# Boeing Alert Service Bulletin DC10-28A261: No revision named

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- Document: [Boeing Alert Service Bulletin DC10-28A261](https://openairdocs.org/service-documents/boeing/dc10-28a261.md)
- Title as filed: U.S. DOT/FAA - Boeing Service Bulletin (3)
- Pages: 55
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### Page 1

McDonnell DouglasCommercial 
Airplanes
DC10
Service Bulletin
ALERT
Number: DC10-28A261
Original Issue: December 01, 2009
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and
Fuel Boost/Transfer Pump - Inspection/Replacement
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). 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 © 2009 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery 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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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 7
A. Effectivity ................................................ 7
1. Airplanes ............................................. 7
2. Spares Affected ........................................ 1 3
B. Concurrent Requirements ...................................... 1 3
C. Reason ................................................ 1 3
D. Description .............................................. 1 3
E. Compliance .............................................. 1 4
F. Approval ............................................... 1 8
G. Manpower .............................................. 1 8
H. Weight and Balance Changes .................................... 2 0
I. Electrical Load Data ......................................... 2 0
J. References .............................................. 2 0
1. Existing Data .......................................... 2 0
2. Data supplied with this Service Bulletin ............................ 2 1
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 2 1
K. Publications Affected ........................................ 2 1
L. Interchangeability and Intermixability of Parts ........................... 2 2
2. MATERIAL INFORMATION ........................................ 2 3
A. Material - Price and Availability ................................... 2 3
B. Industry Support Information .................................... 2 3
C. Parts Necessary For Each Airplane ................................. 2 3
1. Kits/Parts ............................................ 2 3
2. Parts and Materials Supplied by the Operator ........................ 2 9
3. Parts Modified and Reidentified ................................ 3 0
4. Parts Removed and Not Replaced .............................. 3 1
D. Parts Necessary to Change Spares ................................. 3 1
E. Special Tooling - Price and Availability ............................... 3 1
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 1
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 3
A. GENERAL INFORMATION ..................................... 3 3
B. WORK INSTRUCTIONS ....................................... 3 5
APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1 . . 44
APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N
60-84351 ............................................ 4 7
APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351 . . . 50
APPENDIX D: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER
60-84355-1 INSPECTION LOGIC DIAGRAM ......................... 5 4
APPENDIX E: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER
60-84351 INSPECTION LOGIC DIAGRAM .......................... 5 5
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McDonnell DouglasCommercial 
Airplanes
DC10
Service Bulletin
ALERT
SummaryNumber: DC10-28A261Original Issue: December 01, 2009
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and
Fuel Boost/Transfer Pump - Inspection/Replacement
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
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 assembly, part
number 60-84355-1, failures. Inspecting the fuel boost/transfer pump housing electrical connector assembly,
fuel boost/transfer pump and replacing any non-serviceable part with a serviceable part as required based on
inspection results, will minimize the possibility of a potential ignition source in the fuel tanks and potential fuel
tank explosion. If not corrected, insulation resistance degradation and/or arcing in the potted backside of the
fuel boost/transfer pump housing electrical connector assembly could compromise the performance of the fuel
boost/transfer pump housing electrical connector assembly and result in a failure that can introduce an ignition
source into the fuel tank and potential fuel tank explosion.
ACTION
This service bulletin provides instructions to inspect/replace each fuel pump housing electrical connector assembly
and fuel boost/transfer pump.
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, MD-10-10F and MD-10-30F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected
airplanes.
COMPLIANCE
Refer to Paragraph 1.E., Compliance.
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INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes and repair procedures 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.
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McDonnell DouglasCommercial 
Airplanes
DC10
Service Bulletin
ALERT
Number: DC10-28A261
Original Issue: December 01, 2009
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and
Fuel Boost/Transfer Pump - Inspection/Replacement
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is applicable to airplanes that have installed fuel pump housing electrical
connector assembly part number 60-84355-1 in accordance with Service Bulletin DC10-28A259.
NOTE: The fuel pump housing electrical connector replacement with part number 60-84351 was
done on airplane fuselage number 342 prior to the original issue of this service bulletin
in accordance with Drawing SP10280068 and FAA Alternative Method of Compliance
(AMOC) approval letter with referenced Boeing letter CP-L4L-09-00243.
NOTE: Group 3 airplanes with Aft Aux tank installed must inspect fuel boost/transfer pump
installation per this procedure, unless deactivated per SR10280047 "C" change (or later)
Service Rework Drawing.
NOTE: DC-10-10 Airplanes with auxiliary upper fuel tanks that are modified to MD-10-10F
configuration by Boeing Engineering will become Group 5 airplanes.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes with 1, 2, 3, and Auxiliary Upper Fuel Tanks.-1
Airplanes with 1, 2, 3, Auxiliary Upper and Lower Fuel Tanks.-2
Airplanes with 1, 2, 3, Auxiliary Upper, Lower, and AFT Fuel Tanks.-3
Airplanes with 1, 2, 3, Auxiliary Upper, Lower, FWD, AFT, and Wing
Tip Fuel Tanks.
-4
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DESCRIPTIONCONFIGURATIONGROUP
Airplanes with 1, 2, and 3 Fuel Tanks.-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
2100
2103
2106
2110
5112
2114 - 115
2117
5119
2122 - 123
2127
2129
2131 - 135
2137
5138 - 140
5142
5144 - 145
2146 - 147
5148
515
2150
2152
5153 - 155
2156 - 158
2160
5162
2165 - 166
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GroupFuselage Num-
ber
5169
517
2170 - 171
5173
2174
5177
2178 - 179
2183 - 184
2187 - 190
2192
5194
2195 - 196
5198
2199
12
2201
5203
2204
5205
2206
5207 - 210
2211 - 216
2220 - 221
2223 - 227
2229 - 230
2232
2234 - 236
2239 - 240
2242
2244 - 246
5247
2248
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GroupFuselage Num-
ber
5249
525
5250
1251 - 252
2253 - 257
526
2261 - 268
1269
527
5270 - 271
1272
5273
2274 - 275
2277
2281 - 282
1285
2286
2289 - 291
3292
5294
5296 - 298
2299 - 306
5307
2308
5309
2310
4311
2312 - 317
1318
5319
532
5321
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GroupFuselage Num-
ber
5323
2324 - 327
2329
533
2330
2332
4333
2334 - 338
534
2340
3341
2342 - 343
5344
3345
1346
5347
2349
535
5351
5353
2355 - 356
5358
4359 - 361
4363
2366 - 367
1372
4373
4375 - 378
5379
4380
2381
4383 - 389
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GroupFuselage Num-
ber
539
4390 - 399
540
4400 - 408
2409
541
4410 - 411
2412
4413 - 415
2416
4417 - 418
2419
542
4420 - 421
2422
4423 - 429
543
4430 - 432
2433
3434 - 438
4439
2440
4441
2442 - 446
555
559
56
561 - 62
165
570
172
576
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GroupFuselage Num-
ber
578
58
183
586
589
290
296
299
2. Spares Affected
Examine your spares supply for the parts or components identified in below. For the recommended
use Paragraph 2.D., Parts Necessary to Change Spares. If any parts or components are found.
NamePart Number
Pump Housing60-843-3
Pump Housing60-845-3
Connector60-84355-1
B. Concurrent Requirements
None.
C. Reason
MD-11 and DC-10 operators have reported instances of fuel pump housing electrical connector assembly,
part number 60-84355-1, failures. Inspecting the fuel boost/transfer pump housing electrical connector
assembly, fuel boost/transfer pump and replacing any non-serviceable part with a serviceable part as
required based on inspection results, will minimize the possibility of a potential ignition source in the
fuel tanks and potential fuel tank explosion. If not corrected, insulation resistance degradation and/or
arcing in the potted backside of the fuel boost/transfer pump housing electrical connector assembly
could compromise the performance of the fuel boost/transfer pump housing electrical connector assembly
and result in a failure that can introduce an ignition source into the fuel tank and potential fuel tank
explosion.
D. Description
This service bulletin provides instructions to inspect/replace each fuel pump housing electrical connector
assembly and fuel boost/transfer pump.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Group 1:
Affected Maintenance Zones
ZoneModel
144, 145, 511, 512, 514, 541, 611, 612, 614, 641DC-10-10, DC-10-10F, DC-10-
15, MD-10-10F
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
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, 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
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Federal Aviation Administration (FAA) Airworthiness Directive FAA AD 2007-15-05 is related to this
service bulletin.
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Refer to Appendix D for a logic diagram of the work instructions.
TABLE 1: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84355-1 AND FUEL
BOOST/TRANSFER PUMP - REPLACEMENT/INSPECTION
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
(a)Within 10 months af-
ter the original issue
date on this service
bulletin.
Replace fuel pump electrical
connector assemblies with P/N
60-84351 and restore in accor-
dance with Accomplishment In-
structions 3.B. Part 2 and Part
5.
All Airplanes.
OR
Within 10 months af-
ter the original issue
date on this service
bulletin.
Do continuity, resistance and
insulation resistance inspection
in accordance with Accomplish-
ment Instructions 3.B. Part 3.
AND
Replace fuel pump electrical
connector assemblies with P/N
60-84351 and restore in accor-
dance with Accomplishment In-
structions 3.B. Part 2 and Part
5.
(a)Within 12 months af-
ter inspection.
Before further flight.Do restoration in accordance
with Accomplishment Instruc-
tions 3.B. Part 5.
(Serviceable Fuel pump and hous-
ing electrical connector assembly)
Fuel pump housing electrical con-
nector assembly wiring resistance
reading is less than or equal to 2.5
ohms and terminal E is open.
AND
Fuel boost/transfer pump resistance
reading is less than or equal to 2.5
ohms and pin E is open.
AND
Fuel pump housing electrical con-
nector assembly wiring insulation
resistance reading is greater than
or equal to 10 gigaohm.
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TABLE 1: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84355-1 AND FUEL
BOOST/TRANSFER PUMP - REPLACEMENT/INSPECTION
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
Before further flight.Replace fuel boost/transfer
pump and restore in accordance
with Accomplishment Instruc-
tions 3.B. Part 3 and Part 5.
(Defective Fuel boost/transfer
pump)
Fuel boost/transfer pump resistance
reading is greater than 2.5 ohms or
pin E is not open and fuel pump
housing electrical connector assem-
bly wiring resistance reading is less
than or equal to 2.5 ohms and ter-
minal E is open and fuel pump
housing electrical connector assem-
bly wiring insulation resistance
reading is greater than or equal to
10 gigaohm.
(a)Before further flight.Replace fuel pump electrical
connector assemblies with P/N
60-84351 and restore in accor-
dance with Accomplishment In-
structions 3.B. Part 2 and Part
5.
(Defective Fuel pump housing
electrical connector assembly)
Fuel pump housing electrical con-
nector assembly wiring resistance
reading is greater than 2.5 ohms or
terminal E is not open and fuel
boost/transfer pump resistance
reading is less than or equal to 2.5
ohms and pin E is open.
OR
Fuel pump housing electrical con-
nector assembly wiring insulation
resistance reading is less than 10
gigaohm.
(a) REFER TO TABLE 2 AFTER REPLACEMENT OF FUEL PUMP HOUSING ELECTRICAL CONNECTOR
ASSEMBLY P/N 60-84355-1 WITH P/N 60-84351.
TABLE 2: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84351 AND FUEL
BOOST/TRANSFER PUMP - INSPECTION
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
18 MonthsWithin 18 months af-
ter P/N 60-84351 in-
stallation.
Do continuity, resistance and
insulation resistance inspection
in accordance with Accomplish-
ment Instructions 3.B. Part 4.
All Airplanes
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TABLE 2: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84351 AND FUEL
BOOST/TRANSFER PUMP - INSPECTION
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
Before further flight.Do restoration in accordance
with Accomplishment Instruc-
tions 3.B. Part 5.
(Serviceable Fuel pump and hous-
ing electrical connector assembly)
Fuel pump housing electrical con-
nector assembly wiring resistance
reading is less than or equal to 2.5
ohms and terminal E is open.
AND
Fuel boost/transfer pump resistance
reading is less than or equal to 2.5
ohms and pin E is open.
AND
Fuel pump housing electrical con-
nector assembly wiring insulation
resistance reading is greater than
or equal to 10 megaohm.
Before further flight.Replace fuel boost/transfer
pump and restore in accordance
with Accomplishment Instruc-
tions 3.B. Part 4 and Part 5.
(Defective Fuel boost/transfer
pump)
Fuel boost/transfer pump resistance
reading is greater than 2.5 ohms or
pin E is not open and fuel pump
housing electrical connector assem-
bly wiring resistance reading is less
than or equal to 2.5 ohms and ter-
minal E is open and fuel pump
housing electrical connector assem-
bly wiring insulation resistance
reading is greater than or equal to
10 megaohm.
Before further flight.Replace fuel pump electrical
connector assemblies with P/N
60-84351 and restore in accor-
dance with Accomplishment In-
structions 3.B. Part 4 and Part
5.
(Defective Fuel pump housing
electrical connector assembly)
Fuel pump housing electrical con-
nector assembly wiring resistance
reading is greater than 2.5 ohms or
terminal E is not open and fuel
boost/transfer pump resistance
reading is less than or equal to 2.5
ohms and pin E is open.
OR
Fuel pump housing electrical con-
nector assembly wiring insulation
resistance reading is less than 10
megaohm.
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F. Approval
For MD-10 models:
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.
For DC-10 models:
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.
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.
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 (k) of FAA AD 2007-15-05. All provisions of FAA AD 2007-15-05 that
are not specifically referenced in the above statement remain fully applicable and must be complied
with.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection 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:
Elapsed HoursTask HoursNumber of PersonsTask
4.08.02Open Access
12.024.02Inspect
*0.05 - 12.00*0.1 - 24.02Change
4.08.02Close Access
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Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
1.02.02Test
*21.05 - 33.00*42.1 - 66.0TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
4.08.02Open Access
14.028.02Inspect
*0.05 - 14.00*0.1 - 28.02Change
4.08.02Close Access
1.532Test
*23.55 - 37.50*47.1 - 75.0TOTAL FOR EACH AIRPLANE
Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
4.08.02Open Access
15.030.02Inspect
*0.05 - 15.00*0.1 - 30.02Change
4.08.02Close Access
1.532Test
*24.55 -.39.50*49.1 - 79.0TOTAL FOR EACH AIRPLANE
Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
4.012.03Open Access
18.036.02Inspection
*0.05 - 22.00*0.1 - 44.02Change
4.012.03Close Access
2.04.02Test
*30.05 - 50.00*68.1 - 108.0TOTAL FOR EACH AIRPLANE
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Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
3.06.02Open Access
10.020.02Inspect
*0.05 - 10.00*0.1 - 20.02Change
3.06.02Close Access
1.02.02Test
*15.05 - 27.00*30.1 - 54.0TOTAL FOR EACH AIRPLANE
*A range of total task hours and elapsed hours are given for inspection per airplane. Actual task hours
and elapsed hours for the change are contingent upon inspection findings and are to be estimated by
the operator.
H. Weight and Balance Changes
Weight and balance changes affected by incorporation of this service bulletin are contingent upon the
changes to each particular airplane. Weight data is to be computed by the operator by weighing parts
removed and parts installed during this change. Necessary revisions should be made to the appropriate
airplane weight and balance report.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Boeing Service Bulletin DC10-28A229 and DC10-28A259.
b. Boeing Service Rework Drawing SR10280047.
c. Federal Aviation Administration (FAA) Airworthiness Directive 2007-15-05.
d. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-13, 20-00-16,
20-10-01,20-10-04, 20-20-01, 20-20-02, 20-20-03, 20-31-00, and 20-50-01.
e. DC-10, MD-10 Aircraft Maintenance Manual (AMM) 12-11-03, 20-20-06, 28-00-00, 28-22-00
and 28-22-01.
f. DC-10, MD-10 Structural Repair Manual (SRM) 51.
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g. Wiring Diagram Manual (WDM) 28-22-01, 28-22-02, 28-22-03, 28-22-04 and 28-43-01.
h. Crane Hydro-Aire Service Information Letters 60-847-3-1 and 60-843-845-3-28-2.
i. FAA Alternative Method of Compliance (AMOC) approval letter with referenced Boeing letter
CP-L4L-09-00243.
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
MS D800-0019
3855 Lakewood Boulevard
Long Beach, California 90846
Phone: (562) 593-6996
Fax: (562) 593-2001
E-mail: dse.boecom@boeing.com
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
-CDWGELEC INSTL - FUEL PUMP ELECTRICAL
CONNECTOR
SR10280075
3. Installation Drawings Used in the Preparation of this Service Bulletin
None.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
28-22Aircraft Maintenance Manual (DC-10, KC-10,KDC-10, MD-10)
28-14 and 28-22Fault Isolation Manual (FIM) (MD-10)
28-13 and 28-22Illustrated Parts Catalog
28On Aircraft Maintenance Planning (OAMP) (DC-10, MD-10)
28-02Turn Around Fault Isolation Manual (TAFI) (DC-10, KC-10, KDC-10)
28-22 and 28-43Wiring Diagram Manual Equipment List
28-22Wiring Diagram Manual
2. Damage Tolerance Based Structural Inspections:
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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.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
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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 as shown
below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares.
More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the
date Boeing gets the purchase order.
Unit Price thru November 30, 2010ROLT (Weeks)NamePart Number
$267.0013SERVICE KITSR10280075-3
41.0013SERVICE KITSR10280075-5
9.0013SERVICE KITSR10280075-7
1,503.0013SERVICE KITSR10280075-9
1,561.0013SERVICE KITSR10280075-11
372.0013SERVICE KITSR10280075-13
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
After the Unit Price date, new price ROLT data is applicable. Prices are in United States dollars. Terms:
Net 30 days.
Reference this service bulletin and submit your purchase order by one of the methods that follow:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Mail to:
Spares Customer Support - MC 36-65
Boeing Spares Department
P.O. Box 3707
Seattle, Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes and repair procedures 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.
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Group 1:
NotesNameQTYNew Part Number
(a)KIT4SR10280075-3
(a)KIT8SR10280075-5
(a) Total quantity required per airplane.
Group 1:
NotesNameQTYNew Part Number
-5-3SR10280075
NUT GROMMET ASSY1.10-74916-8
COMB.12768771-1
(a)SCREW113D0005-3-12
(a)TERMINAL LUG 765335D0086-25
(a)TERMINAL LUG 766225D0086-26
(a)FERRULE.17D0294-1
(a)PIN.29D0196-1
(a)BUSHING.19D0197-1
GLAND NUT.1M8700-7/3
WASHER33MS35338-137
LOCKWASHER11MS35338-43
NUT33MS35649-284
WASHER33NAS1149CN832R
WASHER11NAS1149F0332P
(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.
Group 2:
NotesNameQTYNew Part Number
(a)KIT4SR10280075-3
(a)KIT8SR10280075-5
(a)KIT2SR10280075-7
(a) Total quantity required per airplane.
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Group 2:
NotesNameQTYNew Part Number
-7-5-3SR10280075
SLEEVE1..10-35916-16
GROMMET1..10-60766-8
NUT GROMMET ASSY.1.10-74916-8
COMB..12768771-1
(a)SCREW1113D0005-3-12
(a)TERMINAL LUG 7653335D0086-25
(a)TERMINAL LUG 7662225D0086-26
(a)FERRULE..17D0294-1
(a)PIN..29D0196-1
(a)BUSHING..19D0197-1
GLAND NUT..1M8700-7/3
WASHER333MS35338-137
LOCKWASHER111MS35338-43
NUT333MS35649-284
WASHER333NAS1149CN832R
WASHER111NAS1149F0332P
(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.
Group 3:
NotesNameQTYNew Part Number
(a)KIT1SR10280075-11
(a)KIT4SR10280075-3
(a)KIT8SR10280075-5
(a)KIT2SR10280075-7
(a)KIT1SR10280075-9
(a) Total quantity required per airplane.
Group 3:
NotesNameQTYNew Part Number
-11-9-7-5-3SR10280075
SLEEVE..1..10-35916-16
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Group 3:
NotesNameQTYNew Part Number
-11-9-7-5-3SR10280075
GROMMET..1..10-60766-8
NUT GROMMET ASSY...1.10-74916-8
COMB11..12768771-1
(a)SCREW111113D0005-3-12
(a)SCREW11...3D0005-3-9
(a)TERMINAL LUG 765..3335D0086-25
(a)TERMINAL LUG 766--2225D0086-26
(a)FERRULE11..17D0294-1
(a)PIN22..29D0196-1
(a)BUSHING11..19D0197-1
PLUG11...ANP0065-513
PLUG11...ANP0065-515
RECEPTACLE1----DC20F14-5P
RECEPTACLE-1---DC20F14-5PW
PIN T/C 70555---LRM16M-32DJ5
GLAND NUT11..1M8700-7/3
SHACKLE11...MS20115-3
NUT11...MS21042L3
WASHER..333MS35338-137
LOCKWASHER11111MS35338-43
NUT..333MS35649-284
WASHER..333NAS1149CN832R
WASHER44...NAS1149DN416H
WASHER11111NAS1149F0332P
SCREW44...NAS1191-04P-6
WASHER22...NAS1252-10L
(b)WIRE KIT1....SR10280075-101
(b)WIRE KIT.1...SR10280075-102
(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.
(b) Refer to Wire Kit Components Table.
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NotesNameWire Kit SR10280075New Part Number
-102-101
(a)TERMINAL LUG T/C 766115D0086-26
(a)WIRE CODE 80121 FT21 FTDC2426-1C-16NM
ELECT DISCONNECT-1KPSE6F14-5S-EL
ELECT DISCONNECT1-KPSE6F14-5SW-EL
SOCKET T/C 70655LRC16M-32DJ5
(a) Or approved Equivalent.
Group 4:
NotesNameQTYNew Part Number
(a)KIT2SR10280075-13
(a)KIT6SR10280075-3
(a)KIT8SR10280075-5
(a)KIT2SR10280075-7
(a) Total quantity required per airplane.
Group 4:
NotesNameQTYNew Part Number
-13-7-5-3SR10280075
SLEEVE.1..10-35916-16
GROMMET.1..10-60766-8
NUT GROMMET ASSY..1.10-74916-8
COMB1..12768771-1
(a)SCREW11113D0005-3-12
(a)TERMINAL LUG 76533335D0086-25
(a)TERMINAL LUG 76622225D0086-26
(a)FERRULE1..17D0294-1
(a)PIN2..29D0196-1
(a)BUSHING1..19D0197-1
GLAND2...AAN7113-517
GLAND NUT1..1M8700-7/3
WASHER3333MS35338-137
LOCKWASHER1111MS35338-43
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Group 4:
NotesNameQTYNew Part Number
-13-7-5-3SR10280075
NUT3333MS35649-284
WASHER3333NAS1149CN832R
WASHER1111NAS1149F0332P
(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.
Group 5:
NotesNameQTYNew Part Number
(a)KIT4SR10280075-3
(a)KIT6SR10280075-5
(a) Total quantity required per airplane.
Group 5:
NotesNameQTYNew Part Number
-5-3SR10280075
NUT GROMMET ASSY1.10-74916-8
COMB.12768771-1
(a)SCREW113D0005-3-12
(a)TERMINAL LUG 765335D0086-25
(a)TERMINAL LUG 766225D0086-26
(a)FERRULE.17D0294-1
(a)PIN.29D0196-1
(a)BUSHING.19D0197-1
GLAND NUT.1M8700-7/3
WASHER33MS35338-137
LOCKWASHER11MS35338-43
NUT33MS35649-284
WASHER33NAS1149CN832R
WASHER11NAS1149F0332P
(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.
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2. Parts and Materials Supplied by the Operator
NOTE: The items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator,
show the total quantity necessary for each airplane unless noted otherwise.
Group 1:
NotesNameQTYPart Number/Specification
(a)CONNECTOR ASSY1260-84351
(a) (b)PUMP ASSY1260-847-X
(a)SCREW48LL500D4-6
Or
ES500D4-6
(a)PACKING12M25988/1-019
CAGEHydro-Aire, Incorporated(a) Can be purchased from:
819823000 Winona Avenue
Burbank, California 91504-2540
(b) Refer to Illustrated Parts Catalog (IPC) for applicable fuel boost/transfer pump configuration.
Group 2:
NotesNameQTYPart Number/Specification
(a)CONNECTOR ASSY1460-84351
(a) (b)PUMP ASSY1460-847-X
(a)SCREW56LL500D4-6
Or
ES500D4-6
(a)PACKING14M25988/1-019
CAGEHydro-Aire, Incorporated(a) Can be purchased from:
819823000 Winona Avenue
Burbank, California 91504-2540
(b) Refer to IPC for applicable fuel boost/transfer pump configuration.
Group 3:
NotesNameQTYPart Number/Specification
(a)CONNECTOR ASSY1660-84351
(a) (b)PUMP ASSY1660-847-X
(a)SCREW64LL500D4-6
Or
ES500D4-6
(a)PACKING16M25988/1-019
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Group 3:
NotesNameQTYPart Number/Specification
LOCKWIRE3 FTDPM684 (NASM20995N20)
Or
DPM5865 (NASM20995C20)
CAGEHydro-Aire, Incorporated(a) Can be purchased from:
819823000 Winona Avenue
Burbank, California 91504-2540
(b) Refer to IPC for applicable fuel boost/transfer pump configuration.
Group 4:
NotesNameQTYPart Number/Specification
(a)CONNECTOR ASSY1860-84351
(a) (b)PUMP ASSY1860-847-X
(a)SCREW72LL500D4-6
Or
ES500D4-6
(a)PACKING18M25988/1-019
CAGEHydro-Aire, Incorporated(a) Can be purchased from:
819823000 Winona Avenue
Burbank, California 91504-2540
(b) Refer to IPC for applicable fuel boost/transfer pump configuration.
Group 5:
NotesNameQTYPart Number/Specification
(a)CONNECTOR ASSY1060-84351
(a) (b)PUMP ASSY1060-847-X
(a)SCREW40LL500D4-6
Or
ES500D4-6
(a)PACKING10M25988/1-019
CAGEHydro-Aire, Incorporated(a) Can be purchased from:
819823000 Winona Avenue
Burbank, California 91504-2540
(b) Refer to IPC for applicable fuel boost/transfer pump configuration.
3. Parts Modified and Reidentified
None.
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4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
To get parts shown below, contact the Crane Spares Department at (818)-526-2500 or FAX to
(818)-526-2658.
NotesNameNew Part Number / Specifica-
tion
(a) (b)CONNECTOR ASSY60-84351
(a) (b)PACKINGM25988/1-019
(a) (b)SCREWLL500D4-6
Or
ES500D4-6
CAGEHydro-Aire, Incorporated(a) Can be purchased from:
819823000 Winona Avenue
Burbank, California 91504-2540 USA
(b) Use applicable quantities to change spare 60-843-3 and 60-845-3 fuel pump housing
assemblies. Replace spare 60-84355-1 with 60-84351 as needed.
E. Special Tooling - Price and Availability
The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this
Service Bulletin. Tool price and supply data are not given.
F. Special Tooling Necessary to do this Service Bulletin
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.
CAGESupplierNameTool / Kit Number
0HYG7Fluke CorporationModel 10Multimeter
1420 75TH Street SouthwestOr
Everett, Washington 98206Equivalent
0PK96Quatech, IncorporatedModel 1864Megohmmeter
5 Clock Tower Place, Suite 210Or
Maynard, Massachusetts 01754Equivalent
* An Equivalent Ohmmeter must be able to apply voltage at 100+/-10 Volts DC and be current limited to
5 Milliamps.
A T67291 or T67291-1 test tool/alternate tool is required to accomplish this inspection. Refer to Crane
Hydro-Aire Service Information Letter 60-847-3-1.
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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.
WARNING: WHILE YOU DO WORK IN THE TAILCONE AREA, MAKE SURE THAT YOU OBEY
ALL SAFETY PRECAUTIONS. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH
OR INJURY TO PERSONS 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 the
installation standards in 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. Not applicable to Crane Hydro-Aire fuel boost/transfer
pump, fuel pump housing or attaching parts.
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.
– Torque limits to tighten nuts and bolts are in SRM, Chapter 51.
7. Refer to these Standard Wiring Practices Manual (SWPM) chapters for applicable
operations, as accepted procedures:
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TitleChapter
IDENTIFICATION OF ELECTRICAL WIRE - COMMER-
CIAL
SWPM 20-00-03
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
FABRICATING AND INSTALLING WIRE HARNESSES
- COMMERCIAL
SWPM 20-10-01
COIL AND STOW - MAINTENANCE PRACTICESSWPM 20-10-04
TERMINALS - MAINTENANCE PRACTICESSWPM 20-20-01
TERMINAL BLOCKS - MAINTENANCE PRACTICESSWPM 20-20-02
GENERAL INSTALLATIONS HARDWARE - MAINTE-
NANCE PRACTICES
SWPM 20-20-03
ELECTRICAL CONNECTORS - MAINTENANCE
PRACTICES
SWPM 20-31-00
ELECTRICAL BONDING - MAINTENANCE PRACTICESSWPM 20-50-01
8. Refer to these Wiring Diagram Manuals (WDM) for applicable operations, as accepted
procedures:
Wiring DiagramLocation
28-22-01Tank 1
28-22-02Tank 2
28-22-03Tank 3
28-22-04Aux Tank *
28-43-01KC-10 Tip
* Including Fwd Fus, Aft Fus, Upper, Lower, and Aft Aux Tanks (If Installed).
9. Obey all of the warnings and cautions given in the specified manual sections.
10. Review and understand all general notes of Service Rework Drawing SR10280075
sheets 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.7.1, 3.8, 3.9, and 7 before start of
modification.
11. Lockwire Safetying - Maintenance Practices. Refer to DC-10, MD-10 AMM 20-20-06
as an accepted procedure.
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12. 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.
13. Any protrusion of threads is acceptable provided that the threads do not rub or ride
against nearby wire assemblies or components.
14. Access panel numbers and locations may vary.
15. Identify and note location of wires prior to removal from terminal strip and/or ground
stud.
16. The inspection order of operation procedures outlined in Parts 3 and 4 of Paragraph
3.B., Work Instructions must be followed. The instructions identified in Paragraph
3.B., Work Instructions give the recommended sequence of steps for which pump
location to inspect. The sequence of steps to inspect the pump locations can be
changed.
B. WORK INSTRUCTIONS
PART 1 (ACCESS/PREPARATION)
WARNING: FUEL TANKS MUST BE FILLED TO SPECIFIED LEVEL OR DRAINED, PURGED, AND
SAFE FOR MAINTENANCE. THIS WILL PREVENT INJURY TO PERSONS AND
DAMAGE TO EQUIPMENT.
1. Make sure fuel tanks are filled to specified level or defuel, purge, and make fuel system safe for
maintenance. Refer to DC-10, MD-10 AMM 12-11-03 and DC-10, MD-10 AMM 28-00-00 as
accepted procedures.
ALL GROUPS:
Minimum Fuel LevelTank
KilogramPounds
9070200001*
10430230002
9070200003*
* Tanks 1 and 3 aft fuel boost/transfer pumps and conduits are located in tank 2. Tank 2 must be filled to
specified level when accomplishing this inspection for tanks 1 and 3 aft fuel boost/transfer pumps.
Group 1-4:
Minimum Fuel LevelTank
KilogramPounds
498011000Upper Aux
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Group 2-4:
Minimum Fuel LevelTank
KilogramPounds
20404500Lower Aux
Group 3:
Minimum Fuel LevelTank
KilogramPounds
18104000Aft Aux (1500 Gallons)
31707000Aft Aux (3200/3317 Gallons)
Group 4:
Minimum Fuel LevelTank
KilogramPounds
34407600Fwd Fuselage
480010600Aft Fuselage
2. Make fuel boost/transfer pumps electrical system safe as follows:
a. MD-10 only - Place fuel system controller (FSC) in manual mode and verify all fuel
boost/transfer pumps are off. Refer to MD-10 AMM 28-00-00 as an accepted procedure.
b. DC-10 - Make sure all fuel boost/transfer pumps are off. Refer to DC10 AMM 28-22-01.
3. Gain access to inspection areas. Refer to DC-10, MD-10 AMM 28-22-01 as an accepted procedure.
4. Open/verify circuit breakers as follows:
a. Open fuel boost/transfer pump power circuit breakers. Refer to DC-10, MD-10 AMM 28-22-01
as an accepted procedure.
b. Make sure Remote Control Circuit Breaker (RCCB) indicators are green/open.
ALL GROUPS:
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
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ALL GROUPS:
LocationCircuit BreakerRCCB
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
Electrical Power PanelTank 2 L AftB1-1572
Group 1-4:
LocationCircuit BreakerRCCB
EPC Bay 1R Upper Aux TankB1-1258
EPC Bay 2L Upper Aux TankB1-1260
Group 2-4:
LocationCircuit BreakerRCCB
EPC Bay 3R Lower Aux TankB1-1259
EPC Bay 2L Lower Aux TankB1-1261
Group 3:
LocationCircuit BreakerRCCB
EPC Bay 3R Aft Aux TankB1-1648
EPC Bay 1L Aft Aux TankB1-1649
Group 4:
LocationCircuit BreakerRCCB
EPC Bay 1Fwd FusB1-1873
EPC Bay 3Aft FusB1-1874
EPC Bay 3Tank 3 TipB1-1875
EPC Bay 2Tank 1 TipB1-1876
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PART 2 (FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY - REPLACEMENT)
1. Replace existing 60-84355-1 fuel pump housing electrical connector assembly in accordance with
Appendix B.
2. Proceed to Part 5 (Restoration).
PART 3 (FUEL BOOST/TRANSFER PUMP AND PUMP HOUSING ELECTRICAL CONNECTOR
ASSEMBLY PART NUMBER 60-84355-1 INSPECTION)
1. Using a digital multimeter, check electrical continuity and resistance from terminal strip through
fuel boost/transfer pump as follows:
a. Disconnect fuel boost/transfer pump wires from terminal strip/ground stud (or disconnect
connectors) and check disconnected wires terminal to terminal in accordance with Appendix
A, Table below and refer to DC-10, MD-10 AMM 28-22-01 as an accepted procedure:
NOTE: Fuel boost/transfer pump wiring resistance should be less than or equal to 2.5 ohms.
NOTE: Terminal E should read open during multimeter check.
Wiring Resistance Check
ResultsCheckResultsCheck
2-31-2
2-E1-3
3-E1-E
NOTE: If Aft Aux tank is installed, Use Table below:
Wiring Resistance Check ( Aft Aux Tank )
ResultsCheckResultsCheck
B-CA-B
C-EA-C
B-EA-E
b. If fuel boost/transfer pump wiring resistance is greater than 2.5 ohms or terminal E is not open,
remove fuel boost/transfer pump, refer to DC-10, MD-10 AMM 28-22-01 as an accepted
procedure and check pin-to-pin as follows:
NOTE: Fuel boost/transfer pump resistance should be less than or equal to 2.5 ohms.
NOTE: Pin E should read open during multimeter check.
Fuel Boost/Transfer Pump Resistance Check
ResultsCheckResultsCheck
B-CA-B
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Fuel Boost/Transfer Pump Resistance Check
ResultsCheckResultsCheck
B-EA-C
C-EA-E
2. If any fuel boost/transfer pump wiring resistance reading is greater than 2.5 ohms or terminal E is
not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms with
pin E open, replace existing fuel pump housing electrical connector assembly in accordance with
Appendix B.
3. Remove and retain fuel boost/transfer pumps, if not previously removed. Refer to DC-10, MD-10
AMM 28-22-01 as an accepted procedure.
4. Using Quadtech 1864 Megohm meter, do a fuel pump housing electrical connector assembly
insulation resistance check as follows:
a. Install T67291 or T6729-1 test tool/alternate tool.
b. Set Megohm meter at 100+/-10 volts DC and current limit to 5 milliamps. Check insulation
resistance by applying test voltage terminal-to-terminal in accordance with Appendix A, and
Table below:
NOTE: Insulation resistance should be greater or equal to 10 gigaohm.
Insulation Resistance Check
ResultsCheckResultsCheck
2-31-2
2-E1-3
3-E1-E
NOTE: If Aft Aux tank is installed, Use Table below
Insulation Resistance Check
ResultsCheckResultsCheck
B-CA-B
C-EA-C
B-EA-E
c. Remove test pump/alternate tool.
5. If any fuel boost/transfer pump resistance reading is greater than 2.5 ohms or pin E is not open.
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### Page 40

a. Replace fuel boost/transfer pump. Refer to DC-10, MD-10 AMM 28-22-01 as an accepted
procedure.
b. Proceed to Part 5 (Restoration).
6. If any fuel pump housing electrical connector assembly insulation resistance reading is less than
10 gigaohm.
a. Replace existing fuel pump housing electrical connector assembly in accordance with Appendix
B.
b. Proceed to Part 5 (Restoration).
7. Proceed to Part 5 (Restoration) If all continuity, resistance and insulation resistance, results are
as follows:
a. Fuel boost/transfer pump wiring resistance reading is less than or equal to 2.5 ohms and
terminal E is open.
b. Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is
open.
c. Fuel pump housing electrical connector assembly insulation resistance reading is greater than
or equal to 10 gigaohm.
PART 4 (FUEL BOOST/TRANSFER PUMP AND FUEL PUMP HOUSING ELECTRICAL CONNECTOR
ASSEMBLY PART NUMBER 60-84351 INSPECTION)
1. Using a digital multimeter, check electrical continuity and resistance from terminal strip through
fuel boost/transfer pump as follows:
a. Disconnect fuel boost/transfer pump wires from terminal strip/ground stud (or disconnect
connectors) and check disconnected wires electrical terminal to terminal in accordance with
DC-10, MD-10 AMM 28-22-01, Appendix C, and Table below:
NOTE: Fuel boost/transfer pump wiring resistance should be less than or equal to 2.5 ohms.
NOTE: Terminal E should read open during multimeter check.
Wiring Resistance Check
ResultsCheckResultsCheck
2-D1-2
2-E1-3
3-D1-D
3-E1-E
D-E2-3
NOTE: If Aft Aux tank is installed, Use Table below:
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Wiring Resistance Check
ResultsCheckResultsCheck
B-DA-B
B-EA-C
C-DA-D
C-EA-E
D-EB-C
b. If fuel boost/transfer pump wiring resistance is greater than 2.5 ohms or terminal E is not open,
remove fuel boost/transfer pump, refer to DC-10, MD-10 AMM 28-22-01 as an accepted
procedure and check pin-to-pin as follows:
NOTE: Fuel boost/transfer pump resistance should be less than or equal to 2.5 ohms.
NOTE: Pin E should read open during multimeter check.
Fuel Boost/Transfer Pump Resistance Check
ResultsCheckResultsCheck
B-DA-B
B-EA-C
C-DA-D
C-EA-E
D-EB-C
2. If any fuel boost/transfer pump wiring resistance reading is greater than 2.5 ohms or terminal E is
not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms with
pin E open, replace the affected fuel pump housing electrical connector assembly. Refer to DC-10
AMM 28-22-01 Approved Repairs, Wiring Charts entitled "without Service Bulletin DC10-28A229
incorporated" or (MD-10 only) MD-10 AMM 28-22-01 Approved Repairs, "Pre Service Bulletin
DC10-28A229" as accepted procedure.
NOTE: If a spring model protective cap is not installed, fuel tank entry is required. Refer to DC-10,
MD-10 AMM 28-00-00 as an accepted procedure.
3. Remove and retain fuel boost/transfer pumps, if not previously removed. Refer to DC-10, MD-10
AMM 28-22-01 as an accepted procedure.
4. Using Quadtech 1864 Megohm meter, do a fuel pump housing electrical connector assembly
insulation resistance check as follows:
a. Install T67291 or T6729-1 test tool/alternate tool.
b. Set ohm meter at 100+/-10 volts DC and current limit to 5 milliamps. Check insulation resistance
by applying test voltage terminal-to-terminal, in accordance with Appendix C, and Table below:
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NOTE: Insulation resistance should be greater or equal to 10 megaohm.
Insulation Resistance Check
ResultsCheckResultsCheck
2-D1-2
2-E1-3
3-D1-D
3-E1-E
D-E2-3
NOTE: If Aft Aux tank is installed, Use Table below:
Insulation Resistance Check
ResultsCheckResultsCheck
B-DA-B
B-EA-C
C-DA-D
C-EA-E
D-EB-C
c. Remove test pump/alternate tool.
5. If any fuel boost/transfer pump resistance reading is greater than 2.5 ohms or terminal E is not
open.
a. Replace fuel boost/transfer pump. Refer to DC-10, MD-10 AMM 28-22-01 as an accepted
procedure.
b. Proceed to Part 5 (Restoration).
6. If any fuel pump housing electrical connector assembly insulation resistance reading is less than
10 megaohm.
a. Replace the affected fuel pump housing electrical connector assembly. Refer to DC-10 AMM
28-22-01 Approved Repairs, Wiring Charts entitled "without Service Bulletin DC10-28A229
incorporated" or (MD-10 only) MD-10 AMM 28-22-01 Approved Repairs, "Pre Service Bulletin
DC10-28A229" as accepted procedure.
NOTE: If a spring model protective cap is not installed, fuel tank entry is required. Refer to
DC-10, MD-10 AMM 28-00-00 as an accepted procedure.
b. Proceed to Part 5 (Restoration).
7. Proceed to Part 5 (Restoration) If all continuity, resistance and insulation resistance, results are
as follows:
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### Page 43

a. Fuel boost/transfer pump wiring resistance reading is less than or equal to 2.5 ohms and
terminal E is open.
b. Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is
open.
c. Fuel pump housing electrical connector assembly insulation resistance reading is greater than
or equal to 10 megaohm.
PART 5 (RESTORATION)
1. If not already accomplished, connect fuel pump housing electrical connector assemblies to terminal
strip and ground studs. Refer to DC-10, MD-10 AMM 28-22-01 and Appendix A (part number
60-84355-1), or Appendix C (part number 60-84351) as an accepted procedure.
2. Install fuel boost/transfer pumps if not previously installed. Refer to DC-10, MD-10 AMM 28-22-01
as an accepted procedure.
3. Do operational test of fuel boost/transfer pumps and using a digital multimeter check that voltage
between applicable terminal strip post and ground is 104 to 122VAC. Refer to DC-10, MD-10 AMM
28-22-00, Appendix A (part number 60-84355-1), or Appendix C (part number 60-84351) as
accepted procedures.
4. Close access. Refer to DC-10, MD-10 AMM 28-22-01 as an accepted procedure.
5. Put the airplane back to a serviceable condition.
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### Page 44

Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-368
A
R5-11021/Forward -2B -3C
5022AE*
-1
S3-370
A
R5-11001/Transfer -2B -3C
4726AE*
-1
S3-369
A
R5-11011/Aft -2B -3C
4727AE*
-1
S3-371
A
R5-11052/Forward -2B -3C
5009AE*
-1
S3-372
A
R5-11042/Left Aft -2B -3C
4728AE*
-1
S3-374
A
R5-10992/Transfer -2B -3C 6078AE*
-1
S3-373
A
R5-11032/Right Aft -2B -3C
4821AE*
-1
S3-377
A
R5-11063/Forward -2B -3C
6022AE*
-1
S3-376
A
R5-11073/Transfer -2B -3C
4823AE*
-1
S3-375
A
R5-11083/Right Aft -2B -3C
4822AE*
* E should read open during multimeter check.
APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1
(SHEET 1 OF 3)
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### Page 45

GROUP 1-4:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-803
A
R5-1934Center Aux/LeftUpper -2B -3C
4729AE*
-1
S3-802
A
R5-1933Center Aux/RightUpper -2B -3C
4824AE*
* E should read open during multimeter check.
GROUP 2-4:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-805
A
R5-1936Center Aux/LeftLower -2B -3C
4895AE*
-1
S3-804
A
R5-1935Center Aux/RightLower -2B -3C
4894AE*
* E should read open during multimeter check.
GROUP 3:
Ground Stud
ConnectorConnector (Pump)
Tank/Pump
SocketNumberSocketNumber
-3R5-4816AR5-1994Aft Aux/R
-2B
-1C
4866A4E*
-3R5-4815AR5-1995Aft Aux/L
-2B
-1C
4865A4E*
* E should read open during multimeter check.
APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1
(SHEET 2 OF 3)
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### Page 46

GROUP 3:
TerminalRelayTank/Pump
A1R2-89Aft Aux R
B1
C1
A1R2-90Aft Aux L
B1
C1
GROUP 4:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-1072
A
R5-49361/Tip -2B -3C
5088AE*
-1
S3-1071
A
R5-49373/Tip -2B -3C
6088AE*
-8
S3-1109
A
R5-2666Fwd Fuselage -9B -10C
4122AE*
-8
S3-1110
A
R5-2667Aft Fuselage -9B -10C
4848AE*
* E should read open during multimeter check.
APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1
(SHEET 3 OF 3)
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### Page 47

1. Replace the affected fuel pump housing electrical connector assembly in accordance with Table below,
DC-10 AMM 28-22-01 Approved Repairs, Wiring Charts entitled "without Service Bulletin DC10-28A229
incorporated" or (MD-10 only) MD-10 AMM 28-22-01 Approved Repairs, "Pre Service Bulletin DC10-28A229"
as accepted procedure.
NOTE: If a spring model protective cap is not installed, fuel tank entry is required. Refer to DC-10, MD-10
AMM 28-00-00 as an accepted procedure.
ALL GROUPS:
Drawing SR10280075ConnectorIdentificationFuel PumpIdentificationLocationTank
Sheets 3, 3.1, 3.3, 3.5, 3.7, 3.8, 3.9,
4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,
5.4, 6, 6.2, 7, 9.0, 9.7, 10, and 19.
R5-1100M1-7Transfer1
R5-1101M1-6Left Aft
Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,
4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,
5.4, 6, 6.1, 6.2, 7, 9.0, 9.7, 10, and 21.
R5-1102M1-5Forward
Sheets 3, 3.1, 3.3, 3.5, 3.7, 3.8, 3.9,
4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,
5.4, 6, 6.1, 6.2, 7, 9.1, 9.8, 10, and 16.
R5-1103M1-11Right Aft2
Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,
4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3, 5.4, 6,
6.2, 7, 9.1, 9.7, 10, and 17.
R5-1099M1-9Transfer
Sheets 3, 3.1, 3.3, 3.5, 3.7, 3.8, 3.9,
4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,
5.4, 6, 6.1, 6.2, 7, 9.1, 9.7, 10, and 19.
R5-1104M1-10Left Aft
Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,
4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,
5.4, 6, 6.1, 6.2, 7, 9.1, 9.7, 10, and 20.
R5-1105M1-8Forward
APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N
60-84351
(SHEET 1 OF 3)
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### Page 48

ALL GROUPS:
Drawing SR10280075ConnectorIdentificationFuel PumpIdentificationLocationTank
Sheets 3, 3.1, 3.3, 3.7, 3.8, 3.9, 4, 4.1,
4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3, 5.4, 6,
6.1, 6.2, 7, 9.2, 9.8, 10, and 18.
R5-1106M1-12Forward3
Sheets 3, 3.1, 3.3, 3.5, 3.7, 3.8, 3.9,
4, 4.1, 4.2, 4.3, 4.4, 5, 5.1, 5.2, 5.3,
5.4, 6, 6.1, 6.2, 7, 9.2, 9.8, 9.9, 10,
and 16.
R5-1107M1-14Transfer
R5-1108M1-13Right Aft
GROUP 1-4:
Drawing SR10280075ConnectorIdentificationFuel PumpIdentificationLocationTank
Sheets 3, 3.1, 3.5, 3.7, 3.8, 3.9, 4, 4.1,
4.2, 4.3, 5, 5.1, 5.2, 5.3, 6, 6.1, 6.2, 7,
9.3, 9.8, 10, and 14.
R5-1934M1-92LeftAuxiliary Upper
R5-1933M1-91RightAuxiliary Upper
GROUP 2-4:
Drawing SR10280075ConnectorIdentificationFuel PumpIdentificationLocationTank
Sheets 3, 3.1, 3.3, 3.7, 3.7.1, 3.8, 3.9,
4.1, 4.2, 4.3, 5.1, 5.2, 5.3, 6, 6.1, 6.2,
7, 9.3, 9.9, 10, 15, and 15.1.
R5-1936M1-94LeftAuxiliary Lower
R5-1935M1-93RightAuxiliary Lower
GROUP 3:
Drawing SR10280075ConnectorIdentificationFuel PumpIdentificationLocationTank
Sheets 3, 3.1, 3.2, 3.3, 3.6, 3.7, 3.8,
3.9, 4.2, 5.2, 6, 6.1, 7, 8.0, 9.4, 9.9, 10,
11, 24, 25, and 26.
R5-1995M1-169Left
Aft Tank
R5-4815
Sheets 3, 3.1, 3.2, 3.3, 3.6, 3.7, 3.8,
3.9, 4.2, 5.2, 6, 6.1, 7, 8.1, 9.4, 9.9, 10,
11, 24, 25, and 26.
R5-1994M1-168Right
R5-4816
APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N
60-84351
(SHEET 2 OF 3)
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### Page 49

GROUP 4:
Drawing SR10280075ConnectorIdentificationFuel PumpIdentificationLocationTank
Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,
4.3, 5.3, 6, 6.1, 7, 9.5, 9.9, 10, and 22.
R5-2666M1-258TransferFwd Fuse Auxiliary
Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,
4.3, 5.3, 6, 6.1, 7, 9.5, 9.9, 10, and 23.
R5-2667M1-259TransferAft Fuse Auxiliary
Sheets 3, 3.1, 3.3, 3.7, 3.8, 3.9, 4.3,
5.3, 6, 6.1, 7, 9.6, 9.10, 10, and 13.
R5-4936M1-249LeftWing Tip
Sheets 3, 3.1, 3.3, 3.4, 3.7, 3.8, 3.9,
4.3, 5.3, 6, 6.1, 7, 9.6, 9.10, 10, and
12.
R5-4937M1-248Right
Wing Tip
APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N
60-84351
(SHEET 3 OF 3)
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### Page 50

ALL GROUPS:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-368
A
R5-11021/Forward
-2B
-3C
5022AD
5022AE*
-1
S3-370
A
R5-11001/Transfer
-2B
-3C
4726AD
4726AE*
-1
S3-369
A
R5-11011/Aft
-2B
-3C
4727AD
4727AE*
-1
S3-371
A
R5-11052/Forward
-2B
-3C
5009AD
5009AE*
-1
S3-372
A
R5-11042/Left Aft
-2B
-3C
4728AD
4728AE*
-
1
S3-374
A
R5-10992/Transfer
-
2
B
-
3
C
6078AD
6078AE*
-1
S3-373
A
R5-11032/Right Aft
-2B
-3C
4821AD
4821AE*
APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351
(SHEET 1 OF 4)
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### Page 51

ALL GROUPS:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-377
A
R5-11063/Forward
-2B
-3C
6022AD
6022AE*
-1
S3-376
A
R5-11073/Transfer
-2B
-3C
4823AD
4823AE*
-1
S3-375
A
R5-11083/Right Aft
-2B
-3C
4822AD
4822AE*
* E should read open during multimeter check.
GROUP 1-4:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-803
A
R5-1934Center Aux/LeftUpper -2B -3C 4729AD
4729AE*
-1
S3-802
A
R5-1933Center Aux/RightUpper -2B -3C 4824AD
4824AE*
* E should read open during multimeter check.
APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351
(SHEET 2 OF 4)
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### Page 52

GROUP 2-4:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-805
A
R5-1936Center Aux/LeftLower -2B -3C 4895AD
4895AE*
-1
S3-804
A
R5-1935Center Aux/RightLower -2B -3C 4894AD
4894AE*
* E should read open during multimeter check.
GROUP 3:
Ground Stud
ConnectorConnector (Pump)
Tank/Pump
SocketNumberSocketNumber
-CR5-4816AR5-1994Aft Aux/R
-BB
-AC
4866ADD
4866AE*E*
-CR5-4815AR5-1995Aft Aux/L
-BB
-AC
4865ADD
4865AE*E*
* E should read open during multimeter check.
GROUP 3:
TerminalRelayTank/Pump
A1R2-89Aft Aux R
B1
C1
A1R2-90Aft Aux L
B1
C1
APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351
(SHEET 3 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 01, 2009
DC10-28A261
52 of 55
BOEING SERVICE BULLETIN DC10-28A261
ALERTALERT

### Page 53

GROUP 4:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-1072
A
R5-49361/Tip
-2B
-3C
5088AD
5088AE*
-1
S3-1071
A
R5-49373/Tip
-2B
-3C
6088AD
6088AE*
-8
S3-1109
A
R5-2666Fwd Fuselage
-9B
-10C
4122AD
4122AE*
-8
S3-1110
A
R5-2667Aft Fuselage
-9B
-10C
4848AD
4848AE*
* E should read open during multimeter check.
APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 01, 2009
DC10-28A261
53 of 55
BOEING SERVICE BULLETIN DC10-28A261
ALERTALERT

### Page 54 (OCR)

BOEING SERVICE BULLETIN DC10-28A261
ALERT  ALERT
Replace fuel Pump Housing  Do Continuity and Resistance
Electrical Connector Assembly  Inspection from terminal strip
with part number 60-84351 IAW  OR  through fuel boost/transfer pump
Accomplishment Instruction 3.B.  IAW Accomplishment Instruction
Part 2 and restore airplane  3.B Part 3
Resistance is Greater  Resistance is Less
than 2.5 ohms or  than or Equal to 2.5
terminal E not open  ohms and Terminal E
reads open
Remove Fuel Boost/
Transfer Pump
Do Fuel Boost/
Transfer Pump  Remove Fuel Boost/
Resistance  Transfer Pump
Inspection
Fuel Boost/Transfer Pump  Fuel Boost/Transfer
Resistance is less than or  Pump Resistance is
equal to 2.5 ohms and  Greater than 2.5 ohms or
Terminal E reads open  terminal E not open
Using Megohm meter, do
Fuel Pump Housing
Replace Fuel Boost/  Transfer Pump  Electrical Connector  Assembly Insulation
Resistance Inspection
Resistance is less  Resistance is Greater than
than 10 Gigaohm  or equal to 10 Gigaohm
Restore Airplane
Replace Fuel Pump Housing  Replace fuel pump housing
Electrical Connector  electrical connector assembly
Assembly with Part Number  part number 60-84355-1 with
60-84351 IAW 3.B. Part 2  part number 60-84351 IAW
and restore airplane  3.B. Part 2 at threshold
Do Repeat Continuity and  specified in Paragraph 1.E.,
Resistance inspection IAW  Compliance Table 1
Accomplishment Instruction
3.B Part 4 at threshold
specified in Paragraph 1.E
Compliance Table 2
APPENDIX D: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER
60-84355-1 INSPECTION LOGIC DIAGRAM
(SHEET 1 OF 1)
Original Issue: December 01, 2009
BOEING PROPRIETARY -  DC10-28A261
Copyright © Unpublished Work - See page 1 for details.  54 of 55

### Page 55 (OCR)

BOEING SERVICE BULLETIN DC10-28A261
ALERT  ALERT
Do Continuity and Resistance
inspection from terminal strip
through fuel boost/transfer pump
IAW Accomplishment Instruction
3.B Part 4
Resistance is Greater  Resistance is Less
than 2.5 ohms or  than or Equal to 2.5
terminal E not open  ohms and Terminal E
reads open
Remove Fuel Boost/
Transfer Pump
Do Fuel Boost/
Transfer Pump  Remove Fuel Boost/
Resistance  Transfer Pump
Inspection
Fuel Boost/Transfer Pump  Fuel Boost/Transfer
Resistance is less than or  Pump Resistance is
equal to 2.5 ohms and  Greater than 2.5 ohms or
Terminal E reads open  terminal E not open
Using Megohm meter, do
Fuel Pump Housing
Replace Fuel Boost/  Electrical Connector
Transfer Pump
Assembly Insulation
Resistance Inspection
Resistance is less  Resistance is Greater than
than 10 Megaohm  or equal to 10 Megaohm
Restore Airplane
Replace Fuel Pump Housing
Electrical Connector
Assembly with Part Number
60-84351 IAW 3.B. Part 4
and restore airplane
Do Repeat Continuity and
Resistance inspection IAW
Accomplishment Instruction
3. B Part 4
APPENDIX E: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER
60-84351 INSPECTION LOGIC DIAGRAM
(SHEET 1 OF 1)
Original Issue: December 01, 2009
DC10-28A261
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  55 of 55

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