134466125 to 1c 130h 2 61fi 00 1 technical manual fault isolation propellers usaf series all c 130...
TRANSCRIPT
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TO 1C-
TECHNICAL MANUA
FAULT ISOLATION
ORGANIZATIONAL MAINTE
PROPELLERS
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TO 1C-130H-2-61FI-00-1INSERT LATEST CHANGED
LIST OF EFFECTIVE PAGESNOTE: The portion of the text affected by
outer margins of the page. Chapointing hands.
Dates of issue for original and changed pages are:
Original. . . . . . .. . . .. . . .. . . .. . . .0 . . . .. .1 Februar y 2002 Cha nge.. . . . .. . . .. . . .. . . .. . . .. .Cha nge. . .. . .. . .. . .. . .. . .. .. . ..1 . .. .15 F ebruary 2003 Cha nge. . .. . .. . .. . .. . .. . .. . .. . .Cha nge.. . . . .. . . .. . . .. . . .. . . .. .2 . . . .. . . 15 August 2003 Cha nge.. . . . .. . . .. . . .. . . .. . . .. .Cha nge. . .. . .. . .. . .. . .. . .. .. . ..3 . .. . .. . 1 J anua ry 2004 Cha nge. . .. . .. . .. . .. . .. . .. . .. . .
TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 694, CONSISTING OF
P a ge *Cha nge P a ge *Cha nge P a g
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INSERT LATES
LIST OF EFFECTIVE PAGES (CONT)
P a ge *Cha nge P a ge *Cha n
No. No. No. No.
4-175 Added....................... 14-176 Bla nk Added .. . .. . . .. . . 14-177 Added....................... 14-178 Bla nk Added .. . .. . . .. . . 14-179 Added....................... 1
4-180 Bla nk Added .. . .. . . .. . . 14-181 Added....................... 14-182 Bla nk Added .. . .. . . .. . . 14-183 Added....................... 14-184 Bla nk Added .. . .. . . .. . . 1
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TABLE OF CONTENTS
Section/Paragraph
LIS T OF TAB LE S ...........................................................
LIS T OF SC HE MATIC DI AG RAMS .............................
INTRODU CTION ............................................................
P urpose.........................................................................U sefulness ....................................................................Sa fety ............................................................................Arra ngement ................................................................Special I nst ructions for Open C ircuit B rea kers........S i l I t ti f Sh i ld d Wi
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LIST OF TABLES
Section Number Title
I I 2-1 P ropeller M alfunct ions ........................................ 66
I I 2-2 P r opeller S yst em Fa ult C odes ............................ 6
I I 2-3 P ropeller Fea ther S yst em Fa ult C odes .............. 6I I 2-4 Nega t ive Torq ue S igna l S yst em F ault Codes .... 6
I I 2-5 P ropeller Low Fluid Wa rning S yst em Fa ultCodes (Airpla nes P rior t o AF92-0547 andAF92-3021 Thr ough AF92-3024)...... .... .... .... ... 6
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LIST OF SCHEMATIC DIAGR
Number Title
2-6 Be t a I n di ca t i on E l ect r ica l Sch em a t i c D i a gr a m (Ai rand Airplanes AF92-3021 Through AF92-3024)
2-7 Be t a I nd ica t i on E lect r ica l Sch em a t i c D i a gr a m (Ai rThr ough AF92-2104 a nd Airpla nes AF92-3281 a
2-8 Neg a t iv e Tor q ue S i gn a l Sy st em E lect r ica l Sch em aP rior to AF92-0547 a nd Airpla nes AF92-3021 ThMC-130H Airplanes).............................................
2-9 Neg a t iv e Tor q ue S i gn a l Sy st em E lect r ica l Sch em aAF92 0547 Thr ough AF92 2104 a nd Airpla nes A
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INTRODUCTION
PURPOSE. This publica tion conta ins fa ult isola tion procedurtion of the C-130 propeller system.
USEFULNESS. The effectiveness of this publication shall, topart icipat ion in t he program by operat ions a nd ma intenan cetion Manua l. U ser feedback is the most important factor if tto-da te. U se the AFTO Form 22 system to recommend n ew ation in this publication.
SAFETY. Fault isolation procedures in this publication are abrief an d concise. Comply w ith War nings a nd Ca utions to prAlways turn off the external power selector switch (located oan y overhead panel. Refer to the ma intenan ce ma nua ls (J obprocedures - always bring the airplane to a safe condition bef
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TO 1C-130H-2-61FI-00-1
E S S E ssent ia l
FIM Fa ult isola t ion ma nua l
FLT E NG R Flight engineer
FRM Fa ult report ing ma nua l
FU S S TA (FS ) F usela ge st a t ion
G RD G round
G round fa ult Mea sura ble ground w hen t here should be
H ot fa ult Mea sura ble volt a ge w hen t here should be
LRU Line repla cea ble unit
MACAWS Mode a dvisory ca ut ion a nd w a rning syst em
NTS Nega t ive t orque signa l
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Section I. GENERAL INFORM
1-1. GENERAL. The C -130 propeller sy stem fau lt a na lysis composed of tw o elements: the Fa ult Report ing Ma nua l (FRM(FIM).
NOTE
Ground maintenance crews may also use FRM in Section XX of TO 1C-130H-2-00FR-00-1 or C130(M)H-2-00FR-00-1) to gain the same result
following para gra ph.1-2. FAULT REPORTING MANUAL (FRM). Flight crews usena nce personnel a bout ma lfunctions th e flight crews encountdures, the flight crew ma kes checks a nd observa tions to helptha t deal w ith symptoms and condit ions occurring a t th e t im
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c. Faul t C ode Indexes. The faul t code indexes l is t a l l appl icablenumerical order. Ea ch fau lt code represents a peculia r malfun ctionw hich could be encountered by th e flight crew. A figure an d block ncode tells where to go in the fault isola tion diagra m to sta rt t he actua ssigned fa ult code num bers betw een 6110001 a nd 6120999 represesynchrophaser system failures, and are subdivided as follows:
SYSTEM/FAILURE ASSIGNED FAULT
P ropeller syst em 6110001-6110008, 6
P ropeller fea ther system 6110010-6110017, 6
Nega t ive t orque signa l system 6110020-6110024, 6
P ropeller low fluid w a rning syst em 6110030-6110034, 6
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sequence in the same manner until every block in the figure blocks in the same figure with the same number).
(3) Fa ult Codes. Any number in the upper right corneblocks w ill not ha ve a fault code in them, an d a few w ill contnumbers are used to make sure troubleshooting starts at the code in dex.
(4) Test Points . A block may conta in a test point syming wh en an electrica l measurement is specified. A note idenw hich the test point is locat ed. The test points on a schematlocat ion of th e mea surement being ma de. Test point num bercorner of th e schemat ic diag ra m. Test points 2 a nd up th en a clockwise rota tion. A single test point reference for volta gevoltage is referenced to airplane ground.
(5) Circuit Int erruption Symbol. A lightning bolt withcircuit interruption symbol ( ). I ts presence means tha t a l
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1-4. SPECIAL TOOLS AND TEST EQUIPMENT REQUIRED FOR FA
AN typedesignation
Nomenclature or part No. Alternate
Synchropha ser system AD 33480-2 E quiva lent
test set
Mult imet er AN/P S M-37( ) E quiva lent
28 VDC light Loca l ma nufa cture E quiva lent
Shim (0.225 inch Loca l ma nufa cture E quiva lent
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Section II. PROPELLER ASS
2-1. GENERAL. The fault isolation material in this section propeller system ma lfunction excluding th e synchropha ser syinclude a m a lfunction in dex, fault code indexes, prepar a tion fault isolation, fault isolation diagrams (the actual troubleshotions for ha rdwa re referenced in the fault isolat ion diagra ms
2-2. MALFUNCTION INDEX. The ma lfunction in dex (ta ble 2encountered during ground ma intenan ce and n o numeric fauFRM dia gram , wh en no numeric fault code wa s provided by
crew only provided an a lphan umeric fault code. Ma lfunctionlisted in the left column of the ta ble. The middle column conwhile the right column identifies the preparation and fault is
Table 2 1 Propeller Malfuncti
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Table 2-2. Propeller System Fault Codes - Con
Fault code AFTO Form 781A report F
6110002 Be t a i nd ica t or li gh t No. (1)(2)(3)(4) f a il ed P e r for m f
to come on in (br ight )(d im)(both br ight go to f igu
and dim) modes when throttle was re-Airplanes
ta rded below FL IG HT ID LE /FLT ID LE3021 thro
gate.
block 74
block 13
block 80
Airplanes
and AF92
block 76
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Table 2-3. Propeller Feather System
Fault code AFTO Form 781A report
6110010 P r op el ler No. (1)(2)(3)(4) f a il s t o g o f rom P e
m a xi mu m r ev er se t o ful l f ea t h er i n 25 g o
seconds.
6110011 P r opeller fea t h er ov er ri de b ut t on lig ht / R
FTHR light No. (1)(2)(3)(4) fails to go off
at end of feather cycle.
6110012 P r opeller fea t her over ride but ton No. P e
(1)(2)(3)(4) f a il s t o pop ou t a t e nd of g o
feather cycle.
6110013 P ROP ELLE R FE ATH ER OVE RRID E N
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Table 2-4. Negative Torque Signal System Fault Code
Fault code AFTO Form 781A report F
6110021 E n g in e No. (1)(2)(3)(4) ex hi bi t s ex ces si ve P e r for m f
NTS indications in relation to other oper- go to figu
ating engines.
6110022 F EATH E R VAL VE AND NTS CH E CK P er for m f
l ight/NTS light No. (1)(2)(3)(4) fai led to go to figu
come on when air start was accom-
plished.
6110023 F EATH E R VAL VE AND NTS CH E CK P er for m f
l ight/NTS light No. (1)(2)(3)(4) fai led to go to figu
come on when engine condition lever was
moved t o FE ATH E R/FTR posit ion
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Table 2-6. Propeller Low Fluid Warning System Fault Codes (Airand AF92-3281 and Up)
Fault code AFTO Form 781A report
6110030 P ROP low oil w a rning light No. F
(1)(2)(3)(4) fails t o go to selected bright / 1C
dim mode. co
6110032 Wit h kn ow n low pr opeller flu id q ua n t it y , P e
P ROP low oil w arning light No. go
(1)(2)(3)(4) fa iled t o come on.
6110034 P ROP low oil w arn ing light No. P
(1)(2)(3)(4) ca me on. go
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2-5. FAULT ISOLATION DIAGRAMS. The fault isolation diatr oubleshooting a ny propeller malfun ction. When th e flight creport a ma lfunction, th a t num ber will be found in one of the
fault code is available, the malfunction index identifies the fi
a . Arrangement . One faul t isola t ion d iagram is includedsecond for th e propeller low fluid wa rnin g system. Opposite diagra m is a n il lustrat ion w hich shows th e physical locat ion fau lt isola tion diag ra m blocks. Double-check these illustra tiowh en making an observat ion or measurement . Following th eelectrical schema tic diag ra ms. The schema tic diag ra ms ar e ldiag ra m is covered up when folded out for use. Thus it is ea
nents, circuits, a nd t est points t ha t a re referenced on t he faub. Using Troubleshoot ing Data . A thorough descr ipt ion o
other troubleshooting data is provided in Section I. In a dditiillustra ted how-to-use figure for this section. U nderst a nd homa tion before at tempting to repair the a irplan e
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1 6110F01, 6110N01,2
6110P01 YES NIs BETA indicator light on bright-
Is airplane equipped with BETA ly?indicator lights (1)?
NOYES
3
YIs airplane serial number AF92-0547 through AF92-2104 orAF92-3281 and up?
NO
4
Momentarily place CAUTION
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TO 1C-130H-2-61FI-00-1
FROM SHT 1
9 6110017
CAUTIONIf PROPELLER FEATHER OVER-RIDE button does not pop out 4to 5 seconds after propeller blademovement stops, pull out manual-ly to prevent damage to auxiliarypump motor. NO
TO SHT 57a. Place FEATHER VALVE ANDNTS CHECK switch (3) toVALVE.
b. Move ENGINE CONDITIONlever (1) to FEATHER.Does PROPELLER FEATHEROVERRIDE button (2) pull in andremain in?
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FROM SHT 1
11 16
NO NOIs airplane prior to AF95-1001 or is Swap torquemeter indica-torquemeter BETA legend (2) pre- tors.sent on indicator? Does malfunction persist?
YES YES
12
a. Place the NORM/NVIS switch (8)
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TO 1C-130H-2-61FI-00-1
FROM SHT 7
28
Did FTHR light (3) go off when NOpropeller feather override button(5) popped out?
YES
29 NOTO SHT 75
Is BETA indicator light (2) off?
YES
30 6110024
a If troubleshooting fault code
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FROM SHT 7
34
Place FEATHER VALVE AND NTS CHECKNOswitch (5) to NTS. TO SHT 123
Is FEATHER VALVE AND NTS CHECKlight (4) on?
YES
35
Move ENGINE CONDITION lever (3) to NOGROUND STOP. TO SHT 125Is FEATHER VALVE AND NTS CHECKlight on?
YES
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TO 1C-130H-2-61FI-00-1
FROM SHT 9 OR 11
37
CAUTIONDo not move throttle and do not move engine condition lever toward FEATH-ER/FTR position while shim is installed. Damage to propeller assembly couldresult. NO
a. Gain access and insert a 0.225-inch thick shim between engine NTSplunger (1) and engine negative torque bracket/lever adjustment screw (2).b. 1 2 3 Place FEATHER VALVE AND NTS CHECK switch (5) to VALVE.c. Hold engine condition lever (7) in AIR START.Did propeller blades (8) move toward feather position?
YES
38
40
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FROM SHT 13
44
a. Connect synchrophaser systemtest set in accordance with Prepa-ration B.b. Start engine under test andsymmetrical engine in accordancewith TO 1C-130H-2-71JG-00-1,
NO71-00-10; or TO 1C-130(A)H-2-71JG-00-1, 71-00-10.c. Perform torquemeter calibrationin accordance with TO 1C-130H-2-77JG-00-1, 77-10-04; or TO 1C-
130(A)H-2-71JG-00-1, 71-00-10.Is torquemeter calibration satisfac-tory?
YES
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FROM SHT 17
61
a. Move throttles (3) to MAXIMUM
REVERSE/MAX RVS.b. Record indications on engine
YEStorque indicators (2) and RPM in-TO SHT 161
dications in test set FUNCTIONdisplay (1).Is there a symmetrical torque dif-ference in excess of 1000 inch-pounds?
NO
62
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FROM SHT 196
S65w
Did pitchlock disengage in accordance with
1NOTO 1C-130H-2-61JG-10-1, 61-10-02 (as indi- 0cated by torque and RPM reading same as
1initially recorded in the pitchlock check)?
reTYES
66
a. Perform synchrophaser index in accordance
with TO 1C-130H-2-61JG-10-1, 61-10-02 (sub-task 1-2-6). NOb. Move throttles (3) to GROUND IDLE/GND TO SHT 167IDLE.Do propeller low pitch stops retract as indicat-
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FROM SHT 1
7371
YES YESIs airplane serial number AF92-Are all BETA indicator lights
0547 through AF92-2104 or(1) on dimly? AF92-3281 and up?
NONO
74 6110002
Gain access to terminals of indi-cator lights dimmer No. 10 (2).
NOIs 28 VDC present between dim-
mer terminals W and X?1 2
YES
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FROM SHT 23
81YES
Is airplane AF92-0547 through TO SHT 27
AF92-2104 or AF92-3281 and up?
NO
82 6110002
YESPress to test affected BETA indi-TO SHT 31
cator light (1).Does light press to test?
NO
83
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O
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FROM SHT 25
96
Is 28 VDC present on specified
terminal of indicator lights dimmerNo. 10 (5)?
Dim TestProp Term Point
NO
1 j3
2 k5
3 m7
4 n9
YES
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TO 1C-130H-2-61FI-00-1
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63/693
TO 1C-130H-2-61FI-00-1
-
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64/693
TO 1C-130H-2-61FI-00-1
FROM SHT 31
111
a. Connect plug P390 (3) to valve housing assembly (4).
b. Gain access to and disconnect plug P398 (2) at engine fire-wall.
NOIs there continuity between pins H and V of receptacle J239 (1)?
28 29,
30 31,
32 33OR
35 36
YES
112YES
Is airplane serial number AF92-0547 through AF92-2104 or TO SHT 35AF92-3281 and up?
-
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65/693
TO 1C-130H-2-61FI-00-1
-
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66/693
TO 1C 130H 2 61FI 00 1
FROM SHT 33
118 YESTO SHT 37
Is airplane AF95-1001 and up?
NO
119
a. Remove power from airplane.b. Gain access to and disconnectplug P1725A (1) from systemscaution/advisory panel.Is a ground present on the speci-fied pin of plug P1725A?
NOPlug TestTO SHT 37
Prop Pin Point
-
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67/693
TO 1C-130H-2-61FI-00-1
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68/693
TO 1C 130H 2 61FI 00 1
FROM SHT 35
121
NOIs an outboard propeller beingtroubleshot?
YES
122
Gain access to and disconnectplug P130/P1139 (4) at outerwing break.Is a ground present on specifiedpin of receptacle J235/J935 (3)?
NO
-
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69/693
TO 1C-130H-2-61FI-00-1
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70/693
FROM SHT 33
126
NOIs an outboard propeller beingtroubleshot?
YES
127
Gain access to and disconnectplug P130 (4) at outer wing break.Is a ground present on specifiedpin of receptacle J235 (3)?
NO
-
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71/693
TO 1C-130H-2-61FI-00-1
-
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72/693
FROM SHT 1
131 6110002YES
Are any BETA indicator lights (1)
on dimly?
NO
132
Gain access to terminals of indi-cator lights dimmer No. 10 (2).
YESIs 28 VDC present between dim-mer terminals W and X?
1 2
NO
-
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73/693
TO 1C-130H-2-61FI-00-1
-
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74/693
FROM SHT 1 OR 5
136
Gain access to and inspect en- YES
gine NTS plunger (2).Is plunger actuated?
NO
137
a. Inspect NTS linkage for correctgap of 0.011 to 0.020 inch in ac-cordance with TO 1C-130H-2- YES
61JG-20-1, 61-20-22.b. Also inspect linkage for anybinding or damaged components.Are any discrepancies found?
-
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75/693
TO 1C-130H-2-61FI-00-1
-
7/28/2019 134466125 to 1C 130H 2 61FI 00 1 Technical Manual Fault Isolation Propellers USAF Series All C 130 Aircraft Change 7 01 Dec 2008
76/693
-
7/28/2019 134466125 to 1C 130H 2 61FI 00 1 Technical Manual Fault Isolation Propellers USAF Series All C 130 Aircraft Change 7 01 Dec 2008
77/693
TO 1C-130H-2-61FI-00-1
-
7/28/2019 134466125 to 1C 130H 2 61FI 00 1 Technical Manual Fault Isolation Propellers USAF Series All C 130 Aircraft Change 7 01 Dec 2008
78/693
FROM SHT 45
153
a. Remove power from airplane.b. Gain access to and disconnectplug P1725A (2) from systemscaution/advisory panel.Is a ground present on specifiedpin of plug P1725A?
NOPlug Test
Prop Pin Point
1 5378
2 5479
3 5580
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79/693
TO 1C-130H-2-61FI-00-1
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80/693
FROM SHT 45
160
a. Place FEATHER VALVE ANDNTS switch (3) to NORMAL.b. Gain access to terminals of
164YES NNTS check relay (2) and discon-nect wire from relay terminal A2. Is airplane an MC-130H?Is a ground present on discon-nected wire?
52,
22,
59OR
29
NO
YES
TO SHT 51
161
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81/693
TO 1C-130H-2-61FI-00-1
-
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82/693
FROM SHT 49
170
Gain access to and disconnectplug 47404A2P1 from indicatorlight dimmer No. 4 (1).Is a ground present on specifiedpins/receptacle points?
Pins Test Points
1069
2470
NO
23
71
2272
373
-
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83/693
TO 1C-130H-2-61FI-00-1
-
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84/693
FROM SHT 1
173
a. Open PROP SYNCHRO
PHASER and SYNCHRO YESPHASER circuit breakers (5,4).b. Gain access to and disconnectplug P390 (6) at valve housing
-
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85/693
TO 1C-130H-2-61FI-00-1
-
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86/693
FROM SHT 53
177
a. Place FEATHER VALVE AND NTSCHECK switch (3) to NORMAL.
b. Gain access to NTS check relay (2) YESand disconnect wire from relay terminal B2.Is a ground present on relay terminal B2?
51,
21,
58OR
28
NO
178
Disconnect wire number _K603A from relayterminal X1. YESIs a ground present on disconnected wire?
-
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87/693
TO 1C-130H-2-61FI-00-1
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88/693
FROM SHT 3 OR 5
186YES
Does propeller feather override TO SHT 63button (2) cycle?
NO
187 6110015
a. If troubleshooting fault code6110015, move engine conditionlever (4) to FEATHER/FTR. 188
NO Yb. Momentarily press propellerIs fault code 6110017 being
feather override button (2). troubleshot?1 3 4 Does light in button comeon while button is pressed?
2 Does FTHR light (5) come onNO
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89/693
TO 1C-130H-2-61FI-00-1
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90/693
FROM SHT 57
192
a. Move engine condition lever (3)to GROUND STOP/GND STOP.
b. Remove power from airplaneand gain access to terminals of NOpropeller feather override button TO SHT 61(2).Is a ground present on button ter-minal 7?
23
YES
193
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91/693
TO 1C-130H-2-61FI-00-1
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92/693
FROM SHT 59
198
NOIs an outboard propeller beingtroubleshot?
YES
199
Gain access to and disconnectplug P124/P1134 (1) at outerwing break. NOIs a ground present on pin V of
-
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93/693
TO 1C-130H-2-61FI-00-1
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94/693
FROM SHT 57
203 6110014
Gain access to and inspect propeller feather override button (3) for YEScorrect jamnut installation, and loose or damaged connections.
Are any discrepancies found?
NO
204
a. Move engine condition lever (4) to GROUND STOP/GND STOP.b. Open FEATHER PUMP MOTOR PHASE A,B,C/ 4 FEATHER PUMPMOTOR circuit breakers (1). NO
c. Gain access to terminals of feather relay (2) and disconnect wirefrom relay terminal X2.d. Move engine condition lever to FEATHER/FTR.Does propeller feather override button pull in and remain in?
-
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95/693
TO 1C-130H-2-61FI-00-1
-
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96/693
FROM SHT 57
215214
NO NPull fire emergency handle (1).Is fault code 6110016 being
Does propeller feather overridetroubleshot?
button (3) pull in?YESYES
216
a. Gain access to terminal boardTB146A (4).b. Move engine condition lever (5)to FEATHER/FTR.
Is 28 VDC present on specifiedterminal?
YTest
-
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97/693
TO 1C-130H-2-61FI-00-1
-
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98/693
FROM SHT 65
219
a. Remove electrical power fromairplane.
b. Gain access to terminals of en-gine condition lever feather con-trol switch (1).Is there continuity between switchterminals 1NO and 2NO?
NOTest
Prop Sw Points
1 S86E40 39
2 S86F40 39
3 S86G40 39
-
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99/693
TO 1C-130H-2-61FI-00-1
-
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100/693
FROM SHT 3 OR 5
227 6110013224
Momentarily hold MACAWSYES NIs airplane serial number AF92-LAMP TEST switch (3) in test po-
0547 through AF92-2104 orsition.
AF92-3281 and up? Does applicable light come on?
NOYES
225 6110013
Remove bulb from affected PRO-
-
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101/693
TO 1C-130H-2-61FI-00-1
-
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102/693
FROM SHT 69
233
a. Remove electrical power fromairplane.
b. Gain access to and disconnectplug P1725A (2) from systemscaution/advisory panel.Is a ground present on applicablepin of plug P1725A?
NOPlug Test
Prop Pin Point
1 4560
2 4662
3 4763
-
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103/693
TO 1C-130H-2-61FI-00-1
-
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104/693
FROM SHT 69
236
Gain access to and disconnect plug47405A1P1 from indicator light dimmer No.
5 (1).Is there continuity between specified pin ofplug 47405A1P1 and terminal G of the ap-plicable PROPELLER FEATHER OVER-RIDE button?
NOProp Pin Test Points
1 1151 27
2 1252 27
3 1353 27
4 2554 27
-
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105/693
TO 1C-130H-2-61FI-00-1
-
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106/693
FROM SHT 7 OR 9
241 6110008
NOTEPerform steps a and b only iftroubleshooting fault code6110008.
a. Move throttle (6) aboveFLIGHT IDLE/FLT IDLE gate.b. Hold engine condition lever (7) YES
in AIR START position until pro-peller blades (2) are above flightidle.
c. Open PROP SYNCHROPHASER and SYNCHROPHASER circuit breakers (5,4).d Gain access to and disconnect
-
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107/693
TO 1C-130H-2-61FI-00-1
-
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108/693
-
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109/693
TO 1C-130H-2-61FI-00-1
-
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110/693
FROM SHT 77
252NO
Is an outboard propeller being
troubleshot?
YES
253
Gain access to and disconnectplug P130/P1139 (4) at outerwing break.
Is a ground present on receptacleJ235/J935 (3) pin?
NO
-
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111/693
TO 1C-130H-2-61FI-00-1
-
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112/693
FROM SHT 77
257NO
Is an outboard propeller being
troubleshot?
YES
258
Gain access to and disconnectplug P130 (4) at outer wing break.
Is a ground present on specifiedplug pin?
NO
-
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113/693
TO 1C-130H-2-61FI-00-1
FROM SHT 7
-
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114/693
FROM SHT 7
262NO
Did propeller blades (1) move to- TO SHT 85ward feather position at all?
YES
263
a. Open FEATHER & AIR STARTcircuit breaker (2).b. 1 3 Open PROP LOW OILLEVEL circuit breaker (3).c. 2 Open MACAWS PILOT, CO-
PILOT and CONTROL circuitbreakers (4,5,6,7,8).
YESd. Gain access to and disconnectTO SHT 95
-
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115/693
TO 1C-130H-2-61FI-00-1
FROM SHT 83
-
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116/693
FROM SHT 83
267
1 3 4 Is FEATHER VALVE AND NONTS CHECK light (3) on?
2 Is NTS light (6) on?
YES
268
YESWith engine condition lever (5) inTO SHT 87
FEATHER/FTR position, is auxiliarypump motor (1) running?
NO
-
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117/693
TO 1C-130H-2-61FI-00-1
FROM SHT 13 OR 85
-
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118/693
FROM SHT 13 OR 85
274
a. If pulled, push in fire emergency han-dle (3).b. Move engine condition lever (2) toGROUND STOP/GND STOP.c. Gain access to and disconnect plug NOP410 (4) at auxiliary pump motor. TO SHT 91d. Move engine condition lever toFEATHER/FTR.Is 115 VAC present on plug pins A, B,and C?
15 16 17
YES
-
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119/693
TO 1C-130H-2-61FI-00-1
-
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120/693
-
7/28/2019 134466125 to 1C 130H 2 61FI 00 1 Technical Manual Fault Isolation Propellers USAF Series All C 130 Aircraft Change 7 01 Dec 2008
121/693
TO 1C-130H-2-61FI-00-1
FROM SHT 87 OR 89
-
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122/693
286
288Gain access to feather pump mo-tor relay (4). Is 115 VAC present on relay ter-Is 115 VAC present on relay ter- minals A2, B2 and C2, or T3, T2,
NO Nminals A1, B1, and C1, or L3, L2, and T1 (depending upon terminaland L1 (depending upon terminal labeling)?labeling)?
3 2 1
8 7 6
YESYES
290
Rep
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123/693
TO 1C-130H-2-61FI-00-1
294FROM SHT 91
-
7/28/2019 134466125 to 1C 130H 2 61FI 00 1 Technical Manual Fault Isolation Propellers USAF Series All C 130 Aircraft Change 7 01 Dec 2008
124/693
FROM SHT 91Repair open circuit between affecteterminal of feather pump motor rela292
NOIs an outboard propeller be-
Plug Pining troubleshot?
A
BC
YES
-
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125/693
TO 1C-130H-2-61FI-00-1
FROM SHT 83
-
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126/693
297
a. Connect plug P392 (3) to pro-peller control.b. Gain access to and disconnect
NOplug P396 (2) at engine firewall.Is a ground present on pin F ofreceptacle J241 (1)?
49
YES
298
Gain access to terminal boardTB107 (4) and disconnect speci-
-
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127/693
TO 1C-130H-2-61FI-00-1
FROM SHT 7
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128/693
302 6110012303.1
a. Move engine condition lever (6) to FEATH-Reseal
ER/FTR.cordanc
b. After propeller blades (1) have reached
61-10-1NOfeather position, check for internal leakage by accordaholding propeller feather override button (4) in
61-10-1while listening for a loud squeal from respec-
cordanctive propeller assembly.
61-10-1Is a loud squeal heard from propeller?
YES
302.1
a. Open affected FEATHER PUMP MOTORPHASE A,B,C/ 4 FEATHER PUMP MOTOR
-
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129/693
TO 1C-130H-2-61FI-00-1
-
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130/693
FROM SHT 97
306
a. Open PROP SYNCHRO PHASER and SYNCHRO PHASER cir-YES
cuit breakers (6,7).b. Gain access to and disconnect plug P390 (9) at valve housingassembly.Does propeller feather override button (5) pop out?
NO
-
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131/693
TO 1C-130H-2-61FI-00-1
FROM SHT 99
-
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132/693
314
Gain access to terminal boardTB107 (3) and disconnect speci-fied wire from terminal 1.
Is a ground present on discon-nected wire?
Test YESProp TB Wire No. Point TO SHT 103
1 TB107S 1K76C1848
2 TB107T 2K76B1848
3 TB107U 3K76B1848
4 TB107V 4K76C1848
-
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133/693
TO 1C-130H-2-61FI-00-1
-
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134/693
FROM SHT 101
318NO
Is an outboard propeller being
troubleshot?
YES
319
Gain access to and disconnect
plug P124/P1134 (3) at outerwing break. YESIs a ground present on plug pin
-
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135/693
TO 1C-130H-2-61FI-00-1
FROM SHT 7
-
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136/693
322.1YES
Is aircraft being troubleshot MACAWS equipped (AF92-0547 TO SHT 113thru AF92-2104 and AF92-3281 thru AF96-7325)?
NO
326
a. Open NTS CHECK circuit breaker (5).323 6110022, 6110023
b. Open FEATHER PUMP MOTOR PHASEa. If troubleshooting fault code A,B,C/2 FEATHER PUMP MOTOR circuit6110022 or 6110023, place breakers (6).FEATHER VALVE AND NTS c. Move ENGINE CONDITION lever (1) toYES
CHECK switch (4) to VALVE. FEATHER.b. Press to test affected d. Temporarily remove power from airplaneFEATHER VALVE AND NTS and gain access to terminals of FEATHER
-
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137/693
TO 1C-130H-2-61FI-00-1
FROM SHT 105
-
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138/693
330
Temporarily remove power fromairplane and gain access to termi-nals of ENG NO. 1 FEATHER
VALVE AND NTS CHECK light YES(1).Is 28 VDC present on light termi-nal 1?
6
NO
331
Temporarily remove power from
-
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139/693
TO 1C-130H-2-61FI-00-1
FROM SHT 9 OR 105
-
7/28/2019 134466125 to 1C 130H 2 61FI 00 1 Technical Manual Fault Isolation Propellers USAF Series All C 130 Aircraft Change 7 01 Dec 2008
140/693
337
a. Open PROP SYNCHRO PHASER andSYNCHRO PHASER circuit breakers (4,3).b. Gain access to and disconnect plug
340P390 (6) at valve housing assembly. NOIs there continuity between pins F and K of Is fault code 6110023 beingvalve housing assembly receptacle (5)? troubleshot?
41 43,
13 15,
66 68OR
38 40
YES
NO
TO SHT 119
-
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141/693
TO 1C-130H-2-61FI-00-1
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-
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TO 1C-130H-2-61FI-00-1
360
a. Remove electrical power from
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pairplane.b. Gain access to and disconnectFROM SHT 105 AND 111plug P1725A (2) from systemscaution/advisory panel.357
NO YIs a ground present on the appli-Is an outboard propeller beingcable plug pin?
troubleshot?
Prop Plug Pin Test Point
2 5479
3 5580
YES
NO
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TO 1C-130H-2-61FI-00-1
FROM SHT 113
364
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364
Momentarily hold the MACAWSLAMP TEST switch (1) in the test NOposition.
Does the applicable light comeon?
YES
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TO 1C-130H-2-61FI-00-1
FROM SHT 111
367
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367
Gain access to and disconnect plug47404A2P1 from indicator light dimmer No.4 (2).
Is a ground present on specified pins? 3
Light No. Plug Pin Test Point RNO
m1 1
764N
2 1675
3 1574
4 373
YES
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TO 1C-130H-2-61FI-00-1
FROM SHT 21 OR 109
372 6110021
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Gain access to and check NTS linkage for correct gap ofNO
0.011 to 0.020 inch in accordance with TO 1C-130H-2-61JG-20-1, 61-20-22.Is adjustment correct?
YES
373
a. Rotate propeller control (2) clockwise as viewed from therear and hold firmly against prop torque retainer assembly (6).b. Check clearance between torque retainer lug (3) and prop YEStorque retainer assembly for a maximum gap of 0.050 inch.
c. Release propeller control.d. Also inspect components for looseness or damage.
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TO 1C-130H-2-61FI-00-1
385FROM SHT 105
Repair 381
ENG NYES
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ENG NYESIs propeller No. 2 being troubleshot? CHECK
2 FEAT(2). (SNO
386382
Repair Press to test ENG NO. 2 FEATHER ENG NNOVALVE AND NTS CHECK light (2). CHECKDoes light press to test? 2 FEAT
(2). (SYES
387
Repair 383
ENG NYES
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TO 1C-130H-2-61FI-00-1
FROM SHT 11
390
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Gain access to terminals of NTScheck relay (1).
YESIs 28 VDC present on relay termi-nal A1?
54,
24,
61OR
31
NO
391
Is 28 VDC present on relay termi-YES
nal A2?
52,
22,
59OR
29
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TO 1C-130H-2-61FI-00-1
FROM SHT 11
395
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Gain access to terminals of NTS398check relay (1).
Is 28 VDC present between relay Is 28 VDC present on relay termi-YES Yterminals X2 and X1? nal A1?
49 50,
19 20, 54 ,
24,
61OR
31
56 57OR
26 27
NO
NO
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TO 1C-130H-2-61FI-00-1
FROM SHT 125
404
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Gain access to terminals ofFEATHER VALVE AND NTSCHECK switch (2). YESIs 28 VDC present on switch ter-
minal 3?
4
NO
405
Is 28 VDC present on FEATHER
VALVE AND NTS CHECK switch YESterminal 2?
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TO 1C-130H-2-61FI-00-1
FROM SHT 125
409
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NOTEPut meter negative lead on relay terminalB2.
a. Open FEATHER & AIR START circuit YESbreaker (4).b. Move ENGINE CONDITION lever (6) toFEATHER.Is a ground present on terminal B2 of NTScheck relay (1)?
51,
21,
58OR
28
NO
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TO 1C-130H-2-61FI-00-1
FROM SHT 9
415
T il f i l
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a. Temporarily remove power from airplane.b. Gain access to and disconnect plug P1725A(4) from systems caution/advisory panel.Is a 28 VDC present on applicable plug pin?
Plug TestProp Pin Point NO
1 5378
2 5479
3 5580
4 5681
YES
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TO 1C-130H-2-61FI-00-1
FROM SHT 131
422
a Temporarily remove power from airplane
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a. Temporarily remove power from airplane.b. Connect plug P1725A (4) to systems cau-tion/advisory panel.
NOc. Gain access to and disconnect plug P18/
P1835 (6) at outer wing break.Is 28 VDC present at pin N?
33OR
47
YES
423
a. Temporarily remove power from airplane.b. Connect plug P18/P1835.
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TO 1C-130H-2-61FI-00-1
FROM SHT 131 OR 133
428
Gain access to valve housing re-
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Gain access to valve housing re-ceptacle (4).Is there continuity between pins F
NOand K?
13 15,
38 40,
41 43, OR
66 68
YES
429
Gain access to and disconnectplug P398 (2) at engine firewall.
NO
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TO 1C-130H-2-61FI-00-1
FROM SHT 129
433
NOTE
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NOTEPut meter negative lead on recep-tacle pin E.
a. Connect plug P390 (3) to valvehousing assembly (4).
NOb. Gain access to and disconnectplug P398 (2) at engine firewall.Is there continuity between pins Eand F of receptacle J239 (1)?
45 44,
17 16,
64 63OR
36 35
YES
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TO 1C-130H-2-61FI-00-1
FROM SHT 125
440YES
Is No. 2 propeller being
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Is No. 2 propeller beingtroubleshot?
NO
441
Gain access to terminals of en-gine No. 2 NTS check relay (3).
NOIs 28 VDC present on relay termi-nal X2?
19
YES
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TO 1C-130H-2-61FI-00-1
FROM SHT 9 OR 11
449
Momentarily hold engine condition NO
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y g NOlever (3) in AIR START. TO SHT 143Does auxiliary pump motor (2) runwhile lever is held?
YES
450
4Inspect NTS linkage (1) for servicea-bility and check for correct gap of A
NO0.011 to 0.020 inch in accordance wwith TO 1C-130H-2-61JG-20-1, 61- 2
20-22. qIs NTS linkage satisfactory?
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TO 1C-130H-2-61FI-00-1
FROM SHT 141
455
a. Gain access to terminals of
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feather relay (2).b. Momentarily hold ENGINECONDITION lever (1) in AIR YES
START.Is 28 VDC present on relay termi-nal B2 while lever is held?
32
NO
456
a. Gain access to pedestal termi-
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TO 1C-130H-2-61FI-00-1
FROM SHT 143
459
Open FEATHER & AIR START circuit breaker(4)
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(4).Is there continuity between terminal 1C of EN-GINE CONDITION lever air start switch (1)
and specified terminal?
TestNO
Prop Sw TB-Term Points
1 S23S TB146A (3) -19337 38
2 S23T TB146A (3) -19437 38
3 S23U TB146A (3) -19537 38
4 S23V TB146A (3) -19637 38
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TO 1C-130H-2-61FI-00-1
FROM SHT 13
464
Check NTS linkage (1) for correctgap of 0 011 to 0 020 inch in ac NO
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gap of 0.011 to 0.020 inch in ac- NOcordance with TO 1C-130H-2-61JG-20-1, 61-20-22.
Is adjustment correct?
YES
465
Inspect NTS linkage through valveYES
housing assembly cover (2) forevidence of binding.Is any binding observed?
NO
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TO 1C-130H-2-61FI-00-1
FROM SHT 13
469YES
Did propeller feather override but- TO SHT 153ton (3) pull in?
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ton (3) pull in?
NO
470
Temporarily remove power fromairplane and gain access to termi-nals of propeller feather override
YESbutton.Is 28 VDC present on button ter-minal 1?
26
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TO 1C-130H-2-61FI-00-1
477FROM SHT 149
Rep474
nal HTemporarily remove power from airplane boarand gain access to terminals of fire emer- 12 )
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and gain access to terminals of fire emer 12.)YES
gency handle switch (3).Is 28 VDC present on switch terminal H1? Prop
143 234NO
475
478Is 28 VDC present on switch terminal G1? YES
Rep42
NO
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TO 1C-130H-2-61FI-00-1
FROM SHT 149
481
-
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Gain access to and disconnectplug P391 (3) at feather solenoid YES
valve.Is 28 VDC present between plugpins A and B?
19 18
NO
484
a. Open EMER FEATHER circuit
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TO 1C-130H-2-61FI-00-1
FROM SHT 153
489NO
Is airplane being troubleshot a C-130B model through AF59-5957?
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g
YES
490
Gain access to terminal boardTB115L (2).Is 28 VDC present on specified ter-minal?
Test
YESProp TB-Term Point
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TO 1C-130H-2-61FI-00-1
-
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-
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TO 1C-130H-2-61FI-00-1
-
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-
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TO 1C-130H-2-61FI-00-1
FROM SHT 19
511 6110006
a. Shut down engines (1) in ac-cordance with TO 1C-130H-2-71JG 00 1 71 00 10 or TO 1C
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71JG-00-1, 71-00-10; or TO 1C-NO
130(A)H-2-71JG-00-1, 71-00-10.b. Check throttle control systemrigging in accordance with TO 1C-130H-2-76JG-00-1, 76-10-01.Is rigging correct?
YES
512
Check engine coordinator-to-pro-
peller control assembly rigging in NO
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 19
520
Did RPM increase to 103.5 per- YEScent or above and hold when fuel TO SHT 165governing switch (1) was held in
-
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governing switch (1) was held inCHECK during pitchlock check?
NO
523
521 Perform propeller synchrophasercheck in accordance with TO 1C-NO NDid RPM increase at all when fuel130H-2-61JG-10-1, 61-10-02governing switch was held in(subtask 1-2-9).CHECK during pitchlock check?Is synchrophaser check satisfac-
tory?YES
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 163
529
Remove dome assembly in accor-dance with TO 1C-130H-2-61JG-
NO10-1 61-10-11
-
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10 1, 61 10 11.Is pin on ratchet ring (1) alignedwith etch mark on lip of No. 2
blade barrel bore (2)?
YES
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 21
532 6110003
a. Shut down engines in accor-dance with TO 1C-130H-2-71JG-00-1, 71-00-10; TO 1C-130(A)H-
-
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00 1, 71 00 10; TO 1C 130(A)H2-71JG-00-1, 71-00-10; or TO 1C-130(M)H-2-71JG-00-1, 71-00-10.
b. Move engine condition lever (2)to FEATHER/FTR.
NOc. After propeller blades (1) havereached feather position, checkfor internal leakage by holdingpropeller feather override button(3) in while listening for a loudsqueal from respective propellerassembly.Is a loud squeal heard from pro-peller?
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 21
537 6110001
Perform inspection for loose propellerYES
blades in accordance with TO 1C-130H-2-61JG-10-1, 61-10-22.
-
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,Are any loose blades found?
NO
538
Perform inspection of propeller bladeNO
tracking in accordance with TO 1C-130H-2-61JG-10-1, 61-10-23.Is tracking satisfactory?
YES
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TO 1C-130H-2-61FI-00-1
FROM SHT 169
549
Inspect engine condition controlsystem for loose, worn, or brokencomponents in accordance with YES
-
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TO 1C-130H-2-76JG-00-1, 76-10-03, 76-10-11, and 76-10-12; or
TO 2J-T56-56, as required.Are any discrepancies found?
NO
550
Inspect throttle control system forloose, worn, or broken compo-
nents in accordance with TO 1C YES
-
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TO 1C-130H-2-61FI-00-1
-
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-
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TO 1C-130H-2-61FI-00-1
FROM SHT 1
10
-
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Check affected propeller assem-blies for correct fluid level in ac-
NOcordance with TO 1C-130H-2-12JG-10-2, 12-16-03.Is fluid level in one propeller as-sembly low?
YES
-
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TO 1C-130H-2-61FI-00-1
-
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-
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TO 1C-130H-2-61FI-00-1
FROM SHT 1
22 6110032
Momentarily hold the MACAWSLAMP TEST switch (4) in the test NOposition.Does the applicable PROP light
-
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Does the applicable PROP light(1) come on?
YES
23
Gain access to related diode CR3(2).Is voltage present on terminal ( )of diode CR3?
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 7
27
Is voltage present on cathode of diode CR3 (2)?
Test
-
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TestProp Diode Point
29YES
1 CR3GB74
Replace
2 CR3GC75
3 CR3GD76
4 CR3GE77
NO
-
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TO 1C-130H-2-61FI-00-1
-
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-
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TO 1C-130H-2-61FI-00-1
FROM SHT 11
40
Inspect wiring to propeller controlYES
receptacle (2) (for plug P392) forloose and broken connections.Is any damage found?
-
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NO
41
Gain access to oil level indicatorswitch (1) and disconnect wiresfrom switch.Is a ground present on discon- YESnected wires?
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 11
45
Gain access to and disconnect applicable wirefrom diode CR3 (2).Is a ground present on disconnected wire?
-
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Wire Test 47YESProp Diode 1 Diode 2 No. PointIs an outboard propellerbeing troubleshot?
1 CR3AX CR3FX 1E600D14
2 CR3AY CR3FY 2E600C16
3 CR3AZ CR3FZ 3E600C18
4 CR3BA CR3GA 4E600D20
YES
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 15
52 YESTO SHT 21
Is airplane an MC-130H?
NO
-
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53
Remove diode CR3 (2) associat-ed with propeller position.Is a ground present on diode bus 54bar?
Gain access to terminals of in-dicator lights dimmer No. 7 (3)
Testand disconnect wire from dim-YES YESProp Diode Pointmer terminal e.Is a ground present on discon-
1 CR3AX13
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 15
58
Remove diode CR3 (3) associat-ed with propeller position.Is a ground present on diode busbar?
-
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TestProp Diode Point YES
1 CR3FX13
2 CR3FY15
3 CR3FZ17
4 CR3GA19
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 17
63
Remove diode CR3 (1) associated with propel-ler position.Is a ground present on diode bus bar?
Prop Diode Test Point
-
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Prop Diode Test PointNO
TO SHT 231 CR3AX 13
2 CR3AY15
3 CR3AZ17
4 CR3BA19
YES
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 21
6870Is ground present on specified pin of plug
47407A1P1 and 40407A2P1 of indicator Replight dimmer No. 7 (2)? of P
lightProp Pin Test Point 4740
-
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Prop Pin Test Point 4740lightYES
1 47407A1P1-10 102
Prop2 47407A1P1-24
10112
3 47407A1P1-2399
34
4 47407A2P1-1083
NO
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 21
7573
RepGain access to terminals of PROP
masLOW OIL QUANTITY master warning
fied light (3) and disconnect wire from
PELNOlight terminal 2.
that Is a ground present on disconnected
-
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s a g ou d p ese t o d sco ectedwire?
Prop1492
YES
76
Rep74
pin CGain access to and disconnect plugs mas
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 17
78
Gain access to terminals of indi-cator lights dimmer No. 7 (3) anddisconnect wire from specifieddimmer terminal.Is a ground present on discon-
-
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g pnected wire?
Dim TestYES
Prop Term Point
1 A7
2 B5
3 C3
1
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 17
83
Gain access to terminals of PROPLOW OIL QUANTITY masterwarning light (2) and disconnect
NOwire from light terminal 2.Is a ground present on discon-
-
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nected wire?
49
YES
84
Gain access to and disconnect
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 5
88
With engine(s) running, hold en-gine condition lever (2) to AIR YESSTART for 15 seconds.Does PROPELLER LOW OILWARNING/PROP light (1) go off?
-
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WARNING/PROP light (1) go off?
NO
89
a. Shut down engine(s) in accor-dance with TO 1C-130H-2-71JG-00-1, 71-00-10; TO 1C-130(A)H-2-71JG-00-1, 71-00-10; or TO 1C-
NO
-
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TO 1C-130H-2-61FI-00-1
-
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-
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TO 1C-130H-2-61FI-00-1
FROM SHT 33
102
Gain access to and disconnect plug47407A2P1 from indicator light dimmer No.7 (2). NOIs a ground present on pin 16 of plug TO SHT 3747407A2P1?
-
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86
YES
103 105
Is airplane equipped with a flight data re- RepNO
corder system? (Check for presence of plug
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 35
108
Is a ground present on pin 24 of plug47404A2P1 of indicator light dimmer No. 7 110NO(4)?
Rep
82
-
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YES
109
Gain access to and disconnect plug P251 111(2) at main instrument panel disconnect.
RepIs a ground present on pin C of receptacle NO
plugJ129 (1)?
No
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 33
113
Disconnect wire from terminal Eof indicator lights dimmer No. 7(3). NOIs a ground present on discon-nected wire?
-
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9
YES
114
Gain access to and disconnectplug P251 (1) at main instrumentpanel disconnect. NO
-
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243/693
TO 1C-130H-2-61FI-00-1
-
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-
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TO 1C-130H-2-61FI-00-1
FROM SHT 41
128NO
Is an outboard propeller beingtroubleshot?
YES
-
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129
Gain access to and disconnectNO
plug P130/P1139 (4) at outer
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 1
133
Press to test affected PROPEL- 137YES NLER LOW OIL WARNING light (1
Is airplane an MC-130H?or 2).Does light press to test?
NO
YES
-
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TO SHT 47
134
Temporarily remove power andgain access to terminals of affect-ed PROPELLER LOW OIL
YESWARNING light.
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 45
141
a. Open PROP LOW OIL LEVEL circuitbreaker (2).b. Gain access to and disconnect plugs
14347407A1P1 and 47407A2P1 from indicatorlight dimmer No. 7 (4). RepIs ground present on specified pin of plug pin o
-
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47407A1P1 and 40407A2P1 of indicator of inlight dimmer No. 7? ed d
NO
Prop Pin Test Point Prop1
1 47407A1P1-491
23
2 47407A1P1-1693
4
3 47407A1P1-1595
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 45
146
a. Open PROP LOW OIL LEVELcircuit breaker (2).b. Gain access to terminals of in-dicator lights dimmer No. 7 (4).Is a ground present on specifieddimmer terminal?
-
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Dim TestNO
Prop Term Point
1 a8
2 b6
3 c4
4 d2
-
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253/693
TO 1C-130H-2-61FI-00-1
FROM SHT 451
151R
Is No. 2 PROPELLER LOW OIL 1YESWARNING light (2) being Wtroubleshot? N
INNO
-
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1152
RPress to test No. 2 PROPELLER 1NOLOW OIL WARNING light. WDoes light press to test? N
INYES
1
-
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TO 1C-130H-2-61FI-00-1
FROM SHT 1163
Temporarily remove power and ga160 6110031cess to terminals of PROP LOW ONOPress to test PROP LOW OIL QUANTI-QUANTITY master warning light.
TY master warning light (2).Is 28 VDC present on light termin
Does light press to test?
48YES
NO
-
7/28/2019 134466125 to 1C 130H 2 61FI 00