# Boeing Alert Service Bulletin MD11-28A133: No revision named

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- Title as filed: SB-MD11-28A133-00--
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## Text

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### Page 1

Commercial 
Airplanes
MD11
Service Bulletin
ALERT
Number: MD11-28A133
Original Issue: June 05, 2014
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Control Relays with Fault Current
Detectors and Change Fuel Tank Boost/Transfer Pump Wire Termination
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2014 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
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3.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 2
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 2
D. Description .............................................. 1 3
E. Compliance .............................................. 1 4
F. Approval ............................................... 1 4
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 7
I. Electrical Load Data ......................................... 1 8
J. References .............................................. 2 5
1. Existing Data: ......................................... 2 5
2. Data Supplied with this Service Bulletin: ........................... 2 6
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 6
4. Process Data: ......................................... 2 7
K. Publications Affected ........................................ 2 7
L. Interchangeability and Intermixability of Parts ........................... 2 7
M. Software Accomplishment Summary ................................ 2 7
2. MATERIAL INFORMATION ........................................ 2 9
A. Material - Price and Availability ................................... 2 9
B. Industry Support Information .................................... 2 9
C. Parts Necessary for Each Airplane ................................. 2 9
1. Kits/Parts ............................................ 2 9
2. Parts and Materials Supplied by the Operator ........................ 3 7
3. Parts Modified and Reidentified ................................ 3 8
4. Parts Removed and Not Replaced .............................. 3 8
D. Parts Necessary to Change Spares ................................. 3 8
E. Special Tooling - Price and Availability ............................... 3 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 9
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 1
A. GENERAL INFORMATION ..................................... 4 1
B. WORK INSTRUCTIONS ....................................... 4 3
APPENDIX A: INPUT SURVEY ........................................ 5 6
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Commercial 
Airplanes
MD11
Service Bulletin
ALERT
SummaryNumber: MD11-28A133Original Issue: June 05, 2014
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Control Relays with Fault Current
Detectors and Change Fuel Tank Boost/Transfer Pump Wire Termination
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 fuel boost/transfer pumps failures have occurred due to electrical ground or phase to phase fault within
the fuel pump electrical interface connector shell, pump motor windings and pump motor assembly lead wires.
These failures have caused arcing damage to the interface connector shell or fuel pump explosion proof
compartment. Investigation by Boeing has determined that during an electrical arcing event the affected Remote
Control Circuit Breaker (RCCB) may not react to the thermal rise from an electrical fault fast enough to prevent
arcing damage. Replacing the fuel boost/transfer pump control relays with Fault Current Detectors (FCD) will
minimize arcing events at the fuel pump electrical interface connector, pump motor windings and pump motor
assembly lead wires that could breach the explosion proof compartment. If not corrected, failure of the connector
or fuel pump motor could result in a breach of the fuel boost/transfer pump interface connector shell or the fuel
pump housing assembly and potentially become a fuel tank ignition source.
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 28-03006, MD-11 FTD 28-12001, MD-11 FTD 28-13001 and
MD-11 FTD 28-13004 are related to this service bulletin.
ACTION
This service bulletin provides instructions to do as follows:
1. Replaces fuel boost/transfer pump control relays in the Center Accessory Compartment (CAC), Electrical
Power Center (EPC) and Avionics Compartment (AC) forward equipment panel with fuel boost/transfer
pump FCDs.
2. Changes lower auxiliary fuel boost/transfer pump terminal board installation and associated wiring
located in the Main Landing Gear (MLG) right-side wheel-well.
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### Page 6

3. Changes fuel tank boost/transfer pump wire termination.
4. Group 4:
Removes the Forward Aux tank relays and associated wiring.
NOTE: The FCD is intended for use with ONLY airplane Original Equipment Manufacturer (OEM) certified fuel
pumps and fuel pump housings, including OEM pump/housing spare parts and parts repaired per OEM
approved repair instructions.
EFFECTIVITY
MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directives AD 2013-08-23, AD 2002-13-10 and AD
2011-11-05 are related to this service bulletin.
Boeing recommends that the change given in this service bulletin be done within 60 months after the effective
date of AD 2013-08-23.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes, given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to help Boeing
predict the quantity and timing of the Boeing Supplied Kits/Parts.
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### Page 7 (OCR)

BOEING SERVICE BULLETIN MD11-28A133
ALERT  ALERT
REPLACE FUEL PUMP CONTROL RELAYS WITH
FAULT CURRENT DETECTORS AND CHANGE FUEL
TANK BOOST/TRANSFER PUMP WIRE TERMINATION
1871518
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### Page 9

Commercial 
Airplanes
MD11
Service Bulletin
ALERT
Number: MD11-28A133
Original Issue: June 05, 2014
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Replace Fuel Pump Control Relays with Fault Current
Detectors and Change Fuel Tank Boost/Transfer Pump Wire Termination
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 for the airplanes shown below.
NOTE: Group 2 airplanes modified to a freighter configuration by Boeing Engineering will become
Group 1 airplanes.
DESCRIPTIONCONFIGURATIONGROUP
Applicable to MD-11 and MD11F Airplanes with fuel tanks 1, 2, 3,
upper and lower auxiliary, and tail configuration which are affected
by Service Rework Drawings SR11280076-7001, -7002 and
SR11280134-7001, -7002.
-1
Applicable to operators that have Not accomplished Service Bulletins
MD11-28-132 and MD11-28-146.
1
Applicable to operators that have accomplished Service Bulletin
MD11-28-132 and have Not accomplished Service Bulletin
MD11-28-146.
2
Applicable to operators that have accomplished Service Bulletin
MD11-28-146.
3
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DESCRIPTIONCONFIGURATIONGROUP
Applicable to MD-11 and MD-11F Airplanes with fuel tanks 1, 2, 3,
upper and lower auxiliary, forward auxiliary, and tail configuration
which are affected by Service Rework Drawing SR11280076-7003,
-7004 and SR11280134-7003, -7004.
-2
Applicable to operators that have Not accomplished Service Bulletins
MD11-28-132 and MD11-28-146.
1
Applicable to operators that have accomplished Service Bulletin
MD11-28-132 and have Not accomplished Service Bulletin
MD11-28-146.
2
Applicable to operators that have accomplished Service Bulletin
MD11-28-146.
3
Applicable to MD-11 Airplanes with fuel tanks 1, 2, 3, upper, lower
and forward auxiliary, and tail configuration which are affected by
Service Rework Drawing SR11280076-7005, -7006 and
SR11280134-7001, -7002.
-3
Applicable to operators that have Not accomplished Service Bulletins
MD11-28-132 and MD11-28-146.
1
Applicable to operators that have accomplished Service Bulletin
MD11-28-132 and have Not accomplished Service Bulletin
MD11-28-146.
2
Applicable to operators that have accomplished Service Bulletin
MD11-28-146.
3
Applicable to MD-11 Airplanes with fuel tanks 1, 2, 3, upper and lower
auxiliary, and tail configuration which are affected by Service Rework
Drawing SR11280076-7007, -7008 and SR11280134-7001, -7002.
-4
Applicable to operators that have Not accomplished Service Bulletins
MD11-28-132 and MD11-28-146.
1
Applicable to operators that have accomplished Service Bulletin
MD11-28-132 and have Not accomplished Service Bulletin
MD11-28-146.
2
Applicable to operators that have accomplished Service Bulletin
MD11-28-146.
3
Airplane Models:
MD-11, MD-11F
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GroupFuselage Num-
ber
1447 - 449
1451 - 459
1460 - 464
1466 - 469
1470 - 479
1480 - 489
1491 - 499
1500 - 509
4510
1511 - 513
4514
1515 - 517
1519
1520 - 529
1530 - 531
3532
1533 - 539
1540 - 543
3544
1545 - 549
1550 - 552
1554 - 559
1560 - 569
1570 - 579
1580 - 589
2590
1591 - 596
2597
1598 - 599
1600 - 609
1610 - 619
1620 - 629
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GroupFuselage Num-
ber
1630 - 639
1640 - 646
2. Spares Affected
None.
B. Concurrent Requirements
For operators who have not accomplished Service Bulletin MD11-28A113 and MD11-28A138 there
are no concurrent requirements.
For operators who have accomplished Service Bulletin MD11-28A113 and MD11-28A138 the service
bulletin or special product drawing listed below must be done before or at the same time as this service
bulletin:
Group 1, Configuration 1-2; Group 2, Configuration 1-2; Group 3, Configuration 1-2; Group 4,
Configuration 1-2:
DescriptionService Bulletin or Spe-
cial Product Drawing
Company
Replaces fuel pump housing electrical con-
nector assembly part number 60-84355-1
with part number 60-84351.
MD11-28A143 Revision 01The Boeing Company
Replaces fuel pump housing electrical con-
nector assembly part number 60-84355-1
with part number 60-84351.
SP11280022The Boeing Company
C. Reason
MD-11 fuel boost/transfer pumps failures have occurred due to electrical ground or phase to phase
fault within the fuel pump electrical interface connector shell, pump motor windings and pump motor
assembly lead wires. These failures have caused arcing damage to the interface connector shell or
fuel pump explosion proof compartment. Investigation by Boeing has determined that during an electrical
arcing event the affected Remote Control Circuit Breaker (RCCB) may not react to the thermal rise
from an electrical fault fast enough to prevent arcing damage. Replacing the fuel boost/transfer pump
control relays with Fault Current Detectors (FCD) will minimize arcing events at the fuel pump electrical
interface connector, pump motor windings and pump motor assembly lead wires that could breach the
explosion proof compartment. If not corrected, failure of the connector or fuel pump motor could result
in a breach of the fuel boost/transfer pump interface connector shell or the fuel pump housing assembly
and potentially become a fuel tank ignition source.
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 28-03006, MD-11 FTD 28-12001, MD-11 FTD 28-13001
and MD-11 FTD 28-13004 are related to this service bulletin.
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D. Description
This service bulletin provides instructions to do as follows:
1. Replaces fuel boost/transfer pump control relays in the Center Accessory Compartment (CAC),
Electrical Power Center (EPC) and Avionics Compartment (AC) forward equipment panel with fuel
boost/transfer pump FCDs.
2. Changes lower auxiliary fuel boost/transfer pump terminal board installation and associated wiring
located in the Main Landing Gear (MLG) right-side wheel-well.
3. Changes fuel tank boost/transfer pump wire termination.
4. Group 4:
Removes the Forward Aux tank relays and associated wiring.
NOTE: The FCD is intended for use with ONLY airplane Original Equipment Manufacturer (OEM)
certified fuel pumps and fuel pump housings, including OEM pump/housing spare parts and
parts repaired per OEM approved repair instructions.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
112, 131, 132, 141, 142, 144, 311, 515, 518,
541, 615, 618, 641
MD-11, MD-11F
Group 2:
Affected Maintenance Zones
ZoneModel
112, 127, 131, 132, 141, 142, 144, 311, 515,
518, 541, 615, 618, 641
MD-11
Group 3:
Affected Maintenance Zones
ZoneModel
112, 131, 132, 141, 142, 144, 311, 515, 518,
541, 615, 618, 641
MD-11
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Group 4:
Affected Maintenance Zones
ZoneModel
112, 131, 132, 141, 142, 144, 311, 515, 518,
541, 615, 618, 641
MD-11F
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directives AD 2013-08-23, AD 2002-13-10 and
AD 2011-11-05 are related to this service bulletin.
Boeing recommends that the change given in this service bulletin be done within 60 months after the
effective date of AD 2013-08-23 .
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the modification
defined in this service bulletin as an Alternative Method of Compliance (AMOC) to the requirements
of paragraph (g), (g)(1) and (h) of AD 2013-08-23 and to the repetitive inspection interval requirement
of paragraph (a) of AD 2002-13-10 and paragraph (j) of AD 2011-11-05 as follows. Accomplishment
of this service bulletin will allow the existing repetitive 18 month inspection interval to be increased to
no later than 24 months and no later than every 24 months thereafter. All provisions of AD 2013-08-23,
AD 2002-13-10 and AD 2011-11-05 that are not specifically referenced in the above statement remain
fully applicable and must be complied with.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 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.
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### Page 15

Group 1, Configuration 1-2:
Elapsed HoursTask HoursNumber of PersonsTask
1.83.62Open Access
8.58.51Replace
4.34.31Change
0.50.51Test
1.83.62Close Access
16.920.5TOTAL FOR EACH AIRPLANE
Group 1, Configuration 3:
Elapsed HoursTask HoursNumber of PersonsTask
1.83.62Open Access
8.58.51Replace
2.62.61Change
0.50.51Test
1.83.62Close Access
15.218.8TOTAL FOR EACH AIRPLANE
Group 2, Configuration 1-2:
Elapsed HoursTask HoursNumber of PersonsTask
2.34.62Open Access
9.59.51Replace
4.64.61Change
0.50.51Test
2.34.62Close Access
19.223.8TOTAL FOR EACH AIRPLANE
Group 2, Configuration 3:
Elapsed HoursTask HoursNumber of PersonsTask
2.34.62Open Access
9.59.51Replace
2.72.71Change
0.50.51Test
2.34.62Close Access
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Group 2, Configuration 3:
Elapsed HoursTask HoursNumber of PersonsTask
17.321.9TOTAL FOR EACH AIRPLANE
Group 3, Configuration 1-2:
Elapsed HoursTask HoursNumber of PersonsTask
1.83.62Open Access
10.510.51Replace
4.34.31Change
0.50.51Test
1.83.62Close Access
18.922.5TOTAL FOR EACH AIRPLANE
Group 3, Configuration 3:
Elapsed HoursTask HoursNumber of PersonsTask
1.83.62Open Access
10.510.51Replace
2.62.61Change
0.50.51Test
1.83.62Close Access
17.220.8TOTAL FOR EACH AIRPLANE
Group 4, Configuration 1-2:
Elapsed HoursTask HoursNumber of PersonsTask
1.83.62Open Access
12.512.51Replace
4.34.31Change
0.50.51Test
1.83.62Close Access
20.924.5TOTAL FOR EACH AIRPLANE
Group 4, Configuration 3:
Elapsed HoursTask HoursNumber of PersonsTask
1.83.62Open Access
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Group 4, Configuration 3:
Elapsed HoursTask HoursNumber of PersonsTask
12.512.51Replace
2.62.61Change
0.50.51Test
1.83.62Close Access
19.222.8TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Group 1, Configuration 1-2:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)Airplane
+7,545.0+7.41,019.6MD-11, MD-11F
Group 1, Configuration 3:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)Airplane
+7,341.1+7.21,019.6MD-11, MD-11F
Group 2:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)Airplane
+8,240.0+8.01,030.0MD-11
Group 3, Configuration 1-2:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)Airplane
+9,345.6+9.01,038.4MD-11
Group 3, Configuration 3:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)Airplane
+9,137.9+8.81,038.4MD-11
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### Page 18

Group 4, Configuration 1-2:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)Airplane
+4,588.2+4.51,019.6MD-11F
Group 4, Configuration 3:
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)Airplane
+4,384.3+4.31,019.6MD-11F
I. Electrical Load Data
1. Direct Current DC Load Changes:
No DC loads added or deleted.
2. Alternating Current (AC) Load Changes:
a. Add AC loads by amounts shown below:
NOTE: Retain removed relay % TIME OPR for each BUS/CHAP/ITEM shown below (for
example BUS 1E, CHAP 280, ITEM 5006, U1-701 shall retain the % TIME OPR for
R2-101).
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-
1206)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
R Fuel Pump Upper Aux
HDGE-X3F-001
ITEM
5006
U1-
701
CHAP
280
BUS
1E
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-
1207)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
L Fuel Pump Upper Aux
HDGE-X3F-001
ITEM
5004
U1-
702
CHAP
280
BUS
2F
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-
1208)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
R Fuel Pump Lower Aux
HDGE-X3F-001
ITEM
5005
U1-
703
CHAP
280
BUS
3G
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Work - See page 1 for details.
Original Issue: June 05, 2014
MD11-28A133
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ALERTALERT

### Page 19

UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-
1209)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
L Fuel Pump Lower Aux
HDGE-X3F-001
ITEM
5005
U1-
704
CHAP
280
BUS
2F
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-615)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
FWD Fuel Pump No 1
Tank
HDGE-X3F-001
ITEM
5003
U1-
751
CHAP
280
BUS
1E
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-613)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
AFT Fuel Pump No 1
Tank
HDGE-X3F-001
ITEM
5002
U1-
752
CHAP
280
BUS
3G
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-611)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
Transfer Fuel Pump
No.1
HDGE-X3F-001
ITEM
5001
U1-
753
CHAP
280
BUS
2F
UNITS
%OPR
1
100
E/NE/M
PHASE
E
B
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-609)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
FWD Fuel Pump No 2
Tank
HDGE-X3F-001
ITEM
5004
U1-
754
CHAP
280
BUS
1E
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-757)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
Transfer Fuel Pump
No.2
HDGE-X3F-001
ITEM
5003
U1-
755
CHAP
280
BUS
3G
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115 VAC
Emer
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-
1572)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
L AFT Fuel Pump No. 2
Tank
HDGE-X3F-001
ITEM
5001
U1-
756
CHAP
280
BUS
3A
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 05, 2014
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BOEING SERVICE BULLETIN MD11-28A133
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### Page 20

UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-603)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
R AFT Fuel Pump No.
2 Tank
HDGE-X3F-001
ITEM
5002
U1-
757
CHAP
280
BUS
2F
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-617)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
FWD Fuel Pump No 3
Tank
HDGE-X3F-001
ITEM
5004
U1-
758
CHAP
280
BUS
3G
UNITS
%OPR
1
100
E/NE/M
PHASE
E
B
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-621)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
AFT Fuel Pump No 3
Tank
HDGE-X3F-001
ITEM
5003
U1-
759
CHAP
280
BUS
2F
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-619)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
Transfer Fuel Pump
No.3
HDGE-X3F-001
ITEM
5005
U1-
760
CHAP
280
BUS
1E
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115 VAC
Emer
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-
1577)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
Tail Tank Alternate
Pump
HDGE-X3F-001
ITEM
5002
U1-
850
CHAP
280
BUS
3A
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-497)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
Tail Tank L Transfer
Pump
HDGE-X3F-001
ITEM
5002
U1-
851
CHAP
280
BUS
1E
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-496)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
Tail Tank R Transfer
Pump
HDGE-X3F-001
ITEM
5006
U1-
852
CHAP
280
BUS
2F
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 05, 2014
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### Page 21

Group 2-3:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-
1645)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
L Fwd Aux Tank Pump
1
HDGE-X3F-001
ITEM
5003
U1-
709
CHAP
280
BUS
1E
Group 2-3:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-
1644)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
R Fwd Aux Tank Pump
1
HDGE-X3F-001
ITEM
5002
U1-
710
CHAP
280
BUS
3G
Group 3:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-542)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
L FWD Aux Tank Pump
2
HDGE-X3F-001
ITEM
5003
U1-
790
CHAP
280
BUS
1E
Group 3:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
6
NOTES
(B1-543)
SUPPLIER
Leach Inter-
national
EQUIPMENT NAME
PART NUMBER
R FWD Aux Tank Pump
2
HDGE-X3F-001
ITEM
5002
U1-
789
CHAP
280
BUS
3G
b. Delete AC loads by amounts shown below:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-
1206)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
R Fuel Pump Control
Upper Aux Tank
DVR-7VC
ITEM
5006
R2-
101
CHAP
280
BUS
1E
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 05, 2014
MD11-28A133
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BOEING SERVICE BULLETIN MD11-28A133
ALERTALERT

### Page 22

UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-
1207)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
Upper Aux Left Tank
DVR-7VC
ITEM
5004
R2-
102
CHAP
280
BUS
2F
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-
1208)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
R Fuel Pump Control
Lower Aux Tank
DVR-7VC
ITEM
5005
R2-
103
CHAP
280
BUS
3G
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-
1209)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
Lower Aux Left Tank
DVR-7VC
ITEM
5005
R2-
104
CHAP
280
BUS
2F
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-615)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
FWD Fuel Pump -1
DVR-7VC
ITEM
5003
R2-51
CHAP
280
BUS
1E
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-613)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
L Fuel Pump Control
Upper Aux Tank
DVR-7VC
ITEM
5002
R2-52
CHAP
280
BUS
3G
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-611)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
Transfer Pump Control
DVR-7VC
ITEM
5001
R2-53
CHAP
280
BUS
2F
UNITS
%OPR
1
100
E/NE/M
PHASE
E
B
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-609)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
FWD Fuel Pump -2
DVR-7VC
ITEM
5004
R2-54
CHAP
280
BUS
1E
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 05, 2014
MD11-28A133
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BOEING SERVICE BULLETIN MD11-28A133
ALERTALERT

### Page 23

UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-757)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
XFR Fuel Pump -2
DVR-7VC
ITEM
5003
R2-55
CHAP
280
BUS
3G
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-
1572)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
L AFT Pump - 2
DVR-7VC
ITEM
5001
R2-56
CHAP
280
BUS
3A
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-603)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
R AFT Pump - 2
DVR-7VC
ITEM
5002
R2-57
CHAP
280
BUS
2F
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-617)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
Fuel Pump -3
DVR-7VC
ITEM
5004
R2-58
CHAP
280
BUS
3G
UNITS
%OPR
1
100
E/NE/M
PHASE
E
B
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-621)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
AFT Fuel Pump -3
DVR-7VC
ITEM
5003
R2-59
CHAP
280
BUS
2F
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-619)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
Fuel XFR Pump -3
DVR-7VC
ITEM
5005
R2-60
CHAP
280
BUS
1E
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115 VAC
Emer
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-
1577)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
Tail Tank Alt Pump
DVR-7VC
ITEM
5002
R2-
250
CHAP
280
BUS
3A
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 05, 2014
MD11-28A133
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BOEING SERVICE BULLETIN MD11-28A133
ALERTALERT

### Page 24

UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115 VAC
Emer
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-497)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
Tail Tank Alt Pump
DVR-7VC
ITEM
5002
R2-
251
CHAP
280
BUS
1E
UNITS
%OPR
1
100
E/NE/M
PHASE
E
A
VAC
PF
115
VAC-2
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-496)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
Tail Tank R Pump
DVR-7VC
ITEM
5006
R2-
252
CHAP
280
BUS
2F
Group 2-3:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-
1645)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
L Fuel Pump Control
Fwd Aux Tank 1
DVR-7VC
ITEM
5003
R2-
109
CHAP
280
BUS
1E
Group 2-3:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-
1644)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
R Fuel Pump Control
Fwd Aux Tank 1
DVR-7VC
ITEM
5002
R2-
110
CHAP
280
BUS
3G
Group 3:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-542)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
L Fuel Pump Control
Fwd Aux Tank 2
DVR-7VC
ITEM
5003
R2-90
CHAP
280
BUS
1E
Group 3:
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-543)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
R Fuel Pump Control
Fwd Aux Tank 2
DVR-7VC
ITEM
5002
R2-89
CHAP
280
BUS
3G
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 05, 2014
MD11-28A133
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BOEING SERVICE BULLETIN MD11-28A133
ALERTALERT

### Page 25

Group 4:
Remove and not replace.
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-
1645)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
L Fuel Pump Control
Fwd Aux Tank 1
DVR-7VC
ITEM
5003
R2-
109
CHAP
280
BUS
1E
Group 4:
Remove and not replace.
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-
1644)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
R Fuel Pump Control
Fwd Aux Tank 1
DVR-7VC
ITEM
5002
R2-
110
CHAP
280
BUS
3G
Group 4:
Remove and not replace.
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-1
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-542)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
L Fuel Pump Control
Fwd Aux Tank 2
DVR-7VC
ITEM
5003
R2-90
CHAP
280
BUS
1E
Group 4:
Remove and not replace.
UNITS
%OPR
1
100
E/NE/M
PHASE
E
C
VAC
PF
115
VAC-3
0.95
UNIT
LOAD
(W)
5
NOTES
(B1-543)
SUPPLIER
Hartman
EQUIPMENT NAME
PART NUMBER
R Fuel Pump Control
Fwd Aux Tank 2
DVR-7VC
ITEM
5002
R2-89
CHAP
280
BUS
3G
J. References
1. Existing Data:
a. Boeing Service Bulletin MD11-28A113, MD11-28A138 and MD11-28A143 Revision 01.
b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2002-13-10, 2011-11-05
and 2013-08-23.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 05, 2014
MD11-28A133
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BOEING SERVICE BULLETIN MD11-28A133
ALERTALERT

### Page 26

c. MD11 Aircraft Maintenance Manual (AMM) 06-31-02, 06-31-03, 06-31-12, 06-31-13, 06-31-27,
06-37-00, 28-00-00,  28-22-01, 28-22-10, 28-22-12 and 28-22-13.
d. MD-11 Fleet Team Digest (FTD) 28-03006, 28-12001, 28-13001 and 28-13004.
e. MD-11 Structural Repair Manual (SRM) 51.
f. Special Product Drawing SP11280022.
g. Standard Overhaul Practices Manual (SOPM) 20-50-01.
h. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-13, 20-00-16, 20-10-01,
20-10-03, 20-20-03, 20-31-01, and 20-50-01.
2. Data Supplied with this Service Bulletin:
No data is supplied with this service bulletin. To obtain the data necessary to support this service
bulletin submit a data request to:
Data and Services Management
Mail Code: 110-SE20 (Bldg 80)
2201 Seal Beach Boulevard
Seal Beach, California 90740 USA
Phone: (562) 797-1717
Fax: (562) 797-3783
E-mail: lbd.dataservicesmanagement@boeing.com
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
E-AEOELECTRICAL INSTALLATION - FUEL
PUMP FAULT CURRENT DETECTOR
SR11280076
-DDWG
H-AEOWIRE INSTALLATION - ELIMINATE CIR-
CUIT GROUND FOR FUEL PUMPS
SR11280134
-GDWG
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 05, 2014
MD11-28A133
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BOEING SERVICE BULLETIN MD11-28A133
ALERTALERT

### Page 27

4. Process Data:
Douglas Process Specifications referred to on the drawings are not given in this service bulletin
since these procedures are frequently used as standard shop practices.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
28-22Aircraft Maintenance Manual
28-14, 28-22, 28-23Fault Isolation Manual
28-22Illustrated Parts Catalog
MDC-02K1003 (ALI 28-1, CDCCL 28-
10)
Special Compliance Item Report
28-22System Schematic Manual
28-22Wiring Diagram Manual
2. 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.
NOTE: This service bulletin replaces existing fuel pump control relays with FCDs. After accomplishment
of this service bulletin airplanes cannot revert to the previously installed non-FCD fuel pump
control relays.
M. Software Accomplishment Summary
Not affected.
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### Page 29

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary for Each Airplane and
Paragraph 2.D., Parts Necessary to Change Spares. Operators are encouraged to share schedule
requirements with Boeing for incorporation of the service bulletin. The kits/parts 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 is-
sue date of this Service Bulletin
(US Dollars)
ROLT as of the original issue
date of this Service Bulletin
(Calendar Days)
NameKit Number
$83,732.00150Service KitSB11280133-3
$92,615.00150Service KitSB11280133-5
$101,151.00150Service KitSB11280133-7
$79,752.00150Service KitSB11280133-9
$88,631.00150Service KitSB11280133-11
$97,171.00150Service KitSB11280133-13
Operators are encouraged to complete the survey provided in APPENDIX A 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
Group 1, Configuration 1-2; Group 4, Configuration 1-2:
Kit SB11280133-3
NotesNameQTYPart Number
(a)SCREW23D0005-08-18
(a)SCREW63D0005-08-20
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Group 1, Configuration 1-2; Group 4, Configuration 1-2:
Kit SB11280133-3
NotesNameQTYPart Number
(a)SCREW23D0005-08-24
(a)SCREW123D0005-08-28
(a)SCREW23D0005-08-30
(a)SCREW23D0005-08-32
(a)SCREW683D0005-08-8
(a)TIE MOUNT25D0061-2
(a)TERMINAL LUG 765145D0086-25
BRACKET ASSEMBLY1ABN7377-600
END CAP3CYW20
FAULT CURRENT DTCTR17HDGE-X3F-001
COVER ASSEMBLY1MS18029-6S7
RIVET32MS20470AD3-3D
RIVET7MS20470AD4-7D
TERM BOARD ASSEMBLY1MS27212-6-7
LOCKWASHER13MS35338-42
LOCKWASHER2MS35338-43
NUT13MS35649-282
WASHER2NAS1149F0332P
WASHER81NAS1149FN816P
WASHER50NAS1252-8L
RIVNUT2NAS1329S08KB75
NUTPLATE16NAS1474A08
SCREW2NAS1801-3-10
SPACER2NAS43DD3-32FC
SPACER6NAS43DD3-64FC
SPACER16NAS43DD3-80FC
WASHER4NAS620-4L
SCREW4NAS8200U7
(b)WIRE KIT1SR11280076-101
(b)WIRE KIT1SR11280076-102
(b)WIRE KIT1SR11280076-103
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Group 1, Configuration 1-2; Group 4, Configuration 1-2:
Kit SB11280133-3
NotesNameQTYPart Number
(b)WIRE KIT1SR11280076-104
BRACKET ASSEMBLY1SR11280134-3
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Kit Table.
Group 2, Configuration 1-2:
Kit SB11280133-5
NotesNameQTYPart Number
(a)SCREW23D0005-08-18
(a)SCREW63D0005-08-20
(a)SCREW13D0005-08-22
(a)SCREW23D0005-08-24
(a)SCREW123D0005-08-28
(a)SCREW23D0005-08-30
(a)SCREW23D0005-08-32
(a)SCREW763D0005-08-8
(a)TIE MOUNT25D0061-2
(a)TERMINAL LUG 765145D0086-25
BRACKET ASSEMBLY1ABN7377-600
END CAP5CYW20
FAULT CURRENT DTCTR19HDGE-X3F-001
COVER ASSEMBLY1MS18029-6S7
RIVET32MS20470AD3-3D
RIVET7MS20470AD4-7D
TERM BOARD ASSEMBLY1MS27212-6-7
LOCKWASHER13MS35338-42
LOCKWASHER2MS35338-43
NUT13MS35649-282
WASHER2NAS1149F0332P
WASHER89NAS1149FN816P
WASHER52NAS1252-8L
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Group 2, Configuration 1-2:
Kit SB11280133-5
NotesNameQTYPart Number
RIVNUT2NAS1329S08KB75
NUTPLATE16NAS1474A08
SCREW2NAS1801-3-10
SPACER2NAS43DD3-32FC
SPACER7NAS43DD3-64FC
SPACER16NAS43DD3-80FC
WASHER4NAS620-4L
SCREW4NAS8200U7
(b)WIRE KIT1SR11280076-101
(b)WIRE KIT1SR11280076-102
(b)WIRE KIT1SR11280076-103
(b)WIRE KIT1SR11280076-105
BRACKET ASSEMBLY1SR11280134-3
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Kit Table.
Group 3, Configuration 1-2:
Kit SB11280133-7
NotesNameQTYPart Number
(a)SCREW23D0005-08-18
(a)SCREW63D0005-08-20
(a)SCREW13D0005-08-22
(a)SCREW23D0005-08-24
(a)SCREW123D0005-08-28
(a)SCREW23D0005-08-30
(a)SCREW23D0005-08-32
(a)SCREW843D0005-08-8
(a)TIE MOUNT25D0061-2
(a)TERMINAL LUG 765145D0086-25
BRACKET ASSEMBLY1ABN7377-600
END CAP3CYW20
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Group 3, Configuration 1-2:
Kit SB11280133-7
NotesNameQTYPart Number
FAULT CURRENT DTCTR21HDGE-X3F-001
COVER ASSEMBLY1MS18029-6S7
RIVET32MS20470AD3-3D
RIVET7MS20470AD4-7D
TERM BOARD ASSEMBLY1MS27212-6-7
LOCKWASHER13MS35338-42
LOCKWASHER2MS35338-43
NUT13MS35649-282
WASHER2NAS1149F0332P
WASHER97NAS1149FN816P
WASHER52NAS1252-8L
RIVNUT2NAS1329S08KB75
NUTPLATE16NAS1474A08
SCREW2NAS1801-3-10
SPACER2NAS43DD3-32FC
SPACER7NAS43DD3-64FC
SPACER16NAS43DD3-80FC
WASHER4NAS620-4L
SCREW4NAS8200U7
(b)WIRE KIT1SR11280076-101
(b)WIRE KIT1SR11280076-102
(b)WIRE KIT1SR11280076-103
(b)WIRE KIT1SR11280076-104
BRACKET ASSEMBLY1SR11280134-3
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Kit Table.
Group 1, 4, Configuration 3:
Kit SB11280133-9
NotesNameQTYPart Number
(a)SCREW23D0005-08-18
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Group 1, 4, Configuration 3:
Kit SB11280133-9
NotesNameQTYPart Number
(a)SCREW63D0005-08-20
(a)SCREW23D0005-08-24
(a)SCREW123D0005-08-28
(a)SCREW23D0005-08-30
(a)SCREW23D0005-08-32
(a)SCREW683D0005-08-8
(a)TIE MOUNT25D0061-2
FAULT CURRENT DTCTR17HDGE-X3F-001
RIVET32MS20470AD3-3D
WASHER68NAS1149FN816P
WASHER50NAS1252-8L
RIVNUT2NAS1329S08KB75
NUTPLATE16NAS1474A08
SPACER2NAS43DD3-32FC
SPACER6NAS43DD3-64FC
SPACER16NAS43DD3-80FC
(b)WIRE KIT1SR11280076-101
(b)WIRE KIT1SR11280076-102
(b)WIRE KIT1SR11280076-103
(b)WIRE KIT1SR11280076-104
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Kit Table.
Group 2, Configuration 3:
Kit SB11280133-11
NotesNameQTYPart Number
(a)SCREW23D0005-08-18
(a)SCREW63D0005-08-20
(a)SCREW13D0005-08-22
(a)SCREW23D0005-08-24
(a)SCREW123D0005-08-28
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Group 2, Configuration 3:
Kit SB11280133-11
NotesNameQTYPart Number
(a)SCREW23D0005-08-30
(a)SCREW23D0005-08-32
(a)SCREW763D0005-08-8
(a)TIE MOUNT25D0061-2
FAULT CURRENT DTCTR19HDGE-X3F-001
RIVET32MS20470AD3-3D
WASHER76NAS1149FN816P
WASHER52NAS1252-8L
RIVNUT2NAS1329S08KB75
NUTPLATE16NAS1474A08
SPACER2NAS43DD3-32FC
SPACER7NAS43DD3-64FC
SPACER16NAS43DD3-80FC
(b)WIRE KIT1SR11280076-101
(b)WIRE KIT1SR11280076-102
(b)WIRE KIT1SR11280076-103
(b)WIRE KIT1SR11280076-105
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Kit Table.
Group 3, Configuration 3:
Kit SB11280133-13
NotesNameQTYPart Number
(a)SCREW23D0005-08-18
(a)SCREW63D0005-08-20
(a)SCREW13D0005-08-22
(a)SCREW23D0005-08-24
(a)SCREW123D0005-08-28
(a)SCREW23D0005-08-30
(a)SCREW23D0005-08-32
(a)SCREW843D0005-08-8
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Group 3, Configuration 3:
Kit SB11280133-13
NotesNameQTYPart Number
(a)TIE MOUNT25D0061-2
FAULT CURRENT DTCTR21HDGE-X3F-001
RIVET32MS20470AD3-3D
WASHER84NAS1149FN816P
WASHER52NAS1252-8L
RIVNUT2NAS1329S08KB75
NUTPLATE16NAS1474A08
SPACER2NAS43DD3-32FC
SPACER7NAS43DD3-64FC
SPACER16NAS43DD3-80FC
(b)WIRE KIT1SR11280076-101
(b)WIRE KIT1SR11280076-102
(b)WIRE KIT1SR11280076-103
(b)WIRE KIT1SR11280076-104
(a) Or approved Equivalent. Refer to AEPL Drawing 7595071.
(b) Refer to Wire Kit Table.
Group 1, 3-4:
Wire Kit Table
NotesNameQTY SR11280076Part Number
-104-103-102-101
(a)WIRE CODE 80149 FT98 FT99 FT64 FTD2426-1C-16NM
(a)WIRE CODE 80112 FT21 FTD2426-1C-20NM
(a)WIRE CODE 80115 FT13 FTD2426-1C-22NM
(b)TERM LUG 76699995D0086-26
(b)TERMINAL LUG 761225D0086-5
(b)TERMINAL LUG 762115D0086-6
(b)TERMINAL LUG 878115D0086-3
(b)TERMINAL LUG 877225D0086-2
SOCKET T/C 11233333DC39-16S
SOCKET T/C 11241111DC39-20S
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Group 1, 3-4:
Wire Kit Table
NotesNameQTY SR11280076Part Number
-104-103-102-101
(a) Or approved alternate. Refer to SWPM 20-00-13.
(b) Or approved Equivalent. Refer to AEPL Drawing 7595071
Group 2:
Wire Kit Table
NotesNameQTY SR11280076Part Number
-105-103-102-101
(a)WIRE CODE 80149 FT98 FT99 FT64 FTD2426-1C-16NM
(a)WIRE CODE 80129 FT21 FTD2426-1C-20NM
(a)WIRE CODE 80115 FT13 FTD2426-1C-22NM
(b)TERM LUG 76699995D0086-26
(b)TERMINAL LUG 761425D0086-5
(b)TERMINAL LUG 762115D0086-6
(b)TERMINAL LUG 878115D0086-3
(b)TERMINAL LUG 877225D0086-2
SOCKET T/C 11233333DC39-16S
SOCKET T/C 11243111DC39-20S
(a) Or approved alternate. Refer to SWPM 20-00-13.
(b) Or approved Equivalent. Refer to AEPL Drawing 7595071
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number / Specifica-
tion
(a)STRING TIE1 ROLL18XTZ, 23XTZ
(DMS 2089)
or
Equivalent
(b)COATING CHEMICAL FILM,
LIQUID
As RequiredAlodine 1200S
(DPM 1453-5)
or
Equivalent
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NotesNameQTYPart Number / Specifica-
tion
(c)PRIMER, FR4 Oz515X347 Base with
910X527 Catalyst
(DMS 1786)
or
Equivalent
(d)ENAMEL, HIGH SOLIDS
EPOXY TOPCOAT, GLOSS
WHITE
1 Oz446-21-Ser Base with 530
Activator
(DMS 2433)
or
Equivalent
(a) Can be purchased from: Gudenbrod, Incorporated, 274 Shoemaker Road, Pottstown,
Pennsylvania 19464, CAGE: 82110
(b) Can be purchased from: Henkel Corporation, 32100 Stephenson Highway, Madison
Heights, Michigan 48071, CAGE: 1N6B3
(c) Can be purchased from: PRC-Desoto International, Incorporated, 11601 United Street,
Mojave, California 93501, CAGE: 85570
(d) Can be purchased from: Akzo Nobel Aerospace Coatings, Incorporated, 1 East Water
Street, Waukegan, Illinois 60085, CAGE: 91342
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
Group 1-3:
None.
Group 4:
NotesQTYNameExisting Part Number
(a)4Relay5D0163-1
(a) Keep the part if there are other uses for it.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
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F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 41

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY
ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE
CAN OCCUR.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Equivalent parts are listed in the AEPL, Drawing 7595071.
3. Use the approved fastener and process material substitutions, in accordance with
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 limits to tighten nuts and bolts are in MD-11 SRM 51.
7. Refer to these SWPM chapters for applicable operations, as accepted procedures:
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Identification of Electrical Wire - CommercialSWPM 20-00-03
General Maintenance Practices - ElectricalSWPM 20-00-09
Electrical Wire CodesSWPM 20-00-13
Electrical Wire End Termination Codes and Tool CodesSWPM 20-00-16
Wiring Installation - Maintenance PracticesSWPM 20-10-01
Wire Splicing - Maintenance PracticesSWPM 20-10-03
General Installation Hardware - Maintenance PracticesSWPM 20-20-03
Amphenol Series 48 Electrical Connectors - Maintenance
Practices
SWPM 20-31-01
Electrical Bonding - Maintenance PracticesSWPM 20-50-01
8. Obey all of the warnings and cautions given in the specified manual sections.
9. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
10. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U' or 'Y' in place of the '-' (dash) in the part number. It is permitted
to install parts identified with a 'U' or 'Y' as an alternative to the '_' (dash) number
part. Boeing Drawing SE10000000, Sheets 5.0 and 6.0 contain more data.
11. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
12. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
13. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
14. Review and understand all general notes of Service Rework Drawings that follow:
SheetsService Rework Drawing
3, 3.1, 3.2, 3.3, 3.4SR11280076
3, 3.1, 3.2SR11280134
15. The FCD is intended for use with ONLY airplane Original Equipment Manufacturer
(OEM) certified fuel pumps and fuel pump housings, including OEM pump/housing
spare parts and parts repaired per OEM approved repair instructions.
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B. WORK INSTRUCTIONS
Group 1, Configuration 1-2:
1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted
procedure.
2. Gain access to the area of change. Refer to the table below:
Refer toLocationDoor Number
MD11 AMM 06-31-02Avionics Equipment Compartment112AB
MD11 AMM 06-31-03Forward Equipment Panel112CZ
MD11 AMM 06-31-13Center Accessory Compartment (CAC)131AB
MD11 AMM 06-31-12Electrical Power Center (EPC) components (Bay 1)131AZ
EPC components (Bay 2)131BZ
EPC components (Bay 3)132AZ
MD11 AMM 06-37-00Main Landing Gear (MLG) door, right-side741AR
3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM
28-22-13 as an accepted procedure.
Service Rework Drawing SR11280076 SheetsLocation
7, 8, 9Generator 1 EPC equipment panel
7, 8, 10Upper EPC equipment panel
7, 8, 11Generator 3 EPC equipment panel
7, 8.1, 12AC forward equipment panel
4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076
sheets 25 and 26.
5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that
follows:
Service Rework Drawing SR11280076 SheetsLocation
6.14, 6.18, 6.22, 6.29, 6.38, 6.42, 7, 8, 9, 13Generator 1 EPC equipment panel
6.17, 6.27, 6.28, 6.42, 7, 8, 9, 14, 17, 18, 19Generator 2 EPC equipment panel
6.16, 6.19, 6.20, 6.23, 6.26, 6.42, 7, 8, 11, 15Generator 3 EPC equipment panel
6.24, 6.37, 6.42, 7, 8.1, 12, 16AC forward equipment panel
6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1Upper EPC equipment panel
7, 8, 20, 21, 22, 23, 24CAC
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### Page 44

6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in steps 7 and
8 below. Refer to MD11 AMM 28-22-10 as an accepted procedure.
7. Change terminal board installation and fuel boost/transfer pump wire termination in accordance
with the table that follows:
Service Rework Drawing SR11280134
Sheets
Equipment Item
Numbers
Location
8.4, 10, 11, 12, 13, 15, 303.201S3-804, S3-805MLG wheel well, right-side
8. Change fuel boost/transfer pump wire termination in accordance with the table that follows:
Service Rework Drawing
SR11280134 Sheets
Equipment Item Num-
bers
Location
8.4, 10, 14, 303.201S3-802, S3-803Center and lower wing fuel
tanks
8.2, 8.3, 10, 16, 304.201S3-373, S3-375, S3-376Wing trailing edge, right-side
8.2, 8.3, 10, 17, 18, 304.201S3-374, S3-377Wing leading edge, right-side
8.1, 8.2, 10, 19, 304.201S3-369, S3-370, S3-372Wing trailing edge, left-side
8.1, 8.2, 10, 20, 21, 304.201S3-368, S3-371Wing leading edge, left-side
8.6, 10, 23, 305.201S3-755, S3-764, S3-765Tail fuel tank, front spar rear
horizontal
9. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.
10. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.
11. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.
12. Close access.
13. Put the airplane back to a serviceable condition.
Group 1, Configuration 3:
1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted
procedure.
2. Gain access to the area of change. Refer to the table below:
Refer toLocationDoor Number
MD11 AMM 06-31-02Avionics Equipment Compartment112AB
MD11 AMM 06-31-03Forward Equipment Panel112CZ
MD11 AMM 06-31-13Center Accessory Compartment (CAC)131AB
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### Page 45

Refer toLocationDoor Number
MD11 AMM 06-31-12Electrical Power Center (EPC) components (Bay 1)131AZ
EPC components (Bay 2)131BZ
EPC components (Bay 3)132AZ
MD11 AMM 06-37-00Main Landing Gear (MLG) door, right-side741AR
3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM
28-22-13 as an accepted procedure.
Service Rework Drawing SR11280076 SheetsLocation
7, 8, 9Generator 1 EPC equipment panel
7, 8, 10Upper EPC equipment panel
7, 8, 11Generator 3 EPC equipment panel
7, 8.1, 12AC forward equipment panel
4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076
sheets 25 and 26.
5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that
follows:
Service Rework Drawing SR11280076 SheetsLocation
6.14, 6.18, 6.22, 6.29, 6.38, 6.42, 7, 8, 9, 13Generator 1 EPC equipment panel
6.17, 6.27, 6.28, 6.42, 7, 8, 9, 14, 17, 18, 19Generator 2 EPC equipment panel
6.16, 6.19, 6.20, 6.23, 6.26, 6.42, 7, 8, 11, 15Generator 3 EPC equipment panel
6.24, 6.37, 6.42, 7, 8.1, 12, 16AC forward equipment panel
6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1Upper EPC equipment panel
7, 8, 20, 21, 22, 23, 24CAC
6. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.
7. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.
8. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.
9. Close access.
10. Put the airplane back to a serviceable condition.
Group 2, Configuration 1-2:
1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted
procedure.
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### Page 46

2. Gain access to the area of change. Refer to the table below:
Refer toLocationDoor Number
MD11 AMM 06-31-02Avionics Compartment (AC)112AB
MD11 AMM 06-31-03Forward Equipment Panel112CZ
MD11 AMM 06-31-13Center Accessory Compartment (CAC)131AB
MD11 AMM 06-31-12Electrical Power Center (EPC) components (Bay 1)131AZ
EPC components (Bay 2)131BZ
EPC components (Bay 3)132AZ
MD11 AMM 06-37-00Main Landing Gear (MLG) door, right-side741AR
MD11 AMM 06-31-27Forward Auxiliary Tank Structure127RA
127SA
127TA
127UA
3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM
28-22-13 as an accepted procedure.
Service Rework Drawing SR11280076 SheetsLocation
7, 8, 9, 9.2Generator 1 EPC equipment panel
7, 8, 10Upper EPC equipment panel
7, 8, 11.1Generator 3 EPC equipment panel
7, 8.1, 12AC forward equipment panel
4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076
sheets 25 and 26.
5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that
follows:
Service Rework Drawing SR11280076 SheetsLocation
6.14, 6.18, 6.22, 6.29, 6.30, 6.39, 6.42, 7, 8, 9,
9.2, 13, 13.2
Generator 1 EPC equipment panel
6.17, 6.27, 6.28, 6.42, 7, 8, 9, 14, 17, 18, 19Generator 2 EPC equipment panel
6.16, 6.19, 6.20, 6.23, 6.26, 6.32, 6.42, 7, 8, 11.1,
15.1
Generator 3 EPC equipment panel
6.24, 6.37, 6.42, 7, 8.1, 12, 16AC forward equipment panel
6.15, 6.21, 6.25, 6.41, 6.42, 7, 8, 10, 14.1Upper EPC equipment panel
7, 8, 20, 21, 22, 23, 24CAC
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### Page 47

6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in steps 7 and
8 below. Refer to MD11 AMM 28-22-10 as an accepted procedure.
7. Change terminal board installation and fuel boost/transfer pump wire termination in accordance
with the table that follows:
Service Rework Drawing SR11280134
Sheets
Equipment Item
Numbers
Location
8.4, 10, 11, 12, 13, 15, 303.201S3-804, S3-805MLG wheel well, right-side
8. Change fuel boost/transfer pump wire termination in accordance with the table that follows:
Service Rework
Drawing SR11280134
Sheets
Connector Recepta-
cle Item Number
Equipment Item
Numbers
Location
8.4, 10, 14, 303.201-S3-802, S3-803Center and lower wing
fuel tanks
8.2, 8.3, 10, 16,
304.201
-S3-373, S3-375, S3-
376
Wing trailing edge,
right-side
8.2, 8.3, 10, 17, 18,
304.201
-S3-374, S3-377Wing leading edge,
right-side
8.1, 8.2, 10, 19,
304.201
-S3-369, S3-370, S3-
372
Wing trailing edge, left-
side
8.1, 8.2, 10, 20, 21,
304.201
-S3-368, S3-371Wing leading edge, left-
side
8.5, 10, 22, 301.201,
302.201
R5-9664, R5-9665-Forward auxiliary fuel
tank
8.6, 10, 23, 305.201-S3-755, S3-764, S3-
765
Tail fuel tank, front spar
rear horizontal
9. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.
10. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.
11. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.
12. Close access.
13. Put the airplane back to a serviceable condition.
Group 2, Configuration 3:
1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted
procedure.
2. Gain access to the area of change. Refer to the table below:
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### Page 48

Refer toLocationDoor Number
MD11 AMM 06-31-02Avionics Compartment (AC)112AB
MD11 AMM 06-31-03Forward Equipment Panel112CZ
MD11 AMM 06-31-13Center Accessory Compartment (CAC)131AB
MD11 AMM 06-31-12Electrical Power Center (EPC) components (Bay 1)131AZ
EPC components (Bay 2)131BZ
EPC components (Bay 3)132AZ
MD11 AMM 06-37-00Main Landing Gear (MLG) door, right-side741AR
MD11 AMM 06-31-27Forward Auxiliary Tank Structure127RA
127SA
127TA
127UA
3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM
28-22-13 as an accepted procedure.
Service Rework Drawing SR11280076 SheetsLocation
7, 8, 9, 9.2Generator 1 EPC equipment panel
7, 8, 10Upper EPC equipment panel
7, 8, 11.1Generator 3 EPC equipment panel
7, 8.1, 12AC forward equipment panel
4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076
sheets 25 and 26.
5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that
follows:
Service Rework Drawing SR11280076 SheetsLocation
6.14, 6.18, 6.22, 6.29, 6.30, 6.39, 6.42, 7, 8, 9,
9.2, 13, 13.2
Generator 1 EPC equipment panel
6.17, 6.27, 6.28, 6.42, 7, 8, 9, 14, 17, 18, 19Generator 2 EPC equipment panel
6.16, 6.19, 6.20, 6.23, 6.26, 6.32, 6.42, 7, 8, 11.1,
15.1
Generator 3 EPC equipment panel
6.24, 6.37, 6.42, 7, 8.1, 12, 16AC forward equipment panel
6.15, 6.21, 6.25, 6.41, 6.42, 7, 8, 10, 14.1Upper EPC equipment panel
7, 8, 20, 21, 22, 23, 24CAC
6. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.
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### Page 49

7. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.
8. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.
9. Close access.
10. Put the airplane back to a serviceable condition.
Group 3, Configuration 1-2:
1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted
procedure.
2. Gain access to the area of change. Refer to the table below:
Refer toLocationDoor Number
MD11 AMM 06-31-02Avionics Compartment (AC)112AB
MD11 AMM 06-31-03Forward Equipment Panel112CZ
MD11 AMM 06-31-13Center Accessory Compartment (CAC)131AB
MD11 AMM 06-31-12Electrical Power Center (EPC) components (Bay 1)131AZ
EPC components (Bay 2)131BZ
EPC components (Bay 3)132AZ
MD11 AMM 06-37-00Main Landing Gear (MLG) door, right-side741AR
3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM
28-22-13 as an accepted procedure.
Service Rework Drawing SR11280076 SheetsLocation
7, 8, 9.1, 9.2Generator 1 EPC equipment panel
7, 8, 10Upper EPC equipment panel
7, 8, 11.2Generator 3 EPC equipment panel
7, 8.1, 12AC forward equipment panel
4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076
sheets 25 and 26.
5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that
follows:
Service Rework Drawing SR11280076 SheetsLocation
6.14, 6.18, 6.22, 6.29, 6.31, 6.36, 6.38, 6.42, 7,
8, 9.1, 9.2, 13.1, 13.2
Generator 1 EPC equipment panel
6.17, 6.27, 6.28, 6.42, 7, 8, 9.1, 14, 17, 18, 19Generator 2 EPC equipment panel
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### Page 50

Service Rework Drawing SR11280076 SheetsLocation
6.16, 6.19, 6.20, 6.23, 6.26, 6.33, 6.35, 6.42, 7,
8, 11.2, 15.2
Generator 3 EPC equipment panel
6.24, 6.37, 6.42, 7, 8.1, 12, 16AC forward equipment panel
6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1Upper EPC equipment panel
7, 8, 20, 21, 22, 23, 24CAC
6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in steps 7 and
8 below. Refer to MD11 AMM 28-22-10 as an accepted procedure.
7. Change terminal board installation and fuel boost/transfer pump wire termination in accordance
with the table that follows:
Service Rework Drawing SR11280134
Sheets
Equipment Item
Numbers
Location
8.4, 10, 11, 12, 13, 15, 303.201S3-804, S3-805MLG wheel well, right-side
8. Change fuel boost/transfer pump wire termination in accordance with the table that follows:
Service Rework Drawing
SR11280134 Sheets
Equipment Item Num-
bers
Location
8.4, 10, 14, 303.201S3-802, S3-803Center and lower wing fuel
tanks
8.2, 8.3, 10, 16, 304.201S3-373, S3-375, S3-376Wing trailing edge, right-side
8.2, 8.3, 10, 17, 18, 304.201S3-374, S3-377Wing leading edge, right-side
8.1, 8.2, 10, 19, 304.201S3-369, S3-370, S3-372Wing trailing edge, left-side
8.1, 8.2, 10, 20, 21, 304.201S3-368, S3-371Wing leading edge, left-side
8.6, 10, 23, 305.201S3-755, S3-764, S3-765Tail fuel tank, front spar rear
horizontal
9. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.
10. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.
11. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.
12. Close access.
13. Put the airplane back to a serviceable condition.
Group 3, Configuration 3:
1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted
procedure.
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### Page 51

2. Gain access to the area of change. Refer to the table below:
Refer toLocationDoor Number
MD11 AMM 06-31-02Avionics Compartment (AC)112AB
MD11 AMM 06-31-03Forward Equipment Panel112CZ
MD11 AMM 06-31-13Center Accessory Compartment (CAC)131AB
MD11 AMM 06-31-12Electrical Power Center (EPC) components (Bay 1)131AZ
EPC components (Bay 2)131BZ
EPC components (Bay 3)132AZ
MD11 AMM 06-37-00Main Landing Gear (MLG) door, right-side741AR
3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM
28-22-13 as an accepted procedure.
Service Rework Drawing SR11280076 SheetsLocation
7, 8, 9.1, 9.2Generator 1 EPC equipment panel
7, 8, 10Upper EPC equipment panel
7, 8, 11.2Generator 3 EPC equipment panel
7, 8.1, 12AC forward equipment panel
4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076
sheets 25 and 26.
5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that
follows:
Service Rework Drawing SR11280076 SheetsLocation
6.14, 6.18, 6.22, 6.29, 6.31, 6.36, 6.38, 6.42, 7,
8, 9.1, 9.2, 13.1, 13.2
Generator 1 EPC equipment panel
6.17, 6.27, 6.28, 6.42, 7, 8, 9.1, 14, 17, 18, 19Generator 2 EPC equipment panel
6.16, 6.19, 6.20, 6.23, 6.26, 6.33, 6.35, 6.42, 7,
8, 11.2, 15.2
Generator 3 EPC equipment panel
6.24, 6.37, 6.42, 7, 8.1, 12, 16AC forward equipment panel
6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1Upper EPC equipment panel
7, 8, 20, 21, 22, 23, 24CAC
6. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.
7. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.
8. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.
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### Page 52

9. Close access.
10. Put the airplane back to a serviceable condition.
Group 4, Configuration 1-2:
1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted
procedure.
2. Gain access to the area of change. Refer to the table below:
Refer toLocationDoor Number
MD11 AMM 06-31-02Avionics Compartment (AC)112AB
MD11 AMM 06-31-03Forward Equipment Panel112CZ
MD11 AMM 06-31-13Center Accessory Compartment (CAC)131AB
MD11 AMM 06-31-12Electrical Power Center (EPC) components (Bay 1)131AZ
EPC components (Bay 2)131BZ
EPC components (Bay 3)132AZ
MD11 AMM 06-37-00Main Landing Gear (MLG) door, right-side741AR
3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM
28-22-13 as an accepted procedure.
NOTE: Some relays and associated wiring will be removed and not replaced.
Service Rework Drawing SR11280076 SheetsLocation
7, 8, 9.3, 9.4Generator 1 EPC equipment panel
7, 8, 10Upper EPC equipment panel
7, 8, 11.3Generator 3 EPC equipment panel
7, 8.1, 12AC forward equipment panel
4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076
sheets 25 and 26.
5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that
follows:
Service Rework Drawing SR11280076 SheetsLocation
6.14, 6.18, 6.22, 6.29, 6.34, 6.38, 6.42, 7, 8, 9.3,
13
Generator 1 EPC equipment panel
6.17, 6.27, 6.28, 6.42, 7, 8, 9.3, 14, 17, 18, 19Generator 2 EPC equipment panel
6.16, 6.19, 6.20, 6.23, 6.26, 6.34, 6.42, 7, 8, 11.3,
15
Generator 3 EPC equipment panel
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### Page 53

Service Rework Drawing SR11280076 SheetsLocation
6.24, 6.37, 6.42, 7, 8.1, 12, 16AC forward equipment panel
6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1Upper EPC equipment panel
7, 8, 20, 21, 22, 23, 24CAC
6. Gain access to fuel boost/transfer pump terminal boards and ground studs noted in steps 7 and
8 below. Refer to MD11 AMM 28-22-10 as an accepted procedure.
7. Change terminal board installation and fuel boost/transfer pump wire termination in accordance
with the table that follows:
Service Rework Drawing SR11280134
Sheets
Equipment Item
Numbers
Location
8.4, 10, 11, 12, 13, 15, 303.201S3-804, S3-805MLG wheel well, right-side
8. Change fuel boost/transfer pump wire termination in accordance with the table that follows:
Service Rework Drawing
SR11280134 Sheets
Equipment Item Num-
bers
Location
8.4, 10, 14, 303.201S3-802, S3-803Center and lower wing fuel
tanks
8.2, 8.3, 10, 16, 304.201S3-373, S3-375, S3-376Wing trailing edge, right-side
8.2, 8.3, 10, 17, 18, 304.201S3-374, S3-377Wing leading edge, right-side
8.1, 8.2, 10, 19, 304.201S3-369, S3-370, S3-372Wing trailing edge, left-side
8.1, 8.2, 10, 20, 21, 304.201S3-368, S3-371Wing leading edge, left-side
8.6, 10, 23, 305.201S3-755, S3-764, S3-765Tail fuel tank, front spar rear
horizontal
9. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.
10. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.
11. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.
12. Close access.
13. Put the airplane back to a serviceable condition.
Group 4, Configuration 3:
1. Open and safety fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted
procedure.
2. Gain access to the area of change. Refer to the table below:
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### Page 54

Refer toLocationDoor Number
MD11 AMM 06-31-02Avionics Compartment (AC)112AB
MD11 AMM 06-31-03Forward Equipment Panel112CZ
MD11 AMM 06-31-13Center Accessory Compartment (CAC)131AB
MD11 AMM 06-31-12Electrical Power Center (EPC) components (Bay 1)131AZ
EPC components (Bay 2)131BZ
EPC components (Bay 3)132AZ
MD11 AMM 06-37-00Main Landing Gear (MLG) door, right-side741AR
3. Remove fuel pump control relays in accordance with the table that follows. Refer to MD11 AMM
28-22-13 as an accepted procedure.
NOTE: Some relays and associated wiring will be removed and not replaced.
Service Rework Drawing SR11280076 SheetsLocation
7, 8, 9.3, 9.4Generator 1 EPC equipment panel
7, 8, 10Upper EPC equipment panel
7, 8, 11.3Generator 3 EPC equipment panel
7, 8.1, 12AC forward equipment panel
4. Change upper EPC equipment panel in accordance with Service Rework Drawing SR11280076
sheets 25 and 26.
5. Install Fault Current Detector (FCD), route and terminate wiring in accordance with the table that
follows:
Service Rework Drawing SR11280076 SheetsLocation
6.14, 6.18, 6.22, 6.29, 6.34, 6.38, 6.42, 7, 8, 9.3,
13
Generator 1 EPC equipment panel
6.17, 6.27, 6.28, 6.42, 7, 8, 9.3, 14, 17, 18, 19Generator 2 EPC equipment panel
6.16, 6.19, 6.20, 6.23, 6.26, 6.34, 6.42, 7, 8, 11.3,
15
Generator 3 EPC equipment panel
6.24, 6.37, 6.42, 7, 8.1, 12, 16AC forward equipment panel
6.15, 6.21, 6.25, 6.40, 6.42, 7, 8, 10, 14.1Upper EPC equipment panel
7, 8, 20, 21, 22, 23, 24CAC
6. Close fuel system circuit breakers. Refer to MD11 AMM 28-00-00 as an accepted procedure.
7. Do operational test of the fuel pumps. Refer to MD11 AMM 28-22-01 as an accepted procedure.
8. Do FCD Functional Test (BIT) in accordance with MD11 AMM 28-22-12.
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### Page 55

9. Close access.
10. Put the airplane back to a serviceable condition.
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MD11-28A133
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BOEING SERVICE BULLETIN MD11-28A133
ALERTALERT

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BOEING SERVICE BULLETIN MD11-28A133
ALERT  ALERT
Boeing Service Bulletin Input Survey
After review of this service bulletin, Boeing asks that the primary engineer fill out this survey to help Boeing
predict the quantity and timing of Boeing supplied kits. This survey is only to help schedule kit/part availability
based on a preliminary review and is not a commitment to order.
Airline:
Contact Name:
Date:
Contact E-mail:
• Yes  • No Have/will you recommend to your airline to accomplish this service bulletin?
- Yes  - No Would issuance of an NPRM change this decision?
_ Yes  No Would issuance of an AD change this decision?
When would you likely be starting this SB incorporation? Month/ Year
How many airplanes per month do you plan to accomplish? Airplane/Month
How many total airplanes do you plan to complete? Total Airplanes_
-or inspection Service Bulletins, are you planning to replace on condition, or a fleet campaign to replace on
all airplanes regardless of condition?
_ On Condition  Campaign
If you are not incorporating this Service Bulletin at this time will you please help us understand the reason/s
why? Your input will help us provide better customer support.
- Cost Prohibitive  _ Continue Inspections  L Other
Operator Comments:
Within 45 days of the SB issue, or as soon after as possible, please scan and send this to:
sbsolutions@boeing.com
Disclaimer: The data provided in this survey will be used for planning purposes only and does not  consitute a commitment on any part of the airlines to purchase the parts in question, nor does it consitute a  2285062
commitment on the part of Boeing to deliver the parts in question. This survey is a projection to help
Boeing forecast demand levels and timing to better support the customers schedule.
APPENDIX A: INPUT SURVEY
(SHEET 1 OF 1)
Original Issue: June 05, 2014
Export Controlled ECCN: 9E991 - BOEING  MD11-28A133
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  56 of 56

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