TO 1C-130H-2-61FI-00-1
TECHNICAL MANUAL
FAULT ISOLATION
ORGANIZATIONAL MAINTENANCE
PROPELLERS
USAF SERIES
ALL C-130 AIRCRAFT
ATOS/DLDSS
BASIC AND ALL CHANGES HAVE BEEN MERGED TO MAKE THIS A COMPLETE PUBLICATION
DISCLOSURE NOTICE - This information is furnished upon the condition that it will not be released to
another nation without the specific authority of the Department of the Air Force of the United States, that it
will 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, any
known or suspected compromise, and that the information will be provided substantially the same degree
of security afforded it by the Department of Defense of the United States. Also, regardless of any other
markings on the document, it will not be downgraded or declassified without written approval of the
originating United States agency.
DISTRIBUTION STATEMENT D - Distribution authorized to the Department of Defense and US DoD
contractors only (Administrative or Operational Use) (1 February 2002). Other requests for this document
shall be referred to 580 ACSG/GFEAH, Robins AFB, GA 31098.
WARNING - This document contains technical data whose export is restricted by the Arms Export
Control Act (Title 22, U.S.C., Sec 2751, et seq.) or the Export Administration Act of 1979, as amended, Title
50, 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 any
method that will prevent disclosure of the contents or reconstruction of the document.
Published under authority of the Secretary of the Air Force
1 FEBRUARY 2002
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TABLE OF CONTENTS
Section/Paragraph
Page
LIST OF TABLES ............................................................................................................................ ii
LIST OF SCHEMATIC DIAGRAMS ............................................................................................. iii
INTRODUCTION ..............................................................................................................................v
Purpose ...........................................................................................................................................v
Usefulness ......................................................................................................................................v
Safety ..............................................................................................................................................v
Arrangement ..................................................................................................................................v
Special Instructions for Open Circuit Breakers..........................................................................v
Special Instruction for Shielded Wires ........................................................................................v
Conditions Not Covered By This Manual....................................................................................v
Abbreviations and Symbols ..........................................................................................................v
Effectivity ..................................................................................................................................... vi
Using This Publication................................................................................................................ vi
I
GENERAL
1-1
1-2
1-3
1-4
INFORMATION......................................................................................................... 1-1
General ..................................................................................................................... 1-1
Fault Reporting Manual (FRM) ............................................................................. 1-1
Fault Isolation Manual (FIM) ................................................................................ 1-1
Special Tools and Test Equipment Required for Fault Isolation ........................ 1-4
II
PROPELLER ASSEMBLY ........................................................................................................... 2-1
2-1
General ..................................................................................................................... 2-1
2-2
Malfunction Index.................................................................................................... 2-1
2-3
Numeric Fault Code Indexes .................................................................................. 2-1
2-4
Preparation Procedures........................................................................................... 2-5
2-5
Fault Isolation Diagrams ...................................................................................... 2-15
III
SYNCHROPHASER SYSTEM ..................................................................................................... 3-1
3-1
General ..................................................................................................................... 3-1
3-2
Malfunction Index.................................................................................................... 3-1
3-3
Numeric Fault Code Index ..................................................................................... 3-1
3-4
Preparation Procedures........................................................................................... 3-2
3-5
Fault Isolation Diagram........................................................................................ 3-13
IV
SYNCHROPHASER SYSTEM (AIRPLANES MODIFIED BY TO 1C-130-1731).................... 4-1
4-1
General ..................................................................................................................... 4-1
4-2
Malfunction Index.................................................................................................... 4-1
4-3
Numeric Fault Code Index ..................................................................................... 4-1
4-4
Preparation Procedures........................................................................................... 4-3
4-5
Fault Isolation Diagram........................................................................................ 4-16
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LIST OF TABLES
Section
Number
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 Fault
Codes (Airplanes Prior to AF92-0547 and
AF92-3021 Through AF92-3024)..................... 6110030 - 6110034...............2-4
II
2-6
Propeller Low Fluid Warning System Fault
Codes (Airplanes AF92-0547 Through
AF92-2104 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 (Airplanes Modified by TO 1C-130-1731) ............. 6120S01 ................................4-1
IV
4-2
Synchrophaser System Fault Codes (Airplanes Modified by TO 1C-130-1731) ............. 6120001 - 6120014...............4-1
ii
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Fault Codes
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TO 1C-130H-2-61FI-00-1
LIST OF SCHEMATIC DIAGRAMS
Number
Title
Page
2-6
Beta Indication Electrical Schematic Diagram (Airplanes Prior to AF92-0547
and Airplanes AF92-3021 Through AF92-3024) ............................................................ 2-251
2-7
Beta Indication Electrical Schematic Diagram (Airplanes AF92-0547
Through AF92-2104 and Airplanes AF92-3281 and Up) .............................................. 2-253
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)......................................................................................................... 2-255
2-9
Negative Torque Signal System Electrical Schematic Diagram (Airplanes
AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up) ........................... 2-257
2-10
Negative Torque Signal System Electrical Schematic Diagram (MC-130H
Airplanes) .......................................................................................................................... 2-259
2-11
Propeller Feather System Electrical Schematic Diagram (Airplanes Prior to
AF92-0547 and Airplanes AF92-3021 Through AF92-3024)......................................... 2-261
2-12
Propeller Feather System Electrical Schematic Diagram (Airplanes
AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up) ........................... 2-277
2-13
Propeller Low Fluid Warning System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 Through AF92-3024) .............. 2-285
2-14
Propeller Low Fluid Warning System Electrical Schematic Diagram (Airplanes 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 to
AF92-0547 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
3-10
In-line Disconnects Location Diagram (Airplanes AF92-1094, AF92-1095,
AF92-2104, and AF93-1036 and Up) .............................................................................. 3-193
4-6
Synchrophaser System Electrical Schematic Diagram (Airplanes Prior to
AF92-0547 and Airplanes AF92-3021 Through AF92-3024)......................................... 4-169
4-7
Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547
Through 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 and
AF92-3021 Through AF92-3024) ..................................................................................... 4-189
4-10
In-line Disconnects Location Diagram (Airplanes AF92-1094, AF92-1095,
AF92-2104, and AF93-1036 and Up) .............................................................................. 4-191
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INTRODUCTION
PURPOSE. This publication contains fault isolation procedures for subsystems/modes of operation of the C-130 propeller system.
USEFULNESS. The effectiveness of this publication shall, to a large extent, depend upon active
participation in the program by operations and maintenance personnel who use the Fault Isolation Manual. User feedback is the most important factor if the manual is to be maintained upto-date. Use the AFTO Form 22 system to recommend new and/or improved data for incorporation in this publication.
SAFETY. Fault isolation procedures in this publication are a guide for troubleshooting and are
brief 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 opening
any overhead panel. Refer to the maintenance manuals (Job Guides) for repair and replacement
procedures - always bring the airplane to a safe condition before repair or replacement.
ARRANGEMENT. This publication contains Section I - General Information, Section II - Propeller Assembly, Section III - Synchrophaser System and Section IV - Syncrophaser System (Airplanes modified by TO 1C-130-1731). Refer to the Table of Contents when a specific paragraph
needs to be located. Placarding differences between airplane models are separated in the text by
a slash.
SPECIAL INSTRUCTIONS FOR OPEN CIRCUIT BREAKERS. When a tripped circuit breaker is
encountered, use TO 1C-130(A)H-2-13, TO 1C-130(A)U-2-13, TO 1C-130H-2-13, TO 1C-130H-214, TO 1C-130B-2-13, TO 1C-130(M)E-2-13, or TO 1C-130(M)H-2-13 to identify circuits which
are 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 applicable
circuit by opening other circuit breakers. Close the tripped circuit breaker. If the circuit
breaker trips again, either the airplane wiring is shorted or the circuit breaker is bad; isolate
and repair as required. If the circuit breaker remains closed, observe it and bring back on line
individual circuits one at a time; when the circuit breaker now trips, the component being
brought on line is bad or there may be a bent pin in its plug or connector. Repair the plug or
connector or replace the component as required. Perform an operational checkout of the system
following the repair action.
SPECIAL INSTRUCTION FOR SHIELDED WIRES. If a synchrophaser malfunction is encountered
where 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 received
by the synchrophaser. First, verify that the suspected equipment is functioning properly and its
associated wiring is routed properly and intact. If the fault persists, refer to figure 3-6 or 3-7/46 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 represent
planned action for conditions normally encountered during maintenance. It is almost impossible
to 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 encouraged
to avoid unnecessary delay when coverage in the manual is incomplete. Any variation from
procedures shall be consistent with standard shop practices and shall not detract from overall
efficiency and operation of the equipment.
ABBREVIATIONS AND SYMBOLS. The following non-military-standard abbreviations, terms
and symbols appear in this publication:
Continuity
Absence of an open circuit
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TO 1C-130H-2-61FI-00-1
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 isolation 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 technical orders. Only current TCTO are listed. A TCTO is deleted from the list when any of the
following occurs:
a. The equipment configuration to which the TCTO is applicable is no longer covered in the
manual.
b. The TCTO is rescinded.
c. The TCTO is superseded or replaced.
TCTO No.
Title
1C-130-1731
Synchrophaser Interface Wiring
Replacement
TCTO Date
USING THIS PUBLICATION. Figure i-1 explains how to use this publication whether a fault code
is provided or not. Do not skip the preparation procedure. The preparation is necessary to
prepare the airplane for fault isolation.
vi
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Figure i-1. How to Use This Manual (Sheet 1 of 2)
vii
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Figure i-1. How to Use This Manual (Sheet 2)
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TO 1C-130H-2-61FI-00-1
Section I.
GENERAL INFORMATION
1-1. GENERAL. The C-130 propeller system fault analysis concept is a troubleshooting method
composed of two elements: the Fault Reporting Manual (FRM) and the Fault Isolation Manual
(FIM).
NOTE
Ground maintenance crews may also use FRM procedures (contained
in Section XX of TO 1C-130H-2-00FR-00-1 or Chapter 20 of TO 1C130(M)H-2-00FR-00-1) to gain the same results as described in the
following paragraph.
1-2. FAULT REPORTING MANUAL (FRM). Flight crews use FRM methods to inform maintenance personnel about malfunctions the flight crews encounter. As directed by the FRM procedures, the flight crew makes checks and observations to help isolate the malfunction. Questions
that deal with symptoms and conditions occurring at the time of the failure are answered. The
result is a peculiar fault code which represents those specific symptoms and conditions accompanying the malfunction. In order that each fault code may be identified and continuity made
possible between the fault reporting manual (FRM) and the fault isolation manual (FIM), a
seven-digit numeric code is assigned to each fault. The first two digits identify the system in
which the fault occurred; the next two digits represent the subsystem in which that fault
occurred; the remaining three digits are the numerical identification assigned to each fault.
System and subsystem identification are assigned in accordance with Specification MIL-M83495. This number and the discrepancy (symptoms) are then entered in the AFTO Form 781A
along with any additional details that will be helpful. Using the Fault Isolation Manual, maintenance personnel interpret the fault code and plan maintenance action that allows them to
start the fault isolation routine at some block other than block 1. The blocks which are skipped
over would normally be used to determine the symptoms and conditions represented by the fault
code. Troubleshooting becomes more accurate, and less time and effort is required.
1-3. FAULT ISOLATION MANUAL (FIM). Maintenance personnel use FIM procedures to isolate
faults for a system, a functional mode, or a specific failure indication. The procedures are based
on a process of elimination; the parts of a system/malfunction are tested in a logical sequence
until a specific line replaceable unit (LRU) failure or a wiring fault is found. This eliminates the
guesswork 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 system
and/or mode of operation when the failure occurred, and also contain the alphanumeric fault
code. These indexes are to be used when the malfunction occurs during ground maintenance or
when the flight crew did not provide a numeric fault code. When using these indexes, troubleshooting 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 in
numerical order. Each fault code represents a peculiar malfunction and its associated symptoms
which could be encountered by the flight crew. A figure and block number reference for each
code tells where to go in the fault isolation diagram to start the actual troubleshooting. All
assigned fault code numbers between 6110001 and 6120999 represent propeller assembly and
synchrophaser 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 uses
pictures and words to simplify preparation. When required, preparation procedures must be
performed to condition the airplane before starting the actual troubleshooting. Each malfunction
and 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 do
not include detailed instructions necessary to gain access to components, to disconnect or connect electrical connectors, or to close panels/covers following troubleshooting. Always backtrack
through the fault isolation diagram and remove any jumpers, reconnect plugs and hydraulic
lines, and reinstall relays, access panels, and other removed components. All maintenance procedures must be properly performed (refer to the applicable Job Guide manual when a problem
or question about maintenance procedures arises). The Job Guide manuals also contain replacement procedures to be used when troubleshooting determines the bad component or LRU.
Always bring the airplane to a safe condition before replacing specified components. Wiring
problems will require the use of TO 1C-130H-2-13, TO 1C-130H-2-14, TO 1C-130B-2-13, TO 1C130(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 fault
code index or malfunction index. From the point of entry, a series of instructions, questions, and
answers lead the mechanic to a defective component or circuit fault. To locate components, a
facing illustration is provided. Switch positions shown on these illustrations do not necessarily
represent the mode of operation; therefore change switch positions only when specified in the
troubleshooting blocks.
(1) Flow Sheets. Each flow sheet of a fault isolation diagram contains either two or three
columns of blocks. The right column always contains rectangular blocks which state the repair
action to be accomplished. The remaining blocks are hexagons that always contain a question to
be answered. If the answer to the question is yes, follow the YES arrow to the next block. If
the answer to the question is no, follow the NO arrow to the next block. When the arrow refers
to 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 with
the block number appearing in the upper left corner of each block. Block number 1 is at the
upper left corner of sheet 1 of each figure. The block numbers go down the page, then to the top
block in the next column to the right. Additional sheets of a figure continue the number
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TO 1C-130H-2-61FI-00-1
sequence in the same manner until every block in the figure is numbered (there are never two
blocks 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. Most
blocks will not have a fault code in them, and a few will contain two or more fault codes. These
numbers are used to make sure troubleshooting starts at the block number specified in the fault
code index.
(4) Test Points. A block may contain a test point symbol ( ) as an aid in troubleshooting when an electrical measurement is specified. A note identifies the schematic diagram on
which the test point is located. The test points on a schematic diagram show the functional
location of the measurement being made. Test point number 1 is always near the upper left
corner of the schematic diagram. Test points 2 and up then generally go around the diagram in
a clockwise rotation. A single test point reference for voltage measurements means that the
voltage is referenced to airplane ground.
(5) Circuit Interruption Symbol. A lightning bolt within a circle at the top of a block is a
circuit interruption symbol ( ). Its presence means that a live circuit may be temporarily
broken to gain access to an electrical measurement point. Circuit breaker(s) or switch(es) feeding the circuit under test are identified elsewhere on the page. If different circuit breaker(s) or
switch(es) apply to different blocks on a page, a delta number (example, 1 ) will be added to the
circuit interruption symbol. When the symbol appears in a block, open the appropriate circuit
breaker(s) or change switch positions before proceeding; break the circuit (remove relay, disconnect plug, etc., specified in the block); then close the circuit breaker(s) or switch(es) before
making the electrical measurement specified in the block.
(6) Figure References. A figure reference in a rectangular block identifies the electrical
schematic diagram that represents the circuit or wiring to be repaired. If a circuit or wiring
fault is encountered, refer to TO 1C-130H-2-13, TO 1C-130H-2-14, TO 1C-130B-2-13, or TO 1C130(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 fleet
configurations. Sometimes, different FIM diagrams, or different paths on a FIM diagram, must
be utilized to account for configuration differences. When necessary, the FIM diagram is annotated by model number, tail number, or TCTO incorporation statement to distinguish configuration differences. FIM diagrams not annotated apply to all airplanes.
(8) Index Numbers. Index numbers on locator illustrations generally start with number 1
at 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 near
each 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 tunnel disconnects, the wheelwell disconnects, and the aft fuselage disconnects are not specifically
troubleshot in the fault isolation diagrams. These disconnects are shown on the schematic
diagrams. An In-line Disconnect Locator figure at the end of each applicable section shows the
location of these disconnects. A hex flag ( ) appears adjacent to the affected reference designators on the applicable schematic diagrams. These hex flags are keyed to the views in the locator
figure that show that particular in-line disconnect.
61-00-00
1-3
TO 1C-130H-2-61FI-00-1
1-4.
SPECIAL TOOLS AND TEST EQUIPMENT REQUIRED FOR FAULT ISOLATION.
Nomenclature
AN type
designation
or part No.
Alternate
Use and
application
Synchrophaser system
test set
AD33480-2
Equivalent
Propeller-related measurements
Multimeter
AN/PSM-37( )
Equivalent
Measure voltages and resistances
28 VDC light
Local manufacture
Equivalent
Test 28 VDC circuits
under load
Shim (0.225 inch
thick)
Local manufacture
Equivalent
Actuate NTS linkage
61-00-00
1-4
TO 1C-130H-2-61FI-00-1
Section II.
PROPELLER ASSEMBLY
2-1. GENERAL. The fault isolation material in this section is used for troubleshooting any
propeller system malfunction excluding the synchrophaser system. Contents of this section
include a malfunction index, fault code indexes, preparation procedures to be performed prior to
fault isolation, fault isolation diagrams (the actual troubleshooting procedures), locator illustrations 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 is
encountered during ground maintenance and no numeric fault code was determined from the
FRM diagram, when no numeric fault code was provided by the flight crew, or when the flight
crew only provided an alphanumeric fault code. Malfunctioning systems/modes of operation are
listed 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
*Alphanumeric
fault code
Malfunction
Fault isolation reference
1.
Propeller system malfunction
6110P01
Perform figure 2-1, Preparation A, then go
to figure 2-4, block 1.
2.
Propeller feather system malfunction
6110F01
Perform figure 2-1, Preparation A, then go
to figure 2-4, block 1.
3.
Negative torque signal system malfunction
6110N01
Perform figure 2-1, Preparation A, then go
to figure 2-4, block 1.
4.
Propeller low fluid
warning system malfunction
6110W01
Perform figure 2-3, Preparation C, then go
to figure 2-5, block 1.
* If provided by flight crew
2-3. NUMERIC FAULT CODE INDEXES. All assigned numeric FRM fault codes for the propeller
assembly are listed in tables 2-2 through 2-6. Fault codes are listed in numerical order in the
left column of each table. The middle column contains the AFTO Form 781A report and lists
symptoms 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 2-2. Propeller System Fault Codes
Fault code
6110001
AFTO Form 781A report
Propeller/engine No. (1)(2)(3)(4) has excessive vibration as indicated by (engine
condition lever) (throttle) (visual) indication.
Fault isolation reference
No preparation required. Go to figure
2-4, block 537.
61-10-00
2-1
TO 1C-130H-2-61FI-00-1
Table 2-2. Propeller System Fault Codes - Continued
Fault code
AFTO Form 781A report
6110002
Beta indicator light No. (1)(2)(3)(4) failed
to come on in (bright)(dim)(both bright
and dim) modes when throttle was retarded below FLIGHT IDLE/FLT IDLE
gate.
Fault isolation reference
Perform figure 2-1, Preparation A, then
go to figure 2-4:
Airplanes prior to AF92-0547 and AF923021 through AF92-3024:
block 74 for bright mode failure
block 131 for dim mode failure
block 80 for both modes failure
Airplanes AF92-0547 through AF92-2104
and 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
slow or stop did not retract when throttle
was placed to GROUND IDLE/GND
IDLE as indicated by lack of torque decrease.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 532.
6110004
No. (1)(2)(3)(4) flight idle torque spread is
not within limits.
No preparation required. Go to figure
2-4, block 47.
6110005
Engine No. (1)(2)(3)(4) RPM is not within
flight manual limits in propeller governing range. RPM indicated __ percent
with throttle at __ position.
Perform figure 2-2, Preparation B. Start
engines in accordance with TO 1C-130H2-71JG-00-1, 71-00-01; or TO 1C130(A)H-2-71JG-00-1, 71-00-10; and go to
figure 2-4, block 52.
6110006
Symmetric engine torque exceeds 1000
inch-pounds for engines (1 and 4)(2 and
3) at maximum reverse setting.
No preparation required. Go to figure 24, block 511.
6110007
Engine RPM is not within limits at maximum reverse setting.
Fault is in engine or RPM indicating system. 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
with throttle above FLIGHT IDLE/FLT
IDLE gate.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 241.
61-10-00
2-2
TO 1C-130H-2-61FI-00-1
Table 2-3.
Fault code
Propeller Feather System Fault Codes
AFTO Form 781A report
Fault isolation reference
6110010
Propeller No. (1)(2)(3)(4) fails to go from
maximum reverse to full feather in 25
seconds.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 39.
6110011
Propeller feather override button light/
FTHR light No. (1)(2)(3)(4) fails to go off
at end of feather cycle.
Replace propeller feather override button.
6110012
Propeller feather override button No.
(1)(2)(3)(4) fails to pop out at end of
feather cycle.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 302.
6110013
PROPELLER FEATHER OVERRIDE
button light/FTHR light No. (1)(2)(3)(4)
fails to come on during feather cycle.
No preparation required. Go to figure
2-4, block 225 (airplanes prior to AF920547 and AF92-3021 through AF92-3024)
or block 227 (airplanes AF92-0547
through AF92-2104 and AF92-3281 and
up).
6110014
Propeller feather override button No.
(1)(2)(3)(4) cycles during feather cycle.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 203.
6110015
Propeller feather override button No.
(1)(2)(3)(4) fails to pull in during feather
cycle.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 187.
6110016
Propeller No. (1)(2)(3)(4) fails to feather
with engine condition lever. Propeller
does feather with fire emergency handle.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 189.
6110017
Propeller No. (1)(2)(3)(4) fails to feather
with engine condition lever or fire emergency handle.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 9 (airplanes prior
to AF92-0547 and AF92-3021 through
AF92-3024) or block 14 (airplanes AF920547 through AF92-2104 and AF92-3281
and up).
Table 2-4. Negative Torque Signal System Fault Codes
Fault code
6110020
AFTO Form 781A report
FEATHER VALVE AND NTS CHECK
light/NTS light No. (1)(2)(3)(4) is on during non-NTS/feather condition.
Fault isolation reference
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 6 (airplanes prior
to AF92-0547 and AF92-3021 through
AF92-3024) or block 13 (airplanes AF920547 through AF92-2104 and AF92-3281
and up).
61-10-00
2-3
TO 1C-130H-2-61FI-00-1
Table 2-4. Negative Torque Signal System Fault Codes - Continued
Fault code
AFTO Form 781A report
Fault isolation reference
6110021
Engine No. (1)(2)(3)(4) exhibits excessive
NTS indications in relation to other operating engines.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 372.
6110022
FEATHER VALVE AND NTS CHECK
light/NTS light No. (1)(2)(3)(4) failed to
come on when air start was accomplished.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 323.
6110023
FEATHER VALVE AND NTS CHECK
light/NTS light No. (1)(2)(3)(4) failed to
come on when engine condition lever was
moved to FEATHER/FTR position.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 323.
6110024
FEATHER VALVE AND NTS CHECK
light/NTS light No. (1)(2)(3)(4) failed to
come on with FEATHER VALVE AND
NTS CHECK switch in NTS position during engine shutdown.
Perform figure 2-1, Preparation A, then
go to figure 2-4, block 26 (airplanes prior
to AF92-0547 and AF92-3021 through
AF92-3024) or block 30 (airplanes AF920547 through AF92-2104 and AF92-3281
and up).
Table 2-5. Propeller Low Fluid Warning System Fault Codes (Airplanes Prior to AF92-0547 and
AF92-3021 Through AF92-3024)
Fault code
AFTO Form 781A report
6110030
(PROP LOW OIL QUANTITY master
warning light) (and) (PROPELLER LOW
OIL WARNING light No. (1)(2)(3)(4)) fail
to go to selected bright/dim mode.
Perform figure 2-3, Preparation C, then
go to figure 2-5, block 189.
6110031
PROP LOW OIL QUANTITY master
warning light fails to come on when PROPELLER LOW OIL WARNING light No.
(1)(2)(3)(4) is on.
Perform figure 2-3, Preparation C, then
go to figure 2-5, block 160.
6110032
With known low propeller fluid quantity,
PROPELLER LOW OIL WARNING light
No. (1)(2)(3)(4) failed to come on.
Perform figure 2-3, Preparation C, then
go to figure 2-5, block 8.
6110033
PROP LOW OIL QUANTITY master
warning light is on with PROPELLER
LOW OIL WARNING lights off.
Perform figure 2-3, Preparation C, then
go to figure 2-5, block 93.
6110034
PROPELLER LOW OIL WARNING light
No. (1)(2)(3)(4) came on.
Perform figure 2-3, Preparation C, then
go to figure 2-5, block 6.
61-10-00
2-4
Fault isolation reference
TO 1C-130H-2-61FI-00-1
Table 2-6. Propeller Low Fluid Warning System Fault Codes (Airplanes AF92-0547 Through AF92-2104
and AF92-3281 and Up)
Fault code
2-4.
AFTO Form 781A report
Fault isolation reference
6110030
PROP low oil warning light No.
(1)(2)(3)(4) fails to go to selected bright/
dim mode.
Fault is in MACAWS. Go to TO
1C-130H-2-33FI-00-1-2, Section IV, and
continue troubleshooting.
6110032
With known low propeller fluid quantity,
PROP low oil warning light No.
(1)(2)(3)(4) failed to come on.
Perform figure 2-3, Preparation C, then
go to figure 2-5, block 22.
6110034
PROP low oil warning light No.
(1)(2)(3)(4) came on.
Perform figure 2-3, Preparation C, then
go to figure 2-5, block 6.
PREPARATION PROCEDURES.
WARNING
Improper or inadequate preparation of the airplane may result in
injury to personnel and/or damage to the airplane.
The applicable preparation procedures must be performed before starting troubleshooting. The
preparation is referenced in the malfunction index and fault code indexes. Each procedure is
contained in a figure that illustrates step-by-step actions to be taken to prepare the airplane for
troubleshooting.
61-10-00
2-5/(2-6 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-1. Preparation A (Sheet 1 of 4)
61-10-00
2-7
TO 1C-130H-2-61FI-00-1
Figure 2-1. Preparation A (Sheet 2)
61-10-00
2-8
TO 1C-130H-2-61FI-00-1
Figure 2-1. Preparation A (Sheet 3)
61-10-00
2-9
TO 1C-130H-2-61FI-00-1
Figure 2-1. Preparation A (Sheet 4)
61-10-00
2-10
TO 1C-130H-2-61FI-00-1
Figure 2-2. Preparation B (Sheet 1 of 3)
61-10-00
2-11
TO 1C-130H-2-61FI-00-1
Figure 2-2. Preparation B (Sheet 2)
61-10-00
2-12
TO 1C-130H-2-61FI-00-1
Figure 2-2. Preparation B (Sheet 3)
61-10-00
2-13
TO 1C-130H-2-61FI-00-1
Figure 2-3. Preparation C
61-10-00
2-14
TO 1C-130H-2-61FI-00-1
2-5. FAULT ISOLATION DIAGRAMS. The fault isolation diagrams in this section are used for
troubleshooting any propeller malfunction. When the flight crew uses a FRM fault code to
report a malfunction, that number will be found in one of the fault code indexes. When no FRM
fault 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 a
second for the propeller low fluid warning system. Opposite each flow sheet of a fault isolation
diagram is an illustration which shows the physical location of items referenced in individual
fault isolation diagram blocks. Double-check these illustrations to verify the correct location
when making an observation or measurement. Following the fault isolation diagrams are the
electrical schematic diagrams. The schematic diagrams are laid out so that no portion of a
diagram is covered up when folded out for use. Thus it is easy to concurrently locate components, circuits, and test points that are referenced on the fault isolation diagram.
b. Using Troubleshooting Data. A thorough description of the fault isolation diagram and
other troubleshooting data is provided in Section I. In addition, the Introduction contains an
illustrated how-to-use figure for this section. Understand how to use the troubleshooting information before attempting to repair the airplane.
61-10-00
2-15
TO 1C-130H-2-61FI-00-1
1
6110F01, 6110N01,
6110P01
YES
Is airplane equipped with BETA
indicator lights (1)?
2
Is BETA indicator light on brightly?
NO
TO SHT 23
YES
NO
3
Is airplane serial number AF920547 through AF92-2104 or
AF92-3281 and up?
YES
TO SHT 5
NO
4
Momentarily place CAUTION
LIGHTS switch (4) to DIM.
Is BETA indicator light now on
dimly?
NO
TO SHT 41
YES
5
Is FEATHER VALVE AND NTS
CHECK light (3) off?
NO
8
Replace FEATHER VALVE
AND NTS CHECK switch (2).
YES
6
6110020
Place FEATHER VALVE AND NTS CHECK switch
(2) to VALVE.
Is FEATHER VALVE AND NTS CHECK light (3) off?
NO
TO SHT 43
YES
7
Place FEATHER VALVE AND NTS CHECK switch
to NTS.
Is FEATHER VALVE AND NTS CHECK light off?
NO
TO SHT 53
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)
61-10-00
2-16
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 2)
61-10-00
2-17
TO 1C-130H-2-61FI-00-1
FROM SHT 1
9
6110017
CAUTION
If PROPELLER FEATHER OVERRIDE button does not pop out 4
to 5 seconds after propeller blade
movement stops, pull out manually to prevent damage to auxiliary
pump motor.
NO
TO SHT 57
a. Place FEATHER VALVE AND
NTS CHECK switch (3) to
VALVE.
b. Move ENGINE CONDITION
lever (1) to FEATHER.
Does PROPELLER FEATHER
OVERRIDE button (2) pull in and
remain in?
YES
10
Did light in PROPELLER FEATHER OVERRIDE button come on?
NO
TO SHT 69
YES
TO SHT 7
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
Figure 2-4. Propeller Assembly Malfunction (Sheet 3)
61-10-00
2-18
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 4)
61-10-00
2-19
TO 1C-130H-2-61FI-00-1
FROM SHT 1
11
16
Is airplane prior to AF95-1001 or is
torquemeter BETA legend (2) present on indicator?
NO
Swap torquemeter indicators.
Does malfunction persist?
YES
NO
17
Remove and replace indicator.
YES
18
Repair open circuit between torquemeter plug P3978 pin g and related Caution Advisory Panel plug
P1725 pin.
12
a. Place the NORM/NVIS switch (8)
to NORM.
b. Momentarily place the BRIGHT/
DIM switch (7) to DIM.
Is BETA indicator light (3) on dimly?
19
NO
YES
13
6110020
NO
Is NTS light (5) off?
TO SHT 43
YES
14
6110017
CAUTION
If propeller feather override button
does not pop out 4 to 5 seconds
after propeller blade movement
stops, pull out manually to prevent
damage to auxiliary pump motor.
NO
TO SHT 57
Move engine condition lever (1) to
FTR.
Does propeller feather override button (6) pull in and remain in?
YES
15
NO
Does FTHR light (4) come on?
TO SHT 69
YES
TO SHT 7
Figure 2-4. Propeller Assembly Malfunction (Sheet 5)
61-10-00
2-20
6110002
Fault is in MACAWS. Go to TO
1C-130H-2-33FI-00-1-2, Section
IV, and continue troubleshooting.
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 6)
61-10-00
2-21
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 7)
61-10-00
2-22
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 8)
61-10-00
2-23
TO 1C-130H-2-61FI-00-1
FROM SHT 7
28
33
Did FTHR light (3) go off when
propeller feather override button
(5) popped out?
NO
Replace propeller feather override button.
YES
29
NO
Is BETA indicator light (2) off?
TO SHT 75
YES
30
6110024
a. If troubleshooting fault code
6110024A, open FEATHER
PUMP MOTOR PHASE A,B,C circuit breakers (8).
b. If troubleshooting fault code
6110024A, move engine condition
lever (6) to FTR.
Is NTS light (4) on?
NO
TO SHT 109
YES
31
Move engine condition lever to
GND STOP.
Is NTS light on?
NO
TO SHT 131
YES
32
a. Move throttle (7) to FLT IDLE
position (bottom of FLT IDLE
gate).
b. Hold engine condition lever in
AIR START until propeller blades
(1) stop moving.
Does propeller move from feather
to low pitch stop position?
NO
TO SHT 141
YES
TO SHT 13
Figure 2-4. Propeller Assembly Malfunction (Sheet 9)
61-10-00
2-24
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 10)
61-10-00
2-25
TO 1C-130H-2-61FI-00-1
FROM SHT 7
34
Place FEATHER VALVE AND NTS CHECK
switch (5) to NTS.
Is FEATHER VALVE AND NTS CHECK
light (4) on?
NO
TO SHT 123
YES
35
Move ENGINE CONDITION lever (3) to
GROUND STOP.
Is FEATHER VALVE AND NTS CHECK
light on?
NO
TO SHT 125
YES
36
a. Close FEATHER PUMP MOTOR
PHASE A, B, C/ 2 FEATHER PUMP MOTOR circuit breakers (6).
b. Move THROTTLE (2) to FLIGHT IDLE
position (bottom of FLIGHT IDLE gate).
c. Hold ENGINE CONDITION lever in AIR
START until propeller blades (1) stop moving.
Does propeller move from feather to low
pitch stop position?
NO
TO SHT 141
YES
TO SHT 13
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
Figure 2-4. Propeller Assembly Malfunction (Sheet 11)
61-10-00
2-26
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 12)
61-10-00
2-27
TO 1C-130H-2-61FI-00-1
FROM SHT 9 OR 11
37
CAUTION
Do not move throttle and do not move engine condition lever toward FEATHER/FTR position while shim is installed. Damage to propeller assembly could
result.
NO
TO SHT 147
a. Gain access and insert a 0.225-inch thick shim between engine NTS
plunger (1) and engine negative torque bracket/lever adjustment screw (2).
b. 1 2 3 Place FEATHER VALVE AND NTS CHECK switch (5) to VALVE.
c. Hold engine condition lever (7) in AIR START.
Did propeller blades (8) move toward feather position?
YES
38
a. Remove shim.
b. Hold engine condition lever in
AIR START until propeller blades
stop moving.
Did propeller blades move to flight
idle position?
42
40
NO
Inspect NTS linkage to and
through valve housing assembly
cover (3) for evidence of binding.
Is any binding observed?
Repair or replace linkage as reYES quired or replace valve housing
assembly cover as required in
accordance with TO 1C-130H2-61JG-20-1, 61-20-02.
NO
YES
43
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
39
6110010
a. Move throttle (6) to MAX REVERSE/MAX RVS.
b. Hold engine condition lever (7)
in AIR START until propeller
blades (8) stop moving.
c. Pull fire emergency handle (4)
for propeller under test while observing propeller blades.
Does propeller feather within 25
seconds?
NO
41
Did propeller blades move toward
feather position?
NO
TO SHT 149
YES
YES
TO SHT 15
TO SHT 87
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024, except MC-130E/H airplanes.
2
MC-130E airplanes.
3
MC-130H airplanes.
Figure 2-4. Propeller Assembly Malfunction (Sheet 13)
61-10-00
2-28
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 14)
61-10-00
2-29
TO 1C-130H-2-61FI-00-1
FROM SHT 13
44
a. Connect synchrophaser system
test set in accordance with Preparation B.
b. Start engine under test and
symmetrical engine in accordance
with TO 1C-130H-2-71JG-00-1,
71-00-10; or TO 1C-130(A)H-271JG-00-1, 71-00-10.
c. Perform torquemeter calibration
in accordance with TO 1C-130H2-77JG-00-1, 77-10-04; or TO 1C130(A)H-2-71JG-00-1, 71-00-10.
Is torquemeter calibration satisfactory?
48
Fault is in engine or torquemeter system. Shut down engines
in accordance with TO 1C130H-2-71JG-00-1, 71-00-10; or
TO 1C-130(A)H-2-71JG-00-1,
71-00-10; then go to TO 1C130H-2-70FI-00-1-1 and continue troubleshooting.
NO
YES
45
a. Move throttles (3) to FLIGHT
IDLE/FLT IDLE.
b. Record indications on engine
torque indicators (2).
c. Advance throttles until ELECTRONIC FUEL CORRECTION/TD
lights (1) first go off.
d. Retard throttles to FLIGHT
IDLE/FLT IDLE.
Is indicated torque now 500 to
2000 inch-pounds higher than recorded in step b?
6110004
47
NO
a. Shut down engines in accordance with TO 1C-130H-2-71JG00-1, 71-00-10; or TO 1C130(A)H-2-71JG-00-1, 71-00-10.
b. Perform operational checkout
of propeller - static condition in
accordance with TO 1C-130H-261JG-10-1, 61-10-01.
Is check satisfactory?
49
NO
Rig engine coordinator-to-propeller control assembly linkage
in accordance with TO 1C130H-2-61JG-20-1, 61-20-21.
YES
YES
50
Adjust or replace low pitch stop assembly in
accordance with TO 1C-130H-2-61JG-10-1,
61-10-12.
51
46
Is torque and RPM at flight idle within limits of TO 1C-130H-2-61JG-10-1,
61-10-02 (subtask 1-2-3)?
NO
YES
Fault is in engine. 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; then go to TO 1C-130H-2-70FI00-1-2 and continue troubleshooting.
TO SHT 17
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 2-4. Propeller Assembly Malfunction (Sheet 15)
61-10-00
2-30
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 16)
61-10-00
2-31
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 17)
61-10-00
2-32
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 18)
61-10-00
2-33
TO 1C-130H-2-61FI-00-1
FROM SHT 17
61
a. Move throttles (3) to MAXIMUM
REVERSE/MAX RVS.
b. Record indications on engine
torque indicators (2) and RPM indications in test set FUNCTION
display (1).
Is there a symmetrical torque difference in excess of 1000 inchpounds?
YES
TO SHT 161
NO
64
Fault is in engine or RPM indicating system. Shut down engines in accordance with TO
1C-130H-2-71JG-00-1, 71-0010; or TO 1C-130(A)H-2-71JG00-1, 71-00-10; then go to TO
1C-130H-2-71FI-00-1-1 and
continue troubleshooting.
62
Are RPM indications within limits
of TO 1C-130H-2-61JG-10-1, 6110-02 (subtask 1-2-2)?
NO
YES
63
CAUTION
Keep pitchlock time to a minimum.
NO
Perform pitchlock check of affected propeller in accordance with
TO 1C-130H-2-61JG-10-1, 61-1002 (subtask 1-2-10).
Was a pitchlock obtained?
TO SHT 163
YES
TO SHT 21
Figure 2-4. Propeller Assembly Malfunction (Sheet 19)
61-10-00
2-34
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 20)
61-10-00
2-35
TO 1C-130H-2-61FI-00-1
FROM SHT 19
69
Shut down engines in accordance
with TO 1C-130H-2-71JG-00-1, 71-0010; TO 1C-130(A)H-2-71JG-00-1, 7100-10; or TO 1C-130(M)H-2-71JG-001, 71-00-10; then replace pitchlock
regulator assembly in accordance with
TO 1C-130H-2-61JG-10-1, 61-10-11.
65
Did pitchlock disengage in accordance with
TO 1C-130H-2-61JG-10-1, 61-10-02 (as indicated by torque and RPM reading same as
initially recorded in the pitchlock check)?
NO
YES
66
a. Perform synchrophaser index in accordance
with TO 1C-130H-2-61JG-10-1, 61-10-02 (subtask 1-2-6).
b. Move throttles (3) to GROUND IDLE/GND
IDLE.
Do propeller low pitch stops retract as indicated by a decrease on engine torque indicators
(1)?
NO
TO SHT 167
YES
67
NOTE
If correct results are not obtained, repeat the
shutdown in normal ground idle rather than
low speed ground idle.
Shut down engines in accordance with TO 1C130H-2-71JG-00-1, 71-00-10; TO 1C-130(A)H2-71JG-00-1, 71-00-10; or TO 1C-130(M)H-271JG-00-1, 71-00-10.
1 3 4 Is FEATHER VALVE AND NTS
CHECK light (2) on?
2 Is NTS light (2) on?
NO
TO SHT 119
YES
68
70
Is there a reported malfunction associated with
a propeller vibration?
NO
Propeller system is normal. Secure
system.
YES
TO SHT 169
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 21)
61-10-00
2-36
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 22)
61-10-00
2-37
TO 1C-130H-2-61FI-00-1
FROM SHT 1
76
73
71
Are all BETA indicator lights
(1) on dimly?
YES
Is airplane serial number AF920547 through AF92-2104 or
AF92-3281 and up?
NO
6110002
YES Fault is in MACAWS. Go to TO
1C-130H-2-33FI-00-1-2, Section
IV, and continue troubleshooting.
NO
74
6110002
Gain access to terminals of indicator lights dimmer No. 10 (2).
Is 28 VDC present between dimmer terminals W and X?
1
NO
77
Replace indicator lights dimmer
No. 10.
2
YES
78
Fault is in dimming circuit. Go to
TO 1C-130H-2-33FI-00-1-1-1, Section II, and continue troubleshooting.
75
72
Is BETA indicator light under
test on dimly?
NO
YES
Is airplane serial number AF920547 through AF92-2104 or
AF92-3281 and up?
79
YES Fault is in MACAWS. Go to TO
1C-130H-2-33FI-00-1-2, Section
IV, and continue troubleshooting.
NO
TO SHT 25
80
Replace indicator lights dimmer
No. 10 (2).
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 2-6 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 23)
61-10-00
2-38
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 24)
61-10-00
2-39
TO 1C-130H-2-61FI-00-1
FROM SHT 23
81
Is airplane AF92-0547 through
AF92-2104 or AF92-3281 and up?
YES
TO SHT 27
NO
82
6110002
Press to test affected BETA indicator light (1).
Does light press to test?
YES
TO SHT 31
NO
83
Gain access to terminals of BETA
indicator light.
Is 28 VDC present on light terminal 1?
16
18
,
,
20
85
YES
Replace BETA indicator light
assembly.
22
OR
NO
84
Gain access to terminals of indicator lights dimmer No. 10 (2).
Is 28 VDC present on specified
dimmer terminal?
Prop
Dim
Term
1
J
2
K
3
M
4
N
Test
Point
4
6
8
86
Repair power circuit to specified
dimmer terminal. (See figure 26.)
NO
Prop
1
2
3
4
10
YES
TO SHT 29
NOTE
See figure 2-6 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 25)
61-10-00
2-40
Dim
Term
J
K
M
N
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 26)
61-10-00
2-41
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 27)
61-10-00
2-42
Change 1
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 28)
61-10-00
2-43
TO 1C-130H-2-61FI-00-1
FROM SHT 25
96
Is 28 VDC present on specified
terminal of indicator lights dimmer
No. 10 (5)?
Dim
Term
Prop
1
j
2
k
3
m
4
n
Test
Point
98
NO
3
Replace indicator lights dimmer
No. 10.
5
7
9
YES
97
a. Remove power from airplane.
b. Open BETA RANGE LIGHT circuit breaker (4).
c. Gain access to and disconnect
plug P599B (2) at main instrument
panel disconnect.
Is there continuity between terminal 1 of BETA indicator light (3)
and specified plug P599B pin?
Prop
Plug
Pin
1
A
2
C
3
E
4
G
Test
Points
16
11
18
12
20
13
22
14
99
Repair open circuit between
specified dimmer terminal and
related pin of receptacle J339B
(1). (See figure 2-6.)
YES
Prop
1
2
3
4
Dim
Term
j
k
m
n
Rcpt
Pin
A
C
E
G
NO
100
Repair open circuit. (See figure
2-6.)
NOTE
See figure 2-6 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 29)
61-10-00
2-44
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 30)
61-10-00
2-45
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 31)
61-10-00
2-46
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 32)
61-10-00
2-47
TO 1C-130H-2-61FI-00-1
FROM SHT 31
111
a. Connect plug P390 (3) to valve housing assembly (4).
b. Gain access to and disconnect plug P398 (2) at engine firewall.
Is there continuity between pins H and V of receptacle J239 (1)?
28
29
32
33
,
30
31
35
OR
115
Repair open circuit between receptacle J239
pin H and plug P390 pin
H. (See figure 2-6 or 27.)
NO
,
36
YES
112
Is airplane serial number AF92-0547 through AF92-2104 or
AF92-3281 and up?
YES
TO SHT 35
NO
113
a. Connect plug P398 at engine firewall.
b. Gain access to terminals of BETA indicator light (5).
Is a ground present on light terminal 2?
15
,
17
,
19
OR
116
YES
Replace BETA indicator
light assembly.
21
NO
114
a. Remove power from airplane.
b. Gain access to and disconnect plug P599B
(6) at main instrument panel disconnect.
Is a ground present on specified pin of receptacle J339B (7)?
Prop
Rcpt
Pin
1
B
2
D
3
F
4
H
Test
Point
23
24
25
117
Repair open circuit between BETA
indicator light terminal 2 and related plug P599B pin. (See figure 26.)
YES
Prop
1
2
3
4
26
NO
TO SHT 39
NOTE
See figure 2-6 or 2-7 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 33)
61-10-00
2-48
Plug
Pin
B
D
F
H
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 34)
61-10-00
2-49
TO 1C-130H-2-61FI-00-1
FROM SHT 33
118
YES
Is airplane AF95-1001 and up?
TO SHT 37
NO
119
a. Remove power from airplane.
b. Gain access to and disconnect
plug P1725A (1) from systems
caution/advisory panel.
Is a ground present on the specified pin of plug P1725A?
Prop
Plug
Pin
1
41
2
42
3
43
4
44
Test
Point
NO
TO SHT 37
54
55
56
57
YES
120
Fault is in MACAWS. Refer to
TO 1C-130H-2-33FI-00-1-2,
Section IV, for troubleshooting.
NOTE
See figure 2-7 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 35)
61-10-00
2-50
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 36)
61-10-00
2-51
TO 1C-130H-2-61FI-00-1
123
FROM SHT 35
121
Is an outboard propeller being
troubleshot?
NO
Repair open circuit between
plug P398 (1) pin H and related
pin of plug P1725A (2). (See
figure 2-7.)
Prop
2
3
YES
Plug
Pin
42
43
122
Gain access to and disconnect
plug P130/P1139 (4) at outer
wing break.
Is a ground present on specified
pin of receptacle J235/J935 (3)?
Prop
RCPT
Pin
1
E
4
H
Test
Point
27
124
NO
Repair open circuit between pin
H of plug P398 (1) and related
receptacle J235/J935 pin. (See
figure 2-7.)
Prop
1
4
RCPT
Pin
E
H
34
YES
125
Repair open circuit between
specified plug P130/P1139 pin
and related pin of plug P1725A
(2). (See figure 2-7.)
Prop
1
4
NOTE
See figure 2-7 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 37)
61-10-00
2-52
Plug
Pin
41
44
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 38)
61-10-00
2-53
TO 1C-130H-2-61FI-00-1
128
FROM SHT 33
126
Is an outboard propeller being
troubleshot?
NO
Repair open circuit between pin
H of plug P398 (1) and related
pin of receptacle J339B (2).
(See figure 2-6.)
Prop
2
3
YES
Rcpt
Pin
D
F
127
129
Gain access to and disconnect
plug P130 (4) at outer wing break.
Is a ground present on specified
pin of receptacle J235 (3)?
NO
Prop
Rcpt
Pin
1
E
4
H
Repair open circuit between pin
H of plug P398 (1) and related
receptacle J235 pin. (See figure 2-6.)
Test
Point
27
34
Prop
1
4
Rcpt
Pin
E
H
YES
130
Repair open circuit between
specified plug P130 pin and related pin of receptacle J339B
(2). (See figure 2-6.)
Prop
1
4
NOTE
See figure 2-6 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 39)
61-10-00
2-54
Plug
Pin
E
H
Rcpt
Pin
B
H
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 40)
61-10-00
2-55
TO 1C-130H-2-61FI-00-1
FROM SHT 1
131
6110002
Are any BETA indicator lights (1)
on dimly?
133
YES
Replace indicator lights dimmer
No. 10 (2).
NO
132
Gain access to terminals of indicator lights dimmer No. 10 (2).
Is 28 VDC present between dimmer terminals W and X?
1
134
YES
Replace indicator lights dimmer
No. 10.
2
NO
135
Fault is in dimming circuit. Go
to TO 1C-130H-2-33FI-00-1-1-1
and continue troubleshooting.
NOTE
See figure 2-6 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 41)
61-10-00
2-56
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 42)
61-10-00
2-57
TO 1C-130H-2-61FI-00-1
FROM SHT 1 OR 5
136
140
Gain access to and inspect engine NTS plunger (2).
Is plunger actuated?
YES
Replace reduction gear in accordance with TO 1C-130H-271JG-00-2, 71-90-20.
NO
137
a. Inspect NTS linkage for correct
gap of 0.011 to 0.020 inch in accordance with TO 1C-130H-261JG-20-1, 61-20-22.
b. Also inspect linkage for any
binding or damaged components.
Are any discrepancies found?
141
YES
Adjust NTS linkage in accordance with TO 1C-130H-261JG-20-1, 61-20-22, or repair
or replace damaged components as required.
NO
138
a. Rotate propeller control (5)
clockwise as viewed from the rear
and hold firmly against prop
torque retainer assembly (1).
b. Check clearance between
torque retainer lug (4) and prop
torque retainer assembly for a
maximum gap of 0.050 inch.
c. Release propeller control.
d. Also inspect components for
looseness or damage.
Are any discrepancies found?
142
YES
As required, replace damaged
components in accordance with
TO 1C-130H-2-61JG-20-1, 6120-11.
NO
139
143
Inspect NTS linkage through valve
housing assembly cover (3).
Is NTS linkage in the actuated position?
YES
Replace valve housing assembly cover in accordance with
TO 1C-130H-2-61JG-20-1, 6120-02.
NO
TO SHT 45
Figure 2-4. Propeller Assembly Malfunction (Sheet 43)
61-10-00
2-58
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 44)
61-10-00
2-59
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 45)
61-10-00
2-60
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 46)
61-10-00
2-61
TO 1C-130H-2-61FI-00-1
FROM SHT 45
153
a. Remove power from airplane.
b. Gain access to and disconnect
plug P1725A (2) from systems
caution/advisory panel.
Is a ground present on specified
pin of plug P1725A?
156
Prop
Plug
Pin
1
53
2
54
3
55
4
56
Test
Point
NO
Fault is in MACAWS. Refer to
TO 1C-130H-2-33FI-00-2 for
troubleshooting.
78
79
80
81
YES
157
154
Is an outboard propeller being
troubleshot?
NO
YES
Repair ground fault between
applicable pin of plug P1725A
(2) and pin F of plug P398 (1).
(See figure 2-9.)
155
Gain access to and disconnect
plug P18/P1835 (3) at outer wing
break.
Is a ground present on plug pin
N?
33
158
NO
Repair ground fault between pin
N of receptacle J233/J956 (4)
and pin F of plug P398 (1).
(See figure 2-9.)
47
YES
159
Repair ground fault between
plug P18/P1835 pin N and applicable pin of plug P1725A (2).
(See figure 2-9.)
NOTE
See figure 2-9 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 47)
61-10-00
2-62
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 48)
61-10-00
2-63
TO 1C-130H-2-61FI-00-1
FROM SHT 45
160
a. Place FEATHER VALVE AND
NTS switch (3) to NORMAL.
b. Gain access to terminals of
NTS check relay (2) and disconnect wire from relay terminal A2.
Is a ground present on disconnected wire?
52
,
22
59
,
165
YES
164
NO
Is airplane an MC-130H?
YES
Repair ground fault between relay terminal A2 and terminal 2
of FEATHER VALVE AND NTS
CHECK light (4). (See figure 28.)
29
OR
NO
TO SHT 51
161
Is there continuity between relay
terminals A1 and A2.
54
61
52
59
24
,
31
OR
22
YES
166
Replace NTS check relay.
,
29
NO
167
162
Is an outboard propeller being
troubleshot?
NO
YES
Repair ground fault between
NTS check relay terminal A3
and pin F of plug P398 (1).
(See figure 2-8.)
163
Gain access to and disconnect
plug P18 (5) at outer wing break.
Is a ground present on plug pin
N?
47
OR
33
168
NO
Repair ground fault between pin
N of receptacle J233 (6) and
pin F of plug P398 (1). (See
figure 2-8.)
YES
169
Repair ground fault between
plug P18 pin N and NTS check
relay terminal A3. (See figure
2-8.)
NOTE
See figure 2-8 or 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 49)
61-10-00
2-64
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 50)
61-10-00
2-65
TO 1C-130H-2-61FI-00-1
FROM SHT 49
170
Gain access to and disconnect
plug 47404A2P1 from indicator
light dimmer No. 4 (1).
Is a ground present on specified
pins/receptacle points?
Pins
10
24
23
22
3
15
16
4
Test Points
69
70
71
171
NO
Replace indicator lights dimmer
No. 4 (1).
72
73
74
75
76
YES
172
Repair ground fault between
plug 47404A2P1 and applicable
terminals. (See figure 2-10.)
NOTE
See figure 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 51)
61-10-00
2-66
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 52)
61-10-00
2-67
TO 1C-130H-2-61FI-00-1
FROM SHT 1
173
175
a. Open PROP SYNCHRO
PHASER and SYNCHRO
PHASER circuit breakers (5,4).
b. Gain access to and disconnect
plug P390 (6) at valve housing
assembly.
Did FEATHER VALVE AND NTS
CHECK light (3) go off?
YES
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02
(because of internal short circuit).
NO
174
176
Gain access to and disconnect
plug P398 (2) at engine firewall.
Did FEATHER VALVE AND NTS
CHECK light go off?
YES
Repair ground fault between
plug P390 pin E and pin E of
receptacle J239 (1). (See figure 2-8 or 2-10.)
NO
TO SHT 55
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
Figure 2-4. Propeller Assembly Malfunction (Sheet 53)
61-10-00
2-68
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 54)
61-10-00
2-69
TO 1C-130H-2-61FI-00-1
FROM SHT 53
177
a. Place FEATHER VALVE AND NTS
CHECK switch (3) to NORMAL.
b. Gain access to NTS check relay (2)
and disconnect wire from relay terminal B2.
Is a ground present on relay terminal B2?
51
,
21
,
58
OR
YES
181
Replace NTS check relay.
28
NO
178
182
Disconnect wire number _K603A from relay
terminal X1.
Is a ground present on disconnected wire?
50
,
20
,
57
OR
YES
27
Repair ground fault on wire
number K603A between relay terminals X1 and B2.
(See figure 2-8 or 2-10.)
NO
183
179
NO
Is an outboard propeller being troubleshot?
YES
180
Repair ground fault between
NTS check relay terminal X1
and pin E of plug P398 (1).
(See figure 2-8 or 2-10.)
184
Gain access to and disconnect plug P18
(4) at outer wing break.
Is a ground present on plug pin P?
48
OR
34
NO
Repair ground fault between
pin E of plug P398 (1) and
pin P of receptacle J233 (5).
(See figure 2-8 or 2-10.)
YES
185
Repair ground fault between
plug P18 pin P and NTS
check relay terminal X1.
(See figure 2-8 or 2-10.)
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
3.
See figure 2-8 or 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 55)
61-10-00
2-70
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 56)
61-10-00
2-71
TO 1C-130H-2-61FI-00-1
FROM SHT 3 OR 5
186
Does propeller feather override
button (2) cycle?
YES
TO SHT 63
NO
187
6110015
a. If troubleshooting fault code
6110015, move engine condition
lever (4) to FEATHER/FTR.
b. Momentarily press propeller
feather override button (2).
1 3 4 Does light in button come
on while button is pressed?
2 Does FTHR light (5) come on
while button is pressed?
NO
188
Is fault code 6110017 being
troubleshot?
YES
190
Replace propeller feather override button.
NO
YES
TO SHT 59
191
6110016
189
Momentarily hold engine condition
lever (4) in AIR START.
Does auxiliary pump motor (1) run
while lever is held?
YES
NO
Repair power circuit to specified
terminal of terminal board
TB146A (3). (See figure 2-11
or 2-12.)
Prop
1
2
3
4
TO SHT 65
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 57)
61-10-00
2-72
TB-Term
193
194
195
196
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 58)
61-10-00
2-73
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 airplane
and gain access to terminals of
propeller feather override button
(2).
Is a ground present on button terminal 7?
NO
TO SHT 61
23
YES
193
Gain access to terminals of feather relay (1).
Is there continuity between relay
terminal A3 and propeller feather
override button terminal 3?
30
195
NO
Repair open circuit. (See figure
2-11 or 2-12.)
24
YES
194
Is there continuity between relay
terminals A2 and A3?
31
NO
196
Replace feather relay.
30
YES
197
Replace propeller feather override button.
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.
5.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 59)
61-10-00
2-74
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 60)
61-10-00
2-75
TO 1C-130H-2-61FI-00-1
200
FROM SHT 59
198
Is an outboard propeller being
troubleshot?
NO
YES
Repair open circuit between terminal 7 of propeller feather
override button (4) and terminal
1 of related terminal board
TB107 (3). (See figure 2-11 or
2-12.)
Prop
2
3
TB
TB107T
TB107U
201
199
Gain access to and disconnect
plug P124/P1134 (1) at outer
wing break.
Is a ground present on pin V of
receptacle J209/J951 (2)?
NO
Repair open circuit between receptacle J209/J951 pin V and
terminal 1 of related terminal
board TB107 (3). (See figure
2-11 or 2-12.)
Prop
1
4
47
YES
TB
TB107S
TB107V
202
Repair open circuit between
plug P124/P1134 pin V and terminal 7 of propeller feather
override button (4). (See figure
2-11 or 2-12.)
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.
5.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 61)
61-10-00
2-76
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 62)
61-10-00
2-77
TO 1C-130H-2-61FI-00-1
FROM SHT 57
203
6110014
208
YES
Gain access to and inspect propeller feather override button (3) for
correct jamnut installation, and loose or damaged connections.
Are any discrepancies found?
Repair or replace propeller
feather override button as
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
MOTOR circuit breakers (1).
c. Gain access to terminals of feather relay (2) and disconnect wire
from relay terminal X2.
d. Move engine condition lever to FEATHER/FTR.
Does propeller feather override button pull in and remain in?
209
NO
Replace propeller feather
override button.
YES
205
a. Remove electrical power.
b. Move engine condition lever to GROUND STOP/GND STOP.
Is there continuity between feather relay terminals
29
A1 and B1?
210
NO
33
Repair open circuit. (See
figure 2-11 or 2-12.)
YES
206
211
Is there continuity between relay terminals
B1 and X1?
NO
33
28
25
28
Repair open circuit. (See
figure 2-11 or 2-12.)
YES
207
Is there continuity between propeller feather override
button terminal 8 and feather relay terminal X1?
YES
212
Replace feather relay.
NO
213
Repair open circuit. (See
figure 2-11 or 2-12.)
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.
5.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 63)
61-10-00
2-78
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 64)
61-10-00
2-79
TO 1C-130H-2-61FI-00-1
FROM SHT 57
215
214
Is fault code 6110016 being
troubleshot?
NO
Pull fire emergency handle (1).
Does propeller feather override
button (3) pull in?
YES
NO
217
Replace propeller feather override button.
YES
216
a. Gain access to terminal board
TB146A (4).
b. Move engine condition lever (5)
to FEATHER/FTR.
Is 28 VDC present on specified
terminal?
Prop
TB-Term
1
197
2
198
3
202
4
205
Test
Point
35
35
35
218
Repair open circuit between terminal A2 of feather relay (2)
and related terminal board
TB146A terminal. (See figure
YES 2-11 or 2-12.)
Prop
1
2
3
4
35
NO
TO SHT 67
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.
5.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 65)
61-10-00
2-80
TB-Term
197
198
202
205
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 66)
61-10-00
2-81
TO 1C-130H-2-61FI-00-1
FROM SHT 65
219
a. Remove electrical power from
airplane.
b. Gain access to terminals of engine condition lever feather control switch (1).
Is there continuity between switch
terminals 1NO and 2NO?
NO
Test
Points
Prop
Sw
1
S86E
2
S86F
3
S86G
4
S86H
221
40
39
40
39
40
39
40
39
Adjust or replace feather control
switch in accordance with TO
1C-130H-2-76JG-00-1, 76-1038.
YES
220
Is there continuity between feather control switch terminal 2NO
and specified terminal of terminal
board TB146A (2)?
Prop Sw
TBTest
Term Points
1
S86E 193
2
S86F 194
3
S86G 195
4
S86H 196
222
YES
39
38
39
38
39
38
39
38
Repair open circuit between
feather control switch terminal
1NO and related terminal board
TB146A terminal. (See figure
2-11 or 2-12.)
Prop
1
2
3
4
Sw
S86E
S86F
S86G
S86H
TB-Term
197
198
202
205
NO
223
Repair open circuit. (See figure
2-11 or 2-12.)
NOTE
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 67)
61-10-00
2-82
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 68)
61-10-00
2-83
TO 1C-130H-2-61FI-00-1
FROM SHT 3 OR 5
227
224
Is airplane serial number AF920547 through AF92-2104 or
AF92-3281 and up?
YES
6110013
Momentarily hold MACAWS
LAMP TEST switch (3) in test position.
Does applicable light come on?
NO
NO
TO SHT 71
YES
229
Fault is in MACAWS. Go to TO
1C-130H-2-33FI-00-1-2, Section
IV, and continue troubleshooting.
225
6110013
Remove bulb from affected PROPELLER FEATHER OVERRIDE
button (2) and inspect for correct
part number (AN3140-327).
Is correct bulb installed?
230
NO
Replace bulb with correct part
number.
YES
226
a. Move ENGINE CONDITION
lever (1) to GROUND STOP.
b. Remove power from airplane
and gain access to terminals of
affected PROPELLER FEATHER
OVERRIDE button.
Is a ground present on button terminal G?
NO
228
NO
Is airplane an MC-130H?
231
Repair ground circuit. (See figure 2-11.)
YES
27
YES
TO SHT 73
232
Replace PROPELLER FEATHER OVERRIDE button.
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.
5.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 69)
61-10-00
2-84
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 70)
61-10-00
2-85
TO 1C-130H-2-61FI-00-1
FROM SHT 69
233
a. Remove electrical power from
airplane.
b. Gain access to and disconnect
plug P1725A (2) from systems
caution/advisory panel.
Is a ground present on applicable
pin of plug P1725A?
Prop
Plug
Pin
1
45
2
46
3
47
4
48
Test
Point
60
234
NO
Repair open circuit between
plug P1725A and propeller
feather override button (1), terminal 2. (See figure 2-12.)
62
63
64
YES
235
Fault is in MACAWS. Refer to
TO 1C-130H-2-33FI-00-1-2 for
troubleshooting.
NOTE
See figure 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 71)
61-10-00
2-86
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 72)
61-10-00
2-87
TO 1C-130H-2-61FI-00-1
FROM SHT 69
236
Gain access to and disconnect plug
47405A1P1 from indicator light dimmer No.
5 (1).
Is there continuity between specified pin of
plug 47405A1P1 and terminal G of the applicable PROPELLER FEATHER OVERRIDE button?
238
NO
Prop
Pin
1
11
2
12
3
13
4
25
Test Points
51
27
52
27
53
27
54
27
Repair open circuit between
applicable points. (See figure 2-11.)
YES
237
Is a ground present on specified
47405A1P1 plug pins?
Pins
5
17
18
6
Test Points
239
NO
55
56
Repair open circuit. (See
figure 2-11.)
57
58
YES
240
Replace indicator light dimmer No. 5 (1).
NOTE
See figure 2-11 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 73)
61-10-00
2-88
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 74)
61-10-00
2-89
TO 1C-130H-2-61FI-00-1
FROM SHT 7 OR 9
241
6110008
NOTE
Perform steps a and b only if
troubleshooting fault code
6110008.
a. Move throttle (6) above
FLIGHT IDLE/FLT IDLE gate.
b. Hold engine condition lever (7)
in AIR START position until propeller blades (2) are above flight
idle.
c. Open PROP SYNCHRO
PHASER and SYNCHRO
PHASER circuit breakers (5,4).
d. Gain access to and disconnect
plug P390 (1) at valve housing
assembly.
Does BETA indicator light (3) go
off?
242
Adjust or replace BETA indicator switch as required in accordance with TO 1C-130H-261JG-20-1, 61-20-04.
YES
NO
1
2
TO SHT 77
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 2-4. Propeller Assembly Malfunction (Sheet 75)
61-10-00
2-90
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 76)
61-10-00
2-91
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 77)
61-10-00
2-92
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 78)
61-10-00
2-93
TO 1C-130H-2-61FI-00-1
254
FROM SHT 77
252
Is an outboard propeller being
troubleshot?
NO
Repair ground fault between
plug P1725A (2) pin and plug
P398 (1) pin H. (See figure 27.)
Prop
2
3
YES
Pin
42
43
253
Gain access to and disconnect
plug P130/P1139 (4) at outer
wing break.
Is a ground present on receptacle
J235/J935 (3) pin?
255
NO
Prop
Plug
Pin
1
E
4
H
Test
Point
Repair ground fault between
plug P130/P1139, pin H and
plug P1725A (2). (See figure
2-7.)
27
34
YES
256
Repair ground fault between receptacle J235/J935, pin H and
plug P398, pin H. (See figure
2-7.)
NOTE
See figure 2-7 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 79)
61-10-00
2-94
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 80)
61-10-00
2-95
TO 1C-130H-2-61FI-00-1
259
FROM SHT 77
257
Is an outboard propeller being
troubleshot?
NO
Repair ground fault between pin
H of plug P398 (1) and related
pin of receptacle J339B (2).
(See figure 2-6.)
Prop
2
3
YES
Rcpt
Pin
D
F
258
260
Gain access to and disconnect
plug P130 (4) at outer wing break.
Is a ground present on specified
plug pin?
NO
Prop
Plug
Pin
1
E
4
H
Repair ground fault between pin
H of plug P398 (1) and related
pin of receptacle J235 (3).
(See figure 2-6.)
Test
Point
27
34
Prop
1
4
Rcpt
Pin
E
H
YES
261
Repair ground fault between
specified plug P130 pin and related pin of receptacle J339B
(2). (See figure 2-6.)
Prop
1
4
NOTE
See figure 2-6 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 81)
61-10-00
2-96
Plug
Pin
E
H
Rcpt
Pin
B
H
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 82)
61-10-00
2-97
TO 1C-130H-2-61FI-00-1
FROM SHT 7
262
Did propeller blades (1) move toward feather position at all?
NO
TO SHT 85
YES
263
a. Open FEATHER & AIR START
circuit breaker (2).
b. 1 3 Open PROP LOW OIL
LEVEL circuit breaker (3).
c. 2 Open MACAWS PILOT, COPILOT and CONTROL circuit
breakers (4,5,6,7,8).
d. Gain access to and disconnect
plug P392 (11) at propeller control.
Is there continuity between pin F
of propeller control receptacle (10)
and airplane ground?
(Use an auxiliary pump motor attaching bolt (9) as ground.)
YES
TO SHT 95
50
NO
264
265
Inspect wiring to propeller control
receptacle for loose and broken
connections.
Is any damage found?
YES
Repair loose or damaged wiring
as required. (See figure 2-11
or 2-12.)
NO
266
Replace propeller control in accordance with TO 1C-130H-261JG-20-1, 61-20-01.
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024, except MC-130H airplanes.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3
MC-130H airplanes.
4.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 83)
61-10-00
2-98
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 84)
61-10-00
2-99
TO 1C-130H-2-61FI-00-1
FROM SHT 83
271
267
Is FEATHER VALVE AND
NTS CHECK light (3) on?
2 Is NTS light (6) on?
1
3
4
Rig engine coordinator-to-propeller control assembly linkage
in accordance with TO 1C130H-2-61JG-20-1, 61-20-21.
NO
YES
268
With engine condition lever (5) in
FEATHER/FTR position, is auxiliary
pump motor (1) running?
YES
TO SHT 87
NO
269
Momentarily hold engine condition
lever in AIR START.
Does auxiliary pump motor run while
lever is held?
NO
TO SHT 89
YES
270
a. Temporarily remove power from
airplane and gain access to propeller
feather override button (4).
b. Move engine condition lever to
FEATHER/FTR.
Is 28 VDC present on button terminal
4?
272
NO
Replace propeller feather override button.
22
YES
273
Repair open circuit between
button terminal 4 and terminal
B3 of feather relay (2). (See
figure 2-11 or 2-12.)
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.
5.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 85)
61-10-00
2-100
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 86)
61-10-00
2-101
TO 1C-130H-2-61FI-00-1
FROM SHT 13 OR 85
274
a. If pulled, push in fire emergency handle (3).
b. Move engine condition lever (2) to
GROUND STOP/GND STOP.
c. Gain access to and disconnect plug
P410 (4) at auxiliary pump motor.
d. Move engine condition lever to
FEATHER/FTR.
Is 115 VAC present on plug pins A, B,
and C?
15
16
NO
TO SHT 91
17
YES
275
a. Move engine condition lever to
GROUND STOP/GND STOP.
b. Check auxiliary pump motor for open
phase by checking continuity between
motor receptacle pins A to B and B to
C.
Is there an open phase in motor?
15
16
AND
16
277
YES
Replace auxiliary pump motor in
accordance with TO 1C-130H-261JG-20-1, 61-20-09.
17
NO
276
278
NOTE
If troubleshooting came from sheet 13
rather than sheet 85, proceed directly to
block 278.
NO
a. Remove auxiliary pump motor in accordance with TO 1C-130H-2-61JG-201, 61-20-09.
b. Inspect motor for sheared motor shaft
(1).
Is auxiliary pump motor shaft sheared?
Reseal pitchlock regulator assembly in accordance with TO 1C130H-2-61JG-10-1, 61-10-11,
reseal low pitch stop assembly in
accordance with TO 1C-130H-261JG-10-1, 61-10-12, and reseal
dome assembly in accordance with
TO 1C-130H-2-61JG-10-1, 61-1013.
YES
279
Replace auxiliary pump motor in
accordance with TO 1C-130H-261JG-20-1, 61-20-09.
NOTE
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 87)
61-10-00
2-102
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 88)
61-10-00
2-103
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 89)
61-10-00
2-104
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 90)
61-10-00
2-105
TO 1C-130H-2-61FI-00-1
FROM SHT 87 OR 89
286
Gain access to feather pump motor relay (4).
Is 115 VAC present on relay terminals A1, B1, and C1, or L3, L2,
and L1 (depending upon terminal
labeling)?
8
7
288
NO
Is 115 VAC present on relay terminals A2, B2 and C2, or T3, T2,
and T1 (depending upon terminal
labeling)?
3
2
289
NO
Repair power circuit to affected
relay terminal. (See figure 2-11
or 2-12.)
1
6
YES
YES
290
Replace feather pump motor relay.
291
287
Gain access to and disconnect plug P283
(2) at engine firewall.
Is 115 VAC present on plug pins A, B, and
C?
12
13
14
Repair open circuit between affected pin
of receptacle J166 (1) and related pin of
plug P410 (3). (See figure 2-11 or 2-12.)
YES
Rcpt
Pin
A
B
C
NO
TO SHT 93
NOTE
1
2.
MC-130H airplanes.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 91)
61-10-00
2-106
Plug
Pin
A
B
C
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 92)
61-10-00
2-107
TO 1C-130H-2-61FI-00-1
294
FROM SHT 91
Repair open circuit between affected pin of plug P283 (1) and related
terminal of feather pump motor relay (4). (See figure 2-11 or 2-12.)
292
Is an outboard propeller being troubleshot?
NO
Plug Pin
A
B
C
YES
Relay Term
C1/L1
B1/L2
A1/L3
293
295
Gain access to and disconnect plug P147/P1833 (2)
at outer wing break.
Is 115 VAC present on plug
pins G, H, and I?
9
10
11
Repair open circuit between affected plug P147/P1833 pin and related
terminal of feather pump motor relay (4). (See figure 2-11 or 2-12.)
NO
Plug Pin
G
H
I
Relay Term
C1/L1
B1/L2
A1/L3
YES
296
Repair open circuit between affected pin of plug P283 (1) and related
pin of receptacle J35/J955 (3). (See figure 2-11 or 2-12.)
Plug Pin
A
B
C
Rcpt Pin
G
H
I
NOTE
1
2.
MC-130H airplanes.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 93)
61-10-00
2-108
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 94)
61-10-00
2-109
TO 1C-130H-2-61FI-00-1
FROM SHT 83
297
a. Connect plug P392 (3) to propeller control.
b. Gain access to and disconnect
plug P396 (2) at engine firewall.
Is a ground present on pin F of
receptacle J241 (1)?
299
NO
Repair open circuit between receptacle J241 pin F and plug
P392 pin F. (See figure 2-11 or
2-12.)
49
YES
298
Gain access to terminal board
TB107 (4) and disconnect specified wire from terminal 1.
Is a ground present on disconnected wire?
Test
Wire No. Point
Prop
TB
1
TB107S 1K76E18
2
TB107T 2K76D18
3
TB107U 3K76D18
4
TB107V 4K76D18
300
NO
Repair open circuit between
plug P396 pin F and terminal 1
of related terminal board
TB107. (See figure 2-11 or 212.)
48
48
Prop TB
1
TB107S
2
TB107T
Prop TB
3
TB107U
4
TB107V
48
48
YES
301
Reseal pitchlock regulator assembly in accordance with TO
1C-130H-2-61JG-10-1, 61-1011, reseal low pitch stop assembly in accordance with TO
1C-130H-2-61JG-10-1, 61-1012, and reseal dome assembly
in accordance with TO 1C130H-2-61JG-10-1, 61-10-13. If
fault persists, replace propeller
control in accordance with TO
1C-130H-2-61JG-20-1, 61-2001.
NOTE
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 95)
61-10-00
2-110
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 96)
61-10-00
2-111
TO 1C-130H-2-61FI-00-1
FROM SHT 7
302
6110012
a. Move engine condition lever (6) to FEATHER/FTR.
b. After propeller blades (1) have reached
feather position, check for internal leakage by
holding propeller feather override button (4) in
while listening for a loud squeal from respective propeller assembly.
Is a loud squeal heard from propeller?
303.1
Reseal pitchlock regulator assembly in accordance with TO 1C-130H-2-61JG-10-1,
61-10-11; reseal low pitch stop assembly in
accordance with TO 1C-130H-2-61JG-10-1,
61-10-12; and reseal dome assembly in accordance with TO 1C-130H-2-61JG-10-1,
61-10-13.
NO
YES
302.1
a. Open affected FEATHER PUMP MOTOR
PHASE A,B,C/ 4 FEATHER PUMP MOTOR
circuit breakers (5).
b. Push affected propeller feather override
button (4) in.
c. Gain access to and disconnect plug P392
(2) at propeller control.
Does propeller feather override button pop
out?
NO
TO SHT 99
YES
303
304
Inspect wiring to propeller control receptacle
(3) for loose and broken connections.
Is any damage found?
YES
Repair loose or damaged wiring as required.
(See figure 2-11 or 2-12.)
NO
305
Replace/repair propeller control in accordance with TO 1C-130H-2-61JG-20-1, 6120-01 and 3HA2-7-3. (If desired, the replacement/repair of the propeller control
may be delayed to the next phase or isochronal inspection to replace the pressure cutout switch in the control, which is the cause
of the fault.)
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 97)
61-10-00
2-112
Change 4
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 98)
61-10-00
2-113
TO 1C-130H-2-61FI-00-1
FROM SHT 97
306
310
a. Open PROP SYNCHRO PHASER and SYNCHRO PHASER circuit breakers (6,7).
b. Gain access to and disconnect plug P390 (9) at valve housing
assembly.
Does propeller feather override button (5) pop out?
YES
Adjust or replace pressure
cutout backup switch as required in accordance with
TO 1C-130H-2-61JG-20-1,
61-20-03.
NO
311
307
YES
Gain access to and disconnect plug P396 (4) at engine firewall.
Does propeller feather override button pop out?
Repair ground fault between
plug P392 pin F and pin F of
receptacle J241 (1). (See
figure 2-11 or 2-12.)
NO
312
308
YES
Gain access to and disconnect plug P398 (3) at engine firewall.
Does propeller feather override button pop out?
Repair ground fault between
plug P390 pin J and pin I of
receptacle J239 (2). (See
figure 2-11 or 2-12.)
NO
309
a. Remove power from airplane.
b. Open FEATHER & AIR START circuit breaker (8).
c. Gain access to terminals of propeller feather override button and
disconnect wire from button terminal 7.
23
Is a ground present on disconnected wire?
313
NO
Replace propeller feather
override button.
YES
TO SHT 101
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.
5.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 99)
61-10-00
2-114
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 100)
61-10-00
2-115
TO 1C-130H-2-61FI-00-1
FROM SHT 99
314
Gain access to terminal board
TB107 (3) and disconnect specified wire from terminal 1.
Is a ground present on disconnected wire?
Test
Wire No. Point
Prop
TB
1
TB107S 1K76C18
2
TB107T 2K76B18
3
TB107U 3K76B18
4
TB107V 4K76C18
YES
TO SHT 103
48
48
48
48
NO
315
Disconnect specified wire from
terminal board TB107 terminal 1.
Is a ground present on disconnected wire?
316
Test
Wire No. Point
Prop
TB
1
TB107S 1K76E18
2
TB107T 2K76D18
3
TB107U 3K76D18
4
TB107V 4K76D18
48
NO
Repair ground fault between
terminal board TB107 terminal
1 and pin I of plug P398 (1).
(See figure 2-11 or 2-12.)
48
48
48
YES
317
Repair ground fault between
terminal board TB107 terminal
1 and pin F of plug P396 (2).
(See figure 2-11 or 2-12.)
NOTE
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 101)
61-10-00
2-116
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 102)
61-10-00
2-117
TO 1C-130H-2-61FI-00-1
320
FROM SHT 101
318
Is an outboard propeller being
troubleshot?
NO
YES
Repair ground fault between
terminal 7 of propeller feather
override button (2) and terminal
1 of related terminal board
TB107 (1). (See figure 2-11 or
2-12.)
Prop TB
1
TB107S
2
TB107T
Prop TB
3
TB107U
4
TB107V
319
Gain access to and disconnect
plug P124/P1134 (3) at outer
wing break.
Is a ground present on plug pin
V?
321
YES
47
Repair ground fault between pin
V of plug P124/P1134 and terminal 7 of propeller feather
override button (2). (See figure
2-11 or 2-12.)
NO
322
Repair ground fault between pin
V of receptacle J209/J951 (4)
and terminal 1 of related terminal board TB107 (1). (See figure 2-11 or 2-12.)
Prop TB
1
TB107S
2
TB107T
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.
5.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 103)
61-10-00
2-118
Prop TB
3
TB107U
4
TB107V
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 104)
61-10-00
2-119
TO 1C-130H-2-61FI-00-1
FROM SHT 7
322.1
YES
Is aircraft being troubleshot MACAWS equipped (AF92-0547
thru AF92-2104 and AF92-3281 thru AF96-7325)?
TO SHT 113
NO
326
6110022, 6110023
323
a. If troubleshooting fault code
6110022 or 6110023, place
FEATHER VALVE AND NTS
CHECK switch (4) to VALVE.
b. Press to test affected
FEATHER VALVE AND NTS
CHECK light (2 or 3).
Does light press to test?
YES
a. Open NTS CHECK circuit breaker (5).
b. Open FEATHER PUMP MOTOR PHASE
A,B,C/ 2 FEATHER PUMP MOTOR circuit
breakers (6).
c. Move ENGINE CONDITION lever (1) to
FEATHER.
d. Temporarily remove power from airplane
and gain access to terminals of FEATHER
VALVE AND NTS CHECK light.
Is a ground present on light terminal 2?
5
NO
,
7
,
9
OR
328
YES Replace FEATHER
VALVE AND NTS
CHECK light assembly.
11
NO
TO SHT 109
324
YES
Is propeller No. 1 being troubleshot?
TO SHT 107
NO
327
325
Press to test No. 1 FEATHER VALVE AND NTS
CHECK light (2).
Does light press to test?
NO
YES
Temporarily remove power from airplane
and gain access to terminals of affected
FEATHER VALVE AND NTS CHECK light.
Is 28 VDC present on light terminal 1?
6
,
8
,
10
OR
329
YES Replace FEATHER VALVE
AND NTS CHECK light assembly.
12
NO
TO SHT 107
TO SHT 121
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
3.
See figure 2-8 or 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 105)
61-10-00
2-120
Change 7
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 106)
61-10-00
2-121
TO 1C-130H-2-61FI-00-1
FROM SHT 105
330
Temporarily remove power from
airplane and gain access to terminals of ENG NO. 1 FEATHER
VALVE AND NTS CHECK light
(1).
Is 28 VDC present on light terminal 1?
333
YES
Replace ENG NO. 1 FEATHER
VALVE AND NTS CHECK light
assembly.
6
NO
331
Temporarily remove power from
airplane and gain access to terminals of FEATHER VALVE AND
NTS CHECK switch (2).
Is 28 VDC present on switch terminal 5?
334
NO
Repair power circuit to switch
terminal 5. (See figure 2-8 or
2-10.)
1
YES
332
With FEATHER VALVE AND NTS
CHECK switch in VALVE position,
is 28 VDC present on switch terminal 4?
335
NO
Replace FEATHER VALVE
AND NTS CHECK switch.
2
YES
336
Repair open circuit between
FEATHER VALVE AND NTS
CHECK switch terminal 4 and
terminal 1 of ENG NO. 1
FEATHER VALVE AND NTS
CHECK light. (See figure 2-8
or 2-10.)
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
3.
See figure 2-8 or 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 107)
61-10-00
2-122
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 108)
61-10-00
2-123
TO 1C-130H-2-61FI-00-1
FROM SHT 9 OR 105
337
a. Open PROP SYNCHRO PHASER and
SYNCHRO PHASER circuit breakers (4,3).
b. Gain access to and disconnect plug
P390 (6) at valve housing assembly.
Is there continuity between pins F and K of
valve housing assembly receptacle (5)?
41
43
66
68
13
,
OR
15
38
342
340
NO
Is fault code 6110023 being
troubleshot?
NO
,
Adjust or replace NTS
YES switch as required in
accordance with TO
1C-130H-2-61JG-20-1,
61-20-05.
40
YES
TO SHT 119
341
338
Is a ground present on plug P390
pin K?
43
,
15
,
68
NO
40
OR
343
Gain access to and disconnect plug
P398 (2) at engine firewall.
Is a ground present on plug pin V?
46
,
18
,
65
OR
YES
37
YES Repair open circuit between
plug P390 pin K and pin V
of receptacle J239 (1). (See
figure 2-8, 2-9, or 2-10.)
NO
344
Repair ground circuit. (See figure 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
engine firewall.
Is there continuity between pins F and pin V of receptacle J239 (1)?
44
46
63
65
16
,
OR
35
18
345
NO
,
Repair open circuit between receptacle J239 pin F and plug
P390 pin F. (See figure 2-8, 29, or 2-10.)
37
YES
TO SHT 111
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.
5.
See figure 2-8, 2-9, or 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 109)
61-10-00
2-124
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 110)
61-10-00
2-125
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 111)
61-10-00
2-126
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 112)
61-10-00
2-127
TO 1C-130H-2-61FI-00-1
360
FROM SHT 105 AND 111
357
NO
Is an outboard propeller being
troubleshot?
YES
a. Remove electrical power from
airplane.
b. Gain access to and disconnect
plug P1725A (2) from systems
caution/advisory panel.
Is a ground present on the applicable plug pin?
Prop
Plug Pin
2
54
3
55
YES
TO SHT 115
Test Point
79
80
NO
361
Repair open circuit between plug
P1725A and plug P398 (1), pin F.
(See figure 2-9.)
358
NOTE
Put ohmmeter negative lead on receptacle pin P.
Gain access to and disconnect plug P18/P1835
(4) at outer wing break.
Is there continuity between pins N and P of receptacle J233/J956 (3)?
47
48
OR
33
362
NO
Repair open circuit between receptacle J233/J956 pin N and plug
P398 pin F. (See figure 2-9.)
34
YES
359
a. Remove electrical power from airplane.
b. Gain access to and disconnect plug P1725A
(2) from systems caution/advisory panel.
Is a ground present on applicable plug pin?
Prop
Plug Pin
1
53
4
56
Test Point
363
NO
Repair open circuit between plug
P1725A and plug P18/P1835 pin
N. (See figure 2-9.)
78
81
YES
TO SHT 115
NOTE
See figure 2-9 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 113)
61-10-00
2-128
Change 7
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 114)
61-10-00
2-129
TO 1C-130H-2-61FI-00-1
FROM SHT 113
364
Momentarily hold the MACAWS
LAMP TEST switch (1) in the test
position.
Does the applicable light come
on?
365
NO
Replace the applicable MACAWS bulb.
YES
366
Fault is in MACAWS. Refer to
TO 1C-130H-2-33FI-00-1-2 for
troubleshooting.
Figure 2-4. Propeller Assembly Malfunction (Sheet 115)
61-10-00
2-130
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 116)
61-10-00
2-131
TO 1C-130H-2-61FI-00-1
FROM SHT 111
367
Gain access to and disconnect plug
47404A2P1 from indicator light dimmer No.
4 (2).
Is a ground present on specified pins?
Light No.
Plug Pin
1
1
2
16
3
15
4
3
Test Point
369
NO
76
75
Repair open circuit between relay terminal A2 and related pin of plug
47404A2P1 of indicator light dimmer
No. 4 (2). (See figure 2-10.
74
73
YES
368
a. Temporarily remove power from airplane
and gain access to terminals of specified
FEATHER VALVE AND NTS CHECK light
(1).
b. Disconnect wire from terminal 2.
Is there continuity between terminal 2 and
related pin of plug 47404A2P1?
370
YES
Light No.
Plug Pin
1
10
2
24
3
23
4
22
Test Point
69
Repair open circuit between FEATHER VALVE AND NTS CHECK light
(1) and related pin of plug 47404A2P1
of indicator light dimmer No. 4 (2).
(See figure 2-10.)
70
71
72
NO
371
Replace indicator light dimmer No. 4
(2).
NOTE
See figure 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 117)
61-10-00
2-132
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 118)
61-10-00
2-133
TO 1C-130H-2-61FI-00-1
FROM SHT 21 OR 109
372
6110021
Gain access to and check NTS linkage for correct gap of
0.011 to 0.020 inch in accordance with TO 1C-130H-2-61JG20-1, 61-20-22.
Is adjustment correct?
376
NO
Adjust NTS linkage in accordance with TO 1C-130H-261JG-20-1, 61-20-22.
YES
373
a. Rotate propeller control (2) clockwise as viewed from the
rear and hold firmly against prop torque retainer assembly (6).
b. Check clearance between torque retainer lug (3) and prop
torque retainer assembly for a maximum gap of 0.050 inch.
c. Release propeller control.
d. Also inspect components for looseness or damage.
Are any discrepancies found?
377
As required, replace damaged components in accordance with TO 1C-130H-261JG-20-1, 61-20-11.
YES
NO
374
a. If necessary, connect plug P390 (4) to valve housing assembly (5).
b. Gain access to and manually actuate NTS switch (1).
378
Adjust or replace NTS
switch as required in accordance with TO 1C-130H-261JG-20-1, 61-20-05.
NO
1 Does FEATHER VALVE AND NTS CHECK light (7) come
on while switch is actuated?
2
Does NTS light (8) come on while switch is actuated?
YES
375
379
Check engine coordinator-to-propeller control assembly rigging in accordance with
TO 1C-130H-2-61JG-20-1, 61-20-21.
Is rigging correct?
NO
Rig engine coordinator-to-propeller
control assembly linkage in accordance with TO 1C-130H-2-61JG-20-1,
61-20-21.
YES
380
Fault is in engine. Go to TO 1C130H-2-70FI-00-1-2, figure 3-3 block
477, and troubleshoot NTS plunger
actuation.
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 119)
61-10-00
2-134
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 120)
61-10-00
2-135
TO 1C-130H-2-61FI-00-1
385
FROM SHT 105
381
YES
Is propeller No. 2 being troubleshot?
NO
Repair open circuit between terminal 1 of
ENG NO. 1 FEATHER VALVE AND NTS
CHECK light (1) and terminal 1 of ENG NO.
2 FEATHER VALVE AND NTS CHECK light
(2). (See figure 2-8.)
386
382
Press to test ENG NO. 2 FEATHER
VALVE AND NTS CHECK light (2).
Does light press to test?
NO
YES
Repair open circuit between terminal 1 of
ENG NO. 1 FEATHER VALVE AND NTS
CHECK light (1) and terminal 1 of ENG NO.
2 FEATHER VALVE AND NTS CHECK light
(2). (See figure 2-8.)
387
383
YES
Is propeller No. 3 being troubleshot?
NO
Repair open circuit between terminal 1 of
ENG NO. 2 FEATHER VALVE AND NTS
CHECK light (2) and terminal 1 of ENG NO.
3 FEATHER VALVE AND NTS CHECK light
(3). (See figure 2-8.)
388
384
Press to test ENG NO. 3 FEATHER
VALVE AND NTS CHECK light (3).
Does light press to test.
YES
NO
Repair open circuit between terminal 1 of
ENG NO. 2 FEATHER VALVE AND NTS
CHECK light (2) and terminal 1 of ENG NO.
3 FEATHER VALVE AND NTS CHECK light
(3). (See figure 2-8.)
389
Repair open circuit between terminal 1 of
ENG NO. 3 FEATHER VALVE AND NTS
CHECK light (3) and terminal 1 of ENG NO.
4 FEATHER VALVE AND NTS CHECK light
(4). (See figure 2-8.)
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
Figure 2-4. Propeller Assembly Malfunction (Sheet 121)
61-10-00
2-136
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 122)
61-10-00
2-137
TO 1C-130H-2-61FI-00-1
FROM SHT 11
390
Gain access to terminals of NTS
check relay (1).
Is 28 VDC present on relay terminal A1?
54
,
24
,
61
OR
392
YES
Repair ground circuit to relay
terminal A1. (See figure 2-8 or
2-10.)
YES
393
31
NO
391
Is 28 VDC present on relay terminal A2?
52
,
22
,
59
OR
Replace NTS check relay.
29
NO
394
Repair open circuit between terminals 4 and 6 of FEATHER
VALVE AND NTS CHECK
switch (2). (See figure 2-8 or
2-10.)
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
3.
See figure 2-8 or 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 123)
61-10-00
2-138
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 124)
61-10-00
2-139
TO 1C-130H-2-61FI-00-1
FROM SHT 11
395
Gain access to terminals of NTS
check relay (1).
Is 28 VDC present between relay
terminals X2 and X1?
49
50
56
57
19
,
20
26
OR
398
YES
Is 28 VDC present on relay terminal A1?
54
,
,
24
,
61
OR
27
31
401
YES Repair ground circuit to relay
terminal A1. (See figure 2-8 or
2-10.)
NO
NO
402
Replace NTS check relay.
399
396
Is 28 VDC present on relay terminal X2?
49
,
19
,
56
OR
YES
26
Open NTS CHECK circuit breaker
(2).
Is a ground present on NTS
check relay terminal B1?
55
NO
,
25
62
,
OR
403
NO
Repair ground circuit to relay
terminal B1. (See figure 2-8 or
2-10.)
32
YES
TO SHT 129
400
397
Is No. 1 propeller being
troubleshot?
YES
NO
Gain access to terminals of engine No. 1 NTS check relay (1).
Is 28 VDC present on relay terminal X2?
YES
TO SHT 139
49
NO
TO SHT 127
TO SHT 127
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
3.
See figure 2-8 or 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 125)
61-10-00
2-140
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 126)
61-10-00
2-141
TO 1C-130H-2-61FI-00-1
FROM SHT 125
404
406
Gain access to terminals of
FEATHER VALVE AND NTS
CHECK switch (2).
Is 28 VDC present on switch terminal 3?
YES
4
Repair open circuit between
FEATHER VALVE AND NTS
CHECK switch terminal 3 and
terminal X2 of engine No. 1
NTS check relay (1). (See figure 2-8 or 2-10.)
NO
405
Is 28 VDC present on FEATHER
VALVE AND NTS CHECK switch
terminal 2?
407
YES
Replace FEATHER VALVE
AND NTS CHECK switch.
3
NO
408
Repair open circuit between
switch terminals 2 and 5. (See
figure 2-8 or 2-10.)
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
3.
See figure 2-8 or 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 127)
61-10-00
2-142
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 128)
61-10-00
2-143
TO 1C-130H-2-61FI-00-1
FROM SHT 125
409
NOTE
Put meter negative lead on relay terminal
B2.
a. Open FEATHER & AIR START circuit
breaker (4).
b. Move ENGINE CONDITION lever (6) to
FEATHER.
Is a ground present on terminal B2 of NTS
check relay (1)?
51
,
21
58
,
YES
412
Replace NTS check relay.
28
OR
NO
410
NOTE
Put meter negative lead on relay terminal
X1.
413
YES
Repair open circuit between relay terminals X1 and B2. (See
figure 2-8 or 2-10.)
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
Is a ground present on relay terminal X1?
50
,
20
57
,
27
OR
NO
411
NOTE
Put meter negative lead on receptacle pin
E.
a. Open PROP SYNCHRO PHASER and
SYNCHRO PHASER circuit breakers (7,5).
b. Gain access to and disconnect plug
P390 (2) at valve housing assembly.
Is there continuity between pins E and F of
valve housing receptacle (3)?
42
67
41
66
14
,
OR
13
39
414
,
38
YES
TO SHT 137
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
3.
See figure 2-8 or 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 129)
61-10-00
2-144
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 130)
61-10-00
2-145
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?
Prop
Plug
Pin
1
53
2
54
3
55
4
56
Test
Point
419
NO
Fault is in MACAWS. Refer
to TO 1C-130H-2-33FI-00-12 for troubleshooting.
78
79
80
81
YES
416
YES
Is an outboard propeller being troubleshot?
TO SHT 133
NO
417
420
a. Temporarily remove power from airplane.
b. Connect plug P1725A to systems caution/advisory panel.
c. Gain access to and disconnect plug P398 (2)
at engine firewall.
Is 28 VDC present at pin F?
16
Repair open circuit between
plug P398, pin F and plug
P1725A at applicable pin.
(See figure 2-9.)
NO
Prop
2
3
63
Plug pin
54
55
YES
418
a. Temporarily remove power from airplane.
b. Connect plug P398 at engine firewall.
c. Gain access to and disconnect plug P390
(3) at valve housing assembly.
Is 28 VDC present at pin F?
13
OR
421
NO
Repair open circuit between plug P390 pin F
and receptacle J239 (1). (See figure 2-9.)
66
YES
TO SHT 135
NOTE
See figure 2-9 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 131)
61-10-00
2-146
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 132)
61-10-00
2-147
TO 1C-130H-2-61FI-00-1
FROM SHT 131
422
425
a. Temporarily remove power from airplane.
b. Connect plug P1725A (4) to systems caution/advisory panel.
c. Gain access to and disconnect plug P18/
P1835 (6) at outer wing break.
Is 28 VDC present at pin N?
33
OR
NO
Repair open circuit between plug
P18/P1835, pin N and plug
P1725A at applicable pin. (See
figure 2-9.)
Prop
1
4
47
Plug pin
53
56
YES
423
a. Temporarily remove power from airplane.
b. Connect plug P18/P1835.
c. Gain access to and disconnect plug P398
(2) at engine firewall.
Is 28 VDC present at pin F?
35
OR
426
NO
Repair open circuit between receptacle J233/J956 (5) pin N, and plug
P398 (2) pin F. (See figure 2-9.)
44
YES
424
a. Temporarily remove power from airplane.
b. Connect plug P398.
c. Gain access to and disconnect plug P390
(3) at valve housing assembly.
Is 28 VDC present at pin F?
38
OR
427
NO
Repair open circuit between receptacle J239 (1) pin F, and plug
P390 pin F. (See figure 2-9.)
41
YES
TO SHT 135
NOTE
See figure 2-9 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 133)
61-10-00
2-148
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 134)
61-10-00
2-149
TO 1C-130H-2-61FI-00-1
FROM SHT 131 OR 133
428
Gain access to valve housing receptacle (4).
Is there continuity between pins F
and K?
13
41
15
43
38
,
, OR
40
66
430
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
NO
Repair open circuit between
plug P398 pin V and ground.
(See figure 2-9.)
,
68
YES
429
Gain access to and disconnect
plug P398 (2) at engine firewall.
Is a ground present at plug P398
pin V?
18
,
37
,
46
OR
431
65
YES
432
Repair open circuit between receptacle J239 (1) pin V and
plug P390 (3) pin K. (See figure 2-9.)
NOTE
See figure 2-9 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 135)
61-10-00
2-150
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 136)
61-10-00
2-151
TO 1C-130H-2-61FI-00-1
FROM SHT 129
433
NOTE
Put meter negative lead on receptacle pin E.
a. Connect plug P390 (3) to valve
housing assembly (4).
b. Gain access to and disconnect
plug P398 (2) at engine firewall.
Is there continuity between pins E
and F of receptacle J239 (1)?
45
64
44
63
17
,
OR
36
16
436
NO
Repair open circuit between receptacle J239 pin E and plug
P390 pin E. (See figure 2-8 or
2-10.)
,
35
YES
437
434
Is an outboard propeller being
troubleshot?
NO
YES
Repair open circuit between
plug P398 pin E and terminal
X1 of NTS check relay (5).
(See figure 2-8 or 2-10.)
435
NOTE
Put meter negative lead on receptacle pin P.
a. Connect plug P398 at engine
firewall.
b. Gain access to and disconnect
plug P18 (6) at outer wing break.
Is there continuity between pins N
and P of receptacle J233 (7)?
47
48
OR
33
438
NO
Repair open circuit between receptacle J233 pin P and plug
P398 pin E. (See figure 2-8 or
2-10.)
34
YES
439
Repair open circuit between
plug P18 pin P and terminal X1
of NTS check relay (5). (See
figure 2-8 or 2-10.)
NOTE
See figure 2-8 or 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 137)
61-10-00
2-152
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 138)
61-10-00
2-153
TO 1C-130H-2-61FI-00-1
444
FROM SHT 125
440
YES
Is No. 2 propeller being
troubleshot?
NO
441
Repair open circuit between terminal X2 of engine No. 1 NTS
check relay (2) and terminal X2
of engine No. 2 NTS check relay (3). (See figure 2-8 or 210.)
445
Gain access to terminals of engine No. 2 NTS check relay (3).
Is 28 VDC present on relay terminal X2?
NO
19
Repair open circuit between terminal X2 of engine No. 1 NTS
check relay (2) and terminal X2
of engine No. 2 NTS check relay (3). (See figure 2-8 or 210.)
YES
446
442
YES
Is No. 3 propeller being
troubleshot?
NO
443
Repair open circuit between terminal X2 of engine No. 2 NTS
check relay (3) and terminal X2
of engine No. 3 NTS check relay (1). (See figure 2-8 or 210.)
447
Gain access to terminals of engine No. 3 NTS check relay (1).
Is 28 VDC present on relay terminal X2?
56
NO
Repair open circuit between terminal X2 of engine No. 2 NTS
check relay (3) and terminal X2
of engine No. 3 NTS check relay (1). (See figure 2-8 or 210.)
YES
448
Repair open circuit between terminal X2 of engine No. 3 NTS
check relay (1) and terminal X2
of engine No. 4 NTS check relay (4). (See figure 2-8 or 210.)
NOTE
See figure 2-8 or 2-10 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 139)
61-10-00
2-154
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 140)
61-10-00
2-155
TO 1C-130H-2-61FI-00-1
FROM SHT 9 OR 11
449
Momentarily hold engine condition
lever (3) in AIR START.
Does auxiliary pump motor (2) run
while lever is held?
NO
TO SHT 143
YES
450
Inspect NTS linkage (1) for serviceability and check for correct gap of
0.011 to 0.020 inch in accordance
with TO 1C-130H-2-61JG-20-1, 6120-22.
Is NTS linkage satisfactory?
452
NO
Adjust NTS linkage in accordance
with TO 1C-130H-2-61JG-20-1, 61-2022, or replace components as required.
YES
451
453
Check engine coordinator-to-propeller
control assembly rigging in accordance with TO 1C-130H-2-61JG-201, 61-20-21.
Is rigging correct?
NO
Rig engine coordinator-to-propeller
control assembly linkage in accordance with TO 1C-130H-2-61JG-20-1,
61-20-21.
YES
454
Reseal pitchlock regulator assembly in
accordance with TO 1C-130H-2-61JG10-1, 61-10-11; reseal low pitch stop
assembly in accordance with TO 1C130H-2-61JG-10-1, 61-10-12; and
reseal dome assembly in accordance
with TO 1C-130H-2-61JG-10-1, 61-1013. If fault persists, replace feather
solenoid valve in accordance with TO
1C-130H-2-61JG-20-1, 61-20-06. If
fault still persists, replace valve housing assembly in accordance with TO
1C-130H-2-61JG-20-1, 61-20-02.
Figure 2-4. Propeller Assembly Malfunction (Sheet 141)
61-10-00
2-156
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 142)
61-10-00
2-157
TO 1C-130H-2-61FI-00-1
FROM SHT 141
455
a. Gain access to terminals of
feather relay (2).
b. Momentarily hold ENGINE
CONDITION lever (1) in AIR
START.
Is 28 VDC present on relay terminal B2 while lever is held?
YES
457
Replace feather relay.
32
NO
456
a. Gain access to pedestal terminal boards.
b. Momentarily hold ENGINE
CONDITION lever in AIR START.
Is 28 VDC present on specified
terminal while lever is held?
Test
Point
Prop TB-Term
1
TB126A (3) -31
2
TB146A (4) -208
3
TB146A (4) -209
4
TB146A (4) -212
34
34
458
YES
Repair open circuit between
feather relay terminal B2 and
related terminal. (See figure 211.)
Prop
1
2
3
4
34
34
NO
TO SHT 145
NOTE
See figure 2-11 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 143)
61-10-00
2-158
TB-Term
TB126A-31
TB146A-208
TB146A-209
TB146A-212
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 144)
61-10-00
2-159
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 ENGINE CONDITION lever air start switch (1)
and specified terminal?
461
Test
Points
Prop Sw
TB-Term
1
S23S
TB146A (3) -193
2
S23T
TB146A (3) -194
3
S23U
TB146A (3) -195
4
S23V
TB146A (3) -196
NO
37
38
37
38
37
38
37
38
Repair open circuit. (See figure
2-11.)
YES
460
Is there continuity between air start switch terminal 1NO and specified terminal?
462
Test
Points
Prop Sw
TB-Term
1
S23S
TB126A (2) -31
2
S23T
TB146A (3) -208
3
S23U
TB146A (3) -209
4
S23V
TB146A (3) -212
36
34
36
34
36
34
36
34
YES
Adjust or replace air start switch
as required in accordance with
TO 1C-130H-2-76JG-00-1, 7610-39.
Prop
1
2
3
4
Sw
S23S
S23T
S23U
S23V
NO
463
Repair open circuit. (See figure
2-11.)
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
3.
See figure 2-11 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 145)
61-10-00
2-160
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 146)
61-10-00
2-161
TO 1C-130H-2-61FI-00-1
FROM SHT 13
464
Check NTS linkage (1) for correct
gap of 0.011 to 0.020 inch in accordance with TO 1C-130H-261JG-20-1, 61-20-22.
Is adjustment correct?
466
NO
Adjust NTS linkage in accordance with TO 1C-130H-261JG-20-1, 61-20-22.
YES
467
465
Inspect NTS linkage through valve
housing assembly cover (2) for
evidence of binding.
Is any binding observed?
YES
Repair or replace linkage as required or replace valve housing
assembly cover as required in
accordance with TO 1C-130H2-61JG-20-1, 61-20-02.
NO
468
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
Figure 2-4. Propeller Assembly Malfunction (Sheet 147)
61-10-00
2-162
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 148)
61-10-00
2-163
TO 1C-130H-2-61FI-00-1
FROM SHT 13
469
Did propeller feather override button (3) pull in?
YES
TO SHT 153
NO
470
Temporarily remove power from
airplane and gain access to terminals of propeller feather override
button.
Is 28 VDC present on button terminal 1?
472
YES
Repair open circuit between
button terminal 1 and terminal
A2 of feather relay (2). (See
figure 2-11 or 2-12.)
26
NO
471
Gain access to terminal board
TB14A (1).
Is 28 VDC present on specified
terminal?
Prop
1
Test
Point
TB-Term
44
3
45
4
46
YES
44
43
2
473
44
44
Repair open circuit between
propeller feather override button
terminal 1 and related terminal
board TB14A terminal. (See figure 2-11 or 2-12.)
Prop
1
2
3
4
44
NO
TO SHT 151
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.
5.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 149)
61-10-00
2-164
TB-Term
43
44
45
46
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 150)
61-10-00
2-165
TO 1C-130H-2-61FI-00-1
477
FROM SHT 149
474
Temporarily remove power from airplane
and gain access to terminals of fire emergency handle switch (3).
Is 28 VDC present on switch terminal H1?
YES
Repair open circuit between switch terminal H1 and related terminal of terminal
board TB14A (4). (See figure 2-11 or 212.)
Prop
1
2
3
4
43
NO
TB-Term
43
44
45
46
475
Is 28 VDC present on switch terminal G1?
YES
478
Replace fire emergency handle switch.
42
NO
476
Gain access to and disconnect plug P350/
P1830 (1) at overhead panel disconnect.
Is 28 VDC present on specified pin of receptacle J217/J952 (2)?
Prop
Rcpt
Pin
1
S
2
T
3
U
4
V
Test
Point
41
41
41
479
Repair open circuit between fire emergency handle switch terminal G1 and related plug P350/P1830 pin. (See figure
2-11 or 2-12.)
YES
Prop
1
2
3
4
Plug
Pin
S
T
U
V
41
NO
480
Repair power circuit. (See figure 2-11 or
2-12.)
NOTE
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 151)
61-10-00
2-166
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 152)
61-10-00
2-167
TO 1C-130H-2-61FI-00-1
FROM SHT 149
481
Gain access to and disconnect
plug P391 (3) at feather solenoid
valve.
Is 28 VDC present between plug
pins A and B?
19
485
YES
Replace feather solenoid valve
in accordance with TO 1C130H-2-61JG-20-1, 61-20-06.
18
NO
484
482
Is 28 VDC present on plug pin A?
YES
19
NO
a. Open EMER FEATHER circuit
breaker (4).
b. Gain access to and disconnect
plug P399 (2) at engine firewall.
Is a ground present on plug pin
B?
486
YES Repair open circuit between
plug P391 pin B and pin B of
receptacle J245 (1). (See figure 2-11 or 2-12.)
20
NO
487
Repair ground circuit. (See figure 2-11 or 2-12.)
483
488
Gain access to and disconnect
plug P399 (2) at engine firewall.
Is 28 VDC present on plug pin A?
YES
Repair open circuit between
plug P391 pin A and pin A of
receptacle J245 (1). (See figure 2-11 or 2-12.)
21
NO
TO SHT 155
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
3.
See figure 2-11 or 2-12 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 153)
61-10-00
2-168
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 154)
61-10-00
2-169
TO 1C-130H-2-61FI-00-1
FROM SHT 153
491
489
Is airplane being troubleshot a C130B model through AF59-5957?
NO
YES
Repair open circuit between pin
A of plug P399 (1) and terminal
14 of propeller feather override
button (3). (See figure 2-11 or
2-12.)
490
Gain access to terminal board
TB115L (2).
Is 28 VDC present on specified terminal?
Prop TB-Term
1
1
2
2
3
3
4
4
Test
Point
45
45
45
45
492
Repair open circuit between pin
A of plug P399 (1) and related
terminal board TB115L terminal.
(See figure 2-11.)
YES
OR
OR
OR
OR
46
46
46
Prop
1
2
3
4
TB-Term
1
2
3
4
46
NO
493
Repair open circuit between terminal 14 of PROPELLER
FEATHER OVERRIDE button
(3) and related terminal board
TB115L terminal. (See figure
2-11.)
Prop
1
2
3
4
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.
5.
See figure 2-11 for:
Figure 2-4. Propeller Assembly Malfunction (Sheet 155)
61-10-00
2-170
TB-Term
1
2
3
4
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 156)
61-10-00
2-171
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 157)
61-10-00
2-172
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 158)
61-10-00
2-173
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 159)
61-10-00
2-174
Change 5
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 160)
61-10-00
2-175
TO 1C-130H-2-61FI-00-1
FROM SHT 19
511
6110006
a. Shut down engines (1) in accordance with TO 1C-130H-271JG-00-1, 71-00-10; or TO 1C130(A)H-2-71JG-00-1, 71-00-10.
b. Check throttle control system
rigging in accordance with TO 1C130H-2-76JG-00-1, 76-10-01.
Is rigging correct?
515
NO
Rig throttle control system in
accordance with TO 1C-130H2-76JG-00-1, 76-10-30, 76-1033, 76-10-34, and 76-10-35.
YES
512
516
Check engine coordinator-to-propeller control assembly rigging in
accordance with TO 1C-130H-261JG-20-1, 61-20-21.
Is rigging correct?
NO
Rig engine coordinator-to-propeller control assembly linkage
in accordance with TO 1C130H-2-61JG-20-1, 61-20-21.
YES
513
517
Perform backup valve blade angle
indicator check and reverse stop
check in accordance with TO 1C130H-2-61JG-10-1, 61-10-01
(subtasks 1-1-3 and 1-1-5).
Are checks satisfactory?
NO
Adjust backup valve blade angle and/or reverse stop as required in accordance with TO
1C-130H-2-61JG-10-1, 61-1001.
YES
514
518
Perform torquemeter calibration in
accordance with TO 1C-130H-277JG-00-1, 77-10-04; or TO 1C130(A)H-2-71JG-00-1, 71-00-10.
Is calibration satisfactory?
NO
Fault is in engine or torquemeter system. Go to TO 1C130H-2-70FI-00-1-2 and continue troubleshooting.
YES
519
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
Figure 2-4. Propeller Assembly Malfunction (Sheet 161)
61-10-00
2-176
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 162)
61-10-00
2-177
TO 1C-130H-2-61FI-00-1
FROM SHT 19
520
Did RPM increase to 103.5 percent or above and hold when fuel
governing switch (1) was held in
CHECK during pitchlock check?
YES
TO SHT 165
NO
525
523
521
Did RPM increase at all when fuel
governing switch was held in
CHECK during pitchlock check?
NO
YES
Perform propeller synchrophaser
check in accordance with TO 1C130H-2-61JG-10-1, 61-10-02
(subtask 1-2-9).
Is synchrophaser check satisfactory?
NO
YES
524
Fault is in synchrophaser system. Shut down engines in accordance with TO 1C-130H-271JG-00-1, 71-00-10; TO 1C130(A)H-2-71JG-00-1, 71-0010; or TO 1C-130(M)H-2-71JG00-1, 71-00-10; then go to Section III and continue troubleshooting.
526
a. Perform synchrophaser index in
accordance with TO 1C-130H-261JG-10-1, 61-10-02 (subtask 12-6).
b. Perform pitchlock check of affected propeller in accordance
with TO 1C-130H-2-61JG-10-1,
61-10-02 (subtask 1-2-10).
Was a pitchlock obtained?
NO
Fault is in synchrophaser system. Shut down engines in accordance with TO 1C-130H-271JG-00-1, 71-00-10; TO 1C130(A)H-2-71JG-00-1, 71-0010; or TO 1C-130(M)H-2-71JG00-1, 71-00-10; then go to Section III and continue troubleshooting.
YES
527
Synchrophaser index corrected malfunction. 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, 71-0010.
522
528
Was RPM increase within limits
when fuel governing switch was
held in CHECK during pitchlock
check?
NO
Adjust fuel control governor in accordance with TO 1C-130H-2-73JG-00-1,
73-20-20.
YES
TO SHT 165
NOTE
1
MC-130H airplanes.
Figure 2-4. Propeller Assembly Malfunction (Sheet 163)
61-10-00
2-178
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 164)
61-10-00
2-179
TO 1C-130H-2-61FI-00-1
FROM SHT 163
529
Remove dome assembly in accordance with TO 1C-130H-2-61JG10-1, 61-10-11.
Is pin on ratchet ring (1) aligned
with etch mark on lip of No. 2
blade barrel bore (2)?
530
NO
Remove and reinstall pitchlock
regulator assembly correctly in
accordance with TO 1C-130H2-61JG-10-1, 61-10-11.
YES
531
Reseal or replace pitchlock regulator assembly in accordance
with TO 1C-130H-61JG-10-1,
61-10-11, as required. If fault
persists, replace propeller assembly in accordance with TO
1C-130H-2-61JG-10-1, 61-1011.
Figure 2-4. Propeller Assembly Malfunction (Sheet 165)
61-10-00
2-180
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 166)
61-10-00
2-181
TO 1C-130H-2-61FI-00-1
FROM SHT 21
532
6110003
a. Shut down engines in accordance with TO 1C-130H-2-71JG00-1, 71-00-10; TO 1C-130(A)H2-71JG-00-1, 71-00-10; or TO 1C130(M)H-2-71JG-00-1, 71-00-10.
b. Move engine condition lever (2)
to FEATHER/FTR.
c. After propeller blades (1) have
reached feather position, check
for internal leakage by holding
propeller feather override button
(3) in while listening for a loud
squeal from respective propeller
assembly.
Is a loud squeal heard from propeller?
534
NO
Reseal pitchlock regulator assembly in accordance with TO
1C-130H-2-61JG-10-1, 61-1011; reseal low pitch stop assembly in accordance with TO
1C-130H-2-61JG-10-1, 61-1012; and reseal dome assembly
in accordance with TO 1C130H-2-61JG-10-1, 61-10-13.
YES
533
535
Check engine coordinator-to-propeller control assembly rigging in
accordance with TO 1C-130H-261JG-20-1, 61-20-21.
Is rigging correct?
NO
Rig engine coordinator-to-propeller control assembly linkage
in accordance with TO 1C130H-2-61JG-20-1, 61-20-21.
YES
536
Replace low pitch stop assembly in accordance with TO 1C130H-2-61JG-10-1, 61-10-12.
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 167)
61-10-00
2-182
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 168)
61-10-00
2-183
TO 1C-130H-2-61FI-00-1
FROM SHT 21
537
6110001
Perform inspection for loose propeller
blades in accordance with TO 1C130H-2-61JG-10-1, 61-10-22.
Are any loose blades found?
543
YES
Replace propeller assembly in accordance with TO 1C-130H-261JG-10-1, 61-10-11.
NO
538
544
Perform inspection of propeller blade
tracking in accordance with TO 1C130H-2-61JG-10-1, 61-10-23.
Is tracking satisfactory?
NO
Replace propeller assembly in accordance with TO 1C-130H-261JG-10-1, 61-10-11.
YES
539
545
Inspect propeller afterbody (2), prop
torque retainer assembly (4), and
front spinner (1) for loose or damaged components.
Are any discrepancies found?
Repair or replace loose or damaged propeller components as required in accordance with TO 1C130H-2-61JG-10-1 or TO 1C130H-2-61JG-20-1.
YES
NO
546
540
Check propeller hub nut (5) for correct torque in accordance with TO
1C-130H-2-61JG-10-1, 61-10-11.
Is torque correct?
NO
542
Was torque at least 1500
inch-pounds?
YES
NO
Replace reduction gear in accordance with TO 1C-130H-2-71JG00-2, 71-90-20. Annotate forms
that propeller shaft (3) is to be removed from service.
YES
547
Torque propeller hub nut in accordance with TO 1C-130H-2-61JG10-1, 61-10-11.
541
548
Check condition of engine rear
mounts in accordance with TO 1C130H-2-71JG-00-2, 71-20-10.
Are any discrepancies found?
YES
Replace engine mounts in accordance with TO 1C-130H-2-71JG00-2, 71-20-20.
NO
TO SHT 171
Figure 2-4. Propeller Assembly Malfunction (Sheet 169)
61-10-00
2-184
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 170)
61-10-00
2-185
TO 1C-130H-2-61FI-00-1
FROM SHT 169
549
Inspect engine condition control
system for loose, worn, or broken
components in accordance with
TO 1C-130H-2-76JG-00-1, 76-1003, 76-10-11, and 76-10-12; or
TO 2J-T56-56, as required.
Are any discrepancies found?
553
YES
Repair or replace engine condition control system components
as required.
NO
550
Inspect throttle control system for
loose, worn, or broken components in accordance with TO 1C130H-2-76JG-00-1, 76-10-01, 7610-02, 76-10-10, and 76-10-12; or
TO 2J-T56-56, as required.
Are any discrepancies found?
554
YES
Repair or replace throttle control system components as required.
NO
551
555
Check propeller balance in accordance with TO 1C-130H-2-61JG10-1, 61-10-41.
Is propeller (2) out of balance?
YES
Balance propeller in accordance
with TO 1C-130H-2-61JG-10-1,
61-10-41.
NO
552
Gain access to and check propeller shaft (1) for excessive vertical
movement and end play in accordance with TO 2J-T56-56.
Are measurements within limits?
556
YES
Replace propeller assembly in
accordance with TO 1C-130H2-61JG-10-1, 61-10-11.
NO
557
As required, repair reduction
gear in accordance with TO 2JT56-56 or replace reduction
gear in accordance with TO 1C130H-2-71JG-00-2, 71-90-20.
Figure 2-4. Propeller Assembly Malfunction (Sheet 171)
61-10-00
2-186
TO 1C-130H-2-61FI-00-1
Figure 2-4. Propeller Assembly Malfunction (Sheet 172)
61-10-00
2-187
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 1 of 62)
61-10-00
2-188
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 2)
61-10-00
2-189
TO 1C-130H-2-61FI-00-1
11
Check diode CR3 (2) associated with PROPELLER LOW OIL
WARNING/PROP light (1) that
is on and replace if defective.
(See figure 2-13 or 2-14.) Then
continue troubleshooting with
sheet 11.
FROM SHT 1
10
Check affected propeller assemblies for correct fluid level in accordance with TO 1C-130H-212JG-10-2, 12-16-03.
Is fluid level in one propeller assembly low?
NO
1
3
Prop Diode
1
CR3AX
2
CR3AY
YES
4
Prop Diode
3
CR3AZ
4
CR3BA
2
Prop Diode
1
CR3FX
2
CR3FY
Prop Diode
3
CR3FZ
4
CR3GA
12
Replace diode CR3 (2) associated with PROPELLER LOW
OIL WARNING light (1) that is
on but whose propeller assembly does not require servicing.
(See figure 2-13 or 2-14.) Then
continue troubleshooting with
sheet 5.
1
3
Prop Diode
1
CR3AX
2
CR3AY
4
Prop Diode
3
CR3AZ
4
CR3BA
2
Prop Diode
1
CR3FX
2
CR3FY
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 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 3)
61-10-00
2-190
Prop Diode
3
CR3FZ
4
CR3GA
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 4)
61-10-00
2-191
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 5)
61-10-00
2-192
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 6)
61-10-00
2-193
TO 1C-130H-2-61FI-00-1
FROM SHT 1
22
6110032
Momentarily hold the MACAWS
LAMP TEST switch (4) in the test
position.
Does the applicable PROP light
(1) come on?
25
NO
Replace the faulty lamp in the
systems caution/advisory panel.
YES
23
Gain access to related diode CR3
(2).
Is voltage present on terminal ( )
of diode CR3?
Test
Point
Prop
Diode
1
CR3FX
2
CR3FY
3
CR3FZ
4
CR3GA
YES
TO SHT 41
14
16
18
20
NO
24
Is voltage present on terminal ( )
of diode CR3 (3)?
Prop
Test
Point
Diode
1
CR3GB
2
CR3GC
3
CR3GD
4
CR3GE
78
26
YES
Repair open circuit between diodes. (See figure 2-14.)
79
80
81
NO
TO SHT 9
NOTE
See figure 2-14 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 7)
61-10-00
2-194
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 8)
61-10-00
2-195
TO 1C-130H-2-61FI-00-1
FROM SHT 7
27
Is voltage present on cathode of diode CR3 (2)?
Prop
Diode
1
CR3GB
2
CR3GC
3
CR3GD
4
CR3GE
Test
Point
YES
74
29
Replace diode CR3. (See figure 2-14.)
75
76
77
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?
Prop
Pin
1
5
9
2
6
10
3
7
11
4
8
12
1
Pin
2
Test
Point
70
30
NO
Fault is in MACAWS. Refer to TO 1C130H-2-33FI-00-1-2 for troubleshooting.
71
72
73
YES
31
Repair open circuit between applicable plug
P1725A and related diode CR3 (2). (See
figure 2-14.)
Plug
Pin
5
6
Diode
CR3GB
CR3GC
Plug
Pin
7
8
NOTE
1
C-130H airplanes.
2
LC-130H and HC-130(H)N airplanes.
3.
See figure 2-14 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 9)
61-10-00
2-196
Diode
CR3GD
CR3GE
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 10)
61-10-00
2-197
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 11)
61-10-00
2-198
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 12)
61-10-00
2-199
TO 1C-130H-2-61FI-00-1
FROM SHT 11
40
Inspect wiring to propeller control
receptacle (2) (for plug P392) for
loose and broken connections.
Is any damage found?
42
YES
Repair loose or damaged wiring
as required. (See figure 2-13.)
NO
41
Gain access to oil level indicator
switch (1) and disconnect wires
from switch.
Is a ground present on disconnected wires?
40
32
41
33
,
OR
38
26
39
,
43
YES
Repair ground fault between
propeller control receptacle and
oil level indicator switch. (See
figure 2-13.)
27
NO
44
Replace oil level indicator
switch in accordance with TO
1C-130H-2-61JG-20-1, 61-2008.
NOTE
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 13)
61-10-00
2-200
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 14)
61-10-00
2-201
TO 1C-130H-2-61FI-00-1
FROM SHT 11
45
Gain access to and disconnect applicable wire
from diode CR3 (2).
Is a ground present on disconnected wire?
Wire
No.
Prop
Diode
1
CR3AX
CR3FX
1E600D
2
CR3AY
CR3FY
2E600C
3
CR3AZ
CR3FZ
3E600C
4
CR3BA
CR3GA
4E600D
1
Diode
2
49
Test
Point
47
YES
Is an outboard propeller
being troubleshot?
14
Repair ground fault between pin D of plug P396
(1) and related diode
CR3. (See figure 2-13 or
2-14.)
NO
YES
16
1
18
2
Prop
2
3
2
3
Diode
CR3AY
CR3AZ
CR3FY
CR3FZ
20
NO
48
Gain access to and disconnect
plug P130/P1139 (4) at outer
wing break.
Is a ground present on plug pin
N?
46
OR
50
NO
Repair ground fault between pin
N of receptacle J235/J935 (3)
and pin D of plug P396 (1).
(See figure 2-13 or 2-14.)
21
YES
51
Repair ground fault between
plug P130/P1139 pin N and related diode CR3. (See figure 213 or 2-14.)
1
2
46
YES
Is airplane serial number AF92-0547 through AF92-2104 or AF92-3281 and up?
Prop
1
4
1
4
TO SHT 19
NO
TO SHT 17
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 2-13 or 2-14 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 15)
61-10-00
2-202
Diode
CR3AX
CR3BA
CR3FX
CR3GA
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 16)
61-10-00
2-203
TO 1C-130H-2-61FI-00-1
FROM SHT 15
52
YES
Is airplane an MC-130H?
TO SHT 21
NO
53
Remove diode CR3 (2) associated with propeller position.
Is a ground present on diode bus
bar?
Test
Point
Prop
Diode
1
CR3AX
2
CR3AY
3
CR3AZ
4
13
56
54
YES
Gain access to terminals of indicator lights dimmer No. 7 (3)
and disconnect wire from dimmer terminal e.
Is a ground present on disconnected wire?
15
Repair ground fault between dimmer terminal e and diode CR3AX
(2), then replace specified diode
YES CR3 associated with PROPELLER
LOW OIL WARNING light (1) that
is on. (See figure 2-13.)
Prop
1
2
10
17
Diode
CR3AX
CR3AY
Prop
3
4
Diode
CR3AZ
CR3BA
NO
19
CR3BA
NO
TO SHT 27
57
55
Disconnect wire from dimmer
terminal E.
Is a ground present on disconnected wire?
9
YES
NO
Replace indicator lights dimmer
No. 7, then replace specified diode
CR3 associated with PROPELLER
LOW OIL WARNING light (1) that
is on. (See figure 2-13.)
Prop
1
2
Diode
CR3AX
CR3AY
TO SHT 29
NOTE
1
2.
MC-130E airplane.
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 17)
61-10-00
2-204
Prop
3
4
Diode
CR3AZ
CR3BA
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 18)
61-10-00
2-205
TO 1C-130H-2-61FI-00-1
FROM SHT 15
58
Remove diode CR3 (3) associated with propeller position.
Is a ground present on diode bus
bar?
Test
Point
Prop
Diode
1
CR3FX
2
CR3FY
3
CR3FZ
4
CR3GA
60
Replace diode CR3 (3) associated with PROP light (2) that is
on. (See figure 2-14.)
YES
Prop
1
2
3
4
13
15
17
Diode
CR3FX
CR3FY
CR3FZ
CR3GA
19
NO
59
Remove wire from anode of applicable diode CR3 (4).
Is a ground present on disconnected wire?
Prop
Test
Point
Diode
1
CR3GB
2
CR3GC
3
CR3GD
4
CR3GE
78
79
61
Repair ground fault between diodes (3,4). (See figure 2-14.)
YES
Prop
1
2
3
4
Diode
CR3FX
CR3FY
CR3FZ
CR3GA
Diode
CR3GB
CR3GC
CR3GD
CR3GE
80
81
NO
62
Repair ground fault between
plug P1725A (1) pin and related
diode CR3 (4). (See figure 214.)
Plug
Pin
5
6
7
8
NOTE
See figure 2-14 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 19)
61-10-00
2-206
Diode
CR3GB
CR3GC
CR3GD
CR3GE
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 20)
61-10-00
2-207
TO 1C-130H-2-61FI-00-1
FROM SHT 17
63
Remove diode CR3 (1) associated with propeller position.
Is a ground present on diode bus bar?
Prop
Diode
1
CR3AX
2
CR3AY
3
CR3AZ
4
CR3BA
Test Point
13
NO
TO SHT 23
15
17
19
YES
66
64
Gain access to disconnect plugs 47407A1P1
and 47407A2P1 from indicator light dimmer
No. 7 (2).
Is a ground present on pin 16 of plug
47407A2P1?
YES
Repair ground fault between pin 16 of
plug 47407A2P1 and diode CR3AX, then
replace specified diode CR3 associated
with PROPELLER LOW OIL WARNING
light (3) that is on. (See figure 2-13.)
Prop
1
2
86
NO
Diode
CR3AX
CR3AY
Prop
3
4
Diode
CR3AZ
CR3BA
67
65
Is a ground present on pin 24 of plug
47407A2P1?
NO
Replace indicator light dimmer No. 7,
then replace specified diode CR3 associated with PROPELLER LOW OIL WARNING light (3) that is on. (See figure 213.)
82
YES
Prop
1
2
Diode
CR3AX
CR3AY
Prop
3
4
TO SHT 25
NOTE
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 21)
61-10-00
2-208
Diode
CR3AZ
CR3BA
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 22)
61-10-00
2-209
TO 1C-130H-2-61FI-00-1
FROM SHT 21
68
70
Is ground present on specified pin of plug
47407A1P1 and 40407A2P1 of indicator
light dimmer No. 7 (2)?
Prop
Pin
Test Point
1
47407A1P1-10
2
47407A1P1-24
3
47407A1P1-23
4
47407A2P1-10
102
YES
Repair ground fault between terminal 2
of PROPELLER LOW OIL WARNING
light (3) and applicable pin of plug
47407A1P1 or 47407A2P1 of indicator
light dimmer No. 7. (See figure 2-13.)
Prop
1
2
3
4
101
99
83
Pin
47407A1P1-10
47407A1P1-24
47407A1P1-23
47407A2P1-10
NO
69
Is ground present on specified pin of plug
47407A1P1 and 40407A2P1 of indicator
light dimmer No. 7?
Prop
Pin
1
47407A1P1-4
71
Test Point
91
2
47407A1P1-16
3
47407A1P1-15
4
47407A2P1-4
93
95
YES
Repair ground fault between diode CR3
(1) and applicable pin of plug
47407A1P1 or 47407A2P1 of indicator
light dimmer No. 7. (See figure 2-13.)
Prop
1
2
3
5
Diode
CR3AX
CR3AY
CR3AZ
CR3BA
Pin
47407A1P1-4
47407A1P1-16
47407A1P1-15
47407A2P1-4
87
NO
72
Replace indicator light dimmer No. 7.
NOTE
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 23)
61-10-00
2-210
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 24)
61-10-00
2-211
TO 1C-130H-2-61FI-00-1
FROM SHT 21
75
73
Gain access to terminals of PROP
LOW OIL QUANTITY master warning
light (3) and disconnect wire from
light terminal 2.
Is a ground present on disconnected
wire?
NO
Repair PROP LOW OIL QUANTITY
master warning light, then replace specified diode CR3 (6) associated with PROPELLER LOW OIL WARNING light (4)
that is on. (See figure 2-13.)
Prop
1
2
49
Diode
CR3AX
CR3AY
Prop
3
4
Diode
CR3AZ
CR3BA
YES
76
74
Gain access to and disconnect plugs
P251 (2) at main instrument panel
disconnect.
Is there a ground present on pin C?
50
NO
YES
Repair ground fault between plug P251,
pin C and PROP LOW OIL QUANTITY
master warning light terminal 2, then replace specified diode CR3 (6) associated
with PROPELLER LOW OIL WARNING
light (4) that is on. (See figure 2-13.)
Prop
1
2
Diode
CR3AX
CR3AY
Prop
3
4
Diode
CR3AZ
CR3BA
77
Repair ground fault between pin 24 of
plug 47407A2P1 of indicator light dimmer
No. 7 (5) and pin C of receptacle J129
(1), then replace specified diode CR3 (6)
associated with PROPELLER LOW OIL
WARNING light (4) that is on. (See figure 2-13.)
Prop
1
2
Diode
CR3AX
CR3AY
Prop
3
4
NOTE
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 25)
61-10-00
2-212
Diode
CR3AZ
CR3BA
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 26)
61-10-00
2-213
TO 1C-130H-2-61FI-00-1
FROM SHT 17
78
Gain access to terminals of indicator lights dimmer No. 7 (3) and
disconnect wire from specified
dimmer terminal.
Is a ground present on disconnected wire?
Prop
Dim
Term
1
A
2
B
3
C
4
D
Test
Point
80
YES
7
Repair ground fault between
terminal 2 of PROPELLER
LOW OIL WARNING light (1)
and related dimmer terminal.
(See figure 2-13.)
Dim
Term
A
B
C
D
Prop
1
2
3
4
5
3
1
NO
79
Disconnect wire from specified
dimmer terminal.
Is a ground present on disconnected wire?
Prop
Dim
Term
1
a
2
b
3
c
4
d
Test
Point
8
6
4
81
Repair ground fault between diode CR3 (2) and related dimmer terminal. (See figure 2-13.)
YES
Prop
1
2
3
4
Diode
CR3AX
CR3AY
CR3AZ
CR3BA
Dim
Term
a
b
c
d
2
NO
82
Replace indicator lights dimmer
No. 7. (See figure 2-13.)
NOTE
1
MC-130E airplanes.
2.
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 27)
61-10-00
2-214
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 28)
61-10-00
2-215
TO 1C-130H-2-61FI-00-1
FROM SHT 17
85
83
Gain access to terminals of PROP
LOW OIL QUANTITY master
warning light (2) and disconnect
wire from light terminal 2.
Is a ground present on disconnected wire?
NO
Replace PROP LOW OIL QUANTITY master warning light, then replace specified diode CR3 (4)
associated with PROPELLER LOW
OIL WARNING light (3) that is on.
(See figure 2-13.)
Prop
1
2
49
Diode
CR3AX
CR3AY
Prop
3
4
Diode
CR3AZ
CR3BA
YES
86
84
Gain access to and disconnect
plug P251 (1) at main instrument
panel disconnect.
Is a ground present on plug pin
C?
YES
Repair ground fault between plug
P251 pin C and PROP LOW OIL
QUANTITY master warning light
terminal 2, then replace specified
diode CR3 (4) associated with
PROPELLER LOW OIL WARNING
light (3) that is on. (See figure 213.)
50
NO
Prop
1
2
Diode
CR3AX
CR3AY
Prop
3
4
Diode
CR3AZ
CR3BA
87
Repair ground fault between terminal E of indicator lights dimmer No.
7 (5) and pin C of receptacle J129
(6), then replace specified diode
CR3 (4) associated with PROPELLER LOW OIL WARNING light (3)
that is on. (See figure 2-13.)
Prop
1
2
Diode
CR3AX
CR3AY
NOTE
1
MC-130E airplanes.
2.
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 29)
61-10-00
2-216
Prop
3
4
Diode
CR3AZ
CR3BA
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 30)
61-10-00
2-217
TO 1C-130H-2-61FI-00-1
90
FROM SHT 5
88
With engine(s) running, hold engine condition lever (2) to AIR
START for 15 seconds.
Does PROPELLER LOW OIL
WARNING/PROP light (1) go off?
YES
NO
Shut down engine(s) in accordance with TO 1C-130H-271JG-00-1, 71-00-10; TO 1C130(A)H-2-71JG-00-1, 71-0010; or 1C-130(M)H-2-71JG-001, 71-00-10. Replace propeller
control in accordance with TO
1C-130H-2-61JG-20-1, 61-2001. (Main scavenge pump malfunction.)
89
a. Shut down engine(s) in accordance with TO 1C-130H-2-71JG00-1, 71-00-10; TO 1C-130(A)H2-71JG-00-1, 71-00-10; or TO 1C130(M)H-2-71JG-00-1, 71-00-10.
b. Recheck affected propeller assembly for low fluid (and service if
required) in accordance with TO
1C-130H-2-12JG-10-2, 12-16-03.
Was fluid level low?
91
NO
Replace oil level indicator
switch in accordance with TO
1C-130H-2-61JG-20-1, 61-2008.
YES
92
Replace prop shaft plug seal in
accordance with TO 1C-130H2-61JG-10-1, 61-10-14.
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 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 31)
61-10-00
2-218
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 32)
61-10-00
2-219
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 33)
61-10-00
2-220
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 34)
61-10-00
2-221
TO 1C-130H-2-61FI-00-1
FROM SHT 33
102
Gain access to and disconnect plug
47407A2P1 from indicator light dimmer No.
7 (2).
Is a ground present on pin 16 of plug
47407A2P1?
NO
TO SHT 37
86
YES
103
105
Is airplane equipped with a flight data recorder system? (Check for presence of
FLIGHT RECORDER and FLIGHT VOICE
RECORDER INHB circuit breakers (3,4).
NO
Repair ground fault between pin 16 of
plug 47407A2P1 of indicator dimmer No.
7 and diode CR3AX (1). (See figure 213.)
YES
104
Gain access to terminals of diode CR3AX
(1) and disconnect wire E604A22 from diode bus bar.
Is a ground present on disconnected wire?
106
NO
Fault in flight data recorder system. Go
to TO 1C-130H-2-31FI-00-1 and continue
troubleshooting.
13
YES
107
Repair ground fault between pin 16 of
plug 47407A2P1 of indicator light dimmer
No. 7 and diode CR3AX. (See figure 213.)
NOTE
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 35)
61-10-00
2-222
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 36)
61-10-00
2-223
TO 1C-130H-2-61FI-00-1
FROM SHT 35
108
Is a ground present on pin 24 of plug
47404A2P1 of indicator light dimmer No. 7
(4)?
NO
110
Replace indicator light dimmer No. 7.
82
YES
109
Gain access to and disconnect plug P251
(2) at main instrument panel disconnect.
Is a ground present on pin C of receptacle
J129 (1)?
111
NO
Repair ground fault between pin 24 of
plug 47407A2P1 of indicator light dimmer
No. 7 and pin C of receptacle J129.
(See figure 2-13.)
50
YES
112
Repair ground fault between pin C of
plug P251 and terminal 2 of PROP LOW
OIL QUANTITY master warning light (3).
(See figure 2-13.)
NOTE
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 37)
61-10-00
2-224
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 38)
61-10-00
2-225
TO 1C-130H-2-61FI-00-1
FROM SHT 33
113
Disconnect wire from terminal E
of indicator lights dimmer No. 7
(3).
Is a ground present on disconnected wire?
115
NO
Replace indicator lights dimmer
No. 7. (See figure 2-13.)
9
YES
114
Gain access to and disconnect
plug P251 (1) at main instrument
panel disconnect.
Is a ground present on plug pin
C?
116
NO
Repair ground fault between
dimmer terminal E and pin C of
receptacle J129 (4). (See figure 2-13.)
50
YES
117
Repair ground fault between
plug P251 pin C and terminal 2
of PROP LOW OIL QUANTITY
master warning light (2). (See
figure 2-13.)
NOTE
1
MC-130E airplanes.
2.
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 39)
61-10-00
2-226
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 40)
61-10-00
2-227
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 41)
61-10-00
2-228
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 42)
61-10-00
2-229
TO 1C-130H-2-61FI-00-1
130
FROM SHT 41
128
Is an outboard propeller being
troubleshot?
NO
Repair open circuit between pin
D of plug P396 (1) and related
diode CR3 (2). (See figure 213 or 2-14.)
1
YES
2
Prop
2
3
2
3
Diode
CR3AY
CR3AZ
CR3FY
CR3FZ
131
129
Gain access to and disconnect
plug P130/P1139 (4) at outer
wing break.
Is voltage present on plug pin N?
NO
Repair open circuit between
plug P130/P1139 pin N and related diode CR3 (2). (See figure 2-13 or 2-14.)
1
46
OR
21
2
Prop
1
4
1
4
Diode
CR3AX
CR3BA
CR3FX
CR3GA
YES
132
Repair open circuit between pin
D of plug P396 (1) and pin N of
receptacle J235/J935 (3). (See
figure 2-13 or 2-14.)
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 2-13 or 2-14 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 43)
61-10-00
2-230
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 44)
61-10-00
2-231
TO 1C-130H-2-61FI-00-1
FROM SHT 1
133
Press to test affected PROPELLER LOW OIL WARNING light (1
or 2).
Does light press to test?
YES
137
NO
Is airplane an MC-130H?
TO SHT 49
YES
NO
TO SHT 47
134
Temporarily remove power and
gain access to terminals of affected PROPELLER LOW OIL
WARNING light.
Is 28 VDC present on light terminal 1?
51
,
53
,
55
OR
138
YES
Replace PROPELLER LOW
OIL WARNING light assembly.
57
NO
139
135
Is No. 1 PROPELLER LOW OIL
WARNING light (1) being
troubleshot?
YES
Repair power circuit to No. 1
PROPELLER LOW OIL WARNING light terminal 1. (See figure 2-13.)
NO
140
136
Press to test No. 1 PROPELLER
LOW OIL WARNING light.
Does light press to test?
NO
Repair power circuit to No. 1
PROPELLER LOW OIL WARNING light terminal 1. (See figure 2-13.)
YES
TO SHT 51
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
3.
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 45)
61-10-00
2-232
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 46)
61-10-00
2-233
TO 1C-130H-2-61FI-00-1
FROM SHT 45
141
a. Open PROP LOW OIL LEVEL circuit
breaker (2).
b. Gain access to and disconnect plugs
47407A1P1 and 47407A2P1 from indicator
light dimmer No. 7 (4).
Is ground present on specified pin of plug
47407A1P1 and 40407A2P1 of indicator
light dimmer No. 7?
Prop
Pin
1
47407A1P1-4
2
47407A1P1-16
3
47407A1P1-15
4
47407A2P1-4
143
Repair open circuit between applicable
pin of plug 47407A1P1 and 47407A2P1
of indicator light dimmer No. 7 and related diode CR3 (3). (See figure 2-13.)
NO
Test Point
Prop
1
2
3
4
91
93
Pin
47407A1P1-4
47407A1P1-16
47407A1P1-15
47407A2P1-4
Diode
CR3AX
CR3AY
CR3AZ
CR3BA
95
87
YES
142
Is there continuity between specified pins of receptacle 47407A1J1 and 47407A2J1 of indicator
lights dimmer No. 7?
Prop
1
Pin
47407A1J1-4
47407A1J1-10
2
47407A1J1-16
47407A1J1-24
92
100
3
47407A1J1-15
47407A1J1-23
94
98
4
47407A2J1-4
47407A2J1-10
85
84
144
Test Point
90
103
YES
Repair open circuit between terminal
2 of PROPELLER LOW OIL WARNING light (1) and applicable pin of
plug 47407A1P1 or 47407A2P1 of indicator light dimmer No. 7. (See figure 2-13.)
Prop
1
2
3
4
Pin
47407A1P1-10
47407A1P1-24
47407A1P1-23
47407A2P1-10
NO
145
Replace indicator light dimmer No. 7.
NOTE
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 47)
61-10-00
2-234
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 48)
61-10-00
2-235
TO 1C-130H-2-61FI-00-1
FROM SHT 45
146
a. Open PROP LOW OIL LEVEL
circuit breaker (2).
b. Gain access to terminals of indicator lights dimmer No. 7 (4).
Is a ground present on specified
dimmer terminal?
Prop
Dim
Term
1
a
2
b
3
c
4
d
Test
Point
148
Repair open circuit between
specified dimmer terminal and
related diode CR3 (3). (See
figure 2-13.)
NO
Prop
1
2
3
4
8
6
4
Dim
Term
a
b
c
d
Diode
CR3AX
CR3AY
CR3AZ
CR3BA
2
YES
147
149
Is a ground present on specified
dimmer terminal?
Prop
Dim
Term
1
A
2
B
3
C
4
D
Test
Point
7
5
3
1
YES
Repair open circuit between terminal 2 of PROPELLER LOW
OIL WARNING light (1) and related dimmer terminal. (See
figure 2-13.)
Prop
1
2
3
4
Dim
Term
A
B
C
D
NO
150
Replace indicator lights dimmer
No. 7.
NOTE
1
MC-130E airplanes.
2.
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 49)
61-10-00
2-236
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 50)
61-10-00
2-237
TO 1C-130H-2-61FI-00-1
FROM SHT 45
155
151
Is No. 2 PROPELLER LOW OIL
WARNING light (2) being
troubleshot?
YES
NO
Repair open circuit between terminal
1 of No. 1 PROPELLER LOW OIL
WARNING light (1) and terminal 1 of
No. 2 PROPELLER LOW OIL WARNING light (2). (See figure 2-13.)
156
152
Press to test No. 2 PROPELLER
LOW OIL WARNING light.
Does light press to test?
NO
YES
Repair open circuit between terminal
1 of No. 1 PROPELLER LOW OIL
WARNING light (1) and terminal 1 of
No. 2 PROPELLER LOW OIL WARNING light (2). (See figure 2-13.)
157
153
Is No. 3 PROPELLER LOW OIL
WARNING light (3) being
troubleshot?
YES
NO
Repair open circuit between terminal
1 of No. 2 PROPELLER LOW OIL
WARNING light (2) and terminal 1 of
No. 3 PROPELLER LOW OIL WARNING light (3). (See figure 2-13.)
158
154
Press to test No. 3 PROPELLER
LOW OIL WARNING light.
Does light press to test?
YES
NO
Repair open circuit between terminal
1 of No. 2 PROPELLER LOW OIL
WARNING light (2) and terminal 1 of
No. 3 PROPELLER LOW OIL WARNING light (3). (See figure 2-13.)
159
Repair open circuit between terminal
1 of No. 3 PROPELLER LOW OIL
WARNING light (3) and terminal 1 of
No. 4 PROPELLER LOW OIL WARNING light (4). (See figure 2-13.)
NOTE
1
MC-130E airplanes.
2
MC-130H airplanes.
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 51)
61-10-00
2-238
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 52)
61-10-00
2-239
TO 1C-130H-2-61FI-00-1
FROM SHT 1
163
160
6110031
Press to test PROP LOW OIL QUANTITY master warning light (2).
Does light press to test?
NO
Temporarily remove power and gain access to terminals of PROP LOW OIL
QUANTITY master warning light.
Is 28 VDC present on light terminal 1?
48
YES
165
YES Replace PROP
LOW OIL QUANTITY master warning
light assembly.
NO
164
a. Remove power from airplane.
b. Gain access to and disconnect plug
P251 (1) at main instrument panel disconnect.
Is there continuity between plug pin B
and light terminal 1?
47
166
YES Repair power circuit to pin B of receptacle J129 (4).
(See figure 2-13.)
48
NO
167
Repair open circuit. (See figure 2-13.)
161
a. Remove power from airplane.
b. Gain access to diode CR3 (3) associated with propeller position.
Is a ground present on diode bus bar?
Test
Point
Prop
Diode
1
CR3AX
2
CR3AY
3
CR3AZ
4
CR3BA
168
Replace defective diode CR3. (See figure 2-13.)
NO
13
15
Prop
1
2
3
4
Diode
CR3AX
CR3AY
CR3AZ
CR3BA
17
19
YES
162
YES
Is airplane an MC-130H?
TO SHT 55
NO
TO SHT 57
NOTE
1
MC-130E airplanes.
2.
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 53)
61-10-00
2-240
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 54)
61-10-00
2-241
TO 1C-130H-2-61FI-00-1
FROM SHT 53
169
a. Gain access to PROP LOW OIL QUANTITY
master warning light (3) and remove bulb from
light.
b. Gain access to terminal or light.
Is a ground present on light terminal 2?
173
YES
Replace PROP LOW OIL QUANTITY master warning light assembly.
49
NO
170
Gain access to and disconnect plug
47407A2P1 from indicator light dimmer No. 7
(5).
Is a ground present on pin 16?
174
NO
Repair open circuit between 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
receptacle 47404A2P1?
82
175
NO
Replace indicator light dimmer No.
7.
86
YES
172
Gain access to and disconnect plug P251 (2)
at main instrument panel disconnect.
Is there continuity between plug pin C and
PROP LOW OIL QUANTITY master warning
light terminal 2?
50
176
NO
Repair open circuit between pin 24
of plug 47407A2P1 and pin C of
receptacle J129 (1). (See figure 213.)
49
YES
177
Repair open circuit. (See figure 213.)
NOTE
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 55)
61-10-00
2-242
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 56)
61-10-00
2-243
TO 1C-130H-2-61FI-00-1
FROM SHT 53
178
a. Gain access to PROP LOW OIL QUANTITY
master warning light (2) and remove bulb from
light.
b. Gain access to terminals of light.
Is a ground present on light terminal 2?
182
YES
Replace PROP LOW OIL
QUANTITY master warning light
assembly.
49
NO
179
Gain access to terminals of indicator lights
dimmer No. 7 (4).
Is a ground present on dimmer terminal e?
183
NO
10
Repair open circuit between
dimmer terminal e and diode
CR3AX (3). (See figure 2-13.)
YES
180
184
Is a ground present on dimmer terminal E?
NO
9
Replace indicator lights dimmer
No. 7.
YES
181
Gain access to and disconnect plug P251 (1)
at main instrument panel disconnect.
Is there continuity between plug pin C and
PROP LOW OIL QUANTITY master warning
light terminal 2?
50
185
YES
Repair open circuit between
dimmer terminal E and pin C of
receptacle J129 (5). (See figure 2-13.)
49
NO
186
Repair open circuit. (See figure
2-13.)
NOTE
1
MC-130E airplanes.
2.
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 57)
61-10-00
2-244
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 58)
61-10-00
2-245
TO 1C-130H-2-61FI-00-1
FROM SHT 1
191
187
Is airplane serial number AF92-0547 through
AF92-2104 or AF92-3281 and up?
YES
Fault is in MACAWS. Refer to
TO 1C-130H-2-33FI-00-1-2 for
troubleshooting.
NO
188
YES
Is airplane an MC-130H?
TO SHT 61
NO
189
6110030
a. Place THUNDERSTORM lights switch (2) to
OFF.
b. Place pilot’s INSTRUMENT lights rheostat
(6) to any position except OFF.
c. Momentarily place CAUTION lights switch
(1) to BRIGHT, then DIM.
Do PROP LOW OIL QUANTITY master warning light (3) and a PROPELLER LOW OIL
WARNING light (4) fail to go to selected
bright/dim mode?
192
NO
Replace indicator lights dimmer
No. 7 (5).
YES
190
a. Gain access to terminals of indicator lights
dimmer No. 7 (5).
b. Momentarily hold CAUTION LIGHTS switch
to DIM.
Is 28 VDC present between dimmer terminals
W and X while switch is held?
12
193
NO
Fault is in dimming circuit. Go
to TO 1C-130H-2-33FI-00-1-1-1
and continue troubleshooting.
11
YES
194
Replace indicator lights dimmer
No. 7.
NOTE
1
MC-130E airplanes.
2.
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 59)
61-10-00
2-246
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 60)
61-10-00
2-247
TO 1C-130H-2-61FI-00-1
FROM SHT 59
195
a. Place THUNDERSTORM lights switch (2) to
off.
b. Place pilot’s INSTRUMENT lights rheostat
(1) to any position except OFF.
c. Place WCA DIM LEVEL switch (5) to 1.
d. Momentarily place WCA lights switch (6) to
DIM.
Do PROP LOW OIL QUANTITY master warning light (3) and a PROPELLER LOW OIL
WARNING light (4) fail to go to dim mode?
197
NO
Replace indicator light dimmer
No. 7 (7).
YES
196
a. Gain access to and disconnect plugs
47404A1P1 and 47407A2P1 from indicator
light dimmer No. 7 (7).
b. Momentarily hold WCA lights switch to DIM.
Is 28 VDC present between specified pins of
47407A1P1 and 47407A2P1 while switch is
held?
198
NO
Pin
47407A1P1-7
47407A1P1-8
47407A2P1-7
47407A2P1-8
Test Point
96
Fault is in dimming circuit. Go
to TO 1C-130H-2-33FI-00-1-1-1
and continue troubleshooting.
97
88
89
YES
199
Replace indicator light dimmer
No. 7.
NOTE
See figure 2-13 for:
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 61)
61-10-00
2-248
TO 1C-130H-2-61FI-00-1
Figure 2-5. Propeller Low Fluid Warning System Malfunction (Sheet 62)
61-10-00
2-249/(2-250 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-6. Beta Indication Electrical Schematic Diagram (Airplanes Prior
to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
61-10-00
F2-6
2-251/(2-252 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-7. Beta Indication Electrical Schematic Diagram (Airplanes
AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)
61-10-00
F2-7
2-253/(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)
61-10-00
F2-8
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)
61-10-00
F2-9
2-257/(2-258 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-10. Negative Torque Signal System Electrical Schematic
Diagram (MC-130H Airplanes)
61-10-00
F2-10
2-259/(2-260 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-11. Propeller Feather System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 1 of 8)
Change 6
61-10-00
F2-11
2-261/(2-262 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-11. Propeller Feather System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 2)
61-10-00
F2-11
2-263/(2-264 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-11. Propeller Feather System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 3)
61-10-00
F2-11
2-265/(2-266 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-11. Propeller Feather System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 4)
61-10-00
F2-11
2-267/(2-268 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-11. Propeller Feather System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 5)
61-10-00
F2-11
2-269/(2-270 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-11. Propeller Feather System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 6)
61-10-00
F2-11
2-271/(2-272 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-11. Propeller Feather System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 7)
61-10-00
F2-11
2-273/(2-274 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-11. Propeller Feather System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 8)
61-10-00
F2-11
2-275/(2-276 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-12. Propeller Feather System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and
Airplanes AF92-3281 and Up) (Sheet 1 of 4)
61-10-00
F2-12
2-277/(2-278 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-12. Propeller Feather System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and
Airplanes AF92-3281 and Up) (Sheet 2)
61-10-00
F2-12
2-279/(2-280 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-12. Propeller Feather System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and
Airplanes AF92-3281 and Up) (Sheet 3)
61-10-00
F2-12
2-281/(2-282 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-12. Propeller Feather System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and
Airplanes AF92-3281 and Up) (Sheet 4)
61-10-00
F2-12
2-283/(2-284 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-13. Propeller Low Fluid Warning System Electrical Schematic
Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021
through AF92-3024) (Sheet 1 of 2)
61-10-00
F2-13
2-285/(2-286 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-13. Propeller Low Fluid Warning System Electrical Schematic
Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021
through AF92-3024) (Sheet 2)
61-10-00
F2-13
2-287/(2-288 blank)
TO 1C-130H-2-61FI-00-1
Figure 2-14. Propeller Low Fluid Warning System Electrical Schematic
Diagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes
AF92-3281 and Up)
61-10-00
F2-14
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
F2-15
2-291/(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 any
synchrophaser system malfunction. Contents of this section include a malfunction index, a fault
code index, preparation procedures to be performed prior to fault isolation, a fault isolation
diagram (the actual troubleshooting procedures), locator illustrations for hardware referenced in
the fault isolation diagram, and schematic diagrams.
3-2. MALFUNCTION INDEX. The malfunction index (table 3-1) is used when a malfunction is
encountered during ground maintenance and no numeric fault code was determined from the
FRM diagram, when no numeric fault code was provided by the flight crew, or when the flight
crew only provided an alphanumeric fault code. Malfunctioning systems/modes of operation are
listed 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 3-1. Synchrophaser System Malfunctions
*Alphanumeric
fault code
Malfunction
1.
Synchrophaser system
malfunction
6120S01
Fault isolation reference
Perform figure 3-1, Preparation A, then go
to figure 3-5, block 1.
* If provided by flight crew
3-3. NUMERIC FAULT CODE INDEX. All assigned numeric FRM fault codes for the synchrophaser system are listed in table 3-2. Fault codes are listed in numerical order in the left
column of the table. The middle column contains the AFTO Form 781A report and lists symptoms 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
Fault code
AFTO Form 781A report
Fault isolation reference
6120001
All slave propellers fail to follow when
No. 3 propeller is selected as master. All
slave propellers follow when No. 2 propeller is selected as master.
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1, 6120-13.
6120002
Propeller No. (1)(2)(4) fails to follow when
No. 3 propeller is selected as master.
Propeller follows when No. 2 propeller is
selected as master.
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1, 6120-13.
6120003
All slave propellers fail to follow when
No. 2 propeller is selected as master. All
slave propellers follow when No. 3 propeller is selected as master.
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1, 6120-13.
61-20-00
3-1
TO 1C-130H-2-61FI-00-1
Table 3-2. Synchrophaser System Fault Codes - Continued
Fault code
3-4.
AFTO Form 781A report
Fault isolation reference
6120004
All slave propellers fail to follow when
No. 2 or No. 3 propeller is selected as
master.
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1, 6120-13.
6120005
Propeller No. (1)(3)(4) fails to follow when
No. 2 propeller is selected as master.
Propeller follows when No. 3 propeller is
selected as master.
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1, 6120-13.
6120006
Propeller No. (1)(3)(4) fails to follow when
No. 2 or No. 3 propeller is selected as
master.
Perform figure 3-1, Preparation A, then
go to figure 3-5, block 146.
6120007
All slave engine RPMs fluctuate when
No. 3 propeller is selected as master.
Perform figure 3-1, Preparation A, then
go to figure 3-5, block 326.
6120008
Engine No. (1)(2)(3)(4) RPM fluctuates
when No. 3 propeller is selected as
master.
Perform figure 3-1, Preparation A, then
go to figure 3-5, block 326.
6120009
All slave engine RPMs fluctuate when
No. 2 propeller is selected as master.
Perform figure 3-1, Preparation A, then
go to figure 3-5, block 326.
6120010
Engine No. (1)(2)(3)(4) RPM fluctuates
when No. 2 propeller is selected as
master.
Perform figure 3-1, Preparation A, then
go to figure 3-5, block 326.
6120011
Engine No. (1)(2)(3)(4) RPM takes excessive time to stabilize after rapid THROTTLE movement.
Perform figure 3-1, Preparation A, then
go to figure 3-5, block 148.
6120012
All engine RPMs (fluctuate) (are out of
limits) in normal governing.
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1, 6120-13.
6120013
Engine No. (1)(2)(3)(4) RPM (fluctuates)
(is out of limits) in normal governing.
Perform figure 3-1, Preparation A, then
go to figure 3-5, block 139.
6120014
Engine No. (1)(2)(3)(4) RPM (fluctuates)
(is out of limits) in mechanical governing.
Fault is in propeller system. Go to Section II and continue fault isolation.
PREPARATION PROCEDURES.
WARNING
Improper or inadequate preparation of the airplane may result in
injury to personnel and/or damage to the airplane.
The applicable preparation procedures must be performed before starting troubleshooting. The
preparation is referenced in the malfunction index and fault code indexes. Each procedure is
contained in a figure that illustrates step-by-step actions to be taken to prepare the airplane for
troubleshooting.
61-20-00
3-2
TO 1C-130H-2-61FI-00-1
Figure 3-1. Preparation A (Sheet 1 of 2)
61-20-00
3-3
TO 1C-130H-2-61FI-00-1
Figure 3-1. Preparation A (Sheet 2)
61-20-00
3-4
TO 1C-130H-2-61FI-00-1
Figure 3-2. Preparation B (Sheet 1 of 2)
61-20-00
3-5
TO 1C-130H-2-61FI-00-1
Figure 3-2. Preparation B (Sheet 2)
61-20-00
3-6
TO 1C-130H-2-61FI-00-1
Figure 3-3. Preparation C (Sheet 1 of 3)
61-20-00
3-7
TO 1C-130H-2-61FI-00-1
Figure 3-3. Preparation C (Sheet 2)
61-20-00
3-8
TO 1C-130H-2-61FI-00-1
Figure 3-3. Preparation C (Sheet 3)
61-20-00
3-9
TO 1C-130H-2-61FI-00-1
Figure 3-4. Preparation D (Sheet 1 of 3)
61-20-00
3-10
TO 1C-130H-2-61FI-00-1
Figure 3-4. Preparation D (Sheet 2)
61-20-00
3-11
TO 1C-130H-2-61FI-00-1
Figure 3-4. Preparation D (Sheet 3)
61-20-00
3-12
TO 1C-130H-2-61FI-00-1
3-5. FAULT ISOLATION DIAGRAM. The fault isolation diagram in this section is used for troubleshooting any synchrophaser system malfunction. When the flight crew uses a FRM fault code
to report a malfunction, that number will be found in the fault code index. When no FRM fault
code 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 physical location of items referenced in individual fault isolation diagram blocks. Double-check these
illustrations to verify the correct location when making an observation or measurement. Following the fault isolation diagram are the electrical schematic diagrams. The schematic diagrams
are laid out so that no portion of a diagram is covered up when folded out for use. Thus it is
easy to concurrently locate components, circuits, and test points that are referenced on the fault
isolation diagram.
b. Using Troubleshooting Data. A thorough description of the fault isolation diagram and
other troubleshooting data is provided in Section I. In addition, the Introduction contains an
illustrated how-to-use figure for this section. Understand how to use the troubleshooting information before attempting to repair the airplane.
61-20-00
3-13
TO 1C-130H-2-61FI-00-1
1
6120S01
Advance throttles (6) to obtain approximately 8,000 inch-pounds on
engine torque indicators (3) with
all ELECTRONIC FUEL CORRECTION/TD lights (2) off.
Did RPM on any engine tachometer (4) exceed 103.5 percent or
did any propeller pitchlock?
5
YES
Perform synchrophaser index in
accordance with TO 1C-130H61JG-10-1, 61-10-02 (subtask 12-6).
Does problem persist?
NO
6
Synchrophaser index corrected
malfunction. Secure system.
YES
NO
TO SHT 7
7
2
Place propeller governor control switches (5)
to MECH GOV/MECH.
Is RPM stable for each propeller?
Fault is in propeller system.
Go to figure 2-5 in Section II
and continue troubleshooting.
NO
YES
3
Is RPM in FUNCTION display (1) between
99.8 and 100.2 percent for each propeller?
NO
TO SHT 147
YES
4
Perform synchrophaser index in accordance
with TO 1C-130H-2-61JG-10-1, 61-10-02 (subtask 1-2-6).
Did RPM of any propeller vary more than 0.2
percent when propeller governor control
switches were moved from MECH GOV/MECH
to NORMAL/NORM during the synchrophaser
index?
YES
TO SHT 25
NO
TO SHT 3
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 3-5. Synchrophaser System Malfunction (Sheet 1 of 152)
61-20-00
3-14
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 2)
61-20-00
3-15
TO 1C-130H-2-61FI-00-1
FROM SHT 1
8
Is RPM stable for each propeller
(1) in NORMAL governing?
NO
TO SHT 41
YES
9
Place SYNCHROPHASE
MASTER/MSTR switch (3) to engine 2.
Is RPM stable for all propellers?
NO
TO SHT 109
YES
10
Perform synchrophaser check in
accordance with TO 1C-130H-261JG-10-1, 61-10-02 (subtask 12-9).
Did RPM of any slave propeller
fail to decrease 1 to 3 percent as
No. 2 throttle (2) was retarded to
FLIGHT IDLE/FLT IDLE during
the check?
YES
TO SHT 43
NO
11
Place SYNCHROPHASE
MASTER/MSTR switch to engine
3.
Is RPM stable for all propellers?
NO
TO SHT 109
YES
TO SHT 5
Figure 3-5. Synchrophaser System Malfunction (Sheet 3)
61-20-00
3-16
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 4)
61-20-00
3-17
TO 1C-130H-2-61FI-00-1
FROM SHT 3
12
15
Did the RPM of any slave propeller fail to decrease 1 to 3 percent
as No. 3 throttle (1) was retarded
to FLIGHT IDLE/FLT IDLE during
the synchrophaser check?
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
YES
NO
13
Perform throttle anticipation check
in accordance with TO 1C-130H2-61JG-10-1, 61-10-02 (subtask
1-2-8).
Was check satisfactory?
NO
TO SHT 45
YES
14
Perform fuel governor and
pitchlock check in accordance
with TO 1C-130H-2-61JG-10-1,
61-10-02 (subtask 1-2-10).
Was check satisfactory?
16
YES
Synchrophaser system is normal. Secure system.
NO
TO SHT 7
Figure 3-5. Synchrophaser System Malfunction (Sheet 5)
61-20-00
3-18
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 6)
61-20-00
3-19
TO 1C-130H-2-61FI-00-1
FROM SHT 1 OR 5
17
CAUTION
Do not retard throttle below 96 percent if pitchlock is engaged.
The RPM may drop below 94 percent and cause an engine
flameout, resulting in overtemperature damage to the turbine.
a. Shut down engines in accordance with TO 1C-130H-2-71JG00-1, 71-00-10; or TO 1C-130(A)H-2-71JG-00-1, 71-00-10.
b. Perform Preparation D.
c. Place TEST SELECT switch (2) to 7.
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 volts while
switch is held?
Prop
4
20
NO
Is airplane serial
number AF92-0547
through AF92-2104
or AF92-3281 and
up?
NO
Sync Rcpt Pins
J267A-8, J267A-45
YES
TO SHT 9
18
a. Place PROP CHANNEL SELECT switch to R/3.
b. Momentarily hold engine 3 fuel governing switch (5) to
CHECK.
Does FUNCTION display indicate -6.5 to -7.5 volts while switch
is held?
Prop
3
NO
TO SHT 15
Sync Rcpt Pins
J268A-13, J267A-45
YES
19
a. Place PROP CHANNEL SELECT switch to L/2.
b. Momentarily hold engine 2 fuel governing switch (4) to
CHECK.
Does FUNCTION display indicate -6.5 to -7.5 volts while switch
is held?
Prop
2
NO
TO SHT 17
Sync Rcpt Pins
J268A-12, J267A-45
YES
TO SHT 19
NOTE
1
AC-130H airplanes only.
2
AC-130U airplanes only.
3
MC-130H airplanes only.
Figure 3-5. Synchrophaser System Malfunction (Sheet 7)
61-20-00
3-20
YES
TO SHT 11
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 8)
61-20-00
3-21
TO 1C-130H-2-61FI-00-1
FROM SHT 7
21
23
NOTE
Put meter positive lead to ground
in following steps.
Gain access to terminals of ENG
4 FUEL GOVERNING switch (1).
Is 15 volts present on switch terminal 2?
NO
7
a. Remove junction box from synchrophaser rack.
b. Install a jumper wire between
pin 14 of receptacle J268A (3)
and airplane ground.
Is a ground present on ENG 4
FUEL GOVERNING switch terminal 2?
24
NO
Remove jumper wire. Repair
open circuit between switch terminal 2 and receptacle J268A
pin 14. (See figure 3-6.)
7
YES
YES
25
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
22
Momentarily hold ENG 4 FUEL
GOVERNING switch to CHECK.
Is 15 volts present on switch terminal 1 while switch is held?
26
NO
Replace ENG 4 FUEL GOVERNING switch.
8
YES
27
Repair open circuit between
switch terminal 1 and pin 8 of
receptacle J267A (2). (See figure 3-6.)
NOTE
1
AC-130H airplanes only.
2
AC-130U airplanes only.
3
MC-130E airplanes only.
4
MC-130H airplanes only.
5.
See figure 3-6 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 9)
61-20-00
3-22
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 10)
61-20-00
3-23
TO 1C-130H-2-61FI-00-1
FROM SHT 7
28
NOTE
Put meter positive lead to ground in following
steps.
NO
Gain access to terminals of engine 4 fuel governing switch (3).
Is 15 volts present on switch terminal 2?
TO SHT 13
7
YES
29
Momentarily hold engine 4 fuel governing switch
to CHECK.
Is 15 volts present on switch terminal 1 while
switch is held?
31
NO
Replace engine 4 fuel
governing switch.
8
YES
30
Gain access to and disconnect plug P1743A (1)
from fuel governing control panel (4).
Is there continuity between receptacle J880A (2)
pin D and related control panel switch terminal 1?
8
32
YES
88
Repair open circuit between plug P1743A pin D
and receptacle J267A (5)
pin 8. (See figure 3-7.)
NO
33
Repair open circuit between receptacle J880A
pin D and switch terminal
1. (See figure 3-7.)
NOTE
See figure 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 11)
61-20-00
3-24
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 12)
61-20-00
3-25
TO 1C-130H-2-61FI-00-1
FROM SHT 11
34
a. Gain access to and disconnect
plug P1743A (1) from fuel governing
control panel (4).
b. Install a jumper wire between pin
E of receptacle J880A (2) and airplane ground.
Is a ground present on engine 4 fuel
governing switch terminal 2 (3)?
36
NO
Remove jumper wire. Repair open
circuit between fuel governing
switch terminal 2 and receptacle
J880A pin E. (See figure 3-7.)
7
YES
35
a. Remove junction box from synchrophaser rack.
b. Install a jumper wire between pin
14 of receptacle J268A (5) and airplane ground.
Is a ground present on engine 4 fuel
governing switch terminal 2?
37
NO
Remove jumper wire. Repair open
circuit between plug P1743A pin E
and receptacle J268A, pin 14.
(See figure 3-7.)
7
YES
38
Replace propeller synchrophaser in
accordance with TO 1C-130H-261JG-20-1, 61-20-13.
NOTE
See figure 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 13)
61-20-00
3-26
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 14)
61-20-00
3-27
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 15)
61-20-00
3-28
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 16)
61-20-00
3-29
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 17)
61-20-00
3-30
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 18)
61-20-00
3-31
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.
Does FUNCTION display (3) indicate -6.5 to -7.5 volts while switch is
held?
Prop
1
NO
TO SHT 21
Sync Rcpt Pins
J267A-7, J267A-45
YES
58
a. Place PROP CHANNEL SELECT switch to propeller under test.
b. Place propeller governor control switch (8) to MECH GOV/MECH.
c. Momentarily hold FUEL GOV switch (5) to ON.
Does FUNCTION display indicate -6.5 to -7.5 volts while switch is held?
Prop
1
2
3
4
60
Replace propeller synchrophaser in accordance with TO 1C130H-2-61JG-20-1,
61-20-13.
NO
Sync Rcpt Pins
J267A-7, J267A-45
J268A-12, J267A-45
J268A-13, J267A-45
J267A-8, J267A-45
YES
59
a. Place propeller governor control switch (8) to NORM GOV/NORM
position.
b. Place TEST SELECT switch (7) to 8.
c. Momentarily hold applicable fuel governing switch (1 or 2) to CHECK
for 10 seconds.
Does AC VOLTS display (4) indicate 50 to 65 volts while switch is
held?
(Speed bias control winding)
Prop
1
2
3
4
61
Replace propeller synchrophaser in accordance with TO 1C130H-2-61JG-20-1,
61-20-13.
NO
Sync Rcpt Pins
J267A-35, J267A-36
J268A-25, J268A-26
J267A-37, J267A-38
J268A-27, J268A-28
YES
TO SHT 23
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024, except MC-130H airplanes.
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.
Figure 3-5. Synchrophaser System Malfunction (Sheet 19)
61-20-00
3-32
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 20)
61-20-00
3-33
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 21)
61-20-00
3-34
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 22)
61-20-00
3-35
TO 1C-130H-2-61FI-00-1
FROM SHT 19
71
a. Record voltage indication in FUNCTION display (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 to MECH GOV/MECH.
e. Record voltage indication in FUNCTION display.
f. Compare the two voltage indications
recorded in steps a and e.
Did voltage change more than 0.2 volts
on any channel?
(Feedback pot)
DC: Sync
Rcpt Pin
J267A-11
J268A-2
J268A-5
J267A-14
AC: Sync
Rcpt Pins
J267A-35 and
J268A-25 and
J267A-37 and
J268A-27 and
72
YES
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
36
26
38
28
NO
73
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024, except MC-130H airplanes.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3
AC-130H airplanes only.
4
AC-130U airplanes only.
5
MC-130H airplanes only.
Figure 3-5. Synchrophaser System Malfunction (Sheet 23)
61-20-00
3-36
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 24)
61-20-00
3-37
TO 1C-130H-2-61FI-00-1
FROM SHT 1
74
Did all propellers (1,2,3, and 4)
fail to respond to the synchrophaser index?
YES
TO SHT 27
NO
75
With No. 2 propeller (2) as master
did No. 3 propeller (3) fail to index, and with No. 3 propeller as
master did No. 2 propeller fail to
index?
YES
TO SHT 39
NO
76
Perform propeller governor servobias clutch-brake check on affected propeller in accordance with
TO 1C-130H-2-61JG-10-1, 61-1002 (subtask 1-2-7).
Was RPM within limits for the affected propeller?
77
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
YES
TO SHT 47
Figure 3-5. Synchrophaser System Malfunction (Sheet 25)
61-20-00
3-38
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 26)
61-20-00
3-39
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 27)
61-20-00
3-40
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 28)
61-20-00
3-41
TO 1C-130H-2-61FI-00-1
FROM SHT 27
89
Place SYNCHROPHASE
MASTER/MSTR switch (1) to engine 2.
Are MASTER light L/2 (2) and
SYNC light (4) on?
Prop
Any
91
NO
Gain access to terminal board
TB146A (5).
Is 28 VDC present on terminal
199?
NO
93
Repair power circuit to terminal
199. (See figure 3-6 or 3-7.)
27
Sync Rcpt Pins
J268A-22
YES
YES
92
94
Is 28 VDC present on terminal
207?
29
YES Repair open circuit between terminal 207 and pin 22 of receptacle J268A (6). (See figure 36 or 3-7.)
NO
TO SHT 31
90
Place SYNCHROPHASE
MASTER/MSTR switch to engine
3.
Are MASTER light R/3 (3) and
SYNC light on?
Prop
Any
NO
TO SHT 33
Sync Rcpt Pins
J267A-27
YES
TO SHT 35
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 29)
61-20-00
3-42
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 30)
61-20-00
3-43
TO 1C-130H-2-61FI-00-1
FROM SHT 29
95
Gain access to terminals of SYNCHROPHASE MASTER/MSTR
switch (3).
Is 28 VDC present on switch terminal 11?
99
NO
Repair open circuit between
switch terminal 11 and terminal
199 of terminal board TB146A
(1). (See figure 3-6 or 3-7.)
14
YES
96
Is 28 VDC present on switch terminal 10?
100
NO
17
Replace SYNCHROPHASE
MASTER/MSTR switch.
YES
97
101
Gain access to terminals of PROP
RESYNCHROPHASE/PROP
SYNC switch (2).
Is 28 VDC present on switch terminal 5?
NO
22
Repair open circuit between
PROP RESYNCHROPHASE/
PROP SYNC switch terminal 5
and SYNCHROPHASE
MASTER/MSTR switch terminal
10. (See figure 3-6 or 3-7.)
YES
102
98
Is 28 VDC present on switch terminal 6?
25
NO
YES
Repair open circuit between
PROP RESYNCHROPHASE/
PROP SYNC switch terminal 6
and terminal board TB146A terminal 207. (See figure 3-6 or
3-7.)
103
Replace PROP RESYNCHROPHASE/PROP SYNC
switch.
NOTE
See figure 3-6 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 31)
61-20-00
3-44
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 32)
61-20-00
3-45
TO 1C-130H-2-61FI-00-1
FROM SHT 29
108
104
Gain access to terminal board
TB146A (1).
Is 28 VDC present on terminal
207?
NO
29
Gain access to terminals of SYNCHROPHASE MASTER/MSTR
switch (2).
Is 28 VDC present on switch terminal 12?
109
YES Repair open circuit between
switch terminals 10 and 12.
(See figure 3-6 or 3-7.)
18
YES
NO
110
Replace SYNCHROPHASE
MASTER/MSTR switch.
105
111
Is 28 VDC present on terminal
206?
YES
28
Repair open circuit between terminal 206 and pin 27 of receptacle J267A (3). (See figure 36 or 3-7.)
NO
106
Gain access to terminals of SYNCHROPHASE MASTER/MSTR
switch (2).
Is 28 VDC present on switch terminal 8?
112
NO
Repair open circuit between
switch terminals 8 and 11.
(See figure 3-6 or 3-7.)
15
YES
107
113
Is 28 VDC present on switch terminal 9?
19
YES
Repair open circuit between
switch terminal 9 and terminal
board TB146A terminal 206.
(See figure 3-6 or 3-7.)
NO
114
Replace SYNCHROPHASE
MASTER/MSTR switch.
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 33)
61-20-00
3-46
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 34)
61-20-00
3-47
TO 1C-130H-2-61FI-00-1
FROM SHT 29
115
Momentarily hold PROP RESYNCHROPHASE/PROP SYNC
switch (3) to RESYNC/INDEX.
Are R/3 light (1) and RESYNC/INDEX light (2) on while switch is
held?
Prop
Any
119
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
YES
Sync Rcpt Pins
J268A-15
NO
116
118
a. Gain access to terminal board
TB128A (6).
b. Momentarily hold PROP
RESYNCHROPHASE/PROP
SYNC switch to RESYNC/INDEX.
Is 28 VDC present on terminal
board terminal 17 while switch is
held?
NO
a. Gain access to terminals of
PROP RESYNCHROPHASE/
PROP SYNC switch.
b. Momentarily hold PROP
RESYNCHROPHASE/PROP
SYNC switch to RESYNC/INDEX.
Is 28 VDC present on switch terminal 4 while switch is held?
30
120
Repair open circuit between
YES PROP RESYNCHROPHASE/
PROP SYNC switch terminal 4
and terminal board TB128A terminal 17. (See figure 3-6 or 37.)
24
YES
NO
121
Replace PROP RESYNCHROPHASE/
PROP SYNC switch.
117
a. Gain access to terminal board TB1C (5).
b. Momentarily hold PROP RESYNCHROPHASE/PROP SYNC switch to
RESYNC/INDEX.
Is 28 VDC present on terminal board terminal 9 while switch is held?
122
NO
Repair open circuit between terminal
board TB1C terminal 9 and terminal
board TB128A terminal 17. (See figure 3-6 or 3-7.)
13
YES
123
Repair open circuit between terminal
board TB1C terminal 9 and pin 15 of
receptacle J268A (4). (See figure 3-6
or 3-7.)
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 35)
61-20-00
3-48
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 36)
61-20-00
3-49
TO 1C-130H-2-61FI-00-1
FROM SHT 27
124
Is a ground present on pin 2 of plug
P1258F (2)?
127
NO
34
Repair ground circuit. (See figure 3-6.)
YES
125
128
Is a ground present on plug pin 4?
NO
35
Repair ground circuit. (See figure 3-6.)
YES
126
Is there continuity between plug P1258F
pin 3 and pin 34 of receptacle J267A
(1)?
36
129
YES
Replace constant voltage transformer (3).
41
NO
130
Repair open circuit. (See figure
3-6.)
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 37)
61-20-00
3-50
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 38)
61-20-00
3-51
TO 1C-130H-2-61FI-00-1
FROM SHT 25
131
a. Shut down engines in accordance with TO 1C-130H-2-71JG00-1, 71-00-10; or TO 1C130(A)H-2-71JG-00-1, 71-00-10.
b. Place SYNCHROPHASE
MASTER/MSTR switch (1) to engine 2 or engine 3.
c. Gain access to terminals of
PROP RESYNCHROPHASE/
PROP SYNC switch (2).
Is 28 VDC present on PROP
RESYNCHROPHASE/PROP
SYNC switch terminal 2?
134
NO
Repair open circuit between
PROP RESYNCHROPHASE/
PROP SYNC switch terminals 2
and 5. (See figure 3-6 or 3-7.)
23
YES
132
Momentarily hold PROP RESYNCHROPHASE/PROP SYNC
switch to RESYNC/INDEX.
Is 28 VDC present on switch terminal 1 while switch is held?
135
NO
Replace PROP RESYNCHROPHASE/PROP SYNC
switch.
26
YES
133
Momentarily hold PROP RESYNCHROPHASE/PROP SYNC
switch to RESYNC/INDEX.
Is 28 VDC present on SYNCHROPHASE MASTER/MSTR
switch terminal 5 while PROP
RESYNCHROPHASE/PROP
SYNC switch is held?
136
NO
Repair open circuit between
SYNCHROPHASE MASTER/
MSTR switch terminal 5 and
PROP RESYNCHROPHASE/
PROP SYNC switch terminal 1.
(See figure 3-6 or 3-7.)
16
YES
137
Replace SYNCHROPHASE
MASTER/MSTR switch.
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 39)
61-20-00
3-52
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 40)
61-20-00
3-53
TO 1C-130H-2-61FI-00-1
FROM SHT 3
138
141
Does RPM of all propellers (2)
fluctuate with propeller governor
control switch (3) in NORMAL/
NORM?
YES
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
NO
139
6120013
Does frequency meter (1) indicate
a fluctuation for the affected propeller?
142
NO
Fault is in tachometer system.
Go to TO 1C-130H-2-70FI-00-11 and continue troubleshooting.
YES
140
Perform synchrophaser index in
accordance with TO 1C-130H-261JG-10-1, 61-10-02 (subtask 12-6).
Did RPM stabilize?
143
YES
Synchrophaser index corrected
malfunction. Secure system.
NO
TO SHT 47
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 3-5. Synchrophaser System Malfunction (Sheet 41)
61-20-00
3-54
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 42)
61-20-00
3-55
TO 1C-130H-2-61FI-00-1
FROM SHT 3
144
If not previously done, perform
synchrophaser check in accordance with TO 1C-130H-2-61JG10-1, 61-10-02 (subtask 1-2-9).
Did RPM of any slave propeller
(2) fail to decrease 1 to 3 percent
as No. 3 throttle (1) was retarded
to FLIGHT IDLE/FLT IDLE during
the check?
NO
TO SHT 109
YES
147
145
Did all slave propellers fail to follow either master?
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
YES
NO
146
6120006
Perform pitchlock check in accordance with TO 1C-130H-2-61JG10-1, 61-10-02 (subtask 1-2-10).
Was check satisfactory?
NO
TO SHT 47
YES
TO SHT 109
Figure 3-5. Synchrophaser System Malfunction (Sheet 43)
61-20-00
3-56
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 44)
61-20-00
3-57
TO 1C-130H-2-61FI-00-1
FROM SHT 5
148
6120011
a. Perform synchrophaser index in
accordance with TO 1C-130H-261JG-10-1, 61-10-02 (subtask 12-6).
b. Perform throttle anticipation
check in accordance with TO 1C130H-2-61JG-10-1, 61-10-02
(subtask 1-2-8).
Does fault persist?
151
NO
Synchrophaser index corrected
malfunction. Secure system.
YES
149
Perform propeller governor servobias clutch-brake check on affected propeller (3) in accordance
with TO 1C-130H-2-61JG-10-1,
61-10-02 (subtask 1-2-7).
Was RPM within limits?
152
NO
Replace valve housing assembly in accordance with TO 1C130H-61JG-20-1, 61-20-02.
NO
Reseal dome assembly in accordance with TO 1C-130H-261JG-10-1, 61-10-13.
YES
150
a. Perform synchrophaser index in
accordance with TO 1C-130H-261JG-10-1, 61-10-02 (subtask 12-6).
b. Shut down engines in accordance with TO 1C-130H-2-71JG00-1, 71-00-10; or TO 1C130(A)H-2-71JG-00-1, 71-00-10.
c. Move throttle (1) to MAXIMUM
REVERSE/MAX RVS.
d. Hold engine condition lever (2)
in AIR START until propeller
blades (3) stop moving (in reverse
position), then release.
e. Place engine condition lever to
FEATHER/FTR and time propeller
movement.
Does propeller go from full reverse to full feather in 25 seconds
or less?
153
YES
TO SHT 47
Figure 3-5. Synchrophaser System Malfunction (Sheet 45)
61-20-00
3-58
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 46)
61-20-00
3-59
TO 1C-130H-2-61FI-00-1
FROM SHT 25, 41, 43, OR 45
154
a. If necessary, shut down engines in accordance with TO 1C-130H-2-71JG-00-1, 71-0010; or TO 1C-130(A)H-2-71JG-00-1, 71-00-10.
b. Perform Preparation C.
Does FUNCTION display (3) indicate 200 to
300 and does AC VOLTS display (4) indicate
3?
(Anticipator pot R)
Prop
1
2
3
4
NO
TO SHT 49
Sync Rcpt Pins
J267A-18, J267A-45
J268A-19, J267A-45
J268A-20, J267A-45
J267A-19, J267A-45
YES
155
157
Place RESISTANCE TEST switch (5) to 2.
Does FUNCTION display indicate 134 to 216
and does AC VOLTS display indicate 3?
(Anticipator pot wiper R)
Prop
1
2
3
4
NO
Sync Rcpt Pins
J267A-22, J267A-45
J267A-20, J267A-45
J267A-21, J267A-45
J267A-9, J267A-45
Gain access to and disconnect
plug P390 (1) at valve housing
assembly.
Is 134K to 216K ohms resistance
present between pins K and S of
valve housing assembly receptacle (2)?
71
70
158
NO
Replace throttle anticipation potentiometer in
accordance with
TO 1C-130H-261JG-20-1, 61-2017.
YES
YES
TO SHT 53
156
Move throttle (6) to TAKE OFF.
Does FUNCTION display indicate 24 to 58
and does AC VOLTS display indicate 3?
(Anticipator pot wiper R in T/O pos)
Prop
1
2
3
4
159
NO
Sync Rcpt Pins
J267A-22, J267A-45
J267A-20, J267A-45
J267A-21, J267A-45
J267A-9, J267A-45
YES
TO SHT 55
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 47)
61-20-00
3-60
Change 2
Replace throttle anticipation potentiometer in
accordance with
TO 1C-130H-261JG-20-1, 61-2017.
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 48)
61-20-00
3-61
TO 1C-130H-2-61FI-00-1
FROM SHT 47
160
Gain access to and disconnect
plug P390 (3) at valve housing
assembly.
Is 200K to 300K ohms resistance
present between pins K and T of
valve housing receptacle (4)?
71
164
Replace throttle anticipation potentiometer in accordance with
TO 1C-130H-2-61JG-20-1, 6120-17.
NO
72
YES
163
161
Is a ground present on plug P390
pin K?
NO
71
Gain access to and disconnect
plug P398 (2) at engine firewall.
Is a ground present on plug pin
V?
59
165
YES Repair open circuit between pin
V of receptacle J239 (1) and
plug P390 pin K. (See figure 36 or 3-7.)
YES
NO
166
Repair ground circuit. (See figure 3-6 or 3-7.)
162
a. Reconnect plug P390 at valve
housing assembly.
b. Gain access to and disconnect
plug P398 (2) at engine firewall.
Is 200K to 300K ohms resistance
present between pins T and V of
receptacle J239 (1)?
60
167
NO
Repair wiring fault between receptacle J239 pin T and plug
P390 pin T. (See figure 3-6 or
3-7.)
59
YES
TO SHT 51
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 49)
61-20-00
3-62
Change 2
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 50)
61-20-00
3-63
TO 1C-130H-2-61FI-00-1
170
FROM SHT 49
168
Is an outboard propeller being
troubleshot?
NO
Repair wiring fault between pin
T of plug P398 (1) and related
pin of receptacle J268A (2).
(See figure 3-6 or 3-7.)
Prop
2
3
YES
Rcpt
Pin
19
20
169
a. Reconnect plug P398 (1) at engine firewall.
b. Gain access to and disconnect
plug P130/P1139 (4) at outer
wing break.
Is 200K to 300K ohms resistance
present between pin g of receptacle J235/J935 (5) and airplane
ground?
171
NO
Repair wiring fault between receptacle J235/J935 pin g and
plug P398 pin T. (See figure 36 or 3-7.)
48
YES
172
Repair wiring fault between plug
P130/P1139 pin g and related
pin of receptacle J267A (3).
(See figure 3-6 or 3-7.)
Prop
1
4
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 51)
61-20-00
3-64
Rcpt
Pin
18
19
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 52)
61-20-00
3-65
TO 1C-130H-2-61FI-00-1
FROM SHT 47
173
a. Reconnect plug P390 (3) at valve housing assembly.
b. Gain access to and disconnect plug P398 (2)
at engine firewall.
Is 134K to 216K ohms resistance present between pins S and V of receptacle J239 (1)?
58
176
NO
Repair wiring fault between receptacle J239 pin
S and plug P390 pin S. (See figure 3-6 or 37.)
59
YES
177
174
NO
Repair wiring fault between plug P398 pin S
and related pin of receptacle J267A (4). (See
figure 3-6 or 3-7.)
Is an outboard propeller being troubleshot?
Rcpt
Pin
20
21
Prop
2
3
YES
175
a. Reconnect plug P398 at engine firewall.
b. Gain access to and disconnect plug P130/
P1139 (6) at outer wing break.
Is 134K to 216K ohms resistance present between specified pin of receptacle J235/J935 (5)
and airplane ground?
Prop
Rcpt
Pin
1
f
4
c
Test
Point
47
178
NO
Repair wiring fault between plug P398 pin S
and related receptacle J235/J935 pin. (See figure 3-6 or 3-7.)
Rcpt
Pin
f
c
Prop
1
4
47
YES
179
Repair wiring fault between specified plug
P130/P1139 pin and related pin of receptacle
J267A (4). (See figure 3-6 or 3-7.)
Prop
1
4
Plug
Pin
f
c
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 53)
61-20-00
3-66
Rcpt
Pin
22
9
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 54)
61-20-00
3-67
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 11
and does AC VOLTS display (4) indicate 3?
(Feedback pot R)
Prop
1
2
3
4
NO
TO SHT 57
Sync Rcpt Pins
J267A-10, J267A-12
J268A-1, J268A-3
J268A-4, J268A-6
J267A-13, J267A-15
YES
181
183
Place RESISTANCE TEST switch to 4.
Does FUNCTION display indicate 1 to 10.5
and does AC VOLTS display indicate 3?
(Feedback pot wiper R)
Prop
1
2
3
4
Sync Rcpt Pins
J267A-10, J267A-11
J268A-2, J268A-3
J268A-4, J268A-5
J267A-14, J267A-15
NO
Gain access to and disconnect plug P390 (1) at valve
housing assembly.
Is 1K to 10.5K ohms resistance present between pins
L and N of valve housing
assembly receptacle (2)?
74
184
NO
73
YES
YES
TO SHT 63
182
Place RESISTANCE TEST switch to 5.
Does FUNCTION display indicate 25 to 50 ohms?
(Speed bias control winding R)
NO
Prop
1
2
3
4
Sync Rcpt Pins
J267A-35, J267A-36
J268A-25, J268A-26
J267A-37, J267A-38
J268A-27, J268A-28
TO SHT 65
YES
TO SHT 71
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 55)
61-20-00
3-68
Replace valve housing
assembly in accordance
with TO 1C-130H-261JG-20-1, 61-20-02.
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 56)
61-20-00
3-69
TO 1C-130H-2-61FI-00-1
FROM SHT 55
185
Gain access to and disconnect
plug P390 (3) at valve housing
assembly.
Is 8K to 11K ohms resistance present between pins C and L of
valve housing assembly receptacle (4)?
75
188
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
74
YES
186
187
a. Reconnect plug P390 at valve
housing assembly.
b. Gain access to and disconnect
plug P398 (2) at engine firewall.
Is 8K to 11K ohms resistance present between pins C and W of receptacle J239 (1)?
63
62
YES
NO
a. Gain access to and disconnect
plug P390 at valve housing assembly.
b. Install a jumper wire between
plug pins K and L.
Is there continuity between receptacle J239 pins V and W?
59
189
NO
Remove jumper wire. Repair
wiring fault between receptacle
J239 pin W and plug P390 pin
L. (See figure 3-6 or 3-7.)
62
YES
TO SHT 59
190
Remove jumper wire. Repair
wiring fault between receptacle
J239 pin C and plug P390 pin
C. (See figure 3-6 or 3-7.)
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 57)
61-20-00
3-70
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 58)
61-20-00
3-71
TO 1C-130H-2-61FI-00-1
FROM SHT 57
191
Is an outboard propeller being
troubleshot?
YES
TO SHT 61
NO
192
a. Install a jumper wire between
pins V and W of plug P398 (1).
b. Remove junction box from synchrophaser rack.
Is a ground present on specified
pin of receptacle J268A (2)?
Prop
Rcpt
Pin
2
3
3
4
193
NO
Remove jumper wire. Repair
wiring fault between plug P398
pin W and related receptacle
J268A pin. (See figure 3-6 or
3-7.)
Test
Point
38
38
Prop
2
3
Rcpt
Pin
3
4
YES
194
Remove jumper wire. Repair
wiring fault between plug P398
pin C and related receptacle
J268A pin. (See figure 3-6 or
3-7.)
Prop
2
3
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 59)
61-20-00
3-72
Rcpt
Pin
1
6
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 60)
61-20-00
3-73
TO 1C-130H-2-61FI-00-1
FROM SHT 59
195
197
a. Reconnect plug P398 (1) at engine firewall.
b. Gain access to and disconnect
plug P130/P1139 (3) at outer
wing break.
Is 8K to 11K ohms resistance present between specified pins of receptacle J235/J935 (2)?
Rcpt
Prop Pins
1
j and k
4
j and e
YES
Test
Points
a. Install a jumper wire between
plug P130/P1139 pin j and airplane ground.
b. Remove junction box from synchrophaser rack.
Is a ground present on specified
pin of receptacle J267A (4)?
Prop
Rcpt
Pin
50
51
1
10
50
51
4
15
Test
Point
38
198
NO
Remove jumper wire. Repair
wiring fault between plug P130/
P1139 pin j and related receptacle J267A pin. (See figure 36 or 3-7.)
Rcpt
Pin
10
15
Prop
1
4
38
YES
NO
199
Remove jumper wire. Repair
wiring fault between specified
plug P130/P1139 pin and related receptacle J267A pin. (See
figure 3-6 or 3-7.)
Prop
1
4
Plug
Pin
k
e
Rcpt
Pin
12
13
200
196
a. Gain access to and disconnect
plug P398 at engine firewall.
b. Install a jumper wire between
plug pins V and W.
Is a ground present on receptacle
J235/J935 pin j?
YES
Remove jumper wire. Repair
wiring fault between plug P398
pin C and related plug P130/
P1139 pin. (See figure 3-6 or
3-7.)
Prop
1
4
50
NO
Plug
Pin
k
e
201
Remove jumper wire. Repair
wiring fault between receptacle
J235/J935 pin j and plug P398
pin W. (See figure 3-6 or 3-7.)
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 61)
61-20-00
3-74
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 62)
61-20-00
3-75
TO 1C-130H-2-61FI-00-1
FROM SHT 55
202
a. Reconnect plug P390 (3) at
valve housing assembly.
b. Gain access to and disconnect
plug P398 (2) at engine firewall.
Is 1K to 10.5K ohms resistance
present between pins N and W of
receptacle J239 (1)?
61
205
NO
Repair wiring fault between receptacle J239 pin N and plug
P390 pin N. (See figure 3-6 or
3-7.)
62
YES
206
203
Is an outboard propeller being
troubleshot?
NO
Repair wiring fault between plug
P398 pin N and related pin of
receptacle J268A (4). (See figure 3-6 or 3-7.)
Prop
2
3
YES
Rcpt
Pin
2
5
204
a. Reconnect plug P398 at engine
firewall.
b. Gain access to and disconnect
plug P130/P1139 (7) at outer
wing break.
Is 1K to 10.5K ohms resistance
present between pins h and j of
receptacle J235/J935 (6)?
49
207
NO
Repair wiring fault between receptacle J235/J935 pin h and
plug P398 pin N. (See figure 36 or 3-7.)
50
YES
208
Repair wiring fault between plug
P130/P1139 pin h and related
pin of receptacle J267A (5).
(See figure 3-6 or 3-7.)
Prop
1
4
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 63)
61-20-00
3-76
Rcpt
Pin
11
14
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 64)
61-20-00
3-77
TO 1C-130H-2-61FI-00-1
FROM SHT 55
209
Gain access to and disconnect
plug P390 (3) at valve housing
assembly.
Is 25 to 50 ohms resistance present between pins B and M of
valve housing assembly receptacle (4)?
68
212
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
67
YES
210
211
a. Reconnect plug P390 at valve
housing assembly.
b. Gain access to and disconnect
plug P398 (2) at engine firewall.
Is 25 to 50 ohms resistance present between pins B and X of receptacle J239 (1)?
56
55
YES
NO
a. Gain access to and disconnect
plug P390 at valve housing assembly.
b. Install a jumper wire between
plug pins K and M.
Is there continuity between receptacle J239 pins V and X?
59
213
YES Remove jumper wire. Repair
open circuit between receptacle
J239 pin B and plug P390 pin
B. (See figure 3-6 or 3-7.)
55
NO
TO SHT 67
214
Remove jumper wire. Repair
open circuit between receptacle
J239 pin X and plug P390 pin
M. (See figure 3-6 or 3-7.)
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 65)
61-20-00
3-78
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 66)
61-20-00
3-79
TO 1C-130H-2-61FI-00-1
FROM SHT 65
215
Is an outboard propeller being
troubleshot?
YES
TO SHT 69
NO
216
a. Install a jumper wire between
pins B and V of plug P398 (1).
b. Remove junction box from synchrophaser rack.
Is a ground present on specified
pin of receptacle J267A (3) or
J268A (2)?
Prop
Rcpt
Pin
Test
Point
2
J268A-26
3
J267A-38
37
217
YES
Remove jumper wire. Repair
open circuit between plug P398
pin X and related receptacle
pin. (See figure 3-6 or 3-7.)
Prop
2
3
Rcpt
Pin
J268A-25
J267A-37
37
NO
218
Remove jumper wire. Repair
open circuit between plug P398
pin B and related receptacle
pin. (See figure 3-6 or 3-7.)
Prop
2
3
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 67)
61-20-00
3-80
Rcpt
Pin
J268A-26
J267A-38
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 68)
61-20-00
3-81
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 69)
61-20-00
3-82
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 70)
61-20-00
3-83
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 180
ohms?
(Speed bias ref winding R)
Prop
1
2
3
4
NO
TO SHT 73
Sync Rcpt Pins
J267A-40, J267A-45
J268A-23, J267A-45
J268A-24, J267A-45
J267A-39, J267A-45
YES
227
Move throttles (1) below GROUND IDLE/GND
IDLE.
Do FUNCTION display (2) and AC VOLTS display (3) indicate 1999?
(Sync disarming switch)
Prop
1
2
3
4
229
NO
Sync Rcpt Pins
J267A-40, J267A-45
J268A-23, J267A-45
J268A-24, J267A-45
J267A-39, J267A-45
Adjust or replace synchrophaser disarming switch (6)
as required in accordance with
TO 1C-130H-2-76JG-00-1, 7610-38.
YES
228
a. Move throttles above FLIGHT IDLE/FLT IDLE.
b. Place propeller governor control switches (5) to
MECH GOV/MECH.
Does FUNCTION display indicate 1999?
(propeller governor control switch)
Prop
1
2
3
4
230
NO
Sync Rcpt Pins
J267A-40, J267A-45
J268A-23, J267A-45
J268A-24, J267A-45
J267A-39, J267A-45
Replace propeller governor control switch.
YES
TO SHT 81
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 3-5. Synchrophaser System Malfunction (Sheet 71)
61-20-00
3-84
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 72)
61-20-00
3-85
TO 1C-130H-2-61FI-00-1
FROM SHT 71
231
Gain access to and disconnect plug P390 (3)
at valve housing assembly.
Is 120 to 180 ohms resistance present between pins A and K of valve housing assembly receptacle (4)?
69
235
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
71
YES
232
a. Reconnect plug P390 at valve housing assembly.
b. Gain access to and disconnect plug P398
(2) at engine firewall.
Is 120 to 180 ohms resistance present between pins A and V of receptacle J239 (1)?
57
236
Repair open circuit between receptacle J239 pin A and plug
P390 pin A. (See figure 3-6 or
3-7.)
NO
59
YES
233
a. Reconnect plug P398 at engine firewall.
b. Disengage junction box from synchrophaser
rack.
c. Gain access to terminals of propeller governor control switch (5).
Is 120 to 180 ohms resistance present between switch terminal 3 and airplane ground?
NO
TO SHT 75
86
YES
234
Is there continuity between switch terminals 2
and 3?
85
237
NO
86
Replace propeller governor control switch.
YES
TO SHT 77
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 73)
61-20-00
3-86
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 74)
61-20-00
3-87
TO 1C-130H-2-61FI-00-1
FROM SHT 73
240
238
Is an outboard propeller being
troubleshot?
NO
YES
Repair open circuit between terminal 3 of propeller governor
control switch (4) and pin A of
plug P398 (1). (See figure 3-6
or 3-7.)
239
Gain access to and disconnect
plug P130/P1139 (3) at outer
wing break.
Is 120 to 180 ohms resistance
present between specified pin of
receptacle J235/J935 (2) and airplane ground?
Prop
Rcpt
Pin
1
e
4
k
241
NO
Test
Point
46
Repair open circuit between pin
A of plug P398 (1) and related
receptacle J235/J935 pin. (See
figure 3-6 or 3-7.)
Prop
1
4
Rcpt
Pin
e
k
46
YES
242
Repair open circuit between terminal 3 of propeller governor
control switch (4) and related
plug P130/P1139 pin. (See figure 3-6 or 3-7.)
Prop
1
4
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 75)
61-20-00
3-88
Plug
Pin
e
k
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 76)
61-20-00
3-89
TO 1C-130H-2-61FI-00-1
FROM SHT 73
243
Gain access to terminal board
TB126A (2).
Is 120 to 180 ohms resistance
present between specified terminal and airplane ground?
Prop
TB
Term
1
36
2
37
3
38
4
39
Test
Point
245
NO
Repair open circuit between terminal
2 of propeller governor control switch
(4) and related terminal board
TB126A terminal. (See figure 3-6 or
3-7.)
84
Prop
1
2
84
84
TB
Term
36
37
Prop
3
4
TB
Term
38
39
84
YES
244
Gain access to specified terminal
board.
Is 120 to 180 ohms resistance
present between specified terminal and airplane ground?
Test
Point
Prop TB-Term
1
TB135A (1) -169
2
TB135A (1) -170
3
TB146A (3) -210
4
TB146A (3) -211
246
Repair open circuit between specified
terminal and related pin of receptacle
J267A (6) or J268A (5). (See figure
3-6 or 3-7.)
YES
81
81
81
Prop
1
2
3
4
TB-Term
TB135A-169
TB135A-170
TB146A-210
TB146A-211
81
NO
TO SHT 79
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024, except MC-130E airplanes.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3
MC-130E airplanes.
4.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 77)
61-20-00
3-90
Rcpt
Pin
J267A-40
J268A-23
J268A-24
J267A-39
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 78)
61-20-00
3-91
TO 1C-130H-2-61FI-00-1
FROM SHT 77
249
247
Gain access to terminals of synchrophaser disarming switch (3).
Is 120 to 180 ohms resistance
present between switch terminal
2NC and airplane ground?
NO
Repair open circuit between
synchrophaser disarming switch
terminal 2NC and related terminal of terminal board TB126A
(1). (See figure 3-6 or 3-7.)
TB
Prop Term
1
36
2
37
83
YES
TB
Prop Term
3
38
4
39
250
248
Is 120 to 180 ohms resistance
present between switch terminal
1NC and airplane ground?
82
NO
YES
Repair open circuit between
synchrophaser disarming switch
terminal 1NC and related terminal. (See figure 3-6 or 3-7.)
Prop
1
2
3
4
TB-Term
TB135A (4)
TB135A (4)
TB146A (2)
TB146A (2)
-169
-170
-210
-211
251
Adjust or replace synchrophaser disarming switch as
required in accordance with TO
1C-130H-2-76JG-00-1, 76-1038.
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 79)
61-20-00
3-92
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 80)
61-20-00
3-93
TO 1C-130H-2-61FI-00-1
FROM SHT 71
252
Is an outboard propeller being
troubleshot?
NO
TO SHT 83
YES
253
a. Place TYPE SELECT switch
(2) to TUBE.
b. Place RESISTANCE TEST
switch (3) to 8.
Does FUNCTION display (1) indicate 30 to 45 ohms?
(Clutch 1 and 4 winding parallel
R)
YES
TO SHT 89
Prop Sync Rcpt Pins
1,4 J268A-15, J267A-45
NO
TO SHT 107
Figure 3-5. Synchrophaser System Malfunction (Sheet 81)
61-20-00
3-94
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 82)
61-20-00
3-95
TO 1C-130H-2-61FI-00-1
256
FROM SHT 81
254
Is No. 2 propeller (1) being
troubleshot?
NO
YES
a. Place TYPE SELECT switch
(4) to TUBE.
b. Place RESISTANCE TEST
switch (5) to 8.
c. Place SYNCHROPHASE
MASTER/MSTR switch (2) to
ENG 2.
d. Momentarily hold PROP
RESYNCHROPHASE/PROP
SYNC switch (3) to RESYNC/INDEX.
Does FUNCTION display (6) indicate 20 to 30 ohms while switch
is held?
(Clutch 3 winding R)
NO
TO SHT 85
Prop Sync Rcpt Pins
3
J268A-15, J267A-45
YES
TO SHT 89
255
a. Place TYPE SELECT switch
(4) to TUBE.
b. Place RESISTANCE TEST
switch (5) to 8.
c. Place SYNCHROPHASE
MASTER/MSTR switch (2) to engine 3.
d. Momentarily hold PROP
RESYNCHROPHASE/PROP
SYNC switch (3) to RESYNC/INDEX.
Does FUNCTION display (6) indicate 20 to 30 ohms while switch
is held?
(Clutch 2 winding R)
NO
TO SHT 87
Prop Sync Rcpt Pins
2
J268A-15, J267A-45
YES
TO SHT 89
Figure 3-5. Synchrophaser System Malfunction (Sheet 83)
61-20-00
3-96
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 84)
61-20-00
3-97
TO 1C-130H-2-61FI-00-1
FROM SHT 83
257
Gain access to and disconnect plug P390C (6)
at valve housing assembly.
Is 60 to 90 ohms resistance present between
pins K and P of valve housing assembly receptacle (5)?
71
261
NO
Replace valve housing assembly in accordance with TO 1C-130H-2-61JG-20-1, 6120-02.
76
YES
258
a. Reconnect plug P390C to valve housing assembly.
b. Gain access to and disconnect plug P398C
(2) at engine firewall.
Is 60 to 90 ohms resistance present between
pins P and V of receptacle J239C (1)?
64
262
NO
Repair open circuit between receptacle
J239C pin P and plug P390C pin P. (See
figure 3-6.)
59
YES
259
a. Reconnect plug P398C at engine firewall.
b. Gain access to terminals of SYNCHROPHASE MASTER/MSTR switch (3).
Is there continuity between switch terminals 4
and 5?
20
263
NO
Replace SYNCHROPHASE MASTER/MSTR
switch.
16
YES
260
Gain access to terminal board TB128A (4).
Is there continuity between terminal board terminal 18 and SYNCHROPHASE MASTER/
MSTR switch terminal 4?
31
264
YES
Repair open circuit between terminal board
terminal 18 and plug P398C pin P. (See
figure 3-6 or 3-7.)
20
NO
265
Repair open circuit. (See figure 3-6 or 3-7.)
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 85)
61-20-00
3-98
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 86)
61-20-00
3-99
TO 1C-130H-2-61FI-00-1
FROM SHT 83
266
Gain access to and disconnect plug P390B (6)
at valve housing assembly.
Is 60 to 90 ohms resistance present between
pins K and P of valve housing assembly receptacle (5)?
71
270
NO
Replace valve housing assembly in accordance with TO 1C-130H-2-61JG-20-1, 6120-02.
76
YES
267
a. Reconnect plug P390B to valve housing assembly.
b. Gain access to and disconnect plug P398B
(2) at engine firewall.
Is 60 to 90 ohms resistance present between
pins P and V of receptacle J239B (1)?
64
271
NO
Repair open circuit between receptacle
J239B pin P and plug P390B pin P. (See
figure 3-6 or 3-7.)
59
YES
268
a. Reconnect plug P398B at engine firewall.
b. Gain access to terminals of SYNCHROPHASE MASTER/MSTR switch (3).
Is there continuity between switch terminals 5
and 6?
16
272
NO
Replace SYNCHROPHASE MASTER/MSTR
switch.
21
YES
269
Gain access to terminal board TB128A (4).
Is there continuity between terminal board terminal 19 and SYNCHROPHASE MASTER/
MSTR switch terminal 6?
32
273
YES
Repair open circuit between terminal board
terminal 19 and plug P398B pin P. (See
figure 3-6 or 3-7.)
21
NO
274
Repair open circuit. (See figure 3-6 or 3-7.)
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 87)
61-20-00
3-100
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 88)
61-20-00
3-101
TO 1C-130H-2-61FI-00-1
FROM SHT 81 OR 83
275
NOTE
During megger checks, an indication of 1999 in both the FUNCTION and AC VOLTS displays is
an acceptable measurement.
a. Place SYNCHROPHASE
MASTER/MSTR switch (5) to
OFF.
b. Place TYPE SELECT switch
(2) to SOLID STATE.
c. Place RESISTANCE TEST
switch (4) to 13.
Does FUNCTION display (1) indicate 0.5 or greater and does AC
VOLTS display (3) indicate 6?
(Control winding megger chk)
Prop
1
2
3
4
NO
TO SHT 91
Sync Rcpt Pins
J267A-35, J267A-45
J268A-25, J267A-45
J267A-37, J267A-45
J268A-27, J267A-45
YES
276
Place RESISTANCE TEST switch
to 14.
Does FUNCTION display indicate
1.0 or greater and does AC
VOLTS display indicate 6?
(Feedback pot megger chk)
Prop
1
2
3
4
NO
TO SHT 99
Sync Rcpt Pins
J267A-12, J267A-45
J268A-2, J267A-45
J268A-5, J267A-45
J267A-14, J267A-45
YES
TO SHT 141
Figure 3-5. Synchrophaser System Malfunction (Sheet 89)
61-20-00
3-102
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 90)
61-20-00
3-103
TO 1C-130H-2-61FI-00-1
FROM SHT 89
277
a. Gain access to and disconnect
plug P390 (3) at valve housing
assembly.
b. Install a jumper wire between
plug pins B and M.
Does FUNCTION display (5) indicate 0.5 or greater and does AC
VOLTS display (4) indicate 6?
281
Remove jumper wire. Replace
valve housing assembly in accordance with TO 1C-130H-261JG-20-1, 61-20-02.
YES
NO
278
a. Remove jumper wire from plug
P390 but do not reconnect plug.
b. Gain access to and disconnect
plug P398 (2) at engine firewall.
c. Install a jumper wire between
plug P398 pins B and X.
Does FUNCTION display indicate
0.5 or greater and does AC
VOLTS display indicate 6?
NO
280
Is an outboard propeller being
troubleshot?
NO
TO SHT 93
YES
YES
TO SHT 95
279
Remove jumper wire from plug
P398 and reconnect plug at engine firewall.
Does FUNCTION display indicate
0.5 or greater and does AC
VOLTS display indicate 6?
282
NO
Repair ground fault between pin
X of receptacle J239 (1) and
plug P390 pin M. (See figure
3-6 or 3-7.)
YES
283
Repair ground fault between pin
B of receptacle J239 (1) and
plug P390 pin B. (See figure 36 or 3-7.)
Figure 3-5. Synchrophaser System Malfunction (Sheet 91)
61-20-00
3-104
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 92)
61-20-00
3-105
TO 1C-130H-2-61FI-00-1
285
FROM SHT 91
284
Remove jumper wire from plug
P398 (1) but do not reconnect
plug.
Does FUNCTION display (5) indicate 0.5 or greater and does AC
VOLTS display (4) indicate 6?
YES
NO
Repair ground fault between
plug P398 pin X and related pin
of receptacle J267A (3) or
J268A (2). (See figure 3-6 or 37.)
Prop
2
3
Rcpt
Pin
J268A-25
J267A-37
286
Repair ground fault between
plug P398 pin B and related pin
of receptacle J267A (3) or
J268A (2). (See figure 3-6 or
3-7.)
Prop
2
3
NOTE
1
MC-130E airplanes.
Figure 3-5. Synchrophaser System Malfunction (Sheet 93)
61-20-00
3-106
Rcpt
Pin
J268A-26
J267A-38
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 94)
61-20-00
3-107
TO 1C-130H-2-61FI-00-1
FROM SHT 91
287
a. Remove jumper wire from plug
P398 (1) but do not reconnect
plug.
b. Gain access to and disconnect
plug P130 (5) at outer wing break.
c. Install a jumper wire between
specified plug pins.
Prop
1
4
NO
TO SHT 97
Plug
Pins
c and d
d and f
Does FUNCTION display (3) indicate 0.5 or greater and does AC
VOLTS display (2) indicate 6?
YES
289
288
Remove jumper wire from plug
P130 and reconnect plug at outer
wing break.
Does FUNCTION display indicate
0.5 or greater and does AC
VOLTS display indicate 6?
YES
NO
Repair ground fault between
plug P398 pin X and related pin
of receptacle J235 (4). (See
figure 3-6 or 3-7.)
Prop
1
4
Rcpt
Pin
c
d
290
Repair ground fault between
plug P398 pin B and related pin
of receptacle J235 (4). (See
figure 3-6 or 3-7.)
Prop
1
4
Figure 3-5. Synchrophaser System Malfunction (Sheet 95)
61-20-00
3-108
Rcpt
Pin
d
f
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 96)
61-20-00
3-109
TO 1C-130H-2-61FI-00-1
292
FROM SHT 95
291
Remove jumper wire from plug
P130/P1139 (5) but do not reconnect plug.
Does FUNCTION display (1) indicate 0.5 or greater and does AC
VOLTS display (2) indicate 6?
NO
YES
Repair ground fault between
specified plug P130/P1139 pin
and related pin of receptacle
J267A (4) or J268A (3). (See
figure 3-6 or 3-7.)
Prop
1
4
Plug
Pin
d
f
Rcpt
Pin
J267A-36
J268A-28
293
Repair ground fault between
specified plug P130/P1139 pin
and related pin of receptacle
J267A (4) or J268A (3). (See
figure 3-6 or 3-7.)
Prop
1
4
NOTE
1
MC-130E airplanes.
Figure 3-5. Synchrophaser System Malfunction (Sheet 97)
61-20-00
3-110
Plug
Pin
c
d
Rcpt
Pin
J267A-35
J268A-27
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 98)
61-20-00
3-111
TO 1C-130H-2-61FI-00-1
FROM SHT 89
294
300
a. Gain access to and disconnect plug
P390 (3) at valve housing assembly.
b. Install a jumper wire between plug
pins C and L.
Does FUNCTION display (5) indicate
1.0 or greater and does AC VOLTS display (4) indicate 6?
297
YES
Remove jumper wire and install it between plug pins C and N.
Does FUNCTION display indicate 1.0 or
greater and does AC VOLTS display indicate 6?
NO
Remove jumper
wire. Replace
YES valve housing in
accordance with
TO 1C-130H-261JG-20-1, 61-2002.
NO
298
301
a. Remove jumper wire from plug P390.
b. Gain access to and disconnect plug
P398 (2) at engine firewall.
c. Install jumper wire between plug
P398 pins C and N.
Does FUNCTION display indicate 1.0 or
greater and does AC VOLTS display indicate 6?
Remove jumper
wire. Repair
YES ground fault between pin N of receptacle J239 (1)
and plug P390 pin
N. (See figure 3-6
or 3-7.)
NO
TO SHT 101
302
299
295
Remove jumper wire and install it between plug pins C and N.
Does FUNCTION display indicate 1.0 or
greater and does AC VOLTS display indicate 6?
NO
YES
a. Remove jumper wire from plug P390.
b. Gain access to and disconnect plug
P398 (2) at engine firewall.
Does FUNCTION display indicate 1.0 or
greater and does AC VOLTS display indicate 6?
Repair ground fault
YES between pin C of
receptacle J239 (1)
and plug P390 pin
C. (See figure 3-6
or 3-7.)
NO
TO SHT 103
296
303
a. Remove jumper wire from plug P390.
b. Gain access to and disconnect plug
P398 (2) at engine firewall.
c. Install jumper wire between plug
P398 pins C and W.
Does FUNCTION display indicate 1.0 or
greater and does AC VOLTS display indicate 6?
YES
NO
TO SHT 105
Figure 3-5. Synchrophaser System Malfunction (Sheet 99)
61-20-00
3-112
Remove jumper
wire. Repair
ground fault between pin W of receptacle J239 (1)
and plug P390 pin
L. (See figure 3-6
or 3-7.)
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 100)
61-20-00
3-113
TO 1C-130H-2-61FI-00-1
306
FROM SHT 99
304
Is an outboard propeller being
troubleshot?
NO
YES
Remove jumper wire. Repair
ground fault between pin N of
plug P398 (1) and related pin of
receptacle J268A (4). (See figure 3-6 or 3-7.)
Prop
2
3
Rcpt
Pin
2
5
305
a. Remove jumper wire from plug
P398 (1).
b. Gain access to and disconnect
plug P130/P1139 (7) at outer
wing break.
c. Install jumper wire between
specified plug P130/P1139 pins.
Prop
1
4
Plug
Pin
h and k
e and h
307
NO
Remove jumper wire. Repair
ground fault between plug
P130/P1139 pin h and related
pin of receptacle J267A (5).
(See figure 3-6 or 3-7.)
Prop
1
4
Rcpt
Pin
11
14
Does FUNCTION display (2) indicate 1.0 or greater and does AC
VOLTS display (3) indicate 6?
YES
308
Remove jumper wire. Repair
ground fault between pin h of
receptacle J235/J935 (6) and
plug P398 pin N. (See figure 36 or 3-7.)
NOTE
1
MC-130E airplanes.
Figure 3-5. Synchrophaser System Malfunction (Sheet 101)
61-20-00
3-114
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 102)
61-20-00
3-115
TO 1C-130H-2-61FI-00-1
311
FROM SHT 99
309
Is an outboard propeller being
troubleshot?
NO
Repair ground fault between pin
C of plug P398 (1) and related
pin of receptacle J268A (4).
(See figure 3-6 or 3-7.)
Rcpt
Pin
1
6
Prop
2
3
YES
312
310
Gain access to and disconnect
plug P130/P1139 (6) at outer
wing break.
Does FUNCTION display (2) indicate 1.0 or greater and does AC
VOLTS display (3) indicate 6?
YES
NO
Repair ground fault between
specified plug P130/P1139 pin
and related pin of receptacle
J267A (5). (See figure 3-6 or
3-7.)
Prop
1
4
Plug
Pin
k
e
Rcpt
Pin
12
13
313
Repair ground fault between pin
C of plug P398 (1) and related
plug P130/P1139 pin. (See figure 3-6 or 3-7.)
Prop
1
4
NOTE
1
MC-130E airplanes.
Figure 3-5. Synchrophaser System Malfunction (Sheet 103)
61-20-00
3-116
Plug
Pin
k
e
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 104)
61-20-00
3-117
TO 1C-130H-2-61FI-00-1
316
FROM SHT 99
314
Is an outboard propeller being
troubleshot?
NO
YES
Remove jumper wire. Repair
ground fault between pin W of
plug P398 (1) and related pin of
receptacle J268A (4). (See figure 3-6 or 3-7.)
Prop
2
3
Rcpt
Pin
3
4
315
a. Remove jumper wire from plug
P398 (1).
b. Gain access to and disconnect
plug P130/P1139 (7) at outer
wing break.
c. Install jumper wire between
specified plug P130/P1139 pins.
Prop
1
4
Plug
Pin
j and k
e and j
317
NO
Remove jumper wire. Repair
ground fault between plug
P130/P1139 pin j and related
pin of receptacle J267A (5).
(See figure 3-6 or 3-7.)
Prop
1
4
Rcpt
Pin
10
15
Does FUNCTION display (2) indicate 1.0 or greater and does AC
VOLTS display (3) indicate 6?
YES
318
Remove jumper wire. Repair
ground fault between pin j of receptacle J235/J935 (6) and plug
P398 pin W. (See figure 3-6 or
3-7.)
NOTE
1
MC-130E airplanes.
Figure 3-5. Synchrophaser System Malfunction (Sheet 105)
61-20-00
3-118
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 106)
61-20-00
3-119
TO 1C-130H-2-61FI-00-1
FROM SHT 81
319
Gain access to and disconnect
plug P390 (3) at valve housing
assembly.
Is 60 to 90 ohms resistance present between pins K and P of
valve housing assembly receptacle (4)?
71
322
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
76
YES
320
a. Reconnect plug P390 to valve
housing assembly.
b. Gain access to and disconnect
plug P398 (2) at engine firewall.
Is 60 to 90 ohms resistance present between plug pins P and V?
64
323
NO
Repair open circuit between pin
P of receptacle J239 (1) and
plug P390 pin P. (See figure 36 or 3-7.)
59
YES
321
a. Reconnect plug P398 at engine
firewall.
b. Gain access to and disconnect
plug P130/P1139 (7) at outer
wing break.
Is 60 to 90 ohms resistance present between pin m of receptacle
J235/J935 (6) and airplane
ground?
324
NO
Repair open circuit between receptacle J235/J935 pin m and
plug P398 pin P. (See figure 36 or 3-7.)
52
YES
325
Repair open circuit between
plug P130/P1139 pin m and terminal 9 of terminal board TB1C
(5). (See figure 3-6 or 3-7.)
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 107)
61-20-00
3-120
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 108)
61-20-00
3-121
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 1C130H-2-71JG-00-1, 71-00-10; TO 1C-130(A)H-271JG-00-1, 71-00-10; or TO 1C-130(M)H-2-71JG00-1, 71-00-10.
b. If necessary, perform Preparation C.
c. If necessary, place propeller governor control
switches (5) to NORMAL/NORM.
d. Place RESISTANCE TEST switch (4) to 7.
Does FUNCTION display (1) indicate 0.3 to 10
ohm?
(Pulse gen R)
Prop
1
2
3
4
NO
TO SHT 111
Sync Rcpt Pins
J267A-17, J267A-23
J268A-11, J268A-18
J268A-17, J268A-21
J267A-25, J267A-43
YES
327
NOTE
During megger checks, an indication of 1999 in
both the FUNCTION and AC VOLTS 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 to 12.
Does FUNCTION display (1) indicate 1.0 or
greater and does AC VOLTS display (3) indicate
6?
(Pulse gen megger chk)
Prop
1
2
3
4
NO
TO SHT 125
Sync Rcpt Pins
J267A-23, J267A-45
J268A-18, J267A-45
J268A-17, J267A-45
J267A-25, J267A-45
YES
TO SHT 141
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 3-5. Synchrophaser System Malfunction (Sheet 109)
61-20-00
3-122
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 110)
61-20-00
3-123
TO 1C-130H-2-61FI-00-1
FROM SHT 109
328
330
Gain access to and disconnect
plug P392 (2) at pump housing.
Is 0.3 to 0.5 ohm resistance present between pins A and B of
valve housing assembly receptacle (3)?
77
NO
Remove pulse generator (4) in accordance with TO 1C-130H-261JG-20-1, 61-20-10.
Is 0.3 to 0.5 ohm resistance present between the two pulse generator pins?
78
79
YES
332
NO
Replace pulse generator in accordance with TO 1C-130H-261JG-20-1, 61-20-10.
80
YES
333
Repair or replace pulse generator wiring on pump housing (5).
329
331
a. Reconnect plug P392 to pump
housing.
b. Gain access to and disconnect
plug P396 (6) at engine firewall.
Is 0.3 to 0.5 ohm resistance present between pins A and B of receptacle J241 (1)?
65
66
YES
NO
a. Gain access to and disconnect
plug P392 at pump housing.
b. Install a jumper wire between
plug pins A and E (ground).
Is resistance between receptacle
J241 pins A and E less than 1
ohm?
334
NO
Remove jumper wire. Repair
wiring fault between receptacle
J241 pin A and plug P392 pin
A. (See figure 3-6 or 3-7.)
65
YES
TO SHT 113
335
Remove jumper wire. Repair
wiring fault between receptacle
J241 pin B and plug P392 pin
B. (See figure 3-6 or 3-7.)
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 111)
61-20-00
3-124
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 112)
61-20-00
3-125
TO 1C-130H-2-61FI-00-1
FROM SHT 111
336
Is airplane being troubleshot
AF90-1057 and up?
YES
TO SHT 115
NO
337
Is an outboard propeller being
troubleshot?
NO
TO SHT 121
YES
338
a. Reconnect plug P396 (1) at engine firewall.
b. Gain access to and disconnect
plug P429 (3) at outer wing break.
Is 0.3 to 0.7 ohm resistance present between pins A and B of receptacle J269 (2)?
53
YES
TO SHT 123
54
NO
339
a. Gain access to and disconnect
plug P396 at engine firewall.
b. Install a jumper wire between
plug pins A and E (ground).
Is resistance between receptacle
J269 pin A and airplane ground
less than 1 ohm?
340
NO
Remove jumper wire. Repair
wiring fault between receptacle
J269 pin A and plug P396 pin
A. (See figure 3-6.)
53
YES
341
Remove jumper wire. Repair
wiring fault between receptacle
J269 pin B and plug P396 pin
B. (See figure 3-6.)
NOTE
See figure 3-6 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 113)
61-20-00
3-126
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 114)
61-20-00
3-127
TO 1C-130H-2-61FI-00-1
FROM SHT 113
343
342
a. Reconnect plug P396 (1) at engine firewall.
b. Gain access to terminal board
TB105AG (2).
Is 0.3 to 0.7 ohm resistance present between specified terminals?
Prop
1
TB
Term
1 and 2
2
3 and 4
3
5 and 6
4
7 and 8
YES
Test
Points
NO
43
42
43
42
43
42
43
42
a. Gain access to and disconnect
plug P396 at engine firewall.
b. Install a jumper wire between
plug pins A and E (ground).
c. Remove junction box from synchrophaser rack.
Is resistance between specified
pin of receptacle J267A (4) or
J268A (3) and airplane ground
less than 1 ohm?
Prop
Rcpt
Pin
Test
Point
1
J267A-23
2
J268A-18
3
J268A-17
4
J267A-25
39
39
344
NO
Remove jumper wire. Repair
wiring fault between specified
receptacle pin and related terminal board TB105AG terminal.
(See figure 3-6 or 3-7.)
Prop
1
2
3
4
Rcpt
Pin
J267A-23
J268A-18
J268A-17
J267A-25
TB
Term
2
4
6
8
39
39
YES
TO SHT 117
345
Remove jumper wire. Repair
wiring fault between specified
receptacle pin and related terminal board TB105AG terminal.
(See figure 3-6 or 3-7.)
Prop
1
2
3
4
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 115)
61-20-00
3-128
Rcpt
Pin
J267A-17
J268A-11
J268A-21
J267A-43
TB
Term
1
3
5
7
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 116)
61-20-00
3-129
TO 1C-130H-2-61FI-00-1
348
FROM SHT 115
346
Is an outboard propeller being
troubleshot?
NO
YES
a. Gain access to and disconnect
plug P396 (1) at engine firewall.
b. Install a jumper wire between
plug pins A and E (ground).
Is resistance between specified
terminal of terminal board
TB105AG (2) and airplane ground
less than 1 ohm?
Prop
TB
Term
2
4
3
6
350
NO
Test
Point
Remove jumper wire. Repair
wiring fault between plug P396
pin A and related terminal
board TB105AG terminal. (See
figure 3-6 or 3-7.)
Prop
2
3
42
TB
Term
4
6
42
YES
351
Remove jumper wire. Repair
wiring fault between plug P396
pin B and related terminal
board TB105AG terminal. (See
figure 3-6 or 3-7.)
Prop
2
3
TB
Term
3
5
349
347
Gain access to and disconnect
plug P429/P1225 (3) at outer
wing break.
Is 0.3 to 0.7 ohm resistance present between pins A and B of receptacle J269/J660 (4)?
53
54
YES
NO
a. Gain access to and disconnect
plug P396 at engine firewall.
b. Install a jumper wire between
plug pins A and E (ground).
Is resistance between receptacle
J269/J660 pin A and airplane
ground less than 1 ohm?
352
NO
Remove jumper wire. Repair
wiring fault between receptacle
J269/J660 pin A and plug P396
pin A. (See figure 3-6 or 3-7.)
53
YES
TO SHT 119
353
Remove jumper wire. Repair
wiring fault between receptacle
J269/J660 pin B and plug P396
pin B. (See figure 3-6 or 3-7.)
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 117)
61-20-00
3-130
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 118)
61-20-00
3-131
TO 1C-130H-2-61FI-00-1
FROM SHT 117
354
a. Gain access to and disconnect
plug P429/P1225 (1) at outer
wing break.
b. Install a jumper wire between
plug pin A and airplane ground.
Is resistance between specified
terminal of terminal board
TB105AG (2) and airplane ground
less than 1 ohm?
Prop
TB
Term
1
2
4
8
Test
Point
42
355
NO
Remove jumper wire. Repair
wiring fault between plug P429/
P1225 pin A and related terminal board TB105AG terminal.
(See figure 3-6 or 3-7.)
Prop
1
4
TB
Term
2
8
42
YES
356
Remove jumper wire. Repair
wiring fault between plug P429/
P1225 pin B and related terminal board TB105AG terminal.
(See figure 3-6 or 3-7.)
Prop
1
4
NOTE
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 119)
61-20-00
3-132
TB
Term
1
7
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 120)
61-20-00
3-133
TO 1C-130H-2-61FI-00-1
FROM SHT 113
357
a. Install a jumper wire between
pins A and E (ground) of plug
P396 (1).
b. Remove junction box from synchrophaser rack.
Is resistance on specified pin of
receptacle J268A (2) less than 1
ohm?
Prop
Rcpt
Pin
2
18
3
17
Test
Point
39
358
NO
Remove jumper wire. Repair
wiring fault between plug P396
pin A and related receptacle
J268A pin. (See figure 3-6.)
Prop
2
3
Rcpt
Pin
18
17
39
YES
359
Remove jumper wire. Repair
wiring fault between plug P396
pin B and related receptacle
J268A pin. (See figure 3-6).
Prop
2
3
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 121)
61-20-00
3-134
Rcpt
Pin
11
21
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 122)
61-20-00
3-135
TO 1C-130H-2-61FI-00-1
FROM SHT 113
360
a. Install a jumper wire between
pin A of plug P429 (1) and airplane ground.
b. Remove junction box from synchrophaser rack.
Is resistance on specified pin of
receptacle J267A (2) less than 1
ohm?
Prop
Rcpt
Pin
1
23
4
25
Test
Point
39
361
NO
Remove jumper wire. Repair
wiring fault between plug P429
pin A and related receptacle
J267A pin. (See figure 3-6.)
Prop
1
4
Rcpt
Pin
23
25
39
YES
362
Remove jumper wire. Repair
wiring fault between plug P429
pin B and related receptacle
J267A pin. (See figure 3-6).
Prop
1
4
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 123)
61-20-00
3-136
Rcpt
Pin
17
43
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 124)
61-20-00
3-137
TO 1C-130H-2-61FI-00-1
366
FROM SHT 109
363
a. Gain access to and disconnect
plug P392 (2) at pump housing.
b. Install a jumper wire between
plug pins A and B.
Does FUNCTION display (5) indicate 1.0 or greater and does AC
VOLTS display (4) indicate 6?
YES
NO
a. Remove jumper wire from plug
P392 and reconnect plug at pump
housing.
b. Remove pulse generator (3) in
accordance with TO 1C-130H-261JG-20-1, 61-20-10.
c. Install a jumper wire between
the two pins of the pulse generator wiring harness where the
pulse generator connects.
Does FUNCTION display indicate
1.0 or greater and does AC
VOLTS display indicate 6?
368
YES Remove jumper wire. Replace
pulse generator in accordance
with TO 1C-130H-2-61JG-20-1,
61-20-10.
NO
369
Repair or replace pulse generator wiring on pump housing.
364
a. Remove jumper wire from plug
P392 but do not reconnect plug.
b. Gain access to and disconnect
plug P396 (6) at engine firewall.
c. Install a jumper wire between
plug P396 pins A and B.
Does FUNCTION display indicate
1.0 or greater and does AC
VOLTS display indicate 6?
367
YES
Remove jumper wire from plug
P396 and reconnect plug at engine firewall.
Does FUNCTION display indicate
1.0 or greater and does AC
VOLTS display indicate 6?
370
NO
Repair ground fault between pin
A of receptacle J241 (1) and
plug P392 pin A. (See figure 36 or 3-7.)
YES
NO
371
Repair ground fault between pin
B of receptacle J241 (1) and
plug P392 pin B. (See figure 36 or 3-7.)
365
Is an outboard propeller being
troubleshot?
NO
TO SHT 127
YES
TO SHT 133
Figure 3-5. Synchrophaser System Malfunction (Sheet 125)
61-20-00
3-138
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 126)
61-20-00
3-139
TO 1C-130H-2-61FI-00-1
FROM SHT 125
372
Is airplane being troubleshot
AF90-1057 and up?
YES
TO SHT 129
NO
374
373
Remove jumper wire from plug
P396 (1) but do not reconnect
plug.
Does FUNCTION display (4) indicate 1.0 or greater and does AC
VOLTS display (3) indicate 6?
YES
NO
Repair ground fault between
plug P396 pin A and related pin
of receptacle J268A (2). (See
figure 3-6.)
Prop
2
3
Rcpt
Pin
18
17
375
Repair ground fault between
plug P396 pin B and related pin
of receptacle J268A (2). (See
figure 3-6.)
Prop
2
3
NOTE
1
MC-130E airplanes.
Figure 3-5. Synchrophaser System Malfunction (Sheet 127)
61-20-00
3-140
Rcpt
Pin
11
21
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 128)
61-20-00
3-141
TO 1C-130H-2-61FI-00-1
FROM SHT 127
376
Remove jumper wire from plug P396 (1)
but do not reconnect plug.
Does FUNCTION display (2) indicate 1.0 or
greater and does AC VOLTS display (3) indicate 6?
YES
TO SHT 131
NO
377
Gain access to terminal board TB105AG
(4) and disconnect specified wire from
specified terminal. (Leave remaining two
wires securely attached.)
Prop
2
3
TB
Term
4
6
Wire No.
2K95D20
3K95D20
379
YES
Repair ground fault on specified wire.
(See figure 3-6 or 3-7.)
Prop
2
3
Wire No.
2K95D20
3K95D20
Does FUNCTION display indicate 1.0 or
greater and does AC VOLTS display indicate 6?
NO
378
380
Disconnect remaining wires from specified
terminal board TB105AG terminal.
Prop
2
3
TB
Term
4
6
Does FUNCTION display indicate 1.0 or
greater and does AC VOLTS display indicate 6?
YES
Repair ground fault between plug P396
pin A and related terminal board
TB105AG terminal. (See figure 3-6 or 37.)
TB
Term
4
6
Prop
2
3
NO
381
Repair ground fault between specified
terminal board TB105AG terminal and related pin of receptacle J268A (5). (See
figure 3-6 or 3-7.)
Prop
2
3
TB
Term
4
6
NOTE
1
MC-130E airplanes.
Figure 3-5. Synchrophaser System Malfunction (Sheet 129)
61-20-00
3-142
Rcpt
Pin
18
17
TO 1C-130H-2-61FI-00-1
Figure 3-5.
Synchrophaser System Malfunction (Sheet 130)
61-20-00
3-143
TO 1C-130H-2-61FI-00-1
FROM SHT 129
382
a. Reinstall jumper wire between
pins A and B of plug P396 (1).
b. Gain access to terminal board
TB105AG (4) and disconnect
specified wire from specified terminal. (Leave remaining two
wires securely attached.)
Prop
2
3
Wire No.
2K97D20
3K97D20
384
YES
TB
Term
3
5
Remove jumper wire. Repair
ground fault on specified wire.
(See figure 3-6 or 3-7.)
Prop
2
3
Wire No.
2K97D20
3K97D20
Does FUNCTION display (2) indicate 1.0 or greater and does AC
VOLTS display (3) indicate 6?
NO
383
385
Disconnect remaining wires from
specified terminal board TB105AG
terminal.
Prop
2
3
TB
Term
3
5
NO
Does FUNCTION display indicate
1.0 or greater and does AC
VOLTS display indicate 6?
Remove jumper wire. Repair
ground fault between plug P396
pin B and related terminal
board TB105AG terminal. (See
figure 3-6 or 3-7.)
TB
Term
3
5
Prop
2
3
YES
386
Remove jumper wire. Repair
ground fault between specified
terminal board TB105AG terminal and related pin of receptacle J268A (5). (See figure 3-6
or 3-7.)
Prop
2
3
NOTE
1
MC-130E airplanes.
Figure 3-5. Synchrophaser System Malfunction (Sheet 131)
61-20-00
3-144
TB
Term
3
5
Rcpt
Pin
11
21
TO 1C-130H-2-61FI-00-1
Figure 3-5.
Synchrophaser System Malfunction (Sheet 132)
61-20-00
3-145
TO 1C-130H-2-61FI-00-1
FROM SHT 125
387
Is airplane being troubleshot a
year model AF90-1057 and up?
YES
TO SHT 135
NO
388
a. Remove jumper wire from plug
P396 (1) but do not reconnect
plug.
b. Gain access to and disconnect
plug P429 (5) at outer wing break.
c. Install a jumper wire between
plug P429 pins A and B.
Does FUNCTION display (3) indicate 1.0 or greater and does AC
VOLTS display (2) indicate 6?
NO
TO SHT 139
YES
389
Remove jumper wire from plug
P429 and reconnect plug at outer
wing break.
Does FUNCTION display indicate
1.0 or greater and does AC
VOLTS display indicate 6?
390
YES
Repair ground fault between pin
B of receptacle J269 (4) and
plug P396 pin B. (See figure 36).
NO
391
Repair ground fault between pin
A of receptacle J269 (4) and
plug P396 pin A. (See figure 36.)
Figure 3-5. Synchrophaser System Malfunction (Sheet 133)
61-20-00
3-146
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 134)
61-20-00
3-147
TO 1C-130H-2-61FI-00-1
FROM SHT 133
392
Remove jumper wire from plug P396 (1) but do not reconnect
plug.
Does FUNCTION display (2) indicate 1.0 or greater and does AC
VOLTS display (3) indicate 6?
YES
TO SHT 137
NO
393
Gain access to terminal board TB105AG (4) and disconnect
specified wire from specified terminal. (Leave remaining two
wires securely attached.)
Prop
1
4
Wire No.
1K95E20
4K95E20
396
Repair ground fault on specified
wire. (See figure 3-6 or 3-7.)
YES
TB Term
2
8
Prop
1
4
Wire No.
1K95E20
4K95E20
Does FUNCTION display indicate 1.0 or greater and does AC
VOLTS display indicate 6?
NO
394
397
Disconnect remaining wires from
specified terminal board TB105AG
terminal.
Prop
1
4
TB Term
2
8
Does FUNCTION display indicate
1.0 or greater and does AC
VOLTS display indicate 6?
395
YES
a. Reconnect all wires to terminal
board TB105AG.
b. Gain access to and disconnect
plug P429/P1225 (6) at outer
wing break.
Does FUNCTION display indicate
1.0 or greater and does AC
VOLTS display indicate 6?
YES
NO
Repair ground fault between
plug P429/P1225 pin A and related terminal board TB105AG
terminal. (See figure 3-6 or 37.)
Prop
1
4
TB
Term
2
8
NO
398
Repair ground fault between pin A of receptacle J269/J660 (7) and plug P396 pin A.
(See figure 3-6 or 3-7.)
399
Repair ground fault between specified terminal board TB105AG terminal and related pin
of receptacle J267A (5). (See figure 3-6 or
3-7.)
Prop
1
4
TB
Term
2
8
Figure 3-5. Synchrophaser System Malfunction (Sheet 135)
61-20-00
3-148
Rcpt
Pin
23
25
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 136)
61-20-00
3-149
TO 1C-130H-2-61FI-00-1
FROM SHT 135
400
a. Reinstall jumper wire between pins A
and B of plug P396 (1).
b. Gain access to terminal board TB105AG
(4) and disconnect specified wire from
specified terminal. (Leave remaining two
wires securely attached.)
403
YES
Prop
1
4
TB
Term
1
7
Wire No.
1K97E20
4K97E20
Remove jumper wire. Repair
ground fault on specified wire.
(See figure 3-6 or 3-7.)
Prop
1
4
Wire No.
1K97E20
4K97E20
Does FUNCTION display (2) indicate 1.0 or
greater and does AC VOLTS display (3) indicate 6?
NO
401
404
Disconnect remaining wires from specified
terminal board TB105AG terminal.
Prop
1
4
TB
Term
1
7
YES
Does FUNCTION display indicate 1.0 or
greater and does AC VOLTS display indicate 6?
Remove jumper wire. Repair
ground fault between specified
terminal board TB105AG terminal and related pin of receptacle J267A (5). (See figure 3-6
or 3-7.)
Prop
1
4
TB
Term
1
7
Rcpt
Pin
17
43
NO
405
402
a. Remove jumper wire from plug P396 but
do not reconnect plug.
b. Gain access to and disconnect plug
P429/P1225 (6) at outer wing break.
c. Install jumper wire between plug P429/
P1225 pins A and B.
Does FUNCTION display indicate 1.0 or
greater and does AC VOLTS display indicate 6?
NO
Remove jumper wire. Repair
ground fault between plug
P429/P1225 pin B and related
terminal board TB105AG terminal. (See figure 3-6 or 3-7.)
Prop
1
4
TB
Term
1
7
YES
406
Remove jumper wire. Repair
ground fault between pin B of
receptacle J269/J660 (7) and
plug P396 pin B. (See figure 36 or 3-7.)
Figure 3-5. Synchrophaser System Malfunction (Sheet 137)
61-20-00
3-150
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 138)
61-20-00
3-151
TO 1C-130H-2-61FI-00-1
FROM SHT 133
408
407
Remove jumper wire from plug
P429 (4) but do not reconnect
plug.
Does FUNCTION display (1) indicate 1.0 or greater and does AC
VOLTS display (2) indicate 6?
NO
YES
Repair ground fault between
plug P429 pin B and related pin
of receptacle J267A (3). (See
figure 3-6.)
Prop
1
4
Rcpt
Pin
17
43
409
Repair ground fault between
plug P429 pin A and related pin
of receptacle J267A (3). (See
figure 3-6.)
Prop
1
4
NOTE
1
MC-130E airplanes.
Figure 2-5. Synchrophaser System Malfunction (Sheet 139)
61-20-00
3-152
Rcpt
Pin
23
25
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 140)
61-20-00
3-153
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.
c. Close PROP SYNCHRO PHASER and SYNCHRO PHASER circuit breakers.
d. Place FUNCTION SELECT switch (6) to DCV.
e. Place TEST SELECT switch (5) to 2.
Does FUNCTION display (7) indicate 11 to 14 volts?
(Feedback pot V supply)
Prop
1
2
3
4
413
NO
Sync Rcpt Pins
J267A-12, J267A-45
J268A-1, J267A-45
J268A-6, J267A-45
J267A-13, J267A-45
Replace propeller
synchrophaser in
accordance with
TO 1C-130H-261JG-20-1, 61-2013.
YES
411
Place TEST SELECT switch to 3.
Does FUNCTION display indicate -11 to -14 volts?
(Feedback pot -V supply)
414
NO
Prop
1
2
3
4
Sync Rcpt Pins
J267A-10, J267A-45
J268A-3, J267A-45
J268A-4, J267A-45
J267A-15, J267A-45
Replace propeller
synchrophaser in
accordance with
TO 1C-130H-261JG-20-1, 61-2013.
YES
412
Place TEST SELECT switch to 4.
Does FUNCTION display indicate -11 to -15 volts?
(Anticipator pot -V supply)
415
NO
Prop
1
2
3
4
Sync Rcpt Pins
J267A-18, J267A-45
J268A-19, J267A-45
J268A-20, J267A-45
J267A-19, J267A-45
Replace propeller
synchrophaser in
accordance with
TO 1C-130H-261JG-20-1, 61-2013.
YES
TO SHT 143
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 3-5. Synchrophaser System Malfunction (Sheet 141)
61-20-00
3-154
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 142)
61-20-00
3-155
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
volts?
(Anticipator pot output in T/O pos)
Prop
1
2
3
4
419
NO
Sync Rcpt Pins
J267A-22, J267A-45
J267A-20, J267A-45
J267A-21, J267A-45
J267A-9, J267A-45
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
YES
417
Move throttle to FLIGHT IDLE/FLT IDLE.
Does FUNCTION display indicate -8.5 to -12
volts?
(Anticipator pot output)
Prop
1
2
3
4
420
NO
Sync Rcpt Pins
J267A-22, J267A-45
J267A-20, J267A-45
J267A-21, J267A-45
J267A-9, J267A-45
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
YES
418
a. Rapidly advance throttles to TAKE OFF.
b. Place PROP CHANNEL SELECT switch (3) to
next highest or lowest position.
c. Return PROP CHANNEL SELECT switch to
previous position and record the indication in AC
VOLTS display (2).
d. Rapidly retard throttles to FLIGHT IDLE/FLT
IDLE and note indication in AC VOLTS display.
Is the difference in the two indications at least 2
volts?
(Speed bias control winding)
Prop
1
2
3
4
421
NO
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
Sync Rcpt Pins
J267A-35, J267A-36
J268A-25, J268A-26
J267A-37, J267A-38
J268A-27, J268A-28
YES
TO SHT 145
Figure 3-5. Synchrophaser System Malfunction (Sheet 143)
61-20-00
3-156
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 144)
61-20-00
3-157
TO 1C-130H-2-61FI-00-1
FROM SHT 143
422
Place TEST SELECT switch (3) to
6.
Does AC VOLTS display (2) indicate 90 to 130 volts?
(Speed bias ref winding)
Prop
1
2
3
4
424
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
NO
Sync Rcpt Pins
J267A-40, J267A-45
J268A-23, J267A-45
J268A-24, J267A-45
J267A-39, J267A-45
YES
423
a. Start engines in accordance
with TO 1C-130H-2-71JG-00-1,
71-00-10; TO 1C-130(A)H-271JG-00-1, 71-00-10; or TO 1C130(M)H-2-71JG-00-1, 71-00-10.
b. Place FUNCTION SELECT
switch (4) to TACH RPM %.
Does FUNCTION display (1) indicate 99.8 to 100.2?
(Tach gen output)
Prop
1
2
3
4
NO
TO SHT 147
Sync Rcpt Pins
J267A-26, J267A-24
J267A-28, J267A-29
J267A-30, J267A-32
J267A-41, J267A-42
YES
TO SHT 149
Figure 3-5. Synchrophaser System Malfunction (Sheet 145)
61-20-00
3-158
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 146)
61-20-00
3-159
TO 1C-130H-2-61FI-00-1
FROM SHT 1 OR 145
425
Is there a flashing 6 in FUNCTION
display (1)?
427
Place FUNCTION SELECT switch
(2) to PROP RPM %.
Does RPM difference between TACH
RPM % indication and PROP RPM
% indication in FUNCTION display
exceed 1 percent?
NO
YES
428
YES Fault is in tachometer
system. Go to TO 1C130H-2-70FI-00-1-1 and
continue troubleshooting.
NO
429
Adjust propeller mechanical
governing speed in accordance
with TO 1C-130H-2-61JG-10-1,
61-10-03.
426
a. Shut down engines in accordance with TO 1C-130H2-71JG-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 accordance 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 receptacle
J267A (3) and related terminals of terminal board TB1C
(4)?
Prop
Rcpt
Pin
TB
Term
24
1
10
1
26
2
28
3
29
4
30
5
32
6
41
7
42
8
Test
Points
2
3
4
9
12
11
10
9
12
11
10
9
12
11
10
9
12
11
430
YES
Fault is in tachometer system.
Go to TO 1C-130H-2-70FI-00-11 and continue troubleshooting.
NO
431
Repair applicable open circuit.
(See figure 3-6 or 3-7.)
NOTE
1
2.
MC-130E airplanes.
See figure 3-6 or 3-7 for:
Figure 3-5. Synchrophaser System Malfunction (Sheet 147)
61-20-00
3-160
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 148)
61-20-00
3-161
TO 1C-130H-2-61FI-00-1
FROM SHT 145
436
432
Does AC VOLTS display (3) indicate 17 to 30?
NO
Fault is in tachometer system.
Go to TO 1C-130H-2-70FI-00-11 and continue troubleshooting.
YES
433
Place FUNCTION SELECT switch
(5) to PROP RPM %.
Does FUNCTION display (1) indicate 99.8 to 100.2?
(Pulse gen output)
Prop
1
2
3
4
437
Adjust clearance between pulse
generator and permanent magnet in accordance with TO 1C130H-2-61JG-20-1, 61-20-10.
NO
Sync Rcpt Pins
J267A-23, J267A-17
J268A-18, J268A-11
J268A-17, J268A-21
J267A-25, J267A-43
YES
434
Does AC VOLTS display indicate
1.2 to 5.0 and is - PULSE POLARITY indicator light (2) on?
YES
NO
435
Is the - PULSE POLARITY indicator light on?
438
YES Replace permanent magnet in
accordance with TO 1C-130H2-61JG-20-1, 61-20-10.
NO
TO SHT 151
439
Polarity of pulse generator (4) is
reversed. Check pulse generator for reversed wiring or improper magnet orientation and
repair as required.
Figure 3-5. Synchrophaser System Malfunction (Sheet 149)
61-20-00
3-162
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 150)
61-20-00
3-163
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?
(Pulse gen output)
Prop
1
2
3
4
442
NO
Sync Rcpt Pins
J267A-23, J267A-17
J268A-18, J268A-11
J268A-17, J268A-21
J267A-25, J267A-43
Replace pulse generator in accordance
with TO 1C-130H-2-61JG-20-1, 61-20-10.
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 MECH
GOV/MECH.
d. Place applicable SPEED DERIVATIVE switch (3) to
OUT.
e. Place propeller governor control switch to NORMAL/
NORM.
f. Record voltage indication in AC VOLTS display.
g. Compare the indications of steps b and f.
Are the values the same?
(Tach gen output)
Prop
1
2
3
4
443
NO
Fault is in tachometer system. Go to TO
1C-130H-2-70FI-00-1-1 and continue
troubleshooting.
Sync Rcpt Pins
J267A-26, J267A-24
J267A-28, J267A-29
J267A-30, J267A-32
J267A-41, J267A-42
YES
444
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1,
61-20-13.
Figure 3-5. Synchrophaser System Malfunction (Sheet 151)
61-20-00
3-164
TO 1C-130H-2-61FI-00-1
Figure 3-5. Synchrophaser System Malfunction (Sheet 152)
61-20-00
3-165/(3-166 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-6. Synchrophaser System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 1 of 5)
61-20-00
F3-6
3-167/(3-168 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-6. Synchrophaser System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 2)
61-20-00
F3-6
3-169/(3-170 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-6. Synchrophaser System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 3)
61-20-00
F3-6
3-171/(3-172 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-6. Synchrophaser System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 4)
61-20-00
F3-6
3-173/(3-174 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-6. Synchrophaser System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 5)
61-20-00
F3-6
3-175/(3-176 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-7. Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)
(Sheet 1 of 5)
61-20-00
F3-7
3-177/(3-178 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-7. Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)
(Sheet 2)
61-20-00
F3-7
3-179/(3-180 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-7. Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)
(Sheet 3)
61-20-00
F3-7
3-181/(3-182 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-7. Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)
(Sheet 4)
61-20-00
F3-7
3-183/(3-184 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-7. Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)
(Sheet 5)
61-20-00
F3-7
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
F3-8
3-187/(3-188 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-8. Synchrophaser Adapter Unit Electrical Schematic Diagram
(Sheet 2)
61-20-00
F3-8
3-189/(3-190 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-9. Synchrophaser System Simplified Electrical Schematic
Diagram
61-20-00
F3-9
3-191/(3-192 blank)
TO 1C-130H-2-61FI-00-1
Figure 3-10. In-line Disconnects Location Diagram (Airplanes AF92-1094,
AF92-1095, AF92-2104, and AF93-1036 and Up)
61-20-00
F3-10
3-193/(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 any
synchrophaser system malfunction. Contents of this section include a malfunction index, a fault
code index, preparation procedures to be performed prior to fault isolation, a fault isolation
diagram (the actual troubleshooting procedures), locator illustrations for hardware referenced in
the fault isolation diagram, and schematic diagrams.
4-2. MALFUNCTION INDEX. The malfunction index (table 4-1) is used when a malfunction is
encountered during ground maintenance and no numeric fault code was determined from the
FRM diagram, when no numeric fault code was provided by the flight crew, or when the flight
crew only provided an alphanumeric fault code. Malfunctioning systems/modes of operation are
listed 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 4-1. Synchrophaser System Malfunctions
*Alphanumeric
fault code
Malfunction
1.
Synchrophaser system
malfunction
6120S01
Fault isolation reference
Perform figure 4-1, Preparation A, then go
to figure 4-5, block 1.
* If provided by flight crew
4-3. NUMERIC FAULT CODE INDEX. All assigned numeric FRM fault codes for the synchrophaser system are listed in table 4-2. Fault codes are listed in numerical order in the left
column of the table. The middle column contains the AFTO Form 781A report and lists symptoms 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 4-2. Synchrophaser System Fault Codes
Fault code
AFTO Form 781A report
Fault isolation reference
6120001
All slave propellers fail to follow when
No. 3 propeller is selected as master. All
slave propellers follow when No. 2 propeller is selected as master.
Replace propeller synchrophaser in accoradance with TO 1C-130H-2-61JG-20-1,
61-20-13.
6120002
Propeller No. (1)(2)(4) fails to follow when
No. 3 propeller is selected as master.
Propeller follows when No. 2 propeller is
selected as master.
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1, 6120-13.
61-20-00
Change 1
4-1
TO 1C-130H-2-61FI-00-1
Table 4-2. Synchrophaser System Fault Codes
Fault code
AFTO Form 781A report
Fault isolation reference
6120003
All slave propellers fail to follow when
No. 2 propeller is selected as master. All
slave propellers follow when No. 3 propeller is selected as master.
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1, 6120-13.
6120004
All slave propellers fail to follow when
No. 2 or No. 3 propeller is selected as
master.
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1, 6120-13.
6120005
Propeller No. (1)(3)(4) fails to follow when
No. 2 propeller is selected as master.
Propeller follows when No. 3 propeller is
selected as master.
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1, 6120-13.
6120006
Propeller No. (1)(3)(4) fails to follow when
No. 2 or No. 3 propeller is selected as
master.
Perform figure 4-1, Preparation A, then
go to figure 4-5, block 144.
6120007
All slave engine RPMs fluctuate when
No. 3 propeller is selected as master.
Perform figure 4-1, Preparation A, then
go to figure 4-5, block 324.
6120008
Engine No. (1)(2)(3)(4) RPM fluctuates
when No. 3 propeller is selected as
master.
Perform figure 4-1, Preparation A, then
go to figure 4-5, block 324.
6120009
All slave engine RPMs fluctuate when
No. 2 propeller is selected as master.
Perform figure 4-1, Preparation A, then
go to figure 4-5, block 324.
6120010
Engine No. (1)(2)(3)(4) RPM fluctuates
when No. 2 propeller is selected as
master.
Perform figure 4-1, Preparation A, then
go to figure 4-5, block 324.
6120011
Engine No. (1)(2)(3)(4) RPM takes excessive time to stabilize after rapid THROTTLE movement.
Perform figure 4-1, Preparation A, then
go to figure 4-5, block 146.
6120012
All engine RPMs (fluctuate) (are out of
limits) in normal governing.
Replace propeller synchrophaser in accordance with TO 1C-130H-2-61JG-20-1, 6120-13.
6120013
Engine No. (1)(2)(3)(4) RPM (fluctuates)
(is out of limits) in normal governing.
Perform figure 4-1, Preparation A, then
go to figure 4-5, block 137.
6120014
Engine No. (1)(2)(3)(4) RPM (fluctuates)
(is of limits) in mechanical governing.
Fault is in propeller system. Go to Section II and continue fault isolation.
61-20-00
4-2
Change 1
TO 1C-130H-2-61FI-00-1
4-4.
PREPARATION PROCEDURES.
WARNING
Improper or inadequate preparation of the airplane may result in
injury to personnel and/or damage to the airplane.
The applicable preparation procedures must be performed before starting troubleshooting. The
preparation is referenced in the malfunction index and fault code indexes. Each procedure is
contained in a figure that illustrates step-by-step actions to be taken to prepare the airplane for
troubleshooting.
61-20-00
Change 1
4-3
TO 1C-130H-2-61FI-00-1
Figure 4-1. Preparation A (Sheet 1 of 2)
61-20-00
4-4
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-1. Preparation A (Sheet 2)
61-20-00
Change 1
4-5
TO 1C-130H-2-61FI-00-1
Figure 4-2. Preparation B (Sheet 1 of 2)
61-20-00
4-6
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-2. Preparation B (Sheet 2)
61-20-00
Change 1
4-7
TO 1C-130H-2-61FI-00-1
Figure 4-3. Preparation C (Sheet 1 of 3)
61-20-00
4-8
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-3. Preparation C (Sheet 2)
61-20-00
Change 1
4-9
TO 1C-130H-2-61FI-00-1
Figure 4-3. Preparation C (Sheet 3)
61-20-00
4-10
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-4. Preparation D (Sheet 1 of 3)
61-20-00
Change 1
4-11
TO 1C-130H-2-61FI-00-1
Figure 4-4. Preparation D (Sheet 2)
61-20-00
4-12
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-4. Preparation D (Sheet 3)
61-20-00
Change 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 troubleshooting any synchrophaser system malfunction. When the flight crew uses a FRM fault code
to report a malfunction, that number will be found in the fault code index. When no FRM fault
code 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 physical location of items referenced in individual fault isolation diagram blocks. Double-check these
illustrations to verify the correct location when making an observation or measurement. Following the fault isolation diagram are the electrical schematic diagrams. The schematic diagrams
are laid out so that no portion of a diagram is covered up when folded out for use. Thus it is
easy to concurrently locate components, circuits, and test points that are referenced on the fault
isolation diagram.
b. Using Troubleshooting Data. A thorough description of the fault isolation diagram and
other troubleshooting data is provided in Section I. In addition, the Introduction contains an
illustrated how-to-use figure for this section. Understand how to use the troubleshooting information before attempting to repair the airplane.
61-20-00
4-14/(4-15 blank)
Change 1
TO 1C-130H-2-61FI-00-1
1
6120S01
Advance throttles (6) to obtain approximately 8,000 inch-pounds on engine
torque indicators (3) with all ELECTRONIC FUEL CORRECTION/TD lights
(2) off.
Did RPM on any engine tachometer (4)
exceed 103.5 percent or did any propeller pitchlock?
6
5
YES
Perform synchrophaser index in accordance with TO 1C-130H-61JG-10-1, 6110-02 (subtask 1-2-6).
Does problem persist?
NO
Synchrophaser index corrected malfunction. Secure
system.
YES
NO
TO SHT 7
7
2
Place propeller governor control switches (5) to MECH GOV/MECH.
Is RPM stable for each propeller?
Fault is in propeller
system. Go to figure 2-5 in Section
II and continue
troubleshooting.
NO
YES
3
Is RPM in FUNCTION display (1) between 99.8 and 100.2 percent for each
propeller?
NO
TO SHT 147
YES
4
Perform synchrophaser index in accordance with TO 1C-130H-2-61JG-10-1,
61-10-02 (subtask 1-2-6). Did RPM of
any propeller vary more than 0.2 percent when propeller governor control
switches (5) were moved from MECH
GOV/MECH to NORMAL/NORM during
the synchrophaser index?
YES
TO SHT 25
NO
TO SHT 3
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 4-5. Synchrophaser System Malfunction (Sheet 1 of 152)
61-20-00
4-16
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 2)
61-20-00
Change 1
4-17
TO 1C-130H-2-61FI-00-1
FROM SHT 1
8
Is RPM stable for each propeller
(1) in NORMAL governing?
NO
TO SHT 41
YES
9
Place SYNCHROPHASE
MASTER/MSTR switch (3) to engine 2.
Is RPM stable for all propellers?
NO
TO SHT 109
YES
10
Perform synchrophaser check in
accordance with TO 1C-130H-261JG-10-1, 61-10-02 (subtask 12-9).
Did RPM of any slave propeller
fail to decrease 1 to 3 percent as
No. 2 throttle (2) was retarded to
FLIGHT IDLE/FLT IDLE during
the check?
YES
TO SHT 43
NO
11
Place SYNCHROPHASE
MASTER/MSTR switch (3) to engine 3.
Is RPM stable for all propellers?
NO
TO SHT 109
YES
TO SHT 5
Figure 4-5. Synchrophaser System Malfunction (Sheet 3)
61-20-00
4-18
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 4)
61-20-00
Change 1
4-19
TO 1C-130H-2-61FI-00-1
FROM SHT 3
12
15
Did the RPM of any slave propeller fail to decrease 1 to 3 percent
as No. 3 throttle (1) was retarded
to FLIGHT IDLE/FLT IDLE during
the synchrophaser check?
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
YES
NO
13
Perform throttle anticipation check
in accordance with TO 1C-130H2-61JG-10-1, 61-10-02 (subtask
1-2-8).
Was check satisfactory?
NO
TO SHT 45
YES
14
Perform fuel governor and
pitchlock check in accordance
with TO 1C-130H-2-61JG-10-1,
61-10-02 (subtask 1-2-10).
Was check satisfactory?
16
YES
Synchrophaser system is normal. Secure system.
NO
TO SHT 7
Figure 4-5. Synchrophaser System Malfunction (Sheet 5)
61-20-00
4-20
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 6)
61-20-00
Change 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 is
engaged. The RPM may drop below 94 percent and
cause an engine flameout, resulting in overtemperature
damage to the turbine.
a. Shut down engines in accordance with TO 1C-130H2-71JG-00-1, 71-00-10.
b. Perform Preparation D.
c. Place TEST SELECT switch (2) to 7.
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 volts
while switch is held?
Prop
4
20
NO
Is airplane serial number
AF92-0547 through AF92-2104
or AF92-3281 and up?
NO
Sync Rcpt Pins
P-B2576A-10, P-B2576A-30
YES
TO SHT 9
18
a. Place PROP CHANNEL SELECT switch to R/3.
b. Momentarily hold engine 3 fuel governing switch (5)
to CHECK.
Does FUNCTION display indicate -6.5 to -7.5 volts
while switch is held?
Prop
3
NO
TO SHT 15
Sync Rcpt Pins
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.
Does FUNCTION display indicate -6.5 to -7.5 volts
while switch is held?
Prop
2
NO
TO SHT 17
Sync Rcpt Pins
P-A2576A-44, P-B2576A-30
YES
TO SHT 19
NOTE
1
AC-130H airplanes only.
2
AC-130U airplanes only.
Figure 4-5. Synchrophaser System Malfunction (Sheet 7)
61-20-00
4-22
Change 1
YES
TO SHT 11
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 8)
61-20-00
Change 1
4-23
TO 1C-130H-2-61FI-00-1
FROM SHT 7
21
23
NOTE
Put meter positive lead to ground
in following steps.
Gain access to terminals of engine 4 fuel governing switch (1).
Is 15 volts present on switch terminal 2?
NO
7
a. Remove junction box from
synchrophaser rack.
b. Install a jumper wire between
pin 39 of receptacle P-A2576A (2)
and airplane ground.
Is a ground present on engine 4
fuel governing switch (1) terminal
2?
24
NO
Remove jumper wire. Repair
open circuit between switch terminal 2 and receptacle PA2576A pin 39. (See figure 46.)
7
YES
YES
25
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
22
Momentarily hold ENG 4 FUEL
GOVERNING switch (1) to
CHECK.
Is 15 volts present on switch terminal 1 while switch is held?
26
NO
Replace ENG 4 FUEL GOVERNING switch.
8
YES
27
Repair open circuit between
switch terminal 1 and pin 10 of
receptacle P-B2576A (3). (See
figure 4-6.)
NOTE
1
AC-130H airplanes only.
2
AC-130U airplanes only.
3.
See figure 4-6 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 9)
61-20-00
4-24
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 10)
61-20-00
Change 1
4-25
TO 1C-130H-2-61FI-00-1
FROM SHT 7
28
NOTE
Put meter positive lead to ground in following
steps.
NO
Gain access to terminals of engine 4 fuel governing switch (3).
Is 15 volts present on switch terminal 2?
TO SHT 13
7
YES
29
Momentarily hold ENG 4 FUEL GOVERNING
switch (3) to CHECK.
Is 15 volts present on switch terminal 1 while
switch is held?
31
NO
Replace ENG 4 FUEL GOVERNING switch.
8
YES
30
Gain access to and disconnect plug P1743A
(1) from fuel governing control panel (4).
Is there continuity between receptacle J880A
(2) pin D and related control panel switch terminal 1?
8
32
YES
Repair open circuit between
plug P1743A pin D and receptacle P-B2576A (5) pin 10.
(See figure 4-7.)
8.2
NO
33
Repair open circuit between receptacle J880A pin D and
switch terminal 1. (See figure
4-7.)
NOTE
See figure 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 11)
61-20-00
4-26
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 12)
61-20-00
Change 1
4-27
TO 1C-130H-2-61FI-00-1
FROM SHT 11
34
a. Gain access to and disconnect
plug P1743A (1) from fuel governing control panel (4).
b. Install a jumper wire between
pin E of receptacle J880A (2) and
airplane ground.
Is a ground present on engine 4
fuel governing switch (3) terminal
2?
36
NO
Remove jumper wire. Repair
open circuit between fuel governing switch terminal 2 and receptacle J880A pin E. (See
figure 4-7.)
7
YES
35
a. Remove junction box from
synchrophaser rack.
b. Install a jumper wire between
pin 39 of receptacle P-A2576A (5)
and airplane ground.
Is a ground present on engine 4
fuel governing switch (3) terminal
2?
37
NO
Remove jumper wire. Repair
open circuit between plug
P1743A pin E and receptacle
P-A2576A, pin 39. (See figure
4-7.)
7
YES
38
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
NOTE
See figure 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 13)
61-20-00
4-28
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 14)
61-20-00
Change 1
4-29
TO 1C-130H-2-61FI-00-1
FROM SHT 7
39
NOTE
Put meter positive lead to ground in following steps.
43
Gain access to terminals of engine 3 fuel governing
switch (4).
Is 15 volts present on switch terminal 2?
Repair open circuit between engine 3 fuel governing switch terminal 2 and terminal 2 of engine 4 fuel governing switch
(3). (See figure 4-6 or 4-7.)
NO
5
YES
40
Momentarily hold ENG 3 FUEL GOVERNING switch (4)
to CHECK.
Is 15 volts present on switch terminal 1 while switch is
held?
44
NO
Replace ENG 3 FUEL GOVERNING
switch.
6
YES
45
41
Is airplane serial number AF92-0547 through AF922104 or AF92-3281 and up?
NO
YES
Repair open circuit between engine 3 fuel governing switch terminal 1 and pin 22
of receptacle P-A2576A (6). (See figure
4-6.)
42
Gain access to and disconnect plug P1743A (1) from
fuel governing control panel (5).
Is there continuity between receptacle J880A (2) pin C
and related control panel switch terminal 1?
6
46
YES
Repair open circuit between plug P1743A
pin C and receptacle P-A2576A (6) pin
37. (See figure 4-7.)
8.3
NO
47
Repair open circuit between receptacle
J880A pin C and switch terminal 1. (See
figure 4-7.)
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3
AC-130H airplanes only.
4
AC-130U airplanes only.
5.
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 15)
61-20-00
4-30
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 16)
61-20-00
Change 1
4-31
TO 1C-130H-2-61FI-00-1
FROM SHT 7
48
NOTE
Put meter positive lead to ground in following steps.
52
Gain access to terminals of engine 2 fuel governing
switch (1).
Is 15 volts present on switch terminal 2?
Repair open circuit between engine 2
fuel governing switch terminal 2 and
terminal 2 of engine 3 fuel governing
switch (2). (See figure 4-6 or 4-7.)
NO
3
YES
49
Momentarily hold ENG 2 FUEL GOVERNING switch (1)
to CHECK.
Is 15 volts present on switch terminal 1 while switch is
held?
53
NO
Replace ENG 2 FUEL GOVERNING
switch.
4
YES
54
50
Is airplane serial number AF92-0547 through AF922104 or AF92-3281 and up?
NO
YES
Repair open circuit between engine 2
fuel governing switch terminal 1 and
pin 44 of receptacle P-A2576A (3).
(See figure 4-6.)
51
Gain access to and disconnect plug P1743A (4) from
fuel governing control panel (6).
Is there continuity between receptacle J880A (5) pin B
and related control panel switch terminal 1?
4
55
YES
Repair open circuit between plug
P1743A pin B and receptacle PA2576A (3) pin 44. (See figure 4-7.)
8.4
NO
56
Repair open circuit between receptacle J880A pin B and switch terminal
1. (See figure 4-7.)
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3
AC-130H airplanes only.
4
AC-130U airplanes only.
5.
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 17)
61-20-00
4-32
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 18)
61-20-00
Change 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.
Does FUNCTION display (3) indicate -6.5 to -7.5 volts
while switch is held?
Prop
1
NO
TO SHT 21
Sync Rcpt Pins
P-B2576A-18, P-B2576A-30
YES
58
a. Place PROP CHANNEL SELECT switch (6) to propeller under test.
b. Place propeller governor control switch (8) to MECH
GOV/MECH.
c. Momentarily hold FUEL GOV switch (5) to ON.
Does FUNCTION display (3) indicate -6.5 to -7.5 volts
while switch is held?
Prop
1
2
3
4
60
NO
Sync Rcpt Pins
P-B2576A-18, P-B2576A-30
P-A2576A-44, P-B2576A-30
P-A2576A-22, P-B2576A-30
P-B2576A-10, P-B2576A-30
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
YES
59
a. Place TEST SELECT switch (7) to 8.
b. Momentarily hold applicable fuel governing switch (1
or 2) to CHECK for 10 seconds.
Does AC VOLTS display (4) indicate 50 to 65 volts
while switch is held?
(Speed bias control winding)
Prop
1
2
3
4
61
NO
Sync Rcpt Pins
P-B2576A-5, P-B2576A-3
P-A2576A-34, P-A2576A-45
P-B2576A-14, P-B2576A-6
P-A2576A-24, P-B2576A-19
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
YES
TO SHT 23
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3
AC-130H airplanes only.
4
AC-130U airplanes only.
Figure 4-5. Synchrophaser System Malfunction (Sheet 19)
61-20-00
4-34
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 20)
61-20-00
Change 1
4-35
TO 1C-130H-2-61FI-00-1
FROM SHT 19
62
NOTE
Put meter positive lead to ground in following steps.
66
Gain access to terminals of engine 1 fuel governing
switch (1).
Is 15 volts present on switch terminal 2?
Repair open circuit between engine 1
fuel governing switch terminal 2 and
terminal 2 of engine 2 fuel governing
switch (2). (See figure 4-6 or 4-7.)
NO
1
YES
63
Momentarily hold ENG 1 FUEL GOVERNING switch (1)
to CHECK.
Is 15 volts present on switch terminal 1 while switch is
held?
67
NO
Replace ENG 1 FUEL GOVERNING
switch.
2
YES
68
64
Is airplane serial number AF92-0547 through AF922104 or AF92-3281 and up?
NO
YES
Repair open circuit between engine 1
fuel governing switch terminal 1 and
pin 18 of receptacle P-B2576A (3).
(See figure 4-6.)
65
Gain access to and disconnect plug P1743A (4) from
fuel governing control panel (6).
Is there continuity between receptacle J880A (5) pin A
and related control panel switch terminal 1?
2
69
YES
Repair open circuit between plug
P1743A pin A and receptacle PB2576A (3) pin 18. (See figure 4-7.)
8.5
NO
70
Repair open circuit between receptacle J880A pin A and switch terminal
1. (See figure 4-7.)
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3
AC-130H airplanes only.
4
AC-130U airplanes only.
5.
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 21)
61-20-00
4-36
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 22)
61-20-00
Change 1
4-37
TO 1C-130H-2-61FI-00-1
FROM SHT 19
71
a. Record voltage indication in FUNCTION
display (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)
to MECH GOV/MECH.
e. Record voltage indication in FUNCTION
display (2).
f. Compare the two voltage indications recorded in steps a and e.
Did voltage change more than 0.2 volts on
any channel?
(Feedback pot)
DC: Sync
Rcpt Pin
P-B2576A-7
P-A2576A-14
P-A2576A-2
P-B2576A-23
72
YES
Replace valve housing assembly in
accordance with TO 1C-130H-2-61JG20-1, 61-20-02.
AC: Sync
Rcpt Pins
P-B2576A-5 and 3
P-A2576A-34 and 45
P-B2576A-14 and 6
P-A2576A-24 and
P-B2576A-19
NO
73
Replace propeller synchrophaser in
accordance with TO 1C-130H-2-61JG20-1, 61-20-13.
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3
AC-130H airplanes only.
4
AC-130U airplanes only.
Figure 4-5. Synchrophaser System Malfunction (Sheet 23)
61-20-00
4-38
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 24)
61-20-00
Change 1
4-39
TO 1C-130H-2-61FI-00-1
FROM SHT 1
74
Did all propellers (1,2,3, and 4) fail to
respond to the synchrophaser index?
YES
TO SHT 27
NO
75
With No. 2 propeller (2) as master did
No. 3 propeller (3) fail to index, and with
No. 3 (3) propeller as master did No. 2
propeller (2) fail to index?
YES
TO SHT 39
NO
76
Perform propeller governor servo-bias
clutch-brake check on affected propeller
in accordance with TO 1C-130H-261JG-10-1, 61-10-02 (subtask 1-2-7).
Was RPM within limits for the affected
propeller?
77
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
YES
TO SHT 47
Figure 4-5. Synchrophaser System Malfunction (Sheet 25)
61-20-00
4-40
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 26)
61-20-00
Change 1
4-41
TO 1C-130H-2-61FI-00-1
FROM SHT 25
78
a. Shut down engines in accordance with TO 1C-130H-2-71JG00-1, 71-00-10.
b. Perform Preparation D.
c. Place TEST SELECT switch
(8) to 1.
Does AC VOLTS display (3) indicate 115 to 125 volts?
Prop
All
82
YES
Sync Rcpt Pins
P-A2576A-8 and
P-B2576A-30
Place propeller governor control
switches (4) to MECH GOV/MECH.
Is MASTER light L/2 (1) on and are
SYNC and RESYNC lights (2) off?
NO
83
Replace SYNCHROPHASE
MASTER/MSTR switch.
Prop Sync Rcpt Pins
All
P-A2576A-38, P-B2576A-22
YES
NO
TO SHT 29
79
Remove junction box from synchrophaser
rack.
Is a ground present on pin 30 of receptacle PB2576A (7)?
84
NO
Repair ground circuit. (See figure 46.)
40
YES
80
85
Is airplane serial number AF92-0547 through
AF92-2104 or AF92-3281 and up?
YES
Repair power circuit to receptacle PA2576A, pin 8. (See figure 4-7.)
NO
81
Gain access to and disconnect plug P1258F
(6) from constant voltage transformer (5).
Is 115 VAC present on plug pin 1?
86
NO
Repair power circuit to plug P1258F
pin 1. (See figure 4-6.)
33
YES
TO SHT 37
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 27)
61-20-00
4-42
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 28)
61-20-00
Change 1
4-43
TO 1C-130H-2-61FI-00-1
FROM SHT 27
87
Place SYNCHROPHASE MASTER/
MSTR switch (1) to engine 2.
Are MASTER light L/2 (2) and SYNC
light (‘‘4’’) on?
Prop
Any
89
NO
Gain access to terminal board
TB146A (5).
Is 28 VDC present on terminal 199?
91
NO
27
Sync Rcpt Pins
P-A2576A-38
Repair power circuit to
terminal 199. (See figure
4-6 or 4-7.)
YES
YES
92
90
Is 28 VDC present on terminal 207?
29
NO
Repair open circuit beYES tween terminal 207 and
pin 38 of receptacle PA2576A (6). (See figure
4-6 or 4-7.)
TO SHT 31
88
Place SYNCHROPHASE MASTER/
MSTR switch to engine 3.
Are MASTER light R/3 (3) and SYNC
light (4) on?
Prop
Any
NO
TO SHT 33
Sync Rcpt Pins
P-B2576A-22
YES
TO SHT 35
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 29)
61-20-00
4-44
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 30)
61-20-00
Change 1
4-45
TO 1C-130H-2-61FI-00-1
FROM SHT 29
93
Gain access to terminals of SYNCHROPHASE MASTER/MSTR
switch (3).
Is 28 VDC present on switch terminal 11?
97
NO
Repair open circuit between
switch terminal 11 and terminal
199 of terminal board TB146A
(1). (See figure 4-6 or 4-7.)
14
YES
94
Is 28 VDC present on switch terminal 10?
98
NO
17
Replace SYNCHROPHASE
MASTER/MSTR switch.
YES
95
99
Gain access to terminals of PROP
RESYNCHROPHASE/PROP
SYNC switch (2).
Is 28 VDC present on switch terminal 5?
NO
22
Repair open circuit between
PROP RESYNCHROPHASE/
PROP SYNC switch terminal 5
and SYNCHROPHASE
MASTER/MSTR switch terminal
10. (See figure 4-6 or 4-7.)
YES
100
96
Is 28 VDC present on switch terminal 6?
25
NO
YES
Repair open circuit between
PROP RESYNCHROPHASE/
PROP SYNC switch terminal 6
and terminal board TB146A (1)
terminal 207. (See figure 4-6
or 4-7.)
101
Replace PROP RESYNCHROPHASE/PROP SYNC
switch.
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 31)
61-20-00
4-46
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 32)
61-20-00
Change 1
4-47
TO 1C-130H-2-61FI-00-1
FROM SHT 29
106
102
Gain access to terminal board
TB146A (1).
Is 28 VDC present on terminal
207?
NO
29
Gain access to terminals of SYNCHROPHASE MASTER/MSTR
switch (2).
Is 28 VDC present on switch terminal 12?
107
YES Repair open circuit between
switch terminals 10 and 12.
(See figure 4-6 or 4-7.)
18
YES
NO
108
Replace SYNCHROPHASE
MASTER/MSTR switch.
103
109
Is 28 VDC present on terminal
206?
YES
28
Repair open circuit between terminal 206 and pin 22 of receptacle P-B2576A (3). (See figure
4-6 or 4-7.)
NO
104
Gain access to terminals of SYNCHROPHASE MASTER/MSTR
switch (2).
Is 28 VDC present on switch terminal 8?
110
NO
Repair open circuit between
switch terminals 8 and 11.
(See figure 4-6 or 4-7.)
15
YES
105
111
Is 28 VDC present on switch terminal 9?
19
YES
Repair open circuit between
switch terminal 9 and terminal
board TB146A terminal 206.
(See figure 4-6 or 4-7.)
NO
112
Replace SYNCHROPHASE
MASTER/MSTR switch.
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 33)
61-20-00
4-48
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 34)
61-20-00
Change 1
4-49
TO 1C-130H-2-61FI-00-1
FROM SHT 29
113
Momentarily hold PROP RESYNCHROPHASE/PROP SYNC switch (3)
to RESYNC/INDEX. Are R/3 light (1)
and RESYNC/INDEX light (2) on while
switch is held?
Prop
Any
117
YES
Replace propeller synchrophaser in
accordance with TO 1C-130H-2-61JG20-1, 61-20-13.
Sync Rcpt Pins
P-A2576A-30
NO
116
114
a. Gain access to terminal board
TB128A (6).
b. Momentarily hold PROP RESYNCHROPHASE/PROP SYNC switch
(3) to RESYNC/INDEX.
Is 28 VDC present on terminal board
terminal 17 while switch is held?
NO
a. Gain access to terminals of
PROP RESYNCHROPHASE/PROP
SYNC switch (3).
b. Momentarily hold PROP RESYNCHROPHASE/PROP SYNC switch
(3) to RESYNC/INDEX.
Is 28 VDC present on switch terminal
4 while switch is held?
30
118
Repair open circuit between PROP RESYNYES CHROPHASE/PROP
SYNC switch terminal 4
and terminal board
TB128A terminal 17.
(See figure 4-6 or 4-7.)
24
YES
NO
119
Replace PROP RESYNCHROPHASE/
PROP SYNC switch.
115
a. Gain access to terminal board TB1C (5).
b. Momentarily hold PROP RESYN
CHROPHASE/PROP SYNC switch (3) to
RESYNC/INDEX.
Is 28 VDC present on terminal board terminal
9 while switch is held?
120
NO
Repair open circuit between terminal
board TB1C terminal 9 and terminal
board TB128A terminal 17. (See figure 4-6 or 4-7.)
13
YES
121
Repair open circuit between terminal
board TB1C terminal 9 and pin 30 of
receptacle P-A2576A (4). (See figure
4-6 or 4-7.)
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 35)
61-20-00
4-50
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 36)
61-20-00
Change 1
4-51
TO 1C-130H-2-61FI-00-1
FROM SHT 27
122
Is a ground present on pin 2 of
plug P1258F (2)?
125
NO
34
Repair ground circuit. (See figure 4-6.)
YES
123
Is a ground present on plug pin
4?
126
NO
35
Repair ground circuit. (See figure 4-6.)
YES
124
Is there continuity between plug
P1258F pin 3 and pin 8 of receptacle P-A2576A (1)?
36
127
YES
Replace constant voltage transformer (3).
41
NO
128
Repair open circuit. (See figure
4-6.)
NOTE
See figure 4-6 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 37)
61-20-00
4-52
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 38)
61-20-00
Change 1
4-53
TO 1C-130H-2-61FI-00-1
FROM SHT 25
129
a. Shut down engines in accordance
with TO 1C-130H-2-71JG-00-1, 71-0010.
b. Place SYNCHROPHASE MASTER/
MSTR switch (1) to engine 2 or engine
3.
c. Gain access to terminals of PROP
RESYNCHROPHASE/PROP SYNC
switch (2).
Is 28 VDC present on PROP RESYNCHROPHASE/PROP SYNC switch (2)
terminal 2?
132
NO
Repair open circuit between
PROP RESYNCHROPHASE/
PROP SYNC switch terminals 2
and 5. (See figure 4-6 or 4-7.)
23
YES
130
Momentarily hold PROP RESYNCHROPHASE/PROP SYNC switch (2)
to RESYNC/INDEX.
Is 28 VDC present on switch terminal 1
while switch is held?
133
NO
Replace PROP RESYNCHROPHASE/PROP SYNC
switch.
26
YES
131
Momentarily hold PROP RESYNCHROPHASE/PROP SYNC switch (2)
to RESYNC/INDEX.
Is 28 VDC present on SYNCHROPHASE MASTER/MSTR switch
(1) terminal 5 while PROP RESYNCHROPHASE/PROP SYNC switch (2) is
held?
134
NO
Repair open circuit between
SYNCHROPHASE MASTER/
MSTR switch terminal 5 and
PROP RESYNCHROPHASE/
PROP SYNC switch terminal 1.
(See figure 4-6 or 4-7.)
16
YES
135
Replace SYNCHROPHASE
MASTER/MSTR switch.
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 39)
61-20-00
4-54
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 40)
61-20-00
Change 1
4-55
TO 1C-130H-2-61FI-00-1
FROM SHT 3
136
139
Does RPM of all propellers (2) fluctuate
with propeller governor control switch
(3) in NORMAL/NORM?
YES
Replace propeller synchrophaser in
accordance with TO 1C-130H-2-61JG20-1, 61-20-13.
NO
140
137
Does frequency meter (1) indicate a
fluctuation for the affected propeller?
NO
Fault is in tachometer system. Go to
TO 1C-130H-2-70FI-00-1-1 and continue troubleshooting.
YES
138
Perform synchrophaser index in accordance with TO 1C-130H-2-61JG-10-1,
61-10-02 (subtask 1-2-6). Did RPM stabilize?
141
YES
Synchrophaser index corrected malfunction. Secure system.
NO
TO SHT 47
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 4-5. Synchrophaser System Malfunction (Sheet 41)
61-20-00
4-56
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 42)
61-20-00
Change 1
4-57
TO 1C-130H-2-61FI-00-1
FROM SHT 3
142
If not previously done, perform
synchrophaser check in accordance with TO 1C-130H-2-61JG10-1, 61-10-02 (subtask 1-2-9).
Did RPM of any slave propeller
(2) fail to decrease 1 to 3 percent
as No. 3 throttle (1) was retarded
to FLIGHT IDLE/FLT IDLE during
the check?
NO
TO SHT 109
YES
145
143
Did all slave propellers fail to follow either master?
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
YES
NO
144
6120006
Perform pitchlock check in accordance with TO 1C-130H-2-61JG10-1, 61-10-02 (subtask 1-2-10).
Was check satisfactory?
NO
TO SHT 47
YES
TO SHT 109
Figure 4-5. Synchrophaser System Malfunction (Sheet 43)
61-20-00
4-58
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 44)
61-20-00
Change 1
4-59
TO 1C-130H-2-61FI-00-1
FROM SHT 5
146
a. Perform synchrophaser index
in accordance with TO 1C-130H2-61JG-10-1, 61-10-02 (subtask
1-2-6).
b. Perform throttle anticipation
check in accordance with TO 1C130H-2-61JG-10-1, 61-10-02
(subtask 1-2-8).
Does fault persist?
149
NO
Synchrophaser index corrected
malfunction. Secure system.
YES
147
Perform propeller governor servobias clutch-brake check on affected propeller (3) in accordance
with TO 1C-130H-61JG-10-1, 6110-02 (subtask 1-2-7).
Was RPM within limits?
150
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
YES
148
a. Perform synchrophaser index
in accordance with TO 1C-130H2-61JG-10-1, 61-10-02 (subtask
1-2-6).
b. Shut down engines in accordance with TO 1C-130H-2-71JG00-1, 71-00-10.
c. Move throttle (1) to MAXIMUM
REVERSE/MAX RVS.
d. Hold engine condition lever (2)
in AIR START until propeller
blades (3) stop moving (in reverse
position), then release.
e. Place engine condition lever
(2) to FEATHER/FTR and time
propeller movement.
Does propeller go from full reverse to full feather in 25 seconds
or less?
151
NO
Reseal dome assembly in accordance with TO 1C-130H-261JG-10-1, 61-10-13.
YES
TO SHT 47
Figure 4-5. Synchrophaser System Malfunction (Sheet 45)
61-20-00
4-60
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 46)
61-20-00
Change 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 accordance with TO 1C-130H-2-71JG-00-1, 71-00-10.
b. Perform Preparation C.
Does FUNCTION display (3) indicate 200 to 300
and does AC VOLTS display (4) indicate 3?
(Anticipator pot R)
Prop
1
2
3
4
NO
TO SHT 49
Sync Rcpt Pins
P-B2576A-27, P-B2576A-30
P-A2576A-7, P-B2576A-30
P-A2576A-13, P-B2576A-30
P-B2576A-36, P-B2576A-30
YES
153
155
Place RESISTANCE TEST switch (5) to 2.
Does FUNCTION display (3) indicate 134 to 216
and does AC VOLTS display (4) indicate 3?
(Anticipator pot wiper R)
Prop
1
2
3
4
NO
Sync Rcpt Pins
P-B2576A-13, P-B2576A-30
P-B2576A-32, P-B2576A-30
P-B2576A-35, P-B2576A-30
P-B2576A-33, P-B2576A-30
Gain access to and disconnect
plug P390 (1) at valve housing
assembly.
Is 134K to 216K ohms resistance present between pins K
and S of valve housing assembly receptacle (2)?
71
156
NO
Replace valve
housing assembly
in accordance with
TO 1C-130H-261JG-20-1, 61-2002.
70
YES
YES
TO SHT 53
154
Move throttle (6) to TAKE OFF.
Does FUNCTION display (3) indicate 24 to 58
and does AC VOLTS display (4) indicate 3?
(Anticipator pot wiper R in T/O pos)
Prop
1
2
3
4
157
NO
Sync Rcpt Pins
P-B2576A-13, P-B2576A-30
P-B2576A-32, P-B2576A-30
P-B2576A-35, P-B2576A-30
P-B2576A-33, P-B2576A-30
YES
TO SHT 55
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 47)
61-20-00
4-62
Change 1
Replace valve
housing assembly
in accordance with
TO 1C-130H-261JG- 20-1, 61-2002.
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 48)
61-20-00
Change 1
4-63
TO 1C-130H-2-61FI-00-1
FROM SHT 47
158
Gain access to and disconnect plug
P390 (3) at valve housing assembly.
Is 200K to 300K ohms resistance present between pins K and T of valve
housing receptacle (4)?
71
162
Replace valve housing assembly in accordance with
TO 1C-130H-2-61JG-20-1,
61-20-02.
NO
72
YES
161
159
Is a ground present on plug P390 (3)
pin K?
NO
71
Gain access to and disconnect
plug P398 (2) at engine firewall.
Is a ground present on plug
pin V?
163
YES Repair open circuit between
pin V of receptacle J239 (1)
and plug P390 pin K. (See
figure 4-6 or 4-7.)
59
YES
NO
164
Repair ground circuit. (See
figure 4-6 or 4-7.)
160
a. Reconnect plug P390 (3) at valve
housing assembly.
b. Gain access to and disconnect plug
P398 (2) at engine firewall.
Is 200K to 300K ohms resistance present between pins T and V of receptacle
J239 (1)?
60
165
NO
Repair wiring fault between
receptacle J239 pin T and
plug P390 pin T. (See figure 4-6 or 4-7.)
59
YES
TO SHT 51
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 49)
61-20-00
4-64
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 50)
61-20-00
Change 1
4-65
TO 1C-130H-2-61FI-00-1
168
FROM SHT 49
166
Is an outboard propeller being
troubleshot?
NO
Repair wiring fault between pin
T of plug P398 (1) and related
pin of receptacle P-A2576A (3).
(See figure 4-6 or 4-7.)
Rcpt
2
3
YES
Prop Pin
7
13
167
a. Reconnect plug P398 (1) at
engine firewall.
b. Gain access to and disconnect
plug P1139 (4) at outer wing
break.
Is 200K to 300K ohms resistance
present between pin g of receptacle J935 (5) and airplane ground?
169
NO
Repair wiring fault between receptacle J935 pin g and plug
P398 pin T. (See figure 4-6 or
4-7.)
48
YES
170
Repair wiring fault between plug
P1139 pin g and related pin of
receptacle P-B2576A (2). (See
figure 4-6 or 4-7.)
Prop
1
4
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 51)
61-20-00
4-66
Change 1
Rcpt Pin
27
36
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 52)
61-20-00
Change 1
4-67
TO 1C-130H-2-61FI-00-1
FROM SHT 47
171
a. Reconnect plug P390 (3) at valve housing
assembly.
b. Gain access to and disconnect plug P398
(2) at engine firewall.
Is 134K to 216K ohms resistance present between pins S and V of receptacle J239 (1)?
58
174
NO
Repair wiring fault between receptacle J239 pin S and plug P390
pin S. (See figure 4-6 or 4-7.)
59
YES
175
172
NO
Is an outboard propeller being troubleshot?
Repair wiring fault between plug
P398 pin S and related pin of receptacle P-B2576A (4).
(See figure 4-6 or 4-7.)
Rcpt
2
3
YES
Prop Pin
32
35
173
a. Reconnect plug P398 (2) at engine firewall.
b. Gain access to and disconnect plug P1139
(6) at outer wing break.
Is 134K to 216K ohms resistance present between specified pin of receptacle J935 (5) and
airplane ground?
Prop
Rcpt Pin
1
f
4
c
176
NO
Test Point
47
Repair wiring fault between plug
P398 pin S and related receptacle
J935 pin. (See figure 4-6 or 4-7.)
Rcpt
1
4
Prop Pin
f
c
47
YES
177
Repair wiring fault between specified plug P1139 pin and related pin
of receptacle P-B2576A (4). (See
figure 4-6 or 4-7.)
Prop
1
4
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 53)
61-20-00
4-68
Change 1
Plug Pin
f
c
Rcpt Pin
13
33
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 54)
61-20-00
Change 1
4-69
TO 1C-130H-2-61FI-00-1
FROM SHT 47
178
a. Move throttle (6) to FLIGHT IDLE/FLT
IDLE.
b. Place RESISTANCE TEST switch (5) to 3.
Does FUNCTION display (3) indicate 8 to 11
and does AC VOLTS display (4) indicate 3?
(Feedback pot R)
Prop
1
2
3
4
NO
TO SHT 57
Sync Rcpt Pins
P-B2576A-16, P-B2576A-8
P-A2576A-3, P-A2576A-5
P-A2576A-6, P-A2576A-4
P-B2576A-17, P-B2576A-26
YES
179
181
Place RESISTANCE TEST switch (5) to 4.
Does FUNCTION display (3) indicate 1 to 10.5
and does AC VOLTS display (4) indicate 3?
(Feedback pot wiper R)
Prop
1
2
3
4
NO
Sync Rcpt Pins
P-B2576A-16, P-B2576A-7
P-A2576A-14, P-A2576A-5
P-A2576A-6, P-A2576A-2
P-B2576A-23, P-B2576A-26
Gain access to and disconnect plug P390 (1) at valve
housing assembly.
Is 1K to 10.5K ohms resistance present between pins
L and N of valve housing
assembly receptacle (2)?
74
182
NO
73
YES
YES
TO SHT 63
180
Place RESISTANCE TEST switch (5) to 5.
Does FUNCTION display (3) indicate 25 to 50
ohms?
(Speed bias control winding R)
Prop
1
2
3
4
NO
TO SHT 65
Sync Rcpt Pins
P-B2576A-5, P-B2576A-3
P-A2576A-34, P-A2576A-45
P-B2576A-14, P-B2576A-6
P-A2576A-24, P-B2576A-19
YES
TO SHT 71
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 55)
61-20-00
4-70
Change 1
Replace valve housing
assembly in accordance
with TO 1C-130H-261JG-20-1, 61-20-02.
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 56)
61-20-00
Change 1
4-71
TO 1C-130H-2-61FI-00-1
FROM SHT 55
183
Gain access to and disconnect
plug P390 (3) at valve housing
assembly.
Is 8K to 11K ohms resistance present between pins C and L of
valve housing assembly receptacle (4)?
75
186
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
74
YES
184
185
a. Reconnect plug P390 (3) at
valve housing assembly.
b. Gain access to and disconnect
plug P398 (2) at engine firewall.
Is 8K to 11K ohms resistance present between pins C and W of receptacle J239 (1)?
63
62
YES
NO
a. Gain access to and disconnect
plug P390 (3) at valve housing
assembly.
b. Install a jumper wire between
plug pins K and L.
Is there continuity between receptacle J239 (1), pins V and W?
59
187
NO
Remove jumper wire. Repair
wiring fault between receptacle
J239 pin W and plug P390 pin
L. (See figure 4-6 or 4-7.)
62
YES
TO SHT 59
188
Remove jumper wire. Repair
wiring fault between receptacle
J239 pin C and plug P390 pin
C. (See figure 4-6 or 4-7.)
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 57)
61-20-00
4-72
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 58)
61-20-00
Change 1
4-73
TO 1C-130H-2-61FI-00-1
FROM SHT 57
189
YES
Is an outboard propeller being troubleshot?
TO SHT 61
NO
190
a. Install a jumper wire between pins V
and W of plug P398 (1).
b. Remove junction box from synchrophaser rack.
Is a ground present on specified pin of receptacle P-A2576A (2)?
Prop
Rcpt Pin
2
5
3
6
Test Point
38
38
191
NO
Remove jumper wire. Repair
wiring fault between plug P398
pin W and related receptacle PA2576A pin. (See figure 4-6 or
4-7.)
Prop
Rcpt Pin
2
3
5
6
YES
192
Remove jumper wire. Repair
wiring fault between plug P398
pin C and related receptacle PA2576A pin. (See figure 4-6 or
4-7.)
Prop
Rcpt Pin
2
3
5
6
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 59)
61-20-00
4-74
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 60)
61-20-00
Change 1
4-75
TO 1C-130H-2-61FI-00-1
FROM SHT 59
193
195
a. Reconnect plug P398 (1) at engine firewall.
b. Gain access to and disconnect
plug P1139 (3) at outer wing break.
Is 8K to 11K ohms resistance present between specified pins of receptacle J935 (2)?
Prop
Rcpt Pins
1
j and k
4
j and e
YES
Test Points
50
51
50
51
NO
a. Install a jumper wire between
plug P1139 (3) pin j and airplane
ground.
b. Remove junction box from synchrophaser rack.
Is a ground present on specified pin
of receptacle P-B2576A (4)?
Prop
Rcpt Pins
1
16
4
26
196
NO
Test Points
38
38
Remove jumper wire.
Repair wiring fault between plug P1139 pin j
and related receptacle PB2576A pin. (See figure
4-6 or 4-7.)
Prop
Rcpt Pin
1
4
16
26
YES
197
Remove jumper wire. Repair
wiring fault between specified
plug P1139 pin and related receptacle P-B2576A pin. (See
figure 4-6 or 4-7.)
194
Prop
Plug Pin
Rcpt Pin
1
4
k
e
8
17
198
a. Gain access to and disconnect
plug P398 (1) at engine firewall.
b. Install a jumper wire between
plug pins V and W.
Is a ground present on receptacle
J935 (2) pin j?
YES
50
Remove jumper wire. Repair
wiring fault between plug P398
pin C and related plug P1139
pin. (See figure 4-6 or 4-7.)
Prop
1
4
Plug Pin
k
e
NO
199
Remove jumper wire. Repair
wiring fault between receptacle
J935 pin j and plug P398 pin
W. (See figure 4-6 or 4-7.)
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 61)
61-20-00
4-76
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 62)
61-20-00
Change 1
4-77
TO 1C-130H-2-61FI-00-1
FROM SHT 55
200
a. Reconnect plug P390 (3) at
valve housing assembly.
b. Gain access to and disconnect
plug P398 (2) at engine firewall.
Is 1K to 10.5K ohms resistance
present between pins N and W of
receptacle J239 (1)?
61
203
NO
Repair wiring fault between receptacle J239 pin N and plug
P390 pin N. (See figure 4-6 or
4-7.)
62
YES
204
201
Is an outboard propeller being
troubleshot?
NO
Repair wiring fault between plug
P398 pin N and related pin of
receptacle P-A2576A (5). (See
figure 4-6 or 4-7.)
Prop
2
3
YES
Rcpt Pin
14
2
202
a. Reconnect plug P398 (2) at
engine firewall.
b. Gain access to and disconnect
plug P1139 (7) at outer wing
break.
Is 1K to 10.5K ohms resistance
present between pins h and j of
receptacle J935 (6)?
49
205
NO
Repair wiring fault between receptacle J935 pin h and plug
P398 pin N. (See figure 4-6 or
4-7.)
50
YES
206
Repair wiring fault between plug
P1139 pin h and related pin of
receptacle P-B2576A (4). (See
figure 4-6 or 4-7.)
Prop
1
4
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 63)
61-20-00
4-78
Change 1
Rcpt Pin
7
23
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 64)
61-20-00
Change 1
4-79
TO 1C-130H-2-61FI-00-1
FROM SHT 55
207
Gain access to and disconnect
plug P390 (3) at valve housing
assembly.
Is 25 to 50 ohms resistance present between pins B and M of
valve housing assembly receptacle (4)?
68
210
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
67
YES
208
209
a. Reconnect plug P390 (3) at
valve housing assembly.
b. Gain access to and disconnect
plug P398 (2) at engine firewall.
Is 25 to 50 ohms resistance present between pins B and X of receptacle J239 (1)?
56
55
YES
NO
a. Gain access to and disconnect
plug P390 (3) at valve housing
assembly.
b. Install a jumper wire between
plug pins K and M.
Is there continuity between receptacle J239 (1) pins V and X?
59
211
YES Remove jumper wire. Repair
open circuit between receptacle
J239 pin B and plug P390 pin
B. (See figure 4-6 or 4-7.)
55
NO
TO SHT 63
212
Remove jumper wire. Repair
open circuit between receptacle
J239 pin X and plug P390 pin
M. (See figure 4-6 or 4-7.)
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 65)
61-20-00
4-80
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 66)
61-20-00
Change 1
4-81
TO 1C-130H-2-61FI-00-1
FROM SHT 65
213
Is an outboard propeller being
troubleshot?
YES
TO SHT 69
NO
214
a. Install a jumper wire between pins B
and V of plug P398 (1).
b. Remove junction box from synchrophaser rack.
Is a ground present on specified pin of
receptacle P-A2576A (3) or P-B2576A
(2)?
Prop
Rcpt Pin
Test Point
2
P-A2576A-45
3
P-B2576A-6
37
215
YES
Remove jumper wire. Repair
open circuit between plug P398
pin X and related receptacle
pin. (See figure 4-6 or 4-7.)
Prop
2
3
Rcpt Pin
P-A2576A-34
P-B2576A-14
37
NO
216
Remove jumper wire. Repair
open circuit between plug P398
pin B and related receptacle
pin. (See figure 4-6 or 4-7.)
Prop
2
3
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 67)
61-20-00
4-82
Change 1
Rcpt Pin
P-A2576A-45
P-B2576A-6
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 68)
61-20-00
Change 1
4-83
TO 1C-130H-2-61FI-00-1
FROM SHT 67
a. Reconnect plug P398 (1) at engine firewall.
b. Gain access to and disconnect plug P1139
(4) at outer wing break.
Is 25 to 50 ohms resistance present between
specified pins of receptacle J935 (5)?
Prop
Rcpt Pins
1
c and d
4
220
219
217
NO
Test Points
d and f
44
45
44
45
YES
a. Gain access to and disconnect
plug P398 (1) at engine firewall.
b. Install a jumper wire between
plug pins B and V.
Is a ground present on specified
receptacle J935 (5) pin?
Prop
Rcpt Pins Test Points
1
d
4
f
45
NO
Remove jumper
wire. Repair open
circuit between
plug P398 pin B
and related receptacle J935 pin.
(See figure 4-6 or
4-7.)
Prop
1
4
45
Rcpt Pin
d
f
YES
221
Remove jumper wire. Repair open circuit
between plug P398 pin X and related receptacle J935 pin. (See figure 4-6 or 4-7.)
Prop
1
4
Rcpt Pin
c
d
218
a. Install a jumper wire between plug
P1139 (4) pin d and airplane ground.
b. Remove junction box from synchrophaser rack.
Is a ground present on specified pin of receptacle P-B2576A (2) or P-A2576A (3)?
Prop
Rcpt Pin
1
P-B2576A-3
4
P-A2576A-24
222
Remove jumper wire. Repair open circuit
between plug P1139 pin d and related receptacle pin. (See figure 4-6 or 4-7.)
NO
Prop
1
4
Test Point
37
Rcpt Pin
P-B2576A-3
P-A2576A-24
37
YES
223
Remove jumper wire. Repair open circuit between
specified plug P1139 pin and related receptacle pin.
(See figure 4-6 or 4-7.)
Prop
1
4
Plug Pin
c
f
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 69)
61-20-00
4-84
Change 1
Rcpt Pin
P-B2576A-5
P-B2576A-19
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 70)
61-20-00
Change 1
4-85
TO 1C-130H-2-61FI-00-1
FROM SHT 55
224
Place RESISTANCE TEST switch (4) to 6
Does FUNCTION display (2) indicate 120
to 180 ohms?
(Speed bias ref winding R)
Prop
1
2
3
4
NO
TO SHT 73
Sync Rcpt Pins
P-B2576A-39, P-B2576A-30
P-A2576A-41, P-B2576A-30
P-A2576A-42, P-B2576A-30
P-B2576A-38, P-B2576A-30
YES
225
Move throttles (1) below GROUND IDLE/
GND IDLE.
Do FUNCTION display (2) and AC VOLTS
display (3) indicate 1999?
(Sync disarming switch)
Prop
1
2
3
4
227
NO
Sync Rcpt Pins
P-B2576A-39, P-B2576A-30
P-A2576A-41, P-B2576A-30
P-A2576A-42, P-B2576A-30
P-B2576A-38, P-B2576A-30
Adjust or replace synchrophaser disarming switch (6)
as required in accordance with
TO 1C-130H-2-76JG-00-1, 7610-33.
YES
226
a. Move throttles (1) above FLIGHT IDLE/
FLT IDLE.
b. Place propeller governor control switches (5) to MECH GOV/MECH.
Does FUNCTION display (2) indicate
1999?
(propeller governor control switch)
Prop
1
2
3
4
228
NO
Replace propeller governor control switch.
Sync Rcpt Pins
P-B2576A-39, P-B2576A-30
P-A2576A-41, P-B2576A-30
P-A2576A-42, P-B2576A-30
P-B2576A-38, P-B2576A-30
YES
TO SHT 81
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 4-5. Synchrophaser System Malfunction (Sheet 71)
61-20-00
4-86
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 72)
61-20-00
Change 1
4-87
TO 1C-130H-2-61FI-00-1
FROM SHT 71
229
Gain access to and disconnect plug P390 (3)
at valve housing assembly.
Is 120 to 180 ohms resistance present between pins A and K of valve housing assembly receptacle (4)?
69
233
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
71
YES
230
a. Reconnect plug P390 (3) at valve housing
assembly.
b. Gain access to and disconnect plug P398
(2) at engine firewall.
Is 120 to 180 ohms resistance present between pins A and V of receptacle J239 (1)?
57
234
Repair open circuit between receptacle J239 pin A and plug
P390 pin A. (See figure 4-6 or
4-7.)
NO
59
YES
231
a. Reconnect plug P398 (2) at engine firewall.
b. Disengage junction box from synchrophaser rack.
c. Gain access to terminals of propeller governor control switch (5).
Is 120 to 180 ohms resistance present between switch terminal 3 and airplane ground?
NO
TO SHT 75
86
YES
232
Is there continuity between switch terminals 2
and 3?
85
235
NO
86
Replace propeller governor control switch.
YES
TO SHT 77
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 73)
61-20-00
4-88
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 74)
61-20-00
Change 1
4-89
TO 1C-130H-2-61FI-00-1
FROM SHT 73
238
236
Is an outboard propeller being
troubleshot?
NO
YES
Repair open circuit between terminal 3 of propeller governor
control switch (4) and pin A of
plug P398 (1). (See figure4-6
or 4-7.)
237
Gain access to and disconnect
plug P1139 (3) at outer wing
break.
Is 120 to 180 ohms resistance
present between specified pin of
receptacle J935 (2) and airplane
ground?
Prop
Rcpt Pin
1
e
4
k
239
NO
Test Point
46
Repair open circuit between pin
A of plug P398 (1) and related
receptacle J395 pin. (See figure 4-6 or 4-7.)
Prop
1
4
Rcpt Pin
e
k
46
YES
240
Repair open circuit between terminal 3 of propeller governor
control switch (4) and related
plug P1139 pin. (See figure 46 or 4-7.)
Prop
1
4
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 4-6 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 75)
61-20-00
4-90
Change 1
Plug Pin
e
k
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 76)
61-20-00
Change 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 between specified terminal and airplane ground?
Prop
TB Term
1
36
2
37
3
38
4
39
243
Test Point
NO
84
Repair open circuit between terminal 2 of
propeller governor control switch (4) and
related terminal board TB126A terminal.
(See figure 4-6 or 4-7.)
Prop
1
2
84
84
TB Term
36
37
Prop
3
4
TB Term
38
39
84
YES
242
Gain access to specified terminal board.
Is 120 to 180 ohms resistance present between specified terminal and airplane ground?
Prop
TB-Term
1
TB135A (1) -169
244
Test Point
2
TB135A (1) -170
3
TB146A (3) -210
4
TB146A (3) -211
81
YES
81
81
Repair open circuit between specified terminal and related pin of receptacle PB2576A (5) or P-A2576A (6). (See figure 4-6 or 4-7.)
Prop
1
2
3
4
TB-Term
TB135A-169
TB135A-170
TB146A-210
TB146A-211
81
NO
TO SHT 79
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 4-6 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 77)
61-20-00
4-92
Change 1
Rcpt Pin
P-B2576A-39
P-A2576A-41
P-A2576A-42
P-B2576A-38
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 78)
61-20-00
Change 1
4-93
TO 1C-130H-2-61FI-00-1
FROM SHT 77
247
245
Gain access to terminals of synchrophaser disarming switch (3).
Is 120 to 180 ohms resistance
present between switch terminal
2NC and airplane ground?
NO
Repair open circuit between synchrophaser disarming switch terminal
2NC and related terminal of terminal
board TB156A (1). (See figure 4-6 or 47.)
Prop
1
2
83
TB Term
36
37
Prop
3
4
TB Term
38
39
YES
248
246
Is 120 to 180 ohms resistance
present between switch terminal
1NC and airplane ground?
82
NO
YES
Repair open circuit between synchrophaser disarming switch terminal
1NC and related terminal. (See figure 46 or 4-7.)
Prop
1
2
3
4
TB-Term
TB135A (4)
TB135A (4)
TB146A (2)
TB146A (2)
-169
-170
-210
-211
249
Adjust or replace synchrophaser disarming switch as required in accordance with
TO 1C-130H-2-76JG-00-1, 76-10-38.
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 79)
61-20-00
4-94
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 80)
61-20-00
Change 1
4-95
TO 1C-130H-2-61FI-00-1
FROM SHT 73
250
NO
Is an outboard propeller being troubleshot?
TO SHT 83
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
ohms?
(Clutch 1 and 4 winding parallel R)
Prop
1,4
YES
TO SHT 89
Sync Rcpt Pins
P-A2576A-30, P-B2576A-30
NO
TO SHT 107
Figure 4-5. Synchrophaser System Malfunction (Sheet 81)
61-20-00
4-96
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 82)
61-20-00
Change 1
4-97
TO 1C-130H-2-61FI-00-1
254
FROM SHT 81
252
NO
Is No. 2 propeller (1) being troubleshot?
YES
a. Place TYPE SELECT switch (4) to
TUBE.
b. Place RESISTANCE TEST switch
(5) to 8.
c. Place SYNCHROPHASE MASTER/
MSTR switch (2) to engine 2.
d. Momentarily hold PROP RESYNCHROPHASE/PROP SYNC switch (3)
to RESYNC/INDEX.
Does FUNCTION display (6) indicate 20
to 30 ohms while switch is held
(Clutch 3 winding R)
Prop
3
Synch Rcpt Pins
P-A2576A-30, P-B2576A-30
YES
TO SHT 89
253
a. Place TYPE SELECT switch (4) to
TUBE.
b. Place RESISTANCE TEST switch
(5) to 8.
c. Place SYNCHROPHASE MASTER/
MSTR switch (2) to engine 3.
d. Momentarily hold PROP RESYNCHROPHASE/PROP SYNC switch (3)
to RESYNC/INDEX.
Does FUNCTION display (6) indicate 20
to 30 ohms while switch is held
(Clutch 2 winding R)
Prop
2
NO
TO SHT 87
Synch Rcpt Pins
P-A2576A-30, P-B2576A-30
YES
TO SHT 89
Figure 4-5. Synchrophaser System Malfunction (Sheet 83)
61-20-00
4-98
Change 1
NO
TO SHT 85
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 84)
61-20-00
Change 1
4-99
TO 1C-130H-2-61FI-00-1
FROM SHT 83
255
Gain access to and disconnect plug P390
(6) at valve housing assembly.
Is 60 to 90 ohms resistance present between pins K and P of valve housing assembly receptacle (5)?
71
259
NO
Replace valve housing assembly in accordance with TO 1C-130H-2-61JG-20-1,
61-20-02.
76
YES
256
a. Reconnect plug P390 (6) to valve housing assembly.
b. Gain access to and disconnect plug
P398 (2) at engine firewall.
Is 60 to 90 ohms resistance present between pins P and V of receptacle J239 (1)?
64
260
NO
Repair open circuit between receptacle
J239 pin P and plug P390 pin P. (See
figure 4-6.)
59
YES
257
a. Reconnect plug P398 (2) at engine firewall.
b. Gain access to terminals of SYNCHROPHASE MASTER/MSTR switch (3).
Is there continuity between switch terminals
4 and 5?
20
261
NO
Replace SYNCHROPHASE MASTER/
MSTR switch.
16
YES
258
Gain access to terminal board TB128A (4).
Is there continuity between terminal board
terminal 18 and SYNCHROPHASE
MASTER/MSTR switch (3) terminal 4?
31
262
YES
Repair open circuit between terminal
board terminal 18 and plug P398 pin P.
(See figure 4-6 or 4-7.)
20
NO
263
Repair open circuit. (See figure 4-6 or 47.)
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 85)
61-20-00
4-100
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 86)
61-20-00
Change 1
4-101
TO 1C-130H-2-61FI-00-1
FROM SHT 83
264
Gain access to and disconnect plug P390 (6) at valve
housing assembly.
Is 60 to 90 ohms resistance present between pins K and P
of valve housing assembly receptacle (5)?
71
268
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
76
YES
265
a. Reconnect plug P390 (6) to valve housing assembly.
b. Gain access to and disconnect plug P398 (2) at engine
firewall.
Is 60 to 90 ohms resistance present between pins P and V
of receptacle J239 (1)?
64
269
NO
Repair open circuit between receptacle J239 pin P and Plug
P390 pin P. (See figure 4-6 or
4-7.)
59
YES
266
a. Reconnect plug P398 (2) at engine firewall.
b. Gain access to terminals of SYNCHROPHASE
MASTER/MSTR switch (3).
Is there continuity between switch terminals 5 and 6?
16
270
NO
Replace SYNCHROPHASE
MASTER/MSTR switch.
21
YES
267
271
Gain access to terminal board TB128A (4).
Is there continuity between terminal board terminal 19 and
SYNCHROPHASE MASTER/MSTR switch (3) terminal 6?
32
21
YES
Repair open cirucit between terminal board terminal 19 and
plug P398 pin P. (See figure 46 or 4-7.)
NO
272
Repair open circuit. (See figure
4-6 or 4-7.)
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 87)
61-20-00
4-102
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 88)
61-20-00
Change 1
4-103
TO 1C-130H-2-61FI-00-1
FROM SHT 81 OR 83
273
NOTE
During megger checks, an indication of
1999 in both the FUNCTION and AC
VOLTS displays is an acceptable measurement.
a. Place SYNCHROPHASE MASTER/
MSTR switch (5) to OFF.
b. Place TYPE SELECT switch (2) to
SOLID STATE.
c. Place RESISTANCE TEST switch (4) to
13.
Does FUNCTION display (1) indicate 0.5 or
greater and does AC VOLTS display (3) indicate 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
NO
TO SHT 91
YES
274
Place RESISTANCE TEST switch (4) to
14.
Does FUNCTION display (1) indicate 1.0 or
greater and does AC VOLTS display (3) indicate 6?
(Feedback pot megger chk)
Prop
Sync Rcpt Pins
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
NO
TO SHT 99
YES
TO SHT 141
Figure 4-5. Synchrophaser System Malfunction (Sheet 89)
61-20-00
4-104
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 90)
61-20-00
Change 1
4-105
TO 1C-130H-2-61FI-00-1
FROM SHT 89
275
a. Gain access to and disconnect
plug P390 (3) at valve housing
assembly.
b. Install a jumper wire between
plug pins B and M.
Does FUNCTION display (5) indicate 0.5 or greater and does AC
VOLTS display (4) indicate 6?
279
Remove jumper wire. Replace
valve housing assembly in accordance with TO 1C-130H-261JG-20-1, 61-20-02.
YES
NO
276
a. Remove jumper wire from plug
P390 (3) but do not reconnect
plug.
b. Gain access to and disconnect
plug P398 (2) at engine firewall.
c. Install a jumper wire between
plug P398 pins B and X.
Does FUNCTION display (5) indicate 0.5 or greater and does AC
VOLTS display (4) indicate 6?
NO
278
Is an outboard propeller being
troubleshot?
NO
TO SHT 93
YES
YES
TO SHT 95
277
Remove jumper wire from plug
P398 (2) and reconnect plug at
engine firewall.
Does FUNCTION display (5) indicate 0.5 or greater and does AC
VOLTS display (4) indicate 6?
280
NO
Repair ground fault between pin
X of receptacle J239 (1) and
plug P390 pin M. (See figure
4-6 or 4-7.)
YES
281
Repair ground fault between pin
B of receptacle J239 (1) and
plug P390 pin B. (See figure 46 or 4-7.)
Figure 4-5. Synchrophaser System Malfunction (Sheet 91)
61-20-00
4-106
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 92)
61-20-00
Change 1
4-107
TO 1C-130H-2-61FI-00-1
FROM SHT 91
283
282
Remove jumper wire from plug
P398 (1) but do not reconnect
plug.
Does FUNCTION display (5) indicate 0.5 or grater and does AC
VOLTS display (4) indicate 6?
YES
NO
Repair ground fault between
plug P398 pin X and related pin
of receptacle P-A2576A (3) or
P-B2576A (2). (See figure 4-6
or 4-7.)
Prop
2
3
Rcpt Pin
P-A2576A-34
P-B2576A-14
284
Repair ground fault between
plug P398 pin B and related pin
of receptacle P-A2576A (3) or
P-B2576A (2). (See figure 4-6
or 4-7.)
Prop
2
3
Figure 4-5. Synchrophaser System Malfunction (Sheet 93)
61-20-00
4-108
Change 1
Rcpt Pin
P-A2576A-45
P-B2576A-6
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 94)
61-20-00
Change 1
4-109
TO 1C-130H-2-61FI-00-1
FROM SHT 91
285
a. Remove jumper wire from plug
P398 (1) but do not reconnect
plug.
b. Gain access to and disconnect
plug P1139 (5) at outer wing
break.
c. Install a jumper wire between
specified plug pins.
Prop
1
4
NO
TO SHT 97
Plug Pins
c and d
d and f
Does FUNCTION display (3) indicate 0.5 or greater and does AC
VOLTS display (2) indicate 6?
YES
287
286
Remove jumper wire from plug
P1139 (5) and reconnect plug at
outer wing break.
Does FUNCTION display (3) indicate 0.5 or greater and does AC
VOLTS display (2) indicate 6?
NO
YES
Repair ground fault between
plug P398 pin X and related pin
of receptacle J935 (4). (See
figure 4-6 or 4-7.)
Prop
1
4
Rcpt Pin
c
d
288
Repair ground fault between
plug P398 pin B and related pin
of receptacle J935 (4). (See
figure 4-6 or 4-7.)
Prop
1
4
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 4-5. Synchrophaser System Malfunction (Sheet 95)
61-20-00
4-110
Change 1
Rcpt Pin
d
f
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 96)
61-20-00
Change 1
4-111
TO 1C-130H-2-61FI-00-1
FROM SHT 95
290
289
Remove jumper wire from plug
P1139 (5) but do not reconnect
plug.
Does FUNCTION display (1) indicate 0.5 or greater and does AC
VOLTS display (2) indicate 6?
YES
NO
Repair ground fault between specified
plug P1139 pin and related pin of receptacle P-B2576A (3). (See figure
4-6 or 4-7.)
Prop
1
4
Plug Pin
d
f
Rcpt Pin
P-B2576A-3
P-B2576A-19
291
Repair ground fault between specified
plug P130/P1139 pin and related pin
of receptacle P-A2576A (4) or PB2576B (3). (See figure 4-6 or 4-7.)
Prop
1
4
Plug Pin
c
d
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 4-5. Synchrophaser System Malfunction (Sheet 97)
61-20-00
4-112
Change 1
Rcpt Pin
P-B2576A-5
P-A2576A-24
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 98)
61-20-00
Change 1
4-113
TO 1C-130H-2-61FI-00-1
FROM SHT 89
292
a. Gain acess to and disconnect
plug P390 (3) at valve housing
assembly.
b. Install a jumper wire between
plug pins C and L.
Does FUNCTION display (5) indicate 1.0 or greater and does AC
VOLTS display (4) indicate 6?
295
YES
298
Remove jumper wire and install it
between plug pins C and N.
Does FUNCTION display (5) indicate 1.0 or greater and does AC
VOLTS display (4) indicate 6?
YES Remove jumper wire. Replace
valve housing in accordance
with TO 1C-130H-2-61JG-20-1,
61-20-02.
NO
NO
296
a. Remove jumper wire from plug P390
(3).
b. Gain access to and disconnect plug
P398 (2) at engine firewall.
c. Install jumper wire between plug P398
(2) pins C and N.
Does FUNCTION display (5) indicate 1.0 or
greater and does AC VOLTS display (4) indicate 6?
299
Remove jumper wire.
Repair ground fault
YES between pin N of receptacle J239 (1) and
plug P390 pin N.
(See figure 4-6 or 47.)
NO
TO SHT 101
300
297
293
Remove jumper wire and install it
between plug pins C and N.
Does FUNCTION display (5) indicate 1.0 or greater and does AC
VOLTS display (4) indicate 6?
NO
a. Remove jumper wire from plug P390 (3).
b. Gain access to and disconnect plug P398
(2) at engine firewall.
Does FUNCTION display (5) indicate 1.0 or
greater and does AC VOLTS display (4) indicate 6?
YES
Repair ground fault
YES between pin C of
receptacle J239 (1)
and plug P390 pin
C. (See figure 4-6
or 4-7.)
NO
TO SHT 103
294
a. Remove jumper wire from plug P390 (3).
b. Gain access to and disconnect plug P398
(2) at engine firewall.
c. Install jumper wire between plug P398 (2)
pins C and W.
Does FUNCTION display (5) indicate 1.0 or
greater and does AC VOLTS display (4) indicate 6?
301
YES
Remove jumper wire. Repair ground
fault between pin W of receptacle
J239 (1) and plug P390 pin L. (See
figure 4-6 or 4-7.)
NO
TO SHT 105
Figure 4-5. Synchrophaser System Malfunction (Sheet 99)
61-20-00
4-114
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 100)
61-20-00
Change 1
4-115
TO 1C-130H-2-61FI-00-1
304
FROM SHT 99
302
Is an outboard propeller being
troubleshot?
NO
Remove jumper wire. Repair
ground fault between pin N of
plug P398 (1) and related pin of
receptacle P-A2576A (5). (See
figure 4-6 or 4-7.)
Prop
2
3
YES
Rcpt Pin
14
2
303
a. Remove jumper wire from plug
P398 (1).
b. Gain access to and disconnect
plug P1139 (7) at outer wing
break.
c. Install jumper wire between
specified plug P1139 (7) pins.
Prop
1
4
305
NO
Plug Pin
h and k
e and h
Remove jumper wire. Repair
ground fault between plug
P1139 pin h and related pin of
receptacle P-B2576A (4). (See
figure 4-6 or 4-7.)
Prop
1
4
Rcpt Pin
7
23
Does FUNCTION display (2) indicate 1.0 or greater and does AC
VOLTS display (3) indicate 6?
YES
306
Remove jumper wire. Repair
ground fault between pin h of
receptacle J935 (6) and plug
P398 pin N. (See figure 4-6 or
4-7.)
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 4-5. Synchrophaser System Malfunction (Sheet 101)
61-20-00
4-116
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 102)
61-20-00
Change 1
4-117
TO 1C-130H-2-61FI-00-1
309
FROM SHT 99
307
Is an outboard propeller being
troubleshot?
NO
Repair ground fault between pin C of
plug P398 (1) and related pin of receptacle P-A2576A (5). (See figure
4-6 or 4-7.)
Prop
2
3
YES
Rcpt Pin
3
4
310
308
Gain access to and disconnect
plug P1139 (6) at outer wing
break.
Does FUNCTION display (2) indicate 1.0 or greater and does AC
VOLTS display (3) indicate 6?
NO
YES
Repair ground fault between specified
plug P1139 pin and related pin of receptacle P-B2576A (4). (See figure
4-6 or 4-7.)
Prop
1
4
Plug Pin
k
e
Rcpt Pin
8
17
311
Repair ground fault between pin C of
plug P398 (1) and related plug P1139
pin. (See figure 4-6 or 4-7.)
Prop
1
4
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 4-5. Synchrophaser System Malfunction (Sheet 103)
61-20-00
4-118
Change 1
Rcpt Pin
k
e
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 104)
61-20-00
Change 1
4-119
TO 1C-130H-2-61FI-00-1
314
FROM SHT 99
312
Is an outboard propeller being
troubleshot?
NO
Remove jumper wire. Repair
ground fault between pin W of
plug P398 (1) and related pin of
receptacle P-A2576A (5). (See
figure 4-6 or 4-7.)
Prop
2
3
YES
Rcpt Pin
5
6
313
a. Remove jumper wire from plug
P398 (1).
b. Gain access to and disconnect
plug P1139 (7) at outer wing
break.
c. Install jumper wire between
specified plug P1139 (7) pins.
Prop
1
4
315
NO
Plug Pin
j and k
e and j
Remove jumper wire. Repair
ground fault between plug
P1139 pin j and related pin of
receptacle P-B2576A (4). (See
figure 4-6 or 4-7.)
Prop
1
4
Rcpt Pin
16
26
Does FUNCTION display (2) indicate 1.0 or greater and does AC
VOLTS display (3) indicate 6?
YES
316
Remove jumper wire. Repair
ground fault between pin j of receptacle J935 (6) and plug
P398 pin W. (See figure 4-6 or
4-7.)
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 4-5. Synchrophaser System Malfunction (Sheet 105)
61-20-00
4-120
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 106)
61-20-00
Change 1
4-121
TO 1C-130H-2-61FI-00-1
FROM SHT 81
317
Gain access to and disconnect plug
P390 (3) at valve housing assembly.
Is 60 to 90 ohms resistance present between pins K and P of valve housing
assembly receptacle (4)?
71
320
NO
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
76
YES
318
a. Reconnect plug P390 (3) to valve
housing assembly.
b. Gain access to and disconnect plug
P398 (2) at engine firewall.
Is 60 to 90 ohms resistance present between plug pins P and V?
64
321
NO
Repair open circuit between pin
P of receptacle J239 (1) and
plug P390 pin P. (See figure 46 or 4-7.)
59
YES
319
a. Reconnect plug P398 (2) at engine
firewall.
b. Gain access to and disconnect plug
P1139 (7) at outer wing break.
Is 60 to 90 ohms resistance present between pin m of receptacle J935 (6) and
airplane ground?
322
NO
Repair open circuit between receptacle J935 pin m and plug
P398 pin P. (See figure 4-6 or
4-7.)
52
YES
323
Repair open circuit between
plug P1139 pin m and terminal
9 of terminal board TB1C (5).
(See figure 4-6 or 4-7.)
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
3.
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 107)
61-20-00
4-122
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 108)
61-20-00
Change 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, 71-0010.
b. If necessary, perform Preparation C.
c. If necessary, place propeller governor control switches (5) to NORMAL/
NORM.
d. Place RESISTANCE TEST switch (4) to 7.
Does FUNCTION display (1) indicate 0.3 to 10 ohms? (Pulse gen R)
Prop
1
2
3
4
NO
TO SHT 111
Sync Rcpt Pins
P-B2576A-20, P-B2576A-34
P-A2576A-28, P-A2576A-37
P-A2576A-36, P-A2576A-29
P-B2576A-1, P-B2576A-31
YES
325
NOTE
During megger checks, an indication of 1999 in both the FUNCTION and AC
VOLTS 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.
Does FUNCTION display (1) indicate 1.0 or greater and does AC VOLTS
display (3) indicate 6?
(Pulse gen megger chk)
Prop
1
2
3
4
NO
TO SHT 125
Sync Rcpt Pins
P-B2576A-34, P-B2576A-30
P-A2576A-37, P-B2576A-30
P-A2576A-36, P-B2576A-30
P-B2576A-1, P-B2576A-30
YES
TO SHT 141
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 4-5. Synchrophaser System Malfunction (Sheet 109)
61-20-00
4-124
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 110)
61-20-00
Change 1
4-125
TO 1C-130H-2-61FI-00-1
FROM SHT 109
326
328
Gain access to and disconnect
plug P392 (2) at pump housing.
Is 0.3 to 0.5 ohm resistance present between pins A and B of
valve housing assembly receptacle (3)?
77
NO
Remove pulse generator (4) in accordance with TO 1C-130H-261JG-20-1, 61-20-10.
Is 0.3 to 0.5 ohm resistance present between the two pulse generator pins?
78
79
YES
330
NO
Replace pulse generator in accordance with TO 1C-130H-261JG-20-1, 61-20-10.
80
YES
331
Repair or replace pulse generator wiring on pump housing (5).
327
329
a. Reconnect plug P392 (2) to
pump housing.
b. Gain access to and disconnect
plug P396 (6) at engine firewall.
Is 0.3 to 0.5 ohm resistance present between pins A and B of receptacle J241 (1)?
65
66
YES
NO
a. Gain access to and disconnect
plug P392 (2) at pump housing.
b. Install a jumper wire between
plug pins A and E (ground).
Is resistance between receptacle
J241 (1) pins A and E less than 1
ohm?
332
NO
Remove jumper wire. Repair
wiring fault between receptacle
J241 pin A and plug P392 pin
A. (See figure 4-6 or 4-7.)
65
YES
TO SHT 113
333
Remove jumper wire. Repair
wiring fault between receptacle
J241 pin B and plug P392 pin
B. (See figure 4-6 or 4-7.)
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 111)
61-20-00
4-126
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 112)
61-20-00
Change 1
4-127
TO 1C-130H-2-61FI-00-1
FROM SHT 111
334
Is airplane being troubleshot a
year model AF90-1057 and up?
YES
TO SHT 115
NO
335
Is an outboard propeller being
troubleshot?
NO
TO SHT 121
YES
336
a. Reconnect plug P396 (1) at
engine firewall.
b. Gain access to and disconnect
plug P1225 (3) at outer wing
break.
Is 0.3 to 0.7 ohm resistance present between pins A and B of receptacle J660 (2)?
53
YES
TO SHT 123
54
NO
337
a. Gain access to and disconnect
plug P396 (1) at engine firewall.
b. Install a jumper wire between
plug pins A and E (ground).
Is resistance between receptacle
J660 (2) pin A and airplane
ground less than 1 ohm?
338
NO
Remove jumper wire. Repair
wiring fault between receptacle
J660 pin A and plug P396 pin
A. (See figure 4-6.)
53
YES
339
Remove jumper wire. Repair
wiring fault between receptacle
J660 pin B and plug P396 pin
B. (See figure 4-6.)
NOTE
See figure 4-6 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 113)
61-20-00
4-128
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 114)
61-20-00
Change 1
4-129
TO 1C-130H-2-61FI-00-1
FROM SHT 113
341
340
a. Reconnect plug P396 (1) at
engine firewall.
b. Gain access to terminal
board TB105AG (2).
Is 0.3 to 0.7 ohm resistance
present between specified terminals?
YES
Prop
TB Term
1
1 and 2
2
3 and 4
3
5 and 6
4
7 and 8
TestPoints
a. Gain access to and disconnect
plug P396 (1) at engine firewall.
b. Install a jumper wire between
plug pins A and E (ground).
c. Remove junction box from
synchrophaser rack.
Is resistance between specified
pin of receptacle P-B2576A (3) or
P-A2576A (4) and airplane ground
less than 1 ohm?
43
42
Prop Rcpt Pin
43
42
1
P-B2576A-34
43
42
2
P-A2576A-37
43
42
3
P-A2576A-36
4
P-B2576A-1
NO
Test Point
39
39
342
NO
Remove jumper wire. Repair wiring fault between specified receptacle pin and related terminal
board TB105AG terminal. (See
figure 4-6 or 4-7.)
Prop
1
2
3
4
Rcpt Pin
P-B2576A-34
P-A2576A-37
P-A2576A-36
P-B2576A-1
TB Term
2
4
6
8
39
39
YES
TO SHT 117
343
Remove jumper wire. Repair wiring fault between specified receptacle pin and related terminal
board TB105AG terminal. (See
figure 4-6 or 4-7.)
Prop
1
2
3
4
Rcpt Pin
P-B2576A-20
P-A2576A-28
P-A2576A-29
P-B2576A-31
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 115)
61-20-00
4-130
Change 1
TB Term
1
3
5
7
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 116)
61-20-00
Change 1
4-131
TO 1C-130H-2-61FI-00-1
346
FROM SHT 115
344
Is an outboard propeller being
troubleshot?
NO
YES
a. Gain access to and disconnect
plug P396 (1) at engine firewall.
b. Install a jumper wire between
plug pins A and E (ground).
Is resistance between specified
terminal of terminal board
TB105AG (2) and airplane ground
less than 1 ohm?
Prop
TB Term
2
4
3
6
348
NO
Remove jumper wire. Repair
wiring fault between plug P396
pin A and related terminal
board TB105AG terminal. (See
figure 4-6 or 4-7.)
Prop
2
3
Test Point
42
TB Term
4
6
42
YES
349
Remove jumper wire. Repair
wiring fault between plug P396
pin B and related terminal
board TB105AG terminal. (See
figure 4-6 or 4-7.)
Prop
2
3
TB Term
3
5
347
345
Gain access to and disconnect
plug P1225 (3) at outer wing
break.
Is 0.3 to 0.7 ohm resistance present between pins A and B of receptacle J660 (4)?
53
54
YES
NO
a. Gain access to and disconnect
plug P396 (1) at engine firewall.
b. Install a jumper wire between
plug pins A and E (ground).
Is resistance between receptacle
J660 (4) pin A and airplane
ground less than 1 ohm?
350
NO
Remove jumper wire. Repair
wiring fault between receptacle
J660 pin A and plug P396 pin
A. (See figure 4-6 or 4-7.)
53
YES
TO SHT 119
351
Remove jumper wire. Repair
wiring fault between receptacle
J660 pin B and plug P396 pin
B. (See figure 4-6 or 4-7.)
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 117)
61-20-00
4-132
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 118)
61-20-00
Change 1
4-133
TO 1C-130H-2-61FI-00-1
FROM SHT 117
352
a. Gain access to and disconnect
plug P1225 (1) at outer wing
break.
b. Install a jumper wire between
plug pin A and airplane ground.
Is resistance between specified
terminal of terminal board
TB105AG (2) and airplane ground
less than 1 ohm?
Prop
TB Term
1
2
4
8
Test Point
42
353
NO
Remove jumper wire. Repair
wiring fault between plug P1225
pin A and related terminal
board TB105AG terminal. (See
figure 4-6 or 4-7.)
Prop
1
4
TB Term
2
8
42
YES
354
Remove jumper wire. Repair
wiring fault between plug P1225
pin B and related terminal
board TB105AG terminal. (See
figure 4-6 or 4-7.)
Prop
1
4
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 119)
61-20-00
4-134
Change 1
TB Term
1
7
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 120)
61-20-00
Change 1
4-135
TO 1C-130H-2-61FI-00-1
FROM SHT 113
355
a. Install a jumper wire between pins A
and E (ground) of plug P396 (1).
b. Remove junction box from synchrophaser rack.
Is resistance on specified pin of receptacle
P-A2576A (2) less than 1 ohm?
Prop
Rcpt Pin
2
37
3
36
Test Point
39
356
NO
Remove jumper wire. Repair
wiring fault between plug P396
pin A and related receptacle PA2576A pin. (See figure 4-6.)
Prop
2
3
Rcpt Pin
37
36
39
YES
357
Remove jumper wire. Repair
wiring fault between plug P396
pin B and related receptacle PA2576A pin. (See figure 4-6.)
Prop
2
3
NOTE
See figure 4-6 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 121)
61-20-00
4-136
Change 1
Rcpt Pin
28
29
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 122)
61-20-00
Change 1
4-137
TO 1C-130H-2-61FI-00-1
FROM SHT 113
358
a. Install a jumper wire between
pin A of plug P1225 (1) and
airpane ground.
b. Remove junction box from
synchrophaser rack.
Is resistance on specified pin of
receptacle P-B2576A (2) less than
1 ohm?
Prop
Rcpt Pin
1
34
4
1
Test Point
39
359
NO
Remove jumper wire. Repair
wiring fault between plug P1225
pin A and related receptacle PB2576A pin. (See figure 4-6.)
Prop
1
4
Rcpt Pin
34
1
39
YES
360
Remove jumper wire. Repair
wiring fault between plug P1225
pin B and related receptacle PB2576A pin. (See figure 4-6.)
Prop
1
4
NOTE
See figure 4-6 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 123)
61-20-00
4-138
Change 1
Rcpt Pin
20
31
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 124)
61-20-00
Change 1
4-139
TO 1C-130H-2-61FI-00-1
FROM SHT 109
364
361
a. Gain access to and disconnect plug P392 (2) at pump
housing.
b. Install a jumper wire between plug pins A and B.
Does FUNCTION display (5)
indicate 1.0 or greater and
does AC VOLTS display (4) indicate 6?
YES
NO
a. Remove jumper wire from plug P392
(2) and reconnect plug at pump housing.
b. Remove pulse generator (3) in accordance with TO 1C-130H-2-61JG-201, 61-20-10.
c. Install a jumper wire between the
two pins of the pulse generator wiring
harness where the pulse generator connects.
Does FUNCTION display (5) indicate
1.0 or greater and does AC VOLTS display (4) indicate 6?
366
YES Remove jumper wire. Replace pulse generator in accordance with TO 1C-130H2-61JG-20-1, 61-20-10.
NO
367
Repair or replace pulse generator wiring on pump housing.
362
a. Remove jumper wire from plug
P392 (2) but do not reconnect
plug.
b. Gain access to and disconnect
plug P396 (6) at engine firewall.
c. Install a jumper wire between
plug P396 (6) pins A and B.
Does FUNCTION display (5) indicate 1.0 or greater and does AC
VOLTS display (4) indicate 6?
365
YES
Remove jumper wire from plug
P396 (6) and reconnect plug at
engine firewall.
Does FUNCTION display (5) indicate 1.0 or greater and does AC
VOLTS display (4) indicate 6?
368
NO
Repair ground fault between pin
A of receptacle J241 (1) and
plug P392 pin A. (See figure 46 or 4-7.)
YES
NO
369
Repair ground fault between pin
B of receptacle J241 (1) and
plug P392 pin B. (See figure 46 or 4-7.)
363
Is an outboard propeller being
troubleshot?
NO
TO SHT 127
YES
TO SHT 133
Figure 4-5. Synchrophaser System Malfunction (Sheet 125)
61-20-00
4-140
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 126)
61-20-00
Change 1
4-141
TO 1C-130H-2-61FI-00-1
FROM SHT 125
370
Is airplane being troubleshot
model AF90-1057 and up?
YES
TO SHT 129
NO
372
371
Remove jumper wire from plug
P396 (1) but do not reconnect
plug.
Does FUNCTION display (4) indicate 1.0 or greater and does AC
VOLTS display (3) indicate 6?
YES
NO
Repair ground fault between
plug P396 pin A and related pin
of receptacle P-A2576A (2).
(See figure 4-6.)
Prop
2
3
Rcpt Pin
37
36
373
Repair ground fault between
plug P396 pin B and related pin
of receptacle P-A2576A (2).
(See figure 4-6.)
Prop
2
3
Figure 4-5. Synchrophaser System Malfunction (Sheet 127)
61-20-00
4-142
Change 1
Rcpt Pin
28
29
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 128)
61-20-00
Change 1
4-143
TO 1C-130H-2-61FI-00-1
FROM SHT 127
374
Remove jumper wire from plug P396 (1)
but do not reconnect plug.
Does FUNCTION display (2) indicate
1.0 or greater and does AC VOLTS display (3) indicate 6?
YES
TO SHT 131
NO
375
Gain access to terminal board TB105AG
(4) and disconnect specified wire from
specified terminal. (Leave remaining two
wires securely attached.)
Prop
2
3
Wire No.
2K95D20
3K95D20
TB Term
4
6
377
YES
Repair ground fault on specified
wire. (See figure 4-6 or 4-7.)
Prop
2
3
Wire No.
2K95D20
3K95D20
Does FUNCTION display (2) indicate
1.0 or greater and does AC VOLTS display (3) indicate 6?
NO
376
Disconnect remaining wires from specified terminal board TB105AG (4) terminal.
Prop
2
3
TB Term
4
6
Does FUNCTION display (2) indicate
1.0 or greater and does AC VOLTS display (3) indicate 6?
378
YES
Repair ground fault between plug
P396 pin A and related terminal
board TB105AG terminal. (See figure 4-6 or 4-7.)
Prop
2
3
TB Term
4
6
NO
379
Repair ground fault between specified terminal board TB105AG terminal and related pin of receptacle
P-A2576A (5). (See figure 4-6 or
4-7.)
Prop
2
3
TB Term
4
6
Figure 4-5. Synchrophaser System Malfunction (Sheet 129)
61-20-00
4-144
Change 1
Rcpt Pin
37
36
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 130)
61-20-00
Change 1
4-145
TO 1C-130H-2-61FI-00-1
FROM SHT 129
380
a. Reinstall jumper wire between
pins A and B of plug P396 (1).
b. Gain access to terminal board
TB105AG (4) and disconnect specified wire from specified terminal.
(Leave remaining two wires securely
attached.)
Prop
2
3
Wire No.
2K97D20
3K97D20
382
YES
TB Term
3
5
Remove jumper wire. Repair ground
fault on specified wire. (See figure 4-6
or 4-7.)
Prop
2
3
Wire No.
2K97D20
3K97D20
Does FUNCTION display (2) indicate
1.0 or greater and does AC VOLTS
display (3) indicate 6?
NO
381
Disconnect remaining wires from
specified terminal board TB105AG
(4) terminal.
Prop
2
3
TB Term
3
5
Does FUNCTION display (2) indicate
1.0 or greater and does AC VOLTS
display (3) indicate 6?
383
NO
Remove jumper wire. Repair ground
fault between plug P396 pin B and related terminal board TB105AG terminal. (See figure 4-6 or 4-7.)
Prop
2
3
TB Term
3
5
YES
384
Remove jumper wire. Repair ground
fault between specified terminal board
TB105AG terminal and related pin of
receptacle P-A2576A (5). (See figure
4-6 or 4-7.)
Prop
2
3
TB Term
3
5
Figure 4-5. Synchrophaser System Malfunction (Sheet 131)
61-20-00
4-146
Change 1
Rcpt Pin
28
29
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 132)
61-20-00
Change 1
4-147
TO 1C-130H-2-61FI-00-1
FROM SHT 125
385
Is airplane being troubleshot a
year model AF90-1057 and up?
YES
TO SHT 135
NO
386
a. Remove jumper wire from plug
P396 (1) but do not reconnect
plug.
b. Gain access to and disconnect
plug P1225 (5) at outer wing
break.
c. Install a jumper wire between
plug P1225 (5) pins A and B.
Does FUNCTION display (3) indicate 1.0 or greater and does AC
VOLTS display (2) indicate 6?
NO
TO SHT 139
YES
387
Remove jumper wire from plug
P1225 (5) and reconnect plug at
outer wing break.
Does FUNCTION display (3) indicate 1.0 or greater and does AC
VOLTS display (2) indicate 6?
388
YES
Repair ground fault between pin
B of receptacle J660 (4) and
plug P396 pin B. (See figure 46.)
NO
389
Repair ground fault between pin
A of receptacle J660 (4) and
plug P396 pin A. (See figure 46.)
Figure 4-5. Synchrophaser System Malfunction (Sheet 133)
61-20-00
4-148
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 134)
61-20-00
Change 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
plug.
Does FUNCTION display (2) indicate 1.0 or greater and does
AC VOLTS display (3) indicate 6?
YES
TO SHT 137
NO
391
Gain access to terminal board TB105AG (4) and disconnect
specified wire from specified terminal. (Leave remaining two
wires securely attached.)
Prop
1
4
Wire No.
1K95E20
4K95E20
394
Repair ground fault on
specified wire. (See
figure 4-6 or 4-7.)
YES
TB Term
2
8
Prop
1
4
Does FUNCTION display (2) indicate 1.0 or greater and does
AC VOLTS display (3) indicate 6?
Wire No.
1K95E20
1K95E20
NO
392
393
Disconnect remaining wires from
specified terminal board TB105AG
(4) terminal.
Prop
1
4
TB Term
2
8
Does FUNCTION display (2) indicate 1.0 or greater and does AC
VOLTS display (3) indicate 6?
NO
YES
a. Reconnect all wires to
terminal board TB105AG
(4).
b. Gain access to and disconnect plug P1225 (6) at
outer wing break.
Does FUNCTION display
(2) indicate 1.0 or greater
and does AC VOLTS display (3) indicate 6?
395
NO
Repair ground fault between plug
P1225 pin A and related terminal
board TB105AG terminal. (See figure
4-6 or 4-7.)
Prop
1
4
TB Term
2
8
YES
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 board
TB105AG terminal and related pin of receptacle PB2576A (5). (See figure 4-6 or 4-7.)
Prop
1
4
TB Term
2
8
Figure 4-5. Synchrophaser System Malfunction (Sheet 135)
61-20-00
4-150
Change 1
Rcpt Pin
34
1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 136)
61-20-00
Change 1
4-151
TO 1C-130H-2-61FI-00-1
FROM SHT 135
398
a. Reinstall jumper wire between pins A and B of
plug P396 (1).
b. Gain access to terminal board TB105AG (4)
and disconnect specified wire from specified terminal. (Leave remaining two wires securely attached.)
Prop
1
4
Wire No.
1K97E20
4K97E20
401
YES
TB Term
1
7
Remove jumper wire. Repair ground
fault on specified wire. (See figure 46 or 4-7.)
Prop
1
4
Wire No.
1K97E20
1K97E20
Does FUNCTION display (2) indicate 1.0 or
greater and does AC VOLTS display (3) indicate
6?
NO
399
402
Disconnect remaining wires from specified terminal board TB105AG (4) terminal.
Prop
1
4
TB Term
1
7
YES
Remove jumper wire. Repair ground
fault between specified terminal board
TB105AG terminal and related pin of
receptacle P-B2576A (5). (See figure
4-6 or 4-7.)
Prop
1
4
Does FUNCTION display (2) indicate 1.0 or
greater and does AC VOLTS display (3) indicate
6?
TB Term
1
7
Rcpt Pin
20
31
NO
400
403
a. Remove jumper wire from plug P396 (1) but
do not reconnect plug.
b. Gain access to and disconnect plug P1225 (6)
at outer wing break.
c. Install jumper wire between plug P1225 (6)
pins A and B.
Does FUNCTION display (2) indicate 1.0 or
greater and does AC VOLTS display (3) indicate
6?
NO
Remove jumper wire. Repair ground
fault between plug P1225 pin B and
related terminal board TB105AG terminal. (See figure 4-6 or 4-7.)
Prop
1
4
TB Term
1
7
YES
404
Remove jumper wire. Repair ground
fault between pin B of receptacle
J660 (7) and plug P396 pin B. (See
figure 4-6 or 4-7.)
Figure 4-5. Synchrophaser System Malfunction (Sheet 137)
61-20-00
4-152
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 138)
61-20-00
Change 1
4-153
TO 1C-130H-2-61FI-00-1
FROM SHT 133
406
405
Remove jumper wire from plug
P1225 (4) but do not reconnect
plug.
Does FUNCTION display (1) indicate 1.0 or greater and does AC
VOLTS display (2) indicate 6?
NO
YES
Repair ground fault between
plug P1225 pin B and related
pin of receptacle P-B2576A (3).
(See figure 4-6.)
Prop
1
4
Rcpt Pin
20
31
407
Repair ground fault between
plug P1225 pin A and related
pin of receptacle P-B2576A (3).
(See figure 4-6.)
Prop
1
4
Figure 4-5. Synchrophaser System Malfunction (Sheet 139)
61-20-00
4-154
Change 1
Rcpt Pin
34
1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 140)
61-20-00
Change 1
4-155
TO 1C-130H-2-61FI-00-1
FROM SHT 89 OR 109
408
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
locking clamps.
c. Close PROP SYNCHRO PHASER and SYNCHRO
PHASER circuit breakers (1,2).
d. Place FUNCTION SELECT switch (6) to DCV.
e. Place TEST SELECT switch (5) to 2.
Does FUNCTION display (7) indicate 11 to 14 volts?
(Feedback pot V supply)
Prop
1
2
3
4
411
NO
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
Sync Rcpt Pins
P-B2576A-8, P-B2576A-30
P-A2576A-3, P-B2576A-30
P-A2576A-4, P-B2576A-30
P-B2576A-17, P-B2576A-30
YES
409
Place TEST SELECT switch (5) to 3.
Does FUNCTION display (7) indicate -11 to -14 volts?
(Feedback pot -V supply)
412
NO
Prop
1
2
3
4
Sync Rcpt Pins
P-B2576A-16, P-B2576A-30
P-A2576A-5, P-B2576A-30
P-A2576A-6, P-B2576A-30
P-B2576A-26, P-B2576A-30
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
YES
410
Place TEST SELECT switch (5) to 4.
Does FUNCTION display (7) indicate -11 to -15 volts?
(Anticipator pot -V supply)
413
NO
Prop
1
2
3
4
Sync Rcpt Pins
P-B2576A-27, P-B2576A-30
P-A2576A-7, P-B2576A-30
P-A2576A-13, P-B2576A-30
P-B2576A-36, P-B2576A-30
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
YES
TO SHT 143
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and airplanes AF92-3281 and up.
Figure 4-5. Synchrophaser System Malfunction (Sheet 141)
61-20-00
4-156
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 142)
61-20-00
Change 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
volts?
(Anticipator pot output in T/O pos)
Prop
1
2
3
4
417
NO
Sync Rcpt Pins
P-B2576A-13, P-B2576A-30
P-B2576A-32, P-B2576A-30
P-B2576A-35, P-B2576A-30
P-B2576A-33, P-B2576A-30
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
YES
415
Move throttle (5) to FLIGHT IDLE/FLT IDLE.
Does FUNCTION display (1) indicate -8.5 to
-12 volts?
(Anticipator pot output)
Prop
1
2
3
4
418
NO
Sync Rcpt Pins
P-B2576A-13, P-B2576A-30
P-B2576A-32, P-B2576A-30
P-B2576A-35, P-B2576A-30
P-B2576A-33, P-B2576A-30
Replace valve housing assembly in accordance with TO 1C130H-2-61JG-20-1, 61-20-02.
YES
416
a. Rapidly advance throttles (5) to TAKE
OFF.
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 indication in AC VOLTS display (2).
d. Rapidly retard throttles (5) to FLIGHT/FLT
IDLE and note indication in AC VOLTS display
(2).
Is the difference in the two indications at least
2 volts?
(Speed bias control winding)
Prop
1
2
3
4
419
NO
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
Sync Rcpt Pins
P-B2576A-5, P-B2576A-3
P-A2576A-34, P-A2576A-45
P-B2576A-14, P-B2576A-6
P-A2576A-24, P-B2576A-19
YES
TO SHT 145
Figure 4-5. Synchrophaser System Malfunction (Sheet 143)
61-20-00
4-158
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 144)
61-20-00
Change 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
to 130 volts?
(Speed bias ref winding)
Prop
1
2
3
4
422
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
NO
Sync Rcpt Pins
P-B2576A-39, P-B2576A-30
P-A2576A-41, P-B2576A-30
P-A2576A-42, P-B2576A-30
P-B2576A-38, P-B2576A-30
YES
421
a. Start engines in accordance with TO
1C-130H-2-71JG-00-1, 71-00-10.
b. Place FUNCTION SELECT switch
(4) to TACH RPM %.
Does FUNCTION display (1) indicate
99.8 to 100.2?
(Tach gen output)
Prop
1
2
3
4
NO
TO SHT 147
Sync Rcpt Pins
P-B2576A-15, P-B2576A-24
P-B2576A-44, P-B2576A-42
P-B2576A-4, P-B2576A-2
P-B2576A-45, P-B2576A-43
YES
TO SHT 149
Figure 4-5. Synchrophaser System Malfunction (Sheet 145)
61-20-00
4-160
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 146)
61-20-00
Change 1
4-161
TO 1C-130H-2-61FI-00-1
FROM SHT 1 OR 145
423
Is there a flashing 6 in FUCTION display (1)?
425
Place FUNCTION SELECT switch (2) to
PROP RPM %.
Does RPM difference between TACH
RPM % indication and PROP RPM %
indication in FUNCTION display (1) exceed 1 percent?
NO
YES
426
YES Fault is in tachometer system. Go to TO 1C-130H-270FI-00-1-1 and continue
troubleshooting.
NO
427
Adjust propeller mechanical
governing speed in accordance with TO 1C-130H-261JG-10-1, 61-10-03.
424
a. Shut down engines in accordance with TO
1C-130H-2-71JG-00-1, 71-00-10.
b. As applicable, remove propeller synchrophaser in accordance with TO 1C-130H-261JG-20-1, 61-20-13, and/or remove junction box
from synchrophaser rack.
Is there continuity between specified pins of receptacle P-B2576A (3) and related terminals of
terminal board TB1C (4)?
Prop
Rcpt Pin
TB Term
24
1
15
2
44
3
42
4
4
5
2
6
45
7
43
8
1
2
3
4
Test Points
10
9
12
11
10
9
12
11
10
9
12
11
10
9
12
11
428
YES
Fault is in tachometer system. Go to TO 1C-130H-270FI-00-1-1 and continue
troubleshooting.
NO
429
Repair applicable open circuit. (See figure 4-6 or 4-7.)
NOTE
See figure 4-6 or 4-7 for:
Figure 4-5. Synchrophaser System Malfunction (Sheet 147)
61-20-00
4-162
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 148)
61-20-00
Change 1
4-163
TO 1C-130H-2-61FI-00-1
FROM SHT 145
434
430
Does AC VOLTS display (3) indicate 17 to
30?
NO
Fault is in tachometer system.
Go to TO 1C-130H-2-70FI-00-11 and continue troubleshooting.
YES
431
Place FUNCTION SELECT switch (5) to
PROP RPM %.
Does FUNCTION display (1) indicate 99.8
to 100.2?
(Pulse gen output)
Prop
1
2
3
4
435
Adjust clearance between pulse
generator and permanent magnet in accordance with TO 1C130H-2-61JG-20-1, 61-20-10.
NO
Sync Rcpt Pins
P-B2576A-34, P-B2576A-20
P-A2576A-37, P-A2576A-28
P-A2576A-36, P-A2576A-29
P-B2576A-1, P-B2576A-31
YES
432
Does AC VOLTS display (3) indicate 1.2 to
5.0 and is - PULSE POLARITY indicator
light (2) on?
YES
NO
433
Is the - PULSE POLARITY indicator light (2) on?
436
YES Replace permanent magnet in
accordance with TO 1C-130H2-61JG-20-1, 61-20-10.
NO
TO SHT 151
437
Polarity of pulse generator (4) is
reversed. Check pulse generator for reversed wiring or improper magnet orientation and
repair as required.
Figure 4-5. Synchrophaser System Malfunction (Sheet 149)
61-20-00
4-164
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 150)
61-20-00
Change 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
-1.2 and -5.0 volts?
(Pulse gen output)
Prop
1
2
3
4
440
NO
Sync Rcpt Pins
P-B2576A-34, P-B2576A-20
P-A2576A-37, P-A2576A-28
P-A2576A-36, P-A2576A-29
P-B2576A-1, P-B2576A-31
Replace pulse generator in accordance with TO 1C-130H-261JG-20-1, 61-20-10.
YES
439
a. Place TEST SELECT switch (4) to 14.
b. Record voltage indication in AC VOLTS display (2) for propeller under test.
c. Place propeller governor control switch (6) to
MECH GOV/MECH.
d. Place applicable SPEED DERIVATIVE switch
(3) to OUT.
e. Place propeller governor control switch (6) to
NORMAL/NORM.
f. Record voltage indication in AC VOLTS display
(2).
g. Compare the indications of steps b and f.
Are the values the same?
(Tach gen output)
Prop
1
2
3
4
441
NO
Fault is in tachometer system.
Go to TO 1C-130H-2-70FI-00-11 and continue troubleshooting.
Sync Rcpt Pins
P-B2576A-15, P-B2576A-24
P-B2576A-44, P-B2576A-42
P-B2576A-4, P-B2576A-2
P-B2576A-45, P-B2576A-43
YES
442
Replace propeller synchrophaser in accordance with
TO 1C-130H-2-61JG-20-1, 6120-13.
NOTE
1
Airplanes prior to AF92-0547 and airplanes AF92-3021 through AF92-3024.
2
Airplanes AF92-0547 through AF92-2104 and AF92-3281 and up.
Figure 4-5. Synchrophaser System Malfunction (Sheet 151)
61-20-00
4-166
Change 1
TO 1C-130H-2-61FI-00-1
Figure 4-5. Synchrophaser System Malfunction (Sheet 152)
Change 1
61-20-00
4-167/(4-168 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-6. Synchrophaser System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 1 of 4)
Change 1
61-20-00
F4-6
4-169/(4-170 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-6. Synchrophaser System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 2)
Change 1
61-20-00
F4-6
4-171/(4-172 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-6. Synchrophaser System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 3)
Change 1
61-20-00
F4-6
4-173/(4-174 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-6. Synchrophaser System Electrical Schematic Diagram (Airplanes Prior to AF92-0547 and Airplanes AF92-3021 through AF92-3024)
(Sheet 4)
Change 1
61-20-00
F4-6
4-175/(4-176 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-7. Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)
(Sheet 1 of 5)
Change 1
61-20-00
F4-7
4-177/(4-178 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-7. Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)
(Sheet 2)
Change 1
61-20-00
F4-7
4-179/(4-180 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-7. Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)
(Sheet 3)
Change 1
61-20-00
F4-7
4-181/(4-182 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-7. Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)
(Sheet 4)
Change 1
61-20-00
F4-7
4-183/(4-184 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-7. Synchrophaser System Electrical Schematic Diagram (Airplanes AF92-0547 Through AF92-2104 and Airplanes AF92-3281 and Up)
(Sheet 5)
Change 1
61-20-00
F4-7
4-185/(4-186 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-8. Synchrophaser System Simplified Electrical Schematic
Diagram
Change 1
61-20-00
F4-8
4-187/(4-188 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-9. In-line Disconnects Location Diagram (Airplanes Prior to
AF92-1094 and AF92-3021 Through AF92-3024)
Change 1
61-20-00
F4-9
4-189/(4-190 blank)
TO 1C-130H-2-61FI-00-1
Figure 4-10. In-line Disconnects Location Diagram (Airplanes AF92-1094,
AF92-1095, AF92-2104, and AF93-1036 and Up)
Change 1
61-20-00
F4-10
4-191/(4-192 blank)