# Boeing Service Bulletin DC10-28-264: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2016-6417, the docket of a proposed AD (Federal Register 2016-10735, 2017-16775). Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Service Bulletin DC10-28-264](https://openairdocs.org/service-documents/boeing/dc10-28-264.md)
- Title as filed: U.S. DOT/FAA - SB-DC10-28-264-00
- Pages: 207
- PDF: https://openairdocs.org/files/sha256/a6/e7/a6e738df2a4278f814fb3cbe88af7d636a031d8527f231254ed87fa35fd7bca1
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## Text

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### Page 1

Commercial 
Airplanes
DC10
Service Bulletin
Number: DC10-28-264
Original Issue: May 15, 2015
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Housing Electrical Connectors
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 © 2015 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Unpublished Work.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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2.0

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Table of Contents
S u m m a r y  ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A . E f f e c t i v i t y  ................................................ 9
1. Airplanes ............................................. 9
2 . S p a r e s  A f f e c t e d  ........................................ 1 5
B. Concurrent Requirements ...................................... 1 5
C. Reason ................................................ 1 5
D. Description .............................................. 1 6
E. Compliance .............................................. 1 7
F . A p p r o v a l  ............................................... 1 7
G. Manpower .............................................. 1 9
H. Weight and Balance Changes .................................... 3 3
I. Electrical Load Data ......................................... 3 4
J . R e f e r e n c e s  .............................................. 3 4
1. Existing Data: ......................................... 3 4
2. Data Supplied with this Service Bulletin: ........................... 3 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 5
K. Publications Affected ........................................ 3 5
L. Interchangeability and Intermixability of Parts ........................... 3 6
M. Software Accomplishment Summary ................................ 3 6
2. MATERIAL INFORMATION ........................................ 3 7
A. Material - Price and Availability ................................... 3 7
B. Industry Support Information .................................... 3 7
C. Parts Necessary for Each Airplane ................................. 3 7
1 . K i t s / P a r t s  ............................................ 3 7
2. Parts and Materials Supplied by the Operator ........................ 4 1
3. Parts Modified and Reidentified ................................ 4 3
4. Parts Removed and Not Replaced .............................. 4 3
D. Parts Necessary to Change Spares ................................. 4 3
E. Special Tooling - Price and Availability ............................... 4 3
F. Special Tooling Necessary to do this Service Bulletin ....................... 4 3
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 5
A. GENERAL INFORMATION ..................................... 4 5
B. WORK INSTRUCTIONS ....................................... 4 8
FIGURE 1: FUEL PUMP HOUSING - IDENTIFY PROTECTIVE CAP TYPE .............. 6 8
FIGURE 2: BENCH WORK - MAKE ALIGNMENT PINS ......................... 7 1
FIGURE 3: LEFT WING REAR SPAR - DISCONNECT FUEL PUMP WIRES .............. 7 2
FIGURE 4: LEFT WING FORWARD SPAR - DISCONNECT FUEL PUMP WIRES ........... 7 5
FIGURE 5: RIGHT WING FORWARD SPAR - DISCONNECT FUEL PUMP WIRES .......... 7 9
FIGURE 6: RIGHT WING REAR SPAR - DISCONNECT FUEL PUMP WIRES ............. 8 3
FIGURE 7: CENTER WING REAR SPAR (UPPER AUX TANK) - DISCONNECT FUEL PUMP WIRES
[Group 1-4] ........................................... 8 6
FIGURE 8: CENTER WING REAR SPAR (LOWER AUX TANK) - DISCONNECT FUEL PUMP WIRES
[Group 2-4] ........................................... 8 9
F I G U R E  9 : A F T  A U X  T A N K  -  D I S C O N N E C T  F U E L  P U M P  W I R E S  [ G r o u p  3 ]  .............. 9 3
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F I G U R E  1 0 : F O R W A R D  F U S E L A G E  T A N K  -  D I S C O N N E C T  F U E L  P U M P  W I R E S  [ G r o u p  4 ]  ..... 9 7
FIGURE 11: AFT FUSELAGE TANK - DISCONNECT FUEL PUMP WIRES [Group 4] ......... 1 0 0
FIGURE 12: LEFT WING TANK 1 TIP - DISCONNECT FUEL PUMP WIRES [Group 4] ........ 1 0 3
F I G U R E  1 3 : R I G H T  W I N G  T A N K  3  T I P  -  D I S C O N N E C T  F U E L  P U M P  W I R E S  [ G r o u p  4 ]  ....... 1 0 6
FIGURE 14: CHANGE FUEL PUMP HOUSING ELECTRICAL CONNECTOR OPTION 1, CONDITION 1 -
A L L  P U M P S .......................................... 1 0 9
FIGURE 15: CHANGE FUEL PUMP HOUSING ELECTRICAL CONNECTOR OPTION 1, CONDITION 2
( R E Q U I R E S  T A N K  E N T R Y )  -  A L L  P U M P S ......................... 1 1 3
FIGURE 16: CHANGE FUEL PUMP HOUSING OPTION 2 (REQUIRES TANK ENTRY) - ALL PUMPS . 117
FIGURE 17: LEFT WING REAR SPAR - ROUTE AND CLIP FUEL PUMP WIRES ........... 1 2 2
FIGURE 18: LEFT WING FWD SPAR - ROUTE AND CLIP FUEL PUMP WIRES ........... 1 2 5
FIGURE 19: RIGHT WING FWD SPAR - ROUTE AND CLIP FUEL PUMP WIRES ........... 1 2 9
FIGURE 20: RIGHT WING REAR SPAR - ROUTE AND CLIP FUEL PUMP WIRES .......... 1 3 3
FIGURE 21: CENTER WING REAR SPAR (UPPER AUX TANK) - ROUTE AND CLIP FUEL PUMP WIRES
[Group 1-4] .......................................... 1 3 6
FIGURE 22: CENTER WING REAR SPAR (LOWER AUX TANK) - ROUTE AND CLIP FUEL PUMP WIRES
[Group 2-4] .......................................... 1 3 9
FIGURE 23: AFT AUX TANK - ROUTE AND CLIP FUEL PUMP WIRES [Group 3] ........... 1 4 3
FIGURE 24: FORWARD FUSELAGE TANK- ROUTE AND CLIP FUEL PUMP WIRES [Group 4] . . . 147
FIGURE 25: AFT FUSELAGE TANK - ROUTE AND CLIP FUEL PUMP WIRES [Group 4] ....... 1 5 1
F I G U R E  2 6 : L E F T  W I N G  T A N K  1  T I P  -  R O U T E  A N D  C L I P  F U E L  P U M P  W I R E S  [ G r o u p  4 ]  ...... 1 5 5
FIGURE 27: RIGHT WING TANK 3 TIP - ROUTE AND CLIP FUEL PUMP WIRES [Group 4] ..... 1 5 8
FIGURE 28: LEFT WING REAR SPAR - TERMINATE FUEL PUMP WIRES .............. 1 6 1
FIGURE 29: LEFT WING FORWARD SPAR - TERMINATE FUEL PUMP WIRES ........... 1 6 5
FIGURE 30: RIGHT WING FORWARD SPAR - TERMINATE FUEL PUMP WIRES .......... 1 6 8
FIGURE 31: RIGHT WING REAR SPAR - TERMINATE FUEL PUMP WIRES ............. 1 7 1
FIGURE 32: CENTER WING REAR SPAR UPPER AUXILIARY TANK - TERMINATE FUEL PUMP WIRES
[Group 1-4] .......................................... 1 7 5
FIGURE 33: CENTER WING REAR SPAR LOWER AUXILIARY TANK - TERMINATE FUEL PUMP WIRES
[Group 2-4] .......................................... 1 7 8
F I G U R E  3 4 : A F T  A U X I L I A R Y  T A N K  -  T E R M I N A T E  F U E L  P U M P  W I R E S  [ G r o u p  3 ]  .......... 1 8 1
FIGURE 35: FORWARD FUSELAGE TANK - TERMINATE FUEL PUMP WIRES [Group 4] ...... 1 8 4
F I G U R E  3 6 : A F T  F U S E L A G E  T A N K  -  T E R M I N A T E  F U E L  P U M P  W I R E S  [ G r o u p  4 ]  .......... 1 8 6
F I G U R E  3 7 : L E F T  W I N G  T A N K  1  T I P  -  T E R M I N A T E  F U E L  P U M P  W I R E S  [ G r o u p  4 ]  ......... 1 8 8
FIGURE 38: RIGHT WING TANK 3 TIP - TERMINATE FUEL PUMP WIRES [Group 4] ........ 1 9 0
APPENDIX A: 24 MONTH REPETITIVE INSPECTION ........................... 1 9 2
APPENDIX B: BOEING PART DEMAND INTENT - SURVEY ....................... 2 0 7
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Commercial 
Airplanes
DC10
Service Bulletin
SummaryNumber: DC10-28-264Original Issue: May 15, 2015
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Housing Electrical Connectors
CONCURRENT REQUIREMENTS
Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND
MD-11 and DC-10 operators have reported instances of fuel pump housing electrical connector failures related
to ingress of airplane fluids. Currently installed fuel pump housing electrical connectors have 18 month repetitive
inspection requirements related to Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2011-11-05
and AD 2002-13-10. An improved fuel pump housing electrical connector has been developed in conjunction
with Hydro-Aire to supersede the currently installed fuel pump housing electrical connectors. In addition to the
new fuel pump housing electrical connector, the use of environmentally sealed terminal lugs will help to prevent
the wicking of airplane fluids into the fuel pump wires and the fuel pump housing electrical connector. If not
corrected, failure of the fuel pump housing electrical connector could result in a potential source of ignition in a
fuel tank and consequent fire or explosion.
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 FTD 28-11002, DC-10 FTD 28-12001 and DC-10 FTD 28-13003 are
related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedYesSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedYesAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
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ReferenceAffectedPlanning Data
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
This service bulletin provides instructions to change/replace fuel pump housing electrical connectors or fuel
pump housings, associated wires, feed-through components and install sealed terminal lugs on fuel pump wires
as follows:
1. Remove fuel boost/transfer pumps (AC Pumping Units).
2. Do Option 1 or Option 2.
Option 1 (Replace Fuel Pump Housing Electrical Connector)
a. Identify the fuel pump housing protective cap type.
Condition 1 (Spring Mounted Protective Cap - Tank Entry Not Required)
(1) Change the fuel pump housing electrical connector, associated wires, fuel tank feed through
components and install sealed terminal lugs on fuel pump wiring.
Condition 2 (No Spring Mounted Protective Cap - Tank Entry Required)
(1) Change the fuel pump housing electrical connector, associated wires, fuel tank feed through
components and install sealed terminal lugs on fuel pump wiring.
Option 2 (Replace Fuel Pump Housing - Tank Entry Required)
a. Replace the fuel pump housing, associated wires, fuel tank feed through components and install
sealed terminal lugs on fuel pump wiring (Tank entry required).
3. Install previously removed fuel boost/transfer pumps (AC Pumping Units).
EFFECTIVITY
All 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-10-10F and MD-10-30F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list
of affected airplane(s).
Refer to Paragraph 1.A.2., Spares Affected for the list of affected components.
COMPLIANCE
Boeing recommends that the change given in this service bulletin be done within 36 months after the original
issue date of this service bulletin.
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The FAA will possibly release an AD related to this service bulletin. The AD will make the compliance tasks and
times given in this service bulletin mandatory.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
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 B of this service bulletin to help Boeing
predict the quantity and timing of the Boeing Supplied Kits/Parts.
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Commercial 
Airplanes
DC10
Service Bulletin
Number: DC10-28-264
Original Issue: May 15, 2015
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Housing Electrical Connectors
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes with Auxiliary Upper Fuel Tank.-1
Airplanes with Auxiliary Upper and Lower Fuel Tanks.-2
Airplanes with Auxiliary Fuel Tanks and Aft Fuel Tank.-3
Airplanes with Auxiliary Fuel Tanks, Fwd and Aft Fuel Tanks.-4
Airplanes with Tank No. 1, Tank No. 2, and Tank No. 3 only.-5
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-10-10F, MD-10-30F
GroupFuselage Num-
ber
12
56
58
515
517
525
526
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GroupFuselage Num-
ber
527
532
533
534
535
539
540
541
542
543
555
559
260
561
562
165
570
271
172
576
578
183
586
589
290
296
299
2100
2103
2106
2110
5112
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GroupFuselage Num-
ber
2114 - 115
2117
5119
2122 - 123
2127
2129
2131 - 135
2137
5138 - 139
5140
5142
5144 - 145
2146 - 147
5148
2150
2152
5153 - 155
2156 - 158
2160
5162
2165 - 166
5169
2170 - 171
5173
2174
5177
2178 - 179
2183 - 184
2187 - 189
2190
2192
5194
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GroupFuselage Num-
ber
2195 - 196
5198
2199
2201
5203
2204
5205
2206
5207 - 209
5210
2211 - 216
2219
2220 - 221
2223 - 227
2229
2230
2232
2234 - 236
2239
2240
2242
2244 - 246
5247
2248
5249
5250
1251 - 252
2253 - 257
2261 - 268
5269
5270 - 273
2274 - 275
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GroupFuselage Num-
ber
2277
2281 - 282
1285
2286
2289
2290 - 291
3292
5294
5296 - 298
2299
2300 - 306
5307
2308
5309
2310
4311
2312 - 317
1318
5319
5321
5323
2324 - 327
2329
2330
2332
4333
2334 - 339
2340
3341
2342 - 343
5344
3345
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GroupFuselage Num-
ber
1346
5347
2349
5351
5353
2355 - 356
5358
4359
4360 - 361
4363
2366 - 367
1372
4373
4375 - 378
5379
4380
2381
4383 - 389
4390 - 399
4400 - 408
2409
4410 - 411
2412
4413 - 415
2416
4417 - 418
2419
4420 - 421
2422
4423 - 429
4430 - 432
2433
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GroupFuselage Num-
ber
3434 - 438
4439
2440
4441
2442 - 446
2. Spares Affected
Examine your spares supply for the parts or components identified below. If any parts or components
are found, refer to Paragraph 2.D., Parts Necessary to Change Spares, for the recommended
action.
More DataNamePart Number
(a)FUEL PUMP HOUSING60-843, 60-843M, 60-843-1, 60-843-1M, 60-
843-2, 60-843-2M, 60-843-3, 60-845, 60-845M,
60-845-1, 60-845-1M, 60-845-2, 60-845-2M,
60-845-3
(a) Refer to Hydro-Aire SB 60-843/845-28-2 for fuel pump housing modification.
B. Concurrent Requirements
The service bulletin listed below must be done before or at the same time as this service bulletin:
DescriptionService BulletinCompany
Modification of Fuel Pump HousingsHydro-Aire SB 60-
843/845-28-2
Hydro-Aire, Incorporat-
ed
C. Reason
MD-11 and DC-10 operators have reported instances of fuel pump housing electrical connector failures
related to ingress of airplane fluids. Currently installed fuel pump housing electrical connectors have
18 month repetitive inspection requirements related to Federal Aviation Administration (FAA)
Airworthiness Directive (AD) 2011-11-05 and AD 2002-13-10. An improved fuel pump housing electrical
connector has been developed in conjunction with Hydro-Aire to supersede the currently installed fuel
pump housing electrical connectors. In addition to the new fuel pump housing electrical connector, the
use of environmentally sealed terminal lugs will help to prevent the wicking of airplane fluids into the
fuel pump wires and the fuel pump housing electrical connector. If not corrected, failure of the fuel
pump housing electrical connector could result in a potential source of ignition in a fuel tank and
consequent fire or explosion.
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 FTD 28-11002, DC-10 FTD 28-12001 and DC-10 FTD 28-13003
are related to this service bulletin.
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D. Description
This service bulletin provides instructions to change/replace fuel pump housing electrical connectors
or fuel pump housings, associated wires, feed-through components and install sealed terminal lugs on
fuel pump wires as follows:
1. Remove fuel boost/transfer pumps (AC Pumping Units).
2. Do Option 1 or Option 2.
Option 1 (Replace Fuel Pump Housing Electrical Connector)
a. Identify the fuel pump housing protective cap type.
Condition 1 (Spring Mounted Protective Cap - Tank Entry Not Required)
(1) Change the fuel pump housing electrical connector, associated wires, fuel tank feed
through components and install sealed terminal lugs on fuel pump wiring.
Condition 2 (No Spring Mounted Protective Cap - Tank Entry Required)
(1) Change the fuel pump housing electrical connector, associated wires, fuel tank feed
through components and install sealed terminal lugs on fuel pump wiring.
Option 2 (Replace Fuel Pump Housing - Tank Entry Required)
a. Replace the fuel pump housing, associated wires, fuel tank feed through components and
install sealed terminal lugs on fuel pump wiring (Tank entry required).
3. Install previously removed fuel boost/transfer pumps (AC Pumping Units).
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
144, 145, 511, 512, 514, 541, 611, 612, 614, 641DC-10-10, DC-10-10F, DC-10-
15
Group 2:
Affected Maintenance Zones
ZoneModel
144, 145, 511, 512, 514, 541, 611, 612, 614, 641DC-10-30, DC-10-30F, DC-10-
30F (KDC-10), DC-10-40, DC-
10-40F, MD-10-30F
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Group 3:
Affected Maintenance Zones
ZoneModel
144, 145, 186, 511, 512, 514, 541, 611, 612,
614, 641
DC-10-30
Group 4:
Affected Maintenance Zones
ZoneModel
144, 145, 186, 254, 511, 512, 514, 541, 551,
611, 612, 614, 641, 651
DC-10-30F (KC-10A)
Group 5:
Affected Maintenance Zones
ZoneModel
511, 512, 514, 541, 611, 612, 614, 641DC-10-10, DC-10-10F, DC-10-
15, MD-10-10F
E. Compliance
Boeing recommends that the change given in this service bulletin be done within 36 months after the
original issue date of this service bulletin.
The FAA will possibly release an AD related to this service bulletin. The AD will make the compliance
tasks and times given in this service bulletin mandatory.
F. Approval
DC-10 Airplanes:
1. This service bulletin was examined by the 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.
2. 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 an alternative method of compliance
to the requirements of paragraph (h)(1) and (h)(2) of AD 2011-11-05 and paragraph (a) and (b) of
AD 2002-13-10. Accomplishment of this service bulletin extends the repetitive inspection
requirements of AD 2002-13-10 paragraph (a) and AD 2011-11-05 paragraph (j) from 18 months
to 24 months. All provisions of AD 2011-11-05 and AD 2002-13-10 that are not specifically
referenced in the above statement remain fully applicable and must be complied with, except as
noted below.
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3. 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 and service bulletin DC10-28A253,
when both actions are accomplished, as terminating action for the repetitive inspection requirements
of the following Boeing Service Bulletins and FAA ADs:
a. DC10-28A228, Rev 00, 01, 02 and paragraphs (a) and (b) of FAA AD 2002-13-10.
b. DC10-28A228, Rev 00, 01, 02 and paragraphs (a) and (b) of FAA AD 2003-07-14.
c. DC10-28A261, Rev 00, 01 and paragraph (j) of FAA AD 2011-11-05.
4. 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 and service bulletin DC10-28A253,
when both actions are accomplished, as terminating action for paragraph (a) of FAA AD 2000-22-21
and paragraph (i) of FAA AD 2011-11-05 and removal from the Airplane Flight Manual (AFM)
Procedures Section and Flight Crew Operations Manual the associated Interim Operating Procedure
(IOP) regarding abnormal operations for fuel pump electrical connector failures associated with
Boeing Flight Operations Bulletin DC-10-00-01A and Boeing DC-10 Operations Bulletin 2-001B.
Paragraph (b) of FAA AD 2000-22-21 affecting the AFM Limitations Section must still be complied
with and is not terminated by this service bulletin.
5. 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.
MD-10 Airplanes:
1. This service bulletin was examined by the 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.
2. 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 an alternative method of compliance
to the requirements of paragraph (h)(1) and (h)(2) of AD 2011-11-05 and paragraph (a) and (b) of
AD 2002-13-10. Accomplishment of this service bulletin extends the repetitive inspection
requirements of AD 2002-13-10 paragraph (a) and AD 2011-11-05 paragraph (j) from 18 months
to 24 months. All provisions of AD 2011-11-05 and AD 2002-13-10 that are not specifically
referenced in the above statement remain fully applicable and must be complied with, except as
noted below.
3. 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 and service bulletin DC10-28A253,
when both actions are accomplished, as terminating action for the repetitive inspection requirements
of the following Boeing Service Bulletins and FAA ADs:
a. DC10-28A228, Rev 00, 01, 02 and paragraphs (a) and (b) of FAA AD 2002-13-10.
b. DC10-28A228, Rev 00, 01, 02 and paragraphs (a) and (b) of FAA AD 2003-07-14.
c. DC10-28A261, Rev 00, 01 and paragraph (j) of FAA AD 2011-11-05.
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4. 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 and service bulletin DC10-28A253,
when both actions are accomplished, as terminating action for paragraph (a) of FAA AD 2000-22-21
and paragraph (i) of FAA AD 2011-11-05 and removal from the Airplane Flight Manual (AFM)
Procedures Section and Flight Crew Operations Manual the associated Interim Operating Procedure
(IOP) regarding abnormal operations for fuel pump electrical connector failures associated with
Boeing Flight Operations Bulletin MD-10-00-02A and Boeing MD-10 Flight Crew Operations Manual
Advisory Bulletin 2-01B. Paragraph (b) of FAA AD 2000-22-21 affecting the AFM Limitations Section
must still be complied with and is not terminated by this service bulletin.
5. 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:
• 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:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 1 (Spring Mounted Cap)
Elapsed HoursTask HoursNumber of PersonsTask
2.02.01Open Access
0.60.61FIGURE 1
0.50.51FIGURE 2
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
0.81.62FIGURE 7
7.214.42FIGURE 14
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
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Group 1:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 1 (Spring Mounted Cap)
Elapsed HoursTask HoursNumber of PersonsTask
0.81.62FIGURE 21
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
2.02.01Close Access
0.51.02Test
23.642.1TOTAL FOR EACH AIRPLANE
Group 1:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 2 (No Spring Mounted
Cap)
Elapsed HoursTask HoursNumber of PersonsTask
4.04.01Open Access
0.60.61FIGURE 1
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
0.81.62FIGURE 7
13.226.42FIGURE 15
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.81.62FIGURE 21
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
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Group 1:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 2 (No Spring Mounted
Cap)
Elapsed HoursTask HoursNumber of PersonsTask
4.04.01Close Access
0.51.02Test
33.157.6TOTAL FOR EACH AIRPLANE
Group 1:
Option 2 (Change Fuel Pump Housings)
Elapsed HoursTask HoursNumber of PersonsTask
2.02.01Open Access
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
0.81.62FIGURE 7
13.226.42FIGURE 16
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.81.62FIGURE 21
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
2.02.01Close Access
0.51.02Test
32.557.0TOTAL FOR EACH AIRPLANE
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Group 2:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 1 (Spring Mounted Cap)
Elapsed HoursTask HoursNumber of PersonsTask
2.02.01Open Access
0.70.71FIGURE 1
0.50.51FIGURE 2
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
0.81.62FIGURE 7
0.81.62FIGURE 8
8.416.82FIGURE 14
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.81.62FIGURE 21
0.81.62FIGURE 22
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
0.20.42FIGURE 33
2.02.01Close Access
0.51.02Test
26.748.2TOTAL FOR EACH AIRPLANE
Group 2:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 2 (No Spring Mounted
Cap)
Elapsed HoursTask HoursNumber of PersonsTask
4.04.01Open Access
0.70.71FIGURE 1
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Group 2:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 2 (No Spring Mounted
Cap)
Elapsed HoursTask HoursNumber of PersonsTask
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
0.81.62FIGURE 7
0.81.62FIGURE 8
15.430.82FIGURE 15
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.81.62FIGURE 21
0.81.62FIGURE 22
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
0.20.42FIGURE 33
4.04.01Close Access
0.51.02Test
37.266.2TOTAL FOR EACH AIRPLANE
Group 2:
Option 2 (Change Fuel Pump Housings)
Elapsed HoursTask HoursNumber of PersonsTask
4.04.01Open Access
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
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Group 2:
Option 2 (Change Fuel Pump Housings)
Elapsed HoursTask HoursNumber of PersonsTask
0.81.62FIGURE 7
0.81.62FIGURE 8
15.430.82FIGURE 14
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.81.62FIGURE 21
0.81.62FIGURE 22
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
0.20.42FIGURE 33
4.04.01Close Access
0.51.02Test
36.565.0TOTAL FOR EACH AIRPLANE
Group 3:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 1 (Spring Mounted Cap)
Elapsed HoursTask HoursNumber of PersonsTask
2.02.01Open Access
0.80.81FIGURE 1
0.50.51FIGURE 2
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
0.81.62FIGURE 7
0.81.62FIGURE 8
0.81.62FIGURE 9
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Group 3:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 1 (Spring Mounted Cap)
Elapsed HoursTask HoursNumber of PersonsTask
9.619.22FIGURE 14
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.81.62FIGURE 21
0.81.62FIGURE 22
0.81.62FIGURE 23
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
0.20.42FIGURE 33
0.20.42FIGURE 34
2.02.01Close Access
0.51.02Test
29.854.3TOTAL FOR EACH AIRPLANE
Group 3:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 2 (No Spring Mounted
Cap)
Elapsed HoursTask HoursNumber of PersonsTask
4.04.01Open Access
0.80.81FIGURE 1
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
0.81.62FIGURE 7
0.81.62FIGURE 8
0.81.62FIGURE 9
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Group 3:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 2 (No Spring Mounted
Cap)
Elapsed HoursTask HoursNumber of PersonsTask
17.635.22FIGURE 15
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.81.62FIGURE 21
0.81.62FIGURE 22
0.81.62FIGURE 23
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
0.20.42FIGURE 33
0.20.42FIGURE 34
4.04.01Close Access
0.51.02Test
41.373.8TOTAL FOR EACH AIRPLANE
Group 3:
Option 2 (Change Fuel Pump Housings)
Elapsed HoursTask HoursNumber of PersonsTask
4.04.01Open Access
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
0.81.62FIGURE 7
0.81.62FIGURE 8
0.81.62FIGURE 9
17.635.22FIGURE 16
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Group 3:
Option 2 (Change Fuel Pump Housings)
Elapsed HoursTask HoursNumber of PersonsTask
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.81.62FIGURE 21
0.81.62FIGURE 22
0.81.62FIGURE 23
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
0.20.42FIGURE 33
0.20.42FIGURE 34
4.04.01Close Access
0.51.02Test
40.573.0TOTAL FOR EACH AIRPLANE
Group 4:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 1 (Spring Mounted Cap)
Elapsed HoursTask HoursNumber of PersonsTask
2.02.01Open Access
0.90.91FIGURE 1
0.50.51FIGURE 2
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
0.81.62FIGURE 7
0.81.62FIGURE 8
0.40.82FIGURE 10
0.40.82FIGURE 11
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Group 4:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 1 (Spring Mounted Cap)
Elapsed HoursTask HoursNumber of PersonsTask
0.40.82FIGURE 12
0.40.82FIGURE 13
10.821.62FIGURE 14
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.81.62FIGURE 21
0.81.62FIGURE 22
0.40.82FIGURE 24
0.40.82FIGURE 25
0.40.82FIGURE 26
0.40.82FIGURE 27
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
0.20.42FIGURE 33
0.10.22FIGURE 35
0.10.22FIGURE 36
0.10.22FIGURE 37
0.10.22FIGURE 38
2.02.01Close Access
0.51.02Test
32.960.4TOTAL FOR EACH AIRPLANE
Group 4:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 2 (No Spring Mounted
Cap)
Elapsed HoursTask HoursNumber of PersonsTask
4.04.01Open Access
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Group 4:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 2 (No Spring Mounted
Cap)
Elapsed HoursTask HoursNumber of PersonsTask
0.90.91FIGURE 1
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
0.81.62FIGURE 7
0.81.62FIGURE 8
0.40.82FIGURE 10
0.40.82FIGURE 11
0.40.82FIGURE 12
0.40.82FIGURE 13
19.839.62FIGURE 15
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.81.62FIGURE 21
0.81.62FIGURE 22
0.40.82FIGURE 24
0.40.82FIGURE 25
0.40.82FIGURE 26
0.40.82FIGURE 27
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
0.20.42FIGURE 33
0.10.22FIGURE 35
0.10.22FIGURE 36
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Group 4:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 2 (No Spring Mounted
Cap)
Elapsed HoursTask HoursNumber of PersonsTask
0.10.22FIGURE 37
0.10.22FIGURE 38
4.04.01Close Access
0.51.02Test
45.481.9TOTAL FOR EACH AIRPLANE
Group 4:
Option 2 (Change Fuel Pump Housings)
Elapsed HoursTask HoursNumber of PersonsTask
4.04.01Open Access
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
0.81.62FIGURE 7
0.81.62FIGURE 8
0.40.82FIGURE 10
0.40.82FIGURE 11
0.40.82FIGURE 12
0.40.82FIGURE 13
19.839.62FIGURE 16
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.81.62FIGURE 21
0.81.62FIGURE 22
0.40.82FIGURE 24
0.40.82FIGURE 25
0.40.82FIGURE 26
0.40.82FIGURE 27
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Group 4:
Option 2 (Change Fuel Pump Housings)
Elapsed HoursTask HoursNumber of PersonsTask
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
0.20.42FIGURE 32
0.20.42FIGURE 33
0.10.22FIGURE 35
0.10.22FIGURE 36
0.10.22FIGURE 37
0.10.22FIGURE 38
4.04.01Close Access
0.51.02Test
44.581.0TOTAL FOR EACH AIRPLANE
Group 5:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 1 (Spring Mounted Cap)
Elapsed HoursTask HoursNumber of PersonsTask
1.01.01Open Access
0.50.51FIGURE 1
0.50.51FIGURE 2
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
6.012.02FIGURE 14
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
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Group 5:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 1 (Spring Mounted Cap)
Elapsed HoursTask HoursNumber of PersonsTask
0.30.62FIGURE 31
1.01.01Close Access
0.51.02Test
18.534.0TOTAL FOR EACH AIRPLANE
Group 5:
Option 1 (Change Fuel Pump Housing Electrical Connectors) Condition 2 (No Spring Mounted
Cap)
Elapsed HoursTask HoursNumber of PersonsTask
2.02.01Open Access
0.50.51FIGURE 1
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
11.022.02FIGURE 15
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
2.02.01Close Access
0.51.02Test
25.045.5TOTAL FOR EACH AIRPLANE
Group 5:
Option 2 (Change Fuel Pump Housings)
Elapsed HoursTask HoursNumber of PersonsTask
2.02.01Open Access
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Group 5:
Option 2 (Change Fuel Pump Housings)
Elapsed HoursTask HoursNumber of PersonsTask
1.22.42FIGURE 3
0.81.62FIGURE 4
0.81.62FIGURE 5
1.22.42FIGURE 6
11.022.02FIGURE 16
1.22.42FIGURE 17
0.81.62FIGURE 18
0.81.62FIGURE 19
1.22.42FIGURE 20
0.30.62FIGURE 28
0.20.42FIGURE 29
0.20.42FIGURE 30
0.30.62FIGURE 31
2.02.01Close Access
0.51.02Test
24.545.0TOTAL 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
-1599.4-1.2+1332.8DC-10-10, DC-10-10F,
DC-10-15
Group 2:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
-1740.6-1.3+1338.9DC-10-30, DC-10-30F,
DC-10-30F(KDC-10),
DC-10-40, DC-10-40F,
MD-10-30F
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Group 3:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
-2238.2-1.6+1398.9DC-10-30
Group 4:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
-2316.1-1.7+1362.4DC-10-30F( KC-10A)
Group 5:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
-1324.4-1.0+1324.4DC-10-10, DC-10-10F,
DC-10-15, MD-10-10F
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin DC10-28A228, DC10-28A253 and DC10-28A261.
b. Boeing DC-10 Operations Bulletin 2-001B.
c. Boeing Flight Operations Bulletin DC-10-00-01A and MD-10-00-02A.
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2000-22-21, 2002-13-10,
2003-07-14 and 2011-11-05.
e. DC-10, MD-10 Aircraft Maintenance Manual (AMM) 12-11-03, 28-00-00, 28-22-00 and 28-22-01.
f. DC-10 Fleet Team Digest (FTD) 28-11002, 28-12001 and 28-13003.
g. DC-10, MD-10 Structural Repair Manual (SRM) 51.
h. DC-10 Operations Bulletin 2-001B.
i. Hydro-Aire Service Bulletin 60-843/845-28-2.
j. Hydro-Aire Service Information Letter 60-847-3-1.
k. MD-10 Flight Crew Operations Manual Advisory Bulletin 2-01B.
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l. Nondestructive Testing Standard Practices Manual, Part 9.
m. Standard Overhaul Practices Manual (SOPM) 20-50-01.
n. Standard Wiring Practices Manual (SWPM) 20-00-00, 20-00-03, 20-00-13, 20-00-16, 20-10-01,
20-10-10, 20-20-01, 20-20-03, 20-31-00 and 20-50-01.
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
ChangeTitleDocument Number
AELECTRICAL INSTALLATION - FUEL PUMP ELECTRICAL
CONNECTOR
SR10280076
AEO BELECTRICAL INSTALLATION - FUEL PUMP ELECTRICAL
CONNECTOR
SR10280076
NEWREPLACEMENT INSTALLATION - FUEL PUMP HOUSINGSR10280080
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
28-22Aircraft Maintenance Manual
Procedures SectionFAA Approved Airplane Flight Manual
28-02Fault Isolation Manual (DC-10)
28-14, 28-22Fault Isolation Manual (MD-10)
Interim Operating ProcedureFlight Crew Operations Manual
28-13, 28-22Illustrated Parts Catalog
28-22Schematic Manual
MDC-02K1003 (CDCCL 28-2)Special Compliance Item Report
28-22Wiring Diagram Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in 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.
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L. Interchangeability and Intermixability of Parts
Old and new parts are not interchangeable.
M. Software Accomplishment Summary
Not affected.
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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
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPON-
DER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFOR-
MATION
Unit Price as of the original
issue date of this Service
Bulletin (US Dollars)
ROLT as of the original issue
date of this Service Bulletin
(Calendar Days)
NameKit Number
$4,310.0090Service KitSB10280264-3
$4,442.0090Service KitSB10280264-5
$6,113.0090Service KitSB10280264-7
$8,275.0090Service KitSB10280264-9
$4,089.0090Service KitSB10280264-11
Operators are encouraged to complete the survey provided in APPENDIX B 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.
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Group 1:
SB10280264-3 Service Kit
NotesExisting Part NumberNameQTYNew Part Number
KIT4SR10280076-3
KIT8SR10280076-5
Group 2:
SB10280264-5 Service Kit
NotesExisting Part NumberNameQTYNew Part Number
KIT4SR10280076-3
KIT8SR10280076-5
KIT2SR10280076-7
Group 3:
SB10280264-7 Service Kit
NotesExisting Part NumberNameQTYNew Part Number
KIT4SR10280076-3
KIT8SR10280076-5
KIT2SR10280076-7
KIT2SR10280076-9
PLUG1ANP0065-537
Group 4:
SB10280264-9 Service Kit
NotesExisting Part NumberNameQTYNew Part Number
KIT4SR10280076-3
KIT8SR10280076-5
KIT2SR10280076-7
KIT4SR10280076-11
GLAND4AAN7113-525
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Group 5:
SB10280264-11 Service Kit
NotesExisting Part NumberNameQTYNew Part Number
KIT4SR10280076-3
KIT6SR10280076-5
SR10280076-3 Kit
NotesExisting Part NumberNameQTYNew Part Number
COMB12768771-505
TERM LUG3D-436-1802-COLD
TERM LUG1D4361102COLD-ES
LOCKWASHER3MS35338-137
LOCKWASHER1MS35338-43
NUT3MS35649-284
GLAND NUT1M8700-7/3
WASHER1NAS620C10L
WASHER3NAS620C8
(a)SCREW13D0005-3-12
(a)FERRULE17D0294-1
(a)PIN19D0196-1
BUSHING19D0357-1
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
SR10280076-5 Kit
NotesExisting Part NumberNameQTYNew Part Number
TERM LUG3D-436-1802-COLD
TERM LUG1D4361102COLD-ES
LOCKWASHER3MS35338-137
LOCKWASHER1MS35338-43
NUT3MS35649-284
WASHER1NAS620C10L
WASHER3NAS620C8
NUT GROMMET ASSY110-74916-8
(a)SCREW13D0005-3-12
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SR10280076-5 Kit
NotesExisting Part NumberNameQTYNew Part Number
(a)SEALING PLUG15D0206-12
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
SR10280076-7 Kit
NotesExisting Part NumberNameQTYNew Part Number
TERM LUG3D-436-1802-COLD
TERM LUG1D4361102COLD-ES
LOCKWASHER3MS35338-137
LOCKWASHER1MS35338-43
NUT3MS35649-284
WASHER1NAS620C10L
WASHER3NAS620C8
SLEEVE110-35916-16
GROMMET110-60766-8
(a)SCREW13D0005-3-12
(a)SEALING PLUG15D0206-12
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
SR10280076-9 Kit
NotesExisting Part NumberNameQTYNew Part Number
COMB12768771-505
PIN T/C 7054LRM16M-32DJ5
GLAND NUT1M8700-7/3
(a)FERRULE17D0294-1
(a)PIN19D0196-1
BUSHING19D0357-1
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
SR10280076-11 Kit
NotesExisting Part NumberNameQTYNew Part Number
COMB12768771-505
TERM LUG3D-436-1802-COLD
TERM LUG1D4361102COLD-ES
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SR10280076-11 Kit
NotesExisting Part NumberNameQTYNew Part Number
LOCKWASHER3MS35338-137
LOCKWASHER1MS35338-43
NUT3MS35649-284
GLAND NUT1M8700-7/3
WASHER1NAS620C10L
WASHER3NAS620C8
(a)SCREW13D0005-3-12
(a)FERRULE17D0294-1
(a)PIN19D0196-1
BUSHING19D0357-1
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
All Groups, Option 1, Condition 1
NotesNameQTY Per GroupPart Number/
Specification 54321
(a) (b) (c)Modification Kit101816141260-843-4901
(a) Refer to Hydro-Aire SB 60-843/845-28-2.
(b) Each Modification Kit Contains:
60-843504 Connector Assembly (QTY 1)
M25988/1-019 Packing, Preformed (QTY 1)
ES500D4-6 or LL500D4-6 Screw, Self-Locking (QTY 4)
(c) Can be purchased from:
Repair and Overhaul
Hydro-Aire, Incorporated
3000 Winona Avenue
Burbank, California 91504 CAGE 81982
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All Groups, Option 1, Condition 2
NotesNameQTY Per GroupPart Number/
Specification 54321
(a) (b) (c)Modification Kit101816141260-843-4901
(a) (c)Protective CapAS REQUIRED60-84349
(a) (c)Packing1018161412MS29513-152
(a) Refer to Hydro-Aire SB 60-843/845-28-2.
(b) Each Modification Kit Contains:
60-84304 Connector Assembly (QTY 1)
M25988/1-019 Packing, Preformed (QTY 1)
ES500D4-6 or LL500D4-6 Screw, Self-Locking (QTY 4)
(c) Can be purchased from:
Repair and Overhaul
Hydro-Aire, Incorporated
3000 Winona Avenue
Burbank, California 91504 CAGE 81982
All Groups, Option 2
NotesNameQTY Per GroupPart Number/
Specification 54321
(a)Seal1018161412460-015-40
(b) (c)Fuel Pump Housing4676560-843-4
(b) (c)Fuel Pump Housing61298760-845-4
(a)PackingAS REQUIREDMS29512-04
(a)Packing1018161412MS29512-06
(a)Packing1018161412MS29512-10
(a)Packing2036322824MS29513-237
(a)2036322824S4892944-230
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Hydro-Aire SB 60-843/845-28-2.
(c) Can be purchased from:
Repair and Overhaul
Hydro-Aire, Incorporated
3000 Winona Avenue
Burbank, California 91504 CAGE 81982
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3. Parts Modified and Reidentified
Refer to Hydro-Aire SB 60-843/845-28-2.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
Refer to Hydro-Aire SB 60-843/845-28-2.
E. Special Tooling - Price and Availability
Special test equipment required to accomplish this inspection is to be fabricated by the operator,
procured from operator's stock, or sources indicated in Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin.
NOTE: A new die (Y1111) was developed to crimp the sealed lugs. The new die can be used with
Tool Code MGP (M22520/5-01 frame).
F. Special Tooling Necessary to do this Service Bulletin
1. To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.
Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also
be necessary. Examine operator tool supply to make sure all necessary tools are available.
SupplierCAGETypeEquipment
Fluke Corporation
1420 75th Street South West
Everett, Washington 98206
0HYG7Model 10Multimeter
or
Equivalent
Quadtech Incorporated
734 Forest Street, Suite 500
Marlborough, Massachusetts
01752
0PK96Model 1864Megohm meter
or
Equivalent (a)
(a) An Equivalent Megohm Meter must be able to apply voltage at 100+/-10 Volts DC and be
current Limited to 5 Milliamps.
2. A T67291 or T67291-1 test tool/alternate tool is required to accomplish this inspection. See
Hydro-Aire Service Information Letter 60-847-3-1.
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### Page 45

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: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
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.
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 installation
standards given 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 given 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 Values:
— Values for structural fasteners are given in DC-10, MD-10 Structural Repair
Manual, Chapter 51.
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— Values for airframe maintenance tasks are included in Chapter 20 of DC-10,
MD-10 Airplane Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of DC-10,
MD-10 Airplane Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
7. Refer to these SWPM chapters for applicable operations, as accepted procedures:
TitleChapter
GENERAL - MAINTENANCE SAFETY PRACTICESSWPM 20-00-00
IDENTIFICATION OF ELECTRICAL WIRE - COMMERCIALSWPM 20-00-03
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
WIRE HARNESS and COMPONENT CLEANINGSWPM 20-10-10
TERMINALS - MAINTENANCE PRACTICESSWPM 20-20-01
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.
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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. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
15. Some steps in the Work Instructions are identified as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
identified as RC must be done to comply with the AD. Alternative procedures for
steps not identified with RC can be used if the RC steps can still be done as specified,
and the airplane can be put back in a serviceable condition. An Alternative Method
of Compliance (AMOC) is not necessary for deviations to steps that are not identified
as RC.
16. The CONDITIONS, ACTIONS and OPTIONS shown apply to each fuel pump
independently.
17. Identify and note location of wires prior to removal from terminal strip and/or ground
stud.
18. Install clamps to ensure a friction fit on wire bundles to prevent movement within the
clamp when moderate pressure is applied. It is permissible to select smaller or larger
size in that type clamp to meet this requirement.
19. For airplanes who have accomplished this service bulletin (airplanes with fuel pump
connector part number 60-843504 installed) the 24 month repetitive inspection
instructions are contained in APPENDIX A.
20. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure or irregularity.
This level of inspection is made from within touching distance unless otherwise
specified. A mirror may be necessary to enhance visual access to all exposed surfaces
in the inspection area. This level of inspection is made under normally available
lighting conditions such as daylight, hanger lighting, flashlight or drop-light and may
require removal or opening of access panels or doors. Stands, ladders or platforms
may be required to gain proximity to the area being checked.
21. Refer to wiring diagram manual for applicable wiring diagrams as follows:
Wire DiagramLocation
28-22-01Tank 1
28-22-02Tank 2
28-22-03Tank 3
28-22-04Aux Tank
28-43-01KC-10 Tip
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22. For test tool information, refer to Hydro-Aire Service Information Letter 60-847-3-1.
Test tool is a pump with electrical connector wire leads cut and connector isolated
from internal windings. Alternate pump test tool is provided. This is for safety in the
vapor area.
23. Refer to Nondestructive Testing Standard Practices Manual (NDTSPM), Part 09 for
visual inspection information.
B. WORK INSTRUCTIONS
Group 1:
1. Make sure circuit breakers are open as follows:
a. Open the fuel pump power circuit breakers and install safety tags. Refer to DC-10 AMM
28-22-01 as an accepted procedure.
b. Make sure the following Remote Control Circuit Breaker (RCCB) indicators, if applicable, are
green/open. If any RCCB indicators are not green/open, take appropriate maintenance actions
to make sure the RCCB indicators are green/open.
LocationCircuit BreakerRCCB
EPC Bay 2Tank 1 TransB1-672
EPC Bay 3Tank 1 AftB1-673
EPC Bay 1Tank 1 FwdB1-674
EPC Bay 2Tank 2 R AftB1-675
EPC Bay 1Tank 2 FwdB1-676
EPC Bay 3Tank 3 FwdB1-677
EPC Bay 1Tank 3 TransB1-678
EPC Bay 3Tank 2 TransB1-682
EPC Bay 2Tank 3 AftB1-679
EPC Bay 1R Upper Aux TankB1-1258
EPC Bay 2L Upper Aux TankB1-1260
Electrical Power Pan-
el
Tank 2 L AftB1-1572
2. Get access to the work area. Refer to DC-10 AMM 28-22-01 for access doors.
3. Remove/keep fuel pumps from fuel pump housings. Refer to DC-10 AMM 28-22-01 as an accepted
procedure.
4. Do OPTION 1 (Replace Fuel Pump Housing Electrical Connector) or OPTION 2 (Replace Fuel
Pump Housing - Tank Entry Required) as follows:
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OPTION 1 (Replace Fuel Pump Housing Electrical Connector)
a. Identify the fuel pump housing protective cap type, refer to FIGURE 1 as an accepted
procedure. Do CONDITION 1 or CONDITION 2 based on protective cap type:
CONDITION 1 (Spring Mounted Protective Cap - Tank Entry Not Required)
(1) Make alignment pins to assist in installation of fuel pump housing electrical connectors.
Refer to FIGURE 2 as an accepted procedure.
(2) RC - Change Fuel Pump Housing Electrical Connectors in accordance with the following
table:
Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 3 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 17 - Route and Clip Wires
FIGURE 28 - Terminate Wires
S3-369M1-6Left Wing Rear Spar
S3-370M1-7
S3-372M1-10
FIGURE 4 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 18 - Route and Clip Wires
FIGURE 29 - Terminate Wires
S3-368M1-5Left Wing Forward Spar
S3-371M1-8
FIGURE 5 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 19 - Route and Clip Wires
FIGURE 30 - Terminate Wires
S3-374M1-9Right Wing Forward Spar
S3-377M1-12
FIGURE 6 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 20 - Route and Clip Wires
FIGURE 31 - Terminate Wires
S3-373M1-11Right Wing Rear Spar
S3-375M1-13
S3-376M1-14
FIGURE 7 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 21 - Route and Clip Wires
FIGURE 32 - Terminate Wires
S3-802M1-91Center Wing Rear Spar -
Upper Auxiliary Tank S3-803M1-92
CONDITION 2 (No Spring Mounted Protective Cap - Tank Entry Required)
(1) Prepare fuel tank for entry, refer to DC-10 AMM 28-00-00 as an accepted procedure.
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(2) RC - Change Fuel Pump Housing Electrical Connectors in accordance with the following
table:
Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 3 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 17 - Route and Clip Wires
FIGURE 28 - Terminate Wires
S3-369M1-6Left Wing Rear Spar
S3-370M1-7
S3-372M1-10
FIGURE 4 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 18 - Route and Clip Wires
FIGURE 29 - Terminate Wires
S3-368M1-5Left Wing Forward Spar
S3-371M1-8
FIGURE 5 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 19 - Route and Clip Wires
FIGURE 30 - Terminate Wires
S3-374M1-9Right Wing Forward Spar
S3-377M1-12
FIGURE 6 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 20 - Route and Clip Wires
FIGURE 31 - Terminate Wires
S3-373M1-11Right Wing Rear Spar
S3-375M1-13
S3-376M1-14
FIGURE 7 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 21 - Route and Clip Wires
FIGURE 32 - Terminate Wires
S3-802M1-91Center Wing Rear Spar -
Upper Auxiliary Tank S3-803M1-92
OPTION 2 (Replace Fuel Pump Housing - Tank Entry Required)
a. Prepare fuel tank for entry. Refer to DC-10 AMM 28-00-00 as an accepted procedure.
b. RC - Change Fuel Pump Housing in accordance with the following table:
Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 3 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 17 - Route and Clip Wires
FIGURE 28 - Terminate Wires
S3-369M1-6Left Wing Rear Spar
S3-370M1-7
S3-372M1-10
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
DC10-28-264
50 of 207
BOEING SERVICE BULLETIN DC10-28-264

### Page 51

Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 4 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 18 - Route and Clip Wires
FIGURE 29 - Terminate Wires
S3-368M1-5Left Wing Forward Spar
S3-371M1-8
FIGURE 5 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 19 - Route and Clip Wires
FIGURE 30 - Terminate Wires
S3-374M1-9Right Wing Forward Spar
S3-377M1-12
FIGURE 6 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 20 - Route and Clip Wires
FIGURE 31 - Terminate Wires
S3-373M1-11Right Wing Rear Spar
S3-375M1-13
S3-376M1-14
FIGURE 7 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 21 - Route and Clip Wires
FIGURE 32 - Terminate Wires
S3-802M1-91Center Wing Rear Spar -
Upper Auxiliary Tank S3-803M1-92
5. Install kept fuel pumps in fuel pump housings and do operational test of fuel pumps (AC Pumping
Units). Refer to DC-10 AMM 28-22-00 as an accepted procedure.
6. Close access. Refer to DC-10 AMM 28-22-01 for access doors.
7. Put the airplane back to a serviceable condition.
Group 2:
1. MD-10 only: Put Fuel System Controller (FSC) in manual mode and make sure all pumps are off.
2. Make sure circuit breakers are open as follows:
a. Open the fuel pump power circuit breakers and install safety tags. Refer to DC-10, MD-10
AMM 28-22-01 as an accepted procedure.
b. Make sure the following Remote Control Circuit Breaker (RCCB) indicators, if applicable, are
green/open. If any RCCB indicators are not green/open, take appropriate maintenance actions
to make sure the RCCB indicators are green/open.
LocationCircuit BreakerRCCB
EPC Bay 2Tank 1 TransB1-672
EPC Bay 3Tank 1 AftB1-673
EPC Bay 1Tank 1 FwdB1-674
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
DC10-28-264
51 of 207
BOEING SERVICE BULLETIN DC10-28-264

### Page 52

LocationCircuit BreakerRCCB
EPC Bay 2Tank 2 R AftB1-675
EPC Bay 1Tank 2 FwdB1-676
EPC Bay 3Tank 3 FwdB1-677
EPC Bay 1Tank 3 TransB1-678
EPC Bay 3Tank 2 TransB1-682
EPC Bay 2Tank 3 AftB1-679
EPC Bay 1R Upper Aux TankB1-1258
EPC Bay 3R Lower Aux TankB1-1259
EPC Bay 2L Upper Aux TankB1-1260
EPC Bay 2L Lower Aux TankB1-1261
Electrical Power Pan-
el
Tank 2 L AftB1-1572
3. Get access to the work area. Refer to DC-10, MD-10 AMM 28-22-01 for access doors.
4. Remove/keep fuel pumps from fuel pump housings. Refer to DC-10, MD-10 AMM 28-22-01 as an
accepted procedure.
5. Do OPTION 1 (Replace Fuel Pump Housing Electrical Connector) or OPTION 2 (Replace Fuel
Pump Housing - Tank Entry Required) as follows:
OPTION 1 (Replace Fuel Pump Housing Electrical Connector)
a. Identify the fuel pump housing protective cap type, refer to FIGURE 1 as an accepted
procedure. Do CONDITION 1 or CONDITION 2 based on protective cap type:
CONDITION 1 (Spring Mounted Protective Cap - Tank Entry Not Required)
(1) Make alignment pins to assist in installation of fuel pump housing electrical connectors.
Refer to FIGURE 2 as an accepted procedure.
(2) RC - Change Fuel Pump Housing Electrical Connectors in accordance with the following
table:
Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 3 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 17 - Route and Clip Wires
FIGURE 28 - Terminate Wires
S3-369M1-6Left Wing Rear Spar
S3-370M1-7
S3-372M1-10
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
DC10-28-264
52 of 207
BOEING SERVICE BULLETIN DC10-28-264

### Page 53

Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 4 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 18 - Route and Clip Wires
FIGURE 29 - Terminate Wires
S3-368M1-5Left Wing Forward Spar
S3-371M1-8
FIGURE 5 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 19 - Route and Clip Wires
FIGURE 30 - Terminate Wires
S3-374M1-9Right Wing Forward Spar
S3-377M1-12
FIGURE 6 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 20 - Route and Clip Wires
FIGURE 31 - Terminate Wires
S3-373M1-11Right Wing Rear Spar
S3-375M1-13
S3-376M1-14
FIGURE 7 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 21 - Route and Clip Wires
FIGURE 32 - Terminate Wires
S3-802M1-91Center Wing Rear Spar -
Upper Auxiliary Tank S3-803M1-92
FIGURE 8 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 22 - Route and Clip Wires
FIGURE 33 - Terminate Wires
S3-804M1-93Center Wing Rear Spar -
Lower Auxiliary Tank S3-805M1-94
CONDITION 2 (No Spring Mounted Protective Cap - Tank Entry Required)
(1) Prepare fuel tank for entry, refer to DC-10, MD-10 AMM 28-00-00 as an accepted
procedure.
(2) RC - Change Fuel Pump Housing Electrical Connectors in accordance with the following
table:
Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 3 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 17 - Route and Clip Wires
FIGURE 28 - Terminate Wires
S3-369M1-6Left Wing Rear Spar
S3-370M1-7
S3-372M1-10
FIGURE 4 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 18 - Route and Clip Wires
FIGURE 29 - Terminate Wires
S3-368M1-5Left Wing Forward Spar
S3-371M1-8
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
DC10-28-264
53 of 207
BOEING SERVICE BULLETIN DC10-28-264

### Page 54

Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 5 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 19 - Route and Clip Wires
FIGURE 30 - Terminate Wires
S3-374M1-9Right Wing Forward Spar
S3-377M1-12
FIGURE 6 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 20 - Route and Clip Wires
FIGURE 31 - Terminate Wires
S3-373M1-11Right Wing Rear Spar
S3-375M1-13
S3-376M1-14
FIGURE 7 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 21 - Route and Clip Wires
FIGURE 32 - Terminate Wires
S3-802M1-91Center Wing Rear Spar -
Upper Auxiliary Tank S3-803M1-92
FIGURE 8 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 22 - Route and Clip Wires
FIGURE 33 - Terminate Wires
S3-804M1-93Center Wing Rear Spar -
Lower Auxiliary Tank S3-805M1-94
OPTION 2 (Replace Fuel Pump Housing - Tank Entry Required)
a. Prepare fuel tank for entry. Refer to DC-10, MD-10 AMM 28-00-00 as an accepted procedure.
b. RC - Change Fuel Pump Housing in accordance with the following table:
Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 3 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 17 - Route and Clip Wires
FIGURE 28 - Terminate Wires
S3-369M1-6Left Wing Rear Spar
S3-370M1-7
S3-372M1-10
FIGURE 4 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 18 - Route and Clip Wires
FIGURE 29 - Terminate Wires
S3-368M1-5Left Wing Forward Spar
S3-371M1-8
FIGURE 5 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 19 - Route and Clip Wires
FIGURE 30 - Terminate Wires
S3-374M1-9Right Wing Forward Spar
S3-377M1-12
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
DC10-28-264
54 of 207
BOEING SERVICE BULLETIN DC10-28-264

### Page 55

Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 6 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 20 - Route and Clip Wires
FIGURE 31 - Terminate Wires
S3-373M1-11Right Wing Rear Spar
S3-375M1-13
S3-376M1-14
FIGURE 7 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 21 - Route and Clip Wires
FIGURE 32 - Terminate Wires
S3-802M1-91Center Wing Rear Spar -
Upper Auxiliary Tank S3-803M1-92
FIGURE 8 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 22 - Route and Clip Wires
FIGURE 33 - Terminate Wires
S3-804M1-93Center Wing Rear Spar -
Lower Auxiliary Tank S3-805M1-94
6. Install kept fuel pumps in fuel pump housings and do operational test of fuel pumps (AC Pumping
Units). Refer to DC-10, MD-10 AMM 28-22-00 as an accepted procedure.
7. Close access. Refer to DC-10, MD-10 AMM 28-22-01 for access doors.
8. Put the airplane back to a serviceable condition.
Group 3:
1. Make sure circuit breakers are open as follows:
a. Open the fuel pump power circuit breakers and install safety tags. Refer to DC-10 AMM
28-22-01 as an accepted procedure.
b. Make sure the following Remote Control Circuit Breaker (RCCB) indicators, if applicable, are
green/open. If any RCCB indicators are not green/open, take appropriate maintenance actions
to make sure the RCCB indicators are green/open.
LocationCircuit BreakerRCCB
EPC Bay 2Tank 1 TransB1-672
EPC Bay 3Tank 1 AftB1-673
EPC Bay 1Tank 1 FwdB1-674
EPC Bay 2Tank 2 R AftB1-675
EPC Bay 1Tank 2 FwdB1-676
EPC Bay 3Tank 3 FwdB1-677
EPC Bay 1Tank 3 TransB1-678
EPC Bay 3Tank 2 TransB1-682
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
DC10-28-264
55 of 207
BOEING SERVICE BULLETIN DC10-28-264

### Page 56

LocationCircuit BreakerRCCB
EPC Bay 2Tank 3 AftB1-679
EPC Bay 1R Upper Aux TankB1-1258
EPC Bay 3R Lower Aux TankB1-1259
EPC Bay 2L Upper Aux TankB1-1260
EPC Bay 2L Lower Aux TankB1-1261
Electrical Power Pan-
el
Tank 2 L AftB1-1572
EPC Bay 3R Aft Aux TankB1-1648
EPC Bay 1L Aft Aux TankB1-1649
2. Get access to the work area. Refer to DC-10 AMM 28-22-01 for access doors.
3. Remove/keep fuel pumps from fuel housings. Refer to DC-10 AMM 28-22-01 as an accepted
procedure.
4. Do OPTION 1 (Replace Fuel Pump Housing Electrical Connector) or OPTION 2 (Replace Fuel
Pump Housing - Tank Entry Required) as follows:
OPTION 1 (Replace Fuel Pump Housing Electrical Connector)
a. Identify the fuel pump housing protective cap type, refer to FIGURE 1 as an accepted
procedure. Do CONDITION 1 or CONDITION 2 based on protective cap type:
CONDITION 1 (Spring Mounted Protective Cap - Tank Entry Not Required)
(1) Make alignment pins to assist in installation of fuel pump housing electrical connectors.
Refer to FIGURE 2 as an accepted procedure.
(2) RC - Change Fuel Pump Housing Electrical Connectors in accordance with the following
table:
Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 3 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 17 - Route and Clip Wires
FIGURE 28 - Terminate Wires
S3-369M1-6Left Wing Rear Spar
S3-370M1-7
S3-372M1-10
FIGURE 4 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 18 - Route and Clip Wires
FIGURE 29 - Terminate Wires
S3-368M1-5Left Wing Forward Spar
S3-371M1-8
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
DC10-28-264
56 of 207
BOEING SERVICE BULLETIN DC10-28-264

### Page 57

Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 5 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 19 - Route and Clip Wires
FIGURE 30 - Terminate Wires
S3-374M1-9Right Wing Forward Spar
S3-377M1-12
FIGURE 6 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 20 - Route and Clip Wires
FIGURE 31 - Terminate Wires
S3-373M1-11Right Wing Rear Spar
S3-375M1-13
S3-376M1-14
FIGURE 7 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 21 - Route and Clip Wires
FIGURE 32 - Terminate Wires
S3-802M1-91Center Wing Rear Spar -
Upper Auxiliary Tank S3-803M1-92
FIGURE 8 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 22 - Route and Clip Wires
FIGURE 33 - Terminate Wires
S3-804M1-93Center Wing Rear Spar -
Lower Auxiliary Tank S3-805M1-94
FIGURE 9 - Disconnect Wires
FIGURE 14 - Change Connector
FIGURE 23 - Route and Clip Wires
FIGURE 34 - Terminate Wires
-M1-168Aft Auxiliary Tank
-M1-169
CONDITION 2 (No Spring Mounted Protective Cap - Tank Entry Required)
(1) Prepare fuel tank for entry, refer to DC-10 AMM 28-00-00 as an accepted procedure.
(2) RC - Change Fuel Pump Housing Electrical Connectors in accordance with the following
table:
Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 3 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 17 - Route and Clip Wires
FIGURE 28 - Terminate Wires
S3-369M1-6Left Wing Rear Spar
S3-370M1-7
S3-372M1-10
FIGURE 4 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 18 - Route and Clip Wires
FIGURE 29 - Terminate Wires
S3-368M1-5Left Wing Forward Spar
S3-371M1-8
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
DC10-28-264
57 of 207
BOEING SERVICE BULLETIN DC10-28-264

### Page 58

Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 5 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 19 - Route and Clip Wires
FIGURE 30 - Terminate Wires
S3-374M1-9Right Wing Forward Spar
S3-377M1-12
FIGURE 6 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 20 - Route and Clip Wires
FIGURE 31 - Terminate Wires
S3-373M1-11Right Wing Rear Spar
S3-375M1-13
S3-376M1-14
FIGURE 7 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 21 - Route and Clip Wires
FIGURE 32 - Terminate Wires
S3-802M1-91Center Wing Rear Spar -
Upper Auxiliary Tank S3-803M1-92
FIGURE 8 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 22 - Route and Clip Wires
FIGURE 33 - Terminate Wires
S3-804M1-93Center Wing Rear Spar -
Lower Auxiliary Tank S3-805M1-94
FIGURE 9 - Disconnect Wires
FIGURE 15 - Change Connector
FIGURE 23 - Route and Clip Wires
FIGURE 34 - Terminate Wires
-M1-168Aft Auxiliary Tank
-M1-169
OPTION 2 (Replace Fuel Pump Housing - Tank Entry Required)
a. Prepare fuel tank for entry. Refer to DC-10 AMM 28-00-00 as an accepted procedure.
b. RC - Change Fuel Pump Housing in accordance with the following table:
Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 3 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 17 - Route and Clip Wires
FIGURE 28 - Terminate Wires
S3-369M1-6Left Wing Rear Spar
S3-370M1-7
S3-372M1-10
FIGURE 4 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 18 - Route and Clip Wires
FIGURE 29 - Terminate Wires
S3-368M1-5Left Wing Forward Spar
S3-371M1-8
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
DC10-28-264
58 of 207
BOEING SERVICE BULLETIN DC10-28-264

### Page 59

Figure(s)/DescriptionTerm
Strip
Fuel
Pump
Location
FIGURE 5 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 19 - Route and Clip Wires
FIGURE 30 - Terminate Wires
S3-374M1-9Right Wing Forward Spar
S3-377M1-12
FIGURE 6 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 20 - Route and Clip Wires
FIGURE 31 - Terminate Wires
S3-373M1-11Right Wing Rear Spar
S3-375M1-13
S3-376M1-14
FIGURE 7 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 21 - Route and Clip Wires
FIGURE 32 - Terminate Wires
S3-802M1-91Center Wing Rear Spar -
Upper Auxiliary Tank S3-803M1-92
FIGURE 8 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 22 - Route and Clip Wires
FIGURE 33 - Terminate Wires
S3-804M1-93Center Wing Rear Spar -
Lower Auxiliary Tank S3-805M1-94
FIGURE 9 - Disconnect Wires
FIGURE 16 - Change Housing
FIGURE 23 - Route and Clip Wires
FIGURE 34 - Terminate Wires
-M1-168Aft Auxiliary Tank
-M1-169
5. Install kept fuel pumps in fuel pump housings and do operational test of fuel pumps (AC Pumping
Units). Refer to DC-10 AMM 28-22-00 as an accepted procedure.
6. Close access. Refer to DC-10 AMM 28-22-01 for access doors.
7. Put the airplane back to a serviceable condition.
Group 4:
1. Make sure circuit breakers are open as follows:
a. Open the fuel pump power circuit breakers and install safety tags. Refer to DC-10 AMM
28-22-01 as an accepted procedure.
b. Make sure the following Remote Control Circuit Breaker (RCCB) indicators, if applicable, are
green/open. If any RCCB indicators are not green/open, take appropriate maintenance actions
to make sure the RCCB indicators are green/open.
LocationCircuit BreakerRCCB
EPC Bay 2Tank 1 TransB1-672
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
DC10-28-264
59 of 207
BOEING SERVICE BULLETIN DC10-28-264

### Page 60

LocationCircuit BreakerRCCB
EPC Bay 3Tank 1 AftB1-673
EPC Bay 1Tank 1 FwdB1-674
EPC Bay 2Tank 2 R AftB1-675
EPC Bay 1Tank 2 FwdB1-676
EPC Bay 3Tank 3 FwdB1-677
EPC Bay 1Tank 3 TransB1-678
EPC Bay 3Tank 2 TransB1-682
EPC Bay 2Tank 3 AftB1-679
EPC Bay 1R Upper Aux TankB1-1258
EPC Bay 3R Lower Aux TankB1-1259
EPC Bay 2L Upper Aux TankB1-1260
EPC Bay 2L Lower Aux TankB1-1261
Electrical Power Pan-
el
Tank 2 L AftB1-1572
EPC Bay 1Fwd FusB1-1873
EPC Bay 3Aft FusB1-1874
EPC Bay 3Tank 3 TipB1-1875
EPC Bay 2Tank 1 TipB1-1876
2. Get access to the work area. Refer to DC-10 AMM 28-22-01 for access doors.
3. Remove/keep fuel pumps from fuel pump housings. Refer to DC-10 AMM 28-22-01 as an accepted
procedure.
4. Do OPTION 1 (Replace Fuel Pump Housing Electrical Connector) or OPTION 2 (Replace Fuel
Pump Housing - Tank Entry Required) as follows:
OPTION 1 (Replace Fuel Pump Housing Electrical Connector)
a. Identify the fuel pump housing protective cap type, refer to FIGURE 1 as an accepted
procedure. Do CONDITION 1 or CONDITION 2 based on protective cap type:
CONDITION 1 (Spring Mounted Protective Cap - Tank Entry Not Required)
(1) Make alignment pins to assist in installation of fuel pump housing electrical connectors.
Refer to FIGURE 2 as an accepted procedure.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
DC10-28-264
60 of 207
BOEING SERVICE BULLETIN DC10-28-264

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