134466125-to-1c-130h-2-61fi-00-1-technical-manual-fault-isolation-propellers-usaf-series-all-c-130-aircraft-change-7-01-dec-2008.pdf...

TO 1C-130H-2-61FI-00-1TECHNICAL MANUAL

FAULT ISOLATIONORGANIZATIONAL MAINTENANCE

PROPELLERS

USAF SERIESALL C-130 AIRCRAFT

ATOS/DLDSS

DISCLOSURE NOTICE - This information is furnished upon the condition that it will not be released toanother nation without the specific authority of the Department of the Air Force of the United States, that itwill be used for military purposes only, that individual or corporate rights originating in the information,whether patented or not, will be respected, that the recipient will report promptly to the United States, anyknown or suspected compromise, and that the information will be provided substantially the same degreeof security afforded it by the Department of Defense of the United States. Also, regardless of any othermarkings on the document, it will not be downgraded or declassified without written approval of theoriginating United States agency.

DISTRIBUTION STATEMENT D - Distribution authorized to the Department of Defense and US DoDcontractors only (Administrative or Operational Use) (1 February 2002). Other requests for this documentshall be referred to 580 ACSG/GFEAH, Robins AFB, GA 31098.

WARNING - This document contains technical data whose export is restricted by the Arms ExportControl Act (Title 22, U.S.C., Sec 2751, et seq.) or the Export Administration Act of 1979, as amended, Title50, U.S.C., App. 2401 et seq. Violations of these export laws are subject to severe criminal penalties.Disseminate in accordance with provisions of DoD Directive 5230.25.

HANDLING AND DESTRUCTION NOTICE - Comply with distribution statement and destroy by anymethod that will prevent disclosure of the contents or reconstruction of the document.

Published under authority of the Secretary of the Air Force

1 FEBRUARY 2002CHANGE 7 - 1 DECEMBER 2008

BASIC AND ALL CHANGES HAVE BEEN MERGED TO MAKE THIS A COMPLETE PUBLICATION

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LIST OF EFFECTIVE PAGESNOTE: The portion of the text affected by the changes is indicated by a vertical line in the

outer margins of the page. Changes to illustrations are indicated by miniaturepointing hands.

Dates of issue for original and changed pages are:

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TABLE OF CONTENTS

Section/Paragraph Page

LIST OF TABLES............................................................................................................................ ii

LIST OF SCHEMATIC DIAGRAMS ............................................................................................. iii

INTRODUCTION..............................................................................................................................vPurpose ...........................................................................................................................................vUsefulness ......................................................................................................................................vSafety..............................................................................................................................................vArrangement ..................................................................................................................................vSpecial Instructions for Open Circuit Breakers..........................................................................vSpecial Instruction for Shielded Wires ........................................................................................vConditions Not Covered By This Manual....................................................................................vAbbreviations and Symbols ..........................................................................................................vEffectivity ..................................................................................................................................... viUsing This Publication................................................................................................................ vi

I GENERAL INFORMATION......................................................................................................... 1-11-1 General ..................................................................................................................... 1-11-2 Fault Reporting Manual (FRM) ............................................................................. 1-11-3 Fault Isolation Manual (FIM) ................................................................................ 1-11-4 Special Tools and Test Equipment Required for Fault Isolation ........................ 1-4

II PROPELLER ASSEMBLY ........................................................................................................... 2-12-1 General ..................................................................................................................... 2-12-2 Malfunction Index.................................................................................................... 2-12-3 Numeric Fault Code Indexes .................................................................................. 2-12-4 Preparation Procedures........................................................................................... 2-52-5 Fault Isolation Diagrams ...................................................................................... 2-15

III SYNCHROPHASER SYSTEM ..................................................................................................... 3-13-1 General ..................................................................................................................... 3-13-2 Malfunction Index.................................................................................................... 3-13-3 Numeric Fault Code Index ..................................................................................... 3-13-4 Preparation Procedures........................................................................................... 3-23-5 Fault Isolation Diagram........................................................................................ 3-13

IV SYNCHROPHASER SYSTEM (AIRPLANES MODIFIED BY TO 1C-130-1731).................... 4-14-1 General ..................................................................................................................... 4-14-2 Malfunction Index.................................................................................................... 4-14-3 Numeric Fault Code Index ..................................................................................... 4-14-4 Preparation Procedures........................................................................................... 4-34-5 Fault Isolation Diagram........................................................................................ 4-16

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LIST OF TABLES

Section Number Title Fault Codes Page

II 2-1 Propeller Malfunctions ........................................ 6110F01, 6110N01,6110P01, 6110W01 ..............2-1

II 2-2 Propeller System Fault Codes ............................ 6110001 - 6110008...............2-1

II 2-3 Propeller Feather System Fault Codes.............. 6110010 - 6110017...............2-3

II 2-4 Negative Torque Signal System Fault Codes.... 6110020 - 6110024...............2-3

II 2-5 Propeller Low Fluid Warning System FaultCodes (Airplanes Prior to AF92-0547 andAF92-3021 Through AF92-3024)..................... 6110030 - 6110034...............2-4

II 2-6 Propeller Low Fluid Warning System FaultCodes (Airplanes AF92-0547 ThroughAF92-2104 and AF92-3281 and Up) ............... 6110030 - 6110034...............2-5

III 3-1 Synchrophaser System Malfunctions ................. 6120S01 ................................3-1

III 3-2 Synchrophaser System Fault Codes................... 6120001 - 6120014...............3-1

IV 4-1 Synchrophaser System Malfunctions (Air-planes Modified by TO 1C-130-1731) ............. 6120S01 ................................4-1

IV 4-2 Synchrophaser System Fault Codes (Air-planes Modified by TO 1C-130-1731) ............. 6120001 - 6120014...............4-1

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LIST OF SCHEMATIC DIAGRAMS

Number Title Page

2-6 Beta Indication Electrical Schematic Diagram (Airplanes Prior to AF92-0547and Airplanes AF92-3021 Through AF92-3024) ............................................................2-251

2-7 Beta Indication Electrical Schematic Diagram (Airplanes AF92-0547Through AF92-2104 and Airplanes AF92-3281 and Up) ..............................................2-253

2-8 Negative Torque Signal System Electrical Schematic Diagram (AirplanesPrior to AF92-0547 and Airplanes AF92-3021 Through AF92-3024, ExceptMC-130H Airplanes).........................................................................................................2-255

2-9 Negative Torque Signal System Electrical Schematic Diagram (AirplanesAF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)...........................2-257

2-10 Negative Torque Signal System Electrical Schematic Diagram (MC-130HAirplanes) ..........................................................................................................................2-259

2-11 Propeller Feather System Electrical Schematic Diagram (Airplanes Prior toAF92-0547 and Airplanes AF92-3021 Through AF92-3024).........................................2-261

2-12 Propeller Feather System Electrical Schematic Diagram (AirplanesAF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)...........................2-277

2-13 Propeller Low Fluid Warning System Electrical Schematic Diagram (Air-planes Prior to AF92-0547 and Airplanes AF92-3021 Through AF92-3024) ..............2-285

2-14 Propeller Low Fluid Warning System Electrical Schematic Diagram (Air-planes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)...............2-289

2-15 In-line Disconnects Location Diagram (Airplanes AF92-1094, AF92-1095,AF92-2104, and AF93-1036 and Up) ..............................................................................2-291

3-6 Synchrophaser System Electrical Schematic Diagram (Airplanes Prior toAF92-0547 and Airplanes AF92-3021 Through AF92-3024).........................................3-167

3-7 Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547,Through AF92-2104, and Airplanes AF92-3281 and Up) .............................................3-177

3-8 Synchrophaser Adapter Unit Electrical Schematic Diagram .......................................... 3-187

3-9 Synchrophaser System Simplified Electrical Schematic Diagram .................................. 3-191


4-6 Synchrophaser System Electrical Schematic Diagram (Airplanes Prior toAF92-0547 and Airplanes AF92-3021 Through AF92-3024).........................................4-169

4-7 Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547Through AF92-2104, and Airplanes AF92-3281 and Up) .............................................4-177

4-8 Synchrophaser System Simplified Electrical Schematic Diagram .................................. 4-187

4-9 In-line Disconnects Location Diagram (Airplanes Prior to AF92-1094 andAF92-3021 Through AF92-3024) .....................................................................................4-189


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INTRODUCTION

PURPOSE. This publication contains fault isolation procedures for subsystems/modes of opera-tion of the C-130 propeller system.

USEFULNESS. The effectiveness of this publication shall, to a large extent, depend upon activeparticipation in the program by operations and maintenance personnel who use the Fault Isola-tion Manual. User feedback is the most important factor if the manual is to be maintained up-to-date. Use the AFTO Form 22 system to recommend new and/or improved data for incorpora-tion in this publication.

SAFETY. Fault isolation procedures in this publication are a guide for troubleshooting and arebrief and concise. Comply with Warnings and Cautions to prevent accidental injury or damage.Always turn off the external power selector switch (located on the overhead panel) while openingany overhead panel. Refer to the maintenance manuals (Job Guides) for repair and replacementprocedures - always bring the airplane to a safe condition before repair or replacement.

ARRANGEMENT. This publication contains Section I - General Information, Section II - Propel-ler Assembly, Section III - Synchrophaser System and Section IV - Syncrophaser System (Air-planes modified by TO 1C-130-1731). Refer to the Table of Contents when a specific paragraphneeds to be located. Placarding differences between airplane models are separated in the text bya slash.

SPECIAL INSTRUCTIONS FOR OPEN CIRCUIT BREAKERS. When a tripped circuit breaker isencountered, use TO 1C-130(A)H-2-13, TO 1C-130(A)U-2-13, TO 1C-130H-2-13, TO 1C-130H-2-14, TO 1C-130B-2-13, TO 1C-130(M)E-2-13, or TO 1C-130(M)H-2-13 to identify circuits whichare on the load side of the circuit breaker. Isolate these circuits by removing electrical plugs,switching circuit functions (by changing switch positions), or removing power from the applicablecircuit by opening other circuit breakers. Close the tripped circuit breaker. If the circuitbreaker trips again, either the airplane wiring is shorted or the circuit breaker is bad; isolateand repair as required. If the circuit breaker remains closed, observe it and bring back on lineindividual circuits one at a time; when the circuit breaker now trips, the component beingbrought on line is bad or there may be a bent pin in its plug or connector. Repair the plug orconnector or replace the component as required. Perform an operational checkout of the systemfollowing the repair action.

SPECIAL INSTRUCTION FOR SHIELDED WIRES. If a synchrophaser malfunction is encounteredwhere it is suspected that the operation of on-airplane equipment (such as UHF or VHF radio)is the cause, it is possible that a defective wiring shield is allowing a false signal to be receivedby the synchrophaser. First, verify that the suspected equipment is functioning properly and itsassociated wiring is routed properly and intact. If the fault persists, refer to figure 3-6 or 3-7/4-6 or 4-7 and determine that the wire shields for the synchrophaser wiring are intact.

CONDITIONS NOT COVERED BY THIS MANUAL. The instructions in this manual representplanned action for conditions normally encountered during maintenance. It is almost impossibleto account for maintenance difficulties that may be only occasionally encountered. Therefore,the use of local decisions for general repair practices, not involving safety of flight, is encouragedto avoid unnecessary delay when coverage in the manual is incomplete. Any variation fromprocedures shall be consistent with standard shop practices and shall not detract from overallefficiency and operation of the equipment.

ABBREVIATIONS AND SYMBOLS. The following non-military-standard abbreviations, termsand symbols appear in this publication:

Continuity Absence of an open circuit

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ESS Essential

FIM Fault isolation manual

FLT ENGR Flight engineer

FRM Fault reporting manual

FUS STA (FS) Fuselage station

GRD Ground

Ground fault Measurable ground when there should be some resistance

Hot fault Measurable voltage when there should be none

LRU Line replaceable unit

MACAWS Mode advisory caution and warning system

NTS Negative torque signal

SHT Sheet

x Underline means lower-case pin letter

Test point designation

Temporary circuit interruption symbol (See para 1-3f(5))

In-line disconnect view identifier

EFFECTIVITY. Time Compliance Technical Order (TCTO) information which affects fault isola-tion procedures is added to this publication at the same time the maintenance (Job Guide)manuals are revised. This is done in the form of a record of applicable time compliance techni-cal orders. Only current TCTO are listed. A TCTO is deleted from the list when any of thefollowing occurs:

a. The equipment configuration to which the TCTO is applicable is no longer covered in themanual.

b. The TCTO is rescinded.

c. The TCTO is superseded or replaced.

TCTO No. Title TCTO Date

1C-130-1731 Synchrophaser Interface WiringReplacement

USING THIS PUBLICATION. Figure i-1 explains how to use this publication whether a fault codeis provided or not. Do not skip the preparation procedure. The preparation is necessary toprepare the airplane for fault isolation.

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Figure i-1. How to Use This Manual (Sheet 1 of 2)

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Figure i-1. How to Use This Manual (Sheet 2)

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Section I. GENERAL INFORMATION

1-1. GENERAL. The C-130 propeller system fault analysis concept is a troubleshooting methodcomposed of two elements: the Fault Reporting Manual (FRM) and the Fault Isolation Manual(FIM).

NOTE

Ground maintenance crews may also use FRM procedures (containedin Section XX of TO 1C-130H-2-00FR-00-1 or Chapter 20 of TO 1C-130(M)H-2-00FR-00-1) to gain the same results as described in thefollowing paragraph.

1-2. FAULT REPORTING MANUAL (FRM). Flight crews use FRM methods to inform mainte-nance personnel about malfunctions the flight crews encounter. As directed by the FRM proce-dures, the flight crew makes checks and observations to help isolate the malfunction. Questionsthat deal with symptoms and conditions occurring at the time of the failure are answered. Theresult is a peculiar fault code which represents those specific symptoms and conditions accompa-nying the malfunction. In order that each fault code may be identified and continuity madepossible between the fault reporting manual (FRM) and the fault isolation manual (FIM), aseven-digit numeric code is assigned to each fault. The first two digits identify the system inwhich the fault occurred; the next two digits represent the subsystem in which that faultoccurred; the remaining three digits are the numerical identification assigned to each fault.System and subsystem identification are assigned in accordance with Specification MIL-M-83495. This number and the discrepancy (symptoms) are then entered in the AFTO Form 781Aalong with any additional details that will be helpful. Using the Fault Isolation Manual, main-tenance personnel interpret the fault code and plan maintenance action that allows them tostart the fault isolation routine at some block other than block 1. The blocks which are skippedover would normally be used to determine the symptoms and conditions represented by the faultcode. Troubleshooting becomes more accurate, and less time and effort is required.

1-3. FAULT ISOLATION MANUAL (FIM). Maintenance personnel use FIM procedures to isolatefaults for a system, a functional mode, or a specific failure indication. The procedures are basedon a process of elimination; the parts of a system/malfunction are tested in a logical sequenceuntil a specific line replaceable unit (LRU) failure or a wiring fault is found. This eliminates theguesswork replacement of components which are operating properly.

a. Contents. Contents of each section of the FIM are:

(1) Malfunction indexes.

(2) Fault code indexes.

(3) Preparation procedures to be performed prior to fault isolation.

(4) Fault isolation diagrams (the actual troubleshooting procedures).

(5) Locator illustrations for hardware referenced in the fault isolation diagrams.

(6) Schematic diagrams.

b. Malfunction Indexes. The malfunction indexes list malfunctions according to the systemand/or mode of operation when the failure occurred, and also contain the alphanumeric faultcode. These indexes are to be used when the malfunction occurs during ground maintenance orwhen the flight crew did not provide a numeric fault code. When using these indexes, trouble-shooting always begins at block 1 of the specified fault isolation diagram.

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c. Fault Code Indexes. The fault code indexes list all applicable numeric fault codes innumerical order. Each fault code represents a peculiar malfunction and its associated symptomswhich could be encountered by the flight crew. A figure and block number reference for eachcode tells where to go in the fault isolation diagram to start the actual troubleshooting. Allassigned fault code numbers between 6110001 and 6120999 represent propeller assembly andsynchrophaser system failures, and are subdivided as follows:

SYSTEM/FAILURE ASSIGNED FAULT CODE RANGE

Propeller system 6110001-6110008, 6110P01

Propeller feather system 6110010-6110017, 6110F01

Negative torque signal system 6110020-6110024, 6110N01

Propeller low fluid warning system 6110030-6110034, 6110W01

Synchrophaser system 6120001-6120014, 6120S01

d. Preparation Procedures. Each procedure is contained in a separate figure which usespictures and words to simplify preparation. When required, preparation procedures must beperformed to condition the airplane before starting the actual troubleshooting. Each malfunctionand fault code index entry specifies the preparation (if required) to be performed.

e. Fault Isolation Procedures. In order to be brief and concise, fault isolation procedures donot include detailed instructions necessary to gain access to components, to disconnect or con-nect electrical connectors, or to close panels/covers following troubleshooting. Always backtrackthrough the fault isolation diagram and remove any jumpers, reconnect plugs and hydrauliclines, and reinstall relays, access panels, and other removed components. All maintenance pro-cedures must be properly performed (refer to the applicable Job Guide manual when a problemor question about maintenance procedures arises). The Job Guide manuals also contain replace-ment procedures to be used when troubleshooting determines the bad component or LRU.Always bring the airplane to a safe condition before replacing specified components. Wiringproblems will require the use of TO 1C-130H-2-13, TO 1C-130H-2-14, TO 1C-130B-2-13, TO 1C-130(M)E-2-13, or TO 1C-130(M)H-2-13.

f. Fault Isolation Diagrams. The fault isolation diagrams follow the preparation procedures(within a section). The fault isolation diagrams are entered at a point designated by the faultcode index or malfunction index. From the point of entry, a series of instructions, questions, andanswers lead the mechanic to a defective component or circuit fault. To locate components, afacing illustration is provided. Switch positions shown on these illustrations do not necessarilyrepresent the mode of operation; therefore change switch positions only when specified in thetroubleshooting blocks.

(1) Flow Sheets. Each flow sheet of a fault isolation diagram contains either two or threecolumns of blocks. The right column always contains rectangular blocks which state the repairaction to be accomplished. The remaining blocks are hexagons that always contain a question tobe answered. If the answer to the question is yes, follow the YES arrow to the next block. Ifthe answer to the question is no, follow the NO arrow to the next block. When the arrow refersto another sheet of the figure, always go to the upper left block on the specified sheet.

(2) Blocks. The blocks within a fault isolation diagram are numbered consecutively withthe block number appearing in the upper left corner of each block. Block number 1 is at theupper left corner of sheet 1 of each figure. The block numbers go down the page, then to the topblock in the next column to the right. Additional sheets of a figure continue the number

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sequence in the same manner until every block in the figure is numbered (there are never twoblocks in the same figure with the same number).

(3) Fault Codes. Any number in the upper right corner of a block is the fault code. Mostblocks will not have a fault code in them, and a few will contain two or more fault codes. Thesenumbers are used to make sure troubleshooting starts at the block number specified in the faultcode index.

(4) Test Points. A block may contain a test point symbol ( ) as an aid in troubleshoot-ing when an electrical measurement is specified. A note identifies the schematic diagram onwhich the test point is located. The test points on a schematic diagram show the functionallocation of the measurement being made. Test point number 1 is always near the upper leftcorner of the schematic diagram. Test points 2 and up then generally go around the diagram ina clockwise rotation. A single test point reference for voltage measurements means that thevoltage is referenced to airplane ground.

(5) Circuit Interruption Symbol. A lightning bolt within a circle at the top of a block is acircuit interruption symbol ( ). Its presence means that a live circuit may be temporarilybroken to gain access to an electrical measurement point. Circuit breaker(s) or switch(es) feed-ing the circuit under test are identified elsewhere on the page. If different circuit breaker(s) orswitch(es) apply to different blocks on a page, a delta number (example, 1 ) will be added to thecircuit interruption symbol. When the symbol appears in a block, open the appropriate circuitbreaker(s) or change switch positions before proceeding; break the circuit (remove relay, discon-nect plug, etc., specified in the block); then close the circuit breaker(s) or switch(es) beforemaking the electrical measurement specified in the block.

(6) Figure References. A figure reference in a rectangular block identifies the electricalschematic diagram that represents the circuit or wiring to be repaired. If a circuit or wiringfault is encountered, refer to TO 1C-130H-2-13, TO 1C-130H-2-14, TO 1C-130B-2-13, or TO 1C-130(M)E-2-13, or TO 1C-130(M)H-2-13 to determine actual wire routing.

(7) Effectivity. Airplane delivery schedules and/or modifications can result in mixed fleetconfigurations. Sometimes, different FIM diagrams, or different paths on a FIM diagram, mustbe utilized to account for configuration differences. When necessary, the FIM diagram is anno-tated by model number, tail number, or TCTO incorporation statement to distinguish configura-tion differences. FIM diagrams not annotated apply to all airplanes.

(8) Index Numbers. Index numbers on locator illustrations generally start with number 1at the upper left corner of the page, and go clockwise around the page. Appropriate directions(forward, aft, inboard, outboard, etc.) and references (fuselage station numbers, etc.) appear neareach view on the illustration when the orientation is questionable.

g. Schematic Diagrams. Schematic diagrams are grouped at the end of each section.

h. In-line Disconnects. The wing leading and trailing edge disconnects, the center wing tun-nel disconnects, the wheelwell disconnects, and the aft fuselage disconnects are not specificallytroubleshot in the fault isolation diagrams. These disconnects are shown on the schematicdiagrams. An In-line Disconnect Locator figure at the end of each applicable section shows thelocation of these disconnects. A hex flag ( ) appears adjacent to the affected reference designa-tors on the applicable schematic diagrams. These hex flags are keyed to the views in the locatorfigure that show that particular in-line disconnect.

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1-4. SPECIAL TOOLS AND TEST EQUIPMENT REQUIRED FOR FAULT ISOLATION.

AN typedesignation Use and

Nomenclature or part No. Alternate application

Synchrophaser system AD33480-2 Equivalent Propeller-related mea-test set surements

Multimeter AN/PSM-37( ) Equivalent Measure voltages and re-sistances

28 VDC light Local manufacture Equivalent Test 28 VDC circuitsunder load

Shim (0.225 inch Local manufacture Equivalent Actuate NTS linkagethick)

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Section II. PROPELLER ASSEMBLY

2-1. GENERAL. The fault isolation material in this section is used for troubleshooting anypropeller system malfunction excluding the synchrophaser system. Contents of this sectioninclude a malfunction index, fault code indexes, preparation procedures to be performed prior tofault isolation, fault isolation diagrams (the actual troubleshooting procedures), locator illustra-tions for hardware referenced in the fault isolation diagrams, and schematic diagrams.

2-2. MALFUNCTION INDEX. The malfunction index (table 2-1) is used when a malfunction isencountered during ground maintenance and no numeric fault code was determined from theFRM diagram, when no numeric fault code was provided by the flight crew, or when the flightcrew only provided an alphanumeric fault code. Malfunctioning systems/modes of operation arelisted in the left column of the table. The middle column contains the alphanumeric fault code,while the right column identifies the preparation and fault isolation figures for troubleshooting.

Table 2-1. Propeller Malfunctions

*AlphanumericMalfunction fault code Fault isolation reference

1. Propeller system mal- 6110P01 Perform figure 2-1, Preparation A, then gofunction to figure 2-4, block 1.

2. Propeller feather sys- 6110F01 Perform figure 2-1, Preparation A, then gotem malfunction to figure 2-4, block 1.

3. Negative torque sig- 6110N01 Perform figure 2-1, Preparation A, then gonal system malfunc- to figure 2-4, block 1.tion

4. Propeller low fluid 6110W01 Perform figure 2-3, Preparation C, then gowarning system mal- to figure 2-5, block 1.function

* If provided by flight crew

2-3. NUMERIC FAULT CODE INDEXES. All assigned numeric FRM fault codes for the propellerassembly are listed in tables 2-2 through 2-6. Fault codes are listed in numerical order in theleft column of each table. The middle column contains the AFTO Form 781A report and listssymptoms and conditions actually observed by the flight crew while performing the FRM proce-dure. The right column identifies the preparation and fault isolation figures for troubleshooting.

Table 2-2. Propeller System Fault Codes

Fault code AFTO Form 781A report Fault isolation reference

6110001 Propeller/engine No. (1)(2)(3)(4) has ex- No preparation required. Go to figurecessive vibration as indicated by (engine 2-4, block 537.condition lever) (throttle) (visual) indica-tion.

61-10-002-1

TO 1C-130H-2-61FI-00-1

Table 2-2. Propeller System Fault Codes - Continued


6110002 Beta indicator light No. (1)(2)(3)(4) failed Perform figure 2-1, Preparation A, thento come on in (bright)(dim)(both bright go to figure 2-4: and dim) modes when throttle was re- Airplanes prior to AF92-0547 and AF92-tarded below FLIGHT IDLE/FLT IDLE 3021 through AF92-3024:gate.

block 74 for bright mode failure block 131 for dim mode failure block 80 for both modes failure

Airplanes AF92-0547 through AF92-2104and AF92-3281 and up:

block 76 for bright mode failure block 19 for dim mode failure block 87 for both modes failure

6110003 Propeller No. (1)(2)(3)(4) low pitch was Perform figure 2-1, Preparation A, thenslow or stop did not retract when throttle go to figure 2-4, block 532.was placed to GROUND IDLE/GNDIDLE as indicated by lack of torque de-crease.

6110004 No. (1)(2)(3)(4) flight idle torque spread is No preparation required. Go to figurenot within limits. 2-4, block 47.

6110005 Engine No. (1)(2)(3)(4) RPM is not within Perform figure 2-2, Preparation B. Startflight manual limits in propeller gov- engines in accordance with TO 1C-130H-erning range. RPM indicated __ percent 2-71JG-00-1, 71-00-01; or TO 1C-with throttle at __ position. 130(A)H-2-71JG-00-1, 71-00-10; and go to

figure 2-4, block 52.

6110006 Symmetric engine torque exceeds 1000 No preparation required. Go to figure 2-inch-pounds for engines (1 and 4)(2 and 4, block 511.3) at maximum reverse setting.

6110007 Engine RPM is not within limits at maxi- Fault is in engine or RPM indicating sys-mum reverse setting. tem. Go to TO 1C-130H-2-70FI-00-1-1,

Section II, and continue troubleshooting.

6110008 Beta indicator light No. (1)(2)(3)(4) is on Perform figure 2-1, Preparation A, thenwith throttle above FLIGHT IDLE/FLT go to figure 2-4, block 241.IDLE gate.

61-10-002-2

TO 1C-130H-2-61FI-00-1

Table 2-3. Propeller Feather System Fault Codes


6110010 Propeller No. (1)(2)(3)(4) fails to go from Perform figure 2-1, Preparation A, thenmaximum reverse to full feather in 25 go to figure 2-4, block 39.seconds.

6110011 Propeller feather override button light/ Replace propeller feather override button.FTHR light No. (1)(2)(3)(4) fails to go offat end of feather cycle.

6110012 Propeller feather override button No. Perform figure 2-1, Preparation A, then(1)(2)(3)(4) fails to pop out at end of go to figure 2-4, block 302.feather cycle.

6110013 PROPELLER FEATHER OVERRIDE No preparation required. Go to figurebutton light/FTHR light No. (1)(2)(3)(4) 2-4, block 225 (airplanes prior to AF92-fails to come on during feather cycle. 0547 and AF92-3021 through AF92-3024)

or block 227 (airplanes AF92-0547through AF92-2104 and AF92-3281 andup).

6110014 Propeller feather override button No. Perform figure 2-1, Preparation A, then(1)(2)(3)(4) cycles during feather cycle. go to figure 2-4, block 203.

6110015 Propeller feather override button No. Perform figure 2-1, Preparation A, then(1)(2)(3)(4) fails to pull in during feather go to figure 2-4, block 187.cycle.

6110016 Propeller No. (1)(2)(3)(4) fails to feather Perform figure 2-1, Preparation A, thenwith engine condition lever. Propeller go to figure 2-4, block 189.does feather with fire emergency handle.

6110017 Propeller No. (1)(2)(3)(4) fails to feather Perform figure 2-1, Preparation A, thenwith engine condition lever or fire emer- go to figure 2-4, block 9 (airplanes priorgency handle. to AF92-0547 and AF92-3021 through

AF92-3024) or block 14 (airplanes AF92-0547 through AF92-2104 and AF92-3281and up).

Table 2-4. Negative Torque Signal System Fault Codes


6110020 FEATHER VALVE AND NTS CHECK Perform figure 2-1, Preparation A, thenlight/NTS light No. (1)(2)(3)(4) is on dur- go to figure 2-4, block 6 (airplanes prioring non-NTS/feather condition. to AF92-0547 and AF92-3021 through

AF92-3024) or block 13 (airplanes AF92-0547 through AF92-2104 and AF92-3281and up).

61-10-002-3

TO 1C-130H-2-61FI-00-1

Table 2-4. Negative Torque Signal System Fault Codes - Continued


6110021 Engine No. (1)(2)(3)(4) exhibits excessive Perform figure 2-1, Preparation A, thenNTS indications in relation to other oper- go to figure 2-4, block 372.ating engines.

6110022 FEATHER VALVE AND NTS CHECK Perform figure 2-1, Preparation A, thenlight/NTS light No. (1)(2)(3)(4) failed to go to figure 2-4, block 323.come on when air start was accom-plished.

6110023 FEATHER VALVE AND NTS CHECK Perform figure 2-1, Preparation A, thenlight/NTS light No. (1)(2)(3)(4) failed to go to figure 2-4, block 323.come on when engine condition lever wasmoved to FEATHER/FTR position.

6110024 FEATHER VALVE AND NTS CHECK Perform figure 2-1, Preparation A, thenlight/NTS light No. (1)(2)(3)(4) failed to go to figure 2-4, block 26 (airplanes priorcome on with FEATHER VALVE AND to AF92-0547 and AF92-3021 throughNTS CHECK switch in NTS position dur- AF92-3024) or block 30 (airplanes AF92-ing engine shutdown. 0547 through AF92-2104 and AF92-3281

and up).

Table 2-5. Propeller Low Fluid Warning System Fault Codes (Airplanes Prior to AF92-0547 andAF92-3021 Through AF92-3024)


6110030 (PROP LOW OIL QUANTITY master Perform figure 2-3, Preparation C, thenwarning light) (and) (PROPELLER LOW go to figure 2-5, block 189.OIL WARNING light No. (1)(2)(3)(4)) failto go to selected bright/dim mode.

6110031 PROP LOW OIL QUANTITY master Perform figure 2-3, Preparation C, thenwarning light fails to come on when PRO- go to figure 2-5, block 160.PELLER LOW OIL WARNING light No.(1)(2)(3)(4) is on.

6110032 With known low propeller fluid quantity, Perform figure 2-3, Preparation C, thenPROPELLER LOW OIL WARNING light go to figure 2-5, block 8.No. (1)(2)(3)(4) failed to come on.

6110033 PROP LOW OIL QUANTITY master Perform figure 2-3, Preparation C, thenwarning light is on with PROPELLER go to figure 2-5, block 93.LOW OIL WARNING lights off.

6110034 PROPELLER LOW OIL WARNING light Perform figure 2-3, Preparation C, thenNo. (1)(2)(3)(4) came on. go to figure 2-5, block 6.

61-10-002-4

TO 1C-130H-2-61FI-00-1

Table 2-6. Propeller Low Fluid Warning System Fault Codes (Airplanes AF92-0547 Through AF92-2104and AF92-3281 and Up)


6110030 PROP low oil warning light No. Fault is in MACAWS. Go to TO(1)(2)(3)(4) fails to go to selected bright/ 1C-130H-2-33FI-00-1-2, Section IV, anddim mode. continue troubleshooting.

6110032 With known low propeller fluid quantity, Perform figure 2-3, Preparation C, thenPROP low oil warning light No. go to figure 2-5, block 22.(1)(2)(3)(4) failed to come on.

6110034 PROP low oil warning light No. Perform figure 2-3, Preparation C, then(1)(2)(3)(4) came on. go to figure 2-5, block 6.

2-4. PREPARATION PROCEDURES.

WARNING

Improper or inadequate preparation of the airplane may result ininjury to personnel and/or damage to the airplane.

The applicable preparation procedures must be performed before starting troubleshooting. Thepreparation is referenced in the malfunction index and fault code indexes. Each procedure iscontained in a figure that illustrates step-by-step actions to be taken to prepare the airplane fortroubleshooting.

61-10-002-5/(2-6 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-1. Preparation A (Sheet 1 of 4)

61-10-002-7

TO 1C-130H-2-61FI-00-1

Figure 2-1. Preparation A (Sheet 2)

61-10-002-8

TO 1C-130H-2-61FI-00-1


61-10-002-9

TO 1C-130H-2-61FI-00-1


61-10-002-10

TO 1C-130H-2-61FI-00-1

Figure 2-2. Preparation B (Sheet 1 of 3)

61-10-002-11

TO 1C-130H-2-61FI-00-1

Figure 2-2. Preparation B (Sheet 2)

61-10-002-12

TO 1C-130H-2-61FI-00-1


61-10-002-13

TO 1C-130H-2-61FI-00-1

Figure 2-3. Preparation C

61-10-002-14

TO 1C-130H-2-61FI-00-1

2-5. FAULT ISOLATION DIAGRAMS. The fault isolation diagrams in this section are used fortroubleshooting any propeller malfunction. When the flight crew uses a FRM fault code toreport a malfunction, that number will be found in one of the fault code indexes. When no FRMfault code is available, the malfunction index identifies the figure to use for fault isolation.

a. Arrangement. One fault isolation diagram is included for the propeller assembly and asecond for the propeller low fluid warning system. Opposite each flow sheet of a fault isolationdiagram is an illustration which shows the physical location of items referenced in individualfault isolation diagram blocks. Double-check these illustrations to verify the correct locationwhen making an observation or measurement. Following the fault isolation diagrams are theelectrical schematic diagrams. The schematic diagrams are laid out so that no portion of adiagram is covered up when folded out for use. Thus it is easy to concurrently locate compo-nents, circuits, and test points that are referenced on the fault isolation diagram.

b. Using Troubleshooting Data. A thorough description of the fault isolation diagram andother troubleshooting data is provided in Section I. In addition, the Introduction contains anillustrated how-to-use figure for this section. Understand how to use the troubleshooting infor-mation before attempting to repair the airplane.

61-10-002-15

TO 1C-130H-2-61FI-00-1

1 6110F01, 6110N01,26110P01 YES NO

TO SHT 23Is BETA indicator light on bright-Is airplane equipped with BETAly?indicator lights (1)?

NOYES

3

YESIs airplane serial number AF92-TO SHT 50547 through AF92-2104 or

AF92-3281 and up?

NO

4

Momentarily place CAUTION NOLIGHTS switch (4) to DIM. TO SHT 41Is BETA indicator light now ondimly?

YES

5 8NO

Is FEATHER VALVE AND NTS Replace FEATHER VALVECHECK light (3) off? AND NTS CHECK switch (2).

YES

6 6110020

NOPlace FEATHER VALVE AND NTS CHECK switchTO SHT 43(2) to VALVE.

Is FEATHER VALVE AND NTS CHECK light (3) off?

YES

7

NOPlace FEATHER VALVE AND NTS CHECK switchTO SHT 53to NTS.

Is FEATHER VALVE AND NTS CHECK light off?

YES

TO SHT 3

NOTE

1 Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024, except MC-130E/H airplanes.

2 Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.

3 MC-130E airplanes.

4 MC-130H airplanes.

Figure 2-4. Propeller Assembly Malfunction (Sheet 1 of 172)

61-10-002-16

TO 1C-130H-2-61FI-00-1

Figure 2-4. Propeller Assembly Malfunction (Sheet 2)

61-10-002-17

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?

YES

10NO

Did light in PROPELLER FEATH- TO SHT 69ER OVERRIDE button come on?

YES

TO SHT 7

NOTE




61-10-002-18

TO 1C-130H-2-61FI-00-1


61-10-002-19

TO 1C-130H-2-61FI-00-1

FROM SHT 1

11 1617NO NOIs airplane prior to AF95-1001 or is Swap torquemeter indica-

torquemeter BETA legend (2) pre- Remove and replace indicator. tors.sent on indicator? Does malfunction persist?

YES YES

18

Repair open circuit between tor-quemeter plug P3978 pin g and re-lated Caution Advisory Panel plugP1725 pin.

1219 6110002a. Place the NORM/NVIS switch (8)

to NORM. NO Fault is in MACAWS. Go to TOb. Momentarily place the BRIGHT/ 1C-130H-2-33FI-00-1-2, SectionDIM switch (7) to DIM. IV, and continue troubleshooting. Is BETA indicator light (3) on dimly?

YES

13 6110020 NOTO SHT 43Is NTS light (5) off?

YES

14 6110017

CAUTIONIf propeller feather override buttondoes not pop out 4 to 5 secondsafter propeller blade movement

NOstops, pull out manually to preventTO SHT 57damage to auxiliary pump motor.

Move engine condition lever (1) toFTR.Does propeller feather override but-ton (6) pull in and remain in?

YES

15 NOTO SHT 69Does FTHR light (4) come on?

YES

TO SHT 7


61-10-002-20

TO 1C-130H-2-61FI-00-1


61-10-002-21

TO 1C-130H-2-61FI-00-1


61-10-002-22

TO 1C-130H-2-61FI-00-1


61-10-002-23

TO 1C-130H-2-61FI-00-1

FROM SHT 7

2833

Did FTHR light (3) go off when NOReplace propeller feather over-propeller feather override buttonride button. (5) popped out?

YES

29 NOTO SHT 75Is BETA indicator light (2) off?

YES

30 6110024

a. If troubleshooting fault code6110024A, open FEATHERPUMP MOTOR PHASE A,B,C cir- NOcuit breakers (8). TO SHT 109b. If troubleshooting fault code6110024A, move engine conditionlever (6) to FTR.Is NTS light (4) on?

YES

31

NOMove engine condition lever toTO SHT 131GND STOP.

Is NTS light on?

YES

32

a. Move throttle (7) to FLT IDLEposition (bottom of FLT IDLEgate). NOb. Hold engine condition lever in TO SHT 141AIR START until propeller blades(1) stop moving.Does propeller move from featherto low pitch stop position?

YES

TO SHT 13


61-10-002-24

TO 1C-130H-2-61FI-00-1


61-10-002-25

TO 1C-130H-2-61FI-00-1

FROM SHT 7

34

Place FEATHER VALVE AND NTS CHECK NOswitch (5) to NTS. TO SHT 123Is 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

36

a. Close FEATHER PUMP MOTORPHASE A, B, C/ 2 FEATHER PUMP MO-TOR circuit breakers (6).b. Move THROTTLE (2) to FLIGHT IDLE NOposition (bottom of FLIGHT IDLE gate). TO SHT 141c. Hold ENGINE CONDITION lever in AIRSTART until propeller blades (1) stop mov-ing.Does propeller move from feather to lowpitch stop position?

YES

TO SHT 13

NOTE




61-10-002-26

TO 1C-130H-2-61FI-00-1


61-10-002-27

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

TO SHT 147a. 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

3842

40a. Remove shim.Repair or replace linkage as re-b. Hold engine condition lever in Inspect NTS linkage to andNO YES quired or replace valve housingAIR START until propeller blades through valve housing assembly assembly cover as required instop moving. cover (3) for evidence of binding. accordance with TO 1C-130H-Did propeller blades move to flight Is any binding observed? 2-61JG-20-1, 61-20-02. idle position?

YESNO

43

Replace valve housing assem-bly in accordance with TO 1C-130H-2-61JG-20-1, 61-20-02.

39 6110010

a. Move throttle (6) to MAX RE-VERSE/MAX RVS.b. Hold engine condition lever (7)

41in AIR START until propeller NO NOblades (8) stop moving. TO SHT 149Did propeller blades move towardc. Pull fire emergency handle (4) feather position?for propeller under test while ob-serving propeller blades.Does propeller feather within 25seconds?

YES

YES

TO SHT 15

TO SHT 87

NOTE





61-10-002-28

TO 1C-130H-2-61FI-00-1


61-10-002-29

TO 1C-130H-2-61FI-00-1

FROM SHT 13

44

a. Connect synchrophaser systemtest set in accordance with Prepa-

48ration B.b. Start engine under test and Fault is in engine or torqueme-symmetrical engine in accordance ter system. Shut down engineswith TO 1C-130H-2-71JG-00-1, in accordance with TO 1C-NO71-00-10; or TO 1C-130(A)H-2- 130H-2-71JG-00-1, 71-00-10; or71JG-00-1, 71-00-10. TO 1C-130(A)H-2-71JG-00-1,c. Perform torquemeter calibration 71-00-10; then go to TO 1C-in accordance with TO 1C-130H- 130H-2-70FI-00-1-1 and contin-2-77JG-00-1, 77-10-04; or TO 1C- ue troubleshooting. 130(A)H-2-71JG-00-1, 71-00-10.Is torquemeter calibration satisfac-tory?

YES

45

a. Move throttles (3) to FLIGHT 47 6110004IDLE/FLT IDLE.

a. Shut down engines in accor-b. Record indications on enginedance with TO 1C-130H-2-71JG- 49torque indicators (2).00-1, 71-00-10; or TO 1C-c. Advance throttles until ELEC- Rig engine coordinator-to-pro-NO NO130(A)H-2-71JG-00-1, 71-00-10.TRONIC FUEL CORRECTION/TD peller control assembly linkageb. Perform operational checkoutlights (1) first go off. in accordance with TO 1C-of propeller - static condition ind. Retard throttles to FLIGHT 130H-2-61JG-20-1, 61-20-21. accordance with TO 1C-130H-2-IDLE/FLT IDLE.61JG-10-1, 61-10-01.Is indicated torque now 500 toIs check satisfactory? 2000 inch-pounds higher than re-

corded in step b?

YES

YES

50

Adjust or replace low pitch stop assembly inaccordance with TO 1C-130H-2-61JG-10-1,61-10-12.

5146Fault is in engine. Shut down engines inIs torque and RPM at flight idle with- NOaccordance with TO 1C-130H-2-71JG-00-1,in limits of TO 1C-130H-2-61JG-10-1,71-00-10; or TO 1C-130(A)H-2-71JG-00-1,61-10-02 (subtask 1-2-3)? 71-00-10; then go to TO 1C-130H-2-70FI-00-1-2 and continue troubleshooting. YES

TO SHT 17

NOTE

1 Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.



61-10-002-30

TO 1C-130H-2-61FI-00-1


61-10-002-31

TO 1C-130H-2-61FI-00-1


61-10-002-32

TO 1C-130H-2-61FI-00-1


61-10-002-33

TO 1C-130H-2-61FI-00-1

FROM SHT 17

61

a. Move throttles (3) to MAXIMUMREVERSE/MAX RVS.b. Record indications on engine

YEStorque indicators (2) and RPM in-TO SHT 161dications in test set FUNCTION

display (1).Is there a symmetrical torque dif-ference in excess of 1000 inch-pounds?

NO

64

Fault is in engine or RPM indi-cating system. Shut down en-62gines in accordance with TOAre RPM indications within limits NO1C-130H-2-71JG-00-1, 71-00-of TO 1C-130H-2-61JG-10-1, 61-10; or TO 1C-130(A)H-2-71JG-10-02 (subtask 1-2-2)?00-1, 71-00-10; then go to TO1C-130H-2-71FI-00-1-1 andcontinue troubleshooting.

YES

63

CAUTIONKeep pitchlock time to a mini-mum.

NOTO SHT 163Perform pitchlock check of affect-

ed propeller in accordance withTO 1C-130H-2-61JG-10-1, 61-10-02 (subtask 1-2-10).Was a pitchlock obtained?

YES

TO SHT 21


61-10-002-34

TO 1C-130H-2-61FI-00-1


61-10-002-35

TO 1C-130H-2-61FI-00-1

FROM SHT 19 69

Shut down engines in accordance65with TO 1C-130H-2-71JG-00-1, 71-00-Did pitchlock disengage in accordance with10; TO 1C-130(A)H-2-71JG-00-1, 71-NO

TO 1C-130H-2-61JG-10-1, 61-10-02 (as indi-00-10; or TO 1C-130(M)H-2-71JG-00-cated by torque and RPM reading same as1, 71-00-10; then replace pitchlockinitially recorded in the pitchlock check)? regulator assembly in accordance withTO 1C-130H-2-61JG-10-1, 61-10-11. YES

66

a. Perform synchrophaser index in accordancewith 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-ed by a decrease on engine torque indicators(1)?

YES

67

NOTEIf correct results are not obtained, repeat theshutdown in normal ground idle rather thanlow speed ground idle.

NOShut down engines in accordance with TO 1C- TO SHT 119130H-2-71JG-00-1, 71-00-10; TO 1C-130(A)H-2-71JG-00-1, 71-00-10; or TO 1C-130(M)H-2-71JG-00-1, 71-00-10.

1 3 4 Is FEATHER VALVE AND NTSCHECK light (2) on?

2 Is NTS light (2) on?

YES

68 70NO

Is there a reported malfunction associated with Propeller system is normal. Securea propeller vibration? system.

YES

TO SHT 169

NOTE






61-10-002-36

TO 1C-130H-2-61FI-00-1


61-10-002-37

TO 1C-130H-2-61FI-00-1

FROM SHT 1

7673 611000271YES YESIs airplane serial number AF92- Fault is in MACAWS. Go to TOAre all BETA indicator lights

0547 through AF92-2104 or 1C-130H-2-33FI-00-1-2, Section(1) on dimly? AF92-3281 and up? IV, and continue troubleshooting.

NONO

74 6110002

Gain access to terminals of indi-77cator lights dimmer No. 10 (2). NO

Is 28 VDC present between dim- Replace indicator lights dimmermer terminals W and X? No. 10.

1 2

YES

78

Fault is in dimming circuit. Go toTO 1C-130H-2-33FI-00-1-1-1, Sec-tion II, and continue troubleshoot-ing.

797572YES YES Fault is in MACAWS. Go to TOIs airplane serial number AF92-Is BETA indicator light under

1C-130H-2-33FI-00-1-2, Section0547 through AF92-2104 ortest on dimly? IV, and continue troubleshooting. AF92-3281 and up?

NONO

TO SHT 2580

Replace indicator lights dimmerNo. 10 (2).

NOTE



3. See figure 2-6 for:


61-10-002-38

TO 1C-130H-2-61FI-00-1


61-10-002-39

TO 1C-130H-2-61FI-00-1

FROM SHT 23

81YES

Is airplane AF92-0547 through TO SHT 27AF92-2104 or AF92-3281 and up?

NO

82 6110002

YESPress to test affected BETA indi-TO SHT 31cator light (1).

Does light press to test?

NO

83

Gain access to terminals of BETA85indicator light.

YESIs 28 VDC present on light termi- Replace BETA indicator lightnal 1? assembly.

16 ,

18 ,

20 OR

22

NO

84

Gain access to terminals of indi-cator lights dimmer No. 10 (2). 86Is 28 VDC present on specified

Repair power circuit to specifieddimmer terminal?dimmer terminal. (See figure 2-6.)Dim Test

Prop Term Point NODim

Prop Term1 J4

1 J2 K2 K

63 M4 N3 M

8

4 N10

YES

TO SHT 29

NOTE

See figure 2-6 for:


61-10-002-40

TO 1C-130H-2-61FI-00-1


61-10-002-41

TO 1C-130H-2-61FI-00-1


61-10-002-42 Change 1

TO 1C-130H-2-61FI-00-1


61-10-002-43

TO 1C-130H-2-61FI-00-1

FROM SHT 25

96

Is 28 VDC present on specifiedterminal of indicator lights dimmerNo. 10 (5)?

Dim Test98Prop Term Point NOReplace indicator lights dimmer

1 j3

No. 10.

2 k5

3 m7

4 n9

YES

97

a. Remove power from airplane.b. Open BETA RANGE LIGHT cir-cuit breaker (4).c. Gain access to and disconnect 99plug P599B (2) at main instrument

Repair open circuit betweenpanel disconnect.specified dimmer terminal andIs there continuity between termi-related pin of receptacle J339Bnal 1 of BETA indicator light (3)(1). (See figure 2-6.)and specified plug P599B pin?

YESDim RcptPlug Test

Prop Term PinProp Pin Points1 j A2 k C1 A

16 113 m E4 n G2 C

18 12

3 E20 13

4 G22 14

NO

100

Repair open circuit. (See figure2-6.)

NOTE

See figure 2-6 for:


61-10-002-44

TO 1C-130H-2-61FI-00-1


61-10-002-45

TO 1C-130H-2-61FI-00-1


61-10-002-46

TO 1C-130H-2-61FI-00-1


61-10-002-47

TO 1C-130H-2-61FI-00-1

FROM SHT 31

111

a. Connect plug P390 (3) to valve housing assembly (4). 115b. Gain access to and disconnect plug P398 (2) at engine fire-

Repair open circuit be-wall.tween receptacle J239NOIs there continuity between pins H and V of receptacle J239 (1)?pin H and plug P390 pinH. (See figure 2-6 or 2-28 29

, 30 31

, 7.)

32 33 OR

35 36

YES

112YES

Is airplane serial number AF92-0547 through AF92-2104 or TO SHT 35AF92-3281 and up?

NO

113

a. Connect plug P398 at engine firewall. 116b. Gain access to terminals of BETA indicator light (5). YES

Replace BETA indicatorIs a ground present on light terminal 2?light assembly.

15,

17,

19 OR

21

NO

114

a. Remove power from airplane.b. Gain access to and disconnect plug P599B 117(6) at main instrument panel disconnect.

Repair open circuit between BETAIs a ground present on specified pin of recep-indicator light terminal 2 and relat-tacle J339B (7)?ed plug P599B pin. (See figure 2-6.)Rcpt Test

YESProp Pin Point

PlugProp Pin1 B

231 B2 D2 D

243 F4 H3 F

25

4 H26

NO

TO SHT 39

NOTE

See figure 2-6 or 2-7 for:


61-10-002-48

TO 1C-130H-2-61FI-00-1


61-10-002-49

TO 1C-130H-2-61FI-00-1

FROM SHT 33

118 YESTO SHT 37Is 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 37Prop Pin Point

1 4154

2 4255

3 4356

4 4457

YES

120

Fault is in MACAWS. Refer toTO 1C-130H-2-33FI-00-1-2,Section IV, for troubleshooting.

NOTE

See figure 2-7 for:


61-10-002-50

TO 1C-130H-2-61FI-00-1


61-10-002-51

TO 1C-130H-2-61FI-00-1

123

Repair open circuit betweenFROM SHT 35plug P398 (1) pin H and relatedpin of plug P1725A (2). (See121figure 2-7.)NO

Is an outboard propeller beingtroubleshot?

PlugProp Pin2 423 43

YES

122

Gain access to and disconnect 124plug P130/P1139 (4) at outer

Repair open circuit between pinwing break.H of plug P398 (1) and relatedIs a ground present on specifiedreceptacle J235/J935 pin. (Seepin of receptacle J235/J935 (3)?figure 2-7.)NO

RCPT TestRCPTProp Pin Point

Prop Pin1 E1 E

274 H

4 H34

YES

125

Repair open circuit betweenspecified plug P130/P1139 pinand related pin of plug P1725A(2). (See figure 2-7.)

PlugProp Pin1 414 44

NOTE

See figure 2-7 for:


61-10-002-52

TO 1C-130H-2-61FI-00-1


61-10-002-53

TO 1C-130H-2-61FI-00-1

128

Repair open circuit between pinFROM SHT 33H of plug P398 (1) and relatedpin of receptacle J339B (2).126(See figure 2-6.)NO


RcptProp Pin2 D3 F

YES

127129Gain access to and disconnect

plug P130 (4) at outer wing break. Repair open circuit between pinIs a ground present on specified H of plug P398 (1) and relatedpin of receptacle J235 (3)? receptacle J235 pin. (See fig-

ure 2-6.)NORcpt Test

Prop Pin Point RcptProp Pin

1 E27

1 E4 H

4 H34

YES

130

Repair open circuit betweenspecified plug P130 pin and re-lated pin of receptacle J339B(2). (See figure 2-6.)

Plug RcptProp Pin Pin1 E B4 H H

NOTE

See figure 2-6 for:


61-10-002-54

TO 1C-130H-2-61FI-00-1


61-10-002-55

TO 1C-130H-2-61FI-00-1

FROM SHT 1

131 6110002 133YES

Are any BETA indicator lights (1) Replace indicator lights dimmeron dimly? No. 10 (2).

NO

132

Gain access to terminals of indi-134cator lights dimmer No. 10 (2).

YESIs 28 VDC present between dim- Replace indicator lights dimmermer terminals W and X? No. 10.

1 2

NO

135

Fault is in dimming circuit. Goto TO 1C-130H-2-33FI-00-1-1-1and continue troubleshooting.

NOTE

See figure 2-6 for:


61-10-002-56

TO 1C-130H-2-61FI-00-1


61-10-002-57

TO 1C-130H-2-61FI-00-1

FROM SHT 1 OR 5

136 140

Gain access to and inspect en- Replace reduction gear in ac-YESgine NTS plunger (2). cordance with TO 1C-130H-2-Is plunger actuated? 71JG-00-2, 71-90-20.

NO

137141a. Inspect NTS linkage for correct

gap of 0.011 to 0.020 inch in ac- Adjust NTS linkage in accor-cordance with TO 1C-130H-2- dance with TO 1C-130H-2-YES61JG-20-1, 61-20-22. 61JG-20-1, 61-20-22, or repairb. Also inspect linkage for any or replace damaged compo-binding or damaged components. nents as required. Are any discrepancies found?

NO

138

a. Rotate propeller control (5)clockwise as viewed from the rearand hold firmly against prop

142torque retainer assembly (1).b. Check clearance between As required, replace damagedYEStorque retainer lug (4) and prop components in accordance withtorque retainer assembly for a TO 1C-130H-2-61JG-20-1, 61-maximum gap of 0.050 inch. 20-11. c. Release propeller control.d. Also inspect components forlooseness or damage.Are any discrepancies found?

NO

139 143

Inspect NTS linkage through valve Replace valve housing assem-YEShousing assembly cover (3). bly cover in accordance withIs NTS linkage in the actuated po- TO 1C-130H-2-61JG-20-1, 61-sition? 20-02.

NO

TO SHT 45


61-10-002-58

TO 1C-130H-2-61FI-00-1


61-10-002-59

TO 1C-130H-2-61FI-00-1


61-10-002-60

TO 1C-130H-2-61FI-00-1


61-10-002-61

TO 1C-130H-2-61FI-00-1

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?

156

Fault is in MACAWS. Refer toNOPlug Test

TO 1C-130H-2-33FI-00-2 forProp Pin Pointtroubleshooting.

1 5378

2 5479

3 5580

4 5681

YES

157154 Repair ground fault betweenNO

Is an outboard propeller being applicable pin of plug P1725Atroubleshot? (2) and pin F of plug P398 (1).

(See figure 2-9.) YES

155

Gain access to and disconnect 158plug P18/P1835 (3) at outer wing

Repair ground fault between pinbreak. NON of receptacle J233/J956 (4)Is a ground present on plug pinand pin F of plug P398 (1).N?(See figure 2-9.)

33 47

YES

159

Repair ground fault betweenplug P18/P1835 pin N and ap-plicable pin of plug P1725A (2).(See figure 2-9.)

NOTE

See figure 2-9 for:


61-10-002-62

TO 1C-130H-2-61FI-00-1


61-10-002-63

TO 1C-130H-2-61FI-00-1

FROM SHT 45

160

a. Place FEATHER VALVE AND165NTS switch (3) to NORMAL.

b. Gain access to terminals of Repair ground fault between re-164YES NONTS check relay (2) and discon- lay terminal A2 and terminal 2

nect wire from relay terminal A2. of FEATHER VALVE AND NTSIs airplane an MC-130H? Is a ground present on discon- CHECK light (4). (See figure 2-nected wire? 8.)

52 ,

22 ,

59 OR

29

NO

YES

TO SHT 51

161

Is there continuity between relayterminals A1 and A2. 166YES

Replace NTS check relay.54 52 ,

24 22 ,

61 59 OR

31 29

NO

167162 Repair ground fault betweenNO

Is an outboard propeller being NTS check relay terminal A3troubleshot? and pin F of plug P398 (1).



plug P18 (5) at outer wing break. Repair ground fault between pinNOIs a ground present on plug pin N of receptacle J233 (6) andN? pin F of plug P398 (1). (See

figure 2-8.)47

OR 33

YES

169

Repair ground fault betweenplug P18 pin N and NTS checkrelay terminal A3. (See figure2-8.)

NOTE



61-10-002-64

TO 1C-130H-2-61FI-00-1


61-10-002-65

TO 1C-130H-2-61FI-00-1

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

17124

70 NOReplace indicator lights dimmerNo. 4 (1). 23

71

2272

373

1574

1675

476

YES

172

Repair ground fault betweenplug 47404A2P1 and applicableterminals. (See figure 2-10.)

NOTE

See figure 2-10 for:


61-10-002-66

TO 1C-130H-2-61FI-00-1


61-10-002-67

TO 1C-130H-2-61FI-00-1

FROM SHT 1

173

175a. Open PROP SYNCHRO

Replace valve housing assem-PHASER and SYNCHRO

bly in accordance with TO 1C-YESPHASER circuit breakers (5,4).

130H-2-61JG-20-1, 61-20-02b. Gain access to and disconnect

(because of internal short cir-plug P390 (6) at valve housing

cuit). assembly.Did FEATHER VALVE AND NTSCHECK light (3) go off?

NO

174176

Repair ground fault betweenYESGain access to and disconnect plug P390 pin E and pin E ofplug P398 (2) at engine firewall. receptacle J239 (1). (See fig-Did FEATHER VALVE AND NTS ure 2-8 or 2-10.) CHECK light go off?

NO

TO SHT 55

NOTE




61-10-002-68

TO 1C-130H-2-61FI-00-1


61-10-002-69

TO 1C-130H-2-61FI-00-1

FROM SHT 53

177

a. Place FEATHER VALVE AND NTSCHECK switch (3) to NORMAL.

181b. Gain access to NTS check relay (2) YESand disconnect wire from relay terminal B2. Replace NTS check relay. Is a ground present on relay terminal B2?

51 ,

21 ,

58 OR

28

NO

178182

Disconnect wire number _K603A from relayRepair ground fault on wireterminal X1. YESnumber K603A between re-Is a ground present on disconnected wire?lay terminals X1 and B2.(See figure 2-8 or 2-10.) 50

, 20

, 57

OR 27

NO

183

Repair ground fault between179 NONTS check relay terminal X1Is an outboard propeller being troubleshot?and pin E of plug P398 (1).(See figure 2-8 or 2-10.) YES

180184

Gain access to and disconnect plug P18Repair ground fault between(4) at outer wing break. NOpin E of plug P398 (1) andIs a ground present on plug pin P?pin P of receptacle J233 (5).(See figure 2-8 or 2-10.) 48

OR 34

YES

185

Repair ground fault betweenplug P18 pin P and NTScheck relay terminal X1.(See figure 2-8 or 2-10.)

NOTE



3. See figure 2-8 or 2-10 for:


61-10-002-70

TO 1C-130H-2-61FI-00-1


61-10-002-71

TO 1C-130H-2-61FI-00-1

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. 190188

NO YESb. Momentarily press propellerReplace propeller feather over-Is fault code 6110017 beingfeather override button (2).ride button.troubleshot? 1 3 4 Does light in button come

on while button is pressed?2 Does FTHR light (5) come on

while button is pressed?

YES

NO

TO SHT 59191

Repair power circuit to specifiedterminal of terminal board

189 6110016 TB146A (3). (See figure 2-11Momentarily hold engine condition or 2-12.)NOlever (4) in AIR START.Does auxiliary pump motor (1) run Prop TB-Termwhile lever is held? 1 193

2 1943 1954 196

YES

TO SHT 65

NOTE






61-10-002-72

TO 1C-130H-2-61FI-00-1


61-10-002-73

TO 1C-130H-2-61FI-00-1

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

Gain access to terminals of feath-er relay (1). 195Is there continuity between relay NO

Repair open circuit. (See figureterminal A3 and propeller feather2-11 or 2-12.) override button terminal 3?

30 24

YES

194

Is there continuity between relay 196NOterminals A2 and A3?Replace feather relay.

31 30

YES

197

Replace propeller feather over-ride button.

NOTE







61-10-002-74

TO 1C-130H-2-61FI-00-1


61-10-002-75

TO 1C-130H-2-61FI-00-1

200

Repair open circuit between ter-FROM SHT 59 minal 7 of propeller feather

override button (4) and terminal198 1 of related terminal boardNO

Is an outboard propeller being TB107 (3). (See figure 2-11 ortroubleshot? 2-12.)

Prop TB2 TB107T3 TB107U

YES

201199 Repair open circuit between re-

Gain access to and disconnect ceptacle J209/J951 pin V andplug P124/P1134 (1) at outer terminal 1 of related terminalwing break. board TB107 (3). (See figureNOIs a ground present on pin V of 2-11 or 2-12.)receptacle J209/J951 (2)?

Prop TB47

1 TB107S4 TB107V

YES

202

Repair open circuit betweenplug P124/P1134 pin V and ter-minal 7 of propeller featheroverride button (4). (See figure2-11 or 2-12.)

NOTE







61-10-002-76

TO 1C-130H-2-61FI-00-1


61-10-002-77

TO 1C-130H-2-61FI-00-1

FROM SHT 57

203 6110014 208

Gain access to and inspect propeller feather override button (3) for Repair or replace propellerYEScorrect jamnut installation, and loose or damaged connections. feather override button asAre any discrepancies found? required.

NO

204

a. Move engine condition lever (4) to GROUND STOP/GND STOP.b. Open FEATHER PUMP MOTOR PHASE A,B,C/ 4 FEATHER PUMP 209MOTOR circuit breakers (1). NO

Replace propeller featherc. Gain access to terminals of feather relay (2) and disconnect wireoverride button. from relay terminal X2.

d. Move engine condition lever to FEATHER/FTR.Does propeller feather override button pull in and remain in?

YES

205210a. Remove electrical power.

NOb. Move engine condition lever to GROUND STOP/GND STOP. Repair open circuit. (SeeIs there continuity between feather relay terminals figure 2-11 or 2-12.)A1 and B1?

29 33

YES

206 211NO

Is there continuity between relay terminals Repair open circuit. (SeeB1 and X1?

33 28figure 2-11 or 2-12.)

YES

207212YES

Is there continuity between propeller feather overrideReplace feather relay.button terminal 8 and feather relay terminal X1?

25 28

NO

213

Repair open circuit. (Seefigure 2-11 or 2-12.)

NOTE







61-10-002-78

TO 1C-130H-2-61FI-00-1


61-10-002-79

TO 1C-130H-2-61FI-00-1

FROM SHT 57

215214 217NO NOPull fire emergency handle (1).Is fault code 6110016 being Replace propeller feather over-

Does propeller feather overridetroubleshot? ride button. button (3) pull in?

YESYES

216

a. Gain access to terminal boardTB146A (4).

218b. Move engine condition lever (5)to FEATHER/FTR. Repair open circuit between ter-Is 28 VDC present on specified minal A2 of feather relay (2)terminal? and related terminal board

TB146A terminal. (See figureYESTest 2-11 or 2-12.)

Prop TB-Term PointProp TB-Term

1 19735

1 1972 198

2 19835

3 2024 205

3 20235

4 20535

NO

TO SHT 67

NOTE







61-10-002-80

TO 1C-130H-2-61FI-00-1


61-10-002-81

TO 1C-130H-2-61FI-00-1

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 switch

221terminals 1NO and 2NO?Adjust or replace feather controlNO

Test switch in accordance with TOProp Sw Points 1C-130H-2-76JG-00-1, 76-10-

38. 1 S86E

40 39

2 S86F40 39

3 S86G40 39

4 S86H40 39

YES

220

Is there continuity between feath-222er control switch terminal 2NO

and specified terminal of terminal Repair open circuit betweenboard TB146A (2)? feather control switch terminal

1NO and related terminal boardTB- Test TB146A terminal. (See figure

Prop Sw Term Points 2-11 or 2-12.) YES

1 S86E 19339 38

Prop Sw TB-Term1 S86E 197

2 S86F 19439 38

2 S86F 1983 S86G 202

3 S86G 19539 38

4 S86H 205

4 S86H 19639 38

NO

223

Repair open circuit. (See figure2-11 or 2-12.)

NOTE



61-10-002-82

TO 1C-130H-2-61FI-00-1


61-10-002-83

TO 1C-130H-2-61FI-00-1

FROM SHT 3 OR 5

227 6110013224Momentarily hold MACAWSYES NOIs airplane serial number AF92-

TO SHT 71LAMP TEST switch (3) in test po-0547 through AF92-2104 orsition.AF92-3281 and up? Does applicable light come on?

NOYES

229

Fault is in MACAWS. Go to TO1C-130H-2-33FI-00-1-2, SectionIV, and continue troubleshoot-ing.

225 6110013

Remove bulb from affected PRO- 230PELLER FEATHER OVERRIDE NO

Replace bulb with correct partbutton (2) and inspect for correctnumber. part number (AN3140-327).

Is correct bulb installed?

YES

226

a. Move ENGINE CONDITIONlever (1) to GROUND STOP.b. Remove power from airplane

231and gain access to terminals of 228NO NOaffected PROPELLER FEATHER Repair ground circuit. (See fig-

Is airplane an MC-130H? OVERRIDE button. ure 2-11.) Is a ground present on button ter-minal G?

27

YES

YES

TO SHT 73232

Replace PROPELLER FEATH-ER OVERRIDE button.

NOTE







61-10-002-84

TO 1C-130H-2-61FI-00-1


61-10-002-85

TO 1C-130H-2-61FI-00-1

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 applicable

234pin of plug P1725A?Repair open circuit betweenNO

Plug Test plug P1725A and propellerProp Pin Point feather override button (1), ter-

minal 2. (See figure 2-12.) 1 45

60

2 4662

3 4763

4 4864

YES

235

Fault is in MACAWS. Refer toTO 1C-130H-2-33FI-00-1-2 fortroubleshooting.

NOTE



61-10-002-86

TO 1C-130H-2-61FI-00-1


61-10-002-87

TO 1C-130H-2-61FI-00-1

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-

238RIDE button?Repair open circuit betweenNO

Prop Pin Test Points applicable points. (See fig-ure 2-11.)

1 1151 27

2 1252 27

3 1353 27

4 2554 27

YES

237

Is a ground present on specified47405A1P1 plug pins?

Pins Test Points239

NO5

55Repair open circuit. (Seefigure 2-11.)

1756

1857

658

YES

240

Replace indicator light dim-mer No. 5 (1).

NOTE



61-10-002-88

TO 1C-130H-2-61FI-00-1


61-10-002-89

TO 1C-130H-2-61FI-00-1

FROM SHT 7 OR 9

241 6110008

NOTEPerform steps a and b only iftroubleshooting fault code6110008.

a. Move throttle (6) above 242FLIGHT IDLE/FLT IDLE gate.

Adjust or replace BETA indica-b. Hold engine condition lever (7) YES

tor switch as required in accor-in AIR START position until pro-

dance with TO 1C-130H-2-peller blades (2) are above flight

61JG-20-1, 61-20-04.idle.c. Open PROP SYNCHROPHASER and SYNCHROPHASER circuit breakers (5,4).d. Gain access to and disconnectplug P390 (1) at valve housingassembly.Does BETA indicator light (3) gooff?

NO

TO SHT 77

1 2

NOTE




61-10-002-90

TO 1C-130H-2-61FI-00-1


61-10-002-91

TO 1C-130H-2-61FI-00-1


61-10-002-92

TO 1C-130H-2-61FI-00-1


61-10-002-93

TO 1C-130H-2-61FI-00-1

254FROM SHT 77 Repair ground fault between

plug P1725A (2) pin and plug252 P398 (1) pin H. (See figure 2-NO

Is an outboard propeller being 7.) troubleshot?

Prop Pin2 423 43

YES

253

Gain access to and disconnectplug P130/P1139 (4) at outerwing break.Is a ground present on receptacle 255J235/J935 (3) pin?

Repair ground fault betweenNOplug P130/P1139, pin H andplug P1725A (2). (See figurePlug Test2-7.) Prop Pin Point

1 E27

4 H34

YES

256

Repair ground fault between re-ceptacle J235/J935, pin H andplug P398, pin H. (See figure2-7.)

NOTE

See figure 2-7 for:


61-10-002-94

TO 1C-130H-2-61FI-00-1


61-10-002-95

TO 1C-130H-2-61FI-00-1

259

Repair ground fault between pinFROM SHT 77H of plug P398 (1) and relatedpin of receptacle J339B (2).257(See figure 2-6.) NO


RcptProp Pin2 D3 F

YES


plug P130 (4) at outer wing break. Repair ground fault between pinIs a ground present on specified H of plug P398 (1) and relatedplug pin? pin of receptacle J235 (3).

(See figure 2-6.)NOPlug Test


1 E27

1 E4 H

4 H34

YES

261

Repair ground fault betweenspecified plug P130 pin and re-lated pin of receptacle J339B(2). (See figure 2-6.)

Plug RcptProp Pin Pin1 E B4 H H

NOTE

See figure 2-6 for:


61-10-002-96

TO 1C-130H-2-61FI-00-1


61-10-002-97

TO 1C-130H-2-61FI-00-1

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 95plug P392 (11) at propeller con-

trol.Is there continuity between pin Fof propeller control receptacle (10)and airplane ground?(Use an auxiliary pump motor at-taching bolt (9) as ground.)

50

NO

264265

Inspect wiring to propeller controlRepair loose or damaged wiringYES

receptacle for loose and brokenas required. (See figure 2-11connections.or 2-12.) Is any damage found?

NO

266

Replace propeller control in ac-cordance with TO 1C-130H-2-61JG-20-1, 61-20-01.

NOTE

1 Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024, except MC-130H airplanes.





61-10-002-98

TO 1C-130H-2-61FI-00-1


61-10-002-99

TO 1C-130H-2-61FI-00-1

FROM SHT 83

271267Rig engine coordinator-to-pro-

1 3 4 Is FEATHER VALVE AND NOpeller control assembly linkageNTS CHECK light (3) on?in accordance with TO 1C-

2 Is NTS light (6) on? 130H-2-61JG-20-1, 61-20-21.

YES

268

YESWith engine condition lever (5) inTO SHT 87FEATHER/FTR position, is auxiliary

pump motor (1) running?

NO

269

Momentarily hold engine condition NOlever in AIR START. TO SHT 89Does auxiliary pump motor run whilelever is held?

YES

270

a. Temporarily remove power fromairplane and gain access to propellerfeather override button (4). 272b. Move engine condition lever to NO

Replace propeller feather over-FEATHER/FTR.ride button. Is 28 VDC present on button terminal

4?

22

YES

273

Repair open circuit betweenbutton terminal 4 and terminalB3 of feather relay (2). (Seefigure 2-11 or 2-12.)

NOTE







61-10-002-100

TO 1C-130H-2-61FI-00-1


61-10-002-101

TO 1C-130H-2-61FI-00-1

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

275

a. Move engine condition lever toGROUND STOP/GND STOP.

277b. Check auxiliary pump motor for openphase by checking continuity between Replace auxiliary pump motor inYESmotor receptacle pins A to B and B to accordance with TO 1C-130H-2-C. 61JG-20-1, 61-20-09. Is there an open phase in motor?

15 16 AND

16 17

NO

276278NOTE

If troubleshooting came from sheet 13 Reseal pitchlock regulator assem-rather than sheet 85, proceed directly to bly in accordance with TO 1C-block 278. 130H-2-61JG-10-1, 61-10-11,

reseal low pitch stop assembly inNOa. Remove auxiliary pump motor in ac- accordance with TO 1C-130H-2-cordance with TO 1C-130H-2-61JG-20- 61JG-10-1, 61-10-12, and reseal1, 61-20-09. dome assembly in accordance withb. Inspect motor for sheared motor shaft TO 1C-130H-2-61JG-10-1, 61-10-(1). 13. Is auxiliary pump motor shaft sheared?

YES

279

Replace auxiliary pump motor inaccordance with TO 1C-130H-2-61JG-20-1, 61-20-09.

NOTE



61-10-002-102

TO 1C-130H-2-61FI-00-1


61-10-002-103

TO 1C-130H-2-61FI-00-1


61-10-002-104

TO 1C-130H-2-61FI-00-1


61-10-002-105

TO 1C-130H-2-61FI-00-1

FROM SHT 87 OR 89

286288Gain access to feather pump mo-

tor relay (4). Is 115 VAC present on relay ter- 289Is 115 VAC present on relay terminals A2, B2 and C2, or T3, T2,NO NO Repair power circuit to affectedminals A1, B1, and C1, or L3, L2, and T1 (depending upon terminal relay terminal. (See figure 2-11and L1 (depending upon terminal labeling)? or 2-12.) labeling)?

3 2 18 7 6

YESYES

290

Replace feather pump motor relay.

291287Repair open circuit between affected pinof receptacle J166 (1) and related pin ofplug P410 (3). (See figure 2-11 or 2-12.)Gain access to and disconnect plug P283

YES(2) at engine firewall.

Rcpt PlugIs 115 VAC present on plug pins A, B, andPin PinC?A AB B12 13 14C C

NO

TO SHT 93

NOTE




61-10-002-106

TO 1C-130H-2-61FI-00-1


61-10-002-107

TO 1C-130H-2-61FI-00-1

294FROM SHT 91

Repair open circuit between affected pin of plug P283 (1) and relatedterminal of feather pump motor relay (4). (See figure 2-11 or 2-12.)292

NOIs an outboard propeller be-

Plug Pin Relay Terming troubleshot? A C1/L1B B1/L2C A1/L3

YES

293295

Repair open circuit between affected plug P147/P1833 pin and relatedGain access to and discon- terminal of feather pump motor relay (4). (See figure 2-11 or 2-12.)nect plug P147/P1833 (2) NOat outer wing break. Plug Pin Relay TermIs 115 VAC present on plug G C1/L1pins G, H, and I? H B1/L2

I A1/L39 10 11

YES

296

Repair open circuit between affected pin of plug P283 (1) and relatedpin of receptacle J35/J955 (3). (See figure 2-11 or 2-12.)

Plug Pin Rcpt PinA GB HC I

NOTE




61-10-002-108

TO 1C-130H-2-61FI-00-1


61-10-002-109

TO 1C-130H-2-61FI-00-1

FROM SHT 83

297

a. Connect plug P392 (3) to pro-299peller control.

b. Gain access to and disconnect Repair open circuit between re-NOplug P396 (2) at engine firewall. ceptacle J241 pin F and plugIs a ground present on pin F of P392 pin F. (See figure 2-11 orreceptacle J241 (1)? 2-12.)

49

YES

298

Gain access to terminal boardTB107 (4) and disconnect speci-fied wire from terminal 1. 300Is a ground present on discon-

Repair open circuit betweennected wire?plug P396 pin F and terminal 1of related terminal boardTestTB107. (See figure 2-11 or 2-NO

Prop TB Wire No. Point12.)

1 TB107S 1K76E1848

Prop TB Prop TB1 TB107S 3 TB107U2 TB107T 2K76D18

482 TB107T 4 TB107V

3 TB107U 3K76D1848

4 TB107V 4K76D1848

YES

301

Reseal pitchlock regulator as-sembly in accordance with TO1C-130H-2-61JG-10-1, 61-10-11, reseal low pitch stop as-sembly in accordance with TO1C-130H-2-61JG-10-1, 61-10-12, and reseal dome assemblyin accordance with TO 1C-130H-2-61JG-10-1, 61-10-13. Iffault persists, replace propellercontrol in accordance with TO1C-130H-2-61JG-20-1, 61-20-01.

NOTE



61-10-002-110

TO 1C-130H-2-61FI-00-1


61-10-002-111

TO 1C-130H-2-61FI-00-1

FROM SHT 7

302 6110012303.1

a. Move engine condition lever (6) to FEATH-Reseal pitchlock regulator assembly in ac-ER/FTR.cordance with TO 1C-130H-2-61JG-10-1,b. After propeller blades (1) have reached61-10-11; reseal low pitch stop assembly inNO

feather position, check for internal leakage byaccordance with TO 1C-130H-2-61JG-10-1,holding propeller feather override button (4) in61-10-12; and reseal dome assembly in ac-while listening for a loud squeal from respec-cordance with TO 1C-130H-2-61JG-10-1,tive propeller assembly.61-10-13. Is a loud squeal heard from propeller?

YES

302.1

a. Open affected FEATHER PUMP MOTORPHASE A,B,C/ 4 FEATHER PUMP MOTORcircuit breakers (5).

NOb. Push affected propeller feather overrideTO SHT 99button (4) in.

c. Gain access to and disconnect plug P392(2) at propeller control.Does propeller feather override button popout?

YES

303304

Inspect wiring to propeller control receptacle YESRepair loose or damaged wiring as required.(3) for loose and broken connections.(See figure 2-11 or 2-12.)Is any damage found?

NO

305

Replace/repair propeller control in accor-dance with TO 1C-130H-2-61JG-20-1, 61-20-01 and 3HA2-7-3. (If desired, the re-placement/repair of the propeller controlmay be delayed to the next phase or isoch-ronal inspection to replace the pressure cut-out switch in the control, which is the causeof the fault.)

NOTE






61-10-002-112 Change 4

TO 1C-130H-2-61FI-00-1


61-10-002-113

TO 1C-130H-2-61FI-00-1

FROM SHT 97

306310

Adjust or replace pressurea. Open PROP SYNCHRO PHASER and SYNCHRO PHASER cir-

cutout backup switch as re-YEScuit breakers (6,7).

quired in accordance withb. Gain access to and disconnect plug P390 (9) at valve housing

TO 1C-130H-2-61JG-20-1,assembly.

61-20-03. Does propeller feather override button (5) pop out?

NO

311307Repair ground fault betweenYESplug P392 pin F and pin F ofGain access to and disconnect plug P396 (4) at engine firewall.receptacle J241 (1). (SeeDoes propeller feather override button pop out? figure 2-11 or 2-12.)

NO

312308Repair ground fault betweenYESplug P390 pin J and pin I ofGain access to and disconnect plug P398 (3) at engine firewall.receptacle J239 (2). (SeeDoes propeller feather override button pop out? figure 2-11 or 2-12.)

NO

309

a. Remove power from airplane. 313b. Open FEATHER & AIR START circuit breaker (8). NO

Replace propeller featherc. Gain access to terminals of propeller feather override button andoverride button. disconnect wire from button terminal 7.

Is a ground present on disconnected wire?23

YES

TO SHT 101

NOTE







61-10-002-114

TO 1C-130H-2-61FI-00-1


61-10-002-115

TO 1C-130H-2-61FI-00-1

FROM SHT 99

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

NO

315

Disconnect specified wire fromterminal board TB107 terminal 1.Is a ground present on discon-nected wire?

316Test

Repair ground fault betweenProp TB Wire No. Point NOterminal board TB107 terminal1 and pin I of plug P398 (1).1 TB107S 1K76E18

48(See figure 2-11 or 2-12.)

2 TB107T 2K76D1848

3 TB107U 3K76D1848

4 TB107V 4K76D1848

YES

317

Repair ground fault betweenterminal board TB107 terminal1 and pin F of plug P396 (2).(See figure 2-11 or 2-12.)

NOTE



61-10-002-116

TO 1C-130H-2-61FI-00-1


61-10-002-117

TO 1C-130H-2-61FI-00-1

320

Repair ground fault betweenFROM SHT 101 terminal 7 of propeller feather

override button (2) and terminal318 1 of related terminal boardNO

Is an outboard propeller being TB107 (1). (See figure 2-11 ortroubleshot? 2-12.)

Prop TB Prop TB1 TB107S 3 TB107U2 TB107T 4 TB107V

YES


plug P124/P1134 (3) at outer Repair ground fault between pinwing break. V of plug P124/P1134 and ter-YESIs a ground present on plug pin minal 7 of propeller featherV? override button (2). (See figure

2-11 or 2-12.) 47

NO

322

Repair ground fault between pinV of receptacle J209/J951 (4)and terminal 1 of related termi-nal board TB107 (1). (See fig-ure 2-11 or 2-12.)

Prop TB Prop TB1 TB107S 3 TB107U2 TB107T 4 TB107V

NOTE







61-10-002-118

TO 1C-130H-2-61FI-00-1


61-10-002-119

TO 1C-130H-2-61FI-00-1

FROM SHT 7

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 PHASE

a. If troubleshooting fault code A,B,C/ 2 FEATHER PUMP MOTOR circuit6110022 or 6110023, place breakers (6). 328FEATHER VALVE AND NTS c. Move ENGINE CONDITION lever (1) toYES YES Replace FEATHERCHECK switch (4) to VALVE. FEATHER. VALVE AND NTSb. Press to test affected d. Temporarily remove power from airplane CHECK light assembly. FEATHER VALVE AND NTS and gain access to terminals of FEATHERCHECK light (2 or 3). VALVE AND NTS CHECK light.Does light press to test? Is a ground present on light terminal 2?

5 ,

7 ,

9 OR

11NO

NO

TO SHT 109

324 YESTO SHT 107Is propeller No. 1 being troubleshot?

NO

327325 Temporarily remove power from airplane 329

Press to test No. 1 FEATH- and gain access to terminals of affectedYES YES Replace FEATHER VALVEER VALVE AND NTS FEATHER VALVE AND NTS CHECK light. AND NTS CHECK light as-CHECK light (2). Is 28 VDC present on light terminal 1? sembly. Does light press to test?6

, 8

, 10

OR 12

NONO

TO SHT 107

TO SHT 121

NOTE





61-10-002-120 Change 7

TO 1C-130H-2-61FI-00-1


61-10-002-121

TO 1C-130H-2-61FI-00-1

FROM SHT 105

330

Temporarily remove power fromairplane and gain access to termi-

333nals of ENG NO. 1 FEATHERVALVE AND NTS CHECK light Replace ENG NO. 1 FEATHERYES(1). VALVE AND NTS CHECK lightIs 28 VDC present on light termi- assembly. nal 1?

6

NO

331

Temporarily remove power fromairplane and gain access to termi- 334nals of FEATHER VALVE AND

Repair power circuit to switchNONTS CHECK switch (2).terminal 5. (See figure 2-8 orIs 28 VDC present on switch ter-2-10.) minal 5?

1

YES

332

With FEATHER VALVE AND NTS335CHECK switch in VALVE position,

NOis 28 VDC present on switch ter- Replace FEATHER VALVEminal 4? AND NTS CHECK switch.

2

YES

336

Repair open circuit betweenFEATHER VALVE AND NTSCHECK switch terminal 4 andterminal 1 of ENG NO. 1FEATHER VALVE AND NTSCHECK light. (See figure 2-8or 2-10.)

NOTE





61-10-002-122

TO 1C-130H-2-61FI-00-1


61-10-002-123

TO 1C-130H-2-61FI-00-1

FROM SHT 9 OR 105

337

a. Open PROP SYNCHRO PHASER andSYNCHRO PHASER circuit breakers (4,3). 342b. Gain access to and disconnect plug

Adjust or replace NTS340P390 (6) at valve housing assembly. NO YES switch as required inIs there continuity between pins F and K of Is fault code 6110023 being accordance with TOvalve housing assembly receptacle (5)? troubleshot? 1C-130H-2-61JG-20-1,61-20-05.41 43

, 13 15

,

66 68 OR

38 40

YES

NO

TO SHT 119

341338 343Gain access to and disconnect plugIs a ground present on plug P390 Repair open circuit betweenNO YESP398 (2) at engine firewall.pin K? plug P390 pin K and pin VIs a ground present on plug pin V? of receptacle J239 (1). (See

43 ,

15 ,

68 OR

40figure 2-8, 2-9, or 2-10.)46

, 18

, 65

OR 37

YESNO

344

Repair ground circuit. (See fig-ure 2-8, 2-9, or 2-10.)

339

a. Connect plug P390 to valve housing assembly.b. Gain access to and disconnect plug P398 (2) at 345engine firewall.

Repair open circuit between re-Is there continuity between pins F and pin V of re- NOceptacle J239 pin F and plugceptacle J239 (1)?P390 pin F. (See figure 2-8, 2-9, or 2-10.)44 46

, 16 18

,

63 65 OR

35 37

YES

TO SHT 111

NOTE





5. See figure 2-8, 2-9, or 2-10 for:


61-10-002-124

TO 1C-130H-2-61FI-00-1


61-10-002-125

TO 1C-130H-2-61FI-00-1


61-10-002-126

TO 1C-130H-2-61FI-00-1


61-10-002-127

TO 1C-130H-2-61FI-00-1

360

a. Remove electrical power fromairplane.b. Gain access to and disconnectFROM SHT 105 AND 111plug P1725A (2) from systemscaution/advisory panel.357

NO YESIs a ground present on the appli-Is an outboard propeller being TO SHT 115cable plug pin?troubleshot?

Prop Plug Pin Test Point

2 5479

3 5580

YES

NO361

Repair open circuit between plugP1725A and plug P398 (1), pin F.(See figure 2-9.)

358

NOTEPut ohmmeter negative lead on receptacle pin P.

362

Gain access to and disconnect plug P18/P1835 Repair open circuit between recep-NO(4) at outer wing break. tacle J233/J956 pin N and plugIs there continuity between pins N and P of re- P398 pin F. (See figure 2-9.) ceptacle J233/J956 (3)?

47 48 OR

33 34

YES

359

a. Remove electrical power from airplane.b. Gain access to and disconnect plug P1725A(2) from systems caution/advisory panel. 363Is a ground present on applicable plug pin?

Repair open circuit between plugNOP1725A and plug P18/P1835 pinProp Plug Pin Test PointN. (See figure 2-9.)

1 5378

4 5681

YES

TO SHT 115

NOTE

See figure 2-9 for:


61-10-002-128 Change 7

TO 1C-130H-2-61FI-00-1


61-10-002-129

TO 1C-130H-2-61FI-00-1

FROM SHT 113

364

Momentarily hold the MACAWS 365LAMP TEST switch (1) in the test NO

Replace the applicable MA-position.CAWS bulb. Does the applicable light come

on?

YES

366

Fault is in MACAWS. Refer toTO 1C-130H-2-33FI-00-1-2 fortroubleshooting.


61-10-002-130

TO 1C-130H-2-61FI-00-1


61-10-002-131

TO 1C-130H-2-61FI-00-1

FROM SHT 111

367

Gain access to and disconnect plug47404A2P1 from indicator light dimmer No.4 (2).Is a ground present on specified pins?

369

Light No. Plug Pin Test Point Repair open circuit between relay ter-NOminal A2 and related pin of plug

1 176

47404A2P1 of indicator light dimmerNo. 4 (2). (See figure 2-10.

2 1675

3 1574

4 373

YES

368

a. Temporarily remove power from airplaneand gain access to terminals of specifiedFEATHER VALVE AND NTS CHECK light(1).b. Disconnect wire from terminal 2.

370Is there continuity between terminal 2 andrelated pin of plug 47404A2P1? Repair open circuit between FEATH-

ER VALVE AND NTS CHECK lightYESLight No. Plug Pin Test Point (1) and related pin of plug 47404A2P1

of indicator light dimmer No. 4 (2).1 10

69(See figure 2-10.)

2 2470

3 2371

4 2272

NO

371

Replace indicator light dimmer No. 4(2).

NOTE



61-10-002-132

TO 1C-130H-2-61FI-00-1


61-10-002-133

TO 1C-130H-2-61FI-00-1

FROM SHT 21 OR 109

372 6110021376

Gain access to and check NTS linkage for correct gap ofAdjust NTS linkage in accor-NO

0.011 to 0.020 inch in accordance with TO 1C-130H-2-61JG-dance with TO 1C-130H-2-20-1, 61-20-22.61JG-20-1, 61-20-22.Is adjustment correct?

YES

373

a. Rotate propeller control (2) clockwise as viewed from the 377rear and hold firmly against prop torque retainer assembly (6).

As required, replace dam-b. Check clearance between torque retainer lug (3) and prop YESaged components in accor-torque retainer assembly for a maximum gap of 0.050 inch.dance with TO 1C-130H-2-c. Release propeller control.61JG-20-1, 61-20-11.d. Also inspect components for looseness or damage.

Are any discrepancies found?

NO

374

a. If necessary, connect plug P390 (4) to valve housing as- 378sembly (5).

Adjust or replace NTSb. Gain access to and manually actuate NTS switch (1). NOswitch as required in accor-

1 Does FEATHER VALVE AND NTS CHECK light (7) come dance with TO 1C-130H-2-on while switch is actuated? 61JG-20-1, 61-20-05.

2 Does NTS light (8) come on while switch is actuated?

YES

375 379

Check engine coordinator-to-propeller con- Rig engine coordinator-to-propellerNOtrol assembly rigging in accordance with control assembly linkage in accor-TO 1C-130H-2-61JG-20-1, 61-20-21. dance with TO 1C-130H-2-61JG-20-1,Is rigging correct? 61-20-21.

YES

380

Fault is in engine. Go to TO 1C-130H-2-70FI-00-1-2, figure 3-3 block477, and troubleshoot NTS plungeractuation.

NOTE






61-10-002-134

TO 1C-130H-2-61FI-00-1


61-10-002-135

TO 1C-130H-2-61FI-00-1

385FROM SHT 105

Repair open circuit between terminal 1 of381 ENG NO. 1 FEATHER VALVE AND NTSYES

Is propeller No. 2 being troubleshot? CHECK light (1) and terminal 1 of ENG NO.2 FEATHER VALVE AND NTS CHECK light(2). (See figure 2-8.) NO

386382 Repair open circuit between terminal 1 of

Press to test ENG NO. 2 FEATHER ENG NO. 1 FEATHER VALVE AND NTSNOVALVE AND NTS CHECK light (2). CHECK light (1) and terminal 1 of ENG NO.Does light press to test? 2 FEATHER VALVE AND NTS CHECK light

(2). (See figure 2-8.)YES

387

Repair open circuit between terminal 1 of383 ENG NO. 2 FEATHER VALVE AND NTSYES

Is propeller No. 3 being troubleshot? CHECK light (2) and terminal 1 of ENG NO.3 FEATHER VALVE AND NTS CHECK light(3). (See figure 2-8.) NO

388384 Repair open circuit between terminal 1 of

Press to test ENG NO. 3 FEATHER ENG NO. 2 FEATHER VALVE AND NTSNOVALVE AND NTS CHECK light (3). CHECK light (2) and terminal 1 of ENG NO.Does light press to test. 3 FEATHER VALVE AND NTS CHECK light

(3). (See figure 2-8.) YES

389

Repair open circuit between terminal 1 ofENG NO. 3 FEATHER VALVE AND NTSCHECK light (3) and terminal 1 of ENG NO.4 FEATHER VALVE AND NTS CHECK light(4). (See figure 2-8.)

NOTE




61-10-002-136

TO 1C-130H-2-61FI-00-1


61-10-002-137

TO 1C-130H-2-61FI-00-1

FROM SHT 11

390

Gain access to terminals of NTS 392check relay (1).

Repair ground circuit to relayYESIs 28 VDC present on relay termi-

terminal A1. (See figure 2-8 ornal A1?2-10.)

54 ,

24 ,

61 OR

31

NO

391

Is 28 VDC present on relay termi- 393YESnal A2?Replace NTS check relay.

52 ,

22 ,

59 OR

29

NO

394

Repair open circuit between ter-minals 4 and 6 of FEATHERVALVE AND NTS CHECKswitch (2). (See figure 2-8 or2-10.)

NOTE





61-10-002-138

TO 1C-130H-2-61FI-00-1


61-10-002-139

TO 1C-130H-2-61FI-00-1

FROM SHT 11

395

Gain access to terminals of NTS398check relay (1). 401

Is 28 VDC present between relay Is 28 VDC present on relay termi-YES YES Repair ground circuit to relayterminals X2 and X1? nal A1? terminal A1. (See figure 2-8 or2-10.) 49 50

, 19 20

, 54 ,

24 ,

61 OR

31

56 57 OR

26 27

NO

NO

402

Replace NTS check relay.

399396

Open NTS CHECK circuit breaker 403Is 28 VDC present on relay termi- (2).YES NO Repair ground circuit to relaynal X2? Is a ground present on NTS terminal B1. (See figure 2-8 or

check relay terminal B1? 2-10.) 49 ,

19 ,

56 OR

26

55 ,

25 ,

62 OR

32

NOYES

TO SHT 129

400

Gain access to terminals of en-397 gine No. 1 NTS check relay (1).NO YES

Is No. 1 propeller being TO SHT 139Is 28 VDC present on relay termi-troubleshot? nal X2?

49YES

NO

TO SHT 127

TO SHT 127

NOTE





61-10-002-140

TO 1C-130H-2-61FI-00-1


61-10-002-141

TO 1C-130H-2-61FI-00-1

FROM SHT 125

404406

Gain access to terminals ofRepair open circuit betweenFEATHER VALVE AND NTSFEATHER VALVE AND NTSCHECK switch (2). YESCHECK switch terminal 3 andIs 28 VDC present on switch ter-terminal X2 of engine No. 1minal 3?NTS check relay (1). (See fig-ure 2-8 or 2-10.) 4

NO

405

Is 28 VDC present on FEATHER 407VALVE AND NTS CHECK switch YES

Replace FEATHER VALVEterminal 2?AND NTS CHECK switch.

3

NO

408

Repair open circuit betweenswitch terminals 2 and 5. (Seefigure 2-8 or 2-10.)

NOTE





61-10-002-142

TO 1C-130H-2-61FI-00-1


61-10-002-143

TO 1C-130H-2-61FI-00-1

FROM SHT 125

409

NOTEPut meter negative lead on relay terminalB2.

a. Open FEATHER & AIR START circuit 412YESbreaker (4).

Replace NTS check relay. b. Move ENGINE CONDITION lever (6) toFEATHER.Is a ground present on terminal B2 of NTScheck relay (1)?

51 ,

21 ,

58 OR

28

NO

410

NOTE413Put meter negative lead on relay terminal

X1. Repair open circuit between re-YESlay terminals X1 and B2. (See

Is a ground present on relay terminal X1? figure 2-8 or 2-10.)

50 ,

20 ,

57 OR

27

NO

411

NOTEPut meter negative lead on receptacle pinE.

a. Open PROP SYNCHRO PHASER and 414SYNCHRO PHASER circuit breakers (7,5).

Replace valve housing assem-NOb. Gain access to and disconnect plugbly in accordance with TO 1C-P390 (2) at valve housing assembly.130H-2-61JG-20-1, 61-20-02. Is there continuity between pins E and F of

valve housing receptacle (3)?

42 41 ,

14 13 ,

67 66 OR

39 38

YES

TO SHT 137

NOTE





61-10-002-144

TO 1C-130H-2-61FI-00-1


61-10-002-145

TO 1C-130H-2-61FI-00-1

FROM SHT 9

415

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?

419Plug TestProp Pin Point Fault is in MACAWS. ReferNO

to TO 1C-130H-2-33FI-00-1-1 53

782 for troubleshooting.

2 5479

3 5580

4 5681

YES

416 YESTO SHT 133Is an outboard propeller being troubleshot?

NO

417 420

a. Temporarily remove power from airplane. Repair open circuit betweenb. Connect plug P1725A to systems caution/advi- plug P398, pin F and plugsory panel. P1725A at applicable pin.NOc. Gain access to and disconnect plug P398 (2) (See figure 2-9.)at engine firewall.Is 28 VDC present at pin F? Prop Plug pin

2 5416 63

3 55

YES

418

a. Temporarily remove power from airplane.b. Connect plug P398 at engine firewall. 421c. Gain access to and disconnect plug P390 NO

Repair open circuit between plug P390 pin F(3) at valve housing assembly.and receptacle J239 (1). (See figure 2-9.) Is 28 VDC present at pin F?

13 OR

66

YES

TO SHT 135

NOTE

See figure 2-9 for:


61-10-002-146

TO 1C-130H-2-61FI-00-1


61-10-002-147

TO 1C-130H-2-61FI-00-1

FROM SHT 131

422 425

a. Temporarily remove power from airplane. Repair open circuit between plugb. Connect plug P1725A (4) to systems cau- P18/P1835, pin N and plugtion/advisory panel. P1725A at applicable pin. (SeeNOc. Gain access to and disconnect plug P18/ figure 2-9.)P1835 (6) at outer wing break.Is 28 VDC present at pin N? Prop Plug pin

1 5333

OR 47

4 56

YES

423

a. Temporarily remove power from airplane.426b. Connect plug P18/P1835.

c. Gain access to and disconnect plug P398 Repair open circuit between recep-NO(2) at engine firewall. tacle J233/J956 (5) pin N, and plugIs 28 VDC present at pin F? P398 (2) pin F. (See figure 2-9.)

35 OR

44

YES

424

a. Temporarily remove power from airplane.427b. Connect plug P398.

c. Gain access to and disconnect plug P390 Repair open circuit between recep-NO(3) at valve housing assembly. tacle J239 (1) pin F, and plugIs 28 VDC present at pin F? P390 pin F. (See figure 2-9.)

38 OR

41

YES

TO SHT 135

NOTE

See figure 2-9 for:


61-10-002-148

TO 1C-130H-2-61FI-00-1


61-10-002-149

TO 1C-130H-2-61FI-00-1

FROM SHT 131 OR 133

428

Gain access to valve housing re-ceptacle (4). 430Is there continuity between pins F

Replace valve housing assem-NOand K?bly in accordance with TO 1C-130H-2-61JG-20-1, 61-20-02. 13 15

, 38 40

,

41 43, OR

66 68

YES

429

Gain access to and disconnect 431plug P398 (2) at engine firewall.

Repair open circuit betweenNOIs a ground present at plug P398plug P398 pin V and ground.pin V?(See figure 2-9.)

18,

37,

46 OR

65

YES

432

Repair open circuit between re-ceptacle J239 (1) pin V andplug P390 (3) pin K. (See fig-ure 2-9.)

NOTE

See figure 2-9 for:


61-10-002-150

TO 1C-130H-2-61FI-00-1


61-10-002-151

TO 1C-130H-2-61FI-00-1

FROM SHT 129

433

NOTEPut meter negative lead on recep-tacle pin E.

436a. Connect plug P390 (3) to valvehousing assembly (4). Repair open circuit between re-NOb. Gain access to and disconnect ceptacle J239 pin E and plugplug P398 (2) at engine firewall. P390 pin E. (See figure 2-8 orIs there continuity between pins E 2-10.) and F of receptacle J239 (1)?

45 44 ,

17 16 ,

64 63 OR

36 35

YES

437434 Repair open circuit betweenNO

Is an outboard propeller being plug P398 pin E and terminaltroubleshot? X1 of NTS check relay (5).

(See figure 2-8 or 2-10.) YES

435

NOTEPut meter negative lead on recep-tacle pin P.

438

a. Connect plug P398 at engine Repair open circuit between re-NOfirewall. ceptacle J233 pin P and plugb. Gain access to and disconnect P398 pin E. (See figure 2-8 orplug P18 (6) at outer wing break. 2-10.) Is there continuity between pins Nand P of receptacle J233 (7)?

47 48 OR

33 34

YES

439

Repair open circuit betweenplug P18 pin P and terminal X1of NTS check relay (5). (Seefigure 2-8 or 2-10.)

NOTE



61-10-002-152

TO 1C-130H-2-61FI-00-1


61-10-002-153

TO 1C-130H-2-61FI-00-1

444FROM SHT 125

Repair open circuit between ter-440 minal X2 of engine No. 1 NTSYES

Is No. 2 propeller being check relay (2) and terminal X2troubleshot? of engine No. 2 NTS check re-

lay (3). (See figure 2-8 or 2-10.) NO

441 445

Gain access to terminals of en- Repair open circuit between ter-gine No. 2 NTS check relay (3). minal X2 of engine No. 1 NTSNOIs 28 VDC present on relay termi- check relay (2) and terminal X2nal X2? of engine No. 2 NTS check re-

lay (3). (See figure 2-8 or 2-19

10.)

YES

446

Repair open circuit between ter-442 minal X2 of engine No. 2 NTSYES

Is No. 3 propeller being check relay (3) and terminal X2troubleshot? of engine No. 3 NTS check re-

lay (1). (See figure 2-8 or 2-10.) NO

443 447

Gain access to terminals of en- Repair open circuit between ter-gine No. 3 NTS check relay (1). minal X2 of engine No. 2 NTSNOIs 28 VDC present on relay termi- check relay (3) and terminal X2nal X2? of engine No. 3 NTS check re-

lay (1). (See figure 2-8 or 2-56

10.)

YES

448

Repair open circuit between ter-minal X2 of engine No. 3 NTScheck relay (1) and terminal X2of engine No. 4 NTS check re-lay (4). (See figure 2-8 or 2-10.)

NOTE



61-10-002-154

TO 1C-130H-2-61FI-00-1


61-10-002-155

TO 1C-130H-2-61FI-00-1

FROM SHT 9 OR 11

449

Momentarily hold engine condition NOlever (3) in AIR START. TO SHT 143Does auxiliary pump motor (2) runwhile lever is held?

YES

450452Inspect NTS linkage (1) for servicea-

bility and check for correct gap of Adjust NTS linkage in accordanceNO0.011 to 0.020 inch in accordance with TO 1C-130H-2-61JG-20-1, 61-20-with TO 1C-130H-2-61JG-20-1, 61- 22, or replace components as re-20-22. quired. Is NTS linkage satisfactory?

YES

451453

Check engine coordinator-to-propellerRig engine coordinator-to-propellercontrol assembly rigging in accor- NOcontrol assembly linkage in accor-dance with TO 1C-130H-2-61JG-20-dance with TO 1C-130H-2-61JG-20-1,1, 61-20-21.61-20-21.Is rigging correct?

YES

454

Reseal pitchlock regulator assembly inaccordance with TO 1C-130H-2-61JG-10-1, 61-10-11; reseal low pitch stopassembly in accordance with TO 1C-130H-2-61JG-10-1, 61-10-12; andreseal dome assembly in accordancewith TO 1C-130H-2-61JG-10-1, 61-10-13. If fault persists, replace feathersolenoid valve in accordance with TO1C-130H-2-61JG-20-1, 61-20-06. Iffault still persists, replace valve hous-ing assembly in accordance with TO1C-130H-2-61JG-20-1, 61-20-02.


61-10-002-156

TO 1C-130H-2-61FI-00-1


61-10-002-157

TO 1C-130H-2-61FI-00-1

FROM SHT 141

455

a. Gain access to terminals offeather relay (2).b. Momentarily hold ENGINE

457CONDITION lever (1) in AIR YESSTART. Replace feather relay.Is 28 VDC present on relay termi-nal B2 while lever is held?

32

NO

456

a. Gain access to pedestal termi-nal boards.b. Momentarily hold ENGINE 458CONDITION lever in AIR START.

Repair open circuit betweenIs 28 VDC present on specifiedfeather relay terminal B2 andterminal while lever is held?related terminal. (See figure 2-11.)Test YES

Prop TB-Term PointProp TB-Term1 TB126A-311 TB126A (3) -31

342 TB146A-2083 TB146A-2092 TB146A (4) -208

344 TB146A-212

3 TB146A (4) -20934

4 TB146A (4) -21234

NO

TO SHT 145

NOTE



61-10-002-158

TO 1C-130H-2-61FI-00-1


61-10-002-159

TO 1C-130H-2-61FI-00-1

FROM SHT 143

459

Open FEATHER & AIR START circuit breaker(4).Is there continuity between terminal 1C of EN-GINE CONDITION lever air start switch (1)and specified terminal?

461Test NOProp Sw TB-Term Points Repair open circuit. (See figure

2-11.)1 S23S TB146A (3) -193

37 38

2 S23T TB146A (3) -19437 38

3 S23U TB146A (3) -19537 38

4 S23V TB146A (3) -19637 38

YES

460

Is there continuity between air start switch ter- 462minal 1NO and specified terminal?

Adjust or replace air start switchas required in accordance withTestTO 1C-130H-2-76JG-00-1, 76-Prop Sw TB-Term Points10-39.YES

1 S23S TB126A (2) -3136 34

Prop Sw1 S23S2 S23T TB146A (3) -208

36 342 S23T3 S23U3 S23U TB146A (3) -209

36 344 S23V

4 S23V TB146A (3) -21236 34

NO

463


NOTE





61-10-002-160

TO 1C-130H-2-61FI-00-1


61-10-002-161

TO 1C-130H-2-61FI-00-1

FROM SHT 13

464466Check NTS linkage (1) for correct

gap of 0.011 to 0.020 inch in ac- Adjust NTS linkage in accor-NOcordance with TO 1C-130H-2- dance with TO 1C-130H-2-61JG-20-1, 61-20-22. 61JG-20-1, 61-20-22.Is adjustment correct?

YES

467465Repair or replace linkage as re-Inspect NTS linkage through valvequired or replace valve housingYES

housing assembly cover (2) forassembly cover as required inevidence of binding.accordance with TO 1C-130H-Is any binding observed?2-61JG-20-1, 61-20-02.

NO

468



61-10-002-162

TO 1C-130H-2-61FI-00-1


61-10-002-163

TO 1C-130H-2-61FI-00-1

FROM SHT 13

469YES

Did propeller feather override but- TO SHT 153ton (3) pull in?

NO

470

Temporarily remove power from472airplane and gain access to termi-

nals of propeller feather override Repair open circuit betweenYESbutton. button terminal 1 and terminalIs 28 VDC present on button ter- A2 of feather relay (2). (Seeminal 1? figure 2-11 or 2-12.)

26

NO

471

Gain access to terminal board473TB14A (1).

Is 28 VDC present on specified Repair open circuit betweenterminal? propeller feather override button

terminal 1 and related terminalTest board TB14A terminal. (See fig-

Prop TB-Term Point ure 2-11 or 2-12.)YES

1 4344

Prop TB-Term1 43

2 4444

2 443 45

3 4544

4 46

4 4644

NO

TO SHT 151

NOTE







61-10-002-164

TO 1C-130H-2-61FI-00-1


61-10-002-165

TO 1C-130H-2-61FI-00-1

477FROM SHT 149

Repair open circuit between switch termi-474 nal H1 and related terminal of terminal

Temporarily remove power from airplane board TB14A (4). (See figure 2-11 or 2-and gain access to terminals of fire emer- 12.)YESgency handle switch (3).Is 28 VDC present on switch terminal H1? Prop TB-Term

1 4343

2 443 454 46NO

475478Is 28 VDC present on switch terminal G1? YESReplace fire emergency handle switch.

42

NO

476

Gain access to and disconnect plug P350/ 479P1830 (1) at overhead panel disconnect.

Repair open circuit between fire emer-Is 28 VDC present on specified pin of re-gency handle switch terminal G1 and re-ceptacle J217/J952 (2)?lated plug P350/P1830 pin. (See figure2-11 or 2-12.)Rcpt Test YES

Prop Pin PointPlug

Prop Pin1 S41

1 S2 T2 T

413 U4 V3 U

41

4 V41

NO

480

Repair power circuit. (See figure 2-11 or2-12.)

NOTE



61-10-002-166

TO 1C-130H-2-61FI-00-1


61-10-002-167

TO 1C-130H-2-61FI-00-1

FROM SHT 149

481

485Gain access to and disconnectplug P391 (3) at feather solenoid Replace feather solenoid valveYESvalve. in accordance with TO 1C-Is 28 VDC present between plug 130H-2-61JG-20-1, 61-20-06. pins A and B?

19 18

NO

484

a. Open EMER FEATHER circuit486482 breaker (4).Repair open circuit betweenb. Gain access to and disconnectYES YESIs 28 VDC present on plug pin A?plug P391 pin B and pin B ofplug P399 (2) at engine firewall.receptacle J245 (1). (See fig-Is a ground present on plug pin19ure 2-11 or 2-12.) B?

20NO

NO

487

Repair ground circuit. (See fig-ure 2-11 or 2-12.)

483

488

Repair open circuit betweenGain access to and disconnect YESplug P391 pin A and pin A ofplug P399 (2) at engine firewall.receptacle J245 (1). (See fig-Is 28 VDC present on plug pin A?ure 2-11 or 2-12.)

21

NO

TO SHT 155

NOTE





61-10-002-168

TO 1C-130H-2-61FI-00-1


61-10-002-169

TO 1C-130H-2-61FI-00-1

FROM SHT 153 491

Repair open circuit between pin489A of plug P399 (1) and terminalNO

Is airplane being troubleshot a C-14 of propeller feather override130B model through AF59-5957?button (3). (See figure 2-11 or2-12.)YES

490

Gain access to terminal boardTB115L (2). 492Is 28 VDC present on specified ter-

Repair open circuit between pinminal?A of plug P399 (1) and relatedterminal board TB115L terminal.(See figure 2-11.)Test

YESProp TB-Term Point

Prop TB-Term1 145

OR 46

1 12 22 2

45 OR

463 34 43 3

45 OR

46

4 445

OR 46

NO

493

Repair open circuit between ter-minal 14 of PROPELLERFEATHER OVERRIDE button(3) and related terminal boardTB115L terminal. (See figure2-11.)

Prop TB-Term1 12 23 34 4

NOTE







61-10-002-170

TO 1C-130H-2-61FI-00-1


61-10-002-171

TO 1C-130H-2-61FI-00-1


61-10-002-172

TO 1C-130H-2-61FI-00-1


61-10-002-173

TO 1C-130H-2-61FI-00-1


61-10-002-174 Change 5

TO 1C-130H-2-61FI-00-1


61-10-002-175

TO 1C-130H-2-61FI-00-1

FROM SHT 19

511 6110006

a. Shut down engines (1) in ac-515cordance with TO 1C-130H-2-

71JG-00-1, 71-00-10; or TO 1C- Rig throttle control system inNO130(A)H-2-71JG-00-1, 71-00-10. accordance with TO 1C-130H-b. Check throttle control system 2-76JG-00-1, 76-10-30, 76-10-rigging in accordance with TO 1C- 33, 76-10-34, and 76-10-35.130H-2-76JG-00-1, 76-10-01.Is rigging correct?

YES

512516

Check engine coordinator-to-pro-Rig engine coordinator-to-pro-peller control assembly rigging in NOpeller control assembly linkageaccordance with TO 1C-130H-2-in accordance with TO 1C-61JG-20-1, 61-20-21.130H-2-61JG-20-1, 61-20-21. Is rigging correct?

YES

513517

Perform backup valve blade angleAdjust backup valve blade an-indicator check and reverse stopgle and/or reverse stop as re-NO

check in accordance with TO 1C-quired in accordance with TO130H-2-61JG-10-1, 61-10-011C-130H-2-61JG-10-1, 61-10-(subtasks 1-1-3 and 1-1-5).01.Are checks satisfactory?

YES

514518

Perform torquemeter calibration inFault is in engine or torqueme-accordance with TO 1C-130H-2- NOter system. Go to TO 1C-77JG-00-1, 77-10-04; or TO 1C-130H-2-70FI-00-1-2 and contin-130(A)H-2-71JG-00-1, 71-00-10.ue troubleshooting.Is calibration satisfactory?

YES

519



61-10-002-176

TO 1C-130H-2-61FI-00-1


61-10-002-177

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 inCHECK during pitchlock check?

NO

525

Fault is in synchrophaser sys-523tem. Shut down engines in ac-

521 Perform propeller synchrophaser cordance with TO 1C-130H-2-check in accordance with TO 1C-NO NODid RPM increase at all when fuel 71JG-00-1, 71-00-10; TO 1C-130H-2-61JG-10-1, 61-10-02governing switch was held in 130(A)H-2-71JG-00-1, 71-00-(subtask 1-2-9).CHECK during pitchlock check? 10; or TO 1C-130(M)H-2-71JG-Is synchrophaser check satisfac- 00-1, 71-00-10; then go to Sec-tory? tion III and continue trouble-

shooting. YES

YES

524 526

a. Perform synchrophaser index in Fault is in synchrophaser sys-accordance with TO 1C-130H-2- tem. Shut down engines in ac-61JG-10-1, 61-10-02 (subtask 1- cordance with TO 1C-130H-2-

NO2-6). 71JG-00-1, 71-00-10; TO 1C-b. Perform pitchlock check of af- 130(A)H-2-71JG-00-1, 71-00-fected propeller in accordance 10; or TO 1C-130(M)H-2-71JG-with TO 1C-130H-2-61JG-10-1, 00-1, 71-00-10; then go to Sec-61-10-02 (subtask 1-2-10). tion III and continue trouble-Was a pitchlock obtained? shooting.

YES

527

Synchrophaser index corrected malfunc-tion. Shut down engines in accordancewith 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-130(M)H-2-71JG-00-1, 71-00-10.

522528

Was RPM increase within limitsAdjust fuel control governor in accor-NO

when fuel governing switch wasdance with TO 1C-130H-2-73JG-00-1,held in CHECK during pitchlock73-20-20. check?

YES

TO SHT 165

NOTE



61-10-002-178

TO 1C-130H-2-61FI-00-1


61-10-002-179

TO 1C-130H-2-61FI-00-1

FROM SHT 163

529530Remove dome assembly in accor-

dance with TO 1C-130H-2-61JG- Remove and reinstall pitchlockNO10-1, 61-10-11. regulator assembly correctly inIs pin on ratchet ring (1) aligned accordance with TO 1C-130H-with etch mark on lip of No. 2 2-61JG-10-1, 61-10-11. blade barrel bore (2)?

YES

531

Reseal or replace pitchlock reg-ulator assembly in accordancewith TO 1C-130H-61JG-10-1,61-10-11, as required. If faultpersists, replace propeller as-sembly in accordance with TO1C-130H-2-61JG-10-1, 61-10-11.


61-10-002-180

TO 1C-130H-2-61FI-00-1


61-10-002-181

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- 5342-71JG-00-1, 71-00-10; or TO 1C-

Reseal pitchlock regulator as-130(M)H-2-71JG-00-1, 71-00-10.sembly in accordance with TOb. Move engine condition lever (2)1C-130H-2-61JG-10-1, 61-10-to FEATHER/FTR.11; reseal low pitch stop as-NO

c. After propeller blades (1) havesembly in accordance with TOreached feather position, check1C-130H-2-61JG-10-1, 61-10-for internal leakage by holding12; and reseal dome assemblypropeller feather override buttonin accordance with TO 1C-(3) in while listening for a loud130H-2-61JG-10-1, 61-10-13. squeal from respective propeller

assembly.Is a loud squeal heard from pro-peller?

YES

533535

Check engine coordinator-to-pro-Rig engine coordinator-to-pro-peller control assembly rigging in NOpeller control assembly linkageaccordance with TO 1C-130H-2-in accordance with TO 1C-61JG-20-1, 61-20-21.130H-2-61JG-20-1, 61-20-21. Is rigging correct?

YES

536

Replace low pitch stop assem-bly in accordance with TO 1C-130H-2-61JG-10-1, 61-10-12.

NOTE






61-10-002-182

TO 1C-130H-2-61FI-00-1


61-10-002-183

TO 1C-130H-2-61FI-00-1

FROM SHT 21

537 6110001543

Perform inspection for loose propellerReplace propeller assembly in ac-YES

blades in accordance with TO 1C-cordance with TO 1C-130H-2-130H-2-61JG-10-1, 61-10-22.61JG-10-1, 61-10-11. Are any loose blades found?

NO

538544

Perform inspection of propeller bladeReplace propeller assembly in ac-NO

tracking in accordance with TO 1C-cordance with TO 1C-130H-2-130H-2-61JG-10-1, 61-10-23.61JG-10-1, 61-10-11. Is tracking satisfactory?

YES

539 545

Inspect propeller afterbody (2), prop Repair or replace loose or dam-torque retainer assembly (4), and aged propeller components as re-YESfront spinner (1) for loose or dam- quired in accordance with TO 1C-aged components. 130H-2-61JG-10-1 or TO 1C-Are any discrepancies found? 130H-2-61JG-20-1.

NO

546540Replace reduction gear in accor-542Check propeller hub nut (5) for cor- NO NO dance with TO 1C-130H-2-71JG-rect torque in accordance with TO Was torque at least 1500 00-2, 71-90-20. Annotate forms1C-130H-2-61JG-10-1, 61-10-11. inch-pounds? that propeller shaft (3) is to be re-Is torque correct?moved from service.

YESYES

547

Torque propeller hub nut in accor-dance with TO 1C-130H-2-61JG-10-1, 61-10-11.

541548

Check condition of engine rearReplace engine mounts in accor-YES

mounts in accordance with TO 1C-dance with TO 1C-130H-2-71JG-130H-2-71JG-00-2, 71-20-10.00-2, 71-20-20. Are any discrepancies found?

NO

TO SHT 171


61-10-002-184

TO 1C-130H-2-61FI-00-1


61-10-002-185

TO 1C-130H-2-61FI-00-1

FROM SHT 169

549

Inspect engine condition control553system for loose, worn, or broken

components in accordance with Repair or replace engine condi-YESTO 1C-130H-2-76JG-00-1, 76-10- tion control system components03, 76-10-11, and 76-10-12; or as required. TO 2J-T56-56, as required.Are any discrepancies found?

NO

550

Inspect throttle control system for554loose, worn, or broken compo-

nents in accordance with TO 1C- Repair or replace throttle con-YES130H-2-76JG-00-1, 76-10-01, 76- trol system components as re-10-02, 76-10-10, and 76-10-12; or quired. TO 2J-T56-56, as required.Are any discrepancies found?

NO

551555

Check propeller balance in accor-Balance propeller in accordanceYES

dance with TO 1C-130H-2-61JG-with TO 1C-130H-2-61JG-10-1,10-1, 61-10-41.61-10-41.Is propeller (2) out of balance?

NO

552556Gain access to and check propel-

ler shaft (1) for excessive vertical Replace propeller assembly inYESmovement and end play in accor- accordance with TO 1C-130H-dance with TO 2J-T56-56. 2-61JG-10-1, 61-10-11. Are measurements within limits?

NO

557

As required, repair reductiongear in accordance with TO 2J-T56-56 or replace reductiongear in accordance with TO 1C-130H-2-71JG-00-2, 71-90-20.


61-10-002-186

TO 1C-130H-2-61FI-00-1


61-10-002-187

TO 1C-130H-2-61FI-00-1

Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 1 of 62)

61-10-002-188

TO 1C-130H-2-61FI-00-1

Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 2)

61-10-002-189

TO 1C-130H-2-61FI-00-1

11

Check diode CR3 (2) associat-ed with PROPELLER LOW OILWARNING/PROP light (1) thatFROM SHT 1is on and replace if defective.(See figure 2-13 or 2-14.) Then10continue troubleshooting withCheck affected propeller assem-sheet 11.blies for correct fluid level in ac- NO

cordance with TO 1C-130H-2- 1 3 4

12JG-10-2, 12-16-03. Prop Diode Prop DiodeIs fluid level in one propeller as- 1 CR3AX 3 CR3AZsembly low? 2 CR3AY 4 CR3BA

2

Prop Diode Prop Diode1 CR3FX 3 CR3FZ2 CR3FY 4 CR3GA

YES

12

Replace diode CR3 (2) associ-ated with PROPELLER LOWOIL WARNING light (1) that ison but whose propeller assem-bly does not require servicing.(See figure 2-13 or 2-14.) Thencontinue troubleshooting withsheet 5.

1 3 4

Prop Diode Prop Diode1 CR3AX 3 CR3AZ2 CR3AY 4 CR3BA

2

Prop Diode Prop Diode1 CR3FX 3 CR3FZ2 CR3FY 4 CR3GA

NOTE






61-10-002-190

TO 1C-130H-2-61FI-00-1


61-10-002-191

TO 1C-130H-2-61FI-00-1


61-10-002-192

TO 1C-130H-2-61FI-00-1


61-10-002-193

TO 1C-130H-2-61FI-00-1

FROM SHT 1

22 6110032

Momentarily hold the MACAWS 25LAMP TEST switch (4) in the test NO

Replace the faulty lamp in theposition.systems caution/advisory panel.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?

Test YESProp Diode Point TO SHT 41

1 CR3FX14

2 CR3FY16

3 CR3FZ18

4 CR3GA20

NO

24

Is voltage present on terminal ( )of diode CR3 (3)?

Test26Prop Diode Point

YESRepair open circuit between di-

1 CR3GB78

odes. (See figure 2-14.)

2 CR3GC79

3 CR3GD80

4 CR3GE81

NO

TO SHT 9

NOTE



61-10-002-194

TO 1C-130H-2-61FI-00-1


61-10-002-195

TO 1C-130H-2-61FI-00-1

FROM SHT 7

27

Is voltage present on cathode of diode CR3 (2)?

TestProp Diode Point

29YES1 CR3GB

74Replace diode CR3. (See figure 2-14.)

2 CR3GC75

3 CR3GD76

4 CR3GE77

NO

28

a. Temporarily remove power from the airplane.b. Gain access to and disconnect plug P1725A (1)from the systems caution/advisory panel.Is voltage present on related receptacle J1 pin?

30TestNO

Prop Pin 1 Pin 2 Point Fault is in MACAWS. Refer to TO 1C-130H-2-33FI-00-1-2 for troubleshooting.

1 5 970

2 6 1071

3 7 1172

4 8 1273

YES

31

Repair open circuit between applicable plugP1725A and related diode CR3 (2). (Seefigure 2-14.)

Plug PlugPin Diode Pin Diode5 CR3GB 7 CR3GD6 CR3GC 8 CR3GE

NOTE

1 C-130H airplanes.

2 LC-130H and HC-130(H)N airplanes.



61-10-002-196

TO 1C-130H-2-61FI-00-1


61-10-002-197

TO 1C-130H-2-61FI-00-1


61-10-002-198

TO 1C-130H-2-61FI-00-1


61-10-002-199

TO 1C-130H-2-61FI-00-1

FROM SHT 11

4042Inspect wiring to propeller control YES

receptacle (2) (for plug P392) for Repair loose or damaged wiringloose and broken connections. as required. (See figure 2-13.) Is any damage found?

NO

41

Gain access to oil level indicatorswitch (1) and disconnect wires 43from switch.

Repair ground fault betweenIs a ground present on discon- YESpropeller control receptacle andnected wires?oil level indicator switch. (Seefigure 2-13.) 40 41

, 38 39

,

32 33 OR

26 27

NO

44

Replace oil level indicatorswitch in accordance with TO1C-130H-2-61JG-20-1, 61-20-08.

NOTE

See figure 2-13 for: Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 13)

61-10-002-200

TO 1C-130H-2-61FI-00-1


61-10-002-201

TO 1C-130H-2-61FI-00-1

FROM SHT 11

45

Gain access to and disconnect applicable wire49from diode CR3 (2).

Is a ground present on disconnected wire? Repair ground fault be-tween pin D of plug P396(1) and related diode

Wire Test CR3. (See figure 2-13 or47YES NOProp Diode 1 Diode 2 No. Point 2-14.)

Is an outboard propellerbeing troubleshot? 1 CR3AX CR3FX 1E600D

14Prop Diode2 CR3AY

2 CR3AY CR3FY 2E600C16 1 3 CR3AZ

2 CR3FY3 CR3AZ CR3FZ 3E600C

18 2 3 CR3FZ

4 CR3BA CR3GA 4E600D20

NO

YES

48

Gain access to and disconnect 50plug P130/P1139 (4) at outer

Repair ground fault between pinNOwing break.N of receptacle J235/J935 (3)Is a ground present on plug pinand pin D of plug P396 (1).N?(See figure 2-13 or 2-14.)

46 OR

21

YES

51

Repair ground fault betweenplug P130/P1139 pin N and re-lated diode CR3. (See figure 2-13 or 2-14.)

Prop Diode1 CR3AX

1 4 CR3BA1 CR3FX

2 4 CR3GA

46 YESTO SHT 19

Is airplane serial number AF92-0547 through AF92-2104 or AF92-3281 and up?

NO

TO SHT 17

NOTE





61-10-002-202

TO 1C-130H-2-61FI-00-1


61-10-002-203

TO 1C-130H-2-61FI-00-1

FROM SHT 15

52 YESTO SHT 21Is airplane an MC-130H?

NO

53

Remove diode CR3 (2) associat-ed with propeller position. 56Is a ground present on diode bus 54 Repair ground fault between dim-bar?

mer terminal e and diode CR3AXGain access to terminals of in-(2), then replace specified diodedicator lights dimmer No. 7 (3)TestCR3 associated with PROPELLERand disconnect wire from dim-YES YESProp Diode PointLOW OIL WARNING light (1) thatmer terminal e.is on. (See figure 2-13.)Is a ground present on discon-1 CR3AX

13nected wire?

Prop Diode Prop Diode2 CR3AY15

1 CR3AX 3 CR3AZ10

2 CR3AY 4 CR3BA3 CR3AZ17

4 CR3BA19

NO

NO

TO SHT 2757

Replace indicator lights dimmer55No. 7, then replace specified diodeDisconnect wire from dimmerCR3 associated with PROPELLERterminal E. NO LOW OIL WARNING light (1) thatIs a ground present on discon-is on. (See figure 2-13.)nected wire?

Prop Diode Prop Diode91 CR3AX 3 CR3AZ2 CR3AY 4 CR3BAYES

TO SHT 29

NOTE

1 MC-130E airplane.



61-10-002-204

TO 1C-130H-2-61FI-00-1


61-10-002-205

TO 1C-130H-2-61FI-00-1

FROM SHT 15

58

Remove diode CR3 (3) associat-ed with propeller position.

60Is a ground present on diode busbar? Replace diode CR3 (3) associ-

ated with PROP light (2) that isTest on. (See figure 2-14.)

Prop Diode Point YESProp Diode

1 CR3FX13

1 CR3FX2 CR3FY

2 CR3FY15

3 CR3FZ4 CR3GA

3 CR3FZ17

4 CR3GA19

NO

59

Remove wire from anode of appli-cable diode CR3 (4).Is a ground present on discon- 61nected wire?

Repair ground fault between di-odes (3,4). (See figure 2-14.)Test

Prop Diode Point YESProp Diode Diode1 CR3FX CR3GB1 CR3GB

782 CR3FY CR3GC3 CR3FZ CR3GD2 CR3GC

794 CR3GA CR3GE

3 CR3GD80

4 CR3GE81

NO

62

Repair ground fault betweenplug P1725A (1) pin and relateddiode CR3 (4). (See figure 2-14.)

Plug DiodePin5 CR3GB6 CR3GC7 CR3GD8 CR3GE

NOTE



61-10-002-206

TO 1C-130H-2-61FI-00-1


61-10-002-207

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 PointNO

TO SHT 231 CR3AX13

2 CR3AY15

3 CR3AZ17

4 CR3BA19

YES

6664 Repair ground fault between pin 16 of

Gain access to disconnect plugs 47407A1P1 plug 47407A2P1 and diode CR3AX, thenand 47407A2P1 from indicator light dimmer replace specified diode CR3 associatedNo. 7 (2). with PROPELLER LOW OIL WARNINGYESIs a ground present on pin 16 of plug light (3) that is on. (See figure 2-13.)47407A2P1?

Prop Diode Prop Diode86

1 CR3AX 3 CR3AZ2 CR3AY 4 CR3BA

NO

67

Replace indicator light dimmer No. 7,then replace specified diode CR3 associ-65ated with PROPELLER LOW OIL WARN-Is a ground present on pin 24 of plugING light (3) that is on. (See figure 2-NO47407A2P1?13.)

82Prop Diode Prop Diode1 CR3AX 3 CR3AZ2 CR3AY 4 CR3BA

YES

TO SHT 25

NOTE



61-10-002-208

TO 1C-130H-2-61FI-00-1


61-10-002-209

TO 1C-130H-2-61FI-00-1

FROM SHT 21

6870Is ground present on specified pin of plug

47407A1P1 and 40407A2P1 of indicator Repair ground fault between terminal 2light dimmer No. 7 (2)? of PROPELLER LOW OIL WARNING

light (3) and applicable pin of plugProp Pin Test Point 47407A1P1 or 47407A2P1 of indicator

light dimmer No. 7. (See figure 2-13.)YES1 47407A1P1-10

102

Prop Pin2 47407A1P1-24

1011 47407A1P1-102 47407A1P1-24

3 47407A1P1-2399

3 47407A1P1-234 47407A2P1-10

4 47407A2P1-1083

NO

69

Is ground present on specified pin of plug 7147407A1P1 and 40407A2P1 of indicator

Repair ground fault between diode CR3light dimmer No. 7?(1) and applicable pin of plug47407A1P1 or 47407A2P1 of indicatorProp Pin Test Pointlight dimmer No. 7. (See figure 2-13.)YES

1 47407A1P1-491

Prop Diode Pin1 CR3AX 47407A1P1-42 47407A1P1-16

932 CR3AY 47407A1P1-163 CR3AZ 47407A1P1-153 47407A1P1-15

955 CR3BA 47407A2P1-4

4 47407A2P1-487

NO

72

Replace indicator light dimmer No. 7.

NOTE



61-10-002-210

TO 1C-130H-2-61FI-00-1


61-10-002-211

TO 1C-130H-2-61FI-00-1

FROM SHT 21

7573Repair PROP LOW OIL QUANTITYGain access to terminals of PROPmaster warning light, then replace speci-LOW OIL QUANTITY master warningfied diode CR3 (6) associated with PRO-light (3) and disconnect wire fromPELLER LOW OIL WARNING light (4)NO

light terminal 2.that is on. (See figure 2-13.)Is a ground present on disconnected

wire?Prop Diode Prop Diode1 CR3AX 3 CR3AZ492 CR3AY 4 CR3BA

YES

76

Repair ground fault between plug P251,74 pin C and PROP LOW OIL QUANTITY

Gain access to and disconnect plugs master warning light terminal 2, then re-P251 (2) at main instrument panel place specified diode CR3 (6) associatedYESdisconnect. with PROPELLER LOW OIL WARNINGIs there a ground present on pin C? light (4) that is on. (See figure 2-13.)

50Prop Diode Prop Diode1 CR3AX 3 CR3AZ2 CR3AY 4 CR3BANO

77

Repair ground fault between pin 24 ofplug 47407A2P1 of indicator light dimmerNo. 7 (5) and pin C of receptacle J129(1), then replace specified diode CR3 (6)associated with PROPELLER LOW OILWARNING light (4) that is on. (See fig-ure 2-13.)


NOTE



61-10-002-212

TO 1C-130H-2-61FI-00-1


61-10-002-213

TO 1C-130H-2-61FI-00-1

FROM SHT 17

78

Gain access to terminals of indi-cator lights dimmer No. 7 (3) and

80disconnect wire from specifieddimmer terminal. Repair ground fault betweenIs a ground present on discon- terminal 2 of PROPELLERnected wire? LOW OIL WARNING light (1)

and related dimmer terminal.Dim Test (See figure 2-13.)YES

Prop Term PointDim

1 A7

Prop Term1 A

2 B5

2 B3 C

3 C3

4 D

4 D1

NO

79

Disconnect wire from specifieddimmer terminal.

81Is a ground present on discon-nected wire? Repair ground fault between di-

ode CR3 (2) and related dim-Dim Test mer terminal. (See figure 2-13.)

Prop Term PointYES

Dim1 a

8Prop Diode Term1 CR3AX a

2 b6

2 CR3AY b3 CR3AZ c

3 c4

4 CR3BA d

4 d2

NO

82

Replace indicator lights dimmerNo. 7. (See figure 2-13.)

NOTE




61-10-002-214

TO 1C-130H-2-61FI-00-1


61-10-002-215

TO 1C-130H-2-61FI-00-1

FROM SHT 1785

83 Replace PROP LOW OIL QUANTI-Gain access to terminals of PROP TY master warning light, then re-LOW OIL QUANTITY master place specified diode CR3 (4)warning light (2) and disconnect associated with PROPELLER LOWNOwire from light terminal 2. OIL WARNING light (3) that is on.Is a ground present on discon- (See figure 2-13.)nected wire?

Prop Diode Prop Diode49

1 CR3AX 3 CR3AZ2 CR3AY 4 CR3BA

YES

86

Repair ground fault between plugP251 pin C and PROP LOW OIL84QUANTITY master warning lightGain access to and disconnectterminal 2, then replace specifiedplug P251 (1) at main instrumentdiode CR3 (4) associated withpanel disconnect. YESPROPELLER LOW OIL WARNINGIs a ground present on plug pinlight (3) that is on. (See figure 2-C?13.)

50Prop Diode Prop Diode1 CR3AX 3 CR3AZ2 CR3AY 4 CR3BA

NO

87

Repair ground fault between termi-nal E of indicator lights dimmer No.7 (5) and pin C of receptacle J129(6), then replace specified diodeCR3 (4) associated with PROPEL-LER LOW OIL WARNING light (3)that is on. (See figure 2-13.)


NOTE




61-10-002-216

TO 1C-130H-2-61FI-00-1


61-10-002-217

TO 1C-130H-2-61FI-00-1

90FROM SHT 5

Shut down engine(s) in accor-dance with TO 1C-130H-2-8871JG-00-1, 71-00-10; TO 1C-With engine(s) running, hold en-130(A)H-2-71JG-00-1, 71-00-gine condition lever (2) to AIR YES10; or 1C-130(M)H-2-71JG-00-START for 15 seconds.1, 71-00-10. Replace propellerDoes PROPELLER LOW OILcontrol in accordance with TOWARNING/PROP light (1) go off?1C-130H-2-61JG-20-1, 61-20-01. (Main scavenge pump mal-function.)

NO

89

a. Shut down engine(s) in accor-dance with TO 1C-130H-2-71JG-

9100-1, 71-00-10; TO 1C-130(A)H-2-71JG-00-1, 71-00-10; or TO 1C- Replace oil level indicatorNO130(M)H-2-71JG-00-1, 71-00-10. switch in accordance with TOb. Recheck affected propeller as- 1C-130H-2-61JG-20-1, 61-20-sembly for low fluid (and service if 08.required) in accordance with TO1C-130H-2-12JG-10-2, 12-16-03.Was fluid level low?

YES

92

Replace prop shaft plug seal inaccordance with TO 1C-130H-2-61JG-10-1, 61-10-14.

NOTE






61-10-002-218

TO 1C-130H-2-61FI-00-1


61-10-002-219

TO 1C-130H-2-61FI-00-1


61-10-002-220

TO 1C-130H-2-61FI-00-1


61-10-002-221

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?

86

YES

103 105

Is airplane equipped with a flight data re- Repair ground fault between pin 16 ofNOcorder system? (Check for presence of plug 47407A2P1 of indicator dimmer No.FLIGHT RECORDER and FLIGHT VOICE 7 and diode CR3AX (1). (See figure 2-RECORDER INHB circuit breakers (3,4). 13.)

YES

104

Gain access to terminals of diode CR3AX 106(1) and disconnect wire E604A22 from di-

Fault in flight data recorder system. GoNOode bus bar.to TO 1C-130H-2-31FI-00-1 and continueIs a ground present on disconnected wire?troubleshooting.

13

YES

107

Repair ground fault between pin 16 ofplug 47407A2P1 of indicator light dimmerNo. 7 and diode CR3AX. (See figure 2-13.)

NOTE



61-10-002-222

TO 1C-130H-2-61FI-00-1


61-10-002-223

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)?


82

YES

109

Gain access to and disconnect plug P251 111(2) at main instrument panel disconnect.

Repair ground fault between pin 24 ofIs a ground present on pin C of receptacle NOplug 47407A2P1 of indicator light dimmerJ129 (1)?No. 7 and pin C of receptacle J129.(See figure 2-13.)

50

YES

112

Repair ground fault between pin C ofplug P251 and terminal 2 of PROP LOWOIL QUANTITY master warning light (3).(See figure 2-13.)

NOTE



61-10-002-224

TO 1C-130H-2-61FI-00-1


61-10-002-225

TO 1C-130H-2-61FI-00-1

FROM SHT 33

113

Disconnect wire from terminal Eof indicator lights dimmer No. 7 115(3). NO

Replace indicator lights dimmerIs a ground present on discon-No. 7. (See figure 2-13.)nected wire?

9

YES

114

Gain access to and disconnect 116plug P251 (1) at main instrument

Repair ground fault betweenpanel disconnect. NOdimmer terminal E and pin C ofIs a ground present on plug pinreceptacle J129 (4). (See fig-C?ure 2-13.)

50

YES

117

Repair ground fault betweenplug P251 pin C and terminal 2of PROP LOW OIL QUANTITYmaster warning light (2). (Seefigure 2-13.)

NOTE




61-10-002-226

TO 1C-130H-2-61FI-00-1


61-10-002-227

TO 1C-130H-2-61FI-00-1


61-10-002-228

TO 1C-130H-2-61FI-00-1


61-10-002-229

TO 1C-130H-2-61FI-00-1

130

Repair open circuit between pinFROM SHT 41 D of plug P396 (1) and related

diode CR3 (2). (See figure 2-128 13 or 2-14.)NO

Is an outboard propeller beingtroubleshot? Prop Diode

2 CR3AY1 3 CR3AZ

2 CR3FY2 3 CR3FZ

YES

131129 Repair open circuit between

plug P130/P1139 pin N and re-lated diode CR3 (2). (See fig-

Gain access to and disconnect ure 2-13 or 2-14.)NOplug P130/P1139 (4) at outerwing break. Prop DiodeIs voltage present on plug pin N? 1 CR3AX

1 4 CR3BA46

OR 21

1 CR3FX2 4 CR3GA

YES

132

Repair open circuit between pinD of plug P396 (1) and pin N ofreceptacle J235/J935 (3). (Seefigure 2-13 or 2-14.)

NOTE





61-10-002-230

TO 1C-130H-2-61FI-00-1


61-10-002-231

TO 1C-130H-2-61FI-00-1

FROM SHT 1

133

Press to test affected PROPEL- 137YES NOLER LOW OIL WARNING light (1 TO SHT 49

Is airplane an MC-130H? or 2).Does light press to test?

NO

YES

TO SHT 47

134

Temporarily remove power andgain access to terminals of affect-

138ed PROPELLER LOW OILYESWARNING light. Replace PROPELLER LOW

Is 28 VDC present on light termi- OIL WARNING light assembly.nal 1?

51 ,

53 ,

55 OR

57

NO

139135Repair power circuit to No. 1Is No. 1 PROPELLER LOW OIL YESPROPELLER LOW OIL WARN-WARNING light (1) beingING light terminal 1. (See fig-troubleshot?ure 2-13.)

NO

140136Repair power circuit to No. 1Press to test No. 1 PROPELLER NOPROPELLER LOW OIL WARN-LOW OIL WARNING light.ING light terminal 1. (See fig-Does light press to test?ure 2-13.)

YES

TO SHT 51

NOTE





61-10-002-232

TO 1C-130H-2-61FI-00-1


61-10-002-233

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). Repair open circuit between applicableIs ground present on specified pin of plug pin of plug 47407A1P1 and 47407A2P147407A1P1 and 40407A2P1 of indicator of indicator light dimmer No. 7 and relat-light dimmer No. 7? ed diode CR3 (3). (See figure 2-13.)NO

Prop Pin Test Point Prop Pin Diode1 47407A1P1-4 CR3AX

1 47407A1P1-491

2 47407A1P1-16 CR3AY3 47407A1P1-15 CR3AZ

2 47407A1P1-1693

4 47407A2P1-4 CR3BA

3 47407A1P1-1595

4 47407A2P1-487

YES

142

Is there continuity between specified pins of re-144ceptacle 47407A1J1 and 47407A2J1 of indicator

lights dimmer No. 7? Repair open circuit between terminal2 of PROPELLER LOW OIL WARN-

Prop Pin Test Point ING light (1) and applicable pin of1 47407A1J1-4 plug 47407A1P1 or 47407A2P1 of in-

47407A1J1-1090 103

dicator light dimmer No. 7. (See fig-YESure 2-13.)

2 47407A1J1-1647407A1J1-24

92 100Prop Pin1 47407A1P1-10

3 47407A1J1-15 2 47407A1P1-2447407A1J1-23

94 983 47407A1P1-234 47407A2P1-10

4 47407A2J1-447407A2J1-10

85 84

NO

145


NOTE



61-10-002-234

TO 1C-130H-2-61FI-00-1


61-10-002-235

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- 148dicator lights dimmer No. 7 (4).

Repair open circuit betweenIs a ground present on specifiedspecified dimmer terminal anddimmer terminal?related diode CR3 (3). (Seefigure 2-13.)Dim Test NO

Prop Term PointDim

Prop Term Diode1 a8

1 a CR3AX2 b CR3AY2 b

63 c CR3AZ4 d CR3BA3 c

4

4 d2

YES

147149Is a ground present on specified

dimmer terminal? Repair open circuit between ter-minal 2 of PROPELLER LOW

Dim Test OIL WARNING light (1) and re-Prop Term Point lated dimmer terminal. (See

figure 2-13.)YES1 A

7

Dim2 B

5Prop Term1 A

3 C3

2 B3 C

4 D1

4 D

NO

150

Replace indicator lights dimmerNo. 7.

NOTE




61-10-002-236

TO 1C-130H-2-61FI-00-1


61-10-002-237

TO 1C-130H-2-61FI-00-1

FROM SHT 45155

151 Repair open circuit between terminalIs No. 2 PROPELLER LOW OIL 1 of No. 1 PROPELLER LOW OILYESWARNING light (2) being WARNING light (1) and terminal 1 oftroubleshot? No. 2 PROPELLER LOW OIL WARN-

ING light (2). (See figure 2-13.)NO

156152 Repair open circuit between terminal

Press to test No. 2 PROPELLER 1 of No. 1 PROPELLER LOW OILNOLOW OIL WARNING light. WARNING light (1) and terminal 1 ofDoes light press to test? No. 2 PROPELLER LOW OIL WARN-

ING light (2). (See figure 2-13.) YES


Is No. 3 PROPELLER LOW OIL 1 of No. 2 PROPELLER LOW OILYESWARNING light (3) being WARNING light (2) and terminal 1 oftroubleshot? No. 3 PROPELLER LOW OIL WARN-

ING light (3). (See figure 2-13.)NO


Press to test No. 3 PROPELLER 1 of No. 2 PROPELLER LOW OILNOLOW OIL WARNING light. WARNING light (2) and terminal 1 ofDoes light press to test? No. 3 PROPELLER LOW OIL WARN-

ING light (3). (See figure 2-13.)YES

159

Repair open circuit between terminal1 of No. 3 PROPELLER LOW OILWARNING light (3) and terminal 1 ofNo. 4 PROPELLER LOW OIL WARN-ING light (4). (See figure 2-13.)

NOTE




61-10-002-238

TO 1C-130H-2-61FI-00-1


61-10-002-239

TO 1C-130H-2-61FI-00-1

FROM SHT 1163

165Temporarily remove power and gain ac-160 6110031Replace PROPcess to terminals of PROP LOW OILNO YESPress to test PROP LOW OIL QUANTI-LOW OIL QUANTI-QUANTITY master warning light.TY master warning light (2).TY master warningIs 28 VDC present on light terminal 1?Does light press to test?light assembly.

48YES

NO

164

a. Remove power from airplane.166b. Gain access to and disconnect plug

P251 (1) at main instrument panel dis- Repair power cir-YESconnect. cuit to pin B of re-Is there continuity between plug pin B ceptacle J129 (4).and light terminal 1? (See figure 2-13.)

47 48

NO

167

Repair open circuit. (See figure 2-13.)

161

a. Remove power from airplane.b. Gain access to diode CR3 (3) associ-ated with propeller position. 168Is a ground present on diode bus bar?

Replace defective diode CR3. (See fig-ure 2-13.)Test

Prop Diode Point NOProp Diode1 CR3AX1 CR3AX

132 CR3AY3 CR3AZ2 CR3AY

154 CR3BA

3 CR3AZ17

4 CR3BA19

YES


NO

TO SHT 57

NOTE




61-10-002-240

TO 1C-130H-2-61FI-00-1


61-10-002-241

TO 1C-130H-2-61FI-00-1

FROM SHT 53

169

a. Gain access to PROP LOW OIL QUANTITYmaster warning light (3) and remove bulb from

173light. YESb. Gain access to terminal or light. Replace PROP LOW OIL QUANTI- Is a ground present on light terminal 2? TY master warning light assembly.

49

NO

170

Gain access to and disconnect plug17447407A2P1 from indicator light dimmer No. 7

(5). Repair open circuit between pin 16NOIs a ground present on pin 16? of plug 47407A2P1 and diode

CR3AX (4). (See figure 2-13.)

86

YES

171

Is there continuity between pins 24 and 16 of 175receptacle 47404A2P1? NO

Replace indicator light dimmer No.7.

82 86

YES

172

Gain access to and disconnect plug P251 (2)176at main instrument panel disconnect.

Is there continuity between plug pin C and Repair open circuit between pin 24NOPROP LOW OIL QUANTITY master warning of plug 47407A2P1 and pin C oflight terminal 2? receptacle J129 (1). (See figure 2-

13.)

50 49

YES

177

Repair open circuit. (See figure 2-13.)

NOTE



61-10-002-242

TO 1C-130H-2-61FI-00-1


61-10-002-243

TO 1C-130H-2-61FI-00-1

FROM SHT 53

178

a. Gain access to PROP LOW OIL QUANTITY182master warning light (2) and remove bulb from

light. Replace PROP LOW OILYESb. Gain access to terminals of light. QUANTITY master warning lightIs a ground present on light terminal 2? assembly.

49

NO

179183Gain access to terminals of indicator lights

dimmer No. 7 (4). Repair open circuit betweenNOIs a ground present on dimmer terminal e? dimmer terminal e and diode

CR3AX (3). (See figure 2-13.)10

YES

180184

Is a ground present on dimmer terminal E? NOReplace indicator lights dimmerNo. 7.9

YES

181

Gain access to and disconnect plug P251 (1) 185at main instrument panel disconnect.

Repair open circuit betweenIs there continuity between plug pin C and YESdimmer terminal E and pin C ofPROP LOW OIL QUANTITY master warningreceptacle J129 (5). (See fig-light terminal 2?ure 2-13.)

50 49

NO

186


NOTE




61-10-002-244

TO 1C-130H-2-61FI-00-1


61-10-002-245

TO 1C-130H-2-61FI-00-1

FROM SHT 1

191187Fault is in MACAWS. Refer toYES

Is airplane serial number AF92-0547 throughTO 1C-130H-2-33FI-00-1-2 forAF92-2104 or AF92-3281 and up? troubleshooting.

NO


NO

189 6110030

a. Place THUNDERSTORM lights switch (2) toOFF.b. Place pilot’s INSTRUMENT lights rheostat

192(6) to any position except OFF.NO

c. Momentarily place CAUTION lights switch Replace indicator lights dimmer(1) to BRIGHT, then DIM. No. 7 (5). Do PROP LOW OIL QUANTITY master warn-ing light (3) and a PROPELLER LOW OILWARNING light (4) fail to go to selectedbright/dim mode?

YES

190

a. Gain access to terminals of indicator lightsdimmer No. 7 (5). 193b. Momentarily hold CAUTION LIGHTS switch

Fault is in dimming circuit. GoNOto DIM.to TO 1C-130H-2-33FI-00-1-1-1Is 28 VDC present between dimmer terminalsand continue troubleshooting.W and X while switch is held?

12 11

YES

194

Replace indicator lights dimmerNo. 7.

NOTE




61-10-002-246

TO 1C-130H-2-61FI-00-1


61-10-002-247

TO 1C-130H-2-61FI-00-1

FROM SHT 59

195

a. Place THUNDERSTORM lights switch (2) tooff.b. Place pilot’s INSTRUMENT lights rheostat

197(1) to any position except OFF. NOc. Place WCA DIM LEVEL switch (5) to 1. Replace indicator light dimmerd. Momentarily place WCA lights switch (6) to No. 7 (7). DIM.Do PROP LOW OIL QUANTITY master warn-ing light (3) and a PROPELLER LOW OILWARNING light (4) fail to go to dim mode?

YES

196

a. Gain access to and disconnect plugs47404A1P1 and 47407A2P1 from indicatorlight dimmer No. 7 (7).b. Momentarily hold WCA lights switch to DIM.Is 28 VDC present between specified pins of47407A1P1 and 47407A2P1 while switch is

198held?Fault is in dimming circuit. GoNO

Pin Test Point to TO 1C-130H-2-33FI-00-1-1-1and continue troubleshooting.

47407A1P1-796

47407A1P1-897

47407A2P1-788

47407A2P1-889

YES

199

Replace indicator light dimmerNo. 7.

NOTE



61-10-002-248

TO 1C-130H-2-61FI-00-1


61-10-002-249/(2-250 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-6. Beta Indication Electrical Schematic Diagram (Airplanes Priorto AF92-0547 and Airplanes AF92-3021 through AF92-3024) 61-10-00

F2-62-251/(2-252 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-7. Beta Indication Electrical Schematic Diagram (AirplanesAF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up) 61-10-00

F2-72-253/(2-254 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-8. Negative Torque Signal System Electrical Schematic Diagram(Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through

AF92-3024, Except MC-130H Airplanes) 61-10-00F2-8

2-255/(2-256 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-9. Negative Torque Signal System Electrical Schematic Diagram(Airplanes AF92-0547 Through AF92-2104 and

Airplanes AF92-3281 and Up) 61-10-00F2-9

2-257/(2-258 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-10. Negative Torque Signal System Electrical SchematicDiagram (MC-130H Airplanes) 61-10-00

F2-102-259/(2-260 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-11. Propeller Feather System Electrical Schematic Diagram (Air-planes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)

(Sheet 1 of 8) 61-10-00F2-11

Change 6 2-261/(2-262 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 2) 61-10-00F2-11

2-263/(2-264 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 3) 61-10-00F2-11

2-265/(2-266 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 4) 61-10-00F2-11

2-267/(2-268 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 5) 61-10-00F2-11

2-269/(2-270 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 6) 61-10-00F2-11

2-271/(2-272 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 7) 61-10-00F2-11

2-273/(2-274 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 8) 61-10-00F2-11

2-275/(2-276 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-12. Propeller Feather System Electrical Schematic Diagram (Air-planes AF92-0547 Through AF92-2104 andAirplanes AF92-3281 and Up) (Sheet 1 of 4) 61-10-00

F2-122-277/(2-278 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-12. Propeller Feather System Electrical Schematic Diagram (Air-planes AF92-0547 Through AF92-2104 and

Airplanes AF92-3281 and Up) (Sheet 2) 61-10-00F2-12

2-279/(2-280 blank)

TO 1C-130H-2-61FI-00-1



2-281/(2-282 blank)

TO 1C-130H-2-61FI-00-1



2-283/(2-284 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-13. Propeller Low Fluid Warning System Electrical SchematicDiagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021

through AF92-3024) (Sheet 1 of 2) 61-10-00F2-13

2-285/(2-286 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-13. Propeller Low Fluid Warning System Electrical SchematicDiagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021

through AF92-3024) (Sheet 2) 61-10-00F2-13

2-287/(2-288 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-14. Propeller Low Fluid Warning System Electrical SchematicDiagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes

AF92-3281 and Up) 61-10-00F2-14

2-289/(2-290 blank)

TO 1C-130H-2-61FI-00-1

Figure 2-15. In-line Disconnects Location Diagram (Airplanes AF92-1094,AF92-1095, AF92-2104, and AF93-1036 and Up) 61-10-00

F2-152-291/(2-292 blank)

TO 1C-130H-2-61FI-00-1

Section III. SYNCHROPHASER SYSTEM

3-1. GENERAL. The fault isolation material in this section is used for troubleshooting anysynchrophaser system malfunction. Contents of this section include a malfunction index, a faultcode index, preparation procedures to be performed prior to fault isolation, a fault isolationdiagram (the actual troubleshooting procedures), locator illustrations for hardware referenced inthe fault isolation diagram, and schematic diagrams.


Table 3-1. Synchrophaser System Malfunctions


1. Synchrophaser system 6120S01 Perform figure 3-1, Preparation A, then gomalfunction to figure 3-5, block 1.


3-3. NUMERIC FAULT CODE INDEX. All assigned numeric FRM fault codes for the syn-chrophaser system are listed in table 3-2. Fault codes are listed in numerical order in the leftcolumn of the table. The middle column contains the AFTO Form 781A report and lists symp-toms and conditions actually observed by the flight crew while performing the FRM procedure.The right column identifies the preparation and fault isolation figures for troubleshooting.

Table 3-2. Synchrophaser System Fault Codes


6120001 All slave propellers fail to follow when Replace propeller synchrophaser in accor-No. 3 propeller is selected as master. All dance with TO 1C-130H-2-61JG-20-1, 61-slave propellers follow when No. 2 propel- 20-13.ler is selected as master.

6120002 Propeller No. (1)(2)(4) fails to follow when Replace propeller synchrophaser in accor-No. 3 propeller is selected as master. dance with TO 1C-130H-2-61JG-20-1, 61-Propeller follows when No. 2 propeller is 20-13.selected as master.


61-20-003-1

TO 1C-130H-2-61FI-00-1

Table 3-2. Synchrophaser System Fault Codes - Continued


6120004 All slave propellers fail to follow when Replace propeller synchrophaser in accor-No. 2 or No. 3 propeller is selected as dance with TO 1C-130H-2-61JG-20-1, 61-master. 20-13.


6120006 Propeller No. (1)(3)(4) fails to follow when Perform figure 3-1, Preparation A, thenNo. 2 or No. 3 propeller is selected as go to figure 3-5, block 146.master.

6120007 All slave engine RPMs fluctuate when Perform figure 3-1, Preparation A, thenNo. 3 propeller is selected as master. go to figure 3-5, block 326.

6120008 Engine No. (1)(2)(3)(4) RPM fluctuates Perform figure 3-1, Preparation A, thenwhen No. 3 propeller is selected as go to figure 3-5, block 326.master.



6120011 Engine No. (1)(2)(3)(4) RPM takes exces- Perform figure 3-1, Preparation A, thensive time to stabilize after rapid THROT- go to figure 3-5, block 148.TLE movement.

6120012 All engine RPMs (fluctuate) (are out of Replace propeller synchrophaser in accor-limits) in normal governing. dance with TO 1C-130H-2-61JG-20-1, 61-

20-13.

6120013 Engine No. (1)(2)(3)(4) RPM (fluctuates) Perform figure 3-1, Preparation A, then(is out of limits) in normal governing. go to figure 3-5, block 139.

6120014 Engine No. (1)(2)(3)(4) RPM (fluctuates) Fault is in propeller system. Go to Sec-(is out of limits) in mechanical governing. tion II and continue fault isolation.


WARNING



61-20-003-2

TO 1C-130H-2-61FI-00-1


61-20-003-3

TO 1C-130H-2-61FI-00-1


61-20-003-4

TO 1C-130H-2-61FI-00-1


61-20-003-5

TO 1C-130H-2-61FI-00-1


61-20-003-6

TO 1C-130H-2-61FI-00-1

Figure 3-3. Preparation C (Sheet 1 of 3)

61-20-003-7

TO 1C-130H-2-61FI-00-1

Figure 3-3. Preparation C (Sheet 2)

61-20-003-8

TO 1C-130H-2-61FI-00-1


61-20-003-9

TO 1C-130H-2-61FI-00-1

Figure 3-4. Preparation D (Sheet 1 of 3)

61-20-003-10

TO 1C-130H-2-61FI-00-1

Figure 3-4. Preparation D (Sheet 2)

61-20-003-11

TO 1C-130H-2-61FI-00-1


61-20-003-12

TO 1C-130H-2-61FI-00-1

3-5. FAULT ISOLATION DIAGRAM. The fault isolation diagram in this section is used for trou-bleshooting any synchrophaser system malfunction. When the flight crew uses a FRM fault codeto report a malfunction, that number will be found in the fault code index. When no FRM faultcode is available, the malfunction index identifies the figure to use for fault isolation.

a. Arrangement. One fault isolation diagram is included for the synchrophaser system.Opposite each flow sheet of the fault isolation diagram is an illustration which shows the physi-cal location of items referenced in individual fault isolation diagram blocks. Double-check theseillustrations to verify the correct location when making an observation or measurement. Follow-ing the fault isolation diagram are the electrical schematic diagrams. The schematic diagramsare laid out so that no portion of a diagram is covered up when folded out for use. Thus it iseasy to concurrently locate components, circuits, and test points that are referenced on the faultisolation diagram.


61-20-003-13

TO 1C-130H-2-61FI-00-1

1 6120S01

Advance throttles (6) to obtain ap- 5proximately 8,000 inch-pounds on

Perform synchrophaser index in 6engine torque indicators (3) with YES NOaccordance with TO 1C-130H-all ELECTRONIC FUEL COR- Synchrophaser index corrected61JG-10-1, 61-10-02 (subtask 1-RECTION/TD lights (2) off. malfunction. Secure system.2-6).Did RPM on any engine tachome-Does problem persist?ter (4) exceed 103.5 percent or

did any propeller pitchlock?

NO

YES

TO SHT 7

72Fault is in propeller system.Place propeller governor control switches (5) NOGo to figure 2-5 in Section IIto MECH GOV/MECH.and continue troubleshoot-Is RPM stable for each propeller?ing.

YES

3NO

Is RPM in FUNCTION display (1) between TO SHT 14799.8 and 100.2 percent for each propeller?

YES

4

Perform synchrophaser index in accordancewith TO 1C-130H-2-61JG-10-1, 61-10-02 (sub-task 1-2-6). YESDid RPM of any propeller vary more than 0.2 TO SHT 25percent when propeller governor controlswitches were moved from MECH GOV/MECHto NORMAL/NORM during the synchrophaserindex?

NO

TO SHT 3

NOTE



Figure 3-5. Synchrophaser System Malfunction (Sheet 1 of 152)

61-20-003-14

TO 1C-130H-2-61FI-00-1

Figure 3-5. Synchrophaser System Malfunction (Sheet 2)

61-20-003-15

TO 1C-130H-2-61FI-00-1

FROM SHT 1

8NO

Is RPM stable for each propeller TO SHT 41(1) in NORMAL governing?

YES

9

Place SYNCHROPHASE NOMASTER/MSTR switch (3) to en- TO SHT 109gine 2.Is RPM stable for all propellers?

YES

10

Perform synchrophaser check inaccordance with TO 1C-130H-2-61JG-10-1, 61-10-02 (subtask 1-

YES2-9).TO SHT 43Did RPM of any slave propeller

fail to decrease 1 to 3 percent asNo. 2 throttle (2) was retarded toFLIGHT IDLE/FLT IDLE duringthe check?

NO

11

Place SYNCHROPHASE NOMASTER/MSTR switch to engine TO SHT 1093.Is RPM stable for all propellers?

YES

TO SHT 5


61-20-003-16

TO 1C-130H-2-61FI-00-1


61-20-003-17

TO 1C-130H-2-61FI-00-1

FROM SHT 3

1215

Did the RPM of any slave propel-Replace propeller syn-ler fail to decrease 1 to 3 percent YESchrophaser in accordance withas No. 3 throttle (1) was retardedTO 1C-130H-2-61JG-20-1, 61-to FLIGHT IDLE/FLT IDLE during20-13.the synchrophaser check?

NO

13

Perform throttle anticipation checkNOin accordance with TO 1C-130H-

TO SHT 452-61JG-10-1, 61-10-02 (subtask1-2-8).Was check satisfactory?

YES

14

Perform fuel governor and 16pitchlock check in accordance YES

Synchrophaser system is nor-with TO 1C-130H-2-61JG-10-1,mal. Secure system. 61-10-02 (subtask 1-2-10).

Was check satisfactory?

NO

TO SHT 7


61-20-003-18

TO 1C-130H-2-61FI-00-1


61-20-003-19

TO 1C-130H-2-61FI-00-1

FROM SHT 1 OR 5

17

CAUTIONDo not retard throttle below 96 percent if pitchlock is engaged.The RPM may drop below 94 percent and cause an engineflameout, resulting in overtemperature damage to the turbine.

20a. Shut down engines in accordance with TO 1C-130H-2-71JG-00-1, 71-00-10; or TO 1C-130(A)H-2-71JG-00-1, 71-00-10. Is airplane serialb. Perform Preparation D. NO YESnumber AF92-0547 TO SHT 11c. Place TEST SELECT switch (2) to 7. through AF92-2104d. Place PROP CHANNEL SELECT switch (3) to 4. or AF92-3281 ande. Momentarily hold engine 4 fuel governing switch (6) to up? CHECK.Does FUNCTION display (1) indicate -6.5 to -7.5 volts whileswitch is held?

Prop Sync Rcpt Pins4 J267A-8, J267A-45

YES

NO

TO SHT 9

18

a. Place PROP CHANNEL SELECT switch to R/3.b. Momentarily hold engine 3 fuel governing switch (5) toCHECK. NODoes FUNCTION display indicate -6.5 to -7.5 volts while switch TO SHT 15is held?


YES

19

a. Place PROP CHANNEL SELECT switch to L/2.b. Momentarily hold engine 2 fuel governing switch (4) toCHECK. NODoes FUNCTION display indicate -6.5 to -7.5 volts while switch TO SHT 17is held?


YES

TO SHT 19

NOTE

1 AC-130H airplanes only.

2 AC-130U airplanes only.

3 MC-130H airplanes only.


61-20-003-20

TO 1C-130H-2-61FI-00-1


61-20-003-21

TO 1C-130H-2-61FI-00-1

FROM SHT 7

21 23

NOTE a. Remove junction box from syn-Put meter positive lead to ground chrophaser rack.

24in following steps. b. Install a jumper wire betweenRemove jumper wire. Repairpin 14 of receptacle J268A (3)NO NO

Gain access to terminals of ENG open circuit between switch ter-and airplane ground.4 FUEL GOVERNING switch (1). minal 2 and receptacle J268AIs a ground present on ENG 4Is 15 volts present on switch ter- pin 14. (See figure 3-6.)FUEL GOVERNING switch termi-minal 2? nal 2?

7 7

YES YES

25

Replace propeller syn-chrophaser in accordance withTO 1C-130H-2-61JG-20-1, 61-20-13.

22

Momentarily hold ENG 4 FUEL26GOVERNING switch to CHECK.

NOIs 15 volts present on switch ter- Replace ENG 4 FUEL GOV-minal 1 while switch is held? ERNING switch.

8

YES

27

Repair open circuit betweenswitch terminal 1 and pin 8 ofreceptacle J267A (2). (See fig-ure 3-6.)

NOTE



3 MC-130E airplanes only.




61-20-003-22

TO 1C-130H-2-61FI-00-1


61-20-003-23

TO 1C-130H-2-61FI-00-1

FROM SHT 7

28

NOTEPut meter positive lead to ground in followingsteps.

NOTO SHT 13Gain access to terminals of engine 4 fuel gov-

erning switch (3).Is 15 volts present on switch terminal 2?

7

YES

29

Momentarily hold engine 4 fuel governing switch31to CHECK.

NOIs 15 volts present on switch terminal 1 while Replace engine 4 fuelswitch is held? governing switch.

8

YES

3032Gain access to and disconnect plug P1743A (1)

from fuel governing control panel (4). Repair open circuit be-YESIs there continuity between receptacle J880A (2) tween plug P1743A pin Dpin D and related control panel switch terminal 1? and receptacle J267A (5)

pin 8. (See figure 3-7.) 8 88

NO

33

Repair open circuit be-tween receptacle J880Apin D and switch terminal1. (See figure 3-7.)

NOTE

See figure 3-7 for:


61-20-003-24

TO 1C-130H-2-61FI-00-1


61-20-003-25

TO 1C-130H-2-61FI-00-1

FROM SHT 11

34

a. Gain access to and disconnectplug P1743A (1) from fuel governing

36control panel (4).b. Install a jumper wire between pin Remove jumper wire. Repair openNOE of receptacle J880A (2) and air- circuit between fuel governingplane ground. switch terminal 2 and receptacleIs a ground present on engine 4 fuel J880A pin E. (See figure 3-7.) governing switch terminal 2 (3)?

7

YES

35

a. Remove junction box from syn-chrophaser rack. 37b. Install a jumper wire between pin

Remove jumper wire. Repair open14 of receptacle J268A (5) and air- NOcircuit between plug P1743A pin Eplane ground.and receptacle J268A, pin 14.Is a ground present on engine 4 fuel(See figure 3-7.)governing switch terminal 2?

7

YES

38

Replace propeller synchrophaser inaccordance with TO 1C-130H-2-61JG-20-1, 61-20-13.

NOTE

See figure 3-7 for:


61-20-003-26

TO 1C-130H-2-61FI-00-1


61-20-003-27

TO 1C-130H-2-61FI-00-1


61-20-003-28

TO 1C-130H-2-61FI-00-1


61-20-003-29

TO 1C-130H-2-61FI-00-1


61-20-003-30

TO 1C-130H-2-61FI-00-1


61-20-003-31

TO 1C-130H-2-61FI-00-1

FROM SHT 7

57

a. Place PROP CHANNEL SELECT switch (6) to 1.b. Momentarily hold engine 1 fuel governing switch (1) to CHECK.

NODoes FUNCTION display (3) indicate -6.5 to -7.5 volts while switch isTO SHT 21held?


YES

58

a. Place PROP CHANNEL SELECT switch to propeller under test.b. Place propeller governor control switch (8) to MECH GOV/MECH. 60c. Momentarily hold FUEL GOV switch (5) to ON.

Replace propeller syn-Does FUNCTION display indicate -6.5 to -7.5 volts while switch is held?chrophaser in accor-NOdance with TO 1C-Prop Sync Rcpt Pins130H-2-61JG-20-1,1 J267A-7, J267A-4561-20-13.2 J268A-12, J267A-45

3 J268A-13, J267A-454 J267A-8, J267A-45

YES

59

a. Place propeller governor control switch (8) to NORM GOV/NORMposition.b. Place TEST SELECT switch (7) to 8.c. Momentarily hold applicable fuel governing switch (1 or 2) to CHECK 61for 10 seconds.

Replace propeller syn-Does AC VOLTS display (4) indicate 50 to 65 volts while switch ischrophaser in accor-NO

held?dance with TO 1C-(Speed bias control winding)130H-2-61JG-20-1,61-20-13. Prop Sync Rcpt Pins

1 J267A-35, J267A-362 J268A-25, J268A-263 J267A-37, J267A-384 J268A-27, J268A-28

YES

TO SHT 23

NOTE


2 Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up. 4 AC-130U airplanes only.

3 AC-130H airplanes only. 5 MC-130H airplanes only.


61-20-003-32

TO 1C-130H-2-61FI-00-1


61-20-003-33

TO 1C-130H-2-61FI-00-1


61-20-003-34

TO 1C-130H-2-61FI-00-1


61-20-003-35

TO 1C-130H-2-61FI-00-1

FROM SHT 19

71

a. Record voltage indication in FUNC-TION display (2) for propeller under test.b. Place propeller governor controlswitch (3) to NORMAL/NORM.c. Actuate applicable fuel governingswitch (1) as follows:

CHECK for 5 seconds,NORMAL/NORM for 5 seconds,CHECK for 5 seconds,

NORMAL/NORM for 5 seconds.d. Place propeller governor control 72switch to MECH GOV/MECH.

Replace valve housing assem-YESe. Record voltage indication in FUNC-

bly in accordance with TO 1C-TION display.130H-2-61JG-20-1, 61-20-02. f. Compare the two voltage indications

recorded in steps a and e.Did voltage change more than 0.2 voltson any channel?(Feedback pot)

DC: Sync AC: SyncRcpt Pin Rcpt PinsJ267A-11 J267A-35 and 36J268A-2 J268A-25 and 26J268A-5 J267A-37 and 38J267A-14 J268A-27 and 28

NO

73


NOTE







61-20-003-36

TO 1C-130H-2-61FI-00-1


61-20-003-37

TO 1C-130H-2-61FI-00-1

FROM SHT 1

74

YESDid all propellers (1,2,3, and 4)TO SHT 27fail to respond to the syn-

chrophaser index?

NO

75

With No. 2 propeller (2) as masterYESdid No. 3 propeller (3) fail to in-

TO SHT 39dex, and with No. 3 propeller asmaster did No. 2 propeller fail toindex?

NO

76

Perform propeller governor servo-77bias clutch-brake check on affect-

ed propeller in accordance with Replace valve housing assem-NOTO 1C-130H-2-61JG-10-1, 61-10- bly in accordance with TO 1C-02 (subtask 1-2-7). 130H-2-61JG-20-1, 61-20-02. Was RPM within limits for the af-fected propeller?

YES

TO SHT 47


61-20-003-38

TO 1C-130H-2-61FI-00-1


61-20-003-39

TO 1C-130H-2-61FI-00-1


61-20-003-40

TO 1C-130H-2-61FI-00-1


61-20-003-41

TO 1C-130H-2-61FI-00-1

FROM SHT 27

8991Place SYNCHROPHASE

MASTER/MSTR switch (1) to en- Gain access to terminal board93gine 2. TB146A (5).NO NO

Are MASTER light L/2 (2) and Repair power circuit to terminalIs 28 VDC present on terminalSYNC light (4) on? 199. (See figure 3-6 or 3-7.)199?

Prop Sync Rcpt Pins 27

Any J268A-22

YESYES

92 94

Is 28 VDC present on terminal Repair open circuit between ter-YES207? minal 207 and pin 22 of recep-

tacle J268A (6). (See figure 3-29

6 or 3-7.)

NO

TO SHT 31

90

Place SYNCHROPHASEMASTER/MSTR switch to engine3. NOAre MASTER light R/3 (3) and TO SHT 33SYNC light on?

Prop Sync Rcpt PinsAny J267A-27

YES

TO SHT 35

NOTE




61-20-003-42

TO 1C-130H-2-61FI-00-1


61-20-003-43

TO 1C-130H-2-61FI-00-1

FROM SHT 29

95

Gain access to terminals of SYN- 99CHROPHASE MASTER/MSTR

Repair open circuit betweenswitch (3). NOswitch terminal 11 and terminalIs 28 VDC present on switch ter-199 of terminal board TB146Aminal 11?(1). (See figure 3-6 or 3-7.)

14

YES

96100Is 28 VDC present on switch ter-

NOminal 10? Replace SYNCHROPHASEMASTER/MSTR switch.

17

YES

97101

Gain access to terminals of PROPRepair open circuit betweenRESYNCHROPHASE/PROPPROP RESYNCHROPHASE/SYNC switch (2). NOPROP SYNC switch terminal 5Is 28 VDC present on switch ter-and SYNCHROPHASEminal 5?MASTER/MSTR switch terminal10. (See figure 3-6 or 3-7.) 22

YES


Is 28 VDC present on switch ter- PROP RESYNCHROPHASE/YESminal 6? PROP SYNC switch terminal 6and terminal board TB146A ter-

25minal 207. (See figure 3-6 or3-7.)

NO

103

Replace PROP RESYN-CHROPHASE/PROP SYNCswitch.

NOTE

See figure 3-6 for:


61-20-003-44

TO 1C-130H-2-61FI-00-1


61-20-003-45

TO 1C-130H-2-61FI-00-1

FROM SHT 29

108104Gain access to terminals of SYN-Gain access to terminal board 109CHROPHASE MASTER/MSTRTB146A (1). NO YES Repair open circuit betweenswitch (2).Is 28 VDC present on terminal

switch terminals 10 and 12.Is 28 VDC present on switch ter-207?(See figure 3-6 or 3-7.) minal 12?

2918

YESNO

110

Replace SYNCHROPHASEMASTER/MSTR switch.

105 111

Is 28 VDC present on terminal Repair open circuit between ter-YES206? minal 206 and pin 27 of recep-tacle J267A (3). (See figure 3-

286 or 3-7.)

NO

106

Gain access to terminals of SYN-112CHROPHASE MASTER/MSTR

switch (2). Repair open circuit betweenNOIs 28 VDC present on switch ter- switch terminals 8 and 11.minal 8? (See figure 3-6 or 3-7.)

15

YES

107 113

Is 28 VDC present on switch ter- Repair open circuit betweenYESminal 9? switch terminal 9 and terminalboard TB146A terminal 206.

19(See figure 3-6 or 3-7.)

NO

114


NOTE




61-20-003-46

TO 1C-130H-2-61FI-00-1


61-20-003-47

TO 1C-130H-2-61FI-00-1

FROM SHT 29

115

Momentarily hold PROP RESYN-CHROPHASE/PROP SYNC 119switch (3) to RESYNC/INDEX.

Replace propeller syn-Are R/3 light (1) and RESYNC/IN- YESchrophaser in accordance withDEX light (2) on while switch isTO 1C-130H-2-61JG-20-1, 61-held?20-13.

Prop Sync Rcpt PinsAny J268A-15

NO

116 118

a. Gain access to terminal board a. Gain access to terminals of120TB128A (6). PROP RESYNCHROPHASE/

b. Momentarily hold PROP Repair open circuit betweenPROP SYNC switch.RESYNCHROPHASE/PROP PROP RESYNCHROPHASE/b. Momentarily hold PROPNO YESSYNC switch to RESYNC/INDEX. PROP SYNC switch terminal 4RESYNCHROPHASE/PROPIs 28 VDC present on terminal and terminal board TB128A ter-SYNC switch to RESYNC/INDEX.board terminal 17 while switch is minal 17. (See figure 3-6 or 3-Is 28 VDC present on switch ter-held? 7.) minal 4 while switch is held?

30 24

YES NO

121

Replace PROP RESYNCHROPHASE/PROP SYNC switch.

117

a. Gain access to terminal board TB1C (5).122b. Momentarily hold PROP RESYN-

CHROPHASE/PROP SYNC switch to Repair open circuit between terminalNORESYNC/INDEX. board TB1C terminal 9 and terminalIs 28 VDC present on terminal board termi- board TB128A terminal 17. (See fig-nal 9 while switch is held? ure 3-6 or 3-7.)

13

YES

123

Repair open circuit between terminalboard TB1C terminal 9 and pin 15 ofreceptacle J268A (4). (See figure 3-6or 3-7.)

NOTE




61-20-003-48

TO 1C-130H-2-61FI-00-1


61-20-003-49

TO 1C-130H-2-61FI-00-1

FROM SHT 27

124127Is a ground present on pin 2 of plug NO

P1258F (2)? Repair ground circuit. (See fig-ure 3-6.)

34

YES

125128

Is a ground present on plug pin 4? NORepair ground circuit. (See fig-ure 3-6.) 35

YES

126

Is there continuity between plug P1258F 129pin 3 and pin 34 of receptacle J267A YES

Replace constant voltage trans-(1)?former (3).

36 41

NO

130


NOTE




61-20-003-50

TO 1C-130H-2-61FI-00-1


61-20-003-51

TO 1C-130H-2-61FI-00-1

FROM SHT 25

131

a. Shut down engines in accor-dance with TO 1C-130H-2-71JG-00-1, 71-00-10; or TO 1C-130(A)H-2-71JG-00-1, 71-00-10.b. Place SYNCHROPHASE 134MASTER/MSTR switch (1) to en-

Repair open circuit betweengine 2 or engine 3. NOPROP RESYNCHROPHASE/c. Gain access to terminals ofPROP SYNC switch terminals 2PROP RESYNCHROPHASE/and 5. (See figure 3-6 or 3-7.) PROP SYNC switch (2).

Is 28 VDC present on PROPRESYNCHROPHASE/PROPSYNC switch terminal 2?

23

YES

132

Momentarily hold PROP RESYN-135CHROPHASE/PROP SYNC

switch to RESYNC/INDEX. Replace PROP RESYN-NOIs 28 VDC present on switch ter- CHROPHASE/PROP SYNCminal 1 while switch is held? switch.

26

YES

133

Momentarily hold PROP RESYN-136CHROPHASE/PROP SYNC

switch to RESYNC/INDEX. Repair open circuit betweenIs 28 VDC present on SYN- SYNCHROPHASE MASTER/NOCHROPHASE MASTER/MSTR MSTR switch terminal 5 andswitch terminal 5 while PROP PROP RESYNCHROPHASE/RESYNCHROPHASE/PROP PROP SYNC switch terminal 1.SYNC switch is held? (See figure 3-6 or 3-7.)

16

YES

137


NOTE



61-20-003-52

TO 1C-130H-2-61FI-00-1


61-20-003-53

TO 1C-130H-2-61FI-00-1

FROM SHT 3

138 141

Does RPM of all propellers (2) Replace propeller syn-YESfluctuate with propeller governor chrophaser in accordance withcontrol switch (3) in NORMAL/ TO 1C-130H-2-61JG-20-1, 61-NORM? 20-13.

NO

139 6120013 142

Does frequency meter (1) indicate Fault is in tachometer system.NOa fluctuation for the affected pro- Go to TO 1C-130H-2-70FI-00-1-peller? 1 and continue troubleshooting.

YES

140

Perform synchrophaser index in 143accordance with TO 1C-130H-2- YES

Synchrophaser index corrected61JG-10-1, 61-10-02 (subtask 1-malfunction. Secure system. 2-6).

Did RPM stabilize?

NO

TO SHT 47

NOTE




61-20-003-54

TO 1C-130H-2-61FI-00-1


61-20-003-55

TO 1C-130H-2-61FI-00-1

FROM SHT 3

144

If not previously done, performsynchrophaser check in accor-dance with TO 1C-130H-2-61JG-

NO10-1, 61-10-02 (subtask 1-2-9).TO SHT 109Did RPM of any slave propeller

(2) fail to decrease 1 to 3 percentas No. 3 throttle (1) was retardedto FLIGHT IDLE/FLT IDLE duringthe check?

YES

147145 Replace propeller syn-YES

Did all slave propellers fail to fol- chrophaser in accordance withlow either master? TO 1C-130H-2-61JG-20-1, 61-

20-13. NO

146 6120006

Perform pitchlock check in accor- NOdance with TO 1C-130H-2-61JG- TO SHT 4710-1, 61-10-02 (subtask 1-2-10).Was check satisfactory?

YES

TO SHT 109


61-20-003-56

TO 1C-130H-2-61FI-00-1


61-20-003-57

TO 1C-130H-2-61FI-00-1

FROM SHT 5

148 6120011

a. Perform synchrophaser index inaccordance with TO 1C-130H-2-61JG-10-1, 61-10-02 (subtask 1- 1512-6). NO

Synchrophaser index correctedb. Perform throttle anticipationmalfunction. Secure system.check in accordance with TO 1C-

130H-2-61JG-10-1, 61-10-02(subtask 1-2-8).Does fault persist?

YES

149

Perform propeller governor servo- 152bias clutch-brake check on affect-

Replace valve housing assem-NOed propeller (3) in accordance

bly in accordance with TO 1C-with TO 1C-130H-2-61JG-10-1,130H-61JG-20-1, 61-20-02. 61-10-02 (subtask 1-2-7).

Was RPM within limits?

YES

150

a. Perform synchrophaser index inaccordance with TO 1C-130H-2-61JG-10-1, 61-10-02 (subtask 1-2-6).b. Shut down engines in accor-dance with TO 1C-130H-2-71JG-00-1, 71-00-10; or TO 1C-130(A)H-2-71JG-00-1, 71-00-10. 153c. Move throttle (1) to MAXIMUM

Reseal dome assembly in ac-NOREVERSE/MAX RVS.

cordance with TO 1C-130H-2-d. Hold engine condition lever (2)61JG-10-1, 61-10-13. in AIR START until propeller

blades (3) stop moving (in reverseposition), then release.e. Place engine condition lever toFEATHER/FTR and time propellermovement.Does propeller go from full re-verse to full feather in 25 secondsor less?

YES

TO SHT 47


61-20-003-58

TO 1C-130H-2-61FI-00-1


61-20-003-59

TO 1C-130H-2-61FI-00-1

FROM SHT 25, 41, 43, OR 45

154

a. If necessary, shut down engines in accor-dance with TO 1C-130H-2-71JG-00-1, 71-00-10; or TO 1C-130(A)H-2-71JG-00-1, 71-00-10.b. Perform Preparation C.Does FUNCTION display (3) indicate 200 to300 and does AC VOLTS display (4) indicate NO3? TO SHT 49(Anticipator pot R)

Prop Sync Rcpt Pins1 J267A-18, J267A-452 J268A-19, J267A-453 J268A-20, J267A-454 J267A-19, J267A-45

YES

155157

Place RESISTANCE TEST switch (5) to 2. 158Gain access to and disconnectDoes FUNCTION display indicate 134 to 216Replace throttle an-plug P390 (1) at valve housingand does AC VOLTS display indicate 3?ticipation potenti-assembly.(Anticipator pot wiper R) NO NO ometer inIs 134K to 216K ohms resistanceaccordance withpresent between pins K and S ofProp Sync Rcpt PinsTO 1C-130H-2-valve housing assembly recepta-1 J267A-22, J267A-4561JG-20-1, 61-20-cle (2)?2 J267A-20, J267A-4517. 3 J267A-21, J267A-45 71 70

4 J267A-9, J267A-45

YESYES

TO SHT 53

156

Move throttle (6) to TAKE OFF. 159Does FUNCTION display indicate 24 to 58

Replace throttle an-and does AC VOLTS display indicate 3?ticipation potenti-(Anticipator pot wiper R in T/O pos)ometer inNOaccordance withProp Sync Rcpt PinsTO 1C-130H-2-1 J267A-22, J267A-4561JG-20-1, 61-20-2 J267A-20, J267A-4517. 3 J267A-21, J267A-45

4 J267A-9, J267A-45

YES

TO SHT 55

NOTE



61-20-003-60 Change 2

TO 1C-130H-2-61FI-00-1


61-20-003-61

TO 1C-130H-2-61FI-00-1

FROM SHT 47

160

Gain access to and disconnect164plug P390 (3) at valve housing

assembly. Replace throttle anticipation po-NOIs 200K to 300K ohms resistance tentiometer in accordance withpresent between pins K and T of TO 1C-130H-2-61JG-20-1, 61-valve housing receptacle (4)? 20-17.

71 72

YES

163161 165Gain access to and disconnect

Is a ground present on plug P390 Repair open circuit between pinplug P398 (2) at engine firewall.NO YESpin K? V of receptacle J239 (1) andIs a ground present on plug pin

plug P390 pin K. (See figure 3-V?716 or 3-7.)

59

YESNO

166

Repair ground circuit. (See fig-ure 3-6 or 3-7.)

162

a. Reconnect plug P390 at valvehousing assembly. 167b. Gain access to and disconnect

Repair wiring fault between re-plug P398 (2) at engine firewall. NOceptacle J239 pin T and plugIs 200K to 300K ohms resistanceP390 pin T. (See figure 3-6 orpresent between pins T and V of3-7.) receptacle J239 (1)?

60 59

YES

TO SHT 51

NOTE



61-20-003-62 Change 2

TO 1C-130H-2-61FI-00-1


61-20-003-63

TO 1C-130H-2-61FI-00-1

170

Repair wiring fault between pinFROM SHT 49T of plug P398 (1) and relatedpin of receptacle J268A (2).168(See figure 3-6 or 3-7.)NO


RcptProp Pin2 193 20

YES

169

a. Reconnect plug P398 (1) at en-gine firewall.b. Gain access to and disconnect 171plug P130/P1139 (4) at outer

Repair wiring fault between re-wing break. NOceptacle J235/J935 pin g andIs 200K to 300K ohms resistanceplug P398 pin T. (See figure 3-present between pin g of recepta-6 or 3-7.) cle J235/J935 (5) and airplane

ground?

48

YES

172

Repair wiring fault between plugP130/P1139 pin g and relatedpin of receptacle J267A (3).(See figure 3-6 or 3-7.)


NOTE




61-20-003-64

TO 1C-130H-2-61FI-00-1


61-20-003-65

TO 1C-130H-2-61FI-00-1

FROM SHT 47

173

a. Reconnect plug P390 (3) at valve housing as-sembly. 176b. Gain access to and disconnect plug P398 (2)

Repair wiring fault between receptacle J239 pinNOat engine firewall.

S and plug P390 pin S. (See figure 3-6 or 3-Is 134K to 216K ohms resistance present be-7.) tween pins S and V of receptacle J239 (1)?

58 59

YES

177

Repair wiring fault between plug P398 pin Sand related pin of receptacle J267A (4). (Seefigure 3-6 or 3-7.)174 NO

Is an outboard propeller being troubleshot? Rcpt

Prop Pin2 203 21

YES

175

a. Reconnect plug P398 at engine firewall.b. Gain access to and disconnect plug P130/

178P1139 (6) at outer wing break.Is 134K to 216K ohms resistance present be- Repair wiring fault between plug P398 pin Stween specified pin of receptacle J235/J935 (5) and related receptacle J235/J935 pin. (See fig-and airplane ground? ure 3-6 or 3-7.)NO

Rcpt Test RcptProp Pin Point Prop Pin

1 f1 f

474 c

4 c47

YES

179

Repair wiring fault between specified plugP130/P1139 pin and related pin of receptacleJ267A (4). (See figure 3-6 or 3-7.)

Plug RcptProp Pin Pin1 f 224 c 9

NOTE




61-20-003-66

TO 1C-130H-2-61FI-00-1


61-20-003-67

TO 1C-130H-2-61FI-00-1

FROM SHT 47

180

a. Move throttle (6) to FLIGHT IDLE/FLT IDLE.b. Place RESISTANCE TEST switch (5) to 3.Does FUNCTION display (3) indicate 8 to 11and does AC VOLTS display (4) indicate 3?(Feedback pot R) NO

TO SHT 57


YES

181183

Place RESISTANCE TEST switch to 4.Gain access to and discon-Does FUNCTION display indicate 1 to 10.5nect plug P390 (1) at valve 184and does AC VOLTS display indicate 3?housing assembly.(Feedback pot wiper R) Replace valve housingNO NOIs 1K to 10.5K ohms resis- assembly in accordancetance present between pinsProp Sync Rcpt Pins with TO 1C-130H-2-L and N of valve housing1 J267A-10, J267A-11 61JG-20-1, 61-20-02. assembly receptacle (2)?2 J268A-2, J268A-3

3 J268A-4, J268A-5 74 734 J267A-14, J267A-15

YESYES

TO SHT 63

182

Place RESISTANCE TEST switch to 5.Does FUNCTION display indicate 25 to 50 ohms?(Speed bias control winding R)

NOTO SHT 65Prop Sync Rcpt Pins


YES

TO SHT 71

NOTE



61-20-003-68

TO 1C-130H-2-61FI-00-1


61-20-003-69

TO 1C-130H-2-61FI-00-1

FROM SHT 55

185

Gain access to and disconnectplug P390 (3) at valve housing

188assembly.Is 8K to 11K ohms resistance pre- Replace valve housing assem-NOsent between pins C and L of bly in accordance with TO 1C-valve housing assembly recepta- 130H-2-61JG-20-1, 61-20-02. cle (4)?

75 74

YES

186 187

a. Reconnect plug P390 at valve a. Gain access to and disconnecthousing assembly. plug P390 at valve housing as- 189b. Gain access to and disconnect sembly. Remove jumper wire. RepairNO NOplug P398 (2) at engine firewall. b. Install a jumper wire between wiring fault between receptacleIs 8K to 11K ohms resistance pre- plug pins K and L. J239 pin W and plug P390 pinsent between pins C and W of re- Is there continuity between recep- L. (See figure 3-6 or 3-7.) ceptacle J239 (1)? tacle J239 pins V and W?

63 62 59 62

YES YES

TO SHT 59190

Remove jumper wire. Repairwiring fault between receptacleJ239 pin C and plug P390 pinC. (See figure 3-6 or 3-7.)

NOTE



61-20-003-70

TO 1C-130H-2-61FI-00-1


61-20-003-71

TO 1C-130H-2-61FI-00-1

FROM SHT 57

191YES

Is an outboard propeller being TO SHT 61troubleshot?

NO

192

a. Install a jumper wire between193pins V and W of plug P398 (1).

b. Remove junction box from syn- Remove jumper wire. Repairchrophaser rack. wiring fault between plug P398Is a ground present on specified pin W and related receptaclepin of receptacle J268A (2)? J268A pin. (See figure 3-6 orNO

3-7.)Rcpt Test


2 338

2 33 4

3 438

YES

194

Remove jumper wire. Repairwiring fault between plug P398pin C and related receptacleJ268A pin. (See figure 3-6 or3-7.)

RcptProp Pin2 13 6

NOTE




61-20-003-72

TO 1C-130H-2-61FI-00-1


61-20-003-73

TO 1C-130H-2-61FI-00-1

FROM SHT 59

195197

a. Reconnect plug P398 (1) at en-a. Install a jumper wire betweengine firewall.plug P130/P1139 pin j and air- 198b. Gain access to and disconnectplane ground.plug P130/P1139 (3) at outer Remove jumper wire. Repairb. Remove junction box from syn-wing break. wiring fault between plug P130/chrophaser rack.Is 8K to 11K ohms resistance pre- P1139 pin j and related recep-Is a ground present on specifiedsent between specified pins of re- tacle J267A pin. (See figure 3-YES NOpin of receptacle J267A (4)?ceptacle J235/J935 (2)? 6 or 3-7.)

Rcpt TestRcpt Test RcptProp Pin PointProp Pins Points Prop Pin

1 101 10

381 j and k

50 514 15

4 1538

4 j and e50 51

NOYES

199

Remove jumper wire. Repairwiring fault between specifiedplug P130/P1139 pin and relat-ed receptacle J267A pin. (Seefigure 3-6 or 3-7.)

Plug RcptProp Pin Pin1 k 124 e 13

200196Remove jumper wire. Repaira. Gain access to and disconnectwiring fault between plug P398plug P398 at engine firewall.pin C and related plug P130/b. Install a jumper wire betweenP1139 pin. (See figure 3-6 orYESplug pins V and W.3-7.)Is a ground present on receptacle

J235/J935 pin j?Plug

Prop Pin501 k4 eNO

201

Remove jumper wire. Repairwiring fault between receptacleJ235/J935 pin j and plug P398pin W. (See figure 3-6 or 3-7.)

NOTE




61-20-003-74

TO 1C-130H-2-61FI-00-1


61-20-003-75

TO 1C-130H-2-61FI-00-1

FROM SHT 55

202

a. Reconnect plug P390 (3) atvalve housing assembly. 205b. Gain access to and disconnect

Repair wiring fault between re-plug P398 (2) at engine firewall. NOceptacle J239 pin N and plugIs 1K to 10.5K ohms resistanceP390 pin N. (See figure 3-6 orpresent between pins N and W of3-7.) receptacle J239 (1)?

61 62

YES

206

Repair wiring fault between plugP398 pin N and related pin ofreceptacle J268A (4). (See fig-203ure 3-6 or 3-7.)NO


RcptProp Pin2 23 5

YES

204

a. Reconnect plug P398 at enginefirewall.

207b. Gain access to and disconnectplug P130/P1139 (7) at outer Repair wiring fault between re-NOwing break. ceptacle J235/J935 pin h andIs 1K to 10.5K ohms resistance plug P398 pin N. (See figure 3-present between pins h and j of 6 or 3-7.) receptacle J235/J935 (6)?

49 50

YES

208

Repair wiring fault between plugP130/P1139 pin h and relatedpin of receptacle J267A (5).(See figure 3-6 or 3-7.)


NOTE




61-20-003-76

TO 1C-130H-2-61FI-00-1


61-20-003-77

TO 1C-130H-2-61FI-00-1

FROM SHT 55

209


212assembly.Is 25 to 50 ohms resistance pre- Replace valve housing assem-NOsent between pins B and M of bly in accordance with TO 1C-valve housing assembly recepta- 130H-2-61JG-20-1, 61-20-02. cle (4)?

68 67

YES

210 211

a. Reconnect plug P390 at valve a. Gain access to and disconnecthousing assembly. plug P390 at valve housing as- 213b. Gain access to and disconnect sembly. Remove jumper wire. RepairNO YESplug P398 (2) at engine firewall. b. Install a jumper wire between open circuit between receptacleIs 25 to 50 ohms resistance pre- plug pins K and M. J239 pin B and plug P390 pinsent between pins B and X of re- Is there continuity between recep- B. (See figure 3-6 or 3-7.) ceptacle J239 (1)? tacle J239 pins V and X?

56 55 59 55

YES NO

TO SHT 67214

Remove jumper wire. Repairopen circuit between receptacleJ239 pin X and plug P390 pinM. (See figure 3-6 or 3-7.)

NOTE



61-20-003-78

TO 1C-130H-2-61FI-00-1


61-20-003-79

TO 1C-130H-2-61FI-00-1

FROM SHT 65

215YES


NO

216

a. Install a jumper wire betweenpins B and V of plug P398 (1).

217b. Remove junction box from syn-chrophaser rack. Remove jumper wire. RepairIs a ground present on specified open circuit between plug P398pin of receptacle J267A (3) or pin X and related receptacleJ268A (2)? pin. (See figure 3-6 or 3-7.)YES

Rcpt Test RcptProp Pin Point Prop Pin

2 J268A-252 J268A-26

373 J267A-37

3 J267A-3837

NO

218

Remove jumper wire. Repairopen circuit between plug P398pin B and related receptaclepin. (See figure 3-6 or 3-7.)

RcptProp Pin2 J268A-263 J267A-38

NOTE




61-20-003-80

TO 1C-130H-2-61FI-00-1


61-20-003-81

TO 1C-130H-2-61FI-00-1


61-20-003-82

TO 1C-130H-2-61FI-00-1


61-20-003-83

TO 1C-130H-2-61FI-00-1

FROM SHT 55

226

Place RESISTANCE TEST switch (4) to 6.Does FUNCTION display (2) indicate 120 to 180ohms?(Speed bias ref winding R) NO

TO SHT 73Prop Sync Rcpt Pins1 J267A-40, J267A-452 J268A-23, J267A-453 J268A-24, J267A-454 J267A-39, J267A-45

YES

227

Move throttles (1) below GROUND IDLE/GNDIDLE.

229Do FUNCTION display (2) and AC VOLTS dis-play (3) indicate 1999? Adjust or replace syn-(Sync disarming switch) chrophaser disarming switch (6)NO

as required in accordance withProp Sync Rcpt Pins TO 1C-130H-2-76JG-00-1, 76-1 J267A-40, J267A-45 10-38. 2 J268A-23, J267A-453 J268A-24, J267A-454 J267A-39, J267A-45

YES

228

a. Move throttles above FLIGHT IDLE/FLT IDLE.b. Place propeller governor control switches (5) toMECH GOV/MECH.Does FUNCTION display indicate 1999? 230(propeller governor control switch) NO

Replace propeller governor con-trol switch. Prop Sync Rcpt Pins


YES

TO SHT 81

NOTE




61-20-003-84

TO 1C-130H-2-61FI-00-1


61-20-003-85

TO 1C-130H-2-61FI-00-1

FROM SHT 71

231

Gain access to and disconnect plug P390 (3)235at valve housing assembly.

Is 120 to 180 ohms resistance present be- Replace valve housing assem-NOtween pins A and K of valve housing assembly in accordance with TO 1C-bly receptacle (4)? 130H-2-61JG-20-1, 61-20-02.

69 71

YES

232

a. Reconnect plug P390 at valve housing as-236sembly.

b. Gain access to and disconnect plug P398 Repair open circuit between re-NO(2) at engine firewall. ceptacle J239 pin A and plugIs 120 to 180 ohms resistance present be- P390 pin A. (See figure 3-6 ortween pins A and V of receptacle J239 (1)? 3-7.)

57 59

YES

233

a. Reconnect plug P398 at engine firewall.b. Disengage junction box from synchrophaserrack.

NOc. Gain access to terminals of propeller gover-TO SHT 75nor control switch (5).

Is 120 to 180 ohms resistance present be-tween switch terminal 3 and airplane ground?

86

YES

234237Is there continuity between switch terminals 2

NOand 3? Replace propeller governor con-trol switch.

85 86

YES

TO SHT 77

NOTE





61-20-003-86

TO 1C-130H-2-61FI-00-1


61-20-003-87

TO 1C-130H-2-61FI-00-1

FROM SHT 73 240

Repair open circuit between ter-238minal 3 of propeller governorNO

Is an outboard propeller beingcontrol switch (4) and pin A oftroubleshot? plug P398 (1). (See figure 3-6or 3-7.) YES

239

Gain access to and disconnectplug P130/P1139 (3) at outer 241wing break.

Repair open circuit between pinIs 120 to 180 ohms resistanceA of plug P398 (1) and relatedpresent between specified pin ofreceptacle J235/J935 pin. (Seereceptacle J235/J935 (2) and air-figure 3-6 or 3-7.)NO

plane ground?

RcptRcpt TestProp PinProp Pin Point1 e4 k1 e

46

4 k46

YES

242

Repair open circuit between ter-minal 3 of propeller governorcontrol switch (4) and relatedplug P130/P1139 pin. (See fig-ure 3-6 or 3-7.)

PlugProp Pin1 e4 k

NOTE





61-20-003-88

TO 1C-130H-2-61FI-00-1


61-20-003-89

TO 1C-130H-2-61FI-00-1

FROM SHT 73

243

Gain access to terminal boardTB126A (2).

245Is 120 to 180 ohms resistancepresent between specified termi- Repair open circuit between terminalnal and airplane ground? 2 of propeller governor control switch

(4) and related terminal boardTB Test TB126A terminal. (See figure 3-6 orNO

Prop Term Point 3-7.)

1 3684

TB TBProp Term Prop Term

2 3784

1 36 3 382 37 4 39

3 3884

4 3984

YES

244

Gain access to specified terminalboard. 246Is 120 to 180 ohms resistance

Repair open circuit between specifiedpresent between specified termi-terminal and related pin of receptaclenal and airplane ground?J267A (6) or J268A (5). (See figure3-6 or 3-7.)Test

YESProp TB-Term Point

RcptProp TB-Term Pin1 TB135A (1) -169

811 TB135A-169 J267A-402 TB135A-170 J268A-232 TB135A (1) -170

813 TB146A-210 J268A-244 TB146A-211 J267A-393 TB146A (3) -210

81

4 TB146A (3) -21181

NO

TO SHT 79

NOTE

1 Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024, except MC-130E airplanes.





61-20-003-90

TO 1C-130H-2-61FI-00-1


61-20-003-91

TO 1C-130H-2-61FI-00-1

FROM SHT 77 249

Repair open circuit between247synchrophaser disarming switchGain access to terminals of syn-terminal 2NC and related termi-chrophaser disarming switch (3).nal of terminal board TB126AIs 120 to 180 ohms resistance NO(1). (See figure 3-6 or 3-7.)present between switch terminal

2NC and airplane ground?TB TB

Prop Term Prop Term831 36 3 382 37 4 39YES

250

Repair open circuit betweensynchrophaser disarming switch248terminal 1NC and related termi-Is 120 to 180 ohms resistancenal. (See figure 3-6 or 3-7.)present between switch terminal YES

1NC and airplane ground?Prop TB-Term1 TB135A (4) -169822 TB135A (4) -1703 TB146A (2) -2104 TB146A (2) -211

NO

251

Adjust or replace syn-chrophaser disarming switch asrequired in accordance with TO1C-130H-2-76JG-00-1, 76-10-38.

NOTE



61-20-003-92

TO 1C-130H-2-61FI-00-1


61-20-003-93

TO 1C-130H-2-61FI-00-1

FROM SHT 71

252NO


YES

253

a. Place TYPE SELECT switch(2) to TUBE.b. Place RESISTANCE TESTswitch (3) to 8.

YESDoes FUNCTION display (1) indi-TO SHT 89cate 30 to 45 ohms?

(Clutch 1 and 4 winding parallelR)

Prop Sync Rcpt Pins1,4 J268A-15, J267A-45

NO

TO SHT 107


61-20-003-94

TO 1C-130H-2-61FI-00-1


61-20-003-95

TO 1C-130H-2-61FI-00-1

256

a. Place TYPE SELECT switch(4) to TUBE.b. Place RESISTANCE TESTswitch (5) to 8.c. Place SYNCHROPHASE

FROM SHT 81 MASTER/MSTR switch (2) toENG 2.

254 d. Momentarily hold PROPNO NOIs No. 2 propeller (1) being TO SHT 85RESYNCHROPHASE/PROPtroubleshot? SYNC switch (3) to RESYNC/IN-

DEX.Does FUNCTION display (6) indi-cate 20 to 30 ohms while switchis held?(Clutch 3 winding R)


YES

YES

TO SHT 89

255

a. Place TYPE SELECT switch(4) to TUBE.b. Place RESISTANCE TESTswitch (5) to 8.c. Place SYNCHROPHASEMASTER/MSTR switch (2) to en-gine 3.d. Momentarily hold PROP NORESYNCHROPHASE/PROP TO SHT 87SYNC switch (3) to RESYNC/IN-DEX.Does FUNCTION display (6) indi-cate 20 to 30 ohms while switchis held?(Clutch 2 winding R)


YES

TO SHT 89


61-20-003-96

TO 1C-130H-2-61FI-00-1


61-20-003-97

TO 1C-130H-2-61FI-00-1

FROM SHT 83

257

Gain access to and disconnect plug P390C (6)261at valve housing assembly.

Is 60 to 90 ohms resistance present between Replace valve housing assembly in accor-NOpins K and P of valve housing assembly re- dance with TO 1C-130H-2-61JG-20-1, 61-ceptacle (5)? 20-02.

71 76

YES

258

a. Reconnect plug P390C to valve housing as-sembly. 262b. Gain access to and disconnect plug P398C

Repair open circuit between receptacleNO(2) at engine firewall.J239C pin P and plug P390C pin P. (SeeIs 60 to 90 ohms resistance present betweenfigure 3-6.) pins P and V of receptacle J239C (1)?

64 59

YES

259

a. Reconnect plug P398C at engine firewall.b. Gain access to terminals of SYN- 263CHROPHASE MASTER/MSTR switch (3). NO

Replace SYNCHROPHASE MASTER/MSTRIs there continuity between switch terminals 4switch.and 5?

20 16

YES

260

Gain access to terminal board TB128A (4). 264Is there continuity between terminal board ter-

Repair open circuit between terminal boardYESminal 18 and SYNCHROPHASE MASTER/terminal 18 and plug P398C pin P. (SeeMSTR switch terminal 4?figure 3-6 or 3-7.)

31 20

NO

265

Repair open circuit. (See figure 3-6 or 3-7.)

NOTE



61-20-003-98

TO 1C-130H-2-61FI-00-1


61-20-003-99

TO 1C-130H-2-61FI-00-1

FROM SHT 83

266

Gain access to and disconnect plug P390B (6)270at valve housing assembly.

Is 60 to 90 ohms resistance present between Replace valve housing assembly in accor-NOpins K and P of valve housing assembly re- dance with TO 1C-130H-2-61JG-20-1, 61-ceptacle (5)? 20-02.

71 76

YES

267

a. Reconnect plug P390B to valve housing as-sembly. 271b. Gain access to and disconnect plug P398B

Repair open circuit between receptacleNO(2) at engine firewall.J239B pin P and plug P390B pin P. (SeeIs 60 to 90 ohms resistance present betweenfigure 3-6 or 3-7.) pins P and V of receptacle J239B (1)?

64 59

YES

268

a. Reconnect plug P398B at engine firewall.b. Gain access to terminals of SYN- 272CHROPHASE MASTER/MSTR switch (3). NO

Replace SYNCHROPHASE MASTER/MSTRIs there continuity between switch terminals 5switch.and 6?

16 21

YES

269

Gain access to terminal board TB128A (4). 273Is there continuity between terminal board ter-

Repair open circuit between terminal boardYESminal 19 and SYNCHROPHASE MASTER/terminal 19 and plug P398B pin P. (SeeMSTR switch terminal 6?figure 3-6 or 3-7.)

32 21

NO

274


NOTE



61-20-003-100

TO 1C-130H-2-61FI-00-1


61-20-003-101

TO 1C-130H-2-61FI-00-1

FROM SHT 81 OR 83

275

NOTEDuring megger checks, an indica-tion of 1999 in both the FUNC-TION and AC VOLTS displays isan acceptable measurement.

a. Place SYNCHROPHASEMASTER/MSTR switch (5) toOFF.b. Place TYPE SELECT switch

NO(2) to SOLID STATE.TO SHT 91c. Place RESISTANCE TEST

switch (4) to 13.Does FUNCTION display (1) indi-cate 0.5 or greater and does ACVOLTS display (3) indicate 6?(Control winding megger chk)


YES

276

Place RESISTANCE TEST switchto 14.Does FUNCTION display indicate1.0 or greater and does ACVOLTS display indicate 6? NO(Feedback pot megger chk) TO SHT 99


YES

TO SHT 141


61-20-003-102

TO 1C-130H-2-61FI-00-1


61-20-003-103

TO 1C-130H-2-61FI-00-1

FROM SHT 89

277

a. Gain access to and disconnect281plug P390 (3) at valve housing

assembly. Remove jumper wire. ReplaceYESb. Install a jumper wire between valve housing assembly in ac-plug pins B and M. cordance with TO 1C-130H-2-Does FUNCTION display (5) indi- 61JG-20-1, 61-20-02.cate 0.5 or greater and does ACVOLTS display (4) indicate 6?

NO

278

a. Remove jumper wire from plugP390 but do not reconnect plug.b. Gain access to and disconnect 280

NO NOplug P398 (2) at engine firewall.TO SHT 93Is an outboard propeller beingc. Install a jumper wire between

troubleshot?plug P398 pins B and X.Does FUNCTION display indicate0.5 or greater and does ACVOLTS display indicate 6?

YES

YES

TO SHT 95

279282Remove jumper wire from plug

P398 and reconnect plug at en- Repair ground fault between pinNOgine firewall. X of receptacle J239 (1) andDoes FUNCTION display indicate plug P390 pin M. (See figure0.5 or greater and does AC 3-6 or 3-7.) VOLTS display indicate 6?

YES

283

Repair ground fault between pinB of receptacle J239 (1) andplug P390 pin B. (See figure 3-6 or 3-7.)


61-20-003-104

TO 1C-130H-2-61FI-00-1


61-20-003-105

TO 1C-130H-2-61FI-00-1

285FROM SHT 91

Repair ground fault between284 plug P398 pin X and related pin

Remove jumper wire from plug of receptacle J267A (3) orP398 (1) but do not reconnect J268A (2). (See figure 3-6 or 3-NOplug. 7.) Does FUNCTION display (5) indi-cate 0.5 or greater and does AC RcptVOLTS display (4) indicate 6? Prop Pin

2 J268A-253 J267A-37YES

286

Repair ground fault betweenplug P398 pin B and related pinof receptacle J267A (3) orJ268A (2). (See figure 3-6 or3-7.)

RcptProp Pin2 J268A-263 J267A-38

NOTE



61-20-003-106

TO 1C-130H-2-61FI-00-1


61-20-003-107

TO 1C-130H-2-61FI-00-1

FROM SHT 91

287

a. Remove jumper wire from plugP398 (1) but do not reconnectplug.b. Gain access to and disconnectplug P130 (5) at outer wing break.c. Install a jumper wire betweenspecified plug pins. NO

TO SHT 97Plug

Prop Pins1 c and d4 d and f

Does FUNCTION display (3) indi-cate 0.5 or greater and does ACVOLTS display (2) indicate 6?

YES

289

Repair ground fault between288plug P398 pin X and related pinRemove jumper wire from plugof receptacle J235 (4). (SeeP130 and reconnect plug at outerfigure 3-6 or 3-7.)NO

wing break.Does FUNCTION display indicate

Rcpt0.5 or greater and does ACProp PinVOLTS display indicate 6?1 c4 dYES

290

Repair ground fault betweenplug P398 pin B and related pinof receptacle J235 (4). (Seefigure 3-6 or 3-7.)

RcptProp Pin1 d4 f


61-20-003-108

TO 1C-130H-2-61FI-00-1


61-20-003-109

TO 1C-130H-2-61FI-00-1

292FROM SHT 95

Repair ground fault between291 specified plug P130/P1139 pin

Remove jumper wire from plug and related pin of receptacleP130/P1139 (5) but do not recon- J267A (4) or J268A (3). (SeeYESnect plug. figure 3-6 or 3-7.)Does FUNCTION display (1) indi-cate 0.5 or greater and does AC Plug RcptVOLTS display (2) indicate 6? Prop Pin Pin

1 d J267A-364 f J268A-28NO

293

Repair ground fault betweenspecified plug P130/P1139 pinand related pin of receptacleJ267A (4) or J268A (3). (Seefigure 3-6 or 3-7.)

Plug RcptProp Pin Pin1 c J267A-354 d J268A-27

NOTE



61-20-003-110

TO 1C-130H-2-61FI-00-1


61-20-003-111

TO 1C-130H-2-61FI-00-1

FROM SHT 89

294 300297a. Gain access to and disconnect plug Remove jumper

P390 (3) at valve housing assembly. wire. ReplaceRemove jumper wire and install it be-YES YESb. Install a jumper wire between plug valve housing intween plug pins C and N.

pins C and L. accordance withDoes FUNCTION display indicate 1.0 orDoes FUNCTION display (5) indicate TO 1C-130H-2-greater and does AC VOLTS display in-1.0 or greater and does AC VOLTS dis- 61JG-20-1, 61-20-dicate 6? play (4) indicate 6? 02.

NONO

298 301

a. Remove jumper wire from plug P390. Remove jumperb. Gain access to and disconnect plug wire. RepairP398 (2) at engine firewall. ground fault be-YESc. Install jumper wire between plug tween pin N of re-P398 pins C and N. ceptacle J239 (1)Does FUNCTION display indicate 1.0 or and plug P390 pingreater and does AC VOLTS display in- N. (See figure 3-6dicate 6? or 3-7.)

NO

TO SHT 101

302299295Repair ground faulta. Remove jumper wire from plug P390.Remove jumper wire and install it be-between pin C ofb. Gain access to and disconnect plugNO YEStween plug pins C and N.receptacle J239 (1)P398 (2) at engine firewall.Does FUNCTION display indicate 1.0 orand plug P390 pinDoes FUNCTION display indicate 1.0 orgreater and does AC VOLTS display in-C. (See figure 3-6greater and does AC VOLTS display in-dicate 6?or 3-7.) dicate 6?

YESNO

TO SHT 103

296 303

a. Remove jumper wire from plug P390. Remove jumperb. Gain access to and disconnect plug wire. RepairP398 (2) at engine firewall. ground fault be-YESc. Install jumper wire between plug tween pin W of re-P398 pins C and W. ceptacle J239 (1)Does FUNCTION display indicate 1.0 or and plug P390 pingreater and does AC VOLTS display in- L. (See figure 3-6dicate 6? or 3-7.)

NO

TO SHT 105


61-20-003-112

TO 1C-130H-2-61FI-00-1


61-20-003-113

TO 1C-130H-2-61FI-00-1

306

Remove jumper wire. RepairFROM SHT 99 ground fault between pin N of

plug P398 (1) and related pin of304 receptacle J268A (4). (See fig-NO

Is an outboard propeller being ure 3-6 or 3-7.)troubleshot?

RcptProp Pin2 23 5

YES

305

a. Remove jumper wire from plugP398 (1).

307b. Gain access to and disconnectplug P130/P1139 (7) at outer Remove jumper wire. Repairwing break. ground fault between plugc. Install jumper wire between P130/P1139 pin h and relatedspecified plug P130/P1139 pins. pin of receptacle J267A (5).NO

(See figure 3-6 or 3-7.)Plug

Prop Pin Rcpt1 h and k Prop Pin4 e and h 1 11

4 14Does FUNCTION display (2) indi-cate 1.0 or greater and does ACVOLTS display (3) indicate 6?

YES

308

Remove jumper wire. Repairground fault between pin h ofreceptacle J235/J935 (6) andplug P398 pin N. (See figure 3-6 or 3-7.)

NOTE



61-20-003-114

TO 1C-130H-2-61FI-00-1


61-20-003-115

TO 1C-130H-2-61FI-00-1

311

Repair ground fault between pinFROM SHT 99C of plug P398 (1) and relatedpin of receptacle J268A (4).309(See figure 3-6 or 3-7.)NO


RcptProp Pin2 13 6

YES

312

Repair ground fault between310 specified plug P130/P1139 pin

Gain access to and disconnect and related pin of receptacleplug P130/P1139 (6) at outer J267A (5). (See figure 3-6 orNOwing break. 3-7.)Does FUNCTION display (2) indi-cate 1.0 or greater and does AC Plug RcptVOLTS display (3) indicate 6? Prop Pin Pin

1 k 124 e 13YES

313

Repair ground fault between pinC of plug P398 (1) and relatedplug P130/P1139 pin. (See fig-ure 3-6 or 3-7.)

PlugProp Pin1 k4 e

NOTE



61-20-003-116

TO 1C-130H-2-61FI-00-1


61-20-003-117

TO 1C-130H-2-61FI-00-1

316

Remove jumper wire. RepairFROM SHT 99 ground fault between pin W of

plug P398 (1) and related pin of314 receptacle J268A (4). (See fig-NO

Is an outboard propeller being ure 3-6 or 3-7.)troubleshot?

RcptProp Pin2 33 4

YES

315


317b. Gain access to and disconnectplug P130/P1139 (7) at outer Remove jumper wire. Repairwing break. ground fault between plugc. Install jumper wire between P130/P1139 pin j and relatedspecified plug P130/P1139 pins. pin of receptacle J267A (5).NO

(See figure 3-6 or 3-7.)Plug

Prop Pin Rcpt1 j and k Prop Pin4 e and j 1 10


YES

318

Remove jumper wire. Repairground fault between pin j of re-ceptacle J235/J935 (6) and plugP398 pin W. (See figure 3-6 or3-7.)

NOTE



61-20-003-118

TO 1C-130H-2-61FI-00-1


61-20-003-119

TO 1C-130H-2-61FI-00-1

FROM SHT 81

319


322assembly.Is 60 to 90 ohms resistance pre- Replace valve housing assem-NOsent between pins K and P of bly in accordance with TO 1C-valve housing assembly recepta- 130H-2-61JG-20-1, 61-20-02. cle (4)?

71 76

YES

320

a. Reconnect plug P390 to valve323housing assembly.

b. Gain access to and disconnect Repair open circuit between pinNOplug P398 (2) at engine firewall. P of receptacle J239 (1) andIs 60 to 90 ohms resistance pre- plug P390 pin P. (See figure 3-sent between plug pins P and V? 6 or 3-7.)

64 59

YES

321

a. Reconnect plug P398 at enginefirewall.b. Gain access to and disconnect 324plug P130/P1139 (7) at outer

Repair open circuit between re-wing break. NOceptacle J235/J935 pin m andIs 60 to 90 ohms resistance pre-plug P398 pin P. (See figure 3-sent between pin m of receptacle6 or 3-7.) J235/J935 (6) and airplane

ground?

52

YES

325

Repair open circuit betweenplug P130/P1139 pin m and ter-minal 9 of terminal board TB1C(5). (See figure 3-6 or 3-7.)

NOTE




61-20-003-120

TO 1C-130H-2-61FI-00-1


61-20-003-121

TO 1C-130H-2-61FI-00-1

FROM SHT 3 OR 43

326 6120007, 6120008,6120009, 6120010

a. Shut down engines in accordance 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-130(M)H-2-71JG-00-1, 71-00-10.b. If necessary, perform Preparation C.c. If necessary, place propeller governor controlswitches (5) to NORMAL/NORM. NOd. Place RESISTANCE TEST switch (4) to 7. TO SHT 111Does FUNCTION display (1) indicate 0.3 to 10ohm?(Pulse gen R)


YES

327

NOTEDuring megger checks, an indication of 1999 inboth the FUNCTION and AC VOLTS displays isan acceptable measurement.

a. Place SYNCHROPHASE MASTER/MSTRswitch (6) to OFF.b. Place TYPE SELECT switch (2) to SOLIDSTATE. NOc. Place RESISTANCE TEST switch to 12. TO SHT 125Does FUNCTION display (1) indicate 1.0 orgreater and does AC VOLTS display (3) indicate6?(Pulse gen megger chk)


YES

TO SHT 141

NOTE




61-20-003-122

TO 1C-130H-2-61FI-00-1


61-20-003-123

TO 1C-130H-2-61FI-00-1

FROM SHT 109

328 330

Gain access to and disconnect Remove pulse generator (4) in ac-plug P392 (2) at pump housing. cordance with TO 1C-130H-2- 332Is 0.3 to 0.5 ohm resistance pre- 61JG-20-1, 61-20-10.NO NO Replace pulse generator in ac-sent between pins A and B of Is 0.3 to 0.5 ohm resistance pre- cordance with TO 1C-130H-2-valve housing assembly recepta- sent between the two pulse gen- 61JG-20-1, 61-20-10.cle (3)? erator pins?

77 78 79 80

YES YES

333

Repair or replace pulse genera-tor wiring on pump housing (5).

329 331

a. Reconnect plug P392 to pump a. Gain access to and disconnecthousing. plug P392 at pump housing. 334b. Gain access to and disconnect b. Install a jumper wire between Remove jumper wire. RepairNO NOplug P396 (6) at engine firewall. plug pins A and E (ground). wiring fault between receptacleIs 0.3 to 0.5 ohm resistance pre- Is resistance between receptacle J241 pin A and plug P392 pinsent between pins A and B of re- J241 pins A and E less than 1 A. (See figure 3-6 or 3-7.) ceptacle J241 (1)? ohm?

65 66 65

YES YES

TO SHT 113335

Remove jumper wire. Repairwiring fault between receptacleJ241 pin B and plug P392 pinB. (See figure 3-6 or 3-7.)

NOTE



61-20-003-124

TO 1C-130H-2-61FI-00-1


61-20-003-125

TO 1C-130H-2-61FI-00-1

FROM SHT 111

336YES

Is airplane being troubleshot TO SHT 115AF90-1057 and up?

NO

337NO


YES

338

a. Reconnect plug P396 (1) at en-gine firewall.b. Gain access to and disconnect

YESplug P429 (3) at outer wing break.TO SHT 123Is 0.3 to 0.7 ohm resistance pre-

sent between pins A and B of re-ceptacle J269 (2)?

53 54

NO

339

a. Gain access to and disconnectplug P396 at engine firewall. 340b. Install a jumper wire between

Remove jumper wire. Repairplug pins A and E (ground). NOwiring fault between receptacleIs resistance between receptacleJ269 pin A and plug P396 pinJ269 pin A and airplane groundA. (See figure 3-6.)less than 1 ohm?

53

YES

341

Remove jumper wire. Repairwiring fault between receptacleJ269 pin B and plug P396 pinB. (See figure 3-6.)

NOTE

See figure 3-6 for:


61-20-003-126

TO 1C-130H-2-61FI-00-1


61-20-003-127

TO 1C-130H-2-61FI-00-1

FROM SHT 113 343

a. Gain access to and disconnect342 plug P396 at engine firewall.

a. Reconnect plug P396 (1) at en- b. Install a jumper wire betweengine firewall. plug pins A and E (ground). 344b. Gain access to terminal board c. Remove junction box from syn- Remove jumper wire. RepairTB105AG (2). chrophaser rack. wiring fault between specifiedIs 0.3 to 0.7 ohm resistance pre- Is resistance between specified receptacle pin and related ter-sent between specified terminals? pin of receptacle J267A (4) or minal board TB105AG terminal.

J268A (3) and airplane ground (See figure 3-6 or 3-7.)YES NOTB Test less than 1 ohm?Prop Term Points

Rcpt TBRcpt Test Prop Pin Term1 1 and 2

43 42Prop Pin Point 1 J267A-23 2

2 J268A-18 42 3 and 443 42

1 J267A-2339

3 J268A-17 64 J267A-25 83 5 and 6

43 422 J268A-18

39

4 7 and 843 42

3 J268A-1739

4 J267A-2539NO

YES

TO SHT 117345

Remove jumper wire. Repairwiring fault between specifiedreceptacle pin and related ter-minal board TB105AG terminal.(See figure 3-6 or 3-7.)

Rcpt TBProp Pin Term1 J267A-17 12 J268A-11 33 J268A-21 54 J267A-43 7

NOTE



61-20-003-128

TO 1C-130H-2-61FI-00-1


61-20-003-129

TO 1C-130H-2-61FI-00-1

348

a. Gain access to and disconnectplug P396 (1) at engine firewall. 350b. Install a jumper wire between Remove jumper wire. Repairplug pins A and E (ground).FROM SHT 115 wiring fault between plug P396Is resistance between specified pin A and related terminalterminal of terminal board346 board TB105AG terminal. (SeeNO NOTB105AG (2) and airplane groundIs an outboard propeller being figure 3-6 or 3-7.)less than 1 ohm?troubleshot?

TBTB Test Prop Term

Prop Term Point 2 43 6

2 442

3 642

YES

YES351

Remove jumper wire. Repairwiring fault between plug P396pin B and related terminalboard TB105AG terminal. (Seefigure 3-6 or 3-7.)

TBProp Term2 33 5

349347a. Gain access to and disconnectGain access to and disconnectplug P396 at engine firewall. 352plug P429/P1225 (3) at outerb. Install a jumper wire betweenwing break. Remove jumper wire. RepairNO NOplug pins A and E (ground).Is 0.3 to 0.7 ohm resistance pre- wiring fault between receptacleIs resistance between receptaclesent between pins A and B of re- J269/J660 pin A and plug P396J269/J660 pin A and airplaneceptacle J269/J660 (4)? pin A. (See figure 3-6 or 3-7.) ground less than 1 ohm?

53 5453

YESYES

TO SHT 119353

Remove jumper wire. Repairwiring fault between receptacleJ269/J660 pin B and plug P396pin B. (See figure 3-6 or 3-7.)

NOTE



61-20-003-130

TO 1C-130H-2-61FI-00-1


61-20-003-131

TO 1C-130H-2-61FI-00-1

FROM SHT 117

354

a. Gain access to and disconnectplug P429/P1225 (1) at outer

355wing break.b. Install a jumper wire between Remove jumper wire. Repairplug pin A and airplane ground. wiring fault between plug P429/Is resistance between specified P1225 pin A and related termi-terminal of terminal board nal board TB105AG terminal.NOTB105AG (2) and airplane ground (See figure 3-6 or 3-7.)less than 1 ohm?

TBTB Test Prop Term

Prop Term Point 1 24 8

1 242

4 842

YES

356

Remove jumper wire. Repairwiring fault between plug P429/P1225 pin B and related termi-nal board TB105AG terminal.(See figure 3-6 or 3-7.)

TBProp Term1 14 7

NOTE



61-20-003-132

TO 1C-130H-2-61FI-00-1


61-20-003-133

TO 1C-130H-2-61FI-00-1

FROM SHT 113

357

a. Install a jumper wire betweenpins A and E (ground) of plug

358P396 (1).b. Remove junction box from syn- Remove jumper wire. Repairchrophaser rack. wiring fault between plug P396Is resistance on specified pin of pin A and related receptaclereceptacle J268A (2) less than 1 J268A pin. (See figure 3-6.)NOohm?

RcptRcpt Test Prop Pin

Prop Pin Point 2 183 17

2 1839

3 1739

YES

359

Remove jumper wire. Repairwiring fault between plug P396pin B and related receptacleJ268A pin. (See figure 3-6).


NOTE




61-20-003-134

TO 1C-130H-2-61FI-00-1


61-20-003-135

TO 1C-130H-2-61FI-00-1

FROM SHT 113

360

a. Install a jumper wire betweenpin A of plug P429 (1) and air-

361plane ground.b. Remove junction box from syn- Remove jumper wire. Repairchrophaser rack. wiring fault between plug P429Is resistance on specified pin of pin A and related receptaclereceptacle J267A (2) less than 1 J267A pin. (See figure 3-6.)NOohm?

RcptRcpt Test Prop Pin

Prop Pin Point 1 234 25

1 2339

4 2539

YES

362

Remove jumper wire. Repairwiring fault between plug P429pin B and related receptacleJ267A pin. (See figure 3-6).


NOTE




61-20-003-136

TO 1C-130H-2-61FI-00-1


61-20-003-137

TO 1C-130H-2-61FI-00-1

366FROM SHT 109 a. Remove jumper wire from plug

P392 and reconnect plug at pump363 housing.

a. Gain access to and disconnect b. Remove pulse generator (3) in 368plug P392 (2) at pump housing. accordance with TO 1C-130H-2- Remove jumper wire. ReplaceYES YESb. Install a jumper wire between 61JG-20-1, 61-20-10. pulse generator in accordanceplug pins A and B. c. Install a jumper wire between with TO 1C-130H-2-61JG-20-1,Does FUNCTION display (5) indi- the two pins of the pulse genera- 61-20-10.cate 1.0 or greater and does AC tor wiring harness where theVOLTS display (4) indicate 6? pulse generator connects.

Does FUNCTION display indicate1.0 or greater and does ACVOLTS display indicate 6?

NO

NO369

Repair or replace pulse genera-tor wiring on pump housing.

364

a. Remove jumper wire from plug 367P392 but do not reconnect plug. 370Remove jumper wire from plugb. Gain access to and disconnect

Repair ground fault between pinP396 and reconnect plug at en-YES NOplug P396 (6) at engine firewall.A of receptacle J241 (1) andgine firewall.c. Install a jumper wire betweenplug P392 pin A. (See figure 3-Does FUNCTION display indicateplug P396 pins A and B.6 or 3-7.) 1.0 or greater and does ACDoes FUNCTION display indicate

VOLTS display indicate 6?1.0 or greater and does ACVOLTS display indicate 6?

NO

YES

371


365NO


YES

TO SHT 133


61-20-003-138

TO 1C-130H-2-61FI-00-1


61-20-003-139

TO 1C-130H-2-61FI-00-1

FROM SHT 125

372YES

Is airplane being troubleshot TO SHT 129AF90-1057 and up?

NO

374

Repair ground fault between373plug P396 pin A and related pinRemove jumper wire from plugof receptacle J268A (2). (SeeP396 (1) but do not reconnectfigure 3-6.)NO

plug.Does FUNCTION display (4) indi-

Rcptcate 1.0 or greater and does ACProp PinVOLTS display (3) indicate 6?2 183 17YES

375

Repair ground fault betweenplug P396 pin B and related pinof receptacle J268A (2). (Seefigure 3-6.)


NOTE



61-20-003-140

TO 1C-130H-2-61FI-00-1


61-20-003-141

TO 1C-130H-2-61FI-00-1

FROM SHT 127

376

Remove jumper wire from plug P396 (1)YESbut do not reconnect plug.

TO SHT 131Does FUNCTION display (2) indicate 1.0 orgreater and does AC VOLTS display (3) in-dicate 6?

NO

377

Gain access to terminal board TB105AG(4) and disconnect specified wire fromspecified terminal. (Leave remaining two 379wires securely attached.)

Repair ground fault on specified wire.(See figure 3-6 or 3-7.)TB YES

Prop Wire No. TermProp Wire No.2 2K95D20 42 2K95D203 3K95D20 63 3K95D20

Does FUNCTION display indicate 1.0 orgreater and does AC VOLTS display indi-cate 6?

NO

378380Disconnect remaining wires from specified

terminal board TB105AG terminal. Repair ground fault between plug P396pin A and related terminal board

TB TB105AG terminal. (See figure 3-6 or 3-Prop Term 7.)YES2 43 6 TB

Prop TermDoes FUNCTION display indicate 1.0 or 2 4greater and does AC VOLTS display indi- 3 6cate 6?

NO

381

Repair ground fault between specifiedterminal board TB105AG terminal and re-lated pin of receptacle J268A (5). (Seefigure 3-6 or 3-7.)

TB RcptProp Term Pin2 4 183 6 17

NOTE



61-20-003-142

TO 1C-130H-2-61FI-00-1


61-20-003-143

TO 1C-130H-2-61FI-00-1

FROM SHT 129

382

a. Reinstall jumper wire betweenpins A and B of plug P396 (1).b. Gain access to terminal boardTB105AG (4) and disconnect 384specified wire from specified ter-

Remove jumper wire. Repairminal. (Leave remaining twoground fault on specified wire.wires securely attached.)(See figure 3-6 or 3-7.)YES

TBProp Wire No.Prop Wire No. Term2 2K97D202 2K97D20 33 3K97D203 3K97D20 5


NO

383385Disconnect remaining wires from

specified terminal board TB105AG Remove jumper wire. Repairterminal. ground fault between plug P396

pin B and related terminalTB board TB105AG terminal. (SeeNO

Prop Term figure 3-6 or 3-7.)2 33 5 TB

Prop TermDoes FUNCTION display indicate 2 31.0 or greater and does AC 3 5VOLTS display indicate 6?

YES

386

Remove jumper wire. Repairground fault between specifiedterminal board TB105AG termi-nal and related pin of recepta-cle J268A (5). (See figure 3-6or 3-7.)


NOTE



61-20-003-144

TO 1C-130H-2-61FI-00-1


61-20-003-145

TO 1C-130H-2-61FI-00-1

FROM SHT 125

387YES

Is airplane being troubleshot a TO SHT 135year model AF90-1057 and up?

NO

388

a. Remove jumper wire from plugP396 (1) but do not reconnectplug.b. Gain access to and disconnect NOplug P429 (5) at outer wing break. TO SHT 139c. Install a jumper wire betweenplug P429 pins A and B.Does FUNCTION display (3) indi-cate 1.0 or greater and does ACVOLTS display (2) indicate 6?

YES


P429 and reconnect plug at outer Repair ground fault between pinYESwing break. B of receptacle J269 (4) andDoes FUNCTION display indicate plug P396 pin B. (See figure 3-1.0 or greater and does AC 6). VOLTS display indicate 6?

NO

391

Repair ground fault between pinA of receptacle J269 (4) andplug P396 pin A. (See figure 3-6.)


61-20-003-146

TO 1C-130H-2-61FI-00-1


61-20-003-147

TO 1C-130H-2-61FI-00-1

FROM SHT 133

392

Remove jumper wire from plug P396 (1) but do not reconnect YESplug. TO SHT 137Does FUNCTION display (2) indicate 1.0 or greater and does ACVOLTS display (3) indicate 6?

NO

393

Gain access to terminal board TB105AG (4) and disconnect396specified wire from specified terminal. (Leave remaining two

wires securely attached.) Repair ground fault on specifiedwire. (See figure 3-6 or 3-7.)YES

Prop Wire No. TB Term1 1K95E20 2 Prop Wire No.4 4K95E20 8 1 1K95E20

4 4K95E20Does FUNCTION display indicate 1.0 or greater and does ACVOLTS display indicate 6?

NO

394397

Disconnect remaining wires from 395 Repair ground fault betweenspecified terminal board TB105AGplug P429/P1225 pin A and re-a. Reconnect all wires to terminalterminal.lated terminal board TB105AGboard TB105AG.terminal. (See figure 3-6 or 3-b. Gain access to and disconnectYES NOProp TB Term7.)plug P429/P1225 (6) at outer1 2

wing break.4 8TBDoes FUNCTION display indicate

Prop Term1.0 or greater and does ACDoes FUNCTION display indicate1 2VOLTS display indicate 6?1.0 or greater and does AC4 8VOLTS display indicate 6?

NO

YES

398

Repair ground fault between pin A of recep-tacle J269/J660 (7) and plug P396 pin A.(See figure 3-6 or 3-7.)

399

Repair ground fault between specified termi-nal board TB105AG terminal and related pinof receptacle J267A (5). (See figure 3-6 or3-7.)



61-20-003-148

TO 1C-130H-2-61FI-00-1


61-20-003-149

TO 1C-130H-2-61FI-00-1

FROM SHT 135

400

a. Reinstall jumper wire between pins Aand B of plug P396 (1).b. Gain access to terminal board TB105AG

403(4) and disconnect specified wire fromspecified terminal. (Leave remaining two Remove jumper wire. Repairwires securely attached.) ground fault on specified wire.

(See figure 3-6 or 3-7.)YESTB

Prop Wire No. Term Prop Wire No.1 1K97E20 1 1 1K97E204 4K97E20 7 4 4K97E20

Does FUNCTION display (2) indicate 1.0 orgreater and does AC VOLTS display (3) in-dicate 6?

NO

401 404

Disconnect remaining wires from specified Remove jumper wire. Repairterminal board TB105AG terminal. ground fault between specified

terminal board TB105AG termi-TB nal and related pin of recepta-

Prop Term cle J267A (5). (See figure 3-6YES1 1 or 3-7.)4 7

TB RcptDoes FUNCTION display indicate 1.0 or Prop Term Pingreater and does AC VOLTS display indi- 1 1 17cate 6? 4 7 43

NO

405402Remove jumper wire. Repaira. Remove jumper wire from plug P396 butground fault between plugdo not reconnect plug.P429/P1225 pin B and relatedb. Gain access to and disconnect plugterminal board TB105AG termi-P429/P1225 (6) at outer wing break. NOnal. (See figure 3-6 or 3-7.)c. Install jumper wire between plug P429/

P1225 pins A and B.TBDoes FUNCTION display indicate 1.0 or

Prop Termgreater and does AC VOLTS display indi-1 1cate 6?4 7

YES

406

Remove jumper wire. Repairground fault between pin B ofreceptacle J269/J660 (7) andplug P396 pin B. (See figure 3-6 or 3-7.)


61-20-003-150

TO 1C-130H-2-61FI-00-1


61-20-003-151

TO 1C-130H-2-61FI-00-1

FROM SHT 133 408

Repair ground fault between407plug P429 pin B and related pinRemove jumper wire from plugof receptacle J267A (3). (SeeP429 (4) but do not reconnectfigure 3-6.)YES

plug.Does FUNCTION display (1) indi-

Rcptcate 1.0 or greater and does ACProp PinVOLTS display (2) indicate 6?1 174 43NO

409

Repair ground fault betweenplug P429 pin A and related pinof receptacle J267A (3). (Seefigure 3-6.)


NOTE



61-20-003-152

TO 1C-130H-2-61FI-00-1


61-20-003-153

TO 1C-130H-2-61FI-00-1

FROM SHT 89 OR 109

410

a. Open PROP SYNCHRO PHASER and SYNCHRO PHASER circuit breakers(1,2).b. Install synchrophaser (4) in rack, ensuring it seats in junction box connectors(3). Secure synchrophaser with adapter bracket. 413c. Close PROP SYNCHRO PHASER and SYNCHRO PHASER circuit breakers.

Replace propellerd. Place FUNCTION SELECT switch (6) to DCV.synchrophaser ine. Place TEST SELECT switch (5) to 2. NOaccordance withDoes FUNCTION display (7) indicate 11 to 14 volts?TO 1C-130H-2-(Feedback pot V supply)61JG-20-1, 61-20-13.Prop Sync Rcpt Pins


YES

411

Place TEST SELECT switch to 3. 414Does FUNCTION display indicate -11 to -14 volts?

Replace propeller(Feedback pot -V supply)synchrophaser inNOaccordance withProp Sync Rcpt PinsTO 1C-130H-2-1 J267A-10, J267A-4561JG-20-1, 61-20-2 J268A-3, J267A-4513.3 J268A-4, J267A-45

4 J267A-15, J267A-45

YES

412

Place TEST SELECT switch to 4. 415Does FUNCTION display indicate -11 to -15 volts?

Replace propeller(Anticipator pot -V supply)synchrophaser inNOaccordance withProp Sync Rcpt PinsTO 1C-130H-2-1 J267A-18, J267A-4561JG-20-1, 61-20-2 J268A-19, J267A-4513.3 J268A-20, J267A-45

4 J267A-19, J267A-45

YES

TO SHT 143

NOTE






61-20-003-154

TO 1C-130H-2-61FI-00-1


61-20-003-155

TO 1C-130H-2-61FI-00-1

FROM SHT 141

416

a. Place TEST SELECT switch (4) to 5.b. Move throttle (5) to TAKE OFF.Does FUNCTION display (1) indicate 0 to -3

419volts?(Anticipator pot output in T/O pos) Replace valve housing assem-NO

bly in accordance with TO 1C-Prop Sync Rcpt Pins 130H-2-61JG-20-1, 61-20-02.1 J267A-22, J267A-452 J267A-20, J267A-453 J267A-21, J267A-454 J267A-9, J267A-45

YES

417

Move throttle to FLIGHT IDLE/FLT IDLE.Does FUNCTION display indicate -8.5 to -12volts? 420(Anticipator pot output)

Replace valve housing assem-NObly in accordance with TO 1C-Prop Sync Rcpt Pins130H-2-61JG-20-1, 61-20-02. 1 J267A-22, J267A-45

2 J267A-20, J267A-453 J267A-21, J267A-454 J267A-9, J267A-45

YES

418

a. Rapidly advance throttles to TAKE OFF.b. Place PROP CHANNEL SELECT switch (3) tonext highest or lowest position.c. Return PROP CHANNEL SELECT switch toprevious position and record the indication in ACVOLTS display (2). 421d. Rapidly retard throttles to FLIGHT IDLE/FLT

Replace propeller syn-IDLE and note indication in AC VOLTS display. NOchrophaser in accordance withIs the difference in the two indications at least 2TO 1C-130H-2-61JG-20-1, 61-volts?20-13.(Speed bias control winding)


YES

TO SHT 145


61-20-003-156

TO 1C-130H-2-61FI-00-1


61-20-003-157

TO 1C-130H-2-61FI-00-1

FROM SHT 143

422

Place TEST SELECT switch (3) to6.Does AC VOLTS display (2) indi- 424cate 90 to 130 volts?

Replace propeller syn-(Speed bias ref winding) NOchrophaser in accordance withTO 1C-130H-2-61JG-20-1, 61-Prop Sync Rcpt Pins20-13. 1 J267A-40, J267A-45

2 J268A-23, J267A-453 J268A-24, J267A-454 J267A-39, J267A-45

YES

423

a. Start engines in accordancewith 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-130(M)H-2-71JG-00-1, 71-00-10.b. Place FUNCTION SELECTswitch (4) to TACH RPM %. NODoes FUNCTION display (1) indi- TO SHT 147cate 99.8 to 100.2?(Tach gen output)


YES

TO SHT 149


61-20-003-158

TO 1C-130H-2-61FI-00-1


61-20-003-159

TO 1C-130H-2-61FI-00-1

FROM SHT 1 OR 145 427428Place FUNCTION SELECT switch

425 Fault is in tachometer(2) to PROP RPM %.NO YESIs there a flashing 6 in FUNCTION system. Go to TO 1C-Does RPM difference between TACHdisplay (1)? 130H-2-70FI-00-1-1 andRPM % indication and PROP RPM

continue troubleshooting. % indication in FUNCTION displayexceed 1 percent?YES

NO429

Adjust propeller mechanicalgoverning speed in accordancewith TO 1C-130H-2-61JG-10-1,61-10-03.

426

a. Shut down engines in accordance 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-130(M)H-2-71JG-00-1, 71-00-10.b. As applicable, remove propeller synchrophaser in ac-cordance with TO 1C-130H-2-61JG-20-1, 61-20-13,and/or remove junction box from synchrophaser rack.Is there continuity between specified pins of receptacleJ267A (3) and related terminals of terminal board TB1C(4)?

Rcpt TB TestProp Pin Term Points

43024 110 9

1 Fault is in tachometer system.YES26 2

12 11Go to TO 1C-130H-2-70FI-00-1-1 and continue troubleshooting.

28 310 9

229 4

12 11

30 510 9

332 6

12 11

41 710 9

442 8

12 11

NO

431

Repair applicable open circuit.(See figure 3-6 or 3-7.)

NOTE




61-20-003-160

TO 1C-130H-2-61FI-00-1


61-20-003-161

TO 1C-130H-2-61FI-00-1

FROM SHT 145

436432Fault is in tachometer system.NO

Does AC VOLTS display (3) indi-Go to TO 1C-130H-2-70FI-00-1-cate 17 to 30? 1 and continue troubleshooting.

YES

433

Place FUNCTION SELECT switch(5) to PROP RPM %.Does FUNCTION display (1) indi- 437cate 99.8 to 100.2?

Adjust clearance between pulse(Pulse gen output) NOgenerator and permanent mag-net in accordance with TO 1C-Prop Sync Rcpt Pins130H-2-61JG-20-1, 61-20-10. 1 J267A-23, J267A-17

2 J268A-18, J268A-113 J268A-17, J268A-214 J267A-25, J267A-43

YES

434 438435

NO YESDoes AC VOLTS display indicate Replace permanent magnet inIs the - PULSE POLARITY indica-1.2 to 5.0 and is - PULSE PO- accordance with TO 1C-130H-tor light on? LARITY indicator light (2) on? 2-61JG-20-1, 61-20-10.

YES NO

TO SHT 151439

Polarity of pulse generator (4) isreversed. Check pulse genera-tor for reversed wiring or im-proper magnet orientation andrepair as required.


61-20-003-162

TO 1C-130H-2-61FI-00-1


61-20-003-163

TO 1C-130H-2-61FI-00-1

FROM SHT 149

440

a. Place FUNCTION SELECT switch (5) to DCV.b. Place TEST SELECT switch (4) to 13.Does FUNCTION display (1) indicate between -1.2 and-5.0 volts? 442(Pulse gen output) NO

Replace pulse generator in accordancewith TO 1C-130H-2-61JG-20-1, 61-20-10.Prop Sync Rcpt Pins


YES

441

a. Place TEST SELECT switch to 14.b. Record voltage indication in AC VOLTS display (2)for propeller under test.c. Place propeller governor control switch (6) to MECHGOV/MECH.d. Place applicable SPEED DERIVATIVE switch (3) toOUT.

443e. Place propeller governor control switch to NORMAL/NORM. Fault is in tachometer system. Go to TONOf. Record voltage indication in AC VOLTS display. 1C-130H-2-70FI-00-1-1 and continueg. Compare the indications of steps b and f. troubleshooting. Are the values the same?(Tach gen output)


YES

444

Replace propeller synchrophaser in ac-cordance with TO 1C-130H-2-61JG-20-1,61-20-13.


61-20-003-164

TO 1C-130H-2-61FI-00-1


61-20-003-165/(3-166 blank)

TO 1C-130H-2-61FI-00-1

Figure 3-6. Synchrophaser System Electrical Schematic Diagram (Air-planes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)

(Sheet 1 of 5) 61-20-00F3-6

3-167/(3-168 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 2) 61-20-00F3-6

3-169/(3-170 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 3) 61-20-00F3-6

3-171/(3-172 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 4) 61-20-00F3-6

3-173/(3-174 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 5) 61-20-00F3-6

3-175/(3-176 blank)

TO 1C-130H-2-61FI-00-1

Figure 3-7. Synchrophaser System Electrical Schematic Diagram (Air-planes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)

(Sheet 1 of 5) 61-20-00F3-7

3-177/(3-178 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 2) 61-20-00F3-7

3-179/(3-180 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 3) 61-20-00F3-7

3-181/(3-182 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 4) 61-20-00F3-7

3-183/(3-184 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 5) 61-20-00F3-7

3-185/(3-186 blank)

TO 1C-130H-2-61FI-00-1

Figure 3-8. Synchrophaser Adapter Unit Electrical Schematic Diagram(Sheet 1 of 2) 61-20-00

F3-83-187/(3-188 blank)

TO 1C-130H-2-61FI-00-1

Figure 3-8. Synchrophaser Adapter Unit Electrical Schematic Diagram(Sheet 2) 61-20-00

F3-83-189/(3-190 blank)

TO 1C-130H-2-61FI-00-1

Figure 3-9. Synchrophaser System Simplified Electrical SchematicDiagram 61-20-00

F3-93-191/(3-192 blank)

TO 1C-130H-2-61FI-00-1


F3-103-193/(3-194 blank)

TO 1C-130H-2-61FI-00-1

Section IV. SYNCHROPHASER SYSTEM

(AIRPLANES MODIFIED BY TO 1C-130-1731)

4-1. GENERAL. The fault isolation material in this section is used for troubleshooting anysynchrophaser system malfunction. Contents of this section include a malfunction index, a faultcode index, preparation procedures to be performed prior to fault isolation, a fault isolationdiagram (the actual troubleshooting procedures), locator illustrations for hardware referenced inthe fault isolation diagram, and schematic diagrams.


Table 4-1. Synchrophaser System Malfunctions


1. Synchrophaser system 6120S01 Perform figure 4-1, Preparation A, then gomalfunction to figure 4-5, block 1.


4-3. NUMERIC FAULT CODE INDEX. All assigned numeric FRM fault codes for the syn-chrophaser system are listed in table 4-2. Fault codes are listed in numerical order in the leftcolumn of the table. The middle column contains the AFTO Form 781A report and lists symp-toms and conditions actually observed by the flight crew while performing the FRM procedure.The right column identifies the preparation and fault isolation figures for troubleshooting.



6120001 All slave propellers fail to follow when Replace propeller synchrophaser in ac-No. 3 propeller is selected as master. All coradance with TO 1C-130H-2-61JG-20-1,slave propellers follow when No. 2 propel- 61-20-13.ler is selected as master.


61-20-00Change 1 4-1

TO 1C-130H-2-61FI-00-1




6120004 All slave propellers fail to follow when Replace propeller synchrophaser in accor-No. 2 or No. 3 propeller is selected as dance with TO 1C-130H-2-61JG-20-1, 61-master. 20-13.


6120006 Propeller No. (1)(3)(4) fails to follow when Perform figure 4-1, Preparation A, thenNo. 2 or No. 3 propeller is selected as go to figure 4-5, block 144.master.





6120011 Engine No. (1)(2)(3)(4) RPM takes exces- Perform figure 4-1, Preparation A, thensive time to stabilize after rapid THROT- go to figure 4-5, block 146.TLE movement.

6120012 All engine RPMs (fluctuate) (are out of Replace propeller synchrophaser in accor-limits) in normal governing. dance with TO 1C-130H-2-61JG-20-1, 61-

20-13.

6120013 Engine No. (1)(2)(3)(4) RPM (fluctuates) Perform figure 4-1, Preparation A, then(is out of limits) in normal governing. go to figure 4-5, block 137.

6120014 Engine No. (1)(2)(3)(4) RPM (fluctuates) Fault is in propeller system. Go to Sec-(is of limits) in mechanical governing. tion II and continue fault isolation.

61-20-004-2 Change 1

TO 1C-130H-2-61FI-00-1


WARNING



61-20-00Change 1 4-3

TO 1C-130H-2-61FI-00-1


61-20-004-4 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-5

TO 1C-130H-2-61FI-00-1


61-20-004-6 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-7

TO 1C-130H-2-61FI-00-1

Figure 4-3. Preparation C (Sheet 1 of 3)

61-20-004-8 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-9

TO 1C-130H-2-61FI-00-1


61-20-004-10 Change 1

TO 1C-130H-2-61FI-00-1

Figure 4-4. Preparation D (Sheet 1 of 3)

61-20-00Change 1 4-11

TO 1C-130H-2-61FI-00-1


61-20-004-12 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-13

TO 1C-130H-2-61FI-00-1

4-5. FAULT ISOLATION DIAGRAM. The fault isolation diagram in this section is used for trou-bleshooting any synchrophaser system malfunction. When the flight crew uses a FRM fault codeto report a malfunction, that number will be found in the fault code index. When no FRM faultcode is available, the malfunction index identifies the figure to use for fault isolation.

a. Arrangement. One fault isolation diagram is included for the synchrophaser system.Opposite each flow sheet of the fault isolation diagram is an illustration which shows the physi-cal location of items referenced in individual fault isolation diagram blocks. Double-check theseillustrations to verify the correct location when making an observation or measurement. Follow-ing the fault isolation diagram are the electrical schematic diagrams. The schematic diagramsare laid out so that no portion of a diagram is covered up when folded out for use. Thus it iseasy to concurrently locate components, circuits, and test points that are referenced on the faultisolation diagram.


61-20-004-14/(4-15 blank) Change 1

TO 1C-130H-2-61FI-00-1

1 6120S01

Advance throttles (6) to obtain approxi-65mately 8,000 inch-pounds on engine

torque indicators (3) with all ELEC- Synchrophaser in-Perform synchrophaser index in accor-YES NOTRONIC FUEL CORRECTION/TD lights dex corrected mal-dance with TO 1C-130H-61JG-10-1, 61-(2) off. function. Secure10-02 (subtask 1-2-6).Did RPM on any engine tachometer (4) system. Does problem persist? exceed 103.5 percent or did any propel-ler pitchlock?

NO

YES

TO SHT 77

2 Fault is in propellerPlace propeller governor control switch- system. Go to fig-NOes (5) to MECH GOV/MECH. ure 2-5 in SectionIs RPM stable for each propeller? II and continue

troubleshooting. YES

3

NOIs RPM in FUNCTION display (1) be-TO SHT 147tween 99.8 and 100.2 percent for each

propeller?

YES

4

Perform synchrophaser index in accor-dance with TO 1C-130H-2-61JG-10-1,61-10-02 (subtask 1-2-6). Did RPM of YESany propeller vary more than 0.2 per- TO SHT 25cent when propeller governor controlswitches (5) were moved from MECHGOV/MECH to NORMAL/NORM duringthe synchrophaser index?

NO

TO SHT 3

NOTE


2 Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.Figure 4-5. Synchrophaser System Malfunction (Sheet 1 of 152)

61-20-004-16 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-17

TO 1C-130H-2-61FI-00-1

FROM SHT 1

8NO

Is RPM stable for each propeller TO SHT 41(1) in NORMAL governing?

YES

9


YES

10

Perform synchrophaser check inaccordance with TO 1C-130H-2-61JG-10-1, 61-10-02 (subtask 1-

YES2-9).TO SHT 43Did RPM of any slave propeller

fail to decrease 1 to 3 percent asNo. 2 throttle (2) was retarded toFLIGHT IDLE/FLT IDLE duringthe check?

NO

11


YES

TO SHT 5


61-20-004-18 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-19

TO 1C-130H-2-61FI-00-1

FROM SHT 3

1215

Did the RPM of any slave propel-Replace propeller syn-ler fail to decrease 1 to 3 percent YESchrophaser in accordance withas No. 3 throttle (1) was retardedTO 1C-130H-2-61JG-20-1, 61-to FLIGHT IDLE/FLT IDLE during20-13. the synchrophaser check?

NO

13

Perform throttle anticipation checkNOin accordance with TO 1C-130H-

TO SHT 452-61JG-10-1, 61-10-02 (subtask1-2-8).Was check satisfactory?

YES

14

Perform fuel governor and 16pitchlock check in accordance YES

Synchrophaser system is nor-with TO 1C-130H-2-61JG-10-1,mal. Secure system. 61-10-02 (subtask 1-2-10).

Was check satisfactory?

NO

TO SHT 7


61-20-004-20 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-21

TO 1C-130H-2-61FI-00-1

FROM SHT 1 OR 5

17

CAUTION

Do not retard throttle below 96 percent if pitchlock isengaged. The RPM may drop below 94 percent andcause an engine flameout, resulting in overtemperaturedamage to the turbine.a. Shut down engines in accordance with TO 1C-130H- 202-71JG-00-1, 71-00-10. NO YESIs airplane serial numberb. Perform Preparation D. TO SHT 11

AF92-0547 through AF92-2104c. Place TEST SELECT switch (2) to 7.or AF92-3281 and up? d. Place PROP CHANNEL SELECT switch (3) to 4.

e. Momentarily hold engine 4 fuel governing switch (6)to CHECK.Does FUNCTION display (1) indicate -6.5 to -7.5 voltswhile switch is held?

Prop Sync Rcpt Pins4 P-B2576A-10, P-B2576A-30

YES

NO

TO SHT 9

18

a. Place PROP CHANNEL SELECT switch to R/3.b. Momentarily hold engine 3 fuel governing switch (5)to CHECK. NODoes FUNCTION display indicate -6.5 to -7.5 volts TO SHT 15while switch is held?

Prop Sync Rcpt Pins3 P-A2576A-22, P-B2576A-30

YES

19

a. Place PROP CHANNEL SELECT switch to L/2.b. Momentarily hold engine 2 fuel governing switch (4)to CHECK. NODoes FUNCTION display indicate -6.5 to -7.5 volts TO SHT 17while switch is held?

Prop Sync Rcpt Pins2 P-A2576A-44, P-B2576A-30

YES

TO SHT 19

NOTE




61-20-004-22 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-23

TO 1C-130H-2-61FI-00-1

FROM SHT 7

21 23

NOTE a. Remove junction box fromPut meter positive lead to ground synchrophaser rack. 24in following steps. b. Install a jumper wire between Remove jumper wire. Repair

pin 39 of receptacle P-A2576A (2)NO NO open circuit between switch ter-Gain access to terminals of en- and airplane ground. minal 2 and receptacle P-gine 4 fuel governing switch (1). Is a ground present on engine 4 A2576A pin 39. (See figure 4-Is 15 volts present on switch ter- fuel governing switch (1) terminal 6.) minal 2? 2?

7 7

YES YES

25


22

Momentarily hold ENG 4 FUELGOVERNING switch (1) to 26CHECK. NO

Replace ENG 4 FUEL GOV-Is 15 volts present on switch ter-ERNING switch. minal 1 while switch is held?

8

YES

27

Repair open circuit betweenswitch terminal 1 and pin 10 ofreceptacle P-B2576A (3). (Seefigure 4-6.)

NOTE





61-20-004-24 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-25

TO 1C-130H-2-61FI-00-1

FROM SHT 7

28

NOTEPut meter positive lead to ground in followingsteps.

NOTO SHT 13Gain access to terminals of engine 4 fuel gov-

erning switch (3).Is 15 volts present on switch terminal 2?

7

YES

29

Momentarily hold ENG 4 FUEL GOVERNING31switch (3) to CHECK.

NOIs 15 volts present on switch terminal 1 while Replace ENG 4 FUEL GOV-switch is held? ERNING switch.

8

YES

30

Gain access to and disconnect plug P1743A 32(1) from fuel governing control panel (4).

Repair open circuit betweenIs there continuity between receptacle J880A YESplug P1743A pin D and recep-(2) pin D and related control panel switch ter-tacle P-B2576A (5) pin 10.minal 1?(See figure 4-7.)

8 8.2

NO

33

Repair open circuit between re-ceptacle J880A pin D andswitch terminal 1. (See figure4-7.)

NOTE

See figure 4-7 for:


61-20-004-26 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-27

TO 1C-130H-2-61FI-00-1

FROM SHT 11

34

a. Gain access to and disconnectplug P1743A (1) from fuel gov-

36erning control panel (4).b. Install a jumper wire between Remove jumper wire. Repairpin E of receptacle J880A (2) and open circuit between fuel gov-NOairplane ground. erning switch terminal 2 and re-Is a ground present on engine 4 ceptacle J880A pin E. (Seefuel governing switch (3) terminal figure 4-7.) 2?

7

YES

35

a. Remove junction box fromsynchrophaser rack. 37b. Install a jumper wire between

Remove jumper wire. Repairpin 39 of receptacle P-A2576A (5)open circuit between plugNOand airplane ground.P1743A pin E and receptacleIs a ground present on engine 4P-A2576A, pin 39. (See figurefuel governing switch (3) terminal4-7.) 2?

7

YES

38


NOTE

See figure 4-7 for:


61-20-004-28 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-29

TO 1C-130H-2-61FI-00-1

FROM SHT 7

39

NOTE43Put meter positive lead to ground in following steps.Repair open circuit between engine 3 fu-NO

Gain access to terminals of engine 3 fuel governing el governing switch terminal 2 and termi-switch (4). nal 2 of engine 4 fuel governing switchIs 15 volts present on switch terminal 2? (3). (See figure 4-6 or 4-7.)

5

YES

40

Momentarily hold ENG 3 FUEL GOVERNING switch (4)44to CHECK.

NOIs 15 volts present on switch terminal 1 while switch is Replace ENG 3 FUEL GOVERNINGheld? switch.

6

YES

4541 Repair open circuit between engine 3 fu-NO

Is airplane serial number AF92-0547 through AF92- el governing switch terminal 1 and pin 222104 or AF92-3281 and up? of receptacle P-A2576A (6). (See figure

4-6.) YES

42

Gain access to and disconnect plug P1743A (1) from 46fuel governing control panel (5).

Repair open circuit between plug P1743AYESIs there continuity between receptacle J880A (2) pin Cpin C and receptacle P-A2576A (6) pinand related control panel switch terminal 1?37. (See figure 4-7.)

6 8.3

NO

47

Repair open circuit between receptacleJ880A pin C and switch terminal 1. (Seefigure 4-7.)

NOTE







61-20-004-30 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-31

TO 1C-130H-2-61FI-00-1

FROM SHT 7

48

NOTE52Put meter positive lead to ground in following steps.Repair open circuit between engine 2NO

Gain access to terminals of engine 2 fuel governing fuel governing switch terminal 2 andswitch (1). terminal 2 of engine 3 fuel governingIs 15 volts present on switch terminal 2? switch (2). (See figure 4-6 or 4-7.)

3

YES

49



4

YES

5450 Repair open circuit between engine 2NO

Is airplane serial number AF92-0547 through AF92- fuel governing switch terminal 1 and2104 or AF92-3281 and up? pin 44 of receptacle P-A2576A (3).

(See figure 4-6.)YES

51


Repair open circuit between plugYESIs there continuity between receptacle J880A (5) pin BP1743A pin B and receptacle P-and related control panel switch terminal 1?A2576A (3) pin 44. (See figure 4-7.)

4 8.4

NO

56

Repair open circuit between recepta-cle J880A pin B and switch terminal1. (See figure 4-7.)

NOTE







61-20-004-32 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-33

TO 1C-130H-2-61FI-00-1

FROM SHT 7

57

a. Place PROP CHANNEL SELECT switch (6) to 1.b. Momentarily hold ENG 1 FUEL GOVERNING switch(1) to CHECK. NODoes FUNCTION display (3) indicate -6.5 to -7.5 volts TO SHT 21while switch is held?

Prop Sync Rcpt Pins1 P-B2576A-18, P-B2576A-30

YES

58

a. Place PROP CHANNEL SELECT switch (6) to pro-peller under test.b. Place propeller governor control switch (8) to MECHGOV/MECH. 60c. Momentarily hold FUEL GOV switch (5) to ON.

Replace propeller syn-Does FUNCTION display (3) indicate -6.5 to -7.5 volts NOchrophaser in accordance withwhile switch is held?TO 1C-130H-2-61JG-20-1, 61-20-13. Prop Sync Rcpt Pins

1 P-B2576A-18, P-B2576A-302 P-A2576A-44, P-B2576A-303 P-A2576A-22, P-B2576A-304 P-B2576A-10, P-B2576A-30

YES

59

a. Place TEST SELECT switch (7) to 8.b. Momentarily hold applicable fuel governing switch (1or 2) to CHECK for 10 seconds.

61Does AC VOLTS display (4) indicate 50 to 65 voltswhile switch is held? Replace propeller syn-NO(Speed bias control winding) chrophaser in accordance with

TO 1C-130H-2-61JG-20-1, 61-Prop Sync Rcpt Pins 20-13.1 P-B2576A-5, P-B2576A-32 P-A2576A-34, P-A2576A-453 P-B2576A-14, P-B2576A-64 P-A2576A-24, P-B2576A-19

YES

TO SHT 23

NOTE






61-20-004-34 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-35

TO 1C-130H-2-61FI-00-1

FROM SHT 19

62

NOTE66Put meter positive lead to ground in following steps.Repair open circuit between engine 1NO

Gain access to terminals of engine 1 fuel governing fuel governing switch terminal 2 andswitch (1). terminal 2 of engine 2 fuel governingIs 15 volts present on switch terminal 2? switch (2). (See figure 4-6 or 4-7.)

1

YES

63



2

YES

6864 Repair open circuit between engine 1NO

Is airplane serial number AF92-0547 through AF92- fuel governing switch terminal 1 and2104 or AF92-3281 and up? pin 18 of receptacle P-B2576A (3).


65


Repair open circuit between plugYESIs there continuity between receptacle J880A (5) pin AP1743A pin A and receptacle P-and related control panel switch terminal 1?B2576A (3) pin 18. (See figure 4-7.)

2 8.5

NO

70

Repair open circuit between recepta-cle J880A pin A and switch terminal1. (See figure 4-7.)

NOTE







61-20-004-36 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-37

TO 1C-130H-2-61FI-00-1

FROM SHT 19

71

a. Record voltage indication in FUNCTIONdisplay (2) for propeller under test.b. Place propeller governor control switch (3)to NORMAL/NORM.c. Actuate applicable fuel governing switch (1)as follows:

CHECK for 5 seconds,NORMAL/NORM for 5 seconds,

CHECK for 5 seconds,NORMAL/NORM for 5 seconds.

d. Place propeller governor control switch (3)72to MECH GOV/MECH.

e. Record voltage indication in FUNCTION Replace valve housing assembly inYESdisplay (2). accordance with TO 1C-130H-2-61JG-f. Compare the two voltage indications record- 20-1, 61-20-02. ed in steps a and e.Did voltage change more than 0.2 volts onany channel?(Feedback pot)

DC: Sync AC: SyncRcpt Pin Rcpt PinsP-B2576A-7 P-B2576A-5 and 3P-A2576A-14 P-A2576A-34 and 45P-A2576A-2 P-B2576A-14 and 6P-B2576A-23 P-A2576A-24 and

P-B2576A-19

NO

73

Replace propeller synchrophaser inaccordance with TO 1C-130H-2-61JG-20-1, 61-20-13.

NOTE






61-20-004-38 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-39

TO 1C-130H-2-61FI-00-1

FROM SHT 1

74YES

Did all propellers (1,2,3, and 4) fail to TO SHT 27respond to the synchrophaser index?

NO

75

With No. 2 propeller (2) as master did YESNo. 3 propeller (3) fail to index, and with TO SHT 39No. 3 (3) propeller as master did No. 2propeller (2) fail to index?

NO

76

Perform propeller governor servo-bias 77clutch-brake check on affected propeller

Replace valve housing assem-NOin accordance with TO 1C-130H-2-

bly in accordance with TO 1C-61JG-10-1, 61-10-02 (subtask 1-2-7).130H-2-61JG-20-1, 61-20-02. Was RPM within limits for the affected

propeller?

YES

TO SHT 47


61-20-004-40 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-41

TO 1C-130H-2-61FI-00-1

FROM SHT 25

78

a. Shut down engines in accor-dance with TO 1C-130H-2-71JG- 8200-1, 71-00-10.

Place propeller governor controlb. Perform Preparation D.switches (4) to MECH GOV/MECH. 83c. Place TEST SELECT switch YES NOIs MASTER light L/2 (1) on and are(8) to 1. Replace SYNCHROPHASESYNC and RESYNC lights (2) off?Does AC VOLTS display (3) indi- MASTER/MSTR switch.

cate 115 to 125 volts?Prop Sync Rcpt PinsAll P-A2576A-38, P-B2576A-22Prop Sync Rcpt Pins

All P-A2576A-8 andP-B2576A-30

NO

YES

TO SHT 29

79

Remove junction box from synchrophaser84rack.

NOIs a ground present on pin 30 of receptacle P- Repair ground circuit. (See figure 4-B2576A (7)? 6.)

40

YES

80 85YES

Is airplane serial number AF92-0547 through Repair power circuit to receptacle P-AF92-2104 or AF92-3281 and up? A2576A, pin 8. (See figure 4-7.)

NO

81

Gain access to and disconnect plug P1258F 86(6) from constant voltage transformer (5). NO

Repair power circuit to plug P1258FIs 115 VAC present on plug pin 1?pin 1. (See figure 4-6.)

33

YES

TO SHT 37

NOTE





61-20-004-42 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-43

TO 1C-130H-2-61FI-00-1

FROM SHT 27

8789Place SYNCHROPHASE MASTER/

91MSTR switch (1) to engine 2. Gain access to terminal boardNO NOAre MASTER light L/2 (2) and SYNC Repair power circuit toTB146A (5).

light (‘‘4’’) on? terminal 199. (See figureIs 28 VDC present on terminal 199?4-6 or 4-7.)

Prop Sync Rcpt Pins 27

Any P-A2576A-38

YESYES

9290 Repair open circuit be-

YESIs 28 VDC present on terminal 207? tween terminal 207 andpin 38 of receptacle P-

29A2576A (6). (See figure4-6 or 4-7.)

NO

TO SHT 31

88

Place SYNCHROPHASE MASTER/MSTR switch to engine 3.

NOAre MASTER light R/3 (3) and SYNCTO SHT 33light (4) on?

Prop Sync Rcpt PinsAny P-B2576A-22

YES

TO SHT 35

NOTE



61-20-004-44 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-45

TO 1C-130H-2-61FI-00-1

FROM SHT 29

93

Gain access to terminals of SYN- 97CHROPHASE MASTER/MSTR

Repair open circuit betweenswitch (3). NOswitch terminal 11 and terminalIs 28 VDC present on switch ter-199 of terminal board TB146Aminal 11?(1). (See figure 4-6 or 4-7.)

14

YES

9498Is 28 VDC present on switch ter-

NOminal 10? Replace SYNCHROPHASEMASTER/MSTR switch.

17

YES

9599

Gain access to terminals of PROPRepair open circuit betweenRESYNCHROPHASE/PROPPROP RESYNCHROPHASE/SYNC switch (2). NOPROP SYNC switch terminal 5Is 28 VDC present on switch ter-and SYNCHROPHASEminal 5?MASTER/MSTR switch terminal10. (See figure 4-6 or 4-7.) 22

YES


Is 28 VDC present on switch ter- PROP RESYNCHROPHASE/YESminal 6? PROP SYNC switch terminal 6and terminal board TB146A (1)

25terminal 207. (See figure 4-6or 4-7.)

NO

101

Replace PROP RESYN-CHROPHASE/PROP SYNCswitch.

NOTE



61-20-004-46 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-47

TO 1C-130H-2-61FI-00-1

FROM SHT 29

106102Gain access to terminals of SYN-Gain access to terminal board 107CHROPHASE MASTER/MSTRTB146A (1). NO YES Repair open circuit betweenswitch (2).Is 28 VDC present on terminal

switch terminals 10 and 12.Is 28 VDC present on switch ter-207?(See figure 4-6 or 4-7.) minal 12?

2918

YESNO

108


103 109

Is 28 VDC present on terminal Repair open circuit between ter-YES206? minal 206 and pin 22 of recep-tacle P-B2576A (3). (See figure

284-6 or 4-7.)

NO

104

Gain access to terminals of SYN-110CHROPHASE MASTER/MSTR

switch (2). Repair open circuit betweenNOIs 28 VDC present on switch ter- switch terminals 8 and 11.minal 8? (See figure 4-6 or 4-7.)

15

YES

105 111

Is 28 VDC present on switch ter- Repair open circuit betweenYESminal 9? switch terminal 9 and terminalboard TB146A terminal 206.

19(See figure 4-6 or 4-7.)

NO

112


NOTE



61-20-004-48 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-49

TO 1C-130H-2-61FI-00-1

FROM SHT 29

113

Momentarily hold PROP RESYN-CHROPHASE/PROP SYNC switch (3) 117to RESYNC/INDEX. Are R/3 light (1)

Replace propeller synchrophaser inYESand RESYNC/INDEX light (2) on while

accordance with TO 1C-130H-2-61JG-switch is held?20-1, 61-20-13.

Prop Sync Rcpt PinsAny P-A2576A-30

NO

116114a. Gain access to terminals of 118a. Gain access to terminal boardPROP RESYNCHROPHASE/PROPTB128A (6). Repair open circuit be-SYNC switch (3).b. Momentarily hold PROP RESYN- tween PROP RESYN-b. Momentarily hold PROP RESYN-NO YESCHROPHASE/PROP SYNC switch CHROPHASE/PROPCHROPHASE/PROP SYNC switch(3) to RESYNC/INDEX. SYNC switch terminal 4(3) to RESYNC/INDEX.Is 28 VDC present on terminal board and terminal boardIs 28 VDC present on switch terminalterminal 17 while switch is held? TB128A terminal 17.4 while switch is held? (See figure 4-6 or 4-7.)

3024

YESNO

119

Replace PROP RESYNCHROPHASE/PROP SYNC switch.

115

a. Gain access to terminal board TB1C (5).120b. Momentarily hold PROP RESYN

CHROPHASE/PROP SYNC switch (3) to Repair open circuit between terminalNORESYNC/INDEX. board TB1C terminal 9 and terminalIs 28 VDC present on terminal board terminal board TB128A terminal 17. (See fig-9 while switch is held? ure 4-6 or 4-7.)

13

YES

121

Repair open circuit between terminalboard TB1C terminal 9 and pin 30 ofreceptacle P-A2576A (4). (See figure4-6 or 4-7.)

NOTE



61-20-004-50 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-51

TO 1C-130H-2-61FI-00-1

FROM SHT 27

122125Is a ground present on pin 2 of NO

plug P1258F (2)? Repair ground circuit. (See fig-ure 4-6.)

34

YES

123126Is a ground present on plug pin

NO4? Repair ground circuit. (See fig-ure 4-6.)

35

YES

124

Is there continuity between plug 127P1258F pin 3 and pin 8 of recep- YES

Replace constant voltage trans-tacle P-A2576A (1)?former (3).

36 41

NO

128


NOTE

See figure 4-6 for:


61-20-004-52 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-53

TO 1C-130H-2-61FI-00-1

FROM SHT 25

129

a. Shut down engines in accordancewith TO 1C-130H-2-71JG-00-1, 71-00-10.b. Place SYNCHROPHASE MASTER/

132MSTR switch (1) to engine 2 or engine3. Repair open circuit betweenNOc. Gain access to terminals of PROP PROP RESYNCHROPHASE/RESYNCHROPHASE/PROP SYNC PROP SYNC switch terminals 2switch (2). and 5. (See figure 4-6 or 4-7.) Is 28 VDC present on PROP RESYN-CHROPHASE/PROP SYNC switch (2)terminal 2?

23

YES

130

Momentarily hold PROP RESYN-133CHROPHASE/PROP SYNC switch (2)

to RESYNC/INDEX. Replace PROP RESYN-NOIs 28 VDC present on switch terminal 1 CHROPHASE/PROP SYNCwhile switch is held? switch.

26

YES

131

Momentarily hold PROP RESYN-134CHROPHASE/PROP SYNC switch (2)

to RESYNC/INDEX. Repair open circuit betweenIs 28 VDC present on SYN- SYNCHROPHASE MASTER/NOCHROPHASE MASTER/MSTR switch MSTR switch terminal 5 and(1) terminal 5 while PROP RESYN- PROP RESYNCHROPHASE/CHROPHASE/PROP SYNC switch (2) is PROP SYNC switch terminal 1.held? (See figure 4-6 or 4-7.)

16

YES

135


NOTE



61-20-004-54 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-55

TO 1C-130H-2-61FI-00-1

FROM SHT 3

136 139

Does RPM of all propellers (2) fluctuate Replace propeller synchrophaser inYESwith propeller governor control switch accordance with TO 1C-130H-2-61JG-(3) in NORMAL/NORM? 20-1, 61-20-13.

NO

140137Fault is in tachometer system. Go toNO

Does frequency meter (1) indicate aTO 1C-130H-2-70FI-00-1-1 and con-fluctuation for the affected propeller? tinue troubleshooting.

YES

138141Perform synchrophaser index in accor-

YESdance with TO 1C-130H-2-61JG-10-1, Synchrophaser index corrected mal-61-10-02 (subtask 1-2-6). Did RPM sta- function. Secure system. bilize?

NO

TO SHT 47

NOTE




61-20-004-56 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-57

TO 1C-130H-2-61FI-00-1

FROM SHT 3

142

If not previously done, performsynchrophaser check in accor-dance with TO 1C-130H-2-61JG-

NO10-1, 61-10-02 (subtask 1-2-9).TO SHT 109Did RPM of any slave propeller

(2) fail to decrease 1 to 3 percentas No. 3 throttle (1) was retardedto FLIGHT IDLE/FLT IDLE duringthe check?

YES

145143 Replace propeller syn-YES

Did all slave propellers fail to fol- chrophaser in accordance withlow either master? TO 1C-130H-2-61JG-20-1, 61-

20-13. NO

144 6120006

Perform pitchlock check in accor- NOdance with TO 1C-130H-2-61JG- TO SHT 4710-1, 61-10-02 (subtask 1-2-10).Was check satisfactory?

YES

TO SHT 109


61-20-004-58 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-59

TO 1C-130H-2-61FI-00-1

FROM SHT 5

146

a. Perform synchrophaser indexin accordance with TO 1C-130H-2-61JG-10-1, 61-10-02 (subtask 1491-2-6). NO

Synchrophaser index correctedb. Perform throttle anticipationmalfunction. Secure system. check in accordance with TO 1C-

130H-2-61JG-10-1, 61-10-02(subtask 1-2-8).Does fault persist?

YES

147

Perform propeller governor servo- 150bias clutch-brake check on affect-

Replace valve housing assem-NOed propeller (3) in accordance

bly in accordance with TO 1C-with TO 1C-130H-61JG-10-1, 61-130H-2-61JG-20-1, 61-20-02. 10-02 (subtask 1-2-7).

Was RPM within limits?

YES

148

a. Perform synchrophaser indexin accordance with TO 1C-130H-2-61JG-10-1, 61-10-02 (subtask1-2-6).b. Shut down engines in accor-dance with TO 1C-130H-2-71JG-00-1, 71-00-10.

151c. Move throttle (1) to MAXIMUMREVERSE/MAX RVS. Reseal dome assembly in ac-NOd. Hold engine condition lever (2) cordance with TO 1C-130H-2-in AIR START until propeller 61JG-10-1, 61-10-13. blades (3) stop moving (in reverseposition), then release.e. Place engine condition lever(2) to FEATHER/FTR and timepropeller movement.Does propeller go from full re-verse to full feather in 25 secondsor less?

YES

TO SHT 47


61-20-004-60 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-61

TO 1C-130H-2-61FI-00-1

FROM SHT 25,41,43, OR 45

152

a. If necessary, shut down engines in accor-dance with TO 1C-130H-2-71JG-00-1, 71-00-10.b. Perform Preparation C.Does FUNCTION display (3) indicate 200 to 300and does AC VOLTS display (4) indicate 3? NO(Anticipator pot R) TO SHT 49

Prop Sync Rcpt Pins1 P-B2576A-27, P-B2576A-302 P-A2576A-7, P-B2576A-303 P-A2576A-13, P-B2576A-304 P-B2576A-36, P-B2576A-30

YES

153155

Place RESISTANCE TEST switch (5) to 2.Gain access to and disconnect 156Does FUNCTION display (3) indicate 134 to 216plug P390 (1) at valve housingand does AC VOLTS display (4) indicate 3? Replace valveassembly. (Anticipator pot wiper R) housing assemblyNO NOIs 134K to 216K ohms resis- in accordance withtance present between pins KProp Sync Rcpt Pins TO 1C-130H-2-and S of valve housing assem-1 P-B2576A-13, P-B2576A-30 61JG-20-1, 61-20-bly receptacle (2)?2 P-B2576A-32, P-B2576A-30 02.

3 P-B2576A-35, P-B2576A-30 71 704 P-B2576A-33, P-B2576A-30

YESYES

TO SHT 53

154

Move throttle (6) to TAKE OFF.157Does FUNCTION display (3) indicate 24 to 58

and does AC VOLTS display (4) indicate 3? Replace valve(Anticipator pot wiper R in T/O pos) housing assemblyNO

in accordance withProp Sync Rcpt Pins TO 1C-130H-2-1 P-B2576A-13, P-B2576A-30 61JG- 20-1, 61-20-2 P-B2576A-32, P-B2576A-30 02. 3 P-B2576A-35, P-B2576A-304 P-B2576A-33, P-B2576A-30

YES

TO SHT 55

NOTE



61-20-004-62 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-63

TO 1C-130H-2-61FI-00-1

FROM SHT 47

158

Gain access to and disconnect plug 162P390 (3) at valve housing assembly.

Replace valve housing as-Is 200K to 300K ohms resistance pre- NOsembly in accordance withsent between pins K and T of valveTO 1C-130H-2-61JG-20-1,housing receptacle (4)?61-20-02.

71 72

YES

161

159 Gain access to and disconnect 163plug P398 (2) at engine fire-Is a ground present on plug P390 (3) Repair open circuit betweenNO YESwall.pin K? pin V of receptacle J239 (1)Is a ground present on plug and plug P390 pin K. (Seepin V?71

figure 4-6 or 4-7.) 59

YES

NO

164

Repair ground circuit. (Seefigure 4-6 or 4-7.)

160

a. Reconnect plug P390 (3) at valvehousing assembly. 165b. Gain access to and disconnect plug

Repair wiring fault betweenP398 (2) at engine firewall. NOreceptacle J239 pin T andIs 200K to 300K ohms resistance pre-plug P390 pin T. (See fig-sent between pins T and V of receptacleure 4-6 or 4-7.) J239 (1)?

60 59

YES

TO SHT 51

NOTE



61-20-004-64 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-65

TO 1C-130H-2-61FI-00-1

168FROM SHT 49 Repair wiring fault between pin

T of plug P398 (1) and related166 pin of receptacle P-A2576A (3).NO

Is an outboard propeller being (See figure 4-6 or 4-7.)troubleshot?

Rcpt Prop Pin2 73 13

YES

167

a. Reconnect plug P398 (1) atengine firewall.

169b. Gain access to and disconnectplug P1139 (4) at outer wing Repair wiring fault between re-NObreak. ceptacle J935 pin g and plugIs 200K to 300K ohms resistance P398 pin T. (See figure 4-6 orpresent between pin g of recepta- 4-7.) cle J935 (5) and airplane ground?

48

YES

170

Repair wiring fault between plugP1139 pin g and related pin ofreceptacle P-B2576A (2). (Seefigure 4-6 or 4-7.)

Prop Rcpt Pin1 274 36

NOTE





61-20-004-66 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-67

TO 1C-130H-2-61FI-00-1

FROM SHT 47

171

a. Reconnect plug P390 (3) at valve housingassembly. 174b. Gain access to and disconnect plug P398

Repair wiring fault between recep-NO(2) at engine firewall.

tacle J239 pin S and plug P390Is 134K to 216K ohms resistance present be-pin S. (See figure 4-6 or 4-7.) tween pins S and V of receptacle J239 (1)?

58 59

YES

175

Repair wiring fault between plugP398 pin S and related pin of re-ceptacle P-B2576A (4).172 NO(See figure 4-6 or 4-7.) Is an outboard propeller being troubleshot?

Rcpt Prop Pin2 323 35

YES

173

a. Reconnect plug P398 (2) at engine firewall.b. Gain access to and disconnect plug P1139 176(6) at outer wing break.

Repair wiring fault between plugIs 134K to 216K ohms resistance present be-P398 pin S and related receptacletween specified pin of receptacle J935 (5) andJ935 pin. (See figure 4-6 or 4-7.)NO

airplane ground?

Rcpt Prop PinProp Rcpt Pin Test Point1 f4 c1 f

47

4 c47

YES

177

Repair wiring fault between speci-fied plug P1139 pin and related pinof receptacle P-B2576A (4). (Seefigure 4-6 or 4-7.)

Prop Plug Pin Rcpt Pin1 f 134 c 33

NOTE





61-20-004-68 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-69

TO 1C-130H-2-61FI-00-1

FROM SHT 47

178

a. Move throttle (6) to FLIGHT IDLE/FLTIDLE.b. Place RESISTANCE TEST switch (5) to 3.Does FUNCTION display (3) indicate 8 to 11and does AC VOLTS display (4) indicate 3? NO(Feedback pot R) TO SHT 57

Prop Sync Rcpt Pins1 P-B2576A-16, P-B2576A-82 P-A2576A-3, P-A2576A-53 P-A2576A-6, P-A2576A-44 P-B2576A-17, P-B2576A-26

YES

179181

Place RESISTANCE TEST switch (5) to 4.Gain access to and discon-Does FUNCTION display (3) indicate 1 to 10.5nect plug P390 (1) at valve 182and does AC VOLTS display (4) indicate 3?housing assembly.(Feedback pot wiper R) Replace valve housingNO NOIs 1K to 10.5K ohms resis- assembly in accordancetance present between pinsProp Sync Rcpt Pins with TO 1C-130H-2-L and N of valve housing1 P-B2576A-16, P-B2576A-7 61JG-20-1, 61-20-02. assembly receptacle (2)?2 P-A2576A-14, P-A2576A-5

3 P-A2576A-6, P-A2576A-2 74 734 P-B2576A-23, P-B2576A-26

YESYES

TO SHT 63

180

Place RESISTANCE TEST switch (5) to 5.Does FUNCTION display (3) indicate 25 to 50ohms?(Speed bias control winding R) NO

TO SHT 65Prop Sync Rcpt Pins1 P-B2576A-5, P-B2576A-32 P-A2576A-34, P-A2576A-453 P-B2576A-14, P-B2576A-64 P-A2576A-24, P-B2576A-19

YES

TO SHT 71

NOTE



61-20-004-70 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-71

TO 1C-130H-2-61FI-00-1

FROM SHT 55

183


186assembly.Is 8K to 11K ohms resistance pre- Replace valve housing assem-NOsent between pins C and L of bly in accordance with TO 1C-valve housing assembly recepta- 130H-2-61JG-20-1, 61-20-02. cle (4)?

75 74

YES

184 185

a. Reconnect plug P390 (3) at a. Gain access to and disconnectvalve housing assembly. plug P390 (3) at valve housing 187b. Gain access to and disconnect assembly. Remove jumper wire. RepairNO NOplug P398 (2) at engine firewall. b. Install a jumper wire between wiring fault between receptacleIs 8K to 11K ohms resistance pre- plug pins K and L. J239 pin W and plug P390 pinsent between pins C and W of re- Is there continuity between recep- L. (See figure 4-6 or 4-7.) ceptacle J239 (1)? tacle J239 (1), pins V and W?

63 62 59 62

YES YES

TO SHT 59188

Remove jumper wire. Repairwiring fault between receptacleJ239 pin C and plug P390 pinC. (See figure 4-6 or 4-7.)

NOTE



61-20-004-72 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-73

TO 1C-130H-2-61FI-00-1

FROM SHT 57

189 YESTO SHT 61Is an outboard propeller being troubleshot?

NO

190191a. Install a jumper wire between pins V

and W of plug P398 (1). Remove jumper wire. Repairb. Remove junction box from syn- wiring fault between plug P398chrophaser rack. pin W and related receptacle P-Is a ground present on specified pin of re- A2576A pin. (See figure 4-6 orNOceptacle P-A2576A (2)? 4-7.)

Prop Rcpt Pin Test Point Prop Rcpt Pin

2 538

2 53 6

3 638

YES

192

Remove jumper wire. Repairwiring fault between plug P398pin C and related receptacle P-A2576A pin. (See figure 4-6 or4-7.)

Prop Rcpt Pin

2 53 6

NOTE



61-20-004-74 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-75

TO 1C-130H-2-61FI-00-1

FROM SHT 59

193 195196a. Reconnect plug P398 (1) at en- a. Install a jumper wire between

gine firewall. Remove jumper wire.plug P1139 (3) pin j and airplaneb. Gain access to and disconnect Repair wiring fault be-ground.plug P1139 (3) at outer wing break. tween plug P1139 pin jb. Remove junction box from syn-Is 8K to 11K ohms resistance pre- and related receptacle P-chrophaser rack.

YES NOsent between specified pins of recep- B2576A pin. (See figureIs a ground present on specified pintacle J935 (2)? 4-6 or 4-7.)of receptacle P-B2576A (4)?

Prop Rcpt Pins Test Points Prop Rcpt PinProp Rcpt Pins Test Points

1 j and k50 51

1 161 1638

4 264 j and e

50 514 26

38

NO YES

197

Remove jumper wire. Repairwiring fault between specifiedplug P1139 pin and related re-ceptacle P-B2576A pin. (Seefigure 4-6 or 4-7.)

Prop Plug Pin Rcpt Pin

1 k 84 e 17

194 198

a. Gain access to and disconnect Remove jumper wire. Repairplug P398 (1) at engine firewall. wiring fault between plug P398b. Install a jumper wire between pin C and related plug P1139YESplug pins V and W. pin. (See figure 4-6 or 4-7.) Is a ground present on receptacleJ935 (2) pin j? Prop Plug Pin

1 k50

4 e

NO

199

Remove jumper wire. Repairwiring fault between receptacleJ935 pin j and plug P398 pinW. (See figure 4-6 or 4-7.)

NOTE





61-20-004-76 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-77

TO 1C-130H-2-61FI-00-1

FROM SHT 55

200

a. Reconnect plug P390 (3) atvalve housing assembly. 203b. Gain access to and disconnect

Repair wiring fault between re-plug P398 (2) at engine firewall. NOceptacle J239 pin N and plugIs 1K to 10.5K ohms resistanceP390 pin N. (See figure 4-6 orpresent between pins N and W of4-7.) receptacle J239 (1)?

61 62

YES

204

Repair wiring fault between plugP398 pin N and related pin of

201 receptacle P-A2576A (5). (SeeNOIs an outboard propeller being figure 4-6 or 4-7.) troubleshot?


YES

202

a. Reconnect plug P398 (2) atengine firewall.

205b. Gain access to and disconnectplug P1139 (7) at outer wing Repair wiring fault between re-NObreak. ceptacle J935 pin h and plugIs 1K to 10.5K ohms resistance P398 pin N. (See figure 4-6 orpresent between pins h and j of 4-7.) receptacle J935 (6)?

49 50

YES

206

Repair wiring fault between plugP1139 pin h and related pin ofreceptacle P-B2576A (4). (Seefigure 4-6 or 4-7.)


NOTE





61-20-004-78 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-79

TO 1C-130H-2-61FI-00-1

FROM SHT 55

207


210assembly.Is 25 to 50 ohms resistance pre- Replace valve housing assem-NOsent between pins B and M of bly in accordance with TO 1C-valve housing assembly recepta- 130H-2-61JG-20-1, 61-20-02. cle (4)?

68 67

YES

208 209

a. Reconnect plug P390 (3) at a. Gain access to and disconnectvalve housing assembly. plug P390 (3) at valve housing 211b. Gain access to and disconnect assembly. Remove jumper wire. RepairNO YESplug P398 (2) at engine firewall. b. Install a jumper wire between open circuit between receptacleIs 25 to 50 ohms resistance pre- plug pins K and M. J239 pin B and plug P390 pinsent between pins B and X of re- Is there continuity between recep- B. (See figure 4-6 or 4-7.) ceptacle J239 (1)? tacle J239 (1) pins V and X?

56 55 59 55

YES NO

TO SHT 63212

Remove jumper wire. Repairopen circuit between receptacleJ239 pin X and plug P390 pinM. (See figure 4-6 or 4-7.)

NOTE



61-20-004-80 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-81

TO 1C-130H-2-61FI-00-1

FROM SHT 65

213YES


NO

214

a. Install a jumper wire between pins Band V of plug P398 (1). 215b. Remove junction box from syn-

Remove jumper wire. Repairchrophaser rack.open circuit between plug P398Is a ground present on specified pin ofpin X and related receptaclereceptacle P-A2576A (3) or P-B2576A YESpin. (See figure 4-6 or 4-7.)(2)?

Prop Rcpt PinProp Rcpt Pin Test Point2 P-A2576A-343 P-B2576A-142 P-A2576A-45

37

3 P-B2576A-637

NO

216

Remove jumper wire. Repairopen circuit between plug P398pin B and related receptaclepin. (See figure 4-6 or 4-7.)

Prop Rcpt Pin2 P-A2576A-453 P-B2576A-6

NOTE



61-20-004-82 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-83

TO 1C-130H-2-61FI-00-1

FROM SHT 67

220219217Remove jumpera. Gain access to and disconnecta. Reconnect plug P398 (1) at engine firewall.wire. Repair openplug P398 (1) at engine firewall.b. Gain access to and disconnect plug P1139circuit betweenb. Install a jumper wire between(4) at outer wing break.plug P398 pin Bplug pins B and V.Is 25 to 50 ohms resistance present betweenand related recep-Is a ground present on specifiedNO NOspecified pins of receptacle J935 (5)?tacle J935 pin.receptacle J935 (5) pin?(See figure 4-6 orProp Rcpt Pins Test Points4-7.)Prop Rcpt Pins Test Points

1 c and d44 45

Prop Rcpt Pin1 d45

1 d4 d and f44 45

4 f4 f45

YESYES

221

Remove jumper wire. Repair open circuitbetween plug P398 pin X and related recep-tacle J935 pin. (See figure 4-6 or 4-7.)

Prop Rcpt Pin1 c4 d

218

a. Install a jumper wire between plugP1139 (4) pin d and airplane ground. 222b. Remove junction box from syn-

Remove jumper wire. Repair open circuitchrophaser rack.between plug P1139 pin d and related re-Is a ground present on specified pin of re-ceptacle pin. (See figure 4-6 or 4-7.) NO

ceptacle P-B2576A (2) or P-A2576A (3)?

Prop Rcpt PinProp Rcpt Pin Test Point1 P-B2576A-34 P-A2576A-241 P-B2576A-3

37

4 P-A2576A-2437

YES

223

Remove jumper wire. Repair open circuit betweenspecified plug P1139 pin and related receptacle pin.(See figure 4-6 or 4-7.)

Prop Plug Pin Rcpt Pin1 c P-B2576A-54 f P-B2576A-19

NOTE





61-20-004-84 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-85

TO 1C-130H-2-61FI-00-1

FROM SHT 55

224

Place RESISTANCE TEST switch (4) to 6Does FUNCTION display (2) indicate 120to 180 ohms?(Speed bias ref winding R) NO

TO SHT 73Prop Sync Rcpt Pins1 P-B2576A-39, P-B2576A-302 P-A2576A-41, P-B2576A-303 P-A2576A-42, P-B2576A-304 P-B2576A-38, P-B2576A-30

YES

225

Move throttles (1) below GROUND IDLE/GND IDLE.

227Do FUNCTION display (2) and AC VOLTSdisplay (3) indicate 1999? Adjust or replace syn-(Sync disarming switch) chrophaser disarming switch (6)NO

as required in accordance withProp Sync Rcpt Pins TO 1C-130H-2-76JG-00-1, 76-1 P-B2576A-39, P-B2576A-30 10-33. 2 P-A2576A-41, P-B2576A-303 P-A2576A-42, P-B2576A-304 P-B2576A-38, P-B2576A-30

YES

226

a. Move throttles (1) above FLIGHT IDLE/FLT IDLE.b. Place propeller governor control switch-es (5) to MECH GOV/MECH.Does FUNCTION display (2) indicate 2281999? NO

Replace propeller governor con-(propeller governor control switch)trol switch.


YES

TO SHT 81

NOTE




61-20-004-86 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-87

TO 1C-130H-2-61FI-00-1

FROM SHT 71

229

Gain access to and disconnect plug P390 (3)233at valve housing assembly.

Is 120 to 180 ohms resistance present be- Replace valve housing assem-NOtween pins A and K of valve housing assembly in accordance with TO 1C-bly receptacle (4)? 130H-2-61JG-20-1, 61-20-02.

69 71

YES

230

a. Reconnect plug P390 (3) at valve housing234assembly.

b. Gain access to and disconnect plug P398 Repair open circuit between re-NO(2) at engine firewall. ceptacle J239 pin A and plugIs 120 to 180 ohms resistance present be- P390 pin A. (See figure 4-6 ortween pins A and V of receptacle J239 (1)? 4-7.)

57 59

YES

231

a. Reconnect plug P398 (2) at engine firewall.b. Disengage junction box from syn-chrophaser rack.

NOc. Gain access to terminals of propeller gov-TO SHT 75ernor control switch (5).

Is 120 to 180 ohms resistance present be-tween switch terminal 3 and airplane ground?

86

YES

232235Is there continuity between switch terminals 2

NOand 3? Replace propeller governor con-trol switch.

85 86

YES

TO SHT 77

NOTE





61-20-004-88 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-89

TO 1C-130H-2-61FI-00-1

FROM SHT 73 238

Repair open circuit between ter-236minal 3 of propeller governorNO

Is an outboard propeller beingcontrol switch (4) and pin A oftroubleshot? plug P398 (1). (See figure4-6or 4-7.) YES

237

Gain access to and disconnectplug P1139 (3) at outer wing 239break.

Repair open circuit between pinIs 120 to 180 ohms resistanceA of plug P398 (1) and relatedpresent between specified pin ofreceptacle J395 pin. (See fig-receptacle J935 (2) and airplane NOure 4-6 or 4-7.)ground?

Prop Rcpt PinProp Rcpt Pin Test Point1 e4 k1 e

46

4 k46

YES

240

Repair open circuit between ter-minal 3 of propeller governorcontrol switch (4) and relatedplug P1139 pin. (See figure 4-6 or 4-7.)

Prop Plug Pin1 e4 k

NOTE





61-20-004-90 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-91

TO 1C-130H-2-61FI-00-1

FROM SHT 73

241

Gain Access to terminal board TB126B (2).Is 120 to 180 ohms resistance present be- 243tween specified terminal and airplane ground?

Repair open circuit between terminal 2 ofpropeller governor control switch (4) andProp TB Term Test Pointrelated terminal board TB126A terminal.NO(See figure 4-6 or 4-7.)1 36

84

Prop TB Term Prop TB Term2 3784

1 36 3 382 37 4 393 38

84

4 3984

YES

242

Gain access to specified terminal board. 244Is 120 to 180 ohms resistance present be-

Repair open circuit between specified ter-tween specified terminal and airplane ground?minal and related pin of receptacle P-B2576A (5) or P-A2576A (6). (See fig-Prop TB-Term Test Pointure 4-6 or 4-7.)YES

1 TB135A (1) -16981

Prop TB-Term Rcpt Pin1 TB135A-169 P-B2576A-392 TB135A (1) -170

812 TB135A-170 P-A2576A-413 TB146A-210 P-A2576A-423 TB146A (3) -210

814 TB146A-211 P-B2576A-38

4 TB146A (3) -21181

NO

TO SHT 79

NOTE





61-20-004-92 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-93

TO 1C-130H-2-61FI-00-1

FROM SHT 77247

245 Repair open circuit between syn-Gain access to terminals of synchrophaser disarming switch terminalchrophaser disarming switch (3). 2NC and related terminal of terminalIs 120 to 180 ohms resistance board TB156A (1). (See figure 4-6 or 4-NOpresent between switch terminal 7.)2NC and airplane ground?

Prop TB Term Prop TB Term83

1 36 3 382 37 4 39

YES

248

Repair open circuit between syn-chrophaser disarming switch terminal2461NC and related terminal. (See figure 4-Is 120 to 180 ohms resistance6 or 4-7.)present between switch terminal YES

1NC and airplane ground?Prop TB-Term1 TB135A (4) -169822 TB135A (4) -1703 TB146A (2) -2104 TB146A (2) -211

NO

249

Adjust or replace synchrophaser disarm-ing switch as required in accordance withTO 1C-130H-2-76JG-00-1, 76-10-38.

NOTE



61-20-004-94 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-95

TO 1C-130H-2-61FI-00-1

FROM SHT 73

250 NOTO SHT 83Is an outboard propeller being troubleshot?

YES

251

a. Place TYPE SELECT switch (2) to TUBE.b. Place RESISTANCE TEST switch (3) to 8.Does FUNCTION display (1) indicate 30 to 45 YESohms? TO SHT 89(Clutch 1 and 4 winding parallel R)

Prop Sync Rcpt Pins1,4 P-A2576A-30, P-B2576A-30

NO

TO SHT 107


61-20-004-96 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-97

TO 1C-130H-2-61FI-00-1

254

a. Place TYPE SELECT switch (4) toTUBE.b. Place RESISTANCE TEST switch(5) to 8.

FROM SHT 81 c. Place SYNCHROPHASE MASTER/MSTR switch (2) to engine 2.

252 NO NOd. Momentarily hold PROP RESYN- TO SHT 85Is No. 2 propeller (1) being troubleshot? CHROPHASE/PROP SYNC switch (3)to RESYNC/INDEX.Does FUNCTION display (6) indicate 20to 30 ohms while switch is held(Clutch 3 winding R)

Prop Synch Rcpt Pins3 P-A2576A-30, P-B2576A-30

YES

YES

TO SHT 89

253

a. Place TYPE SELECT switch (4) toTUBE.b. Place RESISTANCE TEST switch(5) to 8.c. Place SYNCHROPHASE MASTER/MSTR switch (2) to engine 3.

NOd. Momentarily hold PROP RESYN-TO SHT 87CHROPHASE/PROP SYNC switch (3)

to RESYNC/INDEX.Does FUNCTION display (6) indicate 20to 30 ohms while switch is held(Clutch 2 winding R)

Prop Synch Rcpt Pins2 P-A2576A-30, P-B2576A-30

YES

TO SHT 89


61-20-004-98 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-99

TO 1C-130H-2-61FI-00-1

FROM SHT 83

255

Gain access to and disconnect plug P390259(6) at valve housing assembly.

Is 60 to 90 ohms resistance present be- Replace valve housing assembly in ac-NOtween pins K and P of valve housing as- cordance with TO 1C-130H-2-61JG-20-1,sembly receptacle (5)? 61-20-02.

71 76

YES

256

a. Reconnect plug P390 (6) to valve hous-ing assembly. 260b. Gain access to and disconnect plug

Repair open circuit between receptacleNOP398 (2) at engine firewall.J239 pin P and plug P390 pin P. (SeeIs 60 to 90 ohms resistance present be-figure 4-6.) tween pins P and V of receptacle J239 (1)?

64 59

YES

257

a. Reconnect plug P398 (2) at engine fire-wall.

261b. Gain access to terminals of SYN-NOCHROPHASE MASTER/MSTR switch (3). Replace SYNCHROPHASE MASTER/

Is there continuity between switch terminals MSTR switch.4 and 5?

20 16

YES

258

Gain access to terminal board TB128A (4). 262Is there continuity between terminal board

Repair open circuit between terminalYESterminal 18 and SYNCHROPHASEboard terminal 18 and plug P398 pin P.MASTER/MSTR switch (3) terminal 4?(See figure 4-6 or 4-7.)

31 20

NO

263


NOTE



61-20-004-100 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-101

TO 1C-130H-2-61FI-00-1

FROM SHT 83

264

Gain access to and disconnect plug P390 (6) at valve 268housing assembly.

Replace valve housing assem-NOIs 60 to 90 ohms resistance present between pins K and P

bly in accordance with TO 1C-of valve housing assembly receptacle (5)?130H-2-61JG-20-1, 61-20-02.

71 76

YES

265

a. Reconnect plug P390 (6) to valve housing assembly. 269b. Gain access to and disconnect plug P398 (2) at engine

Repair open circuit between re-firewall. NOceptacle J239 pin P and PlugIs 60 to 90 ohms resistance present between pins P and VP390 pin P. (See figure 4-6 orof receptacle J239 (1)?4-7.)

64 59

YES

266

a. Reconnect plug P398 (2) at engine firewall.270b. Gain access to terminals of SYNCHROPHASE

NOMASTER/MSTR switch (3). Replace SYNCHROPHASEIs there continuity between switch terminals 5 and 6? MASTER/MSTR switch.

16 21

YES

267271

Gain access to terminal board TB128A (4).Repair open cirucit between ter-Is there continuity between terminal board terminal 19 and YESminal board terminal 19 andSYNCHROPHASE MASTER/MSTR switch (3) terminal 6?plug P398 pin P. (See figure 4-6 or 4-7.) 32 21

NO

272

Repair open circuit. (See figure4-6 or 4-7.)

NOTE



61-20-004-102 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-103

TO 1C-130H-2-61FI-00-1

FROM SHT 81 OR 83

273

NOTEDuring megger checks, an indication of1999 in both the FUNCTION and ACVOLTS displays is an acceptable measure-ment.

a. Place SYNCHROPHASE MASTER/MSTR switch (5) to OFF.b. Place TYPE SELECT switch (2) toSOLID STATE.c. Place RESISTANCE TEST switch (4) to13. NODoes FUNCTION display (1) indicate 0.5 or TO SHT 91greater and does AC VOLTS display (3) in-dicate 6?(Control winding megger chk)

Prop Sync Rcpt Pins

1 P-B2576A-5, P-B2576A-30

2 P-A2576A-34, P-B2576A-30

3 P-B2576A-14, P-B2576A-30

4 P-A2576A-24, P-B2576A-30

YES

274

Place RESISTANCE TEST switch (4) to14.Does FUNCTION display (1) indicate 1.0 orgreater and does AC VOLTS display (3) in-dicate 6?(Feedback pot megger chk)

NOProp Sync Rcpt Pins TO SHT 99

1 P-B2576A-8, P-B2576A-30

2 P-A2576A-14, P-B2576A-30

3 P-A2576A-2, P-B2576A-30

4 P-B2576A-23, P-B2576A-30

YES

TO SHT 141


61-20-004-104 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-105

TO 1C-130H-2-61FI-00-1

FROM SHT 89

275

a. Gain access to and disconnect279plug P390 (3) at valve housing

assembly. Remove jumper wire. ReplaceYESb. Install a jumper wire between valve housing assembly in ac-plug pins B and M. cordance with TO 1C-130H-2-Does FUNCTION display (5) indi- 61JG-20-1, 61-20-02. cate 0.5 or greater and does ACVOLTS display (4) indicate 6?

NO

276

a. Remove jumper wire from plugP390 (3) but do not reconnectplug.

278b. Gain access to and disconnect NO NOplug P398 (2) at engine firewall. TO SHT 93Is an outboard propeller beingc. Install a jumper wire between troubleshot? plug P398 pins B and X.Does FUNCTION display (5) indi-cate 0.5 or greater and does ACVOLTS display (4) indicate 6?

YES

YES

TO SHT 95


P398 (2) and reconnect plug at Repair ground fault between pinNOengine firewall. X of receptacle J239 (1) andDoes FUNCTION display (5) indi- plug P390 pin M. (See figurecate 0.5 or greater and does AC 4-6 or 4-7.) VOLTS display (4) indicate 6?

YES

281



61-20-004-106 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-107

TO 1C-130H-2-61FI-00-1

FROM SHT 91 283

Repair ground fault between282plug P398 pin X and related pinRemove jumper wire from plugof receptacle P-A2576A (3) orP398 (1) but do not reconnectP-B2576A (2). (See figure 4-6NO

plug.or 4-7.)Does FUNCTION display (5) indi-

cate 0.5 or grater and does ACProp Rcpt PinVOLTS display (4) indicate 6? 2 P-A2576A-343 P-B2576A-14YES

284

Repair ground fault betweenplug P398 pin B and related pinof receptacle P-A2576A (3) orP-B2576A (2). (See figure 4-6or 4-7.)

Prop Rcpt Pin2 P-A2576A-453 P-B2576A-6


61-20-004-108 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-109

TO 1C-130H-2-61FI-00-1

FROM SHT 91

285

a. Remove jumper wire from plugP398 (1) but do not reconnectplug.b. Gain access to and disconnectplug P1139 (5) at outer wingbreak.c. Install a jumper wire between NOspecified plug pins. TO SHT 97

Prop Plug Pins1 c and d4 d and f


YES

287286 Repair ground fault between

Remove jumper wire from plug plug P398 pin X and related pinP1139 (5) and reconnect plug at of receptacle J935 (4). (SeeNOouter wing break. figure 4-6 or 4-7.) Does FUNCTION display (3) indi-cate 0.5 or greater and does AC Prop Rcpt PinVOLTS display (2) indicate 6? 1 c

4 dYES

288

Repair ground fault betweenplug P398 pin B and related pinof receptacle J935 (4). (Seefigure 4-6 or 4-7.)

Prop Rcpt Pin1 d4 f

NOTE




61-20-004-110 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-111

TO 1C-130H-2-61FI-00-1

FROM SHT 95290

289 Repair ground fault between specifiedRemove jumper wire from plug plug P1139 pin and related pin of re-P1139 (5) but do not reconnect ceptacle P-B2576A (3). (See figureYESplug. 4-6 or 4-7.)Does FUNCTION display (1) indi-cate 0.5 or greater and does AC Prop Plug Pin Rcpt PinVOLTS display (2) indicate 6? 1 d P-B2576A-3

4 f P-B2576A-19NO

291

Repair ground fault between specifiedplug P130/P1139 pin and related pinof receptacle P-A2576A (4) or P-B2576B (3). (See figure 4-6 or 4-7.)

Prop Plug Pin Rcpt Pin1 c P-B2576A-54 d P-A2576A-24

NOTE




61-20-004-112 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-113

TO 1C-130H-2-61FI-00-1

FROM SHT 89

292

a. Gain acess to and disconnect 295 298plug P390 (3) at valve housingRemove jumper wire and install itassembly. Remove jumper wire. ReplaceYES YESbetween plug pins C and N.b. Install a jumper wire between valve housing in accordanceDoes FUNCTION display (5) indi-plug pins C and L. with TO 1C-130H-2-61JG-20-1,cate 1.0 or greater and does ACDoes FUNCTION display (5) indi- 61-20-02. VOLTS display (4) indicate 6?cate 1.0 or greater and does AC

VOLTS display (4) indicate 6?

NO

NO

296299a. Remove jumper wire from plug P390

(3). Remove jumper wire.b. Gain access to and disconnect plug Repair ground fault

YESP398 (2) at engine firewall. between pin N of re-c. Install jumper wire between plug P398 ceptacle J239 (1) and(2) pins C and N. plug P390 pin N.Does FUNCTION display (5) indicate 1.0 or (See figure 4-6 or 4-greater and does AC VOLTS display (4) in- 7.) dicate 6?

NO

TO SHT 101

300297293Repair ground faulta. Remove jumper wire from plug P390 (3).Remove jumper wire and install itbetween pin C ofb. Gain access to and disconnect plug P398NO YESbetween plug pins C and N.receptacle J239 (1)(2) at engine firewall.Does FUNCTION display (5) indi-and plug P390 pinDoes FUNCTION display (5) indicate 1.0 orcate 1.0 or greater and does ACC. (See figure 4-6greater and does AC VOLTS display (4) indi-VOLTS display (4) indicate 6?or 4-7.) cate 6?

YESNO

TO SHT 103

294

a. Remove jumper wire from plug P390 (3).301b. Gain access to and disconnect plug P398

(2) at engine firewall. Remove jumper wire. Repair groundYESc. Install jumper wire between plug P398 (2) fault between pin W of receptaclepins C and W. J239 (1) and plug P390 pin L. (SeeDoes FUNCTION display (5) indicate 1.0 or figure 4-6 or 4-7.) greater and does AC VOLTS display (4) indi-cate 6?

NO

TO SHT 105


61-20-004-114 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-115

TO 1C-130H-2-61FI-00-1

304

Remove jumper wire. RepairFROM SHT 99ground fault between pin N ofplug P398 (1) and related pin of302receptacle P-A2576A (5). (SeeNO

Is an outboard propeller beingfigure 4-6 or 4-7.) troubleshot?


YES

303


305b. Gain access to and disconnectplug P1139 (7) at outer wing Remove jumper wire. Repairbreak. ground fault between plugc. Install jumper wire between P1139 pin h and related pin ofspecified plug P1139 (7) pins. receptacle P-B2576A (4). (SeeNO

figure 4-6 or 4-7.) Prop Plug Pin1 h and k Prop Rcpt Pin4 e and h 1 7


YES

306

Remove jumper wire. Repairground fault between pin h ofreceptacle J935 (6) and plugP398 pin N. (See figure 4-6 or4-7.)

NOTE




61-20-004-116 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-117

TO 1C-130H-2-61FI-00-1

309FROM SHT 99 Repair ground fault between pin C of

plug P398 (1) and related pin of re-307 ceptacle P-A2576A (5). (See figureNO

Is an outboard propeller being 4-6 or 4-7.) troubleshot?

Prop Rcpt Pin2 33 4

YES

310308 Repair ground fault between specified

Gain access to and disconnect plug P1139 pin and related pin of re-plug P1139 (6) at outer wing ceptacle P-B2576A (4). (See figureNObreak. 4-6 or 4-7.) Does FUNCTION display (2) indi-cate 1.0 or greater and does AC Prop Plug Pin Rcpt PinVOLTS display (3) indicate 6? 1 k 8

4 e 17YES

311

Repair ground fault between pin C ofplug P398 (1) and related plug P1139pin. (See figure 4-6 or 4-7.)

Prop Rcpt Pin1 k4 e

NOTE




61-20-004-118 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-119

TO 1C-130H-2-61FI-00-1

314

Remove jumper wire. RepairFROM SHT 99ground fault between pin W ofplug P398 (1) and related pin of312receptacle P-A2576A (5). (SeeNO

Is an outboard propeller beingfigure 4-6 or 4-7.)troubleshot?

Prop Rcpt Pin2 53 6

YES

313


315b. Gain access to and disconnectplug P1139 (7) at outer wing Remove jumper wire. Repairbreak. ground fault between plugc. Install jumper wire between P1139 pin j and related pin ofspecified plug P1139 (7) pins. receptacle P-B2576A (4). (SeeNO

figure 4-6 or 4-7.)Prop Plug Pin1 j and k Prop Rcpt Pin4 e and j 1 16


YES

316

Remove jumper wire. Repairground fault between pin j of re-ceptacle J935 (6) and plugP398 pin W. (See figure 4-6 or4-7.)

NOTE




61-20-004-120 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-121

TO 1C-130H-2-61FI-00-1

FROM SHT 81

317

Gain access to and disconnect plug320P390 (3) at valve housing assembly.

Is 60 to 90 ohms resistance present be- Replace valve housing assem-NOtween pins K and P of valve housing bly in accordance with TO 1C-assembly receptacle (4)? 130H-2-61JG-20-1, 61-20-02.

71 76

YES

318

a. Reconnect plug P390 (3) to valve321housing assembly.

b. Gain access to and disconnect plug Repair open circuit between pinNOP398 (2) at engine firewall. P of receptacle J239 (1) andIs 60 to 90 ohms resistance present be- plug P390 pin P. (See figure 4-tween plug pins P and V? 6 or 4-7.)

64 59

YES

319

a. Reconnect plug P398 (2) at enginefirewall. 322b. Gain access to and disconnect plug

Repair open circuit between re-P1139 (7) at outer wing break. NOceptacle J935 pin m and plugIs 60 to 90 ohms resistance present be-P398 pin P. (See figure 4-6 ortween pin m of receptacle J935 (6) and4-7.) airplane ground?

52

YES

323

Repair open circuit betweenplug P1139 pin m and terminal9 of terminal board TB1C (5).(See figure 4-6 or 4-7.)

NOTE





61-20-004-122 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-123

TO 1C-130H-2-61FI-00-1

FROM SHT 3 OR 43

324 6120007, 6120008,6120009, 6120010

a. Shut down engines in accordance with TO 1C-130H-2-71JG-00-1, 71-00-10.b. If necessary, perform Preparation C.c. If necessary, place propeller governor control switches (5) to NORMAL/NORM. NOd. Place RESISTANCE TEST switch (4) to 7. TO SHT 111Does FUNCTION display (1) indicate 0.3 to 10 ohms? (Pulse gen R)

Prop Sync Rcpt Pins1 P-B2576A-20, P-B2576A-342 P-A2576A-28, P-A2576A-373 P-A2576A-36, P-A2576A-294 P-B2576A-1, P-B2576A-31

YES

325

NOTEDuring megger checks, an indication of 1999 in both the FUNCTION and ACVOLTS displays is an acceptable measurement.

a. Place SYNCHROPHASE MASTER/MSTR switch (6) to OFF.b. Place TYPE SELECT switch (2) to SOLID STATE.c. Place RESISTANCE TEST switch (4) to 12. NODoes FUNCTION display (1) indicate 1.0 or greater and does AC VOLTS TO SHT 125display (3) indicate 6?(Pulse gen megger chk)


YES

TO SHT 141

NOTE


2 Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.Figure 4-5. Synchrophaser System Malfunction (Sheet 109)

61-20-004-124 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-125

TO 1C-130H-2-61FI-00-1

FROM SHT 109

326 328

Gain access to and disconnect Remove pulse generator (4) in ac-plug P392 (2) at pump housing. cordance with TO 1C-130H-2- 330Is 0.3 to 0.5 ohm resistance pre- 61JG-20-1, 61-20-10.NO NO Replace pulse generator in ac-sent between pins A and B of Is 0.3 to 0.5 ohm resistance pre- cordance with TO 1C-130H-2-valve housing assembly recepta- sent between the two pulse gen- 61JG-20-1, 61-20-10. cle (3)? erator pins?

77 78 79 80

YES YES

331

Repair or replace pulse genera-tor wiring on pump housing (5).

327 329

a. Reconnect plug P392 (2) to a. Gain access to and disconnectpump housing. plug P392 (2) at pump housing. 332b. Gain access to and disconnect b. Install a jumper wire between Remove jumper wire. RepairNO NOplug P396 (6) at engine firewall. plug pins A and E (ground). wiring fault between receptacleIs 0.3 to 0.5 ohm resistance pre- Is resistance between receptacle J241 pin A and plug P392 pinsent between pins A and B of re- J241 (1) pins A and E less than 1 A. (See figure 4-6 or 4-7.) ceptacle J241 (1)? ohm?

65 66 65

YES YES

TO SHT 113333


NOTE

See figure 4-6 or 4-7 for: Figure 4-5. Synchrophaser System Malfunction (Sheet 111)

61-20-004-126 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-127

TO 1C-130H-2-61FI-00-1

FROM SHT 111

334YES


NO

335NO


YES

336

a. Reconnect plug P396 (1) atengine firewall.b. Gain access to and disconnectplug P1225 (3) at outer wing YESbreak. TO SHT 123Is 0.3 to 0.7 ohm resistance pre-sent between pins A and B of re-ceptacle J660 (2)?

53 54

NO

337

a. Gain access to and disconnectplug P396 (1) at engine firewall. 338b. Install a jumper wire between

Remove jumper wire. Repairplug pins A and E (ground). NOwiring fault between receptacleIs resistance between receptacleJ660 pin A and plug P396 pinJ660 (2) pin A and airplaneA. (See figure 4-6.) ground less than 1 ohm?

53

YES

339

Remove jumper wire. Repairwiring fault between receptacleJ660 pin B and plug P396 pinB. (See figure 4-6.)

NOTE

See figure 4-6 for:


61-20-004-128 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-129

TO 1C-130H-2-61FI-00-1

FROM SHT 113341

a. Gain access to and disconnect340plug P396 (1) at engine firewall.a. Reconnect plug P396 (1) atb. Install a jumper wire betweenengine firewall.plug pins A and E (ground). 342b. Gain access to terminalc. Remove junction box fromboard TB105AG (2). Remove jumper wire. Repair wir-synchrophaser rack.Is 0.3 to 0.7 ohm resistance ing fault between specified recep-Is resistance between specifiedpresent between specified ter- tacle pin and related terminalpin of receptacle P-B2576A (3) orminals? board TB105AG terminal. (SeeP-A2576A (4) and airplane groundYES NO figure 4-6 or 4-7.)less than 1 ohm?Prop TB Term TestPoints

Prop Rcpt Pin TB TermProp Rcpt Pin Test Point1 1 and 2

43 421 P-B2576A-34 22 P-A2576A-37 4

1 P-B2576A-3439

2 3 and 443 42

3 P-A2576A-36 64 P-B2576A-1 8

2 P-A2576A-3739

3 5 and 643 42

3 P-A2576A-3639

4 7 and 843 42

4 P-B2576A-139

NO

YES

TO SHT 117343

Remove jumper wire. Repair wir-ing fault between specified recep-tacle pin and related terminalboard TB105AG terminal. (Seefigure 4-6 or 4-7.)

Prop Rcpt Pin TB Term1 P-B2576A-20 12 P-A2576A-28 33 P-A2576A-29 54 P-B2576A-31 7

NOTE



61-20-004-130 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-131

TO 1C-130H-2-61FI-00-1

346

a. Gain access to and disconnectplug P396 (1) at engine firewall. 348b. Install a jumper wire between Remove jumper wire. RepairFROM SHT 115 plug pins A and E (ground). wiring fault between plug P396Is resistance between specified pin A and related terminal344 terminal of terminal boardNO NO board TB105AG terminal. (SeeIs an outboard propeller being TB105AG (2) and airplane ground figure 4-6 or 4-7.)troubleshot? less than 1 ohm?

Prop TB TermProp TB Term Test Point 2 4

3 62 4

42

3 642

YES

YES349


Prop TB Term2 33 5

347345a. Gain access to and disconnectGain access to and disconnectplug P396 (1) at engine firewall. 350plug P1225 (3) at outer wingb. Install a jumper wire betweenbreak. Remove jumper wire. RepairNO NOplug pins A and E (ground).Is 0.3 to 0.7 ohm resistance pre- wiring fault between receptacleIs resistance between receptaclesent between pins A and B of re- J660 pin A and plug P396 pinJ660 (4) pin A and airplaneceptacle J660 (4)? A. (See figure 4-6 or 4-7.) ground less than 1 ohm?

53 5453

YESYES

TO SHT 119351


NOTE



61-20-004-132 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-133

TO 1C-130H-2-61FI-00-1

FROM SHT 117

352

a. Gain access to and disconnectplug P1225 (1) at outer wing

353break.b. Install a jumper wire between Remove jumper wire. Repairplug pin A and airplane ground. wiring fault between plug P1225Is resistance between specified pin A and related terminalterminal of terminal board board TB105AG terminal. (SeeNOTB105AG (2) and airplane ground figure 4-6 or 4-7.)less than 1 ohm?

Prop TB TermProp TB Term Test Point 1 2

4 81 2

42

4 842

YES

354


Prop TB Term1 14 7

NOTE



61-20-004-134 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-135

TO 1C-130H-2-61FI-00-1

FROM SHT 113

355

a. Install a jumper wire between pins A356and E (ground) of plug P396 (1).

b. Remove junction box from syn- Remove jumper wire. Repairchrophaser rack. wiring fault between plug P396Is resistance on specified pin of receptacle pin A and related receptacle P-NOP-A2576A (2) less than 1 ohm? A2576A pin. (See figure 4-6.)

Prop Rcpt Pin Test Point Prop Rcpt Pin2 37

2 3739

3 36

3 3639

YES

357

Remove jumper wire. Repairwiring fault between plug P396pin B and related receptacle P-A2576A pin. (See figure 4-6.)


NOTE

See figure 4-6 for:


61-20-004-136 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-137

TO 1C-130H-2-61FI-00-1

FROM SHT 113

358

a. Install a jumper wire betweenpin A of plug P1225 (1) and

359airpane ground.b. Remove junction box from Remove jumper wire. Repairsynchrophaser rack. wiring fault between plug P1225Is resistance on specified pin of pin A and related receptacle P-NOreceptacle P-B2576A (2) less than B2576A pin. (See figure 4-6.) 1 ohm?

Prop Rcpt PinProp Rcpt Pin Test Point 1 34

4 11 34

39

4 139

YES

360

Remove jumper wire. Repairwiring fault between plug P1225pin B and related receptacle P-B2576A pin. (See figure 4-6.)


NOTE

See figure 4-6 for:


61-20-004-138 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-139

TO 1C-130H-2-61FI-00-1

FROM SHT 109 364

a. Remove jumper wire from plug P392361 (2) and reconnect plug at pump hous-

a. Gain access to and discon- ing.nect plug P392 (2) at pump b. Remove pulse generator (3) in ac- 366housing. cordance with TO 1C-130H-2-61JG-20- Remove jumper wire. Re-YES YESb. Install a jumper wire be- 1, 61-20-10. place pulse generator in ac-tween plug pins A and B. c. Install a jumper wire between the cordance with TO 1C-130H-Does FUNCTION display (5) two pins of the pulse generator wiring 2-61JG-20-1, 61-20-10. indicate 1.0 or greater and harness where the pulse generator con-does AC VOLTS display (4) in- nects.dicate 6? Does FUNCTION display (5) indicate

1.0 or greater and does AC VOLTS dis-play (4) indicate 6?NO

NO367

Repair or replace pulse genera-tor wiring on pump housing.

362

a. Remove jumper wire from plug365P392 (2) but do not reconnect

368plug. Remove jumper wire from plugb. Gain access to and disconnect Repair ground fault between pinP396 (6) and reconnect plug atYES NOplug P396 (6) at engine firewall. A of receptacle J241 (1) andengine firewall.c. Install a jumper wire between plug P392 pin A. (See figure 4-Does FUNCTION display (5) indi-plug P396 (6) pins A and B. 6 or 4-7.) cate 1.0 or greater and does ACDoes FUNCTION display (5) indi- VOLTS display (4) indicate 6? cate 1.0 or greater and does ACVOLTS display (4) indicate 6?

NO

YES

369


363NO


YES

TO SHT 133


61-20-004-140 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-141

TO 1C-130H-2-61FI-00-1

FROM SHT 125

370YES

Is airplane being troubleshot TO SHT 129model AF90-1057 and up?

NO

372371 Repair ground fault between

Remove jumper wire from plug plug P396 pin A and related pinP396 (1) but do not reconnect of receptacle P-A2576A (2).NOplug. (See figure 4-6.) Does FUNCTION display (4) indi-cate 1.0 or greater and does AC Prop Rcpt PinVOLTS display (3) indicate 6? 2 37

3 36YES

373

Repair ground fault betweenplug P396 pin B and related pinof receptacle P-A2576A (2).(See figure 4-6.)



61-20-004-142 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-143

TO 1C-130H-2-61FI-00-1

FROM SHT 127

374

Remove jumper wire from plug P396 (1)YESbut do not reconnect plug.

TO SHT 131Does FUNCTION display (2) indicate1.0 or greater and does AC VOLTS dis-play (3) indicate 6?

NO

375

Gain access to terminal board TB105AG(4) and disconnect specified wire from

377specified terminal. (Leave remaining twowires securely attached.) Repair ground fault on specified

wire. (See figure 4-6 or 4-7.) YESProp Wire No. TB Term2 2K95D20 4 Prop Wire No.3 3K95D20 6 2 2K95D20

3 3K95D20Does FUNCTION display (2) indicate1.0 or greater and does AC VOLTS dis-play (3) indicate 6?

NO

376

Disconnect remaining wires from speci- 378fied terminal board TB105AG (4) termi-

Repair ground fault between plugnal. P396 pin A and related terminalboard TB105AG terminal. (See fig-Prop TB Term YESure 4-6 or 4-7.)2 4

3 6Prop TB Term2 4Does FUNCTION display (2) indicate3 61.0 or greater and does AC VOLTS dis-

play (3) indicate 6?

NO

379

Repair ground fault between speci-fied terminal board TB105AG ter-minal and related pin of receptacleP-A2576A (5). (See figure 4-6 or4-7.)

Prop TB Term Rcpt Pin2 4 373 6 36


61-20-004-144 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-145

TO 1C-130H-2-61FI-00-1

FROM SHT 129

380

a. Reinstall jumper wire betweenpins A and B of plug P396 (1).b. Gain access to terminal board

382TB105AG (4) and disconnect speci-fied wire from specified terminal. Remove jumper wire. Repair ground(Leave remaining two wires securely fault on specified wire. (See figure 4-6attached.) or 4-7.)YES

Prop Wire No. TB Term Prop Wire No.2 2K97D20 3 2 2K97D203 3K97D20 5 3 3K97D20

Does FUNCTION display (2) indicate1.0 or greater and does AC VOLTSdisplay (3) indicate 6?

NO

381

Disconnect remaining wires from 383specified terminal board TB105AG

Remove jumper wire. Repair ground(4) terminal.fault between plug P396 pin B and re-lated terminal board TB105AG termi-Prop TB Term NOnal. (See figure 4-6 or 4-7.)2 3

3 5Prop TB Term2 3Does FUNCTION display (2) indicate3 51.0 or greater and does AC VOLTS

display (3) indicate 6?

YES

384

Remove jumper wire. Repair groundfault between specified terminal boardTB105AG terminal and related pin ofreceptacle P-A2576A (5). (See figure4-6 or 4-7.)



61-20-004-146 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-147

TO 1C-130H-2-61FI-00-1

FROM SHT 125

385YES


NO

386

a. Remove jumper wire from plugP396 (1) but do not reconnectplug.b. Gain access to and disconnect

NOplug P1225 (5) at outer wingTO SHT 139break.

c. Install a jumper wire betweenplug P1225 (5) pins A and B.Does FUNCTION display (3) indi-cate 1.0 or greater and does ACVOLTS display (2) indicate 6?

YES


P1225 (5) and reconnect plug at Repair ground fault between pinYESouter wing break. B of receptacle J660 (4) andDoes FUNCTION display (3) indi- plug P396 pin B. (See figure 4-cate 1.0 or greater and does AC 6.) VOLTS display (2) indicate 6?

NO

389

Repair ground fault between pinA of receptacle J660 (4) andplug P396 pin A. (See figure 4-6.)


61-20-004-148 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-149

TO 1C-130H-2-61FI-00-1

FROM SHT 133

390

Remove jumper wire from plug P396 (1) but do not reconnect YESplug. TO SHT 137Does FUNCTION display (2) indicate 1.0 or greater and doesAC VOLTS display (3) indicate 6?

NO

391

Gain access to terminal board TB105AG (4) and disconnect 394specified wire from specified terminal. (Leave remaining two

Repair ground fault onwires securely attached.)specified wire. (Seefigure 4-6 or 4-7.) YES

Prop Wire No. TB Term1 1K95E20 2

Prop Wire No.4 4K95E20 81 1K95E204 1K95E20Does FUNCTION display (2) indicate 1.0 or greater and does

AC VOLTS display (3) indicate 6?

NO

392393

Disconnect remaining wires from 395a. Reconnect all wires tospecified terminal board TB105AGRepair ground fault between plugterminal board TB105AG(4) terminal. P1225 pin A and related terminal(4).board TB105AG terminal. (See figureb. Gain access to and dis-YES NOProp TB Term4-6 or 4-7.) connect plug P1225 (6) at1 2

outer wing break.4 8Prop TB TermDoes FUNCTION display1 2(2) indicate 1.0 or greaterDoes FUNCTION display (2) indi-4 8and does AC VOLTS dis-cate 1.0 or greater and does AC

play (3) indicate 6?VOLTS display (3) indicate 6?

NOYES

396

Repair ground fault between pin A of receptacle J660(7) and plug P396 pin A. (See figure 4-6 or 4-7.)

397

Repair ground fault between specified terminal boardTB105AG terminal and related pin of receptacle P-B2576A (5). (See figure 4-6 or 4-7.)



61-20-004-150 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-151

TO 1C-130H-2-61FI-00-1

FROM SHT 135

398

a. Reinstall jumper wire between pins A and B ofplug P396 (1).b. Gain access to terminal board TB105AG (4) 401and disconnect specified wire from specified ter-

Remove jumper wire. Repair groundminal. (Leave remaining two wires securely at-fault on specified wire. (See figure 4-tached.)6 or 4-7.)YES

Prop Wire No. TB TermProp Wire No.1 1K97E20 11 1K97E204 4K97E20 74 1K97E20

Does FUNCTION display (2) indicate 1.0 orgreater and does AC VOLTS display (3) indicate6?

NO

399402

Disconnect remaining wires from specified termi-Remove jumper wire. Repair groundnal board TB105AG (4) terminal.fault between specified terminal boardTB105AG terminal and related pin ofProp TB Termreceptacle P-B2576A (5). (See figureYES

1 14-6 or 4-7.)4 7

Prop TB Term Rcpt PinDoes FUNCTION display (2) indicate 1.0 or1 1 20greater and does AC VOLTS display (3) indicate4 7 316?

NO

400403

a. Remove jumper wire from plug P396 (1) butRemove jumper wire. Repair grounddo not reconnect plug.fault between plug P1225 pin B andb. Gain access to and disconnect plug P1225 (6)related terminal board TB105AG ter-at outer wing break. NOminal. (See figure 4-6 or 4-7.)c. Install jumper wire between plug P1225 (6)

pins A and B.Prop TB TermDoes FUNCTION display (2) indicate 1.0 or1 1greater and does AC VOLTS display (3) indicate4 76?

YES

404

Remove jumper wire. Repair groundfault between pin B of receptacleJ660 (7) and plug P396 pin B. (Seefigure 4-6 or 4-7.)


61-20-004-152 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-153

TO 1C-130H-2-61FI-00-1

FROM SHT 133406

405 Repair ground fault betweenRemove jumper wire from plug plug P1225 pin B and relatedP1225 (4) but do not reconnect pin of receptacle P-B2576A (3).YESplug. (See figure 4-6.)Does FUNCTION display (1) indi-cate 1.0 or greater and does AC Prop Rcpt PinVOLTS display (2) indicate 6? 1 20

4 31NO

407

Repair ground fault betweenplug P1225 pin A and relatedpin of receptacle P-B2576A (3).(See figure 4-6.)



61-20-004-154 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-155

TO 1C-130H-2-61FI-00-1

FROM SHT 89 OR 109

408

a. Open PROP SYNCHRO PHASER and SYNCHROPHASER circuit breakers (1,2).b. Install synchrophaser (4) in rack, ensuring it seats injunction box connectors (3). Secure synchrophaser withlocking clamps.c. Close PROP SYNCHRO PHASER and SYNCHRO 411PHASER circuit breakers (1,2).

Replace propeller syn-d. Place FUNCTION SELECT switch (6) to DCV. NOchrophaser in accordance withe. Place TEST SELECT switch (5) to 2.TO 1C-130H-2-61JG-20-1, 61-Does FUNCTION display (7) indicate 11 to 14 volts?20-13. (Feedback pot V supply)


YES

409

Place TEST SELECT switch (5) to 3.Does FUNCTION display (7) indicate -11 to -14 volts? 412(Feedback pot -V supply)

Replace propeller syn-NOchrophaser in accordance withProp Sync Rcpt PinsTO 1C-130H-2-61JG-20-1, 61-1 P-B2576A-16, P-B2576A-3020-13. 2 P-A2576A-5, P-B2576A-30

3 P-A2576A-6, P-B2576A-304 P-B2576A-26, P-B2576A-30

YES

410

Place TEST SELECT switch (5) to 4. Does FUNCTION display (7) indicate -11 to -15 volts? 413(Anticipator pot -V supply)

Replace propeller syn-NOchrophaser in accordance withProp Sync Rcpt PinsTO 1C-130H-2-61JG-20-1, 61-1 P-B2576A-27, P-B2576A-3020-13. 2 P-A2576A-7, P-B2576A-30

3 P-A2576A-13, P-B2576A-304 P-B2576A-36, P-B2576A-30

YES

TO SHT 143

NOTE




61-20-004-156 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-157

TO 1C-130H-2-61FI-00-1

FROM SHT 141

414

a. Place TEST SELECT switch (4) to 5.b. Move throttle (5) to TAKE OFF.Does FUNCTION display (1) indicate 0 to -3

417volts?(Anticipator pot output in T/O pos) Replace valve housing assem-NO

bly in accordance with TO 1C-Prop Sync Rcpt Pins 130H-2-61JG-20-1, 61-20-02. 1 P-B2576A-13, P-B2576A-302 P-B2576A-32, P-B2576A-303 P-B2576A-35, P-B2576A-304 P-B2576A-33, P-B2576A-30

YES

415

Move throttle (5) to FLIGHT IDLE/FLT IDLE.Does FUNCTION display (1) indicate -8.5 to-12 volts? 418(Anticipator pot output)

Replace valve housing assem-NObly in accordance with TO 1C-Prop Sync Rcpt Pins130H-2-61JG-20-1, 61-20-02. 1 P-B2576A-13, P-B2576A-30

2 P-B2576A-32, P-B2576A-303 P-B2576A-35, P-B2576A-304 P-B2576A-33, P-B2576A-30

YES

416

a. Rapidly advance throttles (5) to TAKEOFF.b. Place PROP CHANNEL SELECT switch(3) to next highest or lowest position.c. Return PROP CHANNEL SELECT switch(3) to previous position and record the indica-tion in AC VOLTS display (2). 419d. Rapidly retard throttles (5) to FLIGHT/FLT

Replace propeller syn-IDLE and note indication in AC VOLTS display NOchrophaser in accordance with(2).TO 1C-130H-2-61JG-20-1, 61-Is the difference in the two indications at least20-13. 2 volts?

(Speed bias control winding)

Prop Sync Rcpt Pins1 P-B2576A-5, P-B2576A-32 P-A2576A-34, P-A2576A-453 P-B2576A-14, P-B2576A-64 P-A2576A-24, P-B2576A-19

YES

TO SHT 145


61-20-004-158 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-159

TO 1C-130H-2-61FI-00-1

FROM SHT 143

420

Place TEST SELECT switch (3) to 6.Does AC VOLTS display (2) indicate 90

422to 130 volts?(Speed bias ref winding) Replace propeller syn-NO

chrophaser in accordance withProp Sync Rcpt Pins TO 1C-130H-2-61JG-20-1, 61-1 P-B2576A-39, P-B2576A-30 20-13. 2 P-A2576A-41, P-B2576A-303 P-A2576A-42, P-B2576A-304 P-B2576A-38, P-B2576A-30

YES

421

a. Start engines in accordance with TO1C-130H-2-71JG-00-1, 71-00-10.b. Place FUNCTION SELECT switch(4) to TACH RPM %.Does FUNCTION display (1) indicate

NO99.8 to 100.2?TO SHT 147(Tach gen output)

Prop Sync Rcpt Pins1 P-B2576A-15, P-B2576A-242 P-B2576A-44, P-B2576A-423 P-B2576A-4, P-B2576A-24 P-B2576A-45, P-B2576A-43

YES

TO SHT 149


61-20-004-160 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-161

TO 1C-130H-2-61FI-00-1

FROM SHT 1 OR 145 425426Place FUNCTION SELECT switch (2) to

423 Fault is in tachometer sys-PROP RPM %.NO YESIs there a flashing 6 in FUC- tem. Go to TO 1C-130H-2-Does RPM difference between TACHTION display (1)? 70FI-00-1-1 and continueRPM % indication and PROP RPM %

troubleshooting. indication in FUNCTION display (1) ex-ceed 1 percent?YES

NO427

Adjust propeller mechanicalgoverning speed in accor-dance with TO 1C-130H-2-61JG-10-1, 61-10-03.

424

a. Shut down engines in accordance with TO1C-130H-2-71JG-00-1, 71-00-10.b. As applicable, remove propeller syn-chrophaser in accordance with TO 1C-130H-2-61JG-20-1, 61-20-13, and/or remove junction boxfrom synchrophaser rack.Is there continuity between specified pins of re-ceptacle P-B2576A (3) and related terminals ofterminal board TB1C (4)?

Prop Rcpt Pin TB Term Test Points 428

Fault is in tachometer sys-24 110 9

YEStem. Go to TO 1C-130H-2-170FI-00-1-1 and continue15 2

12 11troubleshooting.

44 310 9

242 4

12 11

4 510 9

32 6

12 11

45 710 9

443 8

12 11

NO

429

Repair applicable open cir-cuit. (See figure 4-6 or 4-7.)

NOTE



61-20-004-162 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-163

TO 1C-130H-2-61FI-00-1

FROM SHT 145

434430Fault is in tachometer system.NO

Does AC VOLTS display (3) indicate 17 toGo to TO 1C-130H-2-70FI-00-1-30? 1 and continue troubleshooting.

YES

431

Place FUNCTION SELECT switch (5) toPROP RPM %.Does FUNCTION display (1) indicate 99.8 435to 100.2?

Adjust clearance between pulse(Pulse gen output) NOgenerator and permanent mag-net in accordance with TO 1C-Prop Sync Rcpt Pins130H-2-61JG-20-1, 61-20-10. 1 P-B2576A-34, P-B2576A-20

2 P-A2576A-37, P-A2576A-283 P-A2576A-36, P-A2576A-294 P-B2576A-1, P-B2576A-31

YES

432 436433

NO YESDoes AC VOLTS display (3) indicate 1.2 to Replace permanent magnet inIs the - PULSE POLARI-5.0 and is - PULSE POLARITY indicator accordance with TO 1C-130H-TY indicator light (2) on?light (2) on? 2-61JG-20-1, 61-20-10.

YES NO

TO SHT 151437

Polarity of pulse generator (4) isreversed. Check pulse genera-tor for reversed wiring or im-proper magnet orientation andrepair as required.


61-20-004-164 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-165

TO 1C-130H-2-61FI-00-1

FROM SHT 149

438

a. Place FUNCTION SELECT switch (5) to DCV.b. Place TEST SELECT switch (4) to 13.Does FUNCTION display (1) indicate between

440-1.2 and -5.0 volts?(Pulse gen output) Replace pulse generator in ac-NO

cordance with TO 1C-130H-2-Prop Sync Rcpt Pins 61JG-20-1, 61-20-10. 1 P-B2576A-34, P-B2576A-202 P-A2576A-37, P-A2576A-283 P-A2576A-36, P-A2576A-294 P-B2576A-1, P-B2576A-31

YES

439

a. Place TEST SELECT switch (4) to 14.b. Record voltage indication in AC VOLTS dis-play (2) for propeller under test.c. Place propeller governor control switch (6) toMECH GOV/MECH.d. Place applicable SPEED DERIVATIVE switch(3) to OUT.e. Place propeller governor control switch (6) to 441NORMAL/NORM.

Fault is in tachometer system.NOf. Record voltage indication in AC VOLTS display

Go to TO 1C-130H-2-70FI-00-1-(2).1 and continue troubleshooting. g. Compare the indications of steps b and f.

Are the values the same?(Tach gen output)

Prop Sync Rcpt Pins1 P-B2576A-15, P-B2576A-242 P-B2576A-44, P-B2576A-423 P-B2576A-4, P-B2576A-24 P-B2576A-45, P-B2576A-43

YES

442


NOTE


2 Airplanes AF92-0547 through AF92-2104 and AF92-3281 and up.


61-20-004-166 Change 1

TO 1C-130H-2-61FI-00-1


61-20-00Change 1 4-167/(4-168 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 1 of 4) 61-20-00F4-6

Change 1 4-169/(4-170 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 2) 61-20-00F4-6

Change 1 4-171/(4-172 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 3) 61-20-00F4-6

Change 1 4-173/(4-174 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 4) 61-20-00F4-6

Change 1 4-175/(4-176 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 1 of 5) 61-20-00F4-7

Change 1 4-177/(4-178 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 2) 61-20-00F4-7

Change 1 4-179/(4-180 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 3) 61-20-00F4-7

Change 1 4-181/(4-182 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 4) 61-20-00F4-7

Change 1 4-183/(4-184 blank)

TO 1C-130H-2-61FI-00-1


(Sheet 5) 61-20-00F4-7

Change 1 4-185/(4-186 blank)

TO 1C-130H-2-61FI-00-1

Figure 4-8. Synchrophaser System Simplified Electrical SchematicDiagram 61-20-00

F4-8Change 1 4-187/(4-188 blank)

TO 1C-130H-2-61FI-00-1

Figure 4-9. In-line Disconnects Location Diagram (Airplanes Prior toAF92-1094 and AF92-3021 Through AF92-3024) 61-20-00

F4-9Change 1 4-189/(4-190 blank)

TO 1C-130H-2-61FI-00-1


F4-10Change 1 4-191/(4-192 blank)

134466125-to-1c-130h-2-61fi-00-1-technical-manual-fault-isolation-propellers-usaf-series-all-c-130-aircraft-change-7-01-dec-2008.pdf...

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