# Boeing Alert Service Bulletin MD11-28A143: No revision named

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### Page 1

McDonnell DouglasCommercial 
Airplanes
MD11
Service Bulletin
ALERT
Number: MD11-28A143
Original Issue: December 02, 2009
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and
Fuel Boost/Transfer Pump - Inspection/Replacement
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2009 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 7
A. Effectivity ................................................ 7
1. Airplanes ............................................. 7
2. Spares Affected ......................................... 8
B. Concurrent Requirements ....................................... 8
C. Reason ................................................. 8
D. Description ............................................... 8
E. Compliance .............................................. 9
F. Approval ............................................... 1 2
G. Manpower .............................................. 1 2
H. Weight and Balance Changes .................................... 1 3
I. Electrical Load Data ......................................... 1 3
J. References .............................................. 1 4
1. Existing Data .......................................... 1 4
2. Data supplied with this Service Bulletin ............................ 1 4
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 4
K. Publications Affected ........................................ 1 4
L. Interchangeability and Intermixability of Parts ........................... 1 5
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. Kits/Parts ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 2 1
3. Parts Modified and Reidentified ................................ 2 2
4. Parts Removed and Not Replaced .............................. 2 2
D. Parts Necessary to Change Spares ................................. 2 2
E. Special Tooling - Price and Availability ............................... 2 3
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 3
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 5
A. GENERAL INFORMATION ..................................... 2 5
B. WORK INSTRUCTIONS ....................................... 2 7
APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1 . . 35
APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N
60-84351 ............................................ 3 8
APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351 . . . 40
APPENDIX D: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER
60-84355-1 INSPECTION LOGIC DIAGRAM ......................... 4 3
APPENDIX E: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER
60-84351 INSPECTION LOGIC DIAGRAM .......................... 4 4
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McDonnell DouglasCommercial 
Airplanes
MD11
Service Bulletin
ALERT
SummaryNumber: MD11-28A143Original Issue: December 02, 2009
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and
Fuel Boost/Transfer Pump - Inspection/Replacement
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND
MD-11 and DC-10 operators have reported instances of fuel pump housing electrical connector assembly, part
number 60-84355-1, failures. Inspecting the fuel boost/transfer pump housing electrical connector assembly,
fuel boost/transfer pump, and replacing any non-serviceable part with a serviceable part as required based on
inspection results, will minimize the possibility of a potential ignition source in the fuel tanks and potential fuel
tank explosion. If not corrected, insulation resistance degradation and/or arcing in the potted backside of the
fuel boost/transfer pump housing electrical connector assembly could compromise the performance of the fuel
boost/transfer pump housing electrical connector assembly and result in a failure that can introduce an ignition
source into the fuel tank and potential fuel tank explosion.
ACTION
This service bulletin provides instructions to inspect/replace each fuel pump housing electrical connector assembly
and fuel boost/transfer pump.
EFFECTIVITY
MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes and repair procedures given in this
service bulletin.
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MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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McDonnell DouglasCommercial 
Airplanes
MD11
Service Bulletin
ALERT
Number: MD11-28A143
Original Issue: December 02, 2009
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Supply - Fuel Pump Housing Electrical Connector Assembly and
Fuel Boost/Transfer Pump - Inspection/Replacement
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
NOTE: The fuel pump housing electrical connector replacement with part number 60-84351 was
done on fuselage number 466 prior to the original issue of this service bulletin in
accordance with Drawing SP11280022 and FAA Alternative Method of Compliance
(AMOC) approval letter with referenced Boeing letter CP-L4L-09-00243.
This service bulletin is applicable to airplanes that have installed fuel pump housing electrical
connector assembly part number 60-84355-1 in accordance with Service Bulletin MD11-28A138.
DESCRIPTIONCONFIGURATIONGROUP
Applicable to airplanes without ER3060 gallon forward auxiliary.-1
Applicable to airplanes with ER3060 gallon forward auxiliary fuel
tanks.
-2
Airplane Models:
MD-11, MD-11F
GroupFuselage Num-
ber
1447 - 589
2590
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GroupFuselage Num-
ber
1591 - 596
2597
1598 - 607
2608
1609 - 612
2613
1614
2615
1616 - 646
2. Spares Affected
Examine your spares supply for the parts or components identified in below. For the recommended
use Paragraph 2.D., Parts Necessary to Change Spares. If any parts or components are found.
NamePart Number
Pump Housing60-843-3
Pump Housing60-845-3
Connector60-84355-1
B. Concurrent Requirements
None.
C. Reason
MD-11 and DC-10 operators have reported instances of fuel pump housing electrical connector assembly,
part number 60-84355-1, failures. Inspecting the fuel boost/transfer pump housing electrical connector
assembly, fuel boost/transfer pump, and replacing any non-serviceable part with a serviceable part as
required based on inspection results, will minimize the possibility of a potential ignition source in the
fuel tanks and potential fuel tank explosion. If not corrected, insulation resistance degradation and/or
arcing in the potted backside of the fuel boost/transfer pump housing electrical connector assembly
could compromise the performance of the fuel boost/transfer pump housing electrical connector assembly
and result in a failure that can introduce an ignition source into the fuel tank and potential fuel tank
explosion.
D. Description
This service bulletin provides instructions to inspect/replace fuel pump housing electrical connector
assembly and fuel boost/transfer pump.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Group 1:
Affected Maintenance Zones
ZoneModel
141, 142, 311, 515, 517, 531, 532, 533, 541,
615, 617, 632, 633, 641
MD-11, MD-11F
Group 2:
Affected Maintenance Zones
ZoneModel
141, 142, 143, 311, 515, 517, 531, 532, 533,
541, 615, 617, 632, 633, 641
MD-11, MD-11F
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Federal Aviation Administration (FAA) Airworthiness Directive No. FAA AD 2007-15-05 is related to
this service bulletin.
Refer to Appendix D and E for a logic diagram of the work instructions.
TABLE 1: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84355-1 AND FUEL
BOOST/TRANSFER PUMP - REPLACEMENT/INSPECTION
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
(a)Within 10 months af-
ter the original issue
date on this service
bulletin.
Replace fuel pump electrical
connector assemblies with P/N
60-84351 and restore in accor-
dance with Accomplishment In-
structions 3.B. Part 2 and Part
5.
All Airplanes.
OR
Within 10 months af-
ter the original issue
date on this service
bulletin.
Do continuity, resistance and
insulation resistance inspection
in accordance with Accomplish-
ment Instructions 3.B. Part 3.
AND
Replace fuel pump electrical
connector assemblies with P/N
60-84351 and restore in accor-
dance with Accomplishment In-
structions 3.B. Part 2 and Part
5.
(a)Within 12 months af-
ter inspection.
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TABLE 1: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84355-1 AND FUEL
BOOST/TRANSFER PUMP - REPLACEMENT/INSPECTION
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
Before further flight.Do restoration in accordance
with Accomplishment Instruc-
tions 3.B. Part 5.
(Serviceable Fuel pump and hous-
ing electrical connector assembly)
Fuel pump housing electrical con-
nector assembly wiring resistance
reading is less than or equal to 2.5
ohms and terminal E is open.
AND
Fuel boost/transfer pump resistance
reading is less than or equal to 2.5
ohms and pin E is open.
AND
Fuel pump housing electrical con-
nector assembly wiring insulation
resistance reading is greater than
or equal to 10 gigaohm.
Before further flight.Replace fuel boost/transfer
pump and restore in accordance
with Accomplishment Instruc-
tions 3.B. Part 3 and Part 5.
(Defective Fuel boost/transfer
pump)
Fuel boost/transfer pump resistance
reading is greater than 2.5 ohms or
pin E is not open and fuel pump
housing electrical connector assem-
bly wiring resistance reading is less
than or equal to 2.5 ohms and ter-
minal E is open and fuel pump
housing electrical connector assem-
bly wiring insulation resistance
reading is greater than or equal to
10 gigaohm.
(a)Before further flight.Replace fuel pump electrical
connector assemblies with P/N
60-84351 and restore in accor-
dance with Accomplishment In-
structions 3.B. Part 2 and Part
5.
(Defective Fuel pump housing
electrical connector assembly)
Fuel pump housing electrical con-
nector assembly wiring resistance
reading is greater than 2.5 ohms or
terminal E is not open and fuel
boost/transfer pump resistance
reading is less than or equal to 2.5
ohms and pin E is open.
OR
Fuel pump housing electrical con-
nector assembly wiring insulation
resistance reading is less than 10
gigaohm.
(a) REFER TO TABLE 2 AFTER REPLACEMENT OF FUEL PUMP HOUSING ELECTRICAL CONNECTOR
ASSEMBLY P/N 60-84355-1 WITH P/N 60-84351.
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TABLE 2: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84351 AND FUEL
BOOST/TRANSFER PUMP - INSPECTION
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
18 MonthsWithin 18 months af-
ter P/N 60-84351 in-
stallation.
Do continuity, resistance and
insulation resistance inspection
in accordance with Accomplish-
ment Instructions 3.B. Part 4.
All Airplanes
Before further flight.Do restoration in accordance
with Accomplishment Instruc-
tions 3.B. Part 5.
(Serviceable Fuel pump and hous-
ing electrical connector assembly)
Fuel pump housing electrical con-
nector assembly wiring resistance
reading is less than or equal to 2.5
ohms and terminal E is open.
AND
Fuel boost/transfer pump resistance
reading is less than or equal to 2.5
ohms and pin E is open.
AND
Fuel pump housing electrical con-
nector assembly wiring insulation
resistance reading is greater than
or equal to 10 megaohm.
Before further flight.Replace fuel boost/transfer
pump and restore in accordance
with Accomplishment Instruc-
tions 3.B. Part 4 and Part 5.
(Defective Fuel boost/transfer
pump)
Fuel boost/transfer pump resistance
reading is greater than 2.5 ohms or
pin E is not open and fuel pump
housing electrical connector assem-
bly wiring resistance reading is less
than or equal to 2.5 ohms and ter-
minal E is open and fuel pump
housing electrical connector assem-
bly wiring insulation resistance
reading is greater than or equal to
10 megaohm.
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TABLE 2: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY P/N 60-84351 AND FUEL
BOOST/TRANSFER PUMP - INSPECTION
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
Before further flight.Replace fuel pump electrical
connector assemblies with P/N
60-84351 and restore in accor-
dance with Accomplishment In-
structions 3.B. Part 4 and Part
5.
(Defective Fuel pump housing
electrical connector assembly)
Fuel pump housing electrical con-
nector assembly wiring resistance
reading is greater than 2.5 ohms or
terminal E is not open and fuel
boost/transfer pump resistance
reading is less than or equal to 2.5
ohms and pin E is open.
OR
Fuel pump housing electrical con-
nector assembly wiring insulation
resistance reading is less than 10
megaohm.
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.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
In addition, the Manager of the FAA Los Angles 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 (l) of FAA AD 2007-15-05. All provisions of FAA AD 2007-15-05 that
are not specifically referenced in the above statement remain fully applicable and must be complied
with.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
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 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
8.08.01Open Access
15.030.02Inspect
*0.1 - 43.0*0.2 - 86.02Change
8.08.01Close Access
1.02.02Test
*32.1 - 75.0*48.2 -134.0TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
9.09.01Open Access
17.034.02Inspect
*0.1 - 48.0*0.2 - 96.02Change
9.09.01Close Access
1.02.02Test
*36.1 - 84.0*54.2 - 150.0TOTAL FOR EACH AIRPLANE
*A range of total task hours and elapsed hours and given for inspection per airplane. Actual task hours
and elapsed hours for the change are contingent upon inspection findings and are to be estimated by
the operator.
H. Weight and Balance Changes
Weight and balance changes affected by incorporation of this service bulletin are contingent upon the
changes to each particular airplane. Weight data is to be computed by the operator by weighing parts
removed and parts installed during this change. Necessary revisions should be made to the appropriate
airplane weight and balance report.
I. Electrical Load Data
Not changed.
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J. References
1. Existing Data
a. Boeing Service Bulletin MD11-28A138.
b. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-13, 20-00-16, 20-10-01,
20-20-01, 20-20-02, 20-20-03, 20-31-00, and 20-50-01.
c. MD11 Aircraft Maintenance Manual (AMM) 12-11-03, 28-00-00, 28-22-01, 28-22-02 and
28-22-10.
d. MD11 Structural Repair Manual (SRM) 51.
e. FAA Airworthiness Directive (FAA) 2007-15-05.
f. Wiring Diagram Manual (WDM) 28-22-01, 28-22-02, 28-22-03, 28-22-04 and 28-22-05.
g. Crane Hydro-Aire Service Information Letters 60-847-3-1 and 60-843-845-3-28-2.
h. FAA Alternative Method of Compliance (AMOC) approval letter with referenced Boeing letter
CP-L4L-09-00243.
2. Data supplied with this Service Bulletin
No data is supplied with this service bulletin. To obtain the data necessary to support this service
bulletin submit a data request to:
Data and Services Management
MS D800-0019
3855 Lakewood Boulevard
Long Beach, California 90846
Phone: (562) 593-6996
Fax: (562) 593-2001
E-mail: dse.boecom@boeing.com
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
-EDWGELEC INSTL - FUEL PUMP ELECTRICAL
CONNECTOR
SR11280084
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
K. Publications Affected
1. Publications:
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Chapter-SectionPublication
28-14 and 28-22Fault Isolation Manual
28-13 and 28-22Illustrated Parts Catalog
28-22Aircraft Maintenance Manual
28Maintenance Planning Data
28-22Wiring Diagram Manual Equipment List
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
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown
below. If there is a limit to the quantity of available kits, a supply sequence is given by Spares. More
kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date
Boeing gets the purchase order.
Unit Price thru
November 30,
2010
ROLT (Weeks)NamePart Number
$267.0013SERVICE KITSR11280084-3
41.0013SERVICE KITSR11280084-5
9.0013SERVICE KITSR11280084-7
155.0013SERVICE KITSR11280084-9
526.0013SERVICE KITSR11280084-11
526.0013SERVICE KITSR11280084-13
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
After the Unit Price date, new price ROLT data is applicable. Prices are in United States dollars. Terms:
Net 30 days.
Reference this service bulletin and submit your purchase order by one of the methods that follow:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Mail to:
Spares Customer Support - MC 36-65
Boeing Spares Department
P.O. Box 3707
Seattle, Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes and repair procedures given
in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
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Group 1:
NotesNameQTYNew Part Number
(a)KIT4SR11280084-3
(a)KIT8SR11280084-5
(a)KIT2SR11280084-7
(a)KIT3SR11280084-9
(a) Total quantity required per airplane.
Group 1:
SR11280084
NotesNameQTYNew Part Number
-9-7-5-3
SLEEVE.1..10-35916-16
GROMMET.1..10-60766-8
NUT GROMMET ASSY1.1.10-74916-8
COMB...12768771-1
(a)SCREW11113D0005-3-12
(a)TERMINAL LUG 76553335D0086-25
(a)TERMINAL LUG 766.2225D0086-26
CLAMP1...687-118NF08
FERRULE...17D0294-1
(a)FERRULE ASSY1...9D0067-4
(a)BAND,RETAINING1...9D0180-2
(a)PIN...29D0196-1
(a)BUSHING...19D0197-1
GLAND NUT...1M8700-7/3
WASHER3333MS35338-137
LOCKWASHER1111MS35338-43
NUT3333MS35649-284
WASHER3333NAS1149CN832R
WASHER1111NAS1149F0332P
OVERBRAID2 FTNEQL48830
(b)TUBING2 FTSR11280084-15
(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.
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Group 1:
SR11280084
NotesNameQTYNew Part Number
-9-7-5-3
(b) Material specification DMS 2380 Class 1 or approved Equivalent.
Group 2:
SR11280084
NotesNameQTYNew Part Number
(a)KIT1SR11280084-11
(a)KIT1SR11280084-13
(a)KIT4SR11280084-3
(a)KIT8SR11280084-5
(a)KIT2SR11280084-7
(a)KIT3SR11280084-9
(a) Total quantity required per airplane.
Group 2:
SR11280084
NotesNameQTYNew Part Number
-13-11-9-7-5-3
SLEEVE...1..10-35916-16
GROMMET...1..10-60766-8
NUT GROMMET ASSY..1.1.10-74916-8
COMB.....12768771-1
(a)SCREW1111113D0005-3-12
(a)TERMINAL LUG 765..53335D0086-25
(a)TERMINAL LUG 766...2225D0086-26
CLAMP..1...687-118NF08
FERRULE.....17D0294-1
(a)FERRULE ASSY..1...9D0067-4
(a)BAND,RETAINING..1...9D0180-2
(a)PIN.....29D0196-1
(a)BUSHING.....19D0197-1
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Group 2:
SR11280084
NotesNameQTYNew Part Number
-13-11-9-7-5-3
PIN T/C 112755....DC64-16P
GLAND NUT.....1M8700-7/3
(a)CONNECTOR1.....MS3450L16-8P
(a)CONNECTOR.1....MS3450L16-8PX
WASHER..3333MS35338-137
LOCKWASHER111111MS35338-43
NUT..3333MS35649-284
WASHER..3333NAS1149CN832R
WASHER111111NAS1149F0332P
OVERBRAID2 FTNEQL48830
(c)TUBING2 FTSR11280084-15
(b)WIRE KIT.1....SR11280084-101
(b)WIRE KIT1.....SR11280084-102
(b)WIRE KIT.1....SR11280084-103
(b)WIRE KIT1.....SR11280084-104
(a) Or approved Equivalent, refer to AEPL, Drawing 7595071.
(b) Refer to Wire Kit Components Table.
(c) Material specification DMS 2380 Class 1 or approved Equivalent.
Group 2:
Wire Kit SR11280084
NotesNameQTYNew Part Number
-104-103-102-101
(a)TERMINAL LUG T/C 766115D0086-26
(a)WIRE CODE 8017 FT7 FT2 FT2 FTD2426-1C-16NM
PLUG1DC62L16SJ8SN
PLUG1DC62L16SJ8SX
PIN T/C 112711DC64-16P
SKT T/C 11255511DC65-16SS
(a) Or approved Equivalent.
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2. Parts and Materials Supplied by the Operator
NOTE: The items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator,
show the total quantity necessary for each airplane unless noted otherwise.
Group 1:
NotesNameQTYNew Part Number / Specifica-
tion
(a)CONNECTOR ASSY1760-84351
(a) (c)PUMP ASSY1760-847-X
(a)PACKING17M25988/1-019
(a)SCREW68LL500D4-6
Or
ES500D4-6
(b)TAPE1 Inch x .030
Inch x 12 Feet
SR11280084-17
(DMS 2186 Type 2)
Or
AR 386
Or
Equivalent
CAGEHydro-Aire, Incorporated(a) Can be purchased from:
819823000 Winona Avenue
Burbank, California 91504-2540 USA
02988Freudenberg-NOK(b) Can be purchased from:
65 Spruce Street
Tillsonburg, Ontario N4G 4H3 Canada
(c) Refer to Illustrated Parts Catalog (IPC) for applicable fuel boost/transfer pump configuration.
Group 2:
NotesNameQTYNew Part Number / Specifica-
tion
(a)CONNECTOR ASSY1960-84351
(a) (c)PUMP ASSY1960-847-X
(a)PACKING19M25988/1-019
(a)SCREW76LL500D4-6
Or
ES500D4-6
(b)TAPE1 Inch x .030
Inch x 12 Feet
SR11280084-17
(DMS 2186 Type 2)
Or
AR 386
Or
Equivalent
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Group 2:
NotesNameQTYNew Part Number / Specifica-
tion
CAGEHydro-Aire, Incorporated(a) Can be purchased from:
819823000 Winona Avenue
Burbank, California 91504-2540 USA
02988Freudenberg-NOK(b) Can be purchased from:
65 Spruce Street
Tillsonburg, Ontario N4G 4H3 Canada
(c) Refer to IPC for applicable fuel boost/transfer pump configuration.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
To get parts shown below, contact the Crane Spares Department at (818) -526-2500 or FAX to
(818)-526-2658.
NotesNameNew Part Number / Specifica-
tion
(a) (d)CONNECTOR ASSY60-84351
(a) (d)PACKINGM25988/1-019
(a) (d)SCREWLL500D4-6
Or
ES500D4-6
(b) (c)TAPESR11280084-17
(DMS 2186 Type 2)
Or
AR 386
Or
Equivalent
CAGEHydro-Aire, Incorporated(a) Can be purchased from:
819823000 Winona Avenue
Burbank, California 91504-2540 USA
02988Freudenberg-NOK(b) Can be purchased from:
65 Spruce Street
Tillsonburg, Ontario N4G 4H3 Canada
(c) Stock size 1 inch x .030 inch x 12 feet.
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NotesNameNew Part Number / Specifica-
tion
(d) Use applicable quantities to revise spare 60-843-3 and 60-845-3 fuel pump housing
assemblies. Replace spare 60-84355-1 with 60-84351 as needed.
E. Special Tooling - Price and Availability
The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this
Service Bulletin. Tool price and supply data are not given.
F. Special Tooling Necessary to do this Service Bulletin
To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.
Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be
necessary. Examine operator tool supply to make sure all necessary tools are available.
CAGESupplierNameTool / Kit Number
0HYG7Fluke CorporationModel 10Multimeter
1420 75TH Street SouthwestOr
Everett, Washington 98206Equivalent
0PK96Quadtech, IncorporatedModel 1864Megohm meter
5 Clock Tower Place, Suite 210Or
Maynard, Massachusetts 01754Equivalent
* An Equivalent Megohm meter must be able to apply voltage at 100+/-10 Volts DC and be current limited
to 5 Milliamps.
A T67291 or T67291-1 test tool/alternate tool is required to accomplish this inspection. Refer to Crane
Hydro-Aire Service Information Letter 60-847-3-1.
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### Page 25

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY
ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE
CAN OCCUR.
WARNING: WHILE YOU DO WORK IN THE TAILCONE AREA, MAKE SURE THAT YOU OBEY
ALL SAFETY PRECAUTIONS. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH
OR INJURY TO PERSONS CAN OCCUR.
CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Equivalent parts are listed in the AEPL, Drawing 7595071.
3. Use the approved fastener and process material substitutions, in accordance with
MD11 SRM, Chapter 51.
4. If the length of any fastener specified in this service bulletin does not meet the
installation standards in SRM Chapter 51, then a fastener of the same specification,
or an approved substitute, with a length which meets the installation standards in
SRM Chapter 51 may be used. Not applicable to Crane Hydro-Aire fuel pump or fuel
pump housing or attaching parts.
5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is
the maximum thickness which may be used under fastener head or nut to counteract
accumulation of tolerances.
EXCEPTION: When the available fastener length increments are greater than
1/16-inch, a 3/16-inch thick stack of the same type washers may be used.
6. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch.
– Torque limits to tighten nuts and bolts are in SRM, Chapter 51.
7. Refer to these SWPM chapters for applicable operations, as accepted procedures:
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– TITLECHAPTER
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
FABRICATING AND INSTALLING WIRE HARNESSES - COMMERCIALSWPM 20-10-01
TERMINALS - MAINTENANCE PRACTICESSWPM 20-20-01
TERMINAL BLOCKS - MAINTENANCE PRACTICESSWPM 20-20-02
GENERAL INSTALLATIONS HARDWARE - MAINTENANCE PRACTICESSWPM 20-20-03
ELECTRICAL CONNECTORS - MAINTENANCE PRACTICESSWPM 20-31-00
ELECTRICAL BONDING - MAINTENANCE PRACTICESSWPM 20-50-01
8. Refer to Wiring Diagram Manual (WDM) for applicable wiring diagrams as follows:
– WIRING DIAGRAMLOCATION
28-22-01Tank 1
28-22-02Tank 2
28-22-03Tank 3
28-22-04Aux Tank *
28-22-05Tail Tank
* Including Fwd Aux Tanks (If Installed).
9. Obey all of the warnings and cautions given in the specified manual sections.
10. Review and understand all general notes of Service Rework Drawing SR11280084
sheets 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.7.1, 3.8, 3.9, 3.10 and 7 before start of
modification.
11. 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.
12. Any protrusion of threads is acceptable provided that the threads do not rub or ride
against nearby wire assemblies or components.
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13. Access panel numbers and locations may vary.
14. Identify and note location of wires prior to removal from terminal strip and/or ground
stud.
15. The inspection order of operation procedures outlined in Parts 3 and 4 of Paragraph
3.B., Work Instructions must be followed. The instructions identified in Paragraph
3.B., Work Instructions give the recommended sequence of steps for which pump
location to inspect. The sequence of steps to inspect the pump locations can be
changed.
B. WORK INSTRUCTIONS
PART 1 (ACCESS/PREPARATION)
WARNING: FUEL TANKS MUST BE FILLED TO SPECIFIED LEVEL OR DRAINED, PURGED, AND
SAFE FOR MAINTENANCE. THIS WILL PREVENT INJURY TO PERSONS AND
DAMAGE TO EQUIPMENT.
1. Make sure fuel tanks are filled to specified level or defuel, purge, and make fuel system safe for
maintenance. Refer to MD11 AMM 12-11-03 and MD11 AMM 28-00-00 as accepted procedures.
Minimum Fuel LevelTank
KilogramPounds
9070200001*
10430230002
9070200003*
498011000Upper Aux
20404500Lower Aux
31707000Tail
* Tanks 1 and 3 aft fuel boost/transfer pumps and conduits are located in tank 2. Tank 2 must be filled to
specified level when accomplishing this inspection for tanks 1 and 3 aft fuel boost/transfer pumps.
Group 2:
Minimum Fuel LevelTank
KilogramPounds
20404500Fwd Aux
2. Place 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.
3. Gain access to inspection areas. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an
accepted procedure.
4. Open/verify circuit breakers as follows:
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a. Open fuel boost/transfer pump power circuit breakers. Refer to MD11 AMM 28-22-01 and
MD11 AMM 28-22-02 as an accepted procedure.
b. Make sure Remote Control Circuit Breaker (RCCB) 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 1Tank 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
EPC Bay 2Tail Tank R TransB1-1575
Electrical Power PanelTail Tank AltnB1-1577
*If installed
Group 2:
LocationCircuit BreakerRCCB
EPC Bay 1Fwd Aux LB1-391
EPC Bay 3Fwd Aux RB1-392
PART 2 (FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY - REPLACEMENT)
1. Replace existing 60-84355-1 fuel pump housing electrical connector assembly in accordance with
Appendix B.
2. Proceed to Part 5 (Restoration).
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PART 3 (FUEL BOOST/TRANSFER PUMP AND FUEL PUMP HOUSING ELECTRICAL CONNECTOR
ASSEMBLY PART NUMBER 60-84355-1 INSPECTION)
1. Using a digital multimeter, check electrical continuity and resistance from terminal strip through
fuel boost/transfer pump as follows:
a. Disconnect fuel boost/transfer pump wires from terminal strip/ground stud (or disconnect
connectors) and check disconnected wires terminal to terminal in accordance with Appendix
A, Tables below and refer to MD11 AMM 28-22-10 as an accepted procedure:
NOTE: Fuel boost/transfer pump wiring resistance should be less than or equal to 2.5 ohms.
NOTE: Terminal E should read open during multimeter check.
Wiring Resistance Check
ResultsCheckResultsCheck
2-31-2
2-E1-3
3-E1-E
Group 2:
Wiring Resistance Check
ResultsCheckResultsCheck
B-CA-B
B-EA-C
C-EA-E
b. If fuel boost/transfer pump wiring resistance is greater than 2.5 ohms or terminal E is not open,
remove fuel boost/transfer pump, refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as
an acceptable procedure and check pin-to-pin as follows:
NOTE: Fuel boost/transfer pump resistance should be less than or equal to 2.5 ohms.
NOTE: Pin E should read open during multimeter check.
Fuel Boost/Transfer Pump Resistance Check
ResultsCheckResultsCheck
B-CA-B
B-EA-C
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Fuel Boost/Transfer Pump Resistance Check
ResultsCheckResultsCheck
C-EA-E
2. If any fuel boost/transfer pump wiring resistance reading is greater than 2.5 ohms or terminal E is
not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms with
pin E open, replace existing fuel pump housing electrical connector assembly in accordance with
Appendix B.
3. Remove and retain fuel boost/transfer pumps, if not previously removed. Refer to MD11 AMM
28-22-01 and MD11 AMM 28-22-02 as an accepted procedure.
4. Using Quadtech 1864 Megohm meter, do a fuel pump housing electrical connector assembly
insulation resistance check as follows:
a. Install T67291 or T6729-1 test tool/alternate tool.
b. Set Megohm meter at 100+/-10 volts DC and current limit to 5 milliamps. Check insulation
resistance by applying test voltage terminal-to-terminal in accordance with Appendix A, and
Tables below:
NOTE: Insulation resistance should be greater or equal to 10 gigaohm.
Insulation Resistance Check
ResultsCheckResultsCheck
2-31-2
2-E1-3
3-E1-E
Group 2:
Insulation Resistance Check
ResultsCheckResultsCheck
B-CA-B
B-EA-C
C-EA-E
c. Remove test pump/alternate tool.
5. If any fuel boost/transfer pump resistance reading is greater than 2.5 ohms or pin E is not open.
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a. Replace fuel boost/transfer pump. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02
as an accepted procedure.
b. Proceed to Part 5 (Restoration).
6. If any fuel pump housing electrical connector assembly insulation resistance reading is less than
10 gigaohm.
a. Replace existing fuel pump housing electrical connector assembly in accordance with Appendix
B.
b. Proceed to Part 5 (Restoration).
7. Proceed to Part 5 (Restoration) If all continuity, resistance and insulation resistance, results are
as follows:
a. Fuel boost/transfer pump wiring resistance reading is less than or equal to 2.5 ohms and
terminal E is open.
b. Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is
open.
c. Fuel pump housing electrical connector assembly insulation resistance reading is greater than
or equal to 10 gigaohm.
PART 4 (FUEL BOOST/TRANSFER PUMP AND FUEL PUMP HOUSING ELECTRICAL CONNECTOR
ASSEMBLY PART NUMBER 60-84351 INSPECTION)
1. Using a digital multimeter, check electrical continuity and resistance from terminal strip through
fuel boost/transfer pump as follows:
a. Disconnect fuel boost/transfer pump wires from terminal strip/ground stud (or disconnect
connectors) and check disconnected wires terminal to terminal in accordance with Appendix
C, Tables below and refer to MD11 AMM 28-22-10 as an accepted procedure:
NOTE: Fuel boost/transfer pump wiring resistance should be less than or equal to 2.5 ohms.
NOTE: Terminal E should read open during multimeter check.
Wiring Resistance Check
ResultsCheckResultsCheck
2-D1-2
2-E1-3
3-D1-D
3-E1-E
D-E2-3
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Group 2:
Wiring Resistance Check
ResultsCheckResultsCheck
B-DA-B
B-EA-C
C-DA-D
C-EA-E
D-EB-C
b. If fuel boost/transfer pump wiring resistance is greater than 2.5 ohms or terminal E is not open,
remove fuel boost/transfer pump, refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as
an acceptable procedure and check pin-to-pin as follow:
NOTE: Fuel boost/transfer pump resistance should be less than or equal to 2.5 ohms.
NOTE: Pin E should read open during multimeter check.
Fuel Boost/Transfer Pump Resistance Check
ResultsCheckResultsCheck
B-DA-B
B-EA-C
C-DA-D
C-EA-E
D-EB-C
2. If any fuel boost/transfer pump wiring resistance reading is greater than 2.5 ohms or terminal E is
not open and fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms with
pin E open, replace the affected fuel pump housing electrical connector assembly. Refer to MD11
AMM 28-22-10, Section entitled "Pump Housing, A and B Repairs", and "Pre Service Bulletin
MD11-28A113" as an accepted procedure.
3. Remove and retain fuel boost/transfer pumps, if not previously removed. Refer to MD11 AMM
28-22-01 and MD11 AMM 28-22-02 as an accepted procedure.
4. Using Quadtech 1864 Megohm meter, do a fuel pump housing electrical connector assembly
insulation resistance check as follows:
a. Install T67291 or T6729-1 test tool/alternate tool.
b. Set Megohm meter at 100+/-10 volts DC and current limit to 5 milliamps. Check insulation
resistance by applying test voltage terminal-to-terminal in accordance with Appendix C, and
Tables below:
NOTE: Insulation resistance should be greater or equal to 10 megaohm.
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Insulation Resistance Check
ResultsCheckResultsCheck
2-D1-2
2-E1-3
3-D1-D
3-E1-E
D-E2-3
Group 2:
Insulation Resistance Check
ResultsCheckResultsCheck
B-DA-B
B-EA-C
C-DA-D
C-EA-E
D-EB-C
c. Remove test pump/alternate tool.
5. If any fuel boost/transfer pump resistance reading is greater than 2.5 ohms or pin E is not open.
a. Replace fuel boost/transfer pump. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02
as an accepted procedure.
b. Proceed to Part 5 (Restoration).
6. If any fuel pump housing electrical connector assembly insulation resistance reading is less than
10 megaohm.
a. Replace the affected fuel pump housing electrical connector assembly. Refer to MD11 AMM
28-22-10, Section entitled "Pump Housing, A and B Repairs", and "Pre Service Bulletin
MD11-28A113" as an accepted procedure.
b. Proceed to Part 5 (Restoration).
7. Proceed to Part 5 (Restoration) If all continuity, resistance and insulation resistance, results are
as follows:
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a. Fuel boost/transfer pump wiring resistance reading is less than or equal to 2.5 ohms and
terminal E is open.
b. Fuel boost/transfer pump resistance reading is less than or equal to 2.5 ohms and pin E is
open.
c. Fuel pump housing electrical connector assembly insulation resistance reading is greater than
or equal to 10 megaohm.
PART 5 (RESTORATION)
1. If not already accomplished, connect fuel pump housing electrical connector assemblies to terminal
strip and ground studs. Refer to MD11 AMM 28-22-10 and Appendix A (part number 60-84355-1),
or Appendix C (part number 60-84351) as an accepted procedure.
2. Install fuel boost/transfer pumps if not previously installed refer to MD11 AMM 28-22-01 and MD11
AMM 28-22-02 as an accepted procedure.
3. Do operational test of fuel boost/transfer pumps and using a digital multimeter check that voltage
between applicable terminal strip post and ground is 104 to 122VAC. Refer to MD11 AMM 28-22-01,
MD11 AMM 28-22-02 and Appendix A (part number 60-84355-1), or Appendix C (part number
60-84351) as an accepted procedure.
4. Close access. Refer to MD11 AMM 28-22-01 and MD11 AMM 28-22-02 as an accepted procedure.
5. Put the airplane back to a serviceable condition.
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ALL GROUPS:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-368
A
R5-11021/Forward -2B -3C
5022AE*
-1
S3-370
A
R5-11001/Transfer -2B -3C
4726AE*
-1
S3-369
A
R5-11011/Aft -2B -3C
4727AE*
-1
S3-371
A
R5-11052/Forward -2B -3C
5009AE*
-1
S3-372
A
R5-11042/Left Aft -2B -3C
4728AE*
-1
S3-374
A
R5-10992/Transfer -2B -3C
6078AE*
-1
S3-373
A
R5-11032/Right Aft -2B -3C
4821AE*
-1
S3-377
A
R5-11063/Forward -2B -3C
6022AE*
-1
S3-376
A
R5-11073/Transfer -2B -3C
4823AE*
APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1
(SHEET 1 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 02, 2009
MD11-28A143
35 of 44
BOEING SERVICE BULLETIN MD11-28A143
ALERTALERT

### Page 36

ALL GROUPS:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-375
A
R5-11083/Right Aft -2B -3C
4822AE*
-1
S3-803
A
R5-1934Center Aux/LeftUpper -2B -3C
4729AE*
-1
S3-802
A
R5-1933Center Aux/RightUpper -2B -3C
4824AE*
-1
S3-805
A
R5-1936Center Aux/LeftLower -2B -3C
4895AE*
-1
S3-804
A
R5-1935Center Aux/RightLower -2B -3C
4894AE*
-1
S3-764
A
R5-2802Tail/Left Transfer -2B -3C
7043A5E*
-1
S3-765
A
R5-2800Tail/Right Trans-fer -2B -3C
7043A5E*
-1
S3-755
A
R5-2801Tail/Altn -2B -3C
7043A5E*
* E should read open during multimeter check.
APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 02, 2009
MD11-28A143
36 of 44
BOEING SERVICE BULLETIN MD11-28A143
ALERTALERT

### Page 37

GROUP 2:
Ground Stud
ConnectorConnector (Pump)
Tank/Pump
SocketNumberSocketNumber
-A
R5-9668
A
R5-1347Forward AuxRight -BB -CC
9079AE*E*
-A
R5-9669
A
R5-1348Forward Aux Left -BB -CC
9078AE*E*
* E should read open during multimeter check.
GROUP 2:
TerminalRelayLocationTank/Pump
A1R2-110RightForward Aux
B1
C1
A1R2-109LeftForward Aux
B1
C1
APPENDIX A: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84355-1
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 02, 2009
MD11-28A143
37 of 44
BOEING SERVICE BULLETIN MD11-28A143
ALERTALERT

### Page 38

1. Put the 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. Replace the affected fuel pump housing electrical connector assembly in accordance with Table below and
refer to MD11 AMM 28-22-10, Section entitled "Pump Housing, A and B Repairs", and "Pre Service Bulletin
MD11-28A113" as an accepted procedure.
ALL GROUPS:
Drawing
SR11280084
Connector Identifi-
cation
Fuel Pump Identifi-
cation
LocationTank
Sheets 3, 3.1, 3.3,
3.4, 3.8, 3.9, 3.10, 4,
4.1, 5, 5.1, 6, 6.1, 7,
9, 9.6, 10 and 21
R5-1102M1-1102Forward1
Sheets 3, 3.1, 3.3,
3.5, 3.8, 3.9, 3.10, 4,
4.1, 5, 5.1, 6, 6.1, 7,
9, 9.6, 10 and 19.
R5-1100M1-1100Transfer1
R5-1101M1-1101Left Aft1
Sheets 3, 3.1, 3.3,
3.4, 3.8, 3.9, 3.10, 4,
4.1, 5, 5.1, 6, 6.1, 7,
9.1, 9.6, 10 and 20.
R5-1105M1-1105Forward2
Sheets 3, 3.1, 3.3,
3.5, 3.8, 3.9, 3.10, 4,
4.1, 5, 5.1, 6, 6.1, 7,
9.1, 9.6, 10 and 19.
R5-1104M1-1104Left Aft2
Sheets 3, 3.1, 3.3,
3.4, 3.8, 3.9, 3.10, 4,
4.1, 5, 5.1, 6, 6.1, 7,
9.1, 9.6, 10 and 17.
R5-1099M1-1099Transfer2
Sheets 3, 3.1, 3.3,
3.5, 3.8, 3.9, 3.10, 4,
4.1, 5., 5.1, 6, 6.1, 7,
9.1, 9.7, 10 and 16.
R5-1103M1-1103Right Aft2
Sheets 3, 3.1, 3.3,
3.4, 3.8, 3.9, 3.10, 4,
4.1, 5, 5.1, 6, 6.1, 7,
9.2, 9.7, 10 and 18.
R5-1106M1-1106Forward3
APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N
60-84351
(SHEET 1 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 02, 2009
MD11-28A143
38 of 44
BOEING SERVICE BULLETIN MD11-28A143
ALERTALERT

### Page 39

ALL GROUPS:
Drawing
SR11280084
Connector Identifi-
cation
Fuel Pump Identifi-
cation
LocationTank
Sheets 3, 3.1, 3.3,
3.5, 3.8, 3.9, 3.10, 4,
4.1, 5, 5.1, 6. 6.1, 7,
9.2, 9.7, 10 and 16.
R5-1107M1-1107Transfer3
R5-1108M1-1108Right Aft3
Sheets 3, 3.1, 3.3,
3.5, 3.8, 3.9, 3.10, 4,
4.1, 5, 5.1, 6, 6.1, 7,
9.3, 9.7, 10 and 13.
R5-1934M1-1934LeftCenter Aux/Upper
R5-1933M1-1933RightCenter Aux/Upper
Sheets 3, 3.1, 3.2,
3.3, 3.8, 3.9, 3.10, 4,
4.1, 5, 5.1, 6, 6.1, 7,
9.3, 9.8, 10, 14 and
15.
R5-1936M1-1936LeftCenter Aux/Lower
R5-1935M1-1935RightCenter Aux/Lower
Sheets 3, 3.1, 3.3,
3.7, 3.7.1, 3.8, 3.9,
3.10, 4, 4.1, 5, 5.1, 6,
6.1, 7, 9.5, 9.8, 10
and 11.
R5-2802M1-2802Left TransferTail
Sheets 3, 3.1, 3.3,
3.7, 3.7.1, 3.9, 3.10,
4, 4.1, 5, 5.1, 6, 6.1,
7, 9.5, 9.8, 10 and
11.
R5-2800M1-2800Right TransferTail
Sheets 3, 3.1, 3.3,
3.7, 3.7.1, 3.8, 3.9,
3.10, 4, 4.1, 5, 5.1, 6,
6.1, 7, 9.5, 9.9, 10
and 11.
R5-2801M1-2801Alt FeedTail
GROUP 2:
Drawing
SR11280084
Connector Identifi-
cation
Fuel Pump Identifi-
cation
LocationTank
Sheets 3, 3.1, 3.3,
3.6, 3.9, 3.10, 4.1,
5.1, 6.1, 7, 8, 8.1,
8.2, 8.3, 9.4, 9.8, 10
and 12.
R5-1347M1-1347RightForward Aux
R5-1348M1-1348LeftForward Aux
APPENDIX B: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY REPLACEMENT WITH P/N
60-84351
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 02, 2009
MD11-28A143
39 of 44
BOEING SERVICE BULLETIN MD11-28A143
ALERTALERT

### Page 40

ALL GROUPS:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-368
A
R5-11021/Forward
-2B
-3C
5022AD
5022AE*
-1
S3-370
A
R5-11001/Transfer
-2B
-3C
4726AD
4726AE*
-1
S3-369
A
R5-11011/Aft
-2B
-3C
4727AD
4727AE*
-1
S3-371
A
R5-11052/Forward
-2B
-3C
5009AD
5009AE*
-1
S3-372
A
R5-11042/Left Aft
-2B
-3C
4728AD
4728AE*
-1
S3-374
A
R5-10992/Transfer
-2B
-3C
6078AD
6078AE*
-1
S3-373
A
R5-11032/Right Aft
-2B
-3C
4821AD
4821AE*
APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351
(SHEET 1 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 02, 2009
MD11-28A143
40 of 44
BOEING SERVICE BULLETIN MD11-28A143
ALERTALERT

### Page 41

ALL GROUPS:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-377
A
R5-11063/Forward
-2B
-3C
6022AD
6022AE*
-1
S3-376
A
R5-11073/Transfer
-2B
-3C
4823AD
4823AE*
-1
S3-375
A
R5-11083/Right Aft
-2B
-3C
4822AD
4822AE*
-1
S3-803
A
R5-1934Center Aux/LeftUpper -2B -3C 4729AD
4729AE*
-1
S3-802
A
R5-1933Center Aux/RightUpper -2B -3C 4824AD
4824AE*
-1
S3-805
A
R5-1936Center Aux/LeftLower -2B -3C 4895AD
4895AE*
-1
S3-804
A
R5-1935Center Aux/RightLower -2B -3C 4894AD
4894AE*
-1
S3-764
A
R5-2802Tail/Left Transfer
-2B
-3C
7043A5D
7043A5E*
APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 02, 2009
MD11-28A143
41 of 44
BOEING SERVICE BULLETIN MD11-28A143
ALERTALERT

### Page 42

ALL GROUPS:
Ground Stud
Terminal StripConnector
Tank/Pump
PostNumberSocketNumber
-1
S3-765
A
R5-2800Tail/Right Trans-fer -2B -3C 7043A5D
7043A5E*
-1
S3-755
A
R5-2801Tail/Altn
-2B
-3C
7043A5D
7043A5E*
* E should read open during multimeter check.
GROUP 2:
Ground Stud
ConnectorConnector (Pump)
Tank/Pump
SocketNumberSocketNumber
-A
R5-9668
A
R5-1347Forward AuxRight -BB -CC 9079ADD
9079AE*E*
-A
R5-9669
A
R5-1348Forward Aux Left
-BB
-CC
9078ADD
9078AE*E*
* E should read open during multimeter check.
GROUP 2:
TerminalRelayLocationTank/Pump
A1R2-110RightForward Aux
B1
C1
A1R2-109LeftForward Aux
B1
C1
APPENDIX C: FUEL BOOST/TRANSFER PUMP WIRING CHART FOR PART NUMBER 60-84351
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 02, 2009
MD11-28A143
42 of 44
BOEING SERVICE BULLETIN MD11-28A143
ALERTALERT

### Page 43 (OCR)

BOEING SERVICE BULLETIN MD11-28A143
ALERT  ALERT
Replace fuel Pump Housing  Do Continuity and Resistance
Electrical Connector Assembly  inspection from terminal strip
with part number 60-84351 IAW  OR  through fuel boost/transfer pump
Accomplishment Instruction 3.B.  AW Accomplishment Instruction
Part 2 and restore airplane
Resistance is Greater  Resistance is Less
than 2.5 ohms or  than or Equal to 2.5
terminal E not open  ohms and Terminal E
reads open
Remove Fuel Boost/
Transfer Pump
Do Fuel Boost/
Transfer Pump  Remove Fuel Boost/
Resistance  Transfer Pump
Inspection
Fuel Boost/Transfer Pump  Fuel Boost/Transfer
Resistance is less than or  Pump Resistance is
equal to 2.5 ohms and  Greater than 2.5 ohms or
Terminal E reads open  terminal E not open
Using Megohm meter, do
Replace Fuel Boost/  Transfer Pump  Electrical Connector  Fuel Pump Housing  Assembly Insulation
Resistance Inspection
Resistance is less  Resistance is Greater than
than 10 Gigaohm  or equal to 10 Gigaohm
Restore Airplane
Replace Fuel Pump Housing  Replace fuel pump housing
Electrical Connector  electrical connector assembly
Assembly with Part Number  part number 60-84355-1 with
60-84351 IAW 3.B. Part 2  part number 60-84351 IAW
and restore airplane  3.B. Part 2 at threshold
Do Repeat Continuity and  specified in Paragraph 1.E.,
Resistance inspection AW  Compliance Table 1
Accomplishment Instruction
3.B Part 4 at threshold
specified in Paragraph 1.E.
Compliance Table 2
APPENDIX D: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER
60-84355-1 INSPECTION LOGIC DIAGRAM
(SHEET 1 OF 1)
Original Issue: December 02, 2009
BOEING PROPRIETARY -  MD11-28A143
Copyright © Unpublished Work - See page 1 for details.  43 of 44

### Page 44 (OCR)

BOEING SERVICE BULLETIN MD11-28A143
ALERT  ALERT
Do Continuity and Resistance
inspection from terminal strip
through fuel boost/transfer pump
IAW Accomplishment Instruction
3. B Part 4
Resistance is Greater  Resistance is Less
than 2.5 ohms or  than or Equal to 2.5
terminal E not open  ohms and Terminal E
reads open
Remove Fuel Boost/
Transfer Pump
Do Fuel Boost/
Transfer Pump  Remove Fuel Boost/
Resistance  Transfer Pump
Inspection
Fuel Boost/Transfer Pump  Fuel Boost/Transfer
Resistance is less than or  Pump Resistance is
equal to 2.5 ohms and  Greater than 2.5 ohms or
Terminal E reads open  terminal E not open
Using Megohm meter, do
Replace Fuel Boost.  Fuel Pump Housing
Electrical Connector
ranster Pump
Assembly Insulation
Resistance Inspection
Resistance is less  Resistance is Greater than
than 10 Megaohm  or equal to 10 Megaohm
Restore Airplane
Replace Fuel Pump Housing
Electrical Connector
Assembly with Part Number
60-84351 IAW 3.B. Part 4
and restore airplane
Do Repeat Continuity and
Resistance inspection IAW
Accomplishment Instruction  1908751
3.B Part 4
APPENDIX E: FUEL PUMP HOUSING ELECTRICAL CONNECTOR ASSEMBLY FOR PART NUMBER
60-84351 INSPECTION LOGIC DIAGRAM
(SHEET 1 OF 1)
Original Issue: December 02, 2009
BOEING PROPRIETARY -  MD11-28A143
Copyright © Unpublished Work - See page 1 for details.  44 of 44

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