# Boeing Service Bulletin DC10-28-256: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2015-0248; AD 2016-04-16 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Service Bulletin DC10-28-256](https://openairdocs.org/service-documents/boeing/dc10-28-256.md)
- Title as filed: U.S. DOT/FAA - SB-DC10-28-256-00
- Pages: 99
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## Text

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### Page 1

Commercial 
Airplanes
DC10
Service Bulletin
Number: DC10-28-256
Original Issue: June 24, 2014
ATA System: 2800
SUBJECT: FUEL - Fuel Systems - Change Fuel Pump Control and Indication System Wiring
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2014 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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4.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 4
B. Concurrent Requirements ...................................... 1 4
C. Reason ................................................ 1 5
D. Description .............................................. 1 5
E. Compliance .............................................. 1 7
F. Approval ............................................... 1 7
G. Manpower .............................................. 1 7
H. Weight and Balance Changes .................................... 2 0
I. Electrical Load Data ......................................... 2 1
J. References .............................................. 2 5
1. Existing Data: ......................................... 2 5
2. Data Supplied with this Service Bulletin: ........................... 2 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 6
4. Process Data: ......................................... 2 6
K. Publications Affected ........................................ 2 6
L. Interchangeability and Intermixability of Parts ........................... 2 6
M. Software Accomplishment Summary ................................ 2 6
2. MATERIAL INFORMATION ........................................ 2 7
A. Material - Price and Availability ................................... 2 7
B. Industry Support Information .................................... 2 7
C. Parts Necessary for Each Airplane ................................. 2 7
1. Kits/Parts ............................................ 2 7
2. Parts and Materials Supplied by the Operator ........................ 3 9
3. Parts Modified and Reidentified ................................ 3 9
4. Parts Removed and Not Replaced .............................. 4 0
D. Parts Necessary to Change Spares ................................. 4 0
E. Special Tooling - Price and Availability ............................... 4 0
F. Special Tooling Necessary to do this Service Bulletin ....................... 4 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 1
A. GENERAL INFORMATION ..................................... 4 1
B. WORK INSTRUCTIONS ....................................... 4 2
APPENDIX A: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE [Group 1, 4]
.................................................. 4 7
APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE [Group 2-3,
5-6] ............................................... 5 3
APPENDIX C: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE [Group 9]
.................................................. 6 3
APPENDIX D: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURES [Group 8]
.................................................. 7 4
APPENDIX E: INPUT SURVEY ........................................ 9 9
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### Page 5

Commercial 
Airplanes
DC10
Service Bulletin
SummaryNumber: DC10-28-256Original Issue: June 24, 2014
ATA System: 2800
SUBJECT: FUEL - Fuel Systems - Change Fuel Pump Control and Indication System Wiring
CONCURRENT REQUIREMENTS
Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND
Frictional heating or sparking resulting from fuel pump failure, wear of fuel pump rotating components, or ingestion
of debris by the fuel pump, may result in development of a fuel tank ignition source. Frictional heating or sparking
in fuel pump inlets or priming system outlets exposed (i.e. not covered by fuel) to the tank ullage in combination
with the ullage being flammable, may result in a fuel tank ignition event. Center wing auxiliary, fuselage auxiliary,
and wing tip compartment (KC-10 only) fuel tanks may be subject to this condition since they are normally
pumped dry over the course of a mission. A fuel tank ignition event could develop with a fuel pump running in
an empty tank if the normal shutoff command is delayed or as a result of control system failures that keep the
fuel pump in a latent uncommanded running condition. To ensure a timely fuel pump shutoff command revise
flight crew shutoff procedures for center wing auxiliary, fuselage auxiliary, and wing tip compartment (KC-10
only) fuel tanks. To address the latent fuel pump uncommanded running condition change center wing auxiliary,
fuselage auxiliary, and wing tip compartment (KC-10 only) fuel pump control and indication system wiring to
detect and indicate fuel pump uncommanded running conditions. If not corrected, a fuel tank pump running in
an empty fuel tank may result in a fuel tank ignition event.
This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation
Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.
Boeing Fleet Team Digest (FTD) DC-10, MD-10 FTD 28-13001 and DC-10, MD-10 FTD 28-13003 are related
to this service bulletin.
ACTION
This service bulletin changes fuel pump control and indication system wiring.
EFFECTIVITY
DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F(KC-10A), DC-10-30F(KDC-10), DC-10-40,
DC-10-40F and MD-10-30F Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-08-23 is related to this service bulletin.
Boeing recommends that the change given in this service bulletin be done within 60 months after the effective
date of AD 2013-08-23.
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INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Elapsed HoursTotal Task HoursGroup(s)
18.436.81
31.462.82-3, 9
25.651.24
10.120.25
31.663.26
41.583.07
48.697.28
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
Operators are encouraged to complete the survey provided in APPENDIX E of this service bulletin to help Boeing
predict the quantity and timing of the Boeing Supplied Kits/Parts.
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BOEING SERVICE BULLETIN DC10-28-256
CENTER ACCESSORY
COMPARTMENT
FORWARD CARGO
COMPARTMENT
RIGHT SIDE
AIR CONDITIONING
COMPARTMENT
RIGHT SIDE
ELECTRICAL
POWER
CENTER
FORWARD CARGO
COMPARTMENT
LEFT SIDE
AIR CONDITIONING
LOWER NOSE  AND AVIONICS  LEFT SIDE  COMPARTMENT
COMPARTMENT
CHANGE FUEL PUMP CONTROL  1845432
AND INDICATION SYSTEM WIRING
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Commercial 
Airplanes
DC10
Service Bulletin
Number: DC10-28-256
Original Issue: June 24, 2014
ATA System: 2800
SUBJECT: FUEL - Fuel Systems - Change Fuel Pump Control and Indication System Wiring
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
DC-10-10 and DC-10-15 Airplanes that change fuel pump control
and indication system wiring to detect and indicate uncommanded
fuel pump running conditions in accordance with SR10280072-7001,
-7002 and SR10280073-7001 drawing configurations.
-1
DC-10-30, DC-10-30F and DC-10-30F (KDC-10) Airplanes that
change fuel pump control and indication system wiring to detect and
indicate uncommanded fuel pump running conditions in accordance
with SR10280072-7003, -7004 and SR10280073-7003 drawing
configurations.
-2
DC-10-30, DC-10-30F, DC-10-40 and DC-10-40F Airplanes that
change fuel pump control and indication system wiring to detect and
indicate uncommanded fuel pump running conditions in accordance
with SR10280072-7005, -7006 and SR10280073-7005 drawing
configurations.
-3
DC-10-10F Airplanes that change fuel pump control and indication
system wiring to detect and indicate uncommanded fuel pump running
conditions in accordance with SR10280072-7007, -7008 and
SR10280073-7007 drawing configurations.
-4
DC-10-30F Airplanes that change fuel pump control and indication
system wiring to detect and indicate uncommanded fuel pump running
conditions in accordance with SR10280072-7009, -7010 and
SR10280073-7009 drawing configurations.
-5
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DESCRIPTIONCONFIGURATIONGROUP
DC-10-30 Airplanes that change fuel pump control and indication
system wiring to detect and display uncommanded fuel pump running
conditions in accordance with SR10280072-7011, -7012 and
SR10280073-7011 drawing configurations.
-6
DC-10-30F (KC-10A) Airplanes that change fuel pump control and
indication system wiring to detect and indicate uncommanded fuel
pump running conditions in accordance with SR10280072-7013,
-7014 and SR10280073-7013 drawing configurations.
-7
DC-10-30F and MD-10-30F Airplanes that change fuel pump control
and indication system wiring to detect and indicate uncommanded
fuel pump running conditions in accordance with SR10280069-7001,
-7002 and SR10280070-7001 drawing configurations.
-8
DC-10-30 Airplanes with AFT AUX tank that change fuel pump control
and indication system wiring to detect and indicate uncommanded
fuel pump running conditions in accordance with SR10280072-7005,
-7006 and SR10280073-7005 drawing configurations.
-9
Airplane Models:
DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F (KC-10A), DC-10-30F
(KDC-10), DC-10-40, DC-10-40F, MD-10-30F
GroupFuselage Num-
ber
12
360
165
371
172
483
390
896
399
3100
8103
2106
8110
3114 - 115
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GroupFuselage Num-
ber
3117
3122 - 123
2127
3129
3131 - 135
3137
3146 - 147
3150
3152
3156 - 158
3160
2165
3166
3170 - 171
3174
3178 - 179
3183 - 184
3187 - 189
3190
3192
3195 - 196
3199
3201
3204
3206
3211 - 216
8219
3220 - 221
3223 - 227
3229
3230
3232
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GroupFuselage Num-
ber
3234
2235
3236
3239
3240
3242
3244 - 246
2248
1251 - 252
2253
3254
2255
3256
8257
3261 - 263
2264
3265 - 266
2267
3268
3274 - 275
8277
3281
8282
1285
3286
3289
3290 - 291
9292
3299
3300 - 301
5302 - 303
3304 - 306
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GroupFuselage Num-
ber
3308
3310
7311
5312
3313
2314
6315
3316
8317
1318
3324
6325
8326
3327
3329
8330
3332
7333
3334 - 338
3340
9341
3342 - 343
9345
1346
3349
3355 - 356
7359
7360 - 361
7363
3366 - 367
1372
7373
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GroupFuselage Num-
ber
7375 - 378
7380
3381
7383 - 389
7390 - 399
7400 - 408
8409
7410 - 411
8412
7413 - 415
8416
7417 - 418
8419
7420 - 421
8422
7423 - 429
7430 - 432
8433
9434 - 438
7439
8440
7441
8442 - 444
3445 - 446
2. Spares Affected
None.
B. Concurrent Requirements
The service bulletin listed below must be done before or at the same time as this service bulletin:
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DescriptionService BulletinCompany
Replace Fuel Pump Control Relays with Fault Current
Detectors and Change Fuel Tank Boost/Transfer Pump
Wire Termination
DC10-28A253
Original Issue
The Boeing Company
C. Reason
Frictional heating or sparking resulting from fuel pump failure, wear of fuel pump rotating components,
or ingestion of debris by the fuel pump, may result in development of a fuel tank ignition source. Frictional
heating or sparking in fuel pump inlets or priming system outlets exposed (i.e. not covered by fuel) to
the tank ullage in combination with the ullage being flammable, may result in a fuel tank ignition event.
Center wing auxiliary, fuselage auxiliary, and wing tip compartment (KC-10 only) fuel tanks may be
subject to this condition since they are normally pumped dry over the course of a mission. A fuel tank
ignition event could develop with a fuel pump running in an empty tank if the normal shutoff command
is delayed or as a result of control system failures that keep the fuel pump in a latent uncommanded
running condition. To ensure a timely fuel pump shutoff command revise flight crew shutoff procedures
for center wing auxiliary, fuselage auxiliary, and wing tip compartment (KC-10 only) fuel tanks. To
address the latent fuel pump uncommanded running condition change center wing auxiliary, fuselage
auxiliary, and wing tip compartment (KC-10 only) fuel pump control and indication system wiring to
detect and indicate fuel pump uncommanded running conditions. If not corrected, a fuel tank pump
running in an empty fuel tank may result in a fuel tank ignition event.
This service bulletin is the result of the safety assessments conducted by Boeing under a Special
Federal Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.
Boeing Fleet Team Digest (FTD) DC-10, MD-10 FTD 28-13001 and DC-10, MD-10 FTD 28-13003 are
related to this service bulletin.
D. Description
This service bulletin changes fuel pump control and indication system wiring.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 121, 122, 123, 125, 126, 127,
131, 132
DC-10-10, DC-10-15
Group 2:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 121, 122, 123, 125, 126, 127,
131, 132
DC-10-30, DC-10-30F, DC-10-
30F (KDC-10)
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Group 3:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 121, 122, 123, 125, 126, 127,
131, 132
DC-10-30, DC-10-30F, DC-10-
40, DC-10-40F
Group 4:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 121, 122, 123, 125, 126, 127,
131, 132
DC-10-10F
Group 5:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 121, 122, 123, 125, 126, 127,
131, 132
DC-10-30F
Group 6, 9:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 121, 122, 123, 125, 126, 127,
131, 132
DC-10-30
Group 7:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 121, 122, 123, 125, 126, 127,
131, 132
DC-10-30F (KC-10A)
Group 8:
Affected Maintenance Zones
ZoneModel
112, 113, 114, 121, 122, 123, 125, 126, 127,
131, 132
DC-10-30F, MD-10-30F
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E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-08-23 is related to this service
bulletin.
Boeing recommends that the change given in this service bulletin be done within 60 months after the
effective date of AD 2013-08-23.
F. Approval
1. DC-10 Airplanes:
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes
specified in this service bulletin comply with the applicable regulations and are FAA approved, as
well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all
EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its
approval were based on the airplane in its original Boeing delivery configuration or as modified by
other approved Boeing changes.
In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the action
(i.e. inspection or modification) defined in this service bulletin as a Alternative Method of Compliance
(AMOC) to the requirements of paragraph (g)(3) and (g)(4) of AD 2013-08-23. All provisions of AD
2013-08-23 that are not specifically referenced in the above statement remain fully applicable and
must be complied with.
If an airplane has a non-Boeing modification or repair that affects a component or system also
affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory
agency approval before incorporating this service bulletin.
2. MD-10 Airplanes:
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes
specified in this service bulletin comply with the applicable regulations and are FAA approved.
This service bulletin and its approval were based on the airplane in its original Boeing delivery
configuration or as modified by other approved Boeing changes.
In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the action
(i.e. inspection or modification) defined in this service bulletin as a Alternative Method of Compliance
(AMOC) to the requirements of paragraph (g)(2) and (g)(4) of AD 2013-08-23. All provisions of AD
2013-08-23 that are not specifically referenced in the above statement remain fully applicable and
must be complied with.
If an airplane has a non-Boeing modification or repair that affects a component or system also
affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory
agency approval before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
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 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
3.06.02Open Access
0.30.62Install Hardware
11.623.22Route and Terminate
Wiring
3.06.02Close Access
0.51.02Test
18.436.8TOTAL FOR EACH AIRPLANE
Group 2-3, 9:
Elapsed HoursTask HoursNumber of PersonsTask
3.06.02Open Access
0.81.62Install Hardware
24.148.22Route and Terminate
Wiring
3.06.02Close Access
0.51.02Test
31.462.8TOTAL FOR EACH AIRPLANE
Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
3.06.02Open Access
19.138.22Route and Terminate
Wiring
3.06.02Close Access
0.51.02Test
25.651.2TOTAL FOR EACH AIRPLANE
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Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
3.06.02Open Access
0.81.62Install Hardware
2.85.62Route and Terminate
Wiring
3.06.02Close Access
0.51.02Test
10.120.2TOTAL FOR EACH AIRPLANE
Group 6:
Elapsed HoursTask HoursNumber of PersonsTask
3.06.02Open Access
0.81.62Install Hardware
24.348.62Route and Terminate
Wiring
3.06.02Close Access
0.51.02Test
31.663.2TOTAL FOR EACH AIRPLANE
Group 7:
Elapsed HoursTask HoursNumber of PersonsTask
3.06.02Open Access
0.30.62Install Hardware
34.769.42Route and Terminate
Wiring
3.06.02Close Access
0.51.02Test
41.583.0TOTAL FOR EACH AIRPLANE
Group 8:
Elapsed HoursTask HoursNumber of PersonsTask
3.06.02Open Access
0.51.02Install Hardware
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Group 8:
Elapsed HoursTask HoursNumber of PersonsTask
41.683.22Route and Terminate
Wiring
3.06.02Close Access
0.51.02Test
48.697.2TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Group 1:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
+1,216.1+1.5810.7DC-10-10, DC-10-15
Group 2:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
+3,841.0+4.6835.0DC-10-30, DC-10-30F,
DC-10-30F (KDC-10)
Group 3:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
+3,831.8+4.6833.0DC-10-30, DC-10-30F,
DC-10-40, DC-10-40F
Group 4:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
+1,841.6+2.3800.7DC-10-10F
Group 5:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
+3,833.2+4.6833.3DC-10-30F
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Group 6:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
+3,853.9+4.6837.8DC-10-30
Group 7:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
+3,646.4+4.3848.0DC-10-30F (KC-10A)
Group 8:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
+4,366.1+7.3598.1DC-10-30F, MD-10-30F
Group 9:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
+3,831.8+4.6833.0DC-10-30
I. Electrical Load Data
1. Direct Current (DC) Load Changes
a. Add DC loads by amounts shown below:
Group 8:
UNITS
%OPR
1
100
E/NE
E
VDC
28
VDC
UNIT
LOAD
(A)
0.11
NOTES
(B1-475)
SUPPLIER
DACO
EQUIPMENT NAME
PART NUMBER
Lwr Aux L Fuel Pump
Manual Slave Relay
5D0122-1
ITEM
500X
R2-
8980A
CHAP
280
BUS
DB
AVERAGE AMPS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
00000TAKEOFF & CLIMB
Export Controlled ECCN: 9E991 - BOEING
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### Page 22

Group 8:
UNITS
%OPR
1
100
E/NE
E
VDC
28
VDC
UNIT
LOAD
(A)
0.11
NOTES
(B1-475)
SUPPLIER
DACO
EQUIPMENT NAME
PART NUMBER
Lwr Aux L Fuel Pump
Manual Slave Relay
5D0122-1
ITEM
500X
R2-
8980A
CHAP
280
BUS
DB
AVERAGE AMPS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
0.00330.00110.1131CRUISE COLD
0.00330.00110.1131CRUISE HOT
00000DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
Group 8:
UNITS
%OPR
1
100
E/NE
E
VDC
28
VDC
UNIT
LOAD
(A)
0.11
NOTES
(B1-475)
SUPPLIER
DACO
EQUIPMENT NAME
PART NUMBER
Lwr Aux R Fuel Pump
Manual Slave Relay
5D0122-1
ITEM
500X
R2-
8981A
CHAP
280
BUS
DB
AVERAGE AMPS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
00000TAKEOFF & CLIMB
0.00330.00110.1131CRUISE COLD
0.00330.00110.1131CRUISE HOT
00000DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
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### Page 23

Group 2-3, 5-6, 9:
UNITS
%OPR
1
100
E/NE
E
VDC
28
VDC
UNIT
LOAD
(A)
0.25
NOTES
(B1-475)
SUPPLIER
DACO
EQUIPMENT NAME
PART NUMBER
R Lower Aux Pump Con-
trol Relay
5D0397-1
ITEM
50X
R2-703
CHAP
280
BUS
DB
AVERAGE AMPS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
00000TAKEOFF & CLIMB
0.00750.00250.2531CRUISE COLD
0.00750.00250.2531CRUISE HOT
00000DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
Group 2-3, 5-6, 9:
UNITS
%OPR
1
100
E/NE
E
VDC
28
VDC
UNIT
LOAD
(A)
0.25
NOTES
(B1-475)
SUPPLIER
DACO
EQUIPMENT NAME
PART NUMBER
L Lower Aux Pump Con-
trol Relay
5D0397-1
ITEM
50X
R2-704
CHAP
280
BUS
DB
AVERAGE AMPS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
00000TAKEOFF & CLIMB
0.00750.00250.2531CRUISE COLD
0.00750.00250.2531CRUISE HOT
00000DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
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### Page 24

2. Alternating Current (AC) Load Changes
a. Add AC loads by amounts shown below:
Group 8:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-1
1
UNIT
LOAD
(W)
5
NOTES
(B1-
1206)
SUPPLIER
DACO
EQUIPMENT NAME
PART NUMBER
R Upper
Aux Pump Cont. Relay
5D0123-1
ITEM
500X
R2-
5891
CHAP
280
BUS
11
AVERAGE WATTS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
00000TAKEOFF & CLIMB
0.150.2534CRUISE COLD
0.150.2534CRUISE HOT
00000DESCENT & LAND
00000EMERGENCY
00000GROUND SERVICE
Group 8:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-2
1
UNIT
LOAD
(W)
5
NOTES
(B1-
1207)
SUPPLIER
DACO
EQUIPMENT NAME
PART NUMBER
L Upper
Aux Pump Cont. Relay
5D0123-1
ITEM
500X
R2-
5892
CHAP
280
BUS
21
AVERAGE WATTS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000LOADING
00000START
00000TAXI
00000TAKEOFF & CLIMB
0.150.2534CRUISE COLD
0.150.2534CRUISE HOT
00000DESCENT & LAND
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### Page 25

Group 8:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-2
1
UNIT
LOAD
(W)
5
NOTES
(B1-
1207)
SUPPLIER
DACO
EQUIPMENT NAME
PART NUMBER
L Upper
Aux Pump Cont. Relay
5D0123-1
ITEM
500X
R2-
5892
CHAP
280
BUS
21
AVERAGE WATTS% TIME OPR
15/30 M2/5 M5 S15/30 M2/5 MCONDITION
00000EMERGENCY
00000GROUND SERVICE
J. References
1. Existing Data:
a. Boeing Service Bulletin DC10-28A253.
b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2013-08-23.
c. DC-10, MD-10 Aircraft Maintenance Manual (AMM) 06-31-00, 06-32-03 and 52-31-00.
d. DC-10 Aircraft Maintenance Manual (AMM) 24-40-00 and 28-22-00.
e. MD-10 Aircraft Maintenance Manual (AMM) 06-36-00, 12-11-04, 24-40-00 and 32-00-00.
f. DC-10, MD-10 Fleet Team Digest (FTD) 28-13001 and DC-10, MD-10 FTD 28-13003.
g. DC-10, MD-10 Structural Repair Manual (SRM) 51.
h. Standard Overhaul Practices Manual (SOPM) 20-50-01.
i. Standard Wiring Practices Manual (SWPM) 20-00-09, 20-00-13, 20-00-16, 20-10-01, 20-20-03,
20-31-00 and 20-50-01.
2. Data Supplied with this Service Bulletin:
No data is supplied with this service bulletin. To obtain the data necessary to support this service
bulletin submit a data request to:
Data and Services Management
Mail Code: 110-SE20 (bldg 80)
2201 Seal Beach Blvd.
Seal Beach, California 90740 USA
Phone: (562) 797-1717
Fax: (562) 797-3783
E-mail: lbd.dataservicesmanagement@boeing.com
a. Drawings:
Export Controlled ECCN: 9E991 - BOEING
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### Page 26

ADCNDCN/REVSheetTitleDrawing No
C-AEOELEC INSTL - FUEL PUMP UNCOMMAND-
ED SIGNAL
SR10280069
D-AEO
-BDWG
-ADWGWIRE INSTL - FUEL PUMP UNCOMMAND-
ED SIGNAL
SR10280070
D-AEOELEC INSTL - FUEL PUMP UNCOMMAND-
ED SIGNAL
SR10280072
-CDWG
-BDWGWIRE INSTL - FUEL PUMP UNCOMMAND-
ED SIGNAL
SR10280073
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
4. Process Data:
Douglas Process Specifications referred to on the drawings are not given in this service bulletin
since these procedures are frequently used as standard shop practices.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
28-22Aircraft Maintenance Manual
Section 1 and 3FAA Approved Flight Manual
28-02Fault Isolation Manual
Volumes I, II & IIIFlight Crew Operations Manual
MDC-02K1003 (ALI 20-4)Special Compliance Item Report
28-21, 28-22, 28-44Wiring Diagram Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated this service bulletin for effects on Fatigue Critical Structure (FCS) and for
changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This
service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
Export Controlled ECCN: 9E991 - BOEING
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### Page 27

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane . Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
Unit Price as of the original is-
sue date of this Service Bulletin
(US Dollars)
ROLT as of the original issue
date of this Service Bulletin
(Calendar Days)
NameKit Number
$1,213.00120Service KitSB10280256-3
$3,133.00120Service KitSB10280256-5
$3,621.00120Service KitSB10280256-7
$997.00120Service KitSB10280256-9
$3,642.00120Service KitSB10280256-11
$3,705.00120Service KitSB10280256-13
$5,164.00120Service KitSB10280256-15
$3,042.00120Service KitSB10280256-17
Operators are encouraged to complete the survey provided in APPENDIX E of this service bulletin to
help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
Export Controlled ECCN: 9E991 - BOEING
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### Page 28

Group 1:
Kit SB10280256-3
NotesNameQTYPart Number
(a)SCREW43D0005-08-8
(a)TERM BLOCK45D0010-15
(a)END CLAMP45D0101-2
(a)TRACK, TERMINAL29D0090-2U
PIN, T/C 11262DC38-20P
NUT4MS21042L08
WASHER4NAS1252-8L
(b)WIRE KIT1SR10280072-102
(b)WIRE KIT1SR10280072-108
(b)WIRE KIT1SR10280072-112
(b)WIRE KIT1SR10280072-117
(b)WIRE KIT1SR10280072-119
(b)WIRE KIT1SR10280072-125
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to wire kit table below for wire kit contents.
Group 1:
Wire Kit Table
-125-119-117-112-108-102SR10280072
NotesNameQTYNew Part Number
(a)TERMINAL LUG 761225D0086-5
(b)WIRE CODE 80170
FT.
8 FT.10
FT.
74
FT.
82
FT.
40
FT.
D2426-1C-20NM
(b)WIRE CODE 80110
FT.
D2426-1C-24NM
PIN, T/C 11264DC38-20P
(a)PIN T/C 601/70112212S00023-20P
(a)SKT T/C 602/702712S00023-20S
PIN T/C 6132YHMM20-1F50
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Or approved alternate. Refer to SWPM 20-00-13.
Export Controlled ECCN: 9E991 - BOEING
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### Page 29

Group 2:
Kit SB10280256-5
NotesNameQTYPart Number
(a)SCREW23D0005-08-11
(a)SCREW43D0005-08-12
(a)SCREW43D0005-08-8
(a)TERM BLOCK45D0010-15
(a)END CLAMP45D0101-2
(a)RELAY25D0397-1
(a)TRACK, TERMINAL29D0090-2U
PIN, T/C 11264DC38-20P
RIVET8MS20470AD3-3D
NUT4MS21042L08
LOCKWASHER6MS35338-42
WASHER10NAS1252-8L
RIVNUT2NAS1329S08K75
NUTPLATE4NAS1474A08
(b)WIRE KIT1SR10280072-103
(b)WIRE KIT1SR10280072-109
(b)WIRE KIT1SR10280072-113
(b)WIRE KIT1SR10280072-117
(b)WIRE KIT1SR10280072-120
(b)WIRE KIT1SR10280072-123
(b)WIRE KIT1SR10280072-126
TERM BLOCK3YHLZ44
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to wire kit table below for wire kit contents.
Group 2:
Wire Kit Table
-126-123-120-117-113-109-103SR10280072
NotesNameQTYNumber
(a)DIODE25D0013-2A
(a)TERMINAL LUG 7614625D0086-5
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### Page 30

Group 2:
Wire Kit Table
-126-123-120-117-113-109-103SR10280072
NotesNameQTYNumber
(a)TERMINAL LUG 762115D0086-6
(b)WIRE CODE 8015 FT.D2426-1C-16NM
(b)WIRE CODE 801130
FT.
31
FT.
34
FT.
10
FT.
147
FT.
164
FT.
80
FT.
D2426-1C-20NM
(b)WIRE CODE 80115
FT.
5 FT.D2426-1C-24NM
PIN, T/C 1126431DC38-20P
PIN T/C 10031LRM16W-2DE5
(a)PIN T/C 601/701224224S00023-20P
(a)SKT T/C 602/70210514S00023-20S
PIN T/C 61214YHMM16-3F50
PIN T/C 613114YHMM20-1F50
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Or approved alternate. Refer to SWPM 20-00-13.
Group 3, 9:
Kit SB10280256-7
NotesNameQTYPart Number
(a)SCREW23D0005-08-11
(a)SCREW43D0005-08-12
(a)SCREW43D0005-08-8
(a)TERM BLOCK45D0010-15
(a)END CLAMP45D0101-2
(a)RELAY25D0397-1
(a)TRACK, TERMINAL29D0090-2U
PIN, T/C 11264DC38-20P
RIVET8MS20470AD3-3D
NUT4MS21042L08
LOCKWASHER6MS35338-42
WASHER10NAS1252-8L
RIVNUT2NAS1329S08K75
Export Controlled ECCN: 9E991 - BOEING
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### Page 31

Group 3, 9:
Kit SB10280256-7
NotesNameQTYPart Number
NUTPLATE4NAS1474A08
(a)WIRE KIT1SR10280072-103
(b)WIRE KIT1SR10280072-110
(b)WIRE KIT1SR10280072-114
(b)WIRE KIT1SR10280072-117
(b)WIRE KIT1SR10280072-120
(b)WIRE KIT1SR10280072-123
(b)WIRE KIT1SR10280072-127
TERM BLOCK3YHLZ44
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to wire kit table below for wire kit contents.
Group 3, 9:
Wire Kit Table
-127-123-120-117-114-110-103SR10280072
NotesNameQTYNew Part Number
(a)DIODE25D0013-2A
(a)TERMINAL LUG 7614625D0086-5
(a)TERMINAL LUG 762115D0086-6
(b)WIRE CODE 8015 FT.D2426-1C-16NM
(b)WIRE CODE 801130
FT.
31
FT.
34
FT.
10
FT.
147
FT.
164
FT.
80
FT.
D2426-1C-20NM
(b)WIRE CODE 80110
FT.
10
FT.
D2426-1C-24NM
PIN, T/C 112662DC38-20P
PIN T/C 10031LRM16W-2DE5
(a)PIN T/C 601/701224224S00023-20P
(a)SKT T/C 602/7021244S00023-20S
PIN T/C 61214YHMM16-3F50
PIN T/C 613114YHMM20-1F50
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Or approved alternate. Refer to SWPM 20-00-13.
Export Controlled ECCN: 9E991 - BOEING
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### Page 32

Group 4:
Kit SB10280256-9
NotesNameQTYPart Number
(a)TERM BLOCK35D0010-15
PIN, T/C 11264DC38-20P
(b)WIRE KIT1SR10280072-104
(b)WIRE KIT1SR10280072-111
(b)WIRE KIT1SR10280072-115
(b)WIRE KIT1SR10280072-117
(b)WIRE KIT1SR10280072-119
(b)WIRE KIT1SR10280072-128
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to wire kit table below for wire kit contents.
Group 4:
Wire Kit Table
-128-119-117-115-111-104SR10280072
NotesNameQTYNew Part Number
(a)TERMINAL LUG 761225D0086-5
(b)WIRE CODE 80170
FT.
8 FT10
FT.
147
FT.
164
FT.
84
FT.
D2426-1C-20NM
(b)WIRE CODE 80110
FT.
D2426-1C-24NM
PIN, T/C 11268DC38-20P
SOCKET T/C 7062LRC16M-32DJ5
(a)PIN T/C 601/70122224S00023-20P
(a)SKT T/C 602/702624S00023-20S
PIN T/C 6112YHMM22-2DB8
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Or approved alternate. Refer to SWPM 20-00-13.
Group 5:
Kit SB10280256-11
NotesNameQTYPart Number
(a)SCREW23D0005-08-11
Export Controlled ECCN: 9E991 - BOEING
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### Page 33

Group 5:
Kit SB10280256-11
NotesNameQTYPart Number
(a)SCREW43D0005-08-12
(a)SCREW43D0005-08-8
(a)TERM BLOCK45D0010-15
(a)END CLAMP45D0101-2
(a)RELAY25D0397-1
(a)TRACK, TERMINAL29D0090-2U
PIN, T/C 11264DC38-20P
RIVET8MS20470AD3-3D
NUT4MS21042L08
LOCKWASHER6MS35338-42
WASHER10NAS1252-8L
RIVNUT2NAS1329S08K75
NUTPLATE4NAS1474A08
(b)WIRE KIT1SR10280072-105
(b)WIRE KIT1SR10280072-110
(b)WIRE KIT1SR10280072-114
(b)WIRE KIT1SR10280072-117
(b)WIRE KIT1SR10280072-120
(b)WIRE KIT1SR10280072-123
(b)WIRE KIT1SR10280072-127
TERM BLOCK3YHLZ44
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to wire kit table below for wire kit contents.
Group 5:
Wire Kit Table
-127-123-120-117-114-110-105SR10280072
NotesNameQTYNew Part Number
(a)DIODE25D0013-2A
(a)TERMINAL LUG 7614625D0086-5
(a)TERMINAL LUG 762115D0086-6
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### Page 34

Group 5:
Wire Kit Table
-127-123-120-117-114-110-105SR10280072
NotesNameQTYNew Part Number
(b)WIRE CODE 8015 FT.D2426-1C-16NM
(b)WIRE CODE 801130
FT.
31
FT.
34
FT.
10
FT.
147
FT.
164
FT.
80
FT.
D2426-1C-20NM
(b)WIRE CODE 80110
FT.
10
FT.
D2426-1C-24NM
PIN, T/C 112662DC38-20P
PIN T/C 10031LRM16W-2DE5
(a)PIN T/C 601/701224224S00023-20P
(a)SKT T/C 602/7021244S00023-20S
PIN T/C 61214YHMM16-3F50
PIN T/C 613114YHMM20-1F50
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Or approved alternate. Refer to SWPM 20-00-13.
Group 6:
Kit SB10280256-13
NotesNameQTYNew Part Number
(a)SCREW23D0005-08-11
(a)SCREW43D0005-08-12
(a)SCREW43D0005-08-8
(a)TERM BLOCK65D0010-15
(a)END CLAMP45D0101-2
(a)RELAY25D0397-1
(a)TRACK, TERMINAL29D0090-2U
PIN, T/C 112612DC38-20P
RIVET8MS20470AD3-3D
NUT4MS21042L08
LOCKWASHER6MS35338-42
WASHER10NAS1252-8L
RIVNUT2NAS1329S08K75
NUTPLATE4NAS1474A08
Export Controlled ECCN: 9E991 - BOEING
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Group 6:
Kit SB10280256-13
NotesNameQTYNew Part Number
(b)WIRE KIT1SR10280072-106
(b)WIRE KIT1SR10280072-110
(b)WIRE KIT1SR10280072-114
(b)WIRE KIT1SR10280072-117
(b)WIRE KIT1SR10280072-120
(b)WIRE KIT1SR10280072-123
(b)WIRE KIT1SR10280072-127
TERM BLOCK3YHLZ44
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to wire kit table(s) below for wire kit contents.
Group 6:
Wire Kit Table
-127-123-120-117-114-110-106SR10280072
NotesNameQTYNew Part Number
(a)DIODE25D0013-2A
(a)TERMINAL LUG 7614625D0086-5
(a)TERMINAL LUG 762115D0086-6
(b)WIRE CODE 8015 FT.D2426-1C-16NM
(b)WIRE CODE 801130
FT.
31
FT.
34
FT.
10
FT.
147
FT.
164
FT.
80
FT.
D2426-1C-20NM
(b)WIRE CODE 80110
FT.
10
FT.
D2426-1C-24NM
PIN, T/C 1126624DC38-20P
PIN T/C 10031LRM16W-2DE5
(a)PIN T/C 601/701224224S00023-20P
(a)SKT T/C 602/7021244S00023-20S
PIN T/C 61214YHMM16-3F50
PIN T/C 61311YHMM20-1F50
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Or approved alternate. Refer to SWPM 20-00-13.
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Group 7:
Kit SB10280256-15
NotesNameQTYNew Part Number
(a)SCREW43D0005-08-8
(a)TERM BLOCK65D0010-15
(a)END CLAMP45D0101-2
(a)TRACK, TERMINAL29D0090-2U
PIN, T/C 112611DC38-20P
NUT4MS21042L08
WASHER8NAS1252-8L
(b)WIRE KIT1SR10280072-101
(b)WIRE KIT1SR10280072-107
(b)WIRE KIT1SR10280072-110
(b)WIRE KIT1SR10280072-116
(b)WIRE KIT1SR10280072-118
(b)WIRE KIT1SR10280072-121
(b)WIRE KIT1SR10280072-124
(b)WIRE KIT1SR10280072-129
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to wire kit table below for wire kit contents.
Group 7:
Wire Kit Table
-129-124-121-118-116-110-107-101SR10280072
NotesNameQTYNew Part Number
(a)TERMINAL LUG 76124425D0086-5
(a)TERMINAL LUG 76215D0086-6
(a)PIN T/C 100525D0187-2222P
(b)WIRE CODE 801175
FT.
14
FT.
16
FT.
20
FT.
334
FT.
164
FT.
120
FT.
14
FT.
D2426-1C-20NM
(b)WIRE CODE 80110
FT.
D2426-1C-22NM
(b)WIRE CODE 80110
FT.
15
FT.
D2426-1C-24NM
PIN, T/C 1126736DC38-20P
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Group 7:
Wire Kit Table
-129-124-121-118-116-110-107-101SR10280072
NotesNameQTYNew Part Number
(a)PIN T/C 601/7014244442S00023-20P
(a)SKT T/C 602/7021586S00023-20S
PIN T/C 6132YHMM20-1F50
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Or approved alternate. Refer to SWPM 20-00-13.
Group 8:
Kit SB10280256-17
NotesNameQTYNew Part Number
(a)SCREW43D0005-04-9
(a)SCREW23D0005-08-11
(a)SCREW23D0005-3-11
(a)CLIPNUT43D0191-04
(a)TERM BLOCK25D0107-1
(a)RELAY25D0122-1
(a)RELAY25D0123-1
(a)TERMINAL15D0518-4
PIN, T/C 11314DC38-16P
PIN, T/C 11474M39029/1-101
LOCKWASHER2MS35338-42
LOCKWASHER2MS35338-43
WASHER2NAS1252-10L
WASHER4NAS1252-4L
WASHER2NAS1252-8L
RIVNUT2NAS1329S08K75
(b)WIRE KIT1SR10280069-101
(b)WIRE KIT1SR10280069-102
(b)WIRE KIT1SR10280069-103
(b)WIRE KIT1SR10280069-104
(b)WIRE KIT1SR10280069-105
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Group 8:
Kit SB10280256-17
NotesNameQTYNew Part Number
(b)WIRE KIT1SR10280069-106
(b)WIRE KIT1SR10280069-107
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to wire kit table below for wire kit contents.
Group 8:
Wire Kit Table
-107-106-105-104-103-102-101Kit SR10280069
NotesNameQTYNew Part Number
(a)DIODE25D0013-2A
(a)TERMINAL LUG 76425D0086-24
(a)TERMINAL LUG 76645D0086-26
(a)TERMINAL LUG 761225D0086-5
(a)TERMINAL LUG 762115D0086-6
(a)PIN T/C 100545D0187-2222P
SOCKET T/C 4872617220
PIN T/C 5795617240
SOCKET T/C 48611617320
SOCKET T/C 5785617340
RELAY SOCKET265009-020-513
RECEPTACLE2CL3-1007-162
(b)WIRE CODE 80144
FT.
2 FT.84
FT.
217
FT.
332
FT.
D2426-1C-16NM
(b)WIRE CODE 80138
FT.
7 FT.7 FT.84
FT.
109
FT.
109
FT.
21
FT.
D2426-1C-20NM
(b)WIRE CODE 80134
FT.
D2426-1C-24NM
PIN, T/C 11317DC38-16P
SOCKET T/C 70613LRC16M-32DJ5
PIN T/C 70522LRM16M-32DJ5
CONN SKT T/C 1004312LRC16W2
PIN T/C 100332LRM16W-2DE5
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Group 8:
Wire Kit Table
-107-106-105-104-103-102-101Kit SR10280069
NotesNameQTYNew Part Number
PIN T/C 114719M39029/1-101
CONTACT T/C 542/5468M39029/22-193
(a)PIN T/C 601/701211S00023-20P
(a)SKT T/C 602/702211S00023-20S
(a) Or approved equivalent. Refer to AEPL Drawing 7595071.
(b) Or approved alternate. Refer to SWPM 20-00-13.
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number /
Specification
(a)TIE TAPEAs RequiredDMS 2089
(18XTZ), (23XTZ)
or
Equivalent
(b)Coating, Chemical ConversionAs RequiredAlodine 1200S
(DPM 1453-5)
or
Equivalent
(a)Primer, Fluid ResistantAs RequiredDMS 1786
(Koropon 515-700
with Catalyst910-
704)
or
Equivalent
(a) Can be purchased from: Gudebrod, Incorporated, 274 Shoemaker Road, Pottstown, Penn-
sylvania, 19464, CAGE 82110
(b) Can be purchased from: Henkel Corporation, 32100 Stephenson Highway, Madison Heights,
Michigan, 48071, CAGE 1N6B3
3. Parts Modified and Reidentified
None.
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4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY
ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE
CAN OCCUR.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Equivalent parts are listed in the AEPL, Drawing 7595071.
3. Use the approved fastener and process material substitutions, in accordance with
DC-10, MD-10 SRM 51.
4. If the length of any fastener specified in this service bulletin does not meet the
installation standards in Structural Repair Manual (SRM) Chapter 51, then a fastener
of the same specification, or an approved substitute, with a length which meets the
installation standards in SRM Chapter 51 may be used. In addition, washers may
be installed for fastener grip length in accordance with SRM Chapter 51. Refer to
SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation
in this service bulletin.
5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is
the maximum thickness which may be used under fastener head or nut to counteract
accumulation of tolerances.
EXCEPTION: When the available fastener length increments are greater than
1/16-inch, a 3/16-inch thick stack of the same type washers may be used.
6. Unless shown differently, these dimensions and tolerances are used:
 Linear dimensions are in inches.
 Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch.
 Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch.
 Angular tolerance is plus or minus 2 degrees.
 Hole dimensions for standard solid rivets are in DC-10, MD-10 SRM 51.
 Torque limits to tighten nuts and bolts are in DC-10, MD-10 SRM 51.
7. Refer to these SWPM chapters for applicable operations, as accepted procedures:
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TitleChapter
GENERAL MAINTENANCE PRACTICES - ELECTRICALSWPM 20-00-09
ELECTRICAL WIRE CODESSWPM 20-00-13
ELECTRICAL WIRE END TERMINATION CODES AND TOOL
CODES
SWPM 20-00-16
WIRING INSTALLATION - MAINTENANCE PRACTICESSWPM 20-10-01
GENERAL INSTALLATIONS HARDWARE - MAINTENANCE
PRACTICES
SWPM 20-20-03
ELECTRICAL CONNECTORS - MAINTENANCE PRACTICESSWPM 20-31-00
ELECTRICAL BONDING - MAINTENANCE PRACTICESSWPM 20-50-01
8. Obey all of the warnings and cautions given in the specified manual sections.
9. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
10. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U' or 'Y' in place of the '-' (dash) in the part number. It is permitted
to install parts identified with a 'U' or 'Y' as an alternative to the '-' (dash) number
part. Boeing Drawing SE10000000, Sheets 5.0 and 6.0 contain more data.
11. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
12. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
13. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
14. Group 1-7, 9:
Review and understand all general notes of Service Rework Drawings SR10280072
sheets 3, 3.1, 3.2, 3.3 and SR10280073 sheet 1.
Group 8:
Review and understand all general notes of Service Rework Drawings SR10280069
sheets 3, 3.1, 3.2, 3.3, 3.4 and SR10280070 sheet 1.
B. WORK INSTRUCTIONS
1. Gain access:
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a. Open access doors in the table as follow:
ReferenceLocation/DescriptionAccess Door
DC-10, MD-10 AMM 06-31-00Avionics Equipment Compartment112AB
Left-side Air Conditioning Compartment113AL
113DL
Right-side Air Conditioning Compartment114AR
Center Accessory Compartment131AB
b. Open forward cargo compartment door. Refer to DC-10, MD-10 AMM 52-31-00 as an accepted
procedure.
c. Remove/Keep forward cargo compartment ceiling panels and attaching hardware, left and
right sides between stations Y=595.000 and Y=1099.000. Refer to DC-10, MD-10 AMM
06-32-03.
2. Install electrical equipment in accordance with the table(s) as follow:
Group 1, 7:
SheetsDrawing
12-13SR10280072
Group 2-3, 5-6, 9:
SheetsDrawing
12-15SR10280072
Group 4:
None.
Group 8:
SheetsDrawing
8, 12-15SR10280069
3. Route wiring in accordance with the table(s) as follow:
Group 1, 4:
Additional DataSheet(s)Drawing
1-9, 11SR10280073
Views G, AN, AU10SR10280073
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Group 2, 5-6:
Additional DataSheet(s)Drawing
1-9, 11SR10280073
Views AM, AN, AP, AR AU, AZ10SR10280073
Group 3, 9:
Additional DataSheet(s)Drawing
1-9, 11SR10280073
Views AM, AN, AP, AS, AV, AZ10SR10280073
Group 7:
Additional DataSheet(s)Drawing
1-9, 11SR10280073
Views G, AM, AN, AP, AT, AY10SR10280073
Group 8:
Additional DataSheet(s)Drawing
1-11SR10280070
4. Terminate wiring in accordance with the table(s) as follow:
Group 1:
SheetDrawing
6.10, 102.201, 108.201, 112.201, 117.201, 119.201, 125.201,
306.201, 310.201
SR10280072
Group 2:
SheetsDrawing
6.9, 6.11, 6.12, 103.201, 109.201, 113.201, 117.201, 120.201,
123.201, 126.201, 307.201, 311.201, 315.201, 316.201
SR10280072
Group 3, 9:
SheetsDrawing
6.9, 6.13, 6.14, 103.201, 110.201, 114.201, 117.201, 120.201,
123.201, 127.201, 308.201, 312.201, 315.201, 316.201
SR10280072
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Group 4:
SheetDrawing
6.15, 104.201, 111.201, 115.201, 117.201, 119.201, 128.201,
303.201, 317.201
SR10280072
Group 5:
SheetsDrawing
6.9, 6.16, 6.17, 105.201, 110.201, 114.201, 117.201, 120.201,
123.201, 127.201, 309.201, 313.201, 315.201-316.201
SR10280072
Group 6:
SheetsDrawing
6.9, 6.18, 6.19, 106.201, 110.201, 114.201, 117.201, 120.201,
123.201, 127.201, 301.201, 304.201, 309.201, 313.201, 315.201-
316.201
SR10280072
Group 7:
SheetsDrawing
6.20, 6.21, 6.22, 101.201, 107.201, 110.201, 116.201, 118.201,
121.201, 124.201, 129.201, 302.201, 305.201, 307.201, 314.201
SR10280072
Group 8:
SheetsDrawing
6.1 - 6.4, 101.201-107.201, 301.201, 303.201-307.201SR10280069
5. Test:
Group 1, 4:
Test Fuel Pumps Uncommanded On Detection Circuit in accordance with APPENDIX A.
Group 2-3, 5-6:
Test Fuel Pumps Uncommanded On Detection Circuit in accordance with APPENDIX B.
Group 7:
Test Fuel Pumps Uncommanded On Detection Circuit in accordance with DC-10 AMM 28-22-00.
Group 8:
Test Fuel Pumps Uncommanded On Detection Circuit in accordance with APPENDIX D.
Group 9:
Test Fuel Pumps Uncommanded On Detection Circuit in accordance with APPENDIX C.
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6. Close access:
a. Install/Kept forward cargo compartment ceiling panels and attaching hardware, left and right
sides between stations Y=595.000 and Y=1099.000. Refer to DC-10, MD-10 AMM 06-32-03.
b. Close forward cargo compartment door. Refer to DC-10, MD-10 AMM 52-31-00 as an accepted
procedure.
c. Close access doors in the table as follow:
ReferenceLocation/DescriptionAccess Door
DC-10, MD-10 AMM 06-31-00Avionics Equipment Compartment112AB
Left-side Air Conditioning Compartment113AL
113DL
Right-side Air Conditioning Compartment114AR
Center Accessory Compartment131AB
7. Put the airplane back to a serviceable condition.
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This Appendix applies only to: Group 1, 4.
WARNING: THIS TEST PROCEDURE DEALS WITH HIGH VOLTAGE AC POWER. USE OF EXTREME
CAUTION IS ADVISED OR INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN
OCCUR.
1. Test Equipment:
a. An electrical wire jumper, two feet long, with each end soldered to 0.062 +/- .001 DIA pin.
2. Test Procedure for DC-10-10, DC-10-10F, and DC-10-15 Airplanes with Aux Tank:
a. Test Setup:
(1) Energize aircraft electrical busses with external electrical power. Refer to DC-10 AMM 24-40-00
as an accepted procedure.
(2) On the Upper Main Circuit Breaker Panel open circuit breakers as follow:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP POWER AUX TANK RB1-125023B
FUEL PUMP CONTROL AUX TANK RB1-120623E
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP POWER AUX TANK LB1-124823C
FUEL PUMP CONTROL AUX TANK LB1-120723F
b. Right Aux Tank Pump M1-91 Uncommanded On Detection Circuit Test Procedure:
(1) On the Flight Engineer's Fuel Panel set the RIGHT FUEL PUMP AUX TANK switch (S1-838)
to OFF position.
(2) In the Avionics Compartment at the AFT RELAY PANEL Z112FZ remove the R AUX PUMP
SLAVE CONTROL RELAY (R2-5219) from its receptacle (R5-5219).
(3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5219
receptacle located in the AFT RELAY PANEL Z112FZ.
(4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
APPENDIX A:  FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 1 OF 6)
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UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK RB1-120623E
(5) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "TANK PUMP PRESS LO"
light is illuminated.
(6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK RB1-120623E
(7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "TANK PUMP PRESS LO"
light is OFF.
(8) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL DC BUS 1
NameNumberColumnRow
R AUX PUMP PRESS LOW LTB1-124625H
(9) Remove the jumper from pin A1 to pin A2 of the R5-5219 receptacle located in the AFT RELAY
PANEL Z112FZ.
(10) Connect the jumper wire (described in step 1.a.) from pin B1 to pin B2 of the R5-5219
receptacle located in the AFT RELAY PANEL Z112FZ.
(11) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL DC BUS 1
NameNumberColumnRow
R AUX PUMP PRESS LOW LTB1-124625H
(12) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Right "TANK PUMP PRESS
LO" light is illuminated.
(13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL DC BUS 1
NameNumberColumnRow
R AUX PUMP PRESS LOW LTB1-124625H
APPENDIX A:  FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 2 OF 6)
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(14) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "TANK PUMP PRESS LO"
light is OFF.
(15) Remove the jumper from pin B1 to pin B2 of the R5-5219 receptacle located in the AFT RELAY
PANEL Z112FZ.
(16) At the AFT RELAY PANEL Z112FZ install the R AUX PUMP SLAVE CONTROL RELAY
(R2-5219) to its receptacle (R5-5219).
(17) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL DC BUS 1
NameNumberColumnRow
R AUX PUMP PRESS LOW LTB1-124625H
(18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK RB1-120623E
(19) On the Flight Engineer's Fuel Panel set the RIGHT FUEL PUMP CONTROL AUX TANK switch
(S1-838) to ON position.
(20) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "TANK PUMP PRESS LO"
light is illuminated.
(21) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK RB1-120623E
(22) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "TANK PUMP PRESS LO"
light is OFF.
(23) On the Flight Engineer's Fuel Panel set the RIGHT FUEL PUMP AUX TANK switch (S1-838)
to OFF position.
c. Left Aux Tank Pump M1-92 Uncommanded On Detection Circuit Test Procedure:
(1) On the Flight Engineer's Fuel Panel set the LEFT FUEL PUMP AUX TANK switch (S1-839)
to OFF position.
APPENDIX A:  FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 3 OF 6)
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(2) At the AFT RELAY PANEL Z112FZ remove the L AUX PUMP SLAVE CONTROL RELAY
(R2-5220) from its receptacle (R5-5220).
(3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5220
receptacle located in the AFT RELAY PANEL Z112FZ.
(4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK LB1-120723F
(5) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO"
light is illuminated.
(6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK LB1-120723F
(7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO"
light is OFF.
(8) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL DC BUS 2
NameNumberColumnRow
L AUX PUMP PRESS LOW LTB1-124725J
(9) Remove the jumper from pin A1 to pin A2 of the R5-5220 receptacle located in the AFT RELAY
PANEL Z112FZ.
(10) Connect the jumper wire (described in step 1.a.) from pin B1 to pin B2 of the R5-5220
receptacle located in the AFT RELAY PANEL Z112FZ.
(11) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL DC BUS 2
NameNumberColumnRow
L AUX PUMP PRESS LOW LTB1-124725J
APPENDIX A:  FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 4 OF 6)
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### Page 51

(12) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO"
light is illuminated.
(13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL DC BUS 2
NameNumberColumnRow
L AUX PUMP PRESS LOW LTB1-124725J
(14) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO"
light is OFF.
(15) Remove the jumper from pin B1 to pin B2 of the R5-5220 receptacle located in the AFT RELAY
PANEL Z112FZ.
(16) At the AFT RELAY PANEL Z112FZ install the L AUX PUMP SLAVE CONTROL RELAY
(R2-5220) to its receptacle (R5-5220).
(17) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL DC BUS 2
NameNumberColumnRow
L AUX PUMP PRESS LOW LTB1-124725J
(18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK LB1-120723F
(19) On the Flight Engineer's Fuel Panel set the LEFT FUEL PUMP CONTROL AUX TANK switch
(S1-839) to ON position.
(20) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO"
light is illuminated.
(21) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK LB1-120723F
APPENDIX A:  FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 5 OF 6)
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### Page 52

(22) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "TANK PUMP PRESS LO"
light is OFF.
(23) On the Flight Engineer's Fuel Panel set the LEFT FUEL PUMPS AUX TANKS switch (S1-839)
to OFF position.
d. Test Closeout:
(1) On the Upper Main Circuit Breaker Panel close circuit breakers as follow:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP POWER AUX TANK RB1-125023B
FUEL PUMP CONTROL AUX TANK RB1-120623E
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP POWER AUX TANK LB1-124823C
FUEL PUMP CONTROL AUX TANK LB1-120723F
APPENDIX A:  FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 6 OF 6)
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### Page 53

This Appendix applies only to: Group 2-3, 5-6.
WARNING: THIS TEST PROCEDURE DEALS WITH HIGH VOLTAGE AC POWER. USE OF EXTREME
CAUTION IS ADVISED OR INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN
OCCUR.
1. Test Equipment:
a. An electrical wire jumper, two feet long, with each end soldered to 0.062 +/- .001 DIA pin.
2. Test Procedure for DC-10-30, DC-10-30F, DC-10-30F (KDC-10), DC-10-40, and DC-10-40F Airplanes:
a. Test Setup:
(1) Energize aircraft electrical busses with external electrical power. Refer to DC-10 AMM 24-40-00
as an accepted procedure.
(2) On the Upper Main Circuit Breaker Panel open circuit breakers as follow:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP POWER AUX TANK R UPRB1-125023B
FUEL PUMP CONTROL AUX TANK R UPR & LWRB1-120623E
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP POWER AUX TANK L UPRB1-124822C
FUEL PUMP POWER AUX TANK L LWRB1-124923C
FUEL PUMP CONTROL AUX TANK L UPR & LWRB1-120722F
FUEL PUMP CONTROL AUX TANK L LWRB1-120923F
UPPER MAIN, FUEL AC BUS 3
NameNumberColumnRow
FUEL PUMP POWER AUX TANK R LWRB1-125123D
FUEL PUMP CONTROL AUX TANK R LWRB1-120823G
b. Right Upper Aux Tank Pump M1-91 Uncommanded On Detection Circuit Test Procedure:
(1) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to
OFF position.
APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 1 OF 10)
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### Page 54

(2) In the Avionics Compartment at the AFT RELAY PANEL Z112FZ remove the UPPER R AUX
PUMP SLAVE CONTROL RELAY (R2-5219) from its receptacle (R5-5219).
(3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5219
receptacle located in the AFT RELAY PANEL Z112FZ.
(4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK R UPR & LWRB1-120623E
(5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Right "UPR TANK PUMP PRESS
LO" light is illuminated.
(6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK R UPR & LWRB1-120623E
(7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS
LO" light is OFF.
(8) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, DC BUS 1
NameNumberColumnRow
R AUX UPR & LWR PRESS LOW LTSB1-124625H
(9) Remove the jumper from pin A1 to pin A2 of the R5-5219 receptacle located in the AFT RELAY
PANEL Z112FZ.
(10) Connect the jumper wire (described in step 1.a.) from pin B1 to pin B2 of the R5-5219
receptacle located in the AFT RELAY PANEL Z112FZ.
(11) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, DC BUS 1
NameNumberColumnRow
R AUX UPR & LWR PRESS LOW LTSB1-124625H
APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 2 OF 10)
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### Page 55

(12) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Right "UPR TANK PUMP PRESS
LO" light is illuminated.
(13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, DC BUS 1
NameNumberColumnRow
R AUX UPR & LWR PRESS LOW LTSB1-124625H
(14) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS
LO" light is OFF.
(15) Remove the jumper from pin B1 to pin B2 of the R5-5219 receptacle located in the AFT RELAY
PANEL Z112FZ.
(16) At the AFT RELAY PANEL Z112FZ install the UPPER R AUX PUMP SLAVE CONTROL
RELAY (R2-5219) to its receptacle (R5-5219).
(17) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, DC BUS 1
NameNumberColumnRow
R AUX UPR & LWR PRESS LOW LTSB1-124625H
(18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK R UPR & LWRB1-120623E
(19) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to
UPR position.
(20) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS
LO" light is illuminated.
(21) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK R UPR & LWRB1-120623E
APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 3 OF 10)
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### Page 56

(22) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "UPR TANK PUMP PRESS
LO" light is OFF.
(23) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to
OFF position.
c. Left Upper Aux Tank Pump M1-92 Uncommanded On Detection Circuit Test Procedure:
(1) On the Flight Engineer's Fuel Panel set the L FUEL PUMPS AUX TANKS switch (S1-720) to
OFF position.
(2) At the AFT RELAY PANEL Z112FZ remove the UPPER L AUX PUMP SLAVE CONTROL
RELAY (R2-5220) from its receptacle (R5-5220).
(3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5220
receptacle located in the AFT RELAY PANEL Z112FZ.
(4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK L UPR & LWRB1-120722F
(5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Left "UPR TANK PUMP PRESS
LO" light is illuminated.
(6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK L UPR & LWRB1-120722F
(7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS
LO" light is OFF.
(8) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, DC BUS 2
NameNumberColumnRow
L AUX UPR & LWR PRESS LOW LTSB1-124725J
(9) Remove the jumper from pin A1 to pin A2 of the R5-5220 receptacle located in the AFT RELAY
PANEL Z112FZ.
APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 4 OF 10)
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### Page 57

(10) Connect the jumper wire (described in step 1.a.) from pin B1 to pin B2 of the R5-5220
receptacle located in the AFT RELAY PANEL Z112FZ.
(11) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, DC BUS 2
NameNumberColumnRow
L AUX UPR & LWR PRESS LOW LTSB1-124725J
(12) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Right "UPR TANK PUMP PRESS
LO" light is illuminated.
(13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, DC BUS 2
NameNumberColumnRow
L AUX UPR & LWR PRESS LOW LTSB1-124725J
(14) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS
LO" light is OFF.
(15) Remove the jumper from pin B1 to pin B2 of the R5-5220 receptacle located in the AFT RELAY
PANEL Z112FZ.
(16) At the AFT RELAY PANEL Z112FZ install the UPPER L AUX PUMP SLAVE CONTROL
RELAY (R2-5220) to its receptacle (R5-5220).
(17) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, DC BUS 2
NameNumberColumnRow
L AUX UPR & LWR PRESS LOW LTSB1-124725J
(18) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK L UPR & LWRB1-120722F
(19) On the Flight Engineer's Fuel Panel set the L FUEL PUMPS AUX TANKS switch (S1-720) to
UPR position.
APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 5 OF 10)
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### Page 58

(20) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS
LO" light is illuminated.
(21) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK L UPR & LWRB1-120722F
(22) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "UPR TANK PUMP PRESS
LO" light is OFF.
(23) On the Flight Engineer's Fuel Panel set the L FUEL PUMPS AUX TANKS switch (S1-720) to
OFF position.
d. Right Lower Aux Tank Pump M1-93 Uncommanded On Detection Circuit Test Procedure:
(1) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to
OFF position.
(2) At the AFT RELAY PANEL Z112FZ remove the LOWER R AUX PUMP SLAVE CONTROL
RELAY (R2-5221) from its receptacle (R5-5221).
(3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5221
receptacle located in the AFT RELAY PANEL Z112FZ.
(4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 3
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK R LWRB1-120823G
(5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Right "LWR TANK PUMP PRESS
LO" light is illuminated.
(6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 3
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK R LWRB1-120823G
(7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS
LO" light is OFF.
APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 6 OF 10)
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### Page 59

(8) Remove the jumper from pin A1 to pin A2 of the R5-5221 receptacle located in the AFT RELAY
PANEL Z112FZ.
(9) At the AFT RELAY PANEL Z112FZ install the LOWER R AUX PUMP SLAVE CONTROL
RELAY (R2-5221) to its receptacle (R5-5221).
(10) At the Upper Main Circuit Breaker Panel close 5A circuit breakers as follow:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK R UPR & LWRB1-120623E
UPPER MAIN, FUEL AC BUS 3
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK R LWRB1-120823G
(11) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to
ALL position.
(12) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS
LO" and Aux Tank Right "UPR TANK PUMP PRESS LO" lights are illuminated.
(13) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 3
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK R LWRB1-120823G
(14) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS
LO" and Aux Tank Right "UPR TANK PUMP PRESS LO" lights remain illuminated.
(15) On the Flight Engineer's Fuel Panel set the R FUEL PUMPS AUX TANKS switch (S1-719) to
OFF position.
(16) On the Flight Engineer's Fuel Panel verify that the Aux Tank Right "LWR TANK PUMP PRESS
LO" and Aux Tank Right "UPR TANK PUMP PRESS LO" lights are OFF.
(17) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 1
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK R UPR & LWRB1-120623E
APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 7 OF 10)
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### Page 60

e. Left Lower Aux Tank Pump M1-94 Uncommanded On Detection Circuit Test Procedure:
(1) On the Flight Engineer's Fuel Panel set the L FUEL PUMPS AUX TANKS switch (S1-720) to
OFF position.
(2) At the AFT RELAY PANEL Z112FZ remove the LOWER L AUX PUMP SLAVE CONTROL
RELAY (R2-5222) from its receptacle (R5-5222).
(3) Connect the jumper wire (described in step 1.a.) from pin A1 to pin A2 of the R5-5222
receptacle located in the AFT RELAY PANEL Z112FZ.
(4) At the Upper Main Circuit Breaker Panel close 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK L LWRB1-120923F
(5) On the Flight Engineer's Fuel Panel verify that the Aux Tanks Left "LWR TANK PUMP PRESS
LO" light is illuminated.
(6) At the Upper Main Circuit Breaker Panel open 5A circuit breaker as follows:
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK L LWRB1-120923F
(7) On the Flight Engineer's Fuel Panel verify that the Aux Tank Left "LWR TANK PUMP PRESS
LO" light is OFF.
(8) Remove the jumper from pin A1 to pin A2 of the R5-5222 receptacle located in the AFT RELAY
PANEL Z112FZ.
(9) At the AFT RELAY PANEL Z112FZ install the LOWER L AUX PUMP SLAVE CONTROL
RELAY (R2-5222) to its receptacle (R5-5222).
(10) At the Upper Main Circuit Breaker Panel close 5A circuit breakers as follow:
UPPER MAIN, FUEL AC BUS 2
NameNumberColumnRow
FUEL PUMP CONTROL AUX TANK L UPR & LWRB1-120722F
APPENDIX B: FUEL PUMPS UNCOMMANDED ON DETECTION CIRCUIT TEST PROCEDURE
(SHEET 8 OF 10)
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