airbus a320 inst power plant

Customer : AEEType : TF-NRev. Date : Aug 01, 2015

Manual : AMMSelected applicability : ALL

71-00-20-400-040-A - Installation of the Power Plant

Print Date: October 27, 2015 of 42© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

** ON A/C ALL

TASK 71-00-20-400-040-AInstallation of the Power Plant

WARNING: MAKE SURE THAT THE LANDING GEAR GROUND SAFETIES AND THE WHEEL CHOCKSARE IN POSITION.

WARNING: MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOUSUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

CAUTION: DO A CHECK OF THE ENGINE DATA PLATE TO MAKE SURE THAT THE ENGINE IS COR-RECT FOR THE AIRCARFT.IF YOU INSTALL AN ENGINE THAT DOES NOT HAVE THE CORRECT CONFIGURATION FORTHE AIRCRAFT.- DAMAGE TO EQUIPMENT CAN OCCUR IF YOU OPERATE THE ENGINE. - THE TEST

AFTER THE INSTALLATION WILL TELL YOU THE ENGINE CONFIGURATION IS NOT COR-RECT AND MORE WORK WILL BE NECESSARY.

CAUTION: MAKE SURE THAT THE EEC STANDARDS INSTALLED ARE CORRECT. SOME EEC STAND-ARDS CANNOT BE INTERMIXED ON A SAME AIRCRAFT.

FIN : 1000EM1 , 1000EM2

1. Reason for the JobSelf explanatory

2Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment REFERENCE QTY DESIGNATIONNo specific AR ACCESS PLATFORM 1M(3 FT)No specific 1 DRILL - NO 21 (DIA 0.159 IN - 4.039 MM)No specific 1 DYNAMOMETER 15 DAN (33 LBF) - PULLNo specific 1 MAGNIFYING GLASS POWER 10XNo specific AR PENCILNo specific AR PLATE - STEEL, 500X500X3 MM (19.68X19.68X0.12 IN)No specific AR WARNING NOTICE(S)No specific 1 WRENCH - STRAPNo specific Torque wrench: range

to between 15.00 and 150.00 lbf.ft (2.00 and 20.00 m.daN)No specific Torque wrench: range

to between 0.00 and 50.00 lbf.in (0.00 and 0.56 m.daN)No specific Torque wrench: range

to between 62.00 and 900.00 lbf.in (0.70 and 10.00 m.daN)No specific Torque wrench: range

to between 0.20 and 3.60 m.daN (2.00 and 26.00 lbf.ft)No specific Torque wrench: range

to between 2.00 and 20.00 m.daN (15.00 and 150.00 lbf.ft)No specific Torque wrench: range

to between 36.00 and 135.00 m.daN (260.00 and 1000.00 lbf.ft)





REFERENCE QTY DESIGNATION (98D71203001000) 1 CHEST,TORQUE SET-ENGINE R I (S1787CR) 1 ENGINE CRADLE (S487ETT2) 1 ENGINE TROLLEY (TMHEC29-00-00) 1 CRADLE,V2500 ENGINE (TMHET06-00-00) 1 TRAILER,ENGINE GROUND HANDLING(CFM56-5 AND IAE V2500)

B. Consumable Materials REFERENCE DESIGNATION(Material No. V01-457) solvent(Material No. V02-126) lockwire(Material No. V02-147) lockwire(Material No. V02-158A) release agent(Material No. V02-272) safety cable(Material No. V02-273) safety cable(Material No. V02-274) safety cable(Material No. V02-275) safety cable(Material No. V02-276) safety cable(Material No. V02-277) safety cable(Material No. V02-278) safety cable(Material No. V02-279) safety cable(Material No. V02-280) safety cable(Material No. V02-281) safety cable(Material No. V02-282) safety cable(Material No. V02-283) safety cable(Material No. V02-283A) safety cable(Material No. V02-284) safety cable(Material No. V02-285) safety cable(Material No. V02-286) safety cable(Material No. V02-287) safety cable(Material No. V02-288) safety cable(Material No. V02-289) safety cable(Material No. V02-290) safety cable(Material No. V08-030) sealant(Material No. V08-032) primer(Material No. V10-085) anti seize compound(Material No. 14-SBA1) Textile-Lint free Cotton -

C. Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTIONFOR 1000EM1 (ENGINE-1)437AL, 438AR,451AL, 452AR

FOR 1000EM2 (ENGINE-2)447AL, 448AR,461AL, 462AR

D. Expendable Parts





FIG.ITEM DESIGNATION IPC-CSN17 screws 71-51-46-80-01016 seal assembly 71-51-46-80-02015 seal assembly 71-51-46-80-0303 gasket 73-11-48-80-08011 gasket 73-11-48-80-120

E. Referenced Information REFERENCE DESIGNATION

** ON A/C 001-018, 025-025, 027-028, 053-100, 251-450, 513-700(Ref. 05-57-00-200-001-A). Aircraft Stability

** ON A/C 101-104, 108-200, 451-500(Ref. 05-57-00-200-001-B). Aircraft Stability

** ON A/C 201-250(Ref. 05-57-00-200-001-C). Aircraft Stability

** ON A/C ALL(Ref. 12-13-24-612-011-A). IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a

Level Check(Ref. 12-13-79-610-012-A). Prime the Engine Oil System(Ref. 12-13-80-600-010-B). Replenishment of Starter Oil System(Ref. 20-28-00-720-005-A). Check of the Electrical Bonding of the Different Components (But not

Fluid Systems and Components Installed on Composite materials)(Ref. 22-97-00-710-001-A). Operational Test of the LAND CAT III Capability(Ref. 24-21-00-710-042-A). Operational Test of the IDG Disconnect and Reconnect (Reset) Func-

tion - Engine Static(Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power(Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU(Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2)(Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External

Power(Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU(Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine

1(2)(Ref. 30-21-00-710-002-A). Operational Test of the Engine Air Intake Ice Protection (with the En-

gines in operation)(Ref. 31-36-00-740-014-A). Update of the Engine Hours and Cycles in the Flight Data Interface

and Management Unit (FDIMU)(Ref. 31-60-00-860-001-A). EIS Start Procedure(Ref. 31-60-00-860-002-A). EIS Stop Procedure

** ON A/C 001-018, 025-025, 027-028, 053-104, 301-500, 513-700PRE SB 36-1055 for A/C 001-018, 025-025, 027-028, 053-054, 101-104, 301-302, 401-401, 451-452,513-513, 601-601(Ref. 36-11-49-400-016-A). Installation of the Sense Line between the Bleed Pressure-Regulator

Valve (PRV) and the Pylon Interface





REFERENCE DESIGNATION

** ON A/C ALL(Ref. 70-11-50-100-802-A). Local Swab or Wipe Cleaning with Solvent(Ref. 70-23-11-911-013-A). General Torque Tightening Techniques(Ref. 70-23-13-911-010-A). Procedures for the Installation of Preformed Packings(Ref. 70-23-15-912-010-A). Connection of Electrical Connectors(Ref. 70-40-11-911-014-A). Locking Devices General Information(Ref. 70-40-11-911-016-A). General Instructions for Uses of Safety Cable(Ref. 71-00-00-700-011-B). Test No.13 : Pretested Replacement Engine Test(Ref. 71-00-00-710-012-B). Test No.3 : Idle Leak Check(Ref. 71-00-00-710-022-B). Test No.6 : ELectronic Engine Control (EEC) System Idle Test(Ref. 71-00-00-710-046-B). Test No.2 : Wet Motor Leak Check(Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR)(Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR)(Ref. 71-13-00-800-010-A). Functional Check of Fan Cowl Latch Tension(Ref. 71-21-12-200-010-A). Detailed Inspection of FWD Engine Mount Installation(Ref. 71-22-11-200-010-A). Detailed Inspection of AFT Engine Mount Installation(Ref. 71-71-42-400-010-A). Installation of the Drains Mast(Ref. 72-61-49-400-010-B). Installation of the Gearbox Breather Outlet Duct (GBOD)(Ref. 73-13-42-720-010-A). Functional Test of the Fuel Recirculation Cooling System without Bar-

field Tester and without AIDS(Ref. 73-13-42-720-010-A-01). Functional Test of the Fuel Recirculation Cooling System with Barfield

Tester and without AIDS(Ref. 73-13-42-720-010-A-02). Functional Test of the Fuel Recirculation Cooling System without Bar-

field Tester and with AIDS(Ref. 73-13-42-720-010-A-03). Functional Test of the Fuel Recirculation Cooling System with Barfield

Tester and with AIDS(Ref. 73-22-34-710-040-A). Operational Test of the EEC(Ref. 78-30-00-040-012-A). Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for

Ground Maintenance(Ref. 78-30-00-440-012-A). Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after

Ground Maintenance(Ref. 78-30-00-820-010-A). Rig of the Thrust Reverser System(Ref. 78-32-00-010-010-A). Opening of the Thrust Reverser Halves(Ref. 78-32-00-410-010-A). Closing of the Thrust Reverser Halves(Ref. 80-13-49-820-010-B). Rig the Starter Ducts(Ref. 80-13-51-710-040-B). Operational Test of the Pneumatic Starter Valve and FMU with the CF-

DSRef. ESPM 20-48-23 Ref. ESPM 20-48-24 SPM 702304 (Ref. 05-59-00-00). SPECIAL FLIGHTS - DESCRIPTION AND OPERATIONForward Engine Mount SHEET 1Aft Engine Mount SHEET 1Bootstrap InstallationHinge Crossover Beam SHEET 1Fan Cowl and Thrust Reverser BracesTAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1Power Plant, Left Side SHEET 1Left Connectors Location SHEET 1





REFERENCE DESIGNATIONPower Plant, Right Side SHEET 1Forward Junction Box SHEET 1Upper/Lower Link Starter Duct and Link Assembly SHEET 1Forward Junction Box SHEET 1Left Interface Junction Box SHEET 1Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine FireSeals SHEET 1Fire Seal Installation SHEET 1Hydraulic Control Unit SHEET 1FOR 1000EM1 (ENGINE-1)(Ref. 29-11-51-860-040-A). Hydraulic Maintenance Procedure after an Engine Installation (with En-

gine Pump Installed) or after an Engine Pump InstallationFOR 1000EM2 (ENGINE-2)(Ref. 29-13-51-860-001-A). Hydraulic Maintenance Procedure after an Engine Installation (with En-

gine Pump Installed) or after an Engine Pump Installation

B

B

1 BOLT

2 WASHER

3 PYLON

19 SHEAR PIN(2 OFF)

4 forwardENGINE MOUNT

18 BOLT

17 WASHER

16 NUT

9 BOLT

10 WASHER

11 RETAINER

12 RETAINER

5 NUT

6 RETAINER

7 WASHER

8 NUT13 RETAINER

14 WASHER

15 NUT 16865C

C

B

A

C

B

B

A

N_MM_710020_4_XVM0_01_00

Figure 71(IAE)-00-20-991-91000-A / SHEET 1/1 - Forward Engine Mount** ON A/C ALL





UP

6 BARREL NUT

4 AFT MOUNT

2 BOLT

3 WASHER1 PYLON

5 SHEAR PIN

A

A

N_MM_710020_4_XZM0_01_00

Figure 71(IAE)-00-20-991-91200-A / SHEET 1/1 - Aft Engine Mount** ON A/C ALL





3

4

6

3

5

2 11

4

7

5

2

A

A

B

B

N_MM_710020_4_XXM0_01_00

Figure 71(IAE)-00-20-991-91100-A / SHEET 1/2 - Bootstrap Installation** ON A/C ALL





8

9

8

C

C

N_MM_710020_4_XXM0_02_00

Figure 71(IAE)-00-20-991-91100-A / SHEET 2/2 - Bootstrap Installation** ON A/C ALL





B

A

B

A

FAN CASE

HINGE CROSS-OVER BEAM (1)

V-GROOVE (2)

FAN CASE

HINGE CROSS-OVER BEAM (1)

C

CN_MM_710020_4_XZN0_01_00

Figure 71(IAE)-00-20-991-19600-A / SHEET 1/1 - Hinge Crossover Beam** ON A/C ALL





PYLON(1) ADJUSTABLE

STRUT(2) ADJUSTABLE

STRUT

T/R OPENING ACTUATOR

T/R COWL DOOR

A

N_MM_710020_4_YCN0_01_00

Figure 71(IAE)-00-20-991-91400-A / SHEET 1/3 - Fan Cowl and Thrust Reverser Braces** ON A/C ALL





ADJUSTABLESTRUT

T/R OPENINGACTUATOR

THRUST REVERSERCOWL DOOR PYLON

N_MM_710020_4_YCN0_02_00






A

FAN COWLDOOR

4SUPPORT ARM

3BRACKETS

THRUST REVERSERCOWL DOOR

N_MM_710020_4_YCN0_03_00






SENSOR TUBE11 THERMOSTAT

20 PRVSENSOR TUBE

TAI DUCT PYLON

19 COUPLING

18 DUCT

PYLONBLEED AIR

DUCT

7 COUPLING

10 BLEED AIR DUCT19 COUPLING

TAI DUCT

17156A

HYDRAULIC TANKPRESSURISATION TUBE

A

B

C

D

E

A

E

DB

C

N_MM_710020_4_XNM0_01_00

Figure 71(IAE)-00-20-991-90600-A / SHEET 1/1 - TAI Locationand Hydraulic Reservoir Pressurization Tube Location

** ON A/C ALL





16913

HOSESUCTION

1 HYDRAULIC

TUBEPRESSURE

2 HYDRAULIC

11 GASKET

10 WASHER

9 BOLT

8 FUEL SUPPLYTUBE

7 HYDRAULIC CASEDRAIN TUBE

3 GASKET

4 FUEL RETURNTO TANK

TUBE

5 WASHER

6 BOLT

PANELFLUID DISCONNECT

A

B C D EF

B

C

A

E

D

F

N_MM_710020_4_XJM0_01_00

Figure 71(IAE)-00-20-991-90400-A / SHEET 1/1 - Power Plant, Left Side** ON A/C ALL





14006

4004VCCONNECTOR

4101KS-BCONNECTOR

CONNECTOR4101KS-A

G

N_MM_710020_4_XLM0_01_00

Figure 71(IAE)-00-20-991-90500-A / SHEET 1/1 - Left Connectors Location** ON A/C ALL





CONNECTOR4005VC

FORWARDJUNCTION BOX

14047

JUNCTION BOXFORWARD PYLON

W

N_MM_710020_4_XEM0_01_00

Figure 71(IAE)-00-20-991-90200-A / SHEET 1/1 - Power Plant, Right Side** ON A/C ALL





DUCT6 PYLON STARTER

5

4 STARTERDUCT

gc00

a5m

155

3

1 PYLONTAI DUCT

2 TAI DUCT

448VC457VC

402VC

404VC

447VC

406VC

405VC

408VC

407VC

401VC

409VC

403VC

400VC

7

20°

A

A

T-BOLT

COUPLING

COUPLING

N_MM_710020_4_XCM0_01_02

Figure 71(IAE)-00-20-991-90100-A / SHEET 1/1 - Forward Junction Box** ON A/C ALL





UPPER/LOWERLINK ASSEMBLY

pwzx

xe93

97

A

18 BOLT

8 BOLT

7 NUT

13 NUT

11 LOWER LINKASSEMBLY

12 LOWER LINKASSEMBLY

FAN CASEBRACKET

9 WASHER

7 NUT

8 BOLT

8 BOLT

7 NUT

7 NUT

13 NUT

18 BOLT

BOLT 8

9 WASHER

UPPER/LOWERLINK ASSEMBLY

16 UPPER LINKASSEMBLY

17 UPPER LINKASSEMBLY

A

N_MM_710020_4_XDM0_01_00

Figure 71(IAE)-00-20-991-94200-A / SHEET 1/1 - Upper/Lower Link Starter Duct and Link Assembly** ON A/C ALL





A5M

029

AFLANGE A1

A

FLANGE A

D

B

B

C

14

1310

8

10

8

8

10

12

C

7

810

7

9

79

9

11

D

E

14

13

15

11

9

16

9

7

7

9179

7

10

8 10

8

8

10

7

E

1617

TYPICAL

E

E

N_MM_710020_4_XFM0_01_00

Figure 71(IAE)-00-20-991-94300-A / SHEET 1/1 - Forward Junction Box** ON A/C ALL





CONNECTOR4001HA-A

GP5

CONNECTOR452VC-A

CONNECTOR454VC

CONNECTOR450VC-A

14054

A

A

N_MM_710020_4_XGM0_01_00

Figure 71(IAE)-00-20-991-90300-A / SHEET 1/1 - Left Interface Junction Box** ON A/C ALL





B

B

FIRE SHIELD

BLOCK SEAL

15 FIRE SEALASSEMBLY

THRUST REVERSERBRACKET

16 FIRE SEALASSEMBLY

BLOCK SEAL

A

B8373

A

N_MM_710020_4_XAA0_01_00

Figure 71(IAE)-00-20-991-19700-A / SHEET 1/1 - Inspection for the ThrustReverser Brackets and Inspection for/Installation of the Engine Fire Seals

** ON A/C ALL





GC00A5M073

APOST-SB-ENG-72-0230

FIRE SHIELD

15 FIRE SEAL ASSEMBLY

17 SCREWS (4 PLACES)

16 FIRE SEAL ASSEMBLY

A

N_MM_710020_4_XAB0_01_00

Figure 71(IAE)-00-20-991-19800-A / SHEET 1/1 - Fire Seal Installation** ON A/C ALL





13480A

LEVER3 LOCKOUT

FLAG4 WARNING

2 LOCKPIN

PYLON

1 HCU

A

A

N_MM_710020_4_XAM0_01_00

Figure 71(IAE)-00-20-991-90000-A / SHEET 1/1 - Hydraulic Control Unit** ON A/C ALL





3. Job Set-up

Subtask 71-00-20-860-052-B

A. Aircraft Maintenance Configuration

(1) Make sure the aircraft is stable (Ref. AMM TASK 05-57-00-200-001) .

NOTE: If the aircraft is on jacks, make sure it is leveled before you install the engine.

(2) On the center pedestal, on the ENG panel 115VU, make sure that a WARNING NOTICE(S) is inposition to tell persons not to start the engine.

(3) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GNDPWR/1(2) pushbutton switch is off. Make sure that a WARNING NOTICE(S) is in position to tellpersons not to energize the FADEC 1(2).

(4) On the panel 30VU, make sure that the APU BLEED pushbutton switch is released (ON legendoff). Make sure that a WARNING NOTICE(S) is in position to tell persons not to press the APUBLEED pushbutton switch. Make sure that a WARNING NOTICE(S) is in position on the HP groundconnector to tell persons not to pressurize the pneumatic system.

(5) Make sure that the ACCESS PLATFORM 1M(3 FT) is in position.

Subtask 71-00-20-010-053-A

B. Make sure that the fan cowl doors are open (Ref. AMM TASK 71-13-00-010-010) :

(1) FOR 1000EM1 (ENGINE-1)437AL, 438AR


Subtask 71-00-20-040-051-A

C. Make sure that the thrust reverser Hydraulic Control Unit (HCU) is deactivated (Ref. AMM TASK 78-30-00-040-012) .

Subtask 71-00-20-865-051-A

WARNING: MAKE SURE THAT YOU OPEN THE CIRCUIT BREAKERS AS FOLLOWS:- 1JH, 2JH1 AND 3JH1 BEFORE 2KS1- 1JH, 2JH2 AND 3JH2 BEFORE 2KS2.IF YOU DO NOT OBEY THIS SEQUENCE, THERE IS A RISK OF ELECTROCUTION. THIS ISBECAUSE YOU WILL START CONTINUOUS IGNITION IF YOU OPEN CIRCUIT BREAKER2KS1 OR 2KS2 FIRST.

WARNING: OPEN THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND5DA1(2,3) BEFORE YOU OPEN THE PHC CIRCUIT BREAKERS 2DA1(2,3). IF YOU DO NOTOBEY THIS SEQUENCE:- THE PROBES WILL BECOME TOO HOT.- THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PER-

SONNEL.

D. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL DESIGNATION FIN LOCATION

** ON A/C 001-018, 025-025, 027-028, 053-104, 108-500, 513-65049VU COM/CVR/SPLY 2RK E14





PANEL DESIGNATION FIN LOCATION49VU COM/CVR/CTL 4RK E13

** ON A/C ALL49VU ENGINE/1 AND 2/IGN/SYS A 1JH A0349VU ANTI ICE/PROBES/AOA/1 4DA1 D0449VU ANTI ICE/PROBES/PITOT/1 3DA1 D0249VU ANTI ICE/RAIN/RPLNT/CAPT 1DB1 D01

** ON A/C 651-70049VU COM/CVR/SPLY 23RK E1449VU COM/CVR/CTL 26RK E13

** ON A/C ALL121VU ENGINE/ENG1 AND 2 FIRE EX-

TIG/BTL1/SQUIB/B2WE1 Q44

121VU ENGINE/ENG1 AND 2 FIRE EX-TIG/BTL1/SQUIB/A

1WE1 Q43

121VU ENGINE/ENG1 AND 2 FIRE EX-TIG/BTL2/SQUIB/B

2WE2 Q42


1WE2 Q41

122VU ANTI ICE/WINDOWS/R 4DG2 W14122VU ANTI ICE/RAIN/RPLNT/F/O 1DB2 W11122VU ANTI ICE/WINDOWS/L 4DG1 X14122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12123VU ANTI ICE/L/WHSLD 1DG1 AF10123VU ANTI ICE/R/WHSLD 1DG2 AF03FOR FIN 1000EM1 (ENGINE-1)49VU ENGINE/1/FIRE DET/LOOP A 7WD1 A0649VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04121VU RCDR/DFDR 7TU K16121VU ENGINE/IGN/ENG1/SYS B 3JH1 P41121VU ENGINE/IGN/ENG1/SYS A BAT 2JH1 P39121VU ENGINE/ENG1/FIRE DET/LOOP B 8WD1 Q38121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41122VU ELEC/GCU/1 2XU1 T26122VU ANTI ICE/ENG/1 1DN1 X10FOR FIN 1000EM2 (ENGINE-2)49VU ENGINE/2/FIRE DET/LOOP B 8WD2 A0749VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05121VU HYDRAULIC/HYD POWER/Y 3803GX N30121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42





PANEL DESIGNATION FIN LOCATION121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40121VU ENGINE/ENG2/FADEC B/AND EIU 2 4KS2 Q40121VU ENGINE/ENG2/FIRE DET/LOOP A 7WD2 Q39122VU ELEC/GCU/2 2XU2 T27122VU ANTI ICE/ENG/2 1DN2 W10123VU Y HYD/ELEC/PUMP 3802GX AB06123VU Y HYD/ELEC/ELEC PUMP/NORM 3801GX AB03

Subtask 71-00-20-865-070-A

WARNING: OPEN THE PROBE HEATER AND WINDOW HEATER CIRCUIT-BREAKERS BEFOREYOU OPEN THE PHC AND WHC CIRCUIT BREAKERS. IF YOU DO NOT OBEY THIS SE-QUENCE:- THE PROBES WILL BECOME TOO HOT.- THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PER-

SONNEL.

E. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL DESIGNATION FIN LOCATION49VU ANTI ICE/PROBES/PHC/1 2DA1 D03122VU ANTI ICE/WHC/2 5DG2 W13122VU ANTI ICE/WHC/1 5DG1 X13122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12

Subtask 71-00-20-210-050-A

F. Check of the Cowling for Correct Condition

(1) Do a check of the electrical connectors of the aft and forward junction boxes, for correct condition.

(2) Make sure that these parts are not damaged:

(a) The forward engine mount (Ref. AMM TASK 71-21-12-200-010)

(b) The aft engine mount (Ref. AMM TASK 71-22-11-200-010)

(c) The pylon structure that you can see.

Subtask 71-00-20-110-052-A

G. Clean Components

(1) Clean these parts by (Ref. AMM TASK 70-11-50-100-802) .

(a) The mating faces and the shear pins and the fastener holes on the forward and aft enginemounts

(b) The forward and aft mount pads on the pylon.

(2) Clean the bolts (1), (18) and (2), the nuts (16) and (5) and the barrel nuts (6) by (Ref. AMM TASK 70-11-50-100-802) .(Ref. Fig. Forward Engine Mount SHEET 1) (Ref. Fig. Aft Engine Mount SHEET 1)

(3) Make sure that there are no traces of seizure or wear.

Subtask 71-00-20-230-051-A

H. Do an ultra-high sensitivity fluorescent penetrant inspection of the engine mount bolts (1), (2) and (18)SPM 702304. No cracks are permitted.





(Ref. Fig. Forward Engine Mount SHEET 1) (Ref. Fig. Aft Engine Mount SHEET 1)

Subtask 71-00-20-240-051-A

J. Visual Inspections

(1) Do a visual inspection of the forward engine mount nuts (5) and (16) with a MAGNIFYING GLASSPOWER 10X. Do not remove the silver plating.(Ref. Fig. Forward Engine Mount SHEET 1) If an engine nut is cracked, reject it.

(2) Do a visual inspection of the barrel nuts (6) with a MAGNIFYING GLASS POWER 10X . No cracks,nicks, scratches or gouges are allowed. If any damage is found, replace the barrel nut. Silver platingmissing from the external surface of the barrel nut is acceptable.The threads must be in good condition and no silver plating is allowed to be missing from the threads.If silver plating is missing from the barrel nut threads, the barrel nut must be replaced.

Subtask 71-00-20-210-060-A

K. Do a Check of the Running Torque of the Forward and Aft Mount Bolts

(1) Do a check of the running torque of the forward engine mount bolts as follows:(Ref. Fig. Forward Engine Mount SHEET 1)

(a) Apply a thin layer of anti seize compound (Material No. V10-085) to the threads of the enginemount bolts, the nuts and the washers.

(b) Install the washers under the head of the bolts (1) and (18).

(c) Install the bolts (1) and (18) through holes in the pylon and the forward mount.

(d) Install the nuts (5) and (16) on the bolts (1) and (18).

(e) Tighten the nuts by hand until they are hard to turn.

NOTE: Make sure that the nuts are correctly threaded on the bolts.

(f) Use a torque wrench to tighten the nuts until at least two full threads show on the other side ofthe nuts (Ref. AMM TASK 70-23-11-911-013) .

1 Measure the torque required to tighten the bolt (Ref. AMM TASK 70-23-11-911-013) . Theminimum torque should be to 70 lbf.in (0.79 m.daN). The maximum torque should be to 600 lbf.in (6.78 m.daN).

2 If the bolt torque is less than 70 lbf.in (0.79 m.daN), replace the nut (5) or (16) and do steps(a) thru (f) 1_ again.

3 If the torque is more than 600 lbf.in (6.78 m.daN), remove the bolt and the nut and look fordamaged threads. If the threads are damaged, replace the bolt and nut and do steps (a) thru(f) 2_ again.

(g) Remove the forward mount bolts and nuts.

(2) Do a check of the running torque of the aft engine mount bolts as follows:(Ref. Fig. Aft Engine Mount SHEET 1)

(a) Apply a thin layer of anti seize compound (Material No. V10-085) to the threads of the enginemount bolts, the nuts and the washers.

(b) Install the washers (3) under the head of the bolts (2).

(c) Install the aft engine mount bolts (2) into the barrel nuts (6).

(d) Tighten the bolts by hand until they are hard to turn.





NOTE: Make sure that the nuts are correctly threaded on the bolts.

(e) Use a torque wrench to tighten the nuts until at least two full threads show on the other side ofthe nuts (Ref. AMM TASK 70-23-11-911-013) .

1 Measure the torque required to tighten the bolt (Ref. AMM TASK 70-23-11-911-013) . Theminimum torque should be to 90 lbf.in (1.02 m.daN). The maximum torque should be to 800 lbf.in (9.04 m.daN).

2 If the bolt torque is less than 90 lbf.in (1.02 m.daN), replace the nut (6) and do steps (a) thru(e) 1_ again.

3 If the torque is more than 800 lbf.in (9.04 m.daN), remove the bolt and the nut and look fordamaged threads. If the threads are damaged, replace the bolt and nut and do steps (a) thru(e) 2_ again.

(f) Remove the aft mount bolts and nuts.

Subtask 71-00-20-420-050-A

L. If replacement engine does not have all its equipment, remove the accessories from the removed engineand install them on the replacement engine.

4. Procedure

Subtask 71-00-20-420-051-A

A. Put the replacement engine in position under the pylon

(1) Put the ENGINE TROLLEY (S487ETT2) or TRAILER,ENGINE GROUND HANDLING(CFM56-5AND IAE V2500) (TMHET06-00-00) and ENGINE CRADLE (S1787CR) or CRADLE,V2500ENGINE (TMHEC29-00-00) with the replacement engine in position under the pylon.

(2) Install the forward hinge arm (4) and (5) with the ball pins (1) on the forward bootstrap system.(Ref. Fig. Bootstrap Installation)

(3) Install the dynamometers and chain pulley blocks on the bootstrap system.

(4) Attach the chain hooks to the engine cradle.

(5) Remove the pins that attach the engine cradle to the engine trolley.

(6) Put the locking levers of the handling hoist in UP position. Lift the engine cradle to disengage it fromthe trolley.

(7) Slightly raise the forward section of the engine cradle then the aft section.

NOTE: Make sure that the differential load read on the dynamometers is less than:- 600 daN (1350 lbf) (611.6 Kg) between the 2 front chains.- 200 daN (450 lbf) (203.9 Kg) between the 2 rear chains.

NOTE: Use the level indicators on the forward hinge arms of the bootstrap to keep the hinge arms asnear as possible to the horizontal position.

Subtask 71-00-20-210-052-A

B. Make certain that the hinge crossover beam (1) is correctly engaged in the V-groove (2).(Ref. Fig. Hinge Crossover Beam SHEET 1)

Subtask 71-00-20-420-052-A

C. Put the Power Plant in position





WARNING: DEATH OR SERIOUS INJURY MAY RESULT IF THE POWER PLANT FALLS ON PER-SONNEL. THE POWER PLANT WEIGHS APPROXIMATELY 7300 POUNDS.

CAUTION: DO NOT INSERT THE SHEAR PINS OF ONE MOUNT BEFORE THE OTHER OR DAM-AGE TO THE MOUNTS AND PYLON CAN RESULT.

(1) Keep the pylon and engine face of the forward and aft attach fittings parallel so as to put the locatingpins easily in their location.

NOTE: Rear lifts give the roll attitude.

NOTE: At the forward end you can move the engine laterally by plus or minus 20 mm (0.79 in.).

(a) To move the engine to the left side, lift with the right hand hoist and/or lower with the left handhoist.

(b) To move the engine to the right side, lift with the left hand hoist and/or lower with the right handhoist.

(2) Lift the engine:

CAUTION: DO NOT INSTALL THE LOCATING PINS OF ONE MOUNT BEFORE THE OTHER ORDAMAGE TO MOUNTS AND PYLON COULD RESULT.

(a) Slowly lift the engine to the pylon. Make sure that the shear pins on the engine mounts engagewith the holes in the pylon.

(3) Lift the engine chain continuously until a mating load of 200 daN (450 lbf) (203.9 Kg) maximum foreach chain is shown on the dynamometers.

Subtask 71-00-20-420-053-A

D. Installation of the Forward and Aft Engine Mounts

(1) Install the forward engine mount.(Ref. Fig. Forward Engine Mount SHEET 1)

(a) Lubricate the bolts (1) and (18), the washers (2) and (17), the nuts (5) and (16) and the shearpins (19) with anti seize compound (Material No. V10-085).

NOTE: The forward center bolt has no upper retainer, it is locked by lockwire.

(b) Install the bolts (18), the washers (17), the retainers (12) and the nuts (16).

(c) Put the nut (5) and the retainer (6) in position.

(d) Install the washer (7) and the nut (8).

(e) TORQUE the nut (8) to between 35 and 40 lbf.in (0.40 and 0.45 m.daN).

(f) Install the bolt (1) and the washer (2) on the middle front engine mount.

(g) Tighten the bolts (1) and (18) with a standard wrench.

NOTE: You must install the washers (17) and (2) with the recessed side against bolt head.

(h) Torque the forward engine mount bolts.

CAUTION: THIS IS NOT THE FINAL TORQUE FOR THE FORWARD ENGINE MOUNTBOLTS.





1 Hold the nut (16) stable with a wrench and TORQUE the bolts (1) and (18) to between 88.49 and 132.74 lbf.ft (12.00 and 18.00 m.daN).

(i) Remove the padding from between the engine and the engine mount.

(2) Install the aft engine mount attach fittings.(Ref. Fig. Aft Engine Mount SHEET 1)

(a) Lubricate the bolts (2), the washers (3) and the shear pins (5) with anti seizecompound (Material No. V10-085).

(b) Installation of the barrel nut:

CAUTION: BARREL NUT MUST BE INSTALLED WITH ROUNDED SIDE UP.

1 Install the barrel nut (6), the bolts (2) and washers (3).

NOTE: You must install the washers (3) with the recessed side against bolt head.

(c) TORQUE (final value) the bolts (2) to between 65 and 70.5 m.daN (479.35 and 519.91 lbf.ft) (Ref. AMM TASK 70-23-11-911-013) .

NOTE: After you tighten the engine mount bolts to the final torque, make sure that the surfacesbetween the pylon and the aft engine mount are in contact.

(d) Install safety cable (Material No. V02-275) (Ref. AMM TASK 70-40-11-911-016) on bolts (2).Alternate: Use lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-014) ,safety cable (Material No. V02-272), safety cable (Material No. V02-273),safety cable (Material No. V02-274), safety cable (Material No. V02-276), safetycable (Material No. V02-277), safety cable (Material No. V02-278),safety cable (Material No. V02-279), safety cable (Material No. V02-280) or safetycable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .

NOTE: If the pylon flexible seals were removed, install them.

Subtask 71-00-20-080-050-A

E. Removal of the Lifting Equipment and Bootstrap Assembly

(1) Remove the lifting equipment.

(a) Put the pulley locking levers in the DOWN position.

(b) Reduce the load on the engine cradle using the pulley blocks.

(c) Disconnect the engine cradle from the engine.

(d) Lower the engine cradle. Make sure that the engine cradle does not hit the engine.

(e) Install the engine cradle on the engine trolley.

(f) Remove the four chain hooks from the engine cradle.

(g) Remove the engine trolley rearwards.

(2) Remove the bootstrap assembly as follows:(Ref. Fig. Bootstrap Installation)

(a) Remove the four chain pulley blocks and the dynamometers from the rear beam (9) and theforward hinge arms (4) and (5).

(b) Remove the pins (8) and remove the rear beam (9).

(c) Remove the pins (1) and remove the link (2).





(d) Remove the pins (3) and remove the left and right hinge arms (4) and (5).

(e) Release the left and right clamps (7) and remove the spacer and the center hinge clamp from thepylon.

Subtask 71-00-20-760-050-A

F. Do a check of the electrical bonding

(1) Measure the resistance value (ohmic) (Ref. AMM TASK 20-28-00-720-005) . Make sure that theresistance between the engine and the pylon is not more than 1.5 milliohm.

Subtask 71-00-20-420-054-A

G. Final Torque of the Bolts of the Forward Mount

CAUTION: MAKE SURE THAT THE TORQUE WRENCH DOES NOT TOUCH THE FORWARD EN-GINE MOUNT DURING TIGHTENING TO NOT CHANGE THE TORQUE APPLIED TOTHE BOLTS.

(1) Use the special tool CHEST,TORQUE SET-ENGINE R I (98D71203001000) to TORQUE the forward mount bolts to the final torque value to between 43.39 and 47.45 m.daN (319.99 and 349.93 lbf.ft) (Ref. AMM TASK 70-23-11-911-013) .

NOTE: The given torque values take into account the length of the torque wrench.

(a) Use the Torque Wrench to torque the four forward mount bolts (18).

(b) Use the Torque Wrench and Load Reducer to torque the center bolt (1) of the forward mount.

NOTE: The use of the load reducer (P/N GA184A) with the torque wrench (P/N TQFRM14)changes the value of the torque selected. You must set a value between 13 m.daN (96lbf.ft) and 14 m.daN (103 lbf.ft) on the wrench to get the torque required for the forwardcenter mount bolt.

NOTE: After you tighten the engine mount bolts to the final torque, make sure that the surfacesbetween the pylon and the forward engine mount are in contact.

(2) Install safety cable (Material No. V02-275) (Ref. AMM TASK 70-40-11-911-016) on bolt (1).Alternate: Use lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-014) ,safety cable (Material No. V02-272), safety cable (Material No. V02-273),safety cable (Material No. V02-274), safety cable (Material No. V02-276), safetycable (Material No. V02-277), safety cable (Material No. V02-278),safety cable (Material No. V02-279), safety cable (Material No. V02-280) or safetycable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .

NOTE: You can use lockwire diameters ranging from 0.8mm to 1.2mm to safety the bolt (1).

(3) Install the retainers (11) and (13) secured with the bolt (9), the washers (10) and (14) and the nut(15).

(4) TORQUE the bolts (9) to between 24 and 36 lbf.in (0.27 and 0.41 m.daN) (Ref. AMM TASK 70-23-11-911-013) .

(5) Remove the fan cowl and thrust reverser braces(Ref. Fig. Fan Cowl and Thrust Reverser Braces)

(a) Put the fan cowl hold-open rods into position to hold the weight of the fan cowls (Ref. AMM TASK 71-13-00-010-010) .





(b) Put the thrust reverser half hold-open rods into position to hold the weight of the thrust reverserhalves (Ref. AMM TASK 78-32-00-010-010) .

(c) Remove the support arms (5) and (6) from the fan cowls and the thrust reverser halves.

(d) Remove the adjustable struts (1) and (2).

5. Close-up

Subtask 71-00-20-020-081-A

A. Remove ballast installed for aircraft stability.

(1) If all engines are in place, remove all ballast installed for aircraft stability.

Subtask 71-00-20-630-050-A

B. Remove caps from the open ends.

** ON A/C 001-018, 025-025, 027-028, 053-104, 301-500, 513-700PRE SB 36-1055 for A/C 001-018, 025-025, 027-028, 053-054, 101-104, 301-302, 401-401, 451-452, 513-513,601-601

Subtask 71-00-20-420-096-A

C. Installation of the Bleed Pressure Regulator Valve (PRV) Sense Line.

(1) Install the sense line between the bleed pressure regulator valve (PRV) and the pylon interface (Ref. AMM TASK 36-11-49-400-016) .

** ON A/C ALL

Subtask 71-00-20-420-055-A

D. Installation of Components on the Left and the Right Sides of the Engine

(1) Install these components on the left side of the engine.

(a) Connect the sensor tubes.(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)

1 Connect the pressure regulating valve sensor tube (20).

2 TORQUE the tube union nut to between 2.0 and 2.3 m.daN (14.75 and 16.96 lbf.ft).

3 Connect the thermostat sensor tube (11).

4 TORQUE the union nut to between 1.5 and 1.7 m.daN (11.06 and 12.54 lbf.ft) (Ref. AMM TASK 70-23-11-911-013) .

(b) Connect the fuel tubes to the fluid disconnect panel.(Ref. Fig. Power Plant, Left Side SHEET 1)

1 Install a new IPC -CSN (73-11-48-80-120) gasket (11) on the fuel supply tube (8) (Ref. AMM TASK 70-23-13-911-010) .

2 Put the fuel supply tube in position on the fluid disconnect panel and install the four bolts (9)and the washers (10).

3 TORQUE the bolts to 100 lbf.in (1.13 m.daN) (Ref. AMM TASK 70-23-11-911-013) .

4 Safety the bolts (9) with lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-014) .Alternate: Use safety cable (Material No. V02-272), safety cable (Material No. V02-273),safety cable (Material No. V02-274), safety cable (Material No. V02-275),safety cable (Material No. V02-276) safety cable (Material No. V02-277), safetycable (Material No. V02-278),





safety cable (Material No. V02-279), safety cable (Material No. V02-280) or safetycable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .

5 Install a new IPC -CSN (73-11-48-80-080) gasket (3) on the fuel return to tank tube (4).

6 Put the fuel return to tank tube in position on the fuel disconnect panel and install the fourbolts (6) and the washers (5).

7 TORQUE the bolts (6) to between 0.38 and 0.42 m.daN (33.63 and 37.17 lbf.in) (Ref. AMM TASK 70-23-11-911-013) .

8 Safety the bolts (6) with lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-014) .Alternate: Use safety cable (Material No. V02-272), safety cable (Material No. V02-273),safety cable (Material No. V02-274), safety cable (Material No. V02-275),safety cable (Material No. V02-276) safety cable (Material No. V02-277), safetycable (Material No. V02-278),safety cable (Material No. V02-279), safety cable (Material No. V02-280) or safetycable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .

(c) Connect the hydraulic tubes to the fluid disconnect panel.

1 Connect the hydraulic case drain connector (7) to the fluid disconnect panel.

2 TORQUE the connector (7) to between 215 and 245 lbf.in (2.43 and 2.77 m.daN) (Ref. AMM TASK 70-23-11-911-013) .

3 Connect the hydraulic pressure tube connector (2) to the fluid disconnect panel.

4 TORQUE the connector (2) to between 9.7 and 10.7 m.daN (71.53 and 78.91 lbf.ft) (Ref. AMM TASK 70-23-11-911-013) .

5 Connect the hydraulic suction tube connector (1) to the fluid disconnect panel. Handtightenthe connector.

(d) Connect the cabin air duct.(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)

1 Position the duct and install the coupling (7).

2 TORQUE the coupling to between 0.85 and 0.96 m.daN (75.22 and 84.96 lbf.in).

3 Install the coupling. To do this, tap the coupling with a mallet.

4 TORQUE the coupling again to between 0.79 and 0.9 m.daN (69.91 and 79.65 lbf.in).

5 Tap the coupling again.


(e) Connect the Thermal Anti-Ice (TAI) duct.(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)

1 Position the TAI duct and install the couplings (19).

2 TORQUE the coupling (19) to between 0.5084 and 0.6214 m.daN (44.99 and 54.99 lbf.in).


4 TORQUE the coupling again to between 0.5084 and 0.6214 m.daN (44.99 and 54.99 lbf.in) (Ref. AMM TASK 70-23-11-911-013) .







(f) On the fan case near the V-groove at 11 o'clock, connect the electrical connector 4004VC.(Ref. Fig. Left Connectors Location SHEET 1)

(g) Connect the thrust reverser harness connector 4101KS-A and 4101KS-B on the thrust reverserHydraulic Control Unit (HCU).(Ref. Fig. Left Connectors Location SHEET 1)

(2) Install these components from the right side of the engine.(Ref. Fig. Power Plant, Right Side SHEET 1)

(a) Connect the TAI duct (2).(Ref. Fig. Forward Junction Box SHEET 1)

CAUTION: MAKE SURE THE COUPLINGS DO NOT TOUCH ADJACENT COMPONENTSOR FAN COWL DOORS (WHEN CLOSED). DAMAGE TO COMPONENTS CANOCCUR.

1 Position the duct on the pylon and install the coupling (3).

2 Connect the duct (2) with the couplings (3). Make sure the seal is installed correctly. Makesure that the t-bolt (7) on the coupling (3) is installed 20°angle from the top of the duct sothat it does not touch the fan cowl door hinge when closed.

3 TORQUE the coupling to between 0.51 and 0.62 m.daN (45.13 and 54.87 lbf.in).





(b) Connect the starter duct.(Ref. Fig. Forward Junction Box SHEET 1) (Ref. Fig. Upper/Lower Link Starter Duct and Link Assembly SHEET 1) (Ref. Fig. Forward Junction Box SHEET 1)

NOTE: Adjust the link assemblies when the engine is installed on the pylon.

1 Remove the four nuts (7), washers (9) and bolts (8) from the two upper link assemblies (16)and (17). Remove the upper link assemblies.

2 Remove the four nuts (7), washers (9) and bolts (8) from the lower link assemblies (11) and(12). Remove the lower link assemblies.

NOTE: It may be necessary to loosen the coupling at the valve. If this is required, torque thecoupling nut as explained in steps 4_ thru 7_.

3 Position the starter duct (4) on the pylon starter duct (6) and install the coupling (5).

4 TORQUE coupling (5) to between 0.79 and 0.9 m.daN (69.91 and 79.65 lbf.in).

5 Lightly hit around the outside of the coupling with a fiber hammer.

6 TORQUE coupling (5) again to between 0.79 and 0.9 m.daN (69.91 and 79.65 lbf.in).

7 Repeat steps 4_ thru 6_ two more times.

8 Connect the lower link assemblies (11) and (12) to the Fan case brackets with bolts (8),washers (9) and nuts (7). Do not torque the nuts at this time.

9 Connect the upper link assemblies (16) and (17) to the Fan case brackets with bolts (8),washers (9) and nuts (7). Do not torque the nuts at this time.





10 Loosen the nuts (13) on the bolts (18) on the support links (11), (12), (16) and (17).

11 Adjust the links as needed to attach to the starter duct (4) without preload.

12 Install the four link assemblies (11), (12), (16) and (17) onto the starter duct (4) with bolts (8),washers (9) and nuts (7).

13 TORQUE the eight nuts (7) to between 0.6 and 0.8 m.daN (53.10 and 70.80 lbf.in).

14 TORQUE the four nuts (13) on the bolts (18) on the link assemblies (11), (12), (16)and (17) to between 1 and 1.2 m.daN (88.50 and 106.19 lbf.in). The link threadsmust block the safety holes in the link assemblies. This can be checked with a piece oflockwire (Material No. V02-126).Alternate: Use safety cable (Material No. V02-282), safety cable (Material No. V02-283),safety cable (Material No. V02-283A), safety cable (Material No. V02-284),safety cable (Material No. V02-285), safety cable (Material No. V02-286), safetycable (Material No. V02-287),safety cable (Material No. V02-288), safety cable (Material No. V02-289) or safetycable (Material No. V02-290) (Ref. AMM TASK 70-40-11-911-016) .Put the lockwire or safety cable into each safety hole. The lockwire or safety cable must notgo through.

15 Rig the starter duct (Ref. AMM TASK 80-13-49-820-010) .

(c) On the fan case near the V-groove at 1 o'clock, connect the electrical connector 4005VC.(Ref. Fig. Power Plant, Right Side SHEET 1)

(d) On the forward pylon junction box, connect the electrical connectors 402VC, 404VC, 405VC,406VC, 408VC, 447VC, 448VC and 457VC (Ref. AMM TASK 70-23-15-912-010) .(Ref. Fig. Forward Junction Box SHEET 1)

(e) On the pylon junction box, connect the electrical connectors 401VC, 403VC, 407VC and 409VC (Ref. AMM TASK 70-23-15-912-010) .(Ref. Fig. Forward Junction Box SHEET 1)

(f) On the pylon junction box, connect the generator harness connector 400VC.

CAUTION: CONTACTS HAVE TO BE REPLACED IN CASE OF ANY WEAR AND TEARSIGNS (HOLES, SCRATCH, DISCOLORATION, TEARS, PITTED MARKS).

1 Do not clean the contacts with abrasive material.

2 Connect a DYNAMOMETER 15 DAN (33 LBF) - PULL to the test pin to do a pin retentioncheck of the sockets.

a The minimum extraction force value must be 1.2 daN (2.7 lbf) for a CANNON contactRef. ESPM 20-48-23.

b The minimum extraction force value must be 2.8 daN (6.3 lbf) for a FRAMATOME(former SOURIAU) contact Ref. ESPM 20-48-24.

3 Tighten the connector with a WRENCH - STRAP until the orange colour is shown inthe window of the coupling nut and safety the generator harness connector 400VC withlockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-014) .Alternate: Use safety cable (Material No. V02-272), safety cable (Material No. V02-273),safety cable (Material No. V02-274), safety cable (Material No. V02-275),safety cable (Material No. V02-276), safety cable (Material No. V02-277),safety cable (Material No. V02-278), safety cable (Material No. V02-279), safetycable (Material No. V02-280) orsafety cable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .(Ref. Fig. Forward Junction Box SHEET 1)





(g) On the aft interface junction box, connect the electrical connectors 450VC, 452VC and 454VC.(Ref. Fig. Left Interface Junction Box SHEET 1)

(h) On the forward section of the combustion case at 11 o'clock, connect the hydraulic reservoirpressurization tube to the union (engine 1 only).

NOTE: The elbowed union of the hose must be connected to the engine.

(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1) TORQUE the union to between 1.5 and 1.7 m.daN (11.06 and 12.54 lbf.ft) (Ref. AMM TASK 70-23-11-911-013) .

(i) Install the drains mast (Ref. AMM TASK 71-71-42-400-010) .

Subtask 71-00-20-410-062-B

E. If the engine fire seals are not present, install them as follows:(Ref. Fig. Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine FireSeals SHEET 1) (Ref. Fig. Fire Seal Installation SHEET 1)

(1) Close the relevant thrust reverser half (Ref. AMM TASK 78-32-00-410-010) :



(4) Put the fire IPC -CSN (71-51-46-80-030) seal assembly (15) or IPC -CSN (71-51-46-80-020) sealassembly (16) on the heatshield so there is full contact between the seal and the thrust reverserbracket assembly. The fire seal should rest against the bracket with no compression.

(5) Mark the forward and bottom outline of the fire seal on the heatshield with a PENCIL.

(6) Open the relevant thrust reverser half (Ref. AMM TASK 78-32-00-010-010) :



(9) Measure 0.125 in. (3.18 mm) aft of the fire seal forward outline and make a parallel line on theheatshield with a PENCIL.

(10) Align the fire seal with the aft outline and bottom outline on the heatshield.

(11) Put a PLATE - STEEL, 500X500X3 MM (19.68X19.68X0.12 IN) between the strut fairing and theheatshield before you drill the holes to protect the strut fairing.

(12) Drill through the three fire seal pilot holes into the heatshield. Enlarge the holes with a DRILL - NO 21(DIA 0.159 IN - 4.039 MM).

(13) Remove the burrs from the holes in the fire seal and the heatshield.

(14) Cleaning

WARNING: DO NOT GET CLEANING FLUID ON YOUR SKIN OR IN YOUR EYES. PUT ON PRO-TECTIVE CLOTHING, GOGGLES AND A FACE MASK. USE THE FLUID IN A WELLVENTILATED AREA. DO NOT BREATHE THE VAPOR. IF YOU GET THE CLEANINGFLUID ON YOUR SKIN OR IN YOUR EYES FLUSH IT AWAY WITH WATER. GETMEDICAL AID IF YOUR SKIN OR EYES BECOME IRRITATED.





(a) Clean the fire seal and the aft and inboard surfaces of the heatshield and block seal with aTextile-Lint free Cotton - (Material No. 14-SBA1) made moist with solvent (Material No. V01-457).Wipe the surfaces dry before the cleaning solvent evaporates.

(15) Applying of primer

WARNING: DO NOT GET THE PRIMER ON YOUR SKIN OR IN YOUR EYES. PUT ON PRO-TECTIVE CLOTHING, GOGGLES AND A FACE MASK. USE THE PRIMER INA WELL VENTILATED AREA. DO NOT BREATHE THE GAS. IF YOU GET THEPRIMER ON YOUR SKIN OR IN YOUR EYES, FLUSH IT AWAY WITH WATER. GETMEDICAL AID IF YOUR SKIN OR EYES BECOME IRRITATED.

(a) Apply primer (Material No. V08-032) to the mating surfaces of the fire seal assembly. Allow to airdry for twenty minutes.

(16) Apply release agent (Material No. V02-158A) to the aft surface and inboard corner of the block seal.

(17) Applying of sealant

WARNING: DO NOT GET THE SEALANT ON YOUR SKIN OR IN YOUR EYES. PUT ON PRO-TECTIVE CLOTHING, GLOVES, GOGGLES AND A FACE MASK. USE THE SEAL-ANT IN A WELL VENTILATED AREA. DO NOT BREATHE THE GAS. IF YOU GETTHE SEALANT ON YOUR SKIN OR IN YOUR EYES GET MEDICAL AID IMMEDI-ATELY.

(a) Apply sealant (Material No. V08-030) to the mating surfaces of the fire seal.

(18) Put the fire seal into position on the heatshield.

(19) Installation of the fire seals as follows:

(a) Install the fire IPC -CSN (71-51-46-80-030) seal assembly (15) and IPC -CSN (71-51-46-80-020) seal assembly (16) on the fire shield with IPC -CSN (71-51-46-80-010) screws (17).

(b) TORQUE the screws (17) to between 6 and 8 lbf.in (0.07 and 0.09 m.daN).

(20) Using of sealant

WARNING: DO NOT GET THE SEALANT ON YOUR SKIN OR IN YOUR EYES. PUT ON PRO-TECTIVE CLOTHING, GLOVES, GOGGLES AND A FACE MASK. USE THE SEAL-ANT IN A WELL VENTILATED AREA. DO NOT BREATHE THE GAS. IF YOU GETTHE SEALANT ON YOUR SKIN OR IN YOUR EYES GET MEDICAL AID IMMEDI-ATELY.

(a) Fill all the voids in the fire seal with sealant (Material No. V08-030). Allow the sealant to cure for24 hours at 77 deg. F (25 deg.C) and 50 percent humidity.

Subtask 71-00-20-820-050-A

F. Do the Adjustment

(1) Adjust the thrust reverser latches, bumpers and compression struts (Ref. AMM TASK 78-30-00-820-010) .

(2) Adjust the fan cowls (Ref. AMM TASK 71-13-00-800-010) .

NOTE: Make sure that the gearbox breather outlet duct (GBOD) aligns with the gearbox breather out-let vent on the right fan cowl. If it does not align, loosen the GBOD fasteners, align the GBODwith the vent and torque the fasteners (Ref. AMM TASK 72-61-49-400-010) .





Subtask 71-00-20-410-051-A

G. Close access

(1) Check the HP bleed and pressure regulating valves configuration.

NOTE: Make sure that HP bleed and pressure regulating valves are not mechanically locked and canoperate freely.

(2) Close the thrust reverser cowls (Ref. AMM TASK 78-32-00-410-010) :



Subtask 71-00-20-440-050-A

H. Activate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-440-012) .(Ref. Fig. Hydraulic Control Unit SHEET 1)

Subtask 71-00-20-611-050-A

J. Do a Check of the Engine Oil System and Prime It

(1) Prime the engine oil system (Ref. AMM TASK 12-13-79-610-012) .

(2) Fill the Integrated Drive Generator (IDG) oil system (Ref. AMM TASK 12-13-24-612-011) .

Subtask 71-00-20-612-050-B

K. Service the Starter with Oil (Ref. AMM TASK 12-13-80-600-010) .

NOTE: The starter may have been drained when the engine was removed.

Subtask 71-00-20-410-053-A

L. Close Access

(1) Close the fan cowl (Ref. AMM TASK 71-13-00-410-010) :



(4) Remove the access platform(s).

(5) Remove the warning notice(s).

Subtask 71-00-20-865-072-A

WARNING: CLOSE THE PHC AND WHC CIRCUIT BREAKERS BEFORE YOU CLOSE THE PROBEHEATER AND WINDOW HEATER CIRCUIT-BREAKERS. IF YOU DO NOT OBEY THIS SE-QUENCE:- THE PROBES WILL BECOME TOO HOT.- THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PER-

SONNEL.

M. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION49VU ANTI ICE/PROBES/PHC/1 2DA1 D03





PANEL DESIGNATION FIN LOCATION122VU ANTI ICE/WHC/2 5DG2 W13122VU ANTI ICE/WHC/1 5DG1 X13122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12

Subtask 71-00-20-865-052-A

N. Remove the safety clips and tags and close these circuit breakers in this sequence:

PANEL DESIGNATION FIN LOCATION122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12122VU ANTI ICE/PROBES/2/TAT 1DA2 Y1549VU ANTI ICE/PROBES/PITOT/1 3DA1 D02122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z1649VU ANTI ICE/PROBES/AOA/1 4DA1 D04122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z1449VU ANTI ICE/RAIN/RPLNT/CAPT 1DB1 D01122VU ANTI ICE/RAIN/RPLNT/F/O 1DB2 W11123VU ANTI ICE/L/WHSLD 1DG1 AF10123VU ANTI ICE/R/WHSLD 1DG2 AF03122VU ANTI ICE/WINDOWS/L 4DG1 X14122VU ANTI ICE/WINDOWS/R 4DG2 W14121VU ENGINE/ENG1 AND 2 FIRE EX-

TIG/BTL1/SQUIB/A1WE1 Q43


2WE1 Q44


1WE2 Q41


2WE2 Q42

121VU RCDR/DFDR 7TU K16

** ON A/C 001-018, 025-025, 027-028, 053-104, 108-500, 513-65049VU COM/CVR/SPLY 2RK E1449VU COM/CVR/CTL 4RK E13

** ON A/C 651-70049VU COM/CVR/SPLY 23RK E1449VU COM/CVR/CTL 26RK E13

** ON A/C ALLFOR FIN 1000EM1 (ENGINE-1)49VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41121VU ENGINE/IGN/ENG1/SYS B 3JH1 P41121VU ENGINE/IGN/ENG1/SYS A BAT 2JH1 P39





PANEL DESIGNATION FIN LOCATION49VU ENGINE/1/FIRE DET/LOOP A 7WD1 A06121VU ENGINE/ENG1/FIRE DET/LOOP B 8WD1 Q38122VU ELEC/GCU/1 2XU1 T26122VU ANTI ICE/ENG/1 1DN1 X10FOR FIN 1000EM2 (ENGINE-2)49VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05121VU ENGINE/ENG2/FADEC B/AND EIU 2 4KS2 Q40121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P4049VU ENGINE/1 AND 2/IGN/SYS A 1JH A03121VU ENGINE/ENG2/FIRE DET/LOOP A 7WD2 Q3949VU ENGINE/2/FIRE DET/LOOP B 8WD2 A07122VU ELEC/GCU/2 2XU2 T27122VU ANTI ICE/ENG/2 1DN2 W10123VU Y HYD/ELEC/ELEC PUMP/NORM 3801GX AB03123VU Y HYD/ELEC/PUMP 3802GX AB06121VU HYDRAULIC/HYD POWER/Y 3803GX N30FOR FIN 1000EM1 (ENGINE-1)49VU ENGINE/1 AND 2/IGN/SYS A 1JH A03

Subtask 71-00-20-861-050-A

P. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 71-00-20-740-057-A

Q. Update the engine hours and cycles (Ref. AMM TASK 31-36-00-740-005) or (Ref. AMM TASK 31-36-00-740-014) .

NOTE: Some tasks will possibly not be applicable depending on whether a Data Management Unit (DMU)or a Flight Data Interface and Management Unit (FDIMU) is installed on the aircraft.

Subtask 71-00-20-860-050-A

R. Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001) .

Subtask 71-00-20-720-050-B

S. On the MCDU do the following Test:

(1) Push the line key adjacent to the ENG indication. The SYSTEM REPORT/TEST ENG menu comesinto view.

(2) Push the line key adjacent to the FADEC 1(2) A(B) indication. The ENGINE 1(2) MAIN MENU pagecomes into view.

(3) Push the line key adjacent to the TROUBLE SHOOTING indication. The FADEC 1(2) A(B) TROUBLESHOOTING MENU page comes into view.

(4) Push the line key adjacent to the EEC CONFIGURATION indication. The FADEC 1(2) EECCONFIGURATION page comes into view.

(5) Read the data that come on the MCDU (EEC P/N, ENGINE RATING, BUMP LEVEL, EPR MODIFIERand ENGINE SERIAL NUMBER) to make sure they are the same as written on the EEC, data entryplug and engine identification plate using the following engine ratings comparison table.

MCDU (EEC CONFIG Menu) ENGINE DATA PLATE (Engine Model)22000 lbs V252224000 lbs V2524





MCDU (EEC CONFIG Menu) ENGINE DATA PLATE (Engine Model)24000E lbs V2524E27000 lbs V252727000E lbs V2527E27000M lbs V2527M30000 lbs V253030000 lbs V253033000 lbs V2533

(6) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu pagecomes into view.

(7) Stop the MCDU.

Subtask 71-00-20-710-051-A

T. Do an operational test of the EEC (Ref. AMM TASK 73-22-34-710-040) .

NOTE: If the aircraft operates in correct CAT III conditions, do a land test (Ref. AMM TASK 22-97-00-710-001) .

Subtask 71-00-20-710-061-B

U. Do the operational test of the Starter valve and FMU (Ref. AMM TASK 80-13-51-710-040) .

Subtask 71-00-20-710-050-A

V. Do these Tests

(1) Do a functional test of the IDG disconnect system (Ref. AMM TASK 24-21-00-710-042) .

(2) Do an operational test of the anti-ice protection system of the engine air intake (Ref. AMM TASK 30-21-00-710-002) .

(3) Do the Hydraulic Maintenance Procedure after an engine installation:

(a) FOR 1000EM1 (ENGINE-1)· Do the maintenance procedure for Green Hydraulic System

(Ref. AMM TASK 29-11-51-860-040) .

(b) FOR 1000EM2 (ENGINE-2)· Do the maintenance procedure for Yellow Hydraulic System

(Ref. AMM TASK 29-13-51-860-001) .

Subtask 71-00-20-790-050-B

W. Do these Leak Checks

(1) Do a wet motor leak check (Ref. AMM TASK 71-00-00-710-046) .

(2) Do a leak check of the fuel return valve (Ref. AMM TASK 73-13-42-720-010) to make sure that thereare no leaks at pylon connection.

(3) Do a minimum idle leak check and do a check for leaks (Ref. AMM TASK 71-00-00-710-012) .

(4) Do an Electronic Engine Control (EEC) system idle test (Ref. AMM TASK 71-00-00-710-022) .

** ON A/C 108-200, 251-300

Subtask 71-00-20-210-053-A

X. Do a check of the IDG system as follows:

(1) On the lower ECAM DU, get the ELEC page.

(2) Make sure that the frequency and voltage indications are correct with engine running.





** ON A/C 001-018, 025-025, 027-028, 053-104, 201-250, 301-500, 513-700

Subtask 71-00-20-210-053-B

X. Make sure that the IDG is connected:

(1) If the IDG is not connected, make sure that the maintenance message "IDG1(2) (E1(2)-4000XU)RECONFIG" is shown on the EPGS GROUND REPORT page.

(a) Make sure that the related GCU is energized.

(b) Reset the GCU:

1 On the ELEC control panel 35VU, release (OFF) then push the related ELEC/GENpushbutton switch 3XU.

(c) On the ELEC page of the lower ECAM DU, make sure that the line connection between theIDG1(2) and the related busbar is shown green. Make sure that the frequency and voltageindications are correct.

(2) If the IDG1(2) is not connected after the GCU reset, do a check for other maintenance messagesrelated to the IDG.

** ON A/C ALL

Subtask 71-00-20-720-055-A

Y. Do this Test

(1) Do a pretested replacement engine test (Ref. AMM TASK 71-00-00-700-011) .

(2) Do not stop the engine at this step.

Subtask 71-00-20-710-052-A

AA. While the Engine is Running Do this Test

(1) On the lower ECAM DU, get the BLEED page.

(2) On the panel 30VU:Push the ENG 1 (2) BLEED pushbutton switch· on the ENG 1 (2) pushbutton switch, the OFF legend goes off.· on the lower ECAM DU, the PRV and HP valves are shown open.· Monitor the nacelle temperature for unsatisfactory indication. If the temperature increases

incorrectly, do the inspection of the bleed air duct connections.

(3) On the panel 30VU:Release the ENG 1(2) BLEED pushbutton switch· on the ENG 1(2) pushbutton switch the OFF legend comes on.· on the lower ECAM DU, the PRV and HP valves are shown closed.

Subtask 71-00-20-860-051-A

AB. Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .

Subtask 71-00-20-862-050-A

AC. De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 71-00-20-869-058-A

AD. Installation of the two engines.

(1) If the two engines were installed simultaneously refer to (Ref. AMM D/O 05-59-00-00) for specificrecommendations.

End of document

airbus a320 inst power plant

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