# Boeing Service Bulletin MD11-28-146: 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 MD11-28-146](https://openairdocs.org/service-documents/boeing/md11-28-146.md)
- Title as filed: U.S. DOT/FAA - SB-MD11-28-146-00
- Pages: 122
- PDF: https://openairdocs.org/files/sha256/c2/f9/c2f9d9a57930537e5ec19fd49dc061c6b02c42c123f1a5e28a48819239242095
- Page: https://openairdocs.org/service-documents/boeing/md11-28-146/file/c2f9d9a57930

## Text

Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

Commercial 
Airplanes
MD11
Service Bulletin
Number: MD11-28-146
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Unpublished Work.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.
Original Issue: May 15, 2015
MD11-28-146
1 of 122
2.0

### Page 2

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
2 of 122
BOEING SERVICE BULLETIN MD11-28-146
BLANK PAGE

### Page 3

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 0
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 0
D. Description .............................................. 1 1
E. Compliance .............................................. 1 1
F . A p p r o v a l  ............................................... 1 1
G. Manpower .............................................. 1 2
H. Weight and Balance Changes .................................... 1 4
I. Electrical Load Data ......................................... 1 4
J . R e f e r e n c e s  .............................................. 1 5
1. Existing Data: ......................................... 1 5
2. Data Supplied with this Service Bulletin: ........................... 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 5
K. Publications Affected ........................................ 1 5
L. Interchangeability and Intermixability of Parts ........................... 1 6
M. Software Accomplishment Summary ................................ 1 6
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary for Each Airplane ................................. 1 7
1 . K i t s / P a r t s  ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 2 0
3. Parts Modified and Reidentified ................................ 2 1
4. Parts Removed and Not Replaced .............................. 2 1
D. Parts Necessary to Change Spares ................................. 2 1
E. Special Tooling - Price and Availability ............................... 2 1
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 1
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 3
A. GENERAL INFORMATION ..................................... 2 3
B. WORK INSTRUCTIONS ....................................... 2 6
FIGURE 1: BENCH WORK - MAKE ALIGNMENT PINS ......................... 3 0
FIGURE 2: LEFT WING REAR SPAR - DISCONNECT FUEL PUMP WIRES .............. 3 1
FIGURE 3: LEFT WING FWD SPAR - DISCONNECT FUEL PUMP WIRES .............. 3 4
FIGURE 4: RIGHT WING FWD SPAR - DISCONNECT FUEL PUMP WIRES .............. 3 8
FIGURE 5: RIGHT WING REAR SPAR - DISCONNECT FUEL PUMP WIRES ............. 4 2
FIGURE 6: CENTER WING REAR SPAR (UPPER AUX TANK) - DISCONNECT FUEL PUMP WIRES . 45
FIGURE 7: CENTER WING REAR SPAR (LOWER AUX TANK) - DISCONNECT FUEL PUMP WIRES . 48
FIGURE 8: HORIZONTAL FWD SPAR (TAIL TANK) - DISCONNECT FUEL PUMP WIRES ...... 5 3
FIGURE 9: CHANGE FUEL PUMP HOUSING ELECTRICAL CONNECTOR (ALL PUMPS) ...... 5 6
FIGURE 10: CHANGE FUEL PUMP HOUSING (ALL PUMPS) ...................... 6 0
FIGURE 11: LEFT WING REAR SPAR - ROUTE AND CLIP FUEL PUMP WIRES ........... 6 4
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
3 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 4

FIGURE 12: LEFT WING FWD SPAR - ROUTE AND CLIP FUEL PUMP WIRES ............ 6 7
FIGURE 13: RIGHT WING FWD SPAR - ROUTE AND CLIP FUEL PUMP WIRES ........... 7 1
FIGURE 14: RIGHT WING REAR SPAR - ROUTE AND CLIP FUEL PUMP WIRES ........... 7 5
FIGURE 15: CENTER WING REAR SPAR (UPPER AUX TANK) - ROUTE AND CLIP FUEL PUMP WIRES
.................................................. 7 8
FIGURE 16: CENTER WING REAR SPAR (LOWER AUX TANK) - ROUTE AND CLIP FUEL PUMP WIRES
.................................................. 8 1
FIGURE 17: HORIZONTAL FWD SPAR (TAIL TANK) - ROUTE AND CLIP FUEL PUMP WIRES . . . 85
FIGURE 18: LEFT WING REAR SPAR - TERMINATE FUEL PUMP WIRES ............... 8 9
FIGURE 19: LEFT WING FWD SPAR - TERMINATE FUEL PUMP WIRES ............... 9 3
FIGURE 20: RIGHT WING FWD SPAR - TERMINATE FUEL PUMP WIRES ............... 9 6
FIGURE 21: RIGHT WING REAR SPAR - TERMINATE FUEL PUMP WIRES .............. 9 9
FIGURE 22: CENTER WING REAR SPAR (UPPER AUX TANK) - TERMINATE FUEL PUMP WIRES . 103
FIGURE 23: CENTER WING REAR SPAR (LOWER AUX TANK) - TERMINATE FUEL PUMP WIRES . 106
FIGURE 24: HORIZONTAL FWD SPAR (TAIL TANK) - TERMINATE FUEL PUMP WIRES ...... 1 0 9
APPENDIX A: 24 MONTH REPETITIVE INSPECTION ........................... 1 1 3
APPENDIX B: BOEING PART DEMAND INTENT - SURVEY ....................... 1 2 2
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
4 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 5

Commercial 
Airplanes
MD11
Service Bulletin
SummaryNumber: MD11-28-146Original 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) MD-11 FTD 28-11001, MD-11 FTD 28-12001 and MD-11 FTD 28-13004 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
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
5 of 122

### Page 6

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 as follows:
Option 1: Changes fuel pump housing electrical connectors, associated wires, fuel tank feed through components
and installs sealed terminal lugs on fuel pump wiring.
Option 2: Changes fuel pump housings, associated wires, fuel tank feed through components and installs sealed
terminal lugs on fuel pump wiring.
EFFECTIVITY
All MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
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.
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
More DataElapsed HoursTotal Task HoursAirplanes
(a)30.5 - 42.556.5 - 77.0MD-11 and MD-11F Airplanes
(a) Manpower depends on option selected, 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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
6 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 7 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
PLACE FUEL PUMP HOUSIN
LECTRICAL CONNECTOR
2271029
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  7 of 122

### Page 8

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
8 of 122
BOEING SERVICE BULLETIN MD11-28-146
BLANK PAGE

### Page 9

Commercial 
Airplanes
MD11
Service Bulletin
Number: MD11-28-146
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
MD-11 and MD-11F Airplanes.-1
Airplane Models:
MD-11, MD-11F
GroupFuselage Num-
ber
1447 - 449
1451 - 459
1460 - 464
1466 - 469
1470 - 479
1480 - 489
1491 - 499
1500 - 509
1510 - 517
1519
1520 - 529
1530 - 539
1540 - 549
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
9 of 122

### Page 10

GroupFuselage Num-
ber
1550 - 552
1554 - 559
1560 - 569
1570 - 579
1580 - 589
1590 - 599
1600 - 609
1610 - 619
1620 - 629
1630 - 639
1640 - 646
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 HousingHydro-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
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
10 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 11

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) MD-11 FTD 28-11001, MD-11 FTD 28-12001 and MD-11 FTD 28-13004
are related to this service bulletin.
D. Description
This service bulletin provides instructions to change/replace fuel pump housing electrical connectors
or fuel pump housings as follows:
Option 1: Changes fuel pump housing electrical connectors, associated wires, fuel tank feed through
components and installs sealed terminal lugs on fuel pump wiring.
Option 2: Changes fuel pump housings, associated wires, fuel tank feed through components and
installs sealed terminal lugs on fuel pump wiring.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
141, 142, 311, 515, 517, 531, 532, 533, 541,
615, 617, 632, 633, 641
MD-11, MD-11F
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
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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
11 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 12

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.
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 MD11-28A133, when
both actions are accomplished, as terminating action for the repetitive inspection requirements of the
following Boeing Service Bulletins and FAA ADs:
1. MD11-28A112, Rev 00 and paragraphs (a) and (b) of AD 2002-13-10.
2. MD11-28A143, Rev 00, 01 and paragraph (j) of AD 2011-11-05.
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 MD11-28A133, 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-11-00-03A and MD-11 Flight Crew Operations Manual Advisory Bulletin 2-05C. 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.
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.
Option 1: Change Fuel Pump Housing Electrical Connectors
Elapsed HoursTask HoursNumber of PersonsTask
2.02.01Open Access
0.50.51FIGURE 1
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
12 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 13

Option 1: Change Fuel Pump Housing Electrical Connectors
Elapsed HoursTask HoursNumber of PersonsTask
1.22.42FIGURE 2
0.81.62FIGURE 3
0.81.62FIGURE 4
1.22.42FIGURE 5
0.81.62FIGURE 6
0.81.62FIGURE 7
1.22.42FIGURE 8
10.220.42FIGURE 9
1.22.42FIGURE 11
0.81.62FIGURE 12
0.81.62FIGURE 13
1.22.42FIGURE 14
0.81.62FIGURE 15
0.81.62FIGURE 16
1.22.42FIGURE 17
0.30.62FIGURE 18
0.20.42FIGURE 19
0.20.42FIGURE 20
0.30.62FIGURE 21
0.20.42FIGURE 22
0.20.42FIGURE 23
0.30.62FIGURE 24
2.02.01Close Access
0.51.02Test
30.556.5TOTAL FOR EACH AIRPLANE
Option 2: Change Fuel Pump Housings
Elapsed HoursTask HoursNumber of PersonsTask
4.04.01Open Access
1.22.42FIGURE 2
0.81.62FIGURE 3
0.81.62FIGURE 4
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
13 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 14

Option 2: Change Fuel Pump Housings
Elapsed HoursTask HoursNumber of PersonsTask
1.22.42FIGURE 5
0.81.62FIGURE 6
0.81.62FIGURE 7
1.22.42FIGURE 8
18.737.42FIGURE 10
1.22.42FIGURE 11
0.81.62FIGURE 12
0.81.62FIGURE 13
1.22.42FIGURE 14
0.81.62FIGURE 15
0.81.62FIGURE 16
1.22.42FIGURE 17
0.30.62FIGURE 18
0.20.42FIGURE 19
0.20.42FIGURE 20
0.30.62FIGURE 21
0.20.42FIGURE 22
0.20.42FIGURE 23
0.30.62FIGURE 24
4.04.01Close Access
0.51.02Test
42.577.0TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
-2308.3-1.7+1357.8MD-11, MD-11F
I. Electrical Load Data
Not changed.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
14 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 15

J. References
1. Existing Data:
a. Boeing Flight Operations Bulletin MD-11-00-3A.
b. Boeing Service Bulletin MD11-28A112, MD11-28A133 and MD11-28A143.
c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2000-22-21, 2002-13-10
and 2011-11-05.
d. Standard Overhaul Practices Manual (SOPM) 20-50-01.
e. Standard Wiring Practices Manual (SWPM) 20-00-00, 20-00-03, 20-00-13, 20-10-01, 20-10-10,
20-10-17, 20-20-01, 20-20-03, 20-31-00 and 20-50-01.
f. Hydro-Aire Service Bulletin 60-843/845-28-2.
g. Hydro-Aire Service Information Letter 60-847-3-1.
h. MD11 Aircraft Maintenance Manual (AMM) 12-11-03, 28-00-00, 28-22-01 and 28-22-10.
i. MD-11 Fleet Team Digest (FTD) 28-11001, 28-12001 and 28-13004.
j. MD-11 Flight Crew Operations Manual Advisory Bulletin 2-05C.
k. MD-11 Structural Repair Manual (SRM) 51.
l. Nondestructive Testing Standard Practices Manual, Part 9.
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
ChangeTitleDocument Number
AELEC INST - FUEL PUMP ELECTRICAL CONNECTORSR11280085
AEO BELEC INST - FUEL PUMP ELECTRICAL CONNECTORSR11280085
NEWREPLACEMENT INSTALLATION - FUEL PUMP HOUSINGSR11280088
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:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
15 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 16

Chapter-SectionPublication
28-22Aircraft Maintenance Manual
28-11Component Maintenance Manual
Procedures SectionFAA Approved Airplane Flight Manual
28-14, 28-22Fault Isolation Manual
Interim Operating ProcedureFlight Crew Operations Manual
28-13, 28-22Illustrated Parts Catalog
MDC-02K1003 (CDCCL 28-2)Special Compliance Item Report
28-22System Schematic Manual
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.
L. Interchangeability and Intermixability of Parts
Old and new parts are not interchangeable.
M. Software Accomplishment Summary
Not affected.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
16 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 17

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
$5,831.0090Service KitSB11280146-3
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.
SB11280146-3 Service Kit
NotesExisting Part NumberNameQTYNew Part Number
KIT4SR11280085-3
KIT8SR11280085-5
KIT2SR11280085-7
KIT3SR11280085-9
END CAP3CYW20
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
17 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 18

SR11280085-3 Kit
NotesExisting Part NumberNameQTYNew Part Number
(a) (b)2768771-1COMB12768771-505
or
2768771-503
TERM LUG3D-436-1802-COLD
TERM LUG1D4361102COLD-ES
LOCKWASHER3MS35338-137
LOCKWASHER1MS35338-43
NUT3MS35649-284
(a)GLAND NUT1M8700-7/3
NAS1149CN832RWASHER1NAS620C10L
NAS1149F0332PWASHER3NAS620C8
(c)SCREW13D0005-3-12
(a) (c)FERRULE17D0294-1
(c)PIN19D0196-1
9D0197-1 (M8700-7/4 or
Equivalent)
BUSHING19D0357-1
(a) Discard the existing part.
(b) You cannot use the existing part to replace the new or changed part.
(c) Or approved Equivalent. Refer to AEPL Drawing 7595071.
SR11280085-5 Kit
NotesExisting Part NumberNameQTYNew Part Number
TERM LUG3D-436-1802-COLD
TERM LUG1D4361102COLD-ES
LOCKWASHER3MS35338-137
LOCKWASHER1MS35338-43
NUT3MS35649-284
NAS1149CN832RWASHER1NAS620C10L
NAS1149F0332PWASHER3NAS620C8
NUT GROMMET ASSY110-74916-8
(a)SCREW13D0005-3-12
(a)SEALING PLUG15D0206-12
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
18 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 19

SR11280085-7 Kit
NotesExisting Part NumberNameQTYNew Part Number
TERM LUG3D-436-1802-COLD
TERM LUG1D4361102COLD-ES
LOCKWASHER3MS35338-137
LOCKWASHER1MS35338-43
NUT3MS35649-284
NAS1149CN832RWASHER1NAS620C10L
NAS1149F0332PWASHER3NAS620C8
SLEEVE110-35916-16
GROMMET110-60766-8
(a)SCREW13D0005-3-12
(a)SEALING PLUG15D0206-12
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
SR11280085-9 Kit
NotesExisting Part NumberNameQTYNew Part Number
(a)TUBING2 FT.SR11280085-11
TERM LUG4D-436-1802-COLD
LOCKWASHER4MS35338-137
NUT4MS35649-284
NAS1149F0332PWASHER4NAS620C8
OVERBRAID2 FT.NEQL48830
NUT GROMMET ASSY110-74916-8
(b)CLAMP1687-118NF08
(c)SEALING PLUG15D0206-12
(c)FERRULE ASSY19D0067-4
(c)BAND,RETAINING29D0180-2
(a) Alternate tape barrier material P/N DPM 2306-1 or DPM 2306-4 (1/4 IN. I.D. X noted length)
can also be used, refer to SWPM 20-10-17.
(b) Discard the existing part.
(c) Or approved Equivalent. Refer to AEPL Drawing 7595071.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
19 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 20

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.
Option 1
NotesNameQTYPart Number / Specification
(a) (b) (c)Modification Kit1760-843-4901
.030 X 1 IN. (d)Tape, Elastomer12 FT.SR11280085-13
(DMS 2186 Type 2)
or
Equivalent
0.11 IN. DIA. X 18
IN.
Steel Rod2MIL-S-6758
or
Equivalent
(a) Refer to Hydro-Aire SB 60-843/845-28-2.
(b) Can be purchased from:
Repair and Overhaul
Hydro-Aire, Incorporated
3000 Winona Avenue
Burbank, California 91504 CAGE 81982
(c) Each Kit contains:
60-843504 Connector Assembly (QTY 1)
M25988/1-019 Packing, Formed (QTY 1)
ES500D4-6 or LL500D4-6 Screw, Selflocking (QTY 4)
(d) Can be purchased from:
Kirkhill-TA Company
300 East Cypress Street
Brea, California 92821-4007, CAGE 3DBN7
Option 2
NotesNameQTYPart Number / Specification
(a)Seal17460-015-40
(b)Fuel Pump Housing860-843-4
(b)Fuel Pump Housing960-845-4
(a)Packing17MS29512-10
(a)Packing34MS29513-237
(a)Packing34S4892944-230
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
20 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 21

Option 2
NotesNameQTYPart Number / Specification
(c)Tape, Elastomer (.030 X 1 IN.)12 FT.SR11280085-13
(DMS 2186 Type 2)
or
Equivalent
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
(b) Can be purchased from:
Repair and Overhaul
Hydro-Aire, Incorporated
3000 Winona Avenue
Burbank, California 91504 CAGE 81982
(c) Can be purchased from:
Kirkhill-TA Company
300 East Cypress Street
Brea, California 92821-4007, CAGE 3DBN7
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 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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
21 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 22

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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
22 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 23

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
MD-11 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 MD-11 SRM 51.
– Torque Values:
— Values for structural fasteners are given in MD-11 Structural Repair Manual,
Chapter 51.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
23 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 24

— Values for airframe maintenance tasks are included in Chapter 20 of MD-11
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 MD-11
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
WIRING INSTALLATION - MAINTENANCE PRACTICESSWPM 20-10-01
WIRE HARNESS and COMPONENT CLEANINGSWPM 20-10-10
BRAIDED ELECTRICAL WIRE BUNDLESSWPM 20-10-17
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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
24 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 25

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 (Including 3,060 gallon ER)
28-22-05Tail Tank
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
25 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 26

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. Single (1984 gal) or dual (3969 gal) fwd aux tanks are not affected.
24. Refer to Nondestructive Testing Standard Practices Manual (NDTSPM), Part 09 for
visual inspection information.
B. WORK INSTRUCTIONS
1. Put Fuel System Controller (FSC) in manual mode and make sure all pumps are off. Refer to MD11
AMM 28-00-00 as an accepted procedure.
2. Make sure circuit breakers are open as follows:
a. Open the fuel pump power circuit breakers and install safety tags. Refer to MD11 AMM
28-22-01 as an accepted procedure.
b. Make sure the following Remote Control Circuit Breaker (RCCB) indicators are green/open.
If any RCCB indicators are not green/open, take appropriate maintenance actions to make
sure the RCCBs indicators are green/open.
LocationCircuit BreakerRCCB
EPC Bay 2Tank 1 TransB1-672
EPC Bay 3Tank 1 AftB1-673
ADG Equipment PanelTank 1 AftB1-190*
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
ADG Equipment PanelTank 3 AftB1-191*
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 PanelTank 2 L AftB1-1572
EPC Bay 1Tail Tank L TransB1-1573
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
26 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 27

LocationCircuit BreakerRCCB
EPC Bay 2Tail Tank R TransB1-1575
Electrical Power PanelTail Tank AltnB1-1577
* If installed.
3. Get access to the work area. Refer to MD11 AMM 28-22-01 for access doors.
4. Remove/keep the fuel pumps from the fuel pump housings. Refer to MD-11 AMM 28-22-01 as an
accepted procedure.
5. Do OPTION 1 (Change Fuel Pump Housing Electrical Connectors) or OPTION 2 (Change Fuel
Pump Housings - Tank Entry Required) as follows:
Option 1 (Change Fuel Pump Housing Electrical Connectors)
a. Make alignment pins to assist in installation of fuel pump housing electrical connectors. Refer
to FIGURE 1 as an accepted procedure.
b. RC - Change Fuel Pump Housing Electrical Connectors in accordance with the following table:
Figure(s)/DescriptionTerm StripFuel PumpLocation
FIGURE 2 - Disconnect Wires
FIGURE 9 - Change Connector
FIGURE 11 - Route and Clip Wires
FIGURE 18 - Terminate Wires
S3-370M1-1100Left Wing Rear Spar
S3-369M1-1101
S3-372M1-1104
FIGURE 3 - Disconnect Wires
FIGURE 9 - Change Connector
FIGURE 12 - Route and Clip Wires
FIGURE 19 - Terminate Wires
S3-368M1-1102Left Wing Forward Spar
S3-371M1-1105
FIGURE 4 - Disconnect Wires
FIGURE 9 - Change Connector
FIGURE 13 - Route and Clip Wires
FIGURE 20 - Terminate Wires
S3-374M1-1099Right Wing Forward Spar
S3-377M1-1106
FIGURE 5 - Disconnect Wires
FIGURE 9 - Change Connector
FIGURE 14 - Route and Clip Wires
FIGURE 21 - Terminate Wires
S3-373M1-1103Right Wing Rear Spar
S3-376M1-1107
S3-375M1-1108
FIGURE 6 - Disconnect Wires
FIGURE 9 - Change Connector
FIGURE 15 - Route and Clip Wires
FIGURE 22 - Terminate Wires
S3-802M1-1933Center Wing Rear Spar
S3-803M1-1934
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
27 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 28

Figure(s)/DescriptionTerm StripFuel PumpLocation
FIGURE 7 - Disconnect Wires
FIGURE 9 - Change Connector
FIGURE 16 - Route and Clip Wires
FIGURE 23 - Terminate Wires
S3-804M1-1935Center Wing Rear Spar
S3-805M1-1936
FIGURE 8 - Disconnect Wires
FIGURE 9 - Change Connector
FIGURE 17 - Route and Clip Wires
FIGURE 24 - Terminate Wires
S3-765M1-2800Horizontal Forward Spar
S3-755M1-2801
S3-764M1-2802
Option 2 (Change Fuel Pump Housings - Tank Entry Required)
a. Prepare fuel tank for entry. Refer to MD-11 AMM 28-00-00 as an accepted procedure.
b. RC - Change Fuel Pump Housings in accordance with the following table:
Figure(s)/DescriptionTerm StripFuel PumpLocation
FIGURE 2 - Disconnect Wires
FIGURE 10 - Change Housing
FIGURE 11 - Route and Clip Wires
FIGURE 18 - Terminate Wires
S3-370M1-1100Left Wing Rear Spar
S3-369M1-1101
S3-372M1-1104
FIGURE 3 - Disconnect Wires
FIGURE 10 - Change Housing
FIGURE 12 - Route and Clip Wires
FIGURE 19 - Terminate Wires
S3-368M1-1102Left Wing Forward Spar
S3-371M1-1105
FIGURE 4 - Disconnect Wires
FIGURE 10 - Change Housing
FIGURE 13 - Route and Clip Wires
FIGURE 20 - Terminate Wires
S3-374M1-1099Right Wing Forward Spar
S3-377M1-1106
FIGURE 5 - Disconnect Wires
FIGURE 10 - Change Housing
FIGURE 14 - Route and Clip Wires
FIGURE 21 - Terminate Wires
S3-373M1-1103Right Wing Rear Spar
S3-376M1-1107
S3-375M1-1108
FIGURE 6 - Disconnect Wires
FIGURE 10 - Change Housing
FIGURE 15 - Route and Clip Wires
FIGURE 22 - Terminate Wires
S3-802M1-1933Center Wing Rear Spar
S3-803M1-1934
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
28 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 29

Figure(s)/DescriptionTerm StripFuel PumpLocation
FIGURE 7 - Disconnect Wires
FIGURE 10 - Change Housing
FIGURE 16 - Route and Clip Wires
FIGURE 23 - Terminate Wires
S3-804M1-1935Center Wing Rear Spar
S3-805M1-1936
FIGURE 8 - Disconnect Wires
FIGURE 10 - Change Housing
FIGURE 17 - Route and Clip Wires
FIGURE 24 - Terminate Wires
S3-765M1-2800Horizontal Forward Spar
S3-755M1-2801
S3-764M1-2802
6. Install kept fuel pumps and do operational test of fuel pumps (AC Pumping Units). Refer to MD11
AMM 28-22-01 as an accepted procedure.
7. Close access. Refer to MD11 AMM 28-22-01 for access doors.
8. Put the airplane back to a serviceable condition.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
29 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 30

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Make from steel rod
0.11 DIA X 18.00 IN.
2MIL-S-6758 (a)
or
Alignment PinMake1
Equivalent
(a) Operator supplied material, refer to Paragraph 2.C.2., Parts and Materials Supplied by the Operator.
FIGURE 1: BENCH WORK - MAKE ALIGNMENT PINS
(SHEET 1 OF 1)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
30 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 31 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
GND
4727A
GND
4726A
XORS  GND
264.00  4728A
S3-369
FEEDTHRU
FITTING
(M1-1101)
S3-370
FEEDTHRU
FITTING
(M1-1100)
XORS
197.20
WING TRAILING EDGE  FEEDTHRU
LEFT SIDE  FITTING
(M1-1104)  2351556
FIGURE 2: LEFT WING REAR SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 1 OF 3)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  31 of 122

### Page 32 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
SPAR  REAR  FEEDTHRU  FITTING
TYPICAL
2351560
FIGURE 2: LEFT WING REAR SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 2 OF 3)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  32 of 122

### Page 33

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTE: This figure is for fuel pumps M1-1100, M1-1101 and M1-1104.1.
2. The quantities shown are for 1 fuel pump.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove cover from
terminal strip.
1-CoverRemove/Keep1 (not shown)
At the terminal strip
and ground stud
disconnect the wires
coming from the fuel
pump feedthru fit-
ting.
--WiresDisconnect2
Remove clamp(s)
between fuel pump
feedthru fitting,
ground stud and ter-
minal strip.
--Clamp(s)Remove/Keep3 (not shown)
Cut off the terminals
at the wire ends.
--TerminalsCut4 (not shown)
110-74916-8NUT GROMMET
ASSY
Remove5
FIGURE 2: LEFT WING REAR SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
33 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 34 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
S3-368_
FEEDTHRU
FITTING
(M1-1102)
Xfs
391.00
GND
5022A
Xts
354.00
WING LEADING EDGE
LEFT SIDE
2351571
FIGURE 3: LEFT WING FWD SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 1 OF 4)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  34 of 122

### Page 35 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
GND
5009A
• S3-371
FEEDTHRU
•FITTING
(M1-1105)
Xis
225.00
Xis  Vang
204.09
Xis
196.00
WING LEADING EDGE
LEFT SIDE
2351574
FIGURE 3: LEFT WING FWD SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 2 OF 4)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  35 of 122

### Page 36

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTE: This figure is for fuel pumps M1-1102 and M1-1105.1.
2. The quantities shown are for 1 fuel pump.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove cover from
terminal strip.
1-CoverRemove/Keep1 (not shown)
At the terminal strip
and ground stud
disconnect the wires
coming from the fuel
pump feedthru fit-
ting.
--WiresDisconnect2
Remove clamp(s)
between fuel pump
feedthru fitting,
ground stud and ter-
minal strip.
--Clamp(s)Remove/Keep3 (not shown)
Cut off the terminals
at the wire ends.
--TerminalsCut4 (not shown)
1M8700-7/3GLAND NUTRemove5
FIGURE 3: LEFT WING FWD SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
36 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 37

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
17D0294-1FERRULERemove6
19D0197-1BUSHINGRemove7
12768771-1COMBRemove8
or
2768771-503
12653435SLEEVERemove/Keep9
FIGURE 3: LEFT WING FWD SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
37 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 38 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
S3-374
GND
6078A
Xis  C
-243.27
FEEDTHRU
FITTING
(M1-1099)  Xfs
-224.00
WING LEADING EDGE
RIGHT SIDE
2351578
FIGURE 4: RIGHT WING FWD SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 1 OF 4)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.

### Page 39 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
FEEDTHRU
FITTING
(M1-1106)
S3-377
XFS
-382.78
GND
6022A
XFS
-356.00
WING LEADING EDGE
RIGHT SIDE
2351586
FIGURE 4: RIGHT WING FWD SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 2 OF 4)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  39 of 122

### Page 40

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTE: This figure is for fuel pumps M1-1099 and M1-1106.1.
2. The quantities shown are for 1 fuel pump.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove cover from
terminal strip.
1-CoverRemove/Keep1 (not shown)
At the terminal strip
and ground stud
disconnect the wires
coming from the fuel
pump feedthru fit-
ting.
--WiresDisconnect2
Remove clamp(s)
between fuel pump
feedthru fitting,
ground stud and ter-
minal strip.
--Clamp(s)Remove/Keep3 (not shown)
Cut off the terminals
at the wire ends.
--TerminalsCut4 (not shown)
1M8700-7/3GLAND NUTRemove5
FIGURE 4: RIGHT WING FWD SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
40 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 41

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
17D0294-1FERRULERemove6
19D0197-1BUSHINGRemove7
12768771-1COMBRemove8
or
2768771-503
12653435SLEEVERemove/Keep9
FIGURE 4: RIGHT WING FWD SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
41 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 42 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
GND
4822A
GND
4823A
•
GND
-821 A
S3-375
FEEDTHRU
FITTING
(M1-1108)
'S3-376
FEEDTHRU
FITTING
(M1-1107)
XORS
S3-373  -197.20
WING TRAILING EDGE
FEEDTHRU  LOOKING FORWARD
FITTING  RIGHT SIDE
(M1-1103)  2351592
FIGURE 5: RIGHT WING REAR SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 1 OF 3)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  42 of 122

### Page 43 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
REAR
SPAR  FEEDTHRU
FITTING
ELECTRICAL FEEDTHRU
FITTING INSTALLATION
(TYPICAL)
2351594
FIGURE 5: RIGHT WING REAR SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 2 OF 3)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  43 of 122

### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTE: This figure is for fuel pumps M1-1103, M1-1107 and M1-1108.1.
2. The quantities shown are for 1 fuel pump.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove cover from
terminal strip.
1-CoverRemove/Keep1 (not shown)
At the terminal strip
and ground stud
disconnect the wires
coming from the fuel
pump feedthru fit-
ting.
--WiresDisconnect2
Remove clamp(s)
between fuel pump
feedthru fitting,
ground stud and ter-
minal strip.
--Clamp(s)Remove/Keep3 (not shown)
Cut off the terminals
at the wire ends.
--TerminalsCut4 (not shown)
110-74916-8NUT GROMMET
ASSY
Remove5
FIGURE 5: RIGHT WING REAR SPAR - DISCONNECT FUEL PUMP WIRES
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
44 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 45 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
GND
4824A
S3-802
M1-1933
XCW
-81.0
S3-803
GND
4729A
XcW
118.2
REAR SPAR
M1-1934
UPPER AUXILIARY
FUEL TANK
FIGURE 6: CENTER WING REAR SPAR (UPPER AUX TANK) - DISCONNECT FUEL PUMP WIRES
(SHEET 1 OF 3)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  45 of 122

### Page 46 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
REAR
SPAR
FEEDTHRU
FITTING
ELECING INSFALLATION
(TYPICAL)
2352741
FIGURE 6: CENTER WING REAR SPAR (UPPER AUX TANK) - DISCONNECT FUEL PUMP WIRES
(SHEET 2 OF 3)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  46 of 122

### Page 47

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTE: This figure is for fuel pumps M1-1933 and M1-1934.1.
2. The quantities shown are for 1 fuel pump.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove cover from
terminal strip.
1-CoverRemove/Keep1 (not shown)
At the terminal strip
and ground stud
disconnect the wires
coming from the fuel
pump feedthru fit-
ting.
--WiresDisconnect2
Remove clamp(s)
between fuel pump
feedthru fitting,
ground stud and ter-
minal strip.
--Clamp(s)Remove/Keep3 (not shown)
Cut off the terminals
at the wire ends.
--TerminalsCut4 (not shown)
110-74916-8NUT GROMMET
ASSY
Remove5
FIGURE 6: CENTER WING REAR SPAR (UPPER AUX TANK) - DISCONNECT FUEL PUMP WIRES
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
47 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 48 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
GND
4894A•
STA  GND
STA  4895A
1401
STA
1381
MAIN WHEEL WELL  S3-805
(LOOKING INBOARD
RIGHT SIDE)  C
2352527
FIGURE 7: CENTER WING REAR SPAR (LOWER AUX TANK) - DISCONNECT FUEL PUMP WIRES
(SHEET 1 OF 5)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.

### Page 49 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
STA
1387.50
FEEDTHRO
FITTING
(M1-1936)
D
FEEDTHRU
FITTING
(M1-1935)
(VIEW LOOKING UF
FORWARD AND INBOARD
2353914
FIGURE 7: CENTER WING REAR SPAR (LOWER AUX TANK) - DISCONNECT FUEL PUMP WIRES
(SHEET 2 OF 5)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  49 of 122

### Page 50 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
REAR
SPAR
FITTING
CONDUIT
5) ASSEMBL
LOWER CENTER WING REAR SPAR
ELECTRICAL FEEDTHRU
FITTING INSTALLATION
2352794
FIGURE 7: CENTER WING REAR SPAR (LOWER AUX TANK) - DISCONNECT FUEL PUMP WIRES
(SHEET 3 OF 5)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  50 of 122

### Page 51

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTE: This figure is for fuel pumps M1-1935 and M1-1936.1.
2. The quantities shown are for 1 fuel pump.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove cover from
terminal strip.
1-CoverRemove/Keep1 (not shown)
At the terminal strip
and ground stud
disconnect the wires
coming from the fuel
pump feedthru fit-
ting.
--WiresDisconnect2
Cut off the terminals
at the wire ends.
--TerminalsCut3 (not shown)
Attach a string to
the wires, long
enough to reach the
fuel pump feedthru
fitting. The string will
be used to pull the
new fuel pump
housing electrical
connector wires
back through the
conduit. Tie the end
of the string not at-
tached to the wires
to structure to pre-
vent it from being
accidently removed.
--StringAttach4 (not shown)
Disconnect the con-
duit from the
feedthru fitting.
1-ConduitDisconnect5
Pull the wires and
string through the
conduit. Remove
the string from the
wires and tie it to
airplane structure to
prevent it from being
accidently removed.
--Wires/StringPull6 (not shown)
110-35916-16SLEEVERemove7
FIGURE 7: CENTER WING REAR SPAR (LOWER AUX TANK) - DISCONNECT FUEL PUMP WIRES
(SHEET 4 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
51 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 52

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
110-60766-8GROMMETRemove8
FIGURE 7: CENTER WING REAR SPAR (LOWER AUX TANK) - DISCONNECT FUEL PUMP WIRES
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
52 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 53 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
M1-2802 M1-2801
S3-765 M1-2800  A @ S3-755  / S3-764 1
FEEDTHRU  FEEDTHRU  FEEDTHRU
FITTING  He de FITTING  FITTING
XCH = -20.000  XCH = -10.000  XCH =0.000  XCH =10.000  XCH =20.000
A-A
TAIL FUEL TANK
(VIEW LOOKING AFT)
FIGURE 8: HORIZONTAL FWD SPAR (TAIL TANK) - DISCONNECT FUEL PUMP WIRES
(SHEET 1 OF 3)
Original Issue: May 15, 2015
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
Work - See page 1 for details.  53 of 122

### Page 54 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
WIRE BUNDLE
-15 TUBING
REAR
SPAR
FEEDTHRU
FITTING
REAR SPAR
‚FEEDTHRU
FITTING
ELECTRICAL FEEDTHRU
FITTING INSTALLATION
2352596
FIGURE 8: HORIZONTAL FWD SPAR (TAIL TANK) - DISCONNECT FUEL PUMP WIRES
(SHEET 2 OF 3)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  54 of 122

### Page 55

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
NOTE: This figure is for fuel pumps M1-2800, M1-2801 and M1-2802.1.
2. The quantities shown are for 1 fuel pump.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove cover from
terminal strip.
1-CoverRemove/Keep1 (not shown)
At the terminal strip
disconnect the wires
coming from the fuel
pump feedthru fit-
ting.
--WiresDisconnect2
Remove clamps be-
tween the terminal
strip, ground stud
and fuel pump
feedthru fitting.
1S7934111-6SBCLAMPRemove/Keep3 (not shown)
1AN742D14RF ClampRemove/Keep4
--TAPE (RED)Remove5
19D0180-2RETAINER BANDRemove6
19D0067-4FERRULE ASSYRemove7
19D0180-2RETAINER BANDRemove8
-NEQL48830METAL OVER-
BRAID
Remove9
May not be present.1687-118NF08ClampRemove10
If Nut P/N ALL7066-
601-3 or 606-1-16-
08-12 was removed,
keep it for re-installa-
tion. If not a new
Nut Grommet As-
sembly will be in-
stalled.
110-74916-8
or
ALL7066-601-3
or
606-1-16-08-12
NUT GROMMET
ASSY
Remove/Keep11
FIGURE 8: HORIZONTAL FWD SPAR (TAIL TANK) - DISCONNECT FUEL PUMP WIRES
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
55 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 56 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
BAYONET
PUMP  PIN
HOUSING  SPRING
WIRE
PUMP HOUSING  • CONDUIT
END CAP  -PIN A
ALIGNMENT
PINS
/ PUMP
HOUSING  (210 (4 LOCATIONS)
A-A
ALIGNMENT
PINS  (4 LOCATIONS)
(10
SPRING •
TYPICAL  2352450
(17 LOCATIONS)
FIGURE 9: CHANGE FUEL PUMP HOUSING ELECTRICAL CONNECTOR (ALL PUMPS)
(SHEET 1 OF 4)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  56 of 122

### Page 57

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
At the fuel pump
feedthru fitting/termi-
nal strip tie a string
to the disconnected
wires. Tie the other
end of the string to
airplane structure.
As the fuel pump
housing electrical
connector is re-
moved the wires will
pull the string
through the conduit.
The string will then
be used to pull the
new wires back
through the conduit.
--StringAttach1 (not shown)
Remove two screws
from diagonally op-
posite locations on
the protective cap.
Install the alignment
pins in place of the
removed screws.
Then remove the
remaining two
screws.
4-SCREWRemove2
Slide the protective
cap along the align-
ment pins to remove
it from the fuel pump
housing.
160-84349PROTECTIVE CAPRemove/Keep3
FIGURE 9: CHANGE FUEL PUMP HOUSING ELECTRICAL CONNECTOR (ALL PUMPS)
(SHEET 2 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
57 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 58

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Slide the fuel pump
housing electrical
connector with the
attached wires and
string along the
alignment pins to
remove it from the
fuel pump housing.
Untie the string from
the wires and tie it
to airplane structure
to prevent acciden-
tal removal.
1-CONNECTOR AS-
SY
Remove4
1-PACKINGRemove5
Lubricate the pack-
ing and the interface
surface of the fuel
pump housing elec-
trical connector then
install the packing.
1M25988/1-019 (a)PACKINGInstall/New6
Tie the string in the
conduit to the wires
on the new fuel
pump housing elec-
trical connector. Use
the string to pull the
wires through the
conduit.
1-StringAttach/Pull (Not
Shown)
7 (not shown)
Align pin A of the fu-
el pump housing
electrical connector
with the fuel pump
housing bayonet
pin. Slide the fuel
pump housing elec-
trical connector
along the alignment
pins to the fuel
pump housing end
cap.
160-843504 (a)CONNECTOR AS-
SY
Install/New8
FIGURE 9: CHANGE FUEL PUMP HOUSING ELECTRICAL CONNECTOR (ALL PUMPS)
(SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
58 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 59

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Align the spring on
the protective cap
with the fuel pump
housing bayonet
pin. Slide the protec-
tive cap along the
alignment pins to
the fuel pump hous-
ing electrical connec-
tor and end cap.
160-84349 (b)PROTECTIVE CAPInstall/Kept9
Use two of the
screws to attach the
protective cap and
fuel pump housing
electrical connector
to the fuel pump
housing end cap.
Remove the align-
ment pins and re-
place them with the
two remaining
screws. Torque the
four screws to 5-7
inch-pounds.
4ES500D4-6 (a)
or
LL500D4-6 (a)
SCREWInstall/New10
Identify fuel pump
housing with new
part number (60-
843-4 or 60-845-4),
refer to Hydro-Aire
SB 60-843/845-28-
2.
160-843-4
or
60-845-4
FUEL PUMP
HOUSING
Identify11 (not shown)
(a) Operator supplied parts, refer to Paragraph 2.C.2., Parts and Materials Supplied by the Operator.
(b) Replace Protective Cap (60-84349) if required, refer to Hydro-Aire SB 60-843/845-28-2.
FIGURE 9: CHANGE FUEL PUMP HOUSING ELECTRICAL CONNECTOR (ALL PUMPS)
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 15, 2015
MD11-28-146
59 of 122
BOEING SERVICE BULLETIN MD11-28-146

### Page 60 (OCR)

BOEING SERVICE BULLETIN MD11-28-146
SPLIT RING
COUPLING ASSEMBLED
ELECTRICAL BOND  TYPICAL  78
(17 LOCATIONS)
FIGURE 10: CHANGE FUEL PUMP HOUSING (ALL PUMPS)
(SHEET 1 OF 4)
Original Issue: May 15, 2015
Export Controlled ECCN: 9E991 - BOEING  MD11-28-146
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  60 of 122

The text continues at https://openairdocs.org/service-documents/boeing/md11-28-146/file/c2f9d9a57930.md?from=61

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.