door and measure each evaporator blower

outlet temperature and air inlet temperature. Normal

air temperature difference is 25 5) degrees F.

NOTE:

NORMALLY THE EVAPORATOR MODULES CLOSEST TO THE COIIPRESSOR-

CONDENSOR MODULE WILL INOTcRTE A LOWER BLOWER OUTLET TEMPERATURE

THAN OTHER MODULES. ALSO IF AN EVAPORATOR MODULE HI\S A LOWER

BLOWER OUTLET ATR FLOW, THE ATR TEMPERATURE WILL ALSO BE LOWER

THAN A HOO(ILE WTTH HIGH ATR FLOW. THEREFORE, EVERY EFFORT

SHOULD BE MADE TO OBTAIN EPUAL RIR FLOW FOR ALL EVAPORATORS.

(j) After all evaporator module outlet air temperatures are

recorded, the data must be reviewed to determine which

evaporator module expansion valve should be adjusted.

NcTE:

The variance of blower outlet temperature between

evaporator modules can be 20F with out any

adjustment required. However, 100F

difference will require some adjustment.

(k) To lower the outlet air temperature, the expansionvalve adjustment control must be turned clockwise. The

adjustment should be turned slowly and only 1/4 turn.

(1) Note outlet air temperature again and verify that the

compressor suction pressure stays within the limits of

26-34 psig during adjustment. If not, the unit with a

low outlet temperature must have its expansion valve

turned 1/4 turn counterclockwise to offset the increasein suction pressure and at the same time have the same

outlet air temperature as the other unit.

(m) The adjustment procedure is complete when all

evaporators have approximately the same outlet

temperature ZoF) and the compressor suction

pressure is well within desired limits.

(n) Operate system to stabilization or 10 minutes, then

shut systems off.

to) Connect evaporator blower outlet ducting.

(p) Install protective caps on evaporator expansion valves.

(q) Install covers on evaporator modules.

CAUTION:

IPREN PBNORMTNO TEE FOLLOWING STEPI RAND RND EYE PROmECTTON

SBOULD BE WORN DUE TO BTOB PRESSURE REFRIGERANT VENT AT VERY

COLD ~EMPERATURES´• BKIN RND EYES MIST BE PROTECTED.

(r) Cover both compressor service valves with clean shoprag and quickly remove both suction and discharge hoses

from compressor service valves.

(s) Remove all test equipment and disconnect ground powerunit.

86. Leak Check Freon Air Conditioning system (Refer to

Figure 6). The following tools and/or equipment will

he required to leak check the refrigerant plumbing:

1. Gaseous dry nitrogen-regulated source.

2. Charging manifold with gauges and hose. (Robin air

P/N 40153 or equivalent)3. Halogen leak detector (TIF5000 or equivalent)4. Refrigerant R-12 (1 Lb cans)5. Small hand tools and socket sat.

6. R-12 can service valve.

7. Leak check fluid (soapy-water).

TO leak check the refrigerant plumbing, proceed as follows:

(a) Verify that all plumbing connections are tight andelectrical power is OrF.

CAUTION:

WEEN CONNECPCTNOrHe CRRROlNC DYWIIIOLDI TEE RED (RIDBPRESSURE) 8088 MUST Be CONNECTED mo rHE PORT MARRED "o"

(DISCBRROe) RND THE BLUE (LOW PRESSURE) BOSE MUST BE

CONNECTED To TaE PORT MARRED 1’8" (SUCT~ON)´• ~O CONNECT

oTHERWISE MAY RESULT IN DRMRBE TO TEE LOW SIDE PRESSURE OAUOE.

(b) Connect charging manifold to R-12 compressor service

ports and charge inlet hose to refrigerant can servicevalve and bleed refrigerant into system until pressureis stabilized.

(c) close manifold and R-12 service valves.

(d) Remove R-12 can and connect service hose to regulatednitrogen source.

CAUTION:

Do NOT OYER CBRR(IE SYSTEM OR DAMAOe MAY ReSUL~´• RE(I1IWITE:

NTTROGEN INTO SYSTEM SLOWLY´•

(e) Open manifold valves and regulate nitrogen into systemto 250-255 psig.

(f) Apply soapy leak check fluid to all refrigerantplumbing connections and observe for major leaks.

CAUTION’

DO NOT OYER TT(IRTEN PLUMBING CONNECTIONS. STRIPPED 2´•BREADS

OR CRACKED FLARES MAY Re8ULT´•

(g) Wipe off soapy liquid and use halogen leak detector tofind small R-12 leaks. Tighten joints as required.

CAUTION:

SYSTEM MUST BE VEhPEED SLOWLY TO ASSURE TBRT COMPRESSOR OIL IJ

NOT VENTED OVERBOARD WIT8 ReFR~OERRNT´• DO NOT WOW RIR TO

ENTER SYSTEM´•

(h) with system leak tight, vent system slowly to remove

all nitrogen and/or refrigerant. Shut nitrogen systemoff.

(i) Disconnect service hose to nitrogen and reconnect to R-12 can and pressurize system until pressure is stable.

(j) close manifold valves and remove R-12 can. Slowly openboth manifold valves and vent system to 2-5 psig.

87. Perform after installation check out using groundpressurization cart if available. Cabin must reach max

differential in normal flow if it fails to do so

repair cabin leaks as required.

(a) Connect pressurization cart to aft connection of heat

exchanger so that air flow is routed forward thru flow

sensor.

(b) Connect an external air pressure source regulated to

18PSI 1PSI to the inlet side of the cross

containing the over pressure switch located behind the

R/H side baggage compartment trim. In order that the

door seal may be inflated.

(c) Using the enviro system test box connect a VOM to pinsC(+ve) and D(-VE) of the mass flow sensor.

(d) Connect an auxilary power unit to the A/P external

power receptacle 28.5 (c/-.5) VDC.

(e) Remove the static line from the cabin pressurecontroller and cap the static port on the controller.

Attach an H20 meter to the static line. Sat rate

selector knob on cabin pressure controller to full

clockwise position.

(f) Set start mode select switch to CPU/PAR position(battery switch also turned on if required).

(g) Verify that the flow cent. circuit breaker is IN.

87. (h) Close and secure cabin door.

WARNING i

IT IS IMPRACTICAL TO SECURE THE PAEIIENBERICREI DOORBO

THAT TT CANNOT BE OPENED P~ROM THE OUTSIDE. IT I8

RECOMMENDED THAT WHILE PER1"ORMINO O~OUND PRESBURIZATION

CHESKB THAT BAFEOIIRRDB BE TAREN TO PREVENT SOMEONE BROM

OPENIND THE MAIN CABIN DOOR. OPENIN(I DOOR WITH CABIN

PREQS[I~IBED, TO ANY DECREE. WILL CAUSE CONSIDERABLE

BODILY HARM AND DESTRUCTION TO EOUIPMENT. PLACE SICiN8

AROUND THE AIRPLANE. PUT TAPE ACROSS DOOR HANDLE.

HANDLE IN CLOSED POSITION. HAVE PRESSURIZATION

CONTROL PERSONNEL INSIDE THE AIRPLANE AND ENSURE THAT

DOOR LOCKIUNLOCK SWITCH, LOCATED ON OVERHEAD SWITCH

PANEL. IS DEPRESSED TO THE DOOR LOCK POSITION.

WARNING

DO NOT EXCEED MAXIMUM ALLOWABLE DIFFERENTIAL PRESSURE

OF 5.4 P91D OTHERWISE STRUCTURAL DAMAGE AND POSSIBLE

INJURY TO PERSONNEL COULD OCCUR.

PRESSURIBATION SYSTEM CANNOT BE CONTROLLED

ELECTRICALLY WREN CABIN DEPRESS CIRCUIT BREAKER 18

TRIPPED. PUSAINO CIRCUIT BREAKER IN WILL CAUSE RAPID

DECOMPRESSION, IPHICR MAY CAUSE INJURY TO PERSONNEL.

DO NOT OPEN MAIN CABIN DOOR WXILE AIRPLANE 18

PRES8URTgED. SERIOUS INJURY TO PERSONNEL AND DAMAGE

TO EOUIPMENT CAN OCCUR.

(i) Trip cabin depress circuit breaker

CAUTION;

Do NOT EXC&ED 2000 PT PER MINUTE CRBIN RATE OF DESCENT

OR DAMADE CAN OCCUR TO PRESSURIZATION CONTROWIER´•

Wtre~ CABIN PRESSURE BAS SICRBILTZPD RECORD: FLOW MITER

RERDINO ON PRESSURIZATION CART SCFM (SPECTFIC CUBTC

FEET PER MTMPPE)´•

(j) Slowly increase the pressure on pressurization cart

until flow sensor voltage reads 4.15 VDC (low flow)

Flow Sensor VDC

Cabin pressure H20 meter psid

NOTE:

H20 METER REAOINO DIVIOED BY 27.8 EPUAiS CABTN

PRESSURE IN PSID.

(k) Adjust air flow until flow sensor voltage reads 4.71

VDC (max flow). When cabin pressure has stabilizedrecord:

Flow meter SCFM

Flow sensor VDC

Cabin Pressure_

(HZO meter) PSID

Do NO~ EXCEED 2000 FT PER MIN OR DAMAGE CAN OCCUR TO

PRESSURIZATION CONTROLLER.

(1) Slowly decrease the pressure on the pressurizationcart and depressurize the A/c.

(m) When the cabin altitude is close to field elevation

and no further rate of climb is noted reset the cabin

depress circuit breaker. Verify that the vacuum pump

operates, dumping any remaining cabin pressure.

(n) Open cabin door.

(O) Switch off ground power and internal batteries.

(p) If it was not possible to obtain maximum cabin

differential in low flow repair cabin leaks.

(q) Reconnect static line to cabin pressure controller.

(r) Remove all test equipment attached to the A/C for this

test and set cabin pressure controls back to normal.

(s) If a ground pressurization test cart is not available

proceed I.A.W. Step 91.

88. Post installation pressurization test with enginesrunning.

NOTE:

STEPS 91 AND 92 IIAY BE CONOIICTED CONCURRENTLY. ENSURE LOWER

MODI~FIED AVToNIc DOORS RRE REFTTTED PRTOR TO TEST.

CAUTION:

ENSURE PHAT NEEDLE VALVE IS IN FULL OPEN POBITION.

IF NEEDLE VALVE I8 CLOSED AND TEE PREssURISATION

8Y8TEM Is ACTIVATED PRESSURIBA’PION NILL START

IMMEDIATELY AT API DhlKNOWN RATE.

(a) Disconnect the static air line at the cabin pressurecontroller and install a needle valve and a short

piece of hose in series with the static air line and

reconnect to the controller. See Dwg.880736, Sheet 9,Figure II.

(b) Using the enviro system test BOX connect a VOM to pinsC (cVE) and D (-VE) of the mass flow sensor.

(c) Close and secure cabin door.

(d) Start both engines using normal procedures in Pilots

operating Handbook.

(e) set RPM on both anginas to 85% RPM.

(f) Disconnect ground power unit if utilized.

(g) Switch on both generators and cabin bus switch.

WRNINO

PRESSURIZATION SYSTEM CANNOT BE CONTROLLED

ELECTRICALLY WHEN CABIN DEPRESS CIRCUIT BREAKER IS

TRIPPED. POSHINO CIRCUIT BREAKER IN WILL CAUSE

RAPID DECOMPRESBION. WHICB MAY CAUSE INJURY TO

PERSONNEL. DO NOT OPEN MAIN CABIN DOOR WHILE

AIRPLANE IS PRESSDRSBED. BERIOUS INJURY TO

PERSONNEL RND DAMAGE TO EOUIPMENT CAN OCCUR.

ENSURE THAT NEEDLE VALVE IS IN FULL OPEN POSTION.

IF NEEDLE VALVE I8 CLOSED AND TAE PRE8LiURI4ATION

SYSTEM IS ACTIVATED. PRE88URIaA’EION NILL

IMMEDIATELY AT AN UNKNOWN RATE.

(h) Trip cabin depress circuit breaker.

(i) Set cabin pressure rate knob fully clockwise and

altitude select knob fully counterclockwise.

(j) Set bleed air switch to both oPEN and environmental

master switch to DN.

(k) Set mass flow switch to LOW.

CAOTION:

DO NOT EXCEED 2000 FT PER MIN OR DAMAGE CAN OCCUR TO

PRE88m(IZA~ION CONTROLLER

(I) Close needle valve slowly until cabin is pressurizingat a comfortable rate.

(m) Pressurize cabin to max differential and record cabin

PSID Flow sensor VDC.

(n) select mars flow control to max verify max flow

annunciator illuminates on annunciator panel.

to) when cabin has stabilized record:

Cabin --PSID

Flow Sensor VDC

(p) Select mass flow control switch to normal

CAUTION:

DO NOT EXCEED 2000 FT FEB MIN MAXIMUM OR DAMADE CAN

OCCUR 90 PI1E98rmT4ATION CONTROLLER

(q) Open needle valve slowly and depressurize cabin (2000ft per min maximum).

(r) When cabin altitude is close to field elevation reset

cabin depress circuit breaker. Verify that vacuum

pump operates, dumping residual cabin pressure.

(5) Shut down engines utilizing normal procedure in Pilots

operating Handbook.

(t) If it was not possible to reach maximum differential

with normal flow selected, then repair any cabin

leaks. Repeat test

(u) Remove the needle valve and reconnect the static line

to the controller.

(v) Set cabin pressure rate knob and altitude selector

back to normal.

(w) Remove Enviro test box from system.

91. Post installation test with engines running.

(a) Close and secure the cabin door.

(b) Start both engines using normal starting procedures.

(c) Set RPM on both engines at 65 to 70 percent.

(d) Disconnect auxiliary power unit.

(e) Turn on bath generators, cabin bus switch, and air

conditioner switch.

i. verify that air conditioning system is operating.

(f) Turn right generator switch OFF.

I. Verify that air conditioner compressor stopsoperating.

(g) Turn right generator switch ON.

1. Verify that air conditioner compressor starts to

operate again.

(h) Turn left generator switch OFF.

I. Verify that air conditioner compressor stopsoperating.

(i) Turn left generator switch ON.

I. Verify that air conditioner compressor starts to

operate again.

(j) Monitor pilots left and right amp meters with the air

conditioner switch off and with the air conditioner

switch on.

The combination current increase on both amp

meters should be approximately 80 amps or more,

but no more than 1~5 amps.

(k) Set bleed air switch to BOTH CLOSE and select

environmental master switch to ENVIR MASTER (OFF).

i. verify that there is no air flow at floor

outlets.

(I) Set bleed air switch to BOTH OPEN.

i. verify that there is still no air flow into

cabin.

(m) Sat bleed air switch to BOTH CLOSE.

(n) Set Mass Flow Control switch to LOW.

to) Set Temperature Control to full counterclockwise

position.

(p) select environmental master switch to ON.

(q) Set bleed air switch to RIGHT CLOSE.

i. Verify that there is air flow at floor outlets.

(r) Set bleed air switch to LEFT CLOSE.

i. verify that there is air flaw at floor outlets.

(s) Set bleed air switch to BOTH OPEN.

i. verify that there is air flow at floor outlets.

(t) Set mass flow control to MAX position.

i. verify that there is an increase in air flow at

the floor outlets.

2. Verify that MAX FLOW annunciator is illuminated.

fu) Set mass flow control to LOW.

i. Verify that there is a decrease in air flow at

the floor outlets.

2. Verify that MAX FLOW annunciator is extinguished.

(v) Rotate temperature control full clockwise.

i. Verify that temperature at floor outlets increases.

(w) Rotate temperature control to full counterclockwise

position.

i. verify that temperature at floor outlets decreases.

(x) Place temperature control in MANUAL position and press

INCR and hold for 10 seconds.

I. Verify that temperature at floor outlets increases.

(y) Press DECR and hold for 10 seconds.

1. verify that temperature at floor outlets decreases.

90. Install enviro test box between temperature and flow

computer connectors. Connect ground power to the A/Cand select ground power and A/C batteries ON. Place

switch to test position. Operate toggle switch to

bypass and to exchange and verify that temp modulatingY valve operates. Operate flow toggle switch to openand close and verify that mass flow valve runs from

full open to full close and vice-versa.

If system does not operate correctly see trouble

shooting section for corrective adtions.

(a) Disconnect squat switch mechanically and ensure squatswitch controls ram air blower. If blower fails to

shut down when squat switch is extended inspect TA4 in

baggage compartment and install S3A2 diodes between

terminals and terminal stud with exception of wire to

squat switch itself and re-check.

91. Trouble shooting guide.

EOUIPMENT REOUIRED

1. DIGITAL VOLT/OHM METER

2. SYSTEM BREAK OUT TEST BOX (800816-TEST BOX)3. OSCILLOSCOPE (ANY BRAND)4. AIRPLANE ELECTRICAL WIRING DIAGRAM OR DRAWING

800816

5. DIGITAL TEMP METER OR EQUIVALENT TROUBLE SHOOTING

STEP REFERENCE

a. NO FLOW/PRESSURIZATION IN CABIN. SEE STEP 1 AND 2.

b. EXCESSIVE FLOW OR HEAT IN CABIN. SEE STEP 2.

c. NO TEMP CONTROL IN AUTO MODE. SEE STEP 3.

d. NO TEMP CONTROL IN MANUAL MODE. SEE STEP 4.

FLOW CONTROL SYSTEM

1. NO FLOW TO CABIN/NO PRESSURIZATTON.

a. VERIFY ENGINE BLEED AIR VALVES ARE OPEN (BLEEDAIR SWITCH IS IN "BOTH OPEN" POSITION). [REF.FIGURE 7]

b. VERIFY ENVIRO MASTER SWITCH IS IN "NORM" POSTION.

[REF. FIGURE 8]

c. VERIFY DUCTS AND HOSES TN AFT SECTION OF AIRCRAFT

ARE CONNECTED AND SECURE.

d. CHECK ENVIRONMENTAL DIGITAL FLOW CONTROL SYSTEM

[REF. FIGURE 9]1. WITH POWER ON IN THE ACFT (BATTERY SWITCH ON.

FLOW CONTROL CIRCUIT BREAKER PUSHED IN).2. VERIFY THE MASS FLOW VALVE ACTUATOR IS FULL OPEN.

[REF. FIGURE 7A]. THE ACTUATOR DRIVE ARM SHOULD BE

EXTENDED APPROXIMATELY THREE FOURTHS (S/4")INCHESOUT OF THE GEAR DRIVE HOUSING.

2. EXCESSIVE FLOW OR HEAT IN CABIN

a. VERIFY MASS FLOW CONT. SWITCH IS IN "LOW" POSITION.

b. CONNECT 800816-TEST BOX HARNESS TO DIGITAL FLOW

COMPUTER (TCAC SC-100025 HARNESS OR EQUIVALENT).

c. TURN POWER ON (EXTERNAL POWER CART) BATTERY SWITCH.

d. VERIFY 28 VDC AT PINS 9 AND 27 OF DIGITAL FLOW

COMPUTER. (USE PINS 8 OR 13 FOR NEG.)

e. VERIFY 15 .5 VDC AT PINS 31 AND 24 IF

NOT 15 VDC SUSPECT FLOW SENSOR IS LOADING POWER OUT

PUT REPLACE FLOW SENSOR.

i. COVER AMBIENT AIR INPUT PORT (R/H SIDE OF AIRCRAFT).[REF. FIGURE 5] MEASURE VOLTAGE AT PINS 5(1) AND 7(-)VERIFY 0.0 .05 VDC SHOULD BE STABLE IF NOT

STABLE AND DRIFTS h IN EXCESS OF 0.100 VDC

REPLACE FLOW SENSOR. REMOVE COVER FROM AMBIENT AIR

INPUT PORT.

g. WITH SHOP AIR PRESSURIZATION MACHINE, REMOVE HOSE

CLAMP FROM JUNCTION AT HEAT EXCHANGER [SEE FIGURE 5]CONNECT PRESSURE MACHINE.

SHOP AIR PRESSURIZATION MACHINE

(H1 AND H-2)DURING THIS TEST CABIN PRESSURIZATION CAN BE CHECKED. SEE

MAINTENANCE MANUAL.

H-l VERIFY/SET MASS FLOW SWITCH TO LOW WITH SHOP

PRESSURIZATION MACHINE SET AIR FLOW UNTIL YOU GET A

VOLTAGE READING OF 4.16 c/- .07 VDC AT PINS 5(c) AND

7(-) ON DIGITAL FLOW COMPUTER. MONITOR THIS VOLTAGE

FOR SEVERAL MINUTES TO VERIFY IT DOES NOT DRIFT. (IFTHE VOLTAGE DRIFTS, THE FLOW SENSOR SHOULD BE

REPLACED)

H-2 SET MASS FLOW SWITCH TO MAX INCREASE AIP\ ON

PRESSURIZAT1ON MACHINE FOR A VOLTAGE READING OF 4.71

c/- .07 VDC. VERIFY VOLTAGE DOES NOT DRIFT.

ji)

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FIGIIRE 7

E. CONrlFIVlrY ANCIPOWEA CNECIC~

(SEE DW6.800816)

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USING AIRCRAFT ENGINES

(H-3 AND H-4)DURING THIS TEST CABIN pRESSURIZATION CAN BE CHECKED. SEE

MAINTENANCE MANUAL.

H-3 WITH THE ENGINES RUNNING AND WITH BLEED AIR VALVES

OPEN, YOU SHOULD SEE 4.16 .07 VDC AT PINS 5(~) AND

VERIFY THE VOLTAGE DOES NOT DRIFT (IF SO,

REPLACE FLOW SENSOR).

H-4 SET MASS FLOW SWITCH TO MAX. VOLTAGE AT PINS S(t)AND

7(-)SHOULD READ 4.71+/- .07 VDC. VERIFY TT DOES NOT

DRIFT.

NOTE A:

DURING STEPS H-l AND H-2 OR H-3 AND H-4, WATCH THE

FLOW CONTROL VALVE [FIGURE 7.A]. VERIFY THE FLOW-

CONTROL VALVE IS PULL OPEN BEFORE THE AIR FLOW STARTS,

THEN STARTS MOVING TOWARD THE CLOSED POSTION AS THE

VOLITAGE AT PINS 5( AND 7(-) NEARS 4.16 VDC.

NOTE B:

IF THE FLOW CONTROL ACTUATOR ARM DOES NOT MOVE DURING

TEST, CONNECT OSCILLOSCOPE TO PIN 22 (WHEN VALVE

SHOULD BE CLOSING) BLEED AIR RUNNING, OR PIN 23 (WHENVALVE SHOULD BE OPENING) BLEED AJR OFF AND VERIFY 0 TO

28V PULSES. IF NO PULSES SUSPECT DIG. FLOW

COMPUTER.

FLOW CONTROL VALVE MANUAL TEST

DURING THIS TEST LISTEN FOR ROUGH GEAR SOUNDS, BINDING OR

GRINDING. SHOULD BE SMOOTH RUNNING SOUND

NOTE C:

TO MANUALLY CHECK FLOW CONTROL VALVE FOR PROPER OPERATION

(USING 800816-TEST BOX) SET FLOW ROTARY SWITCH TO "TEST"

DEPRESS FLOW TOGGLE SWITCH TO "CLOSE". THE FLOW CONTROL

ACTUATOR ARM SHOULD RUN TOWARD THE CLOSED POSITION

DEPRESS THE FLOW TOGGLE SWITCH TO "OPEN# AND THE FLOW

CONTROL ACTUATOR ARM SHOULD RUN TOWARD THE OPEN POSITION.

(IF NOT, FLOW VALVE TS DEFECTIVE.) SET FLOW ROTARY SWITCH

BACX TO "NORM".

CABIN TEMP CONTROL AUTO MODE. IN THE AUTO MODE THE SYSTEM

WILL TRY TO MAINTAIN A CABIN TEMP OF BETWEEN 540 tO 86", DEPENDS

ON AUTO TEMP. POT SETTING. IF IN REAL COLD CLIMATE AND MORE

HEAT IS REQUIRED SUGGEST USING MANUAL MODE AND SET TO DESIRED

LEVEL. (S~E POH OPERATING PROCEDURES.)

3. NO TEMPERATURE CONTROL

CONNECT TEST HARNESS TO DIGITAL TEMP. COMPUTER. (REFFIGURE 10.)

a. VERIFY SET TEMP. CONTROL SWITCH TO AUTO, SET TEMP

SELECT POT FULL CLOCKWISE.

b. CHECK CABIN TEMP. SENSOR, VERIFY FAN IS TURNING.

c. CHECK VOLTAGE AT PINS A PIN B ON CABIN TEMP SENSOR

AND DUCT TEM SENSOR. GET AMBIENT TEMP. AT EACH SENSOR

REFER TO TABLE r FOR VOLTAGE READINGS FOR THE CABIN

AND DUCT TEMP SENSORS.

d. CHECK VOLTAGE BETWEEN PINS 31 AND as SHOULD BE

5.0 .5 VDC. CHECK VOLTAGE BETWEEN PINS 31(-) AND

5(~), MOVE AUTO-TEMP CONTROL POT CW AND CCW VERIFY VOLTAGE

AT PIN 5 GOES FROM 5.0 VDC TO 0 VDC.

e. CONNECT OSCILLOSCOPE TO PIN 23 (IF AMBIENT TEMPERATURE

IS 70oF OR BELOW) SET AUTO-TEMP CONTROL POT TO FULL CW

POSITION. SET AUTO-MANUAL SWITCH TO MANUAL, DEPRESS I~NCR-

DECR SWITCH TO DECR AND HOLD FOR APPROX 10 SECONDS.

NOTE:

SET AUTO-MANUAL SWITCH TO AUTO. MONITOR

OSCILLOSCOPE FOR 0 TO 28V PULSES (SLOW PULSING) AND

LISTEN TO TEMP MOD. VALVE TO HEAR IF IT IS SLOWLY

BEING DRIVEN (TOWARD BY-PASS POSITION).

NOTE:

WHILE IN MANUAL MODE YOU CAN VERIFY TEE TEMP.

MOD.VALVE IS OPERATING BY LISTENING TO IT RZTN (INCRAND DECR).

f. CONNECT OSCILLOSCOPE TO PIN 22 IF AMBIENT TEMP. IS 700FOR ABOVE. SET AUTO-TEMP CONTROL POT TO FULL CCW

POSITION. SET AUTO-MANUAL SWITCH TO MANUAL, DEPRESS

INCR-DECR SWITCH TO INCR AND HOLD FOR APPROX 10

SECONDS.

NOTE:

SET AUTO-MANUAL SWITCH TO AUTO. MONITOR OSCILLOSCOPE

FOR O TO 28 V PULSES (SLOW PULSING) AND LISTEN TO THE

TEMP MOD VALVE TO HEAR IF IT IS BEING DRIVEN (TOWARDTEE HEAR EXCHANGER POSITION).

61

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O"12 22 le I Z 21 tZ 1I´•1?

3t

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YII~UF

FIGURE 10

61

TEMP. SENSOR DATA

TABLE I

AMBIENT VOLTAGE AMBIENT VOLTAGE

TEMPERATURE VDC TEMPERATURE VDC

DEG. F DEG. F

30 2.719 70 2.941

31 2.724 71 2.947

32 2.730 72 2.952

33 2.736 73 2.958

34 2.741 74 2.964

35 2.747 75 2.969

36 2.752 76 2.975

37 2.758 77 2.980

38 2.763 78 2.986

39 2.769 79 2.991

40 2.774 80 2.997

41 2.780 81 3.002

42 2.786 82 3.008

43 2.791 83 3.014

44 2.797 84 3.019

45 2.802 85 3.025

46 2.808 86 3.030

47 2.813 87 3.036

48 2.819 88 3.041

49 2.825 89 3.047

50 2.830 90 3.052

51 2.836 91 3.058

52 2.841 92 3.064

53 2.847 93 3.069

54 2.852 94 3.075

55 2.858 95 3.080

56 2.863 96 3.086

57 2.869 97 3.091

58 2.875 98 3.097

59 2.880 99 3.103

60 2.886 100 3.108

61 2.891 101 3.L14

62 2.897 102 3.119

63 2.902 103 3.125

64 2.908 104 3.130

65 2.913 105 3.136

66 2.919 106 3.141

67 2.925 107 3.147

68 2.930 108 3.153

69 2.936 109 3.158

70 2.941 110 3.164

66

4. NO CONTROL OF TEMPERATURE IN MANUAL MODE

a. WITH POWER OFF ON ACFT SET AUTO-MANUAL SWITCH TO MANUAL

1. MEASURE CONTINUITY BETWEEN PINS 35 AND 37 ON THE

DIGITAL TEMP COMMUTER (.025 OHMS MAX).2. MEASURE CONTINUITY BETWEEN PINS 25 AND 3 (ON DIGITAL

TEMP. COMPUTER) BY PRESSING INCR-DECR SWITCH TO

INCR. MEASURE CONTINUITY BETWEEN PINS 25 AND 6 BY

PRESSING INCR-DECR SWITCH TO DECR.

b. TURN POWER ON THE ACFT. VERIFY TEMP. CONT. CIRCUIT

BREAKER IS PUSHED IN.

i. WITH AUTO-MANUAL SWITCH IN MANUAL, PRESS TNCR-DECR

SWITCH TO DECR. VERIFY 15 .5 VDC BETWEEN PINS

6 (C) AND 8(-) AND VERIFY 28 c/- .5 VDC BETWEEN PINS

1(-) AND 22

2. PRESS INCR-DECR SWITCH TO INCR POSITION. VERIFY

VOLTAGE BETWEEN PINS 8(-) AND 3(~-) IS 15 f/- .5 VDC,AND PINS 2(-) AND 22(~) IS 28 .5 VDC.

NOTE:

IF UNABLE TO CONTROL THE HEAT INTO THE CABIN IT MAY BE A

FLOW PROBLEM NOT TEMP. CONTROL SYSTEM REFER TO STEP 2.

92. Remove all test equipment

93. Install royalite cover to inside of rear pressurebulkhead. Install upholstery to rear pressurebulkhead. Install all side trim previously removed and

carpets in cabin. Install seats in cabin. Install

all tables and bars in cabin.

94. Install all baggage compartment trim previously removed.

95. Repaint reworked areas of exterior paintwork as

necessary.

96. Install 880734-9 placard ambient air inlet port R/Hside of fuselage I.A.W. Dwg.880734, Sheet B1.

97. Weigh aircraft for weight and blance purposes and

insert new weight and balance data in the Pilots

Operating Handbook.

98. Check that the Pilots Operating Handbook has the

revision dated 29 January 1988 (for both 690C and 695

models) addressing the enviro system incorporated.

99. Conduct enviro system flight test as follows:

1. Prior to engine start:

a. Bleed Air Switch BOTH CLOSE

b. Mass Flow Switch LOW

c. Temp Control AUTO

d. Temp Control as requirede. Air Conditioner Switch OFF

67

2. After engine start:

a. Set RPM of both engines to 65 percenth. Envir Master Switch ON

c. Bleed Air Switch BOTH OPEN

d. Cabin Bus Switch CABIN

e. Air Cond Switch as requiredf. HI/LO Evap Switch as requiredg. Mass Flow Switch as required (LOW for takeoff)

3. Air Conditioner Checks During the flight

NOTE:

AIR COND NOT TO BE SELECTEO ABOVE L8,000 FEET. FAN CAN BE USED FOR

AIR CI~RCULATTON M ANY ALTITUDE.

a. Verify that the AC light is on whenever the Air Cond

Switch is in the AIR COND position.

b. Verify that there is air flow from the air conditioner

system overhead outlets when the Air Cond Switch is in

the AIR COND or FAN position, and that the air is cool

when the switch is in the AIR COND position.

c. verify that the air flow increases when the EvapSwitches are in the HI position.

4. Temperature Control System Checks During the flight

a. Verify that air flow increases out of the floor

outlets with mass flow switch in MAX position and that

the MAX FLOW annunciator illuminates.

b. Verify that cabin temperature is controlled byadjusting temperature control rheostat. Verifytemperature changes using thermometers to monitor the

duct temperature and the duct output temperature in

the cockpit. The temperatures will vary with altitude

and outside temperature.

c. With Auto/Manual Switch in MANUAL, verify that

temperature is controlled by using the INCR/DECRswitch. (Push switch for one second or Less

and wait at least one minute for a temperature

change.)

too. Fill out and mail compliance card.

ELECTRICAL LOAD Total increase with freon compressor an is124.63 amps in flight and 144.63 on ground. With freon

compressor off increase is 4.63 amps in flight and 24.63 amps on

ground.

PUBLICATION8 AFFECTED; The Airplane Maintenance Manual and Wiringdiagram changes required by this document were incorporated byamendments dated December 21st 1987 and July ist 1988 respectively for

the Model 690C and February 24th 1988 and March 15th 1988 respectivelyfor the Model 695.

RECORD COMPLTANCE: Make an appropriate entry in the airplanemaintenance records as follows: Custom Kit No. 141 dated July17,1992 entitled Enviro System Modification accomplished

Fill out compliance and warranty registration forms and return

to Twin Commander A/C Corp.

CUSTOM KIT NO. 141

ENVIRO AIR CONDITIONING AND PRESSURIZATION SYSTEM INSTALLATION

ADDENDUM A

Drawings provided with Custom Kit No. 141.

DRAWING NO. TITLE

800816 ENVIRO ELECT WIRING

880657 PIPING INSTL.

880694 MOD SYS FREON AIRCON

880697 MOD GRL FREON AIRCON

880698 MOD EVAP INSTL FWD

880700 MOD PP FREON AIRCON

880701 MOD ELEC FREON AIRCON

880708 MOD SYS FREON AIRCON

880709 MOD SHRD AIRCON EX

880718 MOD ENVIRO SYS INSTL

880724 MOD FLUSH SCOOP INSTL

880725 MOD EXHAUST AIR DUCT A& I

880726 MOD AFT FUSE PLUMBING

880718 MOD EVAP INSTL

880730 MOD AIRCON AT BLKHD

880732 MOD PLBG INSTL AC

880734 MOD TUBE INSTL

880735 MOD TEMP FLOW CONT

880737 MOD EVAP INSTL

880741 MOD DEFLECT ASSY WTR

Custom Kit ~L Ill/Al

(C=L1AYWAUltLI~AIRCRAFT CORPORATION

P.O. Box 3369, Arlington, WA 98223

(360) 435-9797 lax(360) 435-1112

CUSTOM KIT 158

January 8, 1996

ADDITION OF INBOARD DE-ICE BOOTS

MODELS AFFECTED: 690, 690A, 690B (CK158-501);690c, 695 (CK158-1)

OVERVIEW: These kits add de-ice boots between the nacelles and the fuselage on thoseairplanes of the above models that did not come from the factory with them.

COMPLIANCE: At owner’s discretion.

BY WHOM WORK WILL BE ACCOMPLISHED: A P mechanic

APPROVAL: This kit is approved by the FAA.

ESTIMATED MAN HOURS: For both kits, time to accomplish this conversion is about20 hours. (If the engines are out of the airplane, time to accomplish is shout 12 hours)

OTHER DOCUMENTS AND DRAWINGS REQUIRED: The drawing that is listed inthe parts list on the next page is included in both kits. In addition, the maintenancemanual for the airplane will be needed.

PARTS DATA: These kits are available from authorized Twin Commander ServiceCenters. When ordering, refer to the following kit numbers:

CK158-1 Kit for the addition ofinboard de´•ice boots, for 690C and 696 airplanes.CK158501 Kit for the addition ofinhoard de-ice boots, for 690, 690A, and 69011.

Page 1 of 3

Custom Rit 158

PARTS LIST:

guantityPart number Description -1 kit 501 kit Notes

890480-3 Doubler 2 2

890480-5 Yassy 2

8904807 Tee assy 2890356-503 Doubler 2 2

515194´•1 Boot, LH 1 1

515194-2 Boot, RH 1 1

890480 Drawing 1 1

MIL-H-5599-8 .50 ID hose AR AR (1)MS3367-2´•9 5-Rep AR AR (1)MS21226-() Grommet AR AR (1)AN737TW90 Clamp 8 8 (1)

Notes: (1) Not included in kit. Obtainlocally.

INSTRUCTIONS:

(1) Install the boots and other parts in accordance with installation 890480-1 (for the -1

kit), or 890480-501 (for the -501 kit). Note the following differences andclarifications:

(a) The parts that are called 890480-17, -19, -21, -23, and -25 on the drawing shouldbe fabricated locally of MIL-H-5593´•8 hose, and part-marked CK158-17, -19, -21,-23, and -25, respectively.

(b) Install the boots in accordance with the Maintenance Manual. It is acceptable touse 1300L cement (3M) instead of EC-1403, and to use Pro-Seal 890 instead ofEC1031 and EC801. The Aerazur boots do not require conductive paint or Icex.

(c) Caterpillar grommets installed in a double rib may need to be MS21226-5.(d) Observe the requirements of figure 1 (from TCAC specification 310) on the next

page when clamping hoses or hose couplings to tubes.

(e) Observe usual good practice when routing hoses. In particular, locate, and if

necessary clamp, hoses away from hot or moving parts.(f) Touch-up alodine and prime any bare aluminum edges.(g) It is important that the cement be allowed to cure for the amount of time that the

Maintenance Manual specifies: 24 hours at temperatures above 60"F, 72 hours at

temperatures below 60"F.

(2) Perform a check of the operation of the de-ice boot system in accordance with theMaintenance Manual.

Page 2 of 3

Custom I~t 158

WEIGHT AND BALANCE: For this change, Weight 7.8 ibs., H-hrm 301.5 inches.

ELECTRICAL LOAD: No change

RECORDS COMPLIANCE:

hlake an entry of this modification in the aircraft maintenance records:Custom Kit 158 -1 or ´•501], Addition of Inboard De-Ice Boots, was done on date i.

Figure 1

AM 37TW C~amp

.13 1i. to

Page 3 of 3

1~TI1IIYCustom Kit AIRCRAFT CORPORITION

I´•I:I~)UY1SI

CUSTOM KIT NO. 163

August 4, 1998

PPG WINDSHIELD MOISTURE SEAL INSTALLATION AND REPAIR PROCEDURE

FOR INSTALLED TWIN COMMANDER WINDSHIELDS

MODELS AFFECTED: 690AIBICID, 695/Ale

REASON FOR PUBLICATION: This procedure is applicable to installed windshields for

the addition or repair of hump seals as the primary weather seal between the glass and

fiberglass strap. It is necessary to perform the glass surface preparation/cleaningprocedure detailed below for all repairs that require replacement of a portion of the seal

that contacts the alasssurface or fiberglass surface1s).

COMPLIANCE: At owner’s discretion.

BY WHOM WORK WILL BE ACCOMPLISHED: A 6 P mechanics or equivalent.

APPROVAL: Engineering design aspects are FAA approved.

ESTIMATED MANHOURS: 12 Hours

PLANNING INFORMATION: It is recommended that all subject windshields be inspectedfor outboard moisture seal erosion or delamination every four months. Particular attention

should be taken at the areas eroded by the wiper blades. The entire hump seal area

should be inspected to determine if it is wall bonded to the glass and fiberglass strapsurfaces. If there is evidence that portions of the seal can be lifted with finger or plastic

spatula pressure, those portions should be removed and repaired per the followinginstructions.

NOTE

IT IS ESSENTIAL THAT REPAIRS BE MADE AS NEEDED TO INSURE

MAXIMWTION OF WINDSHIELD SERVICE LIFE.

PARTS DATA:The kit is available from authorized Twin Commander Service Centers.

Order kit no. CK163.

MATERlAtLS SUPPLIED WITH KIT:

1 Products Research Primer PR142 (16 oz.)6 Courtaudls PR 1425 B-1 12 Black with PR 142 Primer (Model 654 SEMKIT)

5 Pr. Rubber Gloves (Powder Free)

PAGE 1 OF 8

CUSTOM ~IT NO. 183

1 Plastic Spatula1 Roll Masking Tape (3m Scotch #232 Or Equiv. Crepe Paper Tape)1 Box Gauze Pads

5 Cotton Cloths

1 Cellulose Sponge2 Sht. Sandpaper (Norton 220 Grit Or Equivalent)2 Razor Blades (Single Edge, Safety)2 Felt Blocks (4x4x.5 in.]1 ZUa~D Cleanser With Oxalic Acid I Pumice I Cerium Oxide

1 CK163 "HUMP SEAL’ Tool

MATERIALS PROCURRED LOCALLY:

Allphatic Naphtha Or Methyl Ethyl t<etcne (MEK)lsopropyl Alcohol (100%)Water

INSTRUC710NS:A. Outboard Glass and FibelRlass S~lao Surface Preoaratlon

1. Mask off the outer glass surface of the window up to the inside edge of the existingoutboard moisture seal. This taping is to insure protection of the glass surface duringremoval of the damaged sealant and fiberglass strap.

2. Completely mask the metal window retainer from the inside edge of the retainer to the

outside edge.

3. When the masking is completed as detailed in steps 1 and 2, an open work area the

width of the existing seal should exist.

4. Carefully remove any damaged, debonded or deteriorated sealant or fiberglass with a

single edge safety razor blade;by shaving along the surface. This is made easier byslightly bending the razor blade at center to insure that the corners do not scratch or

cut into the outboard glass surface.

5. After removal of the damaged sealant, sand the exposed surface of the remainingintact fiberglass strap with 220 grit sandpaper.

CAUTION:

BE CAREFUL NOT TO ABRADE. OR SCRATCH THE OUTER GLASS PLY

SURFACE WITH THE SANDPAPER.

6. After sanding fiberglass strap(s), remove the masking tape and thoroughly clean the

exposed glass surface and remaining fiberglass strap using a clean cloth saturated

with aliphatic naphtha or methyl ethyl ketone (NIEK). Degrease the work area utilizing a

progressive cleaning procedure by cleaning a small area at a time followed by

PAGE 2 OF 8

CUSTOM KIT NO. 163

isopropyl rinse to remove solvent residue, then dry with a clean cloth. Discard soiled

cloths regularly to prevent redepositing contaminants.

7. Apply masking tape as shown in Figure i. After taping, an open work area of

approximately 1.00 inch should exist.

8. Soak a block of clean felt with water and using a slurry of either pumice, cerium oxide

or ZUO~ cleanser and water, polish the exposed glass surface by hand all around until

observing a water-break free surface. A water-break free surface completely"wets" or

"sheets" over the glass surface with no signs of drawing up into droplets showing dry

areas in between. Continue polishing until the water-break free surface is obtained.

Achieving the water-break free surface is critical to insure adhesion of the sealant to

the outer glass surface. This step is critical to achieving proper bond of the PR 1425 B-

1/2 to the glass since complete removal of the PPG surface seal in the bond area is

required.

9. After a water-break free surface is obtained, remove tape from glass and clean the

entire area with isopropyl alcohol (100%) and allow to air dry. Repeat the cleaning

operation changing cloths frequently until no residue is visible on the surface of cloth.

10. Apply 1" masking tape to the outboard glass surface as shown in Figure 2. One layer

of tape should be applied .25 inch from the edge of the fiberglass strap using the

"hump" seal forming tool as a template. Build up the thickness using multiple layers of

tape 50 inch from the edge of the fiberglass strap to form a guide for the "hump" seal

forming tool. After masking, an open area of.25 inch should exist between the inside

edge of the fiberglass strap and the outside edge of the first layer of masking tape

Mask the remaining area of glass (daylight opening) to protect glass surface during

repair operation. Figure 3 and Figure 5 show configuration of repaired "hump’ seal

Figure 4 shows configuration of OEM "hump" seal.

11. Wearing powder free rubber gloves, repeat the cleaning operation with clean cloths

saturated with isopropyl alcohol (100%). Take care not to soak the masltina tape

and contaminate the glass with adhesive from the tape. Again, wipe the surfaces

until no residue is visible on the cloth. Allow surface to air dry a minimum of five

minutes.

12 After a thorough cleaning of the area to be repaired has been accomplished, apply the

new sealant per the following detailed moisture seal application ptocedure.

B. Moisture Seal ADc~lication Procedure General Instructions

1. Follow all established safety rules and practices.

2. Read material safety data sheets for each material to be used

3. Wear powder free clean rubber gloves during all sealant applications to avoid

contamination of the bonding surfaces and to prevent chemical contact with skin.

PAGE 3 OF 8

CUSTOM KIT NO. 163

C. Moisture Seal Apolication Procedure

i. Apply 1 inch masking tape to the outboard metal retainer from the inside edge of the

outboard metal retainer as shown in Figure 2.

2. Using a gauze pad, apply a thin coat (enough to cover without running or dripping) of

the PR 142 primer/cleaner to the cleaned glass surface to be bonded. Allow PR 142 to

dry per manufacturers requirement.

3. Sealant must be applied to windshield immediately after the cleaning operation and

primer application to prevent dust particles and other airborne contaminants from

settling on the cleaned surfaces. Any contaminant on the surface can adversely effect

the adhesion of the sealant to the substrate.

Note: Apply mixed sealant after allowing primer to dry. (See manufacturers’

instructions).

4. Thoroughly mix the contents of the SEMKIT containing the appropriate sealant until no

streaks of either material are visible. Mix components for a minimum of five minutes.

COMPLETE MIXING IS ESSENTIAL

Follow the mixing instructions on the side of the SEMKIT package:

a) Wear safety glasses and gloves while mixing and dispensing

b) Hold cartridge and pull dasher rod back approximately 1/4 of the way up the

cartridgec) Insert ramrod into hollow of dasher rod. Move piston and inject about 1/3 of the

contents of the rod into the cartridge.

CAUTION:

USE FIRM BUT EVEN PRESSURE. DO NOT FORCE, TAP, POUND OR JOLT

RAMROD, IF PISTON DOES NOT MOVE READILY.

d) Repeat steps b and c until ail the contents of the rod are emptied into the cartridge.

Remove ramrod.

a) Hand mix: Mix material for the total number of strokes listed (40 strakes/ 30 strokes

per minute). A stroke is one complete in and out cycle. Hold cartridge and rotate rod

90 degrees in a spiral clockwise motion with each stroke. Each stroke should extend

from the neck end of the cartridge to the plunger end of the cartridge. Accepted

procedure is 30 strokes per minute.

5. Remove the mixed sealant from the SEMKIT tube by the following procedure:

a) Remove bottom cap.

b) Push dasher rod to plunger end of cartridge. Grasp cartridge firmly at plunger end

and detach dasher rod from mixing dasher by turning counter clockwise

PAGE 4 OF 8

CUSTOM I(IT NO. 163

Remove the dasher rod from cartridge. Using the dasher rod, pushlextrude contents of

SEMKIT tube onto the surface to be sealed.

6. Using a plastic spatula or air gun, spread the sealant on the cleaned and primedoutboard glass surface to be bonded.

7. Form the outboard "hump" seal using hump seel tool as shown in Figure 6. The width

of the formed "hump" seal should be 1 inch. The thickness of the formed seal should be

0.10 inch +.02 inch. See Figure 3 and Figure 5 for view of "hump" seal after repair.

Figure 4 shows view of OEM moisture seal.

8. After completing forming of "hump" seal immediately remove the masking tape from the

glass and metal surface while the sealant is still "wet" (uncured). Be careful not to

touch the "wet" (uncured) sealant during tape removal.

9. Smooth the surface of the "wer’ sealant by rubbing the surface of the sealant very

lightly and briskly with a cellulose sponge saturated with water or isopropyl alcohol

(100%).

Note:

Use light pressure only.

10. Allow the sealant to cure. Tackfree cure time for PR 1425 8-1/2 is accomplished at

room temperature (75 degrees F.150% relative humidity) in 8 hours. Cure time to 35

Rex hardness is 24 hours. For every 109150 F. rise in temperature (to a maximum of

140" F.) the cure times are cut in half, for every 100-150 F. decrease in temperature, the

cure time is doubled.

11. After the sealant has cured, inspect for voids and repair as necessary.

PAGE 5 OF 8

CUSTOM KIT NO. 163

MASKING TAPE

SINGLE LAYER OF r"MASKING TAPE

FIGURE 1TAPE FOR CLEANING

MASKINC´•TAPEMULTIPLE LAYERS OF I~ k--;28MASKING TAPE

FIGURE 2

TAPE FOR HUMP SEAL

1.0

.2610 REF.

f

FIGURE 3PROPDSED HUMP SEAL

FIELO REPAIR

PAGE 6 OF 8


South Hill Drive 6AM-5PM PST M´•F

Brisbane, CA 94005 (800)227-4610


Gulfstream Aerospace695, 695A, 6958

AD’S

AD Number

Effective Date Issue Description

84-19-05 TO PREVENT FAILURE OF THE

10/08/84 ENGINE MOUNT SYSTEMS

87-24-07 R1 TO PREVENT ENGINE FLAMEOUT

02/09/88 WHEN IN OR DEPARTING AN ICING

ENVIRONMENT

95-12-23 TO PREVENT WING DAMAGE CAUSED

07/30/95 BY FATIGUE CRACKING,WHICH,IF

Recurring NOT DETECTED AND CORRECTED,

COULD PROGRESS TO THE,CONTD.

95-13-02 TO PREVENT FAILURE OF THE

07/22/95 VERTICAL STABILIZER AS A

Recurring RESULT OF CRACKS, WHICH, IF

NOT DETECTED CORRECTED,CONTD

95-19-18 TO PREVENT STRUCTURAL DAMAGE

10/25/95 TO THE AIRPLANE CAUSED BY

EXCESSIVE TURBULENCE, WHICH

COULD RESULT IN LOSS,CONTD.

98-07-17 TO PREVENT FAILURE OF A FLAP

05/29/98 SYSTEM CABLE CAUSED BY

FATIGUE, WHICH COULD RESULT IN

LOSS OF CONTROL OF THE,CONTD.


GC 0853 SI AD

AD Number

Effective Date Issue Description

98-08-19 TO PREVENT CRACKS AT THE WING

05/18/98 TO FUSELAGE ATTACH POINTS,

Recurring WHICH, IF NOT DETECTED AND

CORRECTED, COULD CAUSE,CONTD.

98-08-25 R1 To prevent the nose landing01/05/99 gear (NLG) from collapsing due

to failure of a drag link

bolt, which could,contd.

98-20-34 TO MINIMIZE THE POTENTIAL

11/03/98 HAZARDS ASSOCIATED WITH

OPERATING THE AIRPLANE IN

SEVERE ICING CONDITIONS,CONTD.

2000-02-30 To activate the pneumatic wing03/24/00 and tail deicing boots at the

first signs of ice

accumulation

2003-07-03 To detect and correct fatigue05/16/03 damage in the wing and

Recurring fuselage areas without

reducing the service,contd.

End of Index


GC 0853 SI AD

Aircraft Technical Publishers Customer Service~s

101 Sduth Hill Drive 6AM-5PM PST H-F

Brisbane, CA 94005 (800)227-4610


Twin Commander A/C

695. 695A. 6958

AD’S

Serial# Tach.Time Total Time N Number Date Researchd

Hours

AD Number Issue Description Date of At Method of One Next Authori zed

EffectiveDate Compliance Compliance Comp Compliance Time Recurring Comp.Due Signature

84-19-05 TO PREVENT FAILURE OF THE I I I I I I I10/08/1984 ENGINE MOUNT SYSTEMS

87-24-07 R1 TO PREVENT ENGINE FLAMEOUT I I I I I I02/09/1988 WHEN IN OR DEPARTING AN ICING

ENVIRONMENT

95-12-23 TO PREVENT WING DAMAGE CAUSED I I I I I I07/30/1995 BY FATIGUE CRACKING.WHICH.IF

Recurring NOT DETECTED AND CORRECTED.

COULD PROGRESS TO THE.CONTD.

95-13-02 TO PREVENT FAILURE OF ME j I I I I I I07/22/1995 VERTICAL STABILIZER AS A

Recurring RESULT OF CRACKS. WHICH. IF

NOT DETECTED 8 CORRECTED.CONTD

95-19-18 TO PREVENT STRUCTURAL DAMAGE I I I I I I I10/25/1995 TO ME AIRPLANE CAUSED BY

EXCESSIVE TURBULENCE. WHICH

COULD RESULT IN LOSS.CONTD.

98-07-17 TO PREVENT FAILURE OF AFLAP I I I I I I I05/29/1998 SYSTEM CABLE CAUSED BY

FATIGUE. WHICH COULD RESULT IN

LOSS OF CONTROL OF THE.CONTD.

98-08-19 TO PREVENT CRACKS AT THE WING I I j I I I I05/18/1998 TO FUSELAGE ATTACH POINTS.

Recurring WHICH, IF NOT DETECTED AND

CORRECTED. COULD CAUSE.CONTD.


GC 0853 SI AD

Hours

AD Number Issue Description Date of At Method of One Next Authorized

Effective Date Compliance Compliance Comp Compliance Time Recurring Comp.Due Signature

98-08-25 R1 To prevent the nose landing I I 1 I I I I

01/05/1999 gear (NLG) from collapsing due

to failure of a drag link

bolt, which could.contd.

98-20-34 TO MINIMIZE THE POTENTIAL I I I I I I I

11/03/1998 HAZARDS ASSOCIATED WITH

OPERATING THE AIRPLANE IN

SEVERE ICING CONDITIONS,CONTD.

2000-02-30 To activate the pneumatic wing I I I I I I I

03/24/2000 and tail deicing boots at the

first signs of ice

accumulation

2003-07-03 To detect and correct fatigue I I I I I I I

05/16/2003 damage in the wing and

Recurring fuselage areas without

reducing the service.contd.

End of Index


GC 0853 SI AD

84’´•19-05 :sTREnM´•nERosPACE MRPORATION:

Amendment 39-4925. Applies to Models 690 and 690A, (S/Ns 11001 through 11284 which

have had engine isolator assemblies replaced after July 28, 1975): 690A (S/Ns 11285 through

11344): B90B (S/Ns 11350 through 11566); 690C (S/Ns 11600 through 11732); 690D (S/Ns15001 through 15033 and 15037); 695 (S/Ns 95000 through 95084); 695A (S/Ns 98001

through 960B1,96063through 96072, 96075, 96078, 96085, and 96088) airplanes certificated

In any category.

Compliance: Required as indicated, unless already accomplished.

To prevent failure of me engine mount systems accomplish the following:

(a) Within 50 hours time-in-service after the eftectlve date of this AD, inspect and

modify, if required, the engine mount systems in accordance with Guffstream Aerospace

Corporation Service Bulletin SB201 issued May 11, 1984.

(b) Airplanes may be flown in accordance with FAR 21.197 to a location where this

AD may be accomplished.

(c) An equivalent method ofcompliance with this AD may be used ifapproved bythe

Manager, Airplane Certification Branch, ASW-150, FAA, Southwest Region, Past ORlce Box

1689, Fort Worth, Texas 76101; telephone (817) 877-2070.

This amendment becomes effective on October 8, 1984.

GULFSTRUIMAMERIC4NCORWR4~/0N

87-24-07 R1CORPORATION: Amendment 395774 as amended by amendment 39-5840. Applies to

Models 690, B90A, 6908, 690C, 690D, 895, 695A, and 6958 tell serial numbers) airplanescertificated in any category.

Compliance: Required within the next 50 hours’ time-in-service after the effective date

of this AD, unless already accomplished.

(a) To prevent engine Rameout when in or departing an icing environment,

accomplish the following:

(1) Revise the airplane POHIAFM by inserting or assun’ng thatthe appropriateGulfstream published revision has been inserted as defined by the following listing:

Modal 690, Revision No. 23, dated May 20, 1987

Model 690A, Revision No. 30, dated May 20, 1987

Model 6908, Revision No. 23, dated May 20, 1987

Mode1690C, Revision No. 21, dated April 9, 1987

Model 690D, Revision No. 12, dated April 9. 1987

Model 695, Revision no. 12, dated April 9, 1987

Model 695A, Revision No. 20, dated April 9, 1987

Model 6958, Revision No, 9, dated April 9, 1987

Ifthe listed revision is not available, revise the POH/AFM by inserting Appendix 1 of this

AD in the "LIMITATIONS" section of the POM/AFM. Appendix 1 procedures supersede any

other POHIAFM procedures which may be contradictory.

NOTE 1: If the above actions have been accomplished in compliance with AD 86-

24-12, no further action is required in order to comply with paragraph (a)(l) of this AD.

(2) Forthose airplanes with ignition systems having a continuous duty cycleof less than 1 hour:

(i) Fabricate and install a placard on the instrument panel in clear view

of the pilot stating, "This airplane is prohibited from flight into known icing," and operate the

airplane in accordance with this limitation. This placard must consist of a minimum of 0.1 inch

high lenerswlth white and red contrasting letterand background colors and may be of a plasticadhesive type.

(ii) The requirements ofsection (a)(2)(i) are no longer applicable when

the aircraft ignition system having a continuous duty cycle of less than 1 hour is modified to

increase the duty cycle to 1 hour or more in accordance with Gulfstream Service information

Nos. SI-211 and/or $1-212 both dated June 30, 1986.

GULFSTRtZ(MAMERIWINCORPaR4nON

(b) The requirements of paragraph (a) of this AD are no longer applicable when the

airplane is modified in accordance with Gulfstream Custom Kit Nos. 138 dated April 15, 1987,or 1 39 dated May 28, 1987, orbythe addition ofother FAA approved automatic rellght ignition

systems for both engines.

NOTE 2: Automatic-rellght ignition is a system which automatically energizes engineignition without pilot action when engine RPM ortorque decays below a specified level and de-

energizes engine ignition when RPM or torque exceeds the specified level. It is not

synonymous with CONTINOUS IGNITION.

(c) The requirements of paragraph (a)(l) and ~a)(2)(1) of this AD may be

accomplished by the holder of a pilot certificate issued under Part 61 of the FAR on any

airplane owned or operated by the pilot, and which is not used under Part 121 or 135. The

person accomplishing these actions must make the appropriate airplane maintenance record

entry as prescribed by FAR 91.173.

(d) Airplanes may be flown in accordance with FAR 21.197 to a location where this

AD may be accomplished.

(e) An equivalent means of compliance with this AD may be used if approved bytheManager, Airplane Certification Branch, ASW-150, FAA, Fort Worth, Texas 76193-0150;

telephone (817) 624-5150.

All persons affected by this directive may obtain copies of the documents(s) referred to

herein upon request to the Gulfstream Aerospace Corporation, Wiley Post Airport, P.O. Box

22500, Oklahoma City, Oklahoma 73123; Telephone (405) 789-5000; or may be examined at

the FAA, Office of the Regional Counsel, Room 1558, 801 East 12th Street, Kansas City,Missouri 84106.

This AD revises AD 81-24-07, Amendment 39-5774, which superseded AD 86-24-12,Amendment 39-5483 (52 FR 43849: November 17, 1987.).

This amendment, 39-5840, becomes effective on Februaty 9, 1988.

APPENDIX I

Supplement to the POH/AFM

Oulfstream Aerospace CorporationModels 690, 690A, 6908, 690C, 690D,

695, 695A, and 6958 Airplanes

Continuous ignition switch shall be assured by selecting Manual IGN or ION Override or IGN

OVRD on the ignition switch as appropriate during all operations in actual or potential icingconditions described herein:

(1) During takeoff and climb out in actual or potential icing conditions.

(2) When ice is visible on, or shedding from propeller(s), splnner(s),or leading edge(s).

"(3) Before selecting ENG INLET, when ice has accumulated.

(4) Immediately, any time engine Rameout occurs as a possible result of ice

Ingestion.(5) During approach and landing while in or shortly following Right in actual or

potential icing conditions.

*Note: If icing conditions are entered in Right without the engine anti-icing system having

been selected, switch one ENGINE system to ENG INLET ON position. If the engine runs

satisfactorily, switch the second ENGINE system tq the ENG INLET ON position and checle

that the second engine continues to run satisfactorily.

CAUTION

Flight in actual or potential icing conditions will be limited by duty cycle of the ignition system.

Ignition system time limits must be observed to prevent exceeding duty cycle times. Operator

should verify these limits for his particular installation.

For the purpose of this supplement, the following definition applies:

"Potentlal icing conditions in precipitation orvlsible moisture meteorological conditions:

(1) Begin when the OAT is +5 degrees C (+41 degrees Fl or colder, and

(2) End when the OAT is +10 degrees C (+50 degrees Fl or warmer.

The procedures and conditions described in this appendix supersede any other POH/AFM

procedures and conditions which may be contradictory.

GULFSTRUIMAMERIWINCORPOR4nON

95-1 2-23TWIN COMMANDER AIRCRAFT CORPORATION:

Amendment 39-9275; Docket No. 94-CE-29-AO.

Applicability: The following airplane models and serial numbers, certificated in anycategory:

Model Serial Numbers

690C 11600 through 11735

695 95000 through 95084

NOTE 1: This AD applies to each airplane identified in the preceding applicabilityprovision, regardless of whether it has been modified, altered, or repaired in the area subjectto the requirements of this AD. For airplanes that have been modified, altered, or repaired so

that the performance of the requirements of this AD is affected, the owner/operator must use

the authority provided in paragraph (g) of this AD to request approval from the FAA. This

approval may address either no action, if the current configuration eliminates the unsafe

condition, or different actions necessary to address the unsafe condition described in this AD.Such a request should include an assessment of the effect of the changed configuration on

the unsafe condition addressed by this AD. In no case does the presence of any modification,alteration, or repair remove any airplane from the applicability of this AD.

Compliance: Required upon the accumulation of 6,000 hours time-in-service (TIS) or

within the next 50 hours TIS after the effective date of this AD, whichever occurs later, unless

already accomplished, and thereafter as indicated in the body of this AD.

To prevent wing damage caused by fatigue cracking, which, if not detected and

corrected, could progress to the point of structural failure, accomplish the following:

(a) For all affected serial number Model 695 airplanes, and any Model 690C

airplane incorporating a serial number in the 11600 through 11730 range, inspect the wingstructure for cracks in accordance with the PART I ACCOMPLISHMENT INSTRUCTIONS

(INSPECTIONS) section of Twin Commander Service Bulletin (SB) No. 213, dated July 29,1994.

(b) For any Model 690C airplane incorporating a serial number in the 11731 through11735 range, inspect the wing structure for cracks in accordance with item 10 of the PART IACCOMPLISHMENT INSTRUCTIONS (INSPECTIONS) section of Twin Commander SE No.

213, dated July 29, 1994.

TWIN COMMANDER AIRCRP~FT CORPORPITION

(c) If, during the inspections required in paragraphs (a) and (b) of this AD, cracks

are found in the areas referenced in Figures 1 through 5 and the instructions of the service

information referenced above, prior to further flight, replace the damaged structure and modifythe wing structure in accordance with the PART II ACCOMPLISHMENT INSTRUCTIONS

(MODIFICATIONS) section of Twin Commander SE No. 213, dated July 29, 1994.

(d) If no cracks are found, accomplish one of the following:

11) For all airplanes, upon the accumulation of 7,500 hours TIS or within

1,000 hours TIS after the initial inspection, whichever occurs later, reinspect the structure in

accordance with either paragraph (a) or (b) of this AD, as applicable, and reinspect thereafter

at intervals not to exceed 1,000 hours TIS, and, if applicable, replace any damaged part or

modify the wing structure as specified in paragraph (c) of this AD; or

(2) For Model 695 airplanes and any Model 690C airplane incorporating a

serial number in the 1 1600 through 1 1730 range, prior to further flight, modify the wingstructure in accordance with the PART II ACCOMPLISHMENT INSTRUCTIONS

(MCDIFICATIONS) section of Twin Commander SE No. 213, dated July 29, 1994.

(e) For all affected Model 695 airplanes and any Model 690C airplane incorporatinga serial number in the 11600 through 11730 range, the modification referenced in paragraphs(c) and (d)(2) of this AD may be accomplished any time after the initial inspection as

terminating action for the repetitive inspection requirement of this AD, except for the inspectionof the doublers at the wing attach fittings located in the Fuselage Station 144 frame (Item 10 of

PART I ACCOMPLISHMENT INSTRUCTIONS section of the Twin Commander SE No. 213,dated July 29, 1994). All affected model and serial number airplanes must inspect in this area

at every 1,000 hours TIS.

NOTE 2. For those airplanes that have not accumulated 6,000 hours TIS, the initial

and first repetitive inspection required by this AD were established to coincide with the 6,000-hour Major Inspection Guide I and 7,500-hour Major Inspection Guide II inspections,respectively, so that the operator may schedule the required action in accordance with these

major inspections.

(f) Special flight permits may be issued in accordance with sections 21.197 and

21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the

airplane to a location where the requirements of this AD can be accomplished.

(g) An alternative method of compliance or adjustment of the initial or repetitivecompliance times that provides an equivalent level of safety may be approved by the

Manager, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region, 1601

Lind Avenue S.W., Renton, Washington 98055-4056. The request shall be forwarded throughan appropriate FAA Maintenance Inspector, who may add comments and then send it to the

Manager, Seattle AGO.

95-12-23

TWIH COLHIIINOER blRCRI\FT CORPORbTIOYL

NOTE 3: Information concerning the existence of approved alternative methods of

compliance with this AD, if any, may be obtained from the Seattle AGO.

(h) The inspections and modification required by this AD shall be done in

accordance with Twin Commander Service Bulletin No. 213, dated July 29, 1994. This

incorporation by reference was approved by the Director of the Federal Register in

accordance with 5 U.S,C. 552(a) and 1 CFR palt 51.Copies may be obtained from Twin

Commander Aircraft Corporation, 19003 59th Drive, NE., Arlington, Washington 98223.

Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel,Room 1558, 601 E. 121h Street, Kansas City, Missouri, or at the Office of the Federal Register,800 North Capitol Street, NW., suite 700, Washington, DC.

(i) This amendment becomes effective on July 30, 1995.


Mr. David D. Swartz, Aerospace Engineer. FAA, Northwest Mountain Region, 1601 Lind

Avenue S.W., Renton, Washington 98055-4056: telephone (206) 227-2624; facsimile (206)227-1181.

95-12-23

TWIN COMMANDER nlRCRACT CORPORATION

3

95-~ 3_Q2TW.

Amendment 39-9283; Docket No. 94-CE-27-AD.

Applicability: The following airplane models and serial numbers, certificated in any

category, that do not have the vertical stabilizer modified in accordance with the

ACCOMPLISHMENT INSTRUCTIONS: PART II MODIFICATION section of Twin Commander

Service Bulletin (88) No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated

July 11, 1994, and September 23, 1994, respectively:

Model Serial Numbers

685 12000 through 12088

690 11000 through 11079

680A 11100 through 11344

690B 11350 through 11566

BBOC 11600through11735690D 15001 through 15042

695 95000 through 85084

695A 88001 through 86100

NOTE 1: This AD applies to each airplane identified in the preceding applicabilityprovision, regardless of whether it has been modified, altered, or repaired in the area subjectto the requirements of this AD. For airplanes that have been modified, altered, or repaired so

that the performance of the requirements of this AD is affected, the owner/operator must use

the authority provided in paragraph (O of this AD to request approval from the FAA. This

approval may address either no action, if the current configuration eliminates the unsafe

condition, or different actions necessary to address the unsafe condition described in this AD.

Such a request should include an assessment of the effect of the changed configuration on

the unsafe condition addressed by this AD. In no case does the presence of any modification,alteration, or repair remove any airplane from the applicability of this AD.

Compliance: Required upon the accumulation of 2,000 hours time-in-service (TIS) on

a vertical stabilizer or within the next 50 hours TIS after the effective date of this AD,whichever occurs later, unless already accomplished, and thereafter as indicated in the bodyof this AD.

To prevent failure of the vertical stabilizer as a result of cracks, which, if not detected

and corrected, could result in loss of control of the airplane, accomplish the following:


(a) Inspect the vertical stabilizer for cracks in accordance with the

ACCOMPLISHMENT INSTRUCTIONS: PART I INSPECTION section of Twin Commander

SE No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994,and September 23, 1994, respectively.

(b) If damage or cracks are found within the limits of Figures 1 and 2 of the service

information referenced above, prior to further flight, modify the vertical stabilizer in accordance

with the ACCOMPLISHMENT INSTRUCTIONS: PART II MODIFICATION section of Twin

Commander SE No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July11, 1994, and September 23, 1994, respectively.

(c) If damage or cracks are found outside the limits referenced in Figures 1 and 2 of

the service information referenced above or if cracks intersect, prior to further flight, replacethe damaged pads with new parts in accordance with the applicable maintenance manual

instructions. The requirements of this AD still apply when the damaged parts are replaced,unless the stabilizer is modified as specified in paragraph (b) of this AD.

(d) If no cracks are found, accomplish one of the following:

(1) Reinspect at intervals not to exceed 500 hours TIS, and modify any

damaged or cracked vertical stabilizer as specified in paragraphs (b) and (c) of this AD: or

(2) Prior to further flight, modify the vertical stabilizer in accordance with the

ACCOMPLISHMENT INSTRUCTIONS PART II MODIFICATION section of Twin

Commander SE No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July11, 1994, and September 23, 1994, respectively. This modification may be accomplished priorto furhter flight after any repetitive inspection as terminating action for the repetitiveinspections provided no cracks are found.

(e) Special flight permits may be issued in accordance with sections 21.197 and

21.198 of the Federal Aviation Regulations (14 CFR 21.197 and 21.198) to operate the


(f) An alternative method of compliance or adjustment of the initial or repetitivecompliance times that provides an equivalent level of safety may be approved by the

Manager, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region, 1601

Lind Avenue S.W., Renton, Washington 98055-4056. The request shall be forwarded throughan appropriate FAA Maintenance Inspector, who may add comments and then send it to the

Manager, Seattle AGO.

NOTE 2: Information concerning the existence of approved alternative methods of


as-13-oz


(g) The inspections and modification required by this AD shall be done in

accordance with Twin Commander Service Bulletin 218, dated May 19, 1994, includingRevision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively. This

incorporation by reference was approved by the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR palt 51. Copies may be obtained from Twin

Commander Aircraft Corporation, 18003 59th Drive, NE., Arlington, Washington 98223.

Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel,Room 1558, 801 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register,800 North Capitol Street, NW., suite 700, Washington, DC.

(h) This amendment becomes effective on July 22, 1985.


Mr. David D. Swartz, Aerospace Engineer, FAA, Northwest Mountain Region, 1801 Lind

Avenue S.W., Renton, Washington 98055-4058; telephone (206) 227-2624; facsimile (206)227-1181.

95-13-02


4

95-1 9-1 8TWIN rm~LMNDeR BRCRIFTCORPD~UTIOII:

Amendment 39-9379: Docket No. 95-CE-20-AD.

Applicability: The following airplane models and serial numbers, certificated in any

category.

Models Serlel Numbers

680T and 680V 1473 through 1720

680W 1721 through 1850

681 8001 through 6072

690 11001 through 11079

690A 11100 through 11344

6908 11350 through 11566

690C 11800 through 11735

890D 15001 through 15042

695 95000 through 95084

695A 96000 through 96100

6958 96201 through 86208

NOTE 1: This AD applies to each airplane identified in the preceding applicabilityrevision, regardless of whether it has been modified, altered, or repaired in the area subjectto the requirements of this AD. For airplanes that have been modified, altered, or repaired so

that the performance of the requirements of this AD is affected, the owner/operator must

request approval for an anemative method of compliance in accordance with paragraph (c) of

this AD. The request should include an assessment of the effect of the modification,

alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe

condition has not been eliminated, the request should include specific proposed actions to

address it.

Compliance: Required within the next 50 hours time-in-service after the effective date of

this AD, unless already accomplished.

To prevent structural damage to the airplane caused by excessive turbulence, which

could result in loss of the airplane, accomplish the following:

(a) Install the placard (to the windshield centerpost) and incorporate the airplaneflight manual/pilot operating handbook (AFMIPOH) revisions that are included with the kits

presented below. The placard and AFM/POH revisions provide warnings to the airplaneoperator of the impo~tance of observing the Tult~ulent Air Penetration and Maneuveringspeeds:

TWIN COMMANDER nlRCRIFT CORPORATION

Kit No. Model Affected

SB220-1 680T

58220-2 680V

58220-3 680W

58220-4 681

58220-5 690

58220-6 690A

58220-7 6908

SB220´•8 890C58220-9 690D

58~20-10 695

SB22011 6951\

58220-12 6958

NOTE 2: Twin Commander Service Bulletin No. 220, dated February 1, 1995,relates to the subject of this AD, and references the 58220 senrice kits specified above.

(b) Special flight permits may be issued in accordance with sections 21.197 and21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the


(C) An altemative method of compliance or adjustment of the compliance time that

provides an equivalent level of safety may be approved by the Manager, Seattle AircraftCertification Office (ACO), FAA, Northwest Mountain Region, 1601 Lind Avenue S.W., Renton,Washington 96055-4056. The request shall be forwarded through an appropriate FAAMaintenance Inspector, who may add comments and then send it to the Manager, SeattleAGO.

NOTE 3: Information concerning the existence of approved altemative methods of


(d) All persons affected by this directive may obtain copies of the kits referencedabove that include the placard and the AFM revisions upon request to the Twin CommanderAircraft Corporation, 19010 5Wh Drive, NE., Arlington, Washington 98223; or may examinethis document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558,601 E. 12th Street, Kansas City, Missouri 64106.

(e) This amendment becomes effective on October 25, 1995.

FOR FURTHER INFORMATION CONTACT:Mr. David D. Swartz, Aerospace Engineer, FAA, Northwest Mountain Region, 1601 LindAvenue S.W., Renton, Washington 98055-4058; telephone (206) 227-2624; facsimile (208)227-1181.

95-19-18

TWIN COMMANMR AIRCRAFT CORPORATION

98-07-17 TWIN COMMANDER AIRCRAFT

CORPORATION: Amendment 39-10437; Docket No. 97-CE-69-AD. Supersedes AD

94-04-17, Amendment 39-8837.

Applicability: The following airplane models tall serial numbers), ce~tificated in

any category:

500 500-A 500-B 500-5 500-U

520 560 560-A 580-E 560-F

seo seo-e 680-F 680FL 680FL(P)680FP 680T 680V 680W 681

885 690 690A 69013 690C

690D 695 695A 695B 720

NOTE 1: This AD applies to each airplane identified in the precedingapplicability provision, regardless of whether it has been modified, altered, or repairedin the area subject to the requirements of this AD. For airplanes that have been

modified, altered, or repaired so that the performance of the requirements of this AD is

affected, the owner/operator must request approval for an alternative method of

compliance in accordance with paragraph (e) of this AD. The request should include an

assessment of the effect of the modification, alteration, or repair on the unsafe condition

addressed by this AD; and, if the unsafe condition has not been eliminated, the requestshould include specific proposed actions to address it.

Compliance: Required as indicated in the body of this AD, unless alreadyaccomplished.

To prevent failure of a flap system cable caused by fatigue, which could result in

loss of control of the airplane, accomplish the following:

(a) Within the next 300 hours timein-selvice (TIS) after the effective date ofthis AD, unless already accomplished, perform the following in accordance with the

ACCOMPLISHMENT INSTRUCTIONS section of Twin Commander Aircraft Corporation(Twin Commander) Mandatory Service Bulletin No. 226, dated April 14, 1997 (RevisionNo. 1 Release Date: July~lB, 1997):

(1) Inspect all flap system cable grooves for the correct width;

(2) Inspect all flap system pulleys for rubbing on the support brackets;

(3) Inspect all flap pulley cable assemblies for frayed wires; and


(4) Mark pulleys that have been inspected and have the correct grooveradius with two parallel lines as specified in the service bulletin.

NOTE 2: Revision No. 1 Release Date: July 15, 1997, of Twin Commander

Mandatory Service Bulletin No. 226, specifies changes in the workhours necessary to

accomplish this action and makes reference to a gauge that is available from the

manufacturer for use in accomplishing the inspection.

(b) If any of the above discrepancies are found, prior to further flight after the

inspections required by paragraph (a), including all subparagraphs, of this AD, rework

or replace the affected palt in accordance with Twin Commander Mandatory Service

Bulletin No. 226, dated April 14, 1997 (Revision No. 1 Release Date: July 15, 1997).

(C) As Of the effective date of this AD, no person may install a pulley that

does not have the criteria presented in either paragraph (c)(l), (c)(2), or (c)(3) of this

AD:

(1) A pulley that has been inspected, found acceptable, and marked

with two parallel lines in accordance with paragraph (a), including allsubparagraphs, of

this AD;

(2) A pulley that has been reworked in accordance with an FAA-

approved procedure and is marked "SB 226"; or

(3) A new pulley that is marked "SB 226-NEW".

(d) Special flight permits may be issued in accordance with sections 21.197

and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operatethe airplane to a location where the requirements of this AD can be accomplished.

(e) An alternative method of compliance or adjustment of the compliance time

that provides an equivalent level of safety may be approved by the Manager, Seattle

Aircraft Certification Office (ACO), Northwest Mountain Region, FAA, f 601 Lind Avenue

S.W., Renton, Washington 98055-4056.

(1) The request shall be foNvarded through an appropriate FAA

Maintenance inspector, who may add comments and then send it to the Manager,Seattle AGO.

(2) Alternative methods of compliance approved in accordance with

AD 84-04-17 (superseded by this AD) are not considered approved as alternative

methods of compliance for this AD.

NOTE 3: information concerning the existence of approved alternativemethods of compliance with this AD, if any, may be obtained from the Seattle AGO.

981)7-17


(f) The inspections and replacements required by this AD shall be done in

accordance with Twin Commander Mandatory Service Bulletin No. 226, dated April 14,1997 (Revision No. 1 Release Date: July 15, 1997). This incorporation by reference

was approved by the Director of the Federal Register in accordance with 5 U.S.C.

552(8) and 1 CFR part 51. Copies may be obtained from the Twin Commander Aircraft

Corporation, 19003 59th Drive, NE, Arlington, Washington 98223-7832. Copies may be

inspected at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601

E. 1 2th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North

Capitol Street, NW, suite 700, Washington, DC.

(9) This amendment supersedes AD 94-04-17, Amendment 39-8837.

(h) This amendment becomes effective on May 29, 1998.

FOR FURTHER INFORMATION CONTACT:Mr. Jeffrey Morfitt, Aerospace Engineer, FAA, Northwest Mountain Region, 1601 Lind

Avenue S.W., Renton, Washington 98055-4056; telephone: (425) 227-2595: facsimile:

(425) 227-1181.

98-07-17


98-08-1 9iwa co..narun alncna~

CORPORA710N: Amendment 39-10468; Docket No. 95-CE-92-AD.

Applicability: Models 500, 500A, 5008, 5008, 500U, 520, 560, 560A, 560E,560F, 680, 680E, 680F, 680FL, 680FLP, 680FP, 680T, 680V, 680W, 681, 685, 690,690A, 6908, 690C, 690D, 695, 695A, 6958 and 720 airplanes, all serial numbers,certificated in any category.

NOTE 1: This AD applies to each airplane identified in the precedingapplicability provision, regardless of whether it has been modified, altered, or repairedin the area subject to the requirements of this AD. For airplanes that have been

modified, altered, or repaired so that the performance of the requirements of this AD is

affected, the owner/operator must request approval for an alternative method of

compliance in accordance with paragraph (f) of this AD. The request should include an

assessment of the effect of the modification, alteration, or repair on the unsafe conditionaddressed by this AD; and, if the unsafe condition has not been eliminated, the requestshould include specific proposed actions to address it.

Compliance: Required as indicated in the body of this AD after the effective dateof this AD, unless already accomplished.

To prevent cracks at the wing to fuselage attach points, which, if not detectedand corrected, could cause structural failure and loss of control of the airplane,accomplish the following:

(a) For all models except Models 520, 560, 690C and 695, accomplish theactions in the following table in accordance with the Compliance section and Part I, II,and III of the ACCOMPLISHMENT INSTRUCTIONS sections of Twin CommanderService Bulletin No. 223, dated October 24, 1996 as amended by Revision Notice No.1, dated May 8, 1997 and Revision Notice No. 2, dated August 18, 1997:


A B IC

Upon the if cracked, prior to if no cracks are

accumulation of further flight, replace found, repeat6,000 hours total the brackets and inspection at 1,000time-in-service CTIS) straps or repair the hour (hr.) intervals

PART I or within the next 100 part by an approved until cracks are

hours TIS, whichever repair scheme (see found, replace theoccurs later, install paragraph (b) of this cracked part or repair byaccess holes in left AD). Then, accomplish an approved repairand right wing leading PART II of this AD. scheme (seeedges and inspect the paragraph (b) of thisforward attach (Accomplish in AD), then accomplishbrackets and straps accordance with PART II.

for cracks. PART I of ComplianceSection in Twin Commander (Accomplish in

For any airplanes that SE 223, accordance withhave wings modified dated Oct. 24, 1996 as PART I of Compliancewith titanium leading amended by Revision Notice Section in Twin

edges through an No. 1, dated Commander SE 223,STC, remove the wing May 8, 1997 and dated Oct. 24, 1996root farlngs to Revision Notice No. 2, as amended byaccomplish the required dated August 18, 1997) Revision Notice No. 1,inspections, dated May 8, 1997in lieu of installing and Revision Noticethe access holes. No. 2, dated

August 18, 1997.)(Accomplish in

accordance with

PART I of ComplianceSection in Twin

Commander SE 223,dated Oct. 24, 1996

as amended byRevision Notice No. 1,dated May 8, 1997

and Revision Notice

No. 2, dated

August 18,1997.)

ss-os-´•ca


A B C

Inspect for cracks at if cracked, prior to After repair or

the wing leading edge further flight, replace replacement is

close-outs, upper any cracked part or accomplished,lower return flange radius, repair the part with an continue to inspect at

PART II fuselage frame where tee approved repair 6,000 hr. intervals.

bracket attaches, inboard scheme (see paragraphside (b) of this AD). If no (Accomplish in

of attach bracket and cracks are found, accordance with

frame tee bracket, continue to repetitively PART II of Complianceinspect at 1,000 hour Section in Twin

(Acoomplish in TIS intervals. Commander SE 223,accordance with dated Oct. 24, 1996

PART II of Compliance (Accomplish in as amended bySection in Twin accordance with Revision Notice No. i,Commander SE 223, PART II of Compliance dated May 8, 1997

dated Oct. 24, 1996 Section in Twin and Revision Notice

as amended by Commander SE 223, No. 2, dated

Revision Notice No. 1, dated Oct. 24, 1996 as August 18, 1997.)dated May 8, 1997, amended by Revision Notice

and Revision Notice No. I,datedNo. 2, dated May 8, 1997 and

August 18, 1997.) Revision Notice No. 2,dated August 18,1997

For pressurized airplanes, if cracked, prior to if no cracks, repeatat further flight, repair inspection at

6,000 hr. total TIS or with an approved 1,000 hr, intervals

the next repair scheme (see until cracks are

100 hours TIS paragraph (b) of this found, then

PARTIII whicheveroccurs AD), and continue to accomplish PART III B

later, inspect fuselage inspect at 1,000 hr. of this AD.

station (F.S.) 100 for intervals.

cracks. (Accomplish in

(Accomplish in accordance with

For non-pressurized accordance with PART iii of

airplanes, at 12,000 PART III of Compliance Compliance Section in

hr. total TIS or within Section in Twin Twin Commander

the next 100 hours I Commder SE 223, SE 223, dated

SIS whichever occurs dated Oct. 24, 1996 as Oct. 24, 1996 as

later, inspect F.S. 100 amended by Revision Notice amended by Revision

for cracks. No. 1, dated Notice No. i, dated

May 8, 1997 and May 8, 1997 and

(Accomplish in Revision Notice No. 2, Revision Notice No. 2,

accordance with dated August 18, dated August 18,PART III of 1997.) 1 1997

g8-OCls

TWIN COMMANDER AIRCRAFT CORPORPITION

Compliance Section in

Twin Commander

SE 223, dated

Oct. 24, 1996 as

amended by Revision

Notice No. 1 dated

May 8, f 997 and

Revision Notice No. 2,dated August 18,1997.

(b) Obtain an FAA-approved repair scheme from the manufacturer throughthe Manager of the Seattle Aircraft Certification Office at the address specified in

paragraph (f) of this AD.

(c) For Twin Commander Models 520 and 560 airplanes, upon the

accumulation of 6,000 hours total TIS or within the next 100 hours TIS, whichever

occurs later, accomplish PART II of the table in paragraph (a) of this AD. AccomplishPART III in accordance with the compliance times in the above table of paragraph (a).These models are excluded from the wing leading edge access hole installation in

PART I of the table in paragraph (a) of this AD.

(d) For Twin Commander Models 690C and 695 airplanes, accomplishPARTS I and II in accordance with the compliance times in the above table of

paragraph (a). These Models are excluded from PART III of the table in paragraph (a)of this AD.

(e) Special flight permits may be issued in accordance with sections 21.1 97and 21.189 of the FederalAviation Regulations (14 CFR 21.197 and 21.199) to operatethe airplane to a location where the requirements of this AD can be accomplished.

(f) An altemative method of compliance or adiustment of the initial or

repetitive compliance times that provides an equivalent level of safety may be approvedby the Manager, Seattle Aircraft Certification Office, 1601 Lind Ave. S.W., Renton,Washington, 98055-4056 The request shall be forwarded through an appropriate FAAMaintenance Inspector, who may add comments and then send it to the Manager,Seattle Aircraft Certification Office.

NOTE 2: Information concerning the existence of approved alternativemethods of compliance with this AD, if any, may be obtained from the Seattle AircraftCertification Office.

(g) The inspections and installations required by this AD shall be done in

accordance with the Twin Commander Service Bulletin No. 223, dated October 24,1996 as amended by Revision Notice No. 1, dated May 8, 1997 and Revision NoticeNo. 2, dated August 18, 1997. This incorporation by reference was approved by the

as-as-is


Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 61.

Copies may be obtained from Twin Commander Aircraft Corporation, P.O. Box 3369,Arlington, Washington, 98223. Copies may be inspected at the FAA, Central Region,Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri,or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700,Washington, DC.

(h) This amendment becomes effective on May 18, 1998.

FOR FVRTHER INFORMATION CONTACT:

Jeffrey Morfitt, Aerospace Engineer, FAA, Seattle Aircraft Certification Office, 1601 LindAve. S.W., Renton, Washington, 98055-4058; telephone (425) 227-2595; facsimile

(425) 227-1181.

9B-0&ls


Revision issued January 1999

98-08-25 R1 TMnN COMMANDER

A1RCRAFT CORPORATION: Amendment 39-10821: Docket No. 98-CE-54-AD.

Revises AD 98-08-25, Amendment 39-10474, which superseded AD 96-12-08,Amendment 39-9650.

Applicability: The following model and serial number airplanes,ce~tificated in any catego~y:Models Serial Numbers

5005 3185, 3228, 3230, 3262, and 3291

500U 1785

680F 1195

681 6027

680V 1677

690 11035, 11053, 11068, and 11074

690A 11111, 11134,11146,11153,11173,11177,11205.11215.11237, 11249, 11271, 11273, and 11282

890B 11360, 11382, 11409, 11424, 11451, 11455, 11463, 11491,11513, 11521,11535, 11536, 11539, and 11586

690C 11638, 11643, 11676, 11689, and 11719

690D 15041

695 95010, 95033, 95044, and 95066

695A 96010, 98041,96056, and 96061

NOTE 1: This AD applies to each airplane identified in the precedingapplicability provision, regardless of whether it has been modified, altered, or

repaired in the area subject to the requirements of this AD. For airplanes that

have been modified, altered, or repaired so that the performance of the

requirements of this AD is affected, the owner/operator must request approvalfor an altemative method of compliance in accordance with paragraph (g) of this

AD. The request should include an assessment of the effect of the modification,alteration, or repair on the unsafe condition addressed by this AD; and, if the

unsafe condition has not been eliminated, the request should include specificproposed actions to address it.

Compliance: Required as indicated below, unless already accomplished:

1. For all affected airplane models, except for Model 695A airplanes:Within 75 hours time-in-service (TIS) after May 18, 1998 (the effective date of

AD 98-08-25).


2. For Model 695A airplanes: Within the next 75 hours TIS after the

effective date of this AD.

To prevent the nose landing gear (NLG) from collapsing due to failure of a

drag link bolt, which could result in loss of control of the airplane during landingoperations, accomplish the following:

(a) For all airplane models, except for Models 690D and 695A, replacethe NLG drag link bolt, part number (P/N) ED 10055, with a new bolt in

accordance with the INSTRVCTIONS section of Twin Commander ServiceBulletin (SB) 224, Revision C, dated July 25, 1996.

(b) For airplane Models 690D and 695A, replace the NLG drag link bolt

(PIN ED 10055), with a new bolt (P/N 750076-1) in accordance with Twin

Commander SE 224, Revision C, dated July 25, 1996.

(c) The new replacement bolt must be marked with the manufacturer’s

serial number, the date of manufacture, and the last three digits of the drawingnumber, 055, on the bolthead forall but Models 690D and 695A. Models 690D

and 695A bolts must be marked with the manufacturer’s serial number, the date

of manufacture, and the last three digits of the drawing number, 76-1, on the bolt

head.

NOTE 2: Although not required by this AD, FAA highly recommends

that the removed bolt (P/N ED 10055) be retumed to Twin Commander for

Rockwell Hardness testing.

(d) For all affected airplane models, except for Models 690D and 695A

airplanes, compliance with Twin Commander SE 224, Revision A, dated April 24,1996; or Twin Commander SE 224, Revision C, dated July 25, 1996, fulfills the

applicable requirements of this AD. For the affected Models 690 and 695A

airplanes, compliance must be in accordance with Twin Commander SE 224,Revision C, dated July 25, 1998.

(e) As of the effective date of this AD, no person shall install, on anyaffected airplane, a NLG drag link bolt that does not have the manufacturer’s

serial number, manufacture date, and the last three digits of the drawing number

as specified in paragraph (8) of this AD.

(f) Special flight permits may be issued in accordance with sections

21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and

21.199) to operate the airplane to a location where the requirements of this AD

can be accomplished.

~&08-25 R1

NYIN COMMANDER AIRCRAFT CORPORAnOM

(0) An alternative method of compliance or adjustment of the

compliance time that provides an equivalent level of safety may be approved bythe Manager, Seattle Aircraft Certification Office, 1601 Lind Ave. SW, Renton,

Washington, 98055-4056. The request shall be forwarded through an

appropriate FAA Maintenance Inspector. who may add comments and then send

it to the Manager, Seattle Aircraft Certification Office.

NOTE 3: information conceming the existence of approved altemative

methods of compliance with this AD, if any, may be obtained Seattle Aircraft

Certification Office.

(h) The inspection and replacement required by this AD shall be done

in accordance with Twin Commander Service Bulletin 224, Revision C, dated

July 25, 1996. This incorporation by reference was previously approved by the

Director of the Federal Register as of May 18, 1998 (63 FR 19387, April 20,

1998). Copies may be obtained from Twin Commander Aircraft Corporation,19010 59th Drive NE, Arlington. Washington 98223-7832. Copies may be

inspected at the FAA, Central Region, Office of the Regional Counsel, Room

1558, 601 E. 12th Street, Kansas City, Missouri. or at the Office of the Federal

Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

(i) This amendment revises AD 98-08-25, Amendment 39-10474,which superseded AD 96-12-08, Amendment No. 39-9650.

(j) This amendment becomes effective on January 5, 1989.


Jeffrey Morfitt, Aerospace Engineer, FAA, Seattle Aircraft Certification Office,1601 Lind Ave. S.W., Renton, Washington, 98055-4056; telephone:(206) 227-2595; facsimile: (206) 227-1181.

48´•0&25 Al

NYIN COMMANDER AIRCRAFT CORPOR~TION

98-2O -34TWIN COMMANDER AIRCRAFT

CORPORATION: Amendment 39-10801; Docltet Na. 97-CE-57-AD.

Applicability: Models 500,-500-A, -500-8, -500-8, -500-U, -520, -560,-560-A, -560-8, -560-F, -BB0, -680-8, -B8OFL(F), -680T, -680V, -680W, -681,-685, -690, -690A,-BgOB, 690C,-690D, -695, -695A, -6958, and 720 airplanestall serial numbers), certificated in any category.

NOTE 1: This AD applies to each airplane identified in the precedingapplicability provision, regardless of whether it has been modified, altered, or

repaired in the area subject to the requirements of this AD. For airplanes that

have been modified, altered, or repaired so that the performance of the

requirements of this AD is affected, the owner/operator must request approvalfor an alternative method of compliance in accordance with paragraph (d) of

this AD. The request should include an assessment of the effect of the

modification, alteration, or repair on the unsafe condition addressed by this

AD; and, if the unsafe condition has not been eliminated, the request should

include specific proposed actions to address it.

Compliance: Required as indicated, unless already accomplished.

To minimize the potential hazards associated with operating the airplanein severe icing conditions by providing more clearly defined procedures and

limitations associated with such conditions, accomplish the following:

(a) Within 30 days after the effective date of this AD, accomplish the

requirements of paragraphs (a)(l) and (a)(2) of this AD.

NOTE 2: Operators should initiate action to notify and ensure that

flight crewmembers are apprised of this change.

(1) Revise the FAA-approved Airplane Flight Manual (AFM) byincorporating the following into the Limitations Section of the AFM. This may be

accomplished by inserting a copy of this AD in the AFM.

"WARNING

Severe icing may result from environmental conditions outside of those for

which the airplane is certificated. Flight in freezing rain, freezing drizzle, or mixed

icing conditions (supercooled liquid water and ice crystals) may result in ice

build-up on protected surfaces exceeding the capability of the ice protectionsystem, or may result in ice forming aft of the protected surfaces. This ice may


not be shed using the ice protection systems, and may seriously degrade the

performance and controllabilny of the airplane.

During flight, severe icing conditions that exceed those for which the

airplane is certificated shall be determined by the following visual cues. If

one or more of these visual cues exists, immediately request priorityhandling from Air Traffic Control to facilitate a route or an altitude changeto exit the icing conditions.

Unusually extensive ice accumulation on the airframe and windshield in

areas not normally observed to collect ice.

Accumulation of ice on the lower surface of the wing aft of the protectedarea.

Accumulation of ice on the engine nacelles and propeller spinnersfarther aft than normally observed.

Since the autopilot, when installed and operating, may mask tactile

cues that indicate adverse changes in handling characteristics, use of the

autopilot is prohibited when any of the visual cues specified above exist, or

when unusual lateral trim requirements or autopilot trim warnings are

encountered while the airplane is in icing conditions.

Allwing icing inspection lights must be operative prior to flight into

known or forecast icing conditions at night. [Note: This supersedes any relief

provided by the Master Minimum Equipment List (MMEL).]"

(2) Revise the FAA-approved AFM by incorporating the

following into the Normal Procedures Section of the AFM. This may be

accomplished by inserting a copy of this AD in the AFM.

"THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO

SEVERE IN-FLIGHT ICING:

Visible rain at temperatures below O degrees Celsius ambient air

temperature.

Droplets that splash or splatter on impact at temperatures below O

degrees Celsius ambient air temperature.

PROCEDURES FOR EXITING THE SEVERE ICING ENVIRONMENT:

These procedures are applicable to all flight phases from takeoff to

landing. Monitor the ambient air temperature. While severe icing may form at

98-20-34


temperatures as cold as -18 degrees Celsius, increased vigilance is warranted

at temperatures around freezing with visible moisture present. If the visual

cues specified in the Limitations Section of the AFM for identifying severe

icing conditions are observed, accomplish the following:

Immediately request priority handling from Air Traffic Control to

facilitate a route or an altitude change to exit the severe icing conditions

in order to avoid extended exposure to flight conditions more severe than

those for which the airplane has been certificated.

Avoid abrupt and excessive maneuvering that may exacerbate control

difficulties.

Do not engage the autopilot.

If the autopilot is engaged, hold the control wheel firmly and disengagethe autopilot.

If an unusual roll response or uncommanded roll control movement is

observed, reduce the angle-of-attack.

Do not extend flaps when holding in icing conditions. Operation with

flaps extended can result in a reduced wing angle-ofattack, with the

possibility of ice forming on the upper surface further aft on the wing than

normal, possibly aft of the protected area.

If the flaps are extended, do not retract them until the airframe is

clear of ice.

Report these weather conditions to Air Traffic Control."

(b) Incorporating the AFM revisions, as required by this AD, may be

performed by the owner/operator holding at least a private pilot certificate as

authorized by section 43.7 of the FederalAviation Regulations (14 CFR 43.7),and must be entered into the aircraft records showing compliance with this AD inaccordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).

(c) Special flight permits may be issued in accordance with sections21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and

21.199) to operate the airplane to a location where the requirements of this AD

can be accomplished.

(d) An alternative method of compliance or adjustment of the

compliance tim$ that provides an equivalent level of safety may be approved bythe Manager, Small Airplane Directorate, FAA, 1201 Walnut, suite 900, Kansas

98-20-34


City, Missouri 64106. The request shall be forwarded through an appropriateFAA Maintenance Inspector, who may add comments and then send it to the

Manager, SmallAirplane Directorate.

NOTE 3: Information concerning the existence of approved alternativemethods of compliance with this AD, if any, may be obtained from the Small

Airplane Directorate.

(e) All persons affected by this directive may examine informationrelated to this AD at the FAA, Central Region, Office of the Regional Counsel,Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

(f) This amendment becomes effective on November 3, 1998.

FOR FVRTHER INFORMATION CONTACT:

Mr. John P. Dow, Sr., Aerospace Engineer, SmallAirplane Directorate, AircraftCertification Service, 1201 Walnut, suite 900, Kansas City, Missouri 64106,telephone (816) 426-6932, facsimile (816) 426-2169.

98-20-34

TWIN COMMANDIR AIRCRAFT CORPORATION

2000-02-30CORPORATION: Amendment 39-11548; Docket No. 99-CE-51-AD.

(a) What airplanes are affected by this AO?: The following Model 600 series

airplanes, all serial numbers, that are:

(1) equipped with pneumatic deicing boots; and

(2) certificated in any category.

Models

680, 680E, 680F, 680FL, 680FL(P), 680T, 680V, 680W, 681, 690, 685, 690A, 690B,690C, 690D, 695, 695A, and 6958

(b) Who must comply with this AD?: Anyone who wishes to operate any of the

above airplanes on the U.S. Register. The AD does not apply to your airplane if it is not

equipped with pneumatic de-icing boots.

(c) What problem does this AD address?: The information necessary to

activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation

is critical for flight in icing conditions. If we did not take action to include this information,flight crews could experience reduced controllability of the aircraft due to adverse

aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.

(d) What must I do to address this problem?: To address this problem, youmust revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM)to include the following requirements for activation of the ice protection systems. You

must accomplish this action within the next 10 calendar days after the effective date of

this AD, unless already accomplished. You may insert a copy of this AD in the AFM to

accomplish this action:

Except for certain phases of flight where the AFM specifies that deicingboots should not be used (e.g., take´•off, final approach, and landing), compliance with

the following is required.

Wing and Tail Leading Edge Pneumatic Deicing Boot System, if installed,must be activated:

At the first sign of ice formation anywhere on the aircraft, or uponannunciation from an ice detector system, whichever occurs first; and

TWIN COMMANDER AIRCRAFT CORPORPITION

The system must either be continued to be operated in the

automatic cycling mode, if available; or the system must be manually cycled as needed

to minimize the ice accretions on the airframe.

The wing and tail leading edge pneumatic deicing boot system may be

deactivated only after leaving icing conditions and after the airplane is determined to be

clear of ice."

(e) Can the pilot accomplish the action?: Yes. Anyone who holds at least a

private pilot certificate, as authorized by section 43.7 of the Federal Aviation

Regulations (14 CFR 43.7), may incorporate the AFM revisions required by this AD.

You must make an entry into the aircraft records that shows compliance with this AD, in

accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).

(f) Can I comply with this AD in any other way?: Yes.

(1) You may use an alternative method of compliance or adjust the

compliance time if:

(i) Your alternative method of compliance provides an

equivalent level of safety; and

(ii) The Manager, Small Airplane Directorate, approves

your alternative. Submit your request through an FAA Principal Maintenance Inspector,who may add comments and then send it to the Manager.

(2) This AD applies to each airplane identified in the precedingapplicability provision, regardless of whether it has been modified, altered, or repaired in

the area subject to the requirements of this AD. For airplanes that have been modified,altered, or repaired so that the performance of the requirements of this AD is affected,the owner/operator must request approval for an alternative method of compliance in

accordance with paragraph (f)(l) of this AD. The request should include an assessment

of the effect of the modification, alteration, or repair on the unsafe condition addressed

by this AD: and, if you have not eliminated the unsafe condition, specific actions you

propose to address it.

(g) Where can I get information about any already-approved alternative

methods of compliance?: Contact the Small Airplane Directorate, 901 Locust, Room

301, Kansas City, Missouri 64106; telephone: (816) 329-4121;facsimile:(316)329-4091.

(h) What if I need to fly the airplane to another location to comply with this

AD?: The FAA can issue a special flight permit under sections 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a

location where you can accomplish the requirements of this AD.

2000-02-30


(i) When does this amendment become effective?: This amendment

becomes effective on March 24, 2000.

FOR FURTHER INFORMATION CONTACT:Mr. John P. Dow, Sr., Aerospace Engineer, FAA, Small Airplane Directorate, 901

Locust, Room 506, Kansas City, Missouri 64106; telephone: (816) 329-4121: facsimile:

(816)329-4090.

Issued in Kansas City, Missouri, on January 25, 2000.

Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service

2000-02-30


2003-07-03Tlin Commander lircran

Corporation: Amendment 39-13099; Docket No. 2000-CE-56-AD.

(a) What airplanes are affected by this AD? This AD affects the following Twin

Commander Aviation Corporation (TCAC) airplane models and serial numbers that are

certificated in any category:

Model Serial Nos.

690D 15001 through 15036 and 15038 through 15040.

695A96001 through 96062, 96065 through 96068, 96070, 96071,96073, 96074, 96076, 96077,and 96079 through 96084, 96086, 96087, and 96089 through 96100.

6958 96063, 96069, 96075, 96078, 96085, and 96204 through 96208.

(b) Who must comply with this AD? Anyone who wishes to operate any of the

airplanes identified in paragraph (a) of this AD must comply with this AD.

(c) What problem does this AD address? The actions specified by this AD are

intended to detect and correct fatigue damage in the wing and fuselage areas without

reducing the service life of the airplane. Such undetected and uncorrected damagecould result in structural failure with consequent loss of control of the airplane.

(d) What must I do to address this problem? To address this problem, youmust initially inspect and modify the wing and fuselage areas (Part 1

Inspection/Modifications as identified in Twin Commander Aircraft CorporationMandatory Service Bulletin No. 214, dated January 26, 2000) and repetitively inspectwith necessary modification or replacement of damaged parts (Part 2 Recurrent

Inspections as identified in Twin Commander Aircraft Corporation Mandatory Service

Bulletin No. 214, dated January 26, 2000) in accordance with the following schedules:

(1) Part 1 Initial Inspections/Modifications: Initially (unless alreadydone) accomplish the Part 1 Inspections/Modifications at whichever compliance time in

paragraph (d)(l)(i) or (d)(l)(ii) of this AD that occurs later:

(i) the compliance times presented in Part 1 Table 1 of Twin

Commander Aircraft Corporation Mandatory Service Bulletin No. 214, dated January 26,2000; Twin Commander Aircraft Corporation Service Publications revision notice to

Service Bulletin No. 214, Revision 1, Release Date: April 19, 2000; and Twin

Commander Aircraft Corporation Service Publications revision notice to Service Bulletin

No. 214, Revision 2, Release Date: May 21, 2001; or


(ii) the Table A compliance times presented on page 1 of the

service information and replicated below:

Current airframe hours Initial compliance time

time-in-service (TIS)

(A) 0000 through 1,700 Upon accumulating 2,700 hours TIS or within the next 36 months after May16, 2003 (the effective date of this AD), whichever occurs first.

(B) 1,701 through 2,500 Upon accumulating 3,400 hours TIS or within the next 36 months after May16, 2003 (the effective date of this AD), whichever occurs first.

(C) 2,501 through 3,000 Upon accumulating 3,800 hours TIS or within the next 36 months after May16, 2003 (the effective date of this AD), whichever occurs first.

(D) 3,001 through 5,000 Upon accumulating 5,500 hours TIS or within the next 30 months after May16, 2003 (the effective date of this AD), whichever occurs first.

(E) 5,001 through 6,000 Upon accumulating 6,400 hours TIS or within the next 24 months after May16, 2003 (the effective date of this AD), whichever occurs first.

(F) 6,001 through 7,500 Upon accumulating 7,800 hours TIS or within the next 18 months after May16, 2003 (the effective date of this AD), whichever occurs first.

(G) Over 7,500 Within the next 12 months after May 16, 2003 (the effective date of this AD).

(2) Part 2 Recurring Inspections: Repetitively inspect as referenced in

Part 2 Recurring Inspections on page 62 of Twin Commander Aircraft CorporationMandatory Service Bulletin No. 214, dated January 26, 2000; Twin Commander Aircraft

Corporation Service Publications revision notice to Service Bulletin No. 214, Revision 1,Release Date: April 19, 2000; and Twin Commander Aircraft Corporation Service

Publications revision notice to Service Bulletin No. 214, Revision 2, Release Date: May21,2001.

(3) Mandatory Replacements and Modifications: If any damage is

found during any inspection required by paragraphs (d), (d)(l), and (d)(2) of this AD,prior to further flight, replace or modify the part as specified in the following:

(i) Twin Commander Aircraft Corporation Mandatory Service

Bulletin No. 214, dated January 26, 2000;

(ii) Twin Commander Aircraft Corporation Service Publications

revision notice to Service Bulletin No. 214, Revision 1, Release Date: April 19, 2000;and

(iii) Twin Commander Aircraft Corporation Service Publications

revision notice to Service Bulletin No. 214, Revision 2, Release Date: May 21, 2001.

(e) Can I comply with this AD in any other way? You may use an alternative

method of compliance or adjust the compliance time if:

2003-07-03


(1) Your alternative method of compliance provides an equivalent level

of safety; and

(2) The Manager, Seattle Aircraft Certification Office (ACO), approves

your alternative. Submit your request through an FAA Principal Maintenance Inspector,who may add comments and then send it to the Manager, Seattle AGO.

Note: This AD applies to each airplane identified in paragraph (a) of this

AD, regardless of whether it has been modified, altered, or repaired in the area subjectto the requirements of this AD. For airplanes that have been modified, altered, or

repaired so that the performance of the requirements of this AD is affected, the

owner/operator must request approval for an alternative method of compliance in

accordance with paragraph (e) of this AD. The request should include an assessment of

the effect of the modification, alteration, or repair on the unsafe condition addressed bythis AD; and, if you have not eliminated the unsafe condition, specific actions you

propose to address it.

(f) Where can I get information about any already-approved alternative

methods of compliance? Contact Della Swartz, Aerospace Engineer, FAA, Seattle

Aircraft Certification Office, 1601 Lind Avenue, SW, Renton, Washington 98055-4065;telephone: (425) 687-4246; facsimile: (425) 687-4248.

(g) What if I need to fly the airplane to another location to comply with this

AD? The FAA can issue a special flight permit under sections 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a

location where you can accomplish the requirements of this AD.

(h) Are any service bulletins incorporated into this AD by reference? Actions

required by this AD must be done in accordance with Twin Commander Aircraft

Corporation Mandatory Service Bulletin No. 214, dated January 26, 2000; Twin

Commander Aircraft Corporation Service Bulletin No. 214, Revision 1, Release Date:

April 19, 2000; and Twin Commander Aircraft Corporation Service Bulletin No. 214,Revision 2, Release Date: May 21, 2001. The Director of the Federal Register approvedthis incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You may getcopies from Twin Commander Aircraft Corporation, 19010 59th Drive N.E., Arlington,Washington 98223-7832; telephone: (360) 435-9797; facsimile: (360) 435-1112. You

may view copies at the FAA, Central Region, Office of the Regional Counsel, 901

Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700, Washington, DC.

(i) When does this amendment become effective? This amendment becomes

effective on May 16, 2003.

2003-07-03


FOR FURTHER INFORMATION CONTACT: Della Swartz, Aerospace Engineer, FAA,Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington98055-4065; telephone: (425) 687-4246; facsimile: (425) 687-4248.

Issued in Kansas City, MO, on March 25, 2003.

Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service.

2003-07-03


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