# Boeing Service Bulletin MD11-28-132: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2010-0384; AD 2010-20-14 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Service Bulletin MD11-28-132](https://openairdocs.org/service-documents/boeing/md11-28-132.md)
- Title as filed: U.S. DOT/FAA - SB-MD11-28-132-01
- Pages: 45
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### Page 1

Commercial 
Airplanes
MD11
Service Bulletin
Number: MD11-28-132
Original Issue: November 25, 2008
Revision 1: July 06, 2010
ATA System: 2800
SUBJECT: FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses
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 © 2008 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Unpublished Work - All Rights Reserved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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2.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 0
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 0
D. Description .............................................. 1 0
E. Compliance .............................................. 1 1
F. Approval ............................................... 1 1
G. Manpower .............................................. 1 2
H. Weight and Balance Changes .................................... 1 3
I. Electrical Load Data ......................................... 1 3
J. References .............................................. 1 3
1. Existing Data: ......................................... 1 3
2. Data supplied with this Service Bulletin: ........................... 1 3
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 3
4. Process Data: ......................................... 1 3
K. Publications Affected ........................................ 1 3
L. Interchangeability and Intermixability of Parts ........................... 1 4
2. MATERIAL INFORMATION ........................................ 1 5
A. Material - Price and Availability ................................... 1 5
B. Industry Support Information .................................... 1 5
C. Parts Necessary For Each Airplane ................................. 1 5
1. Kits/Parts: ........................................... 1 5
2. Parts and Materials Supplied by the Operator: ........................ 2 2
3. Parts Modified and Reidentified: ............................... 2 2
4. Parts Removed and Not Replaced: .............................. 2 3
D. Parts Necessary to Change Spares ................................. 2 3
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 6
Appendix A: FUEL TANK 1 [Group 1-4] ................................... 3 0
Appendix B: FUEL TANK 2 [Group 1-4] ................................... 3 1
Appendix C: FUEL TANK 3 [Group 1-4] ................................... 3 2
Appendix D: UPPER AND LOWER AUXILIARY FUEL TANKS [Group 1-4] ................ 3 3
Appendix E: TAIL FUEL TANK [Group 1-4] ................................. 3 4
Appendix F: FORWARD AUXILIARY FUEL TANK [Group 2] ....................... 3 5
Appendix G: FORWARD AUXILIARY FUEL TANK [Group 3] ....................... 3 6
Appendix H: FORWARD AUXILIARY FUEL TANK NO. 1 STATION 1044.437 AND NO. 2 STATION 1124.437
[Group 4] ............................................ 3 7
Appendix I: FUEL TESTS [Group 1] .................................... 3 8
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Appendix J: FUEL TESTS [Group 2] .................................... 4 0
Appendix K: FUEL TESTS [Group 3] .................................... 4 2
Appendix L: FUEL TESTS [Group 4] .................................... 4 4
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Commercial 
Airplanes
MD11
Service Bulletin
Revision Transmittal SheetNumber: MD11-28-132Original Issue: November 25, 2008
Revision 1: July 06, 2010
ATA System: 2800
SUBJECT: FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on the airplane(s) changed in accordance with the original issue of this service
bulletin.
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2010-NM-003-AD, is related to this
service bulletin.
Airplane fuselage number 0608 was moved to Group 1 from Group 3 of this service bulletin effectivity.
REASON FOR REVISION
This revision is sent to incorporate changes outlined in Information Notices (IN)s MD11-28-132 IN 01, IN 02 and
IN 03.
The data given in Information Notices (IN)s MD11-28-132 IN 01, IN 02 and IN 03, is included in this revision.
These sections were changed:
1. In Paragraph 1.D., Description, added Maintenance Zone table.
2. In Paragraph 1.E., Compliance, added Federal Aviation Administration (FAA) Notice of Proposed Rule
Making 2010-NM-003-AD and changed recommended compliance statement.
3. In Paragraph 1.F., Approval, changed statement.
4. In Paragraph 1.J.1., Existing Data, added Federal Aviation Administration (FAA) Notice of Proposed Rule
Making 2010-NM-003-AD.
5. In Paragraph 1.H., Weight and Balance Changes, changed values.
6. In Paragraph 1.K.1., Publications, changed Aircraft Maintenance Manual and Fault Isolation Manual
chapter-section.
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7. In Paragraph 1.K.2., Damage Tolerance Based Structural Inspections, added statement.
8. In Paragraph 2.A., Material - Price and Availability, changed pricing data.
9. In Paragraph 2.C.1., Kit/Parts, changed wire kit number for Groups 1 through 4, Group 3 top kit number
and AEPL drawing number.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
November 25, 2008Original Issue:
July 06, 2010Revision 1:
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Commercial 
Airplanes
MD11
Service Bulletin
SummaryNumber: MD11-28-132Original Issue: November 25, 2008
Revision 1: July 06, 2010
ATA System: 2800
SUBJECT: FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses
CONCURRENT REQUIREMENTS
None.
BACKGROUND
An investigation by Boeing has determined that float level switch wires located on the left and right wing forward
spar, right main landing gear wheel well, horizontal stabilizer front spar, empennage, and forward cargo
compartment are routed in the same bundles as power wires. If a short circuit between a float level switch wire
and a power wire occurs, an over current can cause excessive temperatures in the float level switch wires,
resulting in damage. Adding an in-line fuse as a self-contained component in each float level switch circuit and
sleeving the wires between the fuel tank and the in-line fuse will minimize the possibility of excessive temperatures
in the float level switch wires. If not corrected, and there is a short circuit of the float level switch wire to a power
wire, possible damage to the float level switch wire could occur, and become a potential ignition source for the
fuel tank.
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.
ACTION
This service bulletin installs fuel tank float level switch in-line fuses.
EFFECTIVITY
All MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2010-NM-003-AD, is related to this
service bulletin.
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.
Boeing recommends that the operators do this service bulletin within 5 years after the original issue date on this
service bulletin.
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INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G, for Manpower information.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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Commercial 
Airplanes
MD11
Service Bulletin
Number: MD11-28-132
Original Issue: November 25, 2008
Revision 1: July 06, 2010
ATA System: 2800
SUBJECT: FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below.
NOTE: When any Group 3 or 4 passenger airplane shown below is modified to a freighter
configuration by Boeing Passenger to Freighter (P to F) engineering, it will become a
Group 1 airplane.
DESCRIPTIONCONFIGURATIONGROUP
Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower
auxiliary, and tail configuration.
-1
Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower
auxiliary, foward auxiliary, tail, and unique wiring configuration.
-2
Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower
auxiliary, foward auxiliary, tail, and unique wiring configuration.
-3
Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower
auxiliary, foward auxiliary No. 1, foward auxiliary No. 2, and tail
configuration.
-4
Airplane Models:
MD-11, MD-11F
GroupFuselage Num-
ber
1447 - 449
1451 - 464
1466 - 489
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GroupFuselage Num-
ber
1491 - 517
1519 - 531
4532
1533 - 543
4544
1545 - 552
1554 - 589
2590
1591 - 596
3597
1598 - 646
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
An investigation by Boeing has determined that float level switch wires located on the left and right
wing forward spar, right main landing gear wheel well, horizontal stabilizer front spar, empennage, and
forward cargo compartment are routed in the same bundles as power wires. If a short circuit between
a float level switch wire and a power wire occurs, an over current can cause excessive temperatures
in the float level switch wires, resulting in damage. Adding an in-line fuse as a self-contained component
in each float level switch circuit and sleeving the wires between the fuel tank and the in-line fuse will
minimize the possibility of excessive temperatures in the float level switch wires. If not corrected, and
there is a short circuit of the float level switch wire to a power wire, possible damage to the float level
switch wire could occur, and become a potential ignition source for the fuel tank.
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.
Revision 1 is sent to incorporate changes outlined in Information Notices (IN)s MD11-28-132 IN 01, IN
02 and IN 03.
The data given in Information Notices (IN)s MD11-28-132 IN 01, IN 02 and IN 03, is included in this
revision.
D. Description
This service bulletin installs fuel tank float level switch in-line fuses.
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Revision 1 - No more work is necessary on the airplane(s) changed in accordance with the original
issue of this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
144, 145, 146, 371, 516, 518, 525, 526, 527,
618, 625, 626, 627
MD-11, MD-11F
Group 2-4:
Affected Maintenance Zones
ZoneModel
123, 144, 145, 146, 254, 371, 516, 518, 525,
526, 527, 618, 625, 626, 627
MD-11
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2010-NM-003-AD, is related
to this service bulletin.
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.
Boeing recommends that the operators do this service bulletin within 5 years after the original issue
date on this service bulletin.
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.
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G. Manpower
The table below shows an estimate of the task hours necessary to do this modification 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 examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
10.521.02Open Access
62.5125.02Change
3.06.02Test
12.525.02Close Access
88.5177.0TOTAL FOR EACH AIRPLANE
Group 2-3:
Elapsed HoursTask HoursNumber of PersonsTask
10.521.02Open Access
66.0132.02Change
3.16.22Test
12.525.02Close Access
92.1184.2TOTAL FOR EACH AIRPLANE
Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
10.521.02Open Access
67.6135.21Change
3.36.62Test
12.525.02Close Access
93.9187.8TOTAL FOR EACH AIRPLANE
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H. Weight and Balance Changes
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)
Airplane
Group
+10129.1+6.71511.81
+10787.0+7.01541.02 and 3
+10478.2+7.11475.84
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. MD-11-1F Structural Repair Manual (SRM) 51-00-01.
b. MD-11-1P Structural Repair Manual (SRM) 51-00-01.
c. MD-11 Aircraft Maintenance Manual (AMM) 06-28-00, 06-32-34, 06-33-00, 06-35-00, 06-36-00,
12-11-03, 28-14-01 and 28-00-00.
d. Standard Wiring Practices Manual (SWPM) 20-00-00, 20-00-09, 20-00-13, 20-00-16, 20-10-01,
20-10-04, 20-20-02, 20-20-03 and 20-40-01.
e. Wire Diagram Manual (WDM) 28-21-01, 28-22-06, 28-22-07, 28-22-08, 28-43-01, 28-43-02,
and 28-46-01.
f. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)
2010-NM-003-AD.
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
4. Process Data:
Douglas Process Specifications referred to on the drawing are not given in this service bulletin
since these procedures are frequently used as standard shop practices.
K. Publications Affected
1. Publications:
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Chapter-SectionPublication
28-14, 28-21, 28-30, 28-40, 28-43, 28-46
and 36-14
Aircraft Maintenance Manual
28-14, 36-23Fault Isolation Manual
28-42 and 28-43Illustrated Parts Catalog
28-21, 28-22, 28-43 and 28-46Wiring 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
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
Revision 1 date of
this Service Bul-
letin (US Dollars)
ROLT as of Revi-
sion 1 date of this
Service Bulletin
(Calendar Days)
QTYDateNameKit Number
$9,951.00901Service KitSB11280132-3
10,212.00901Service KitSB11280132-5
10,541.00901Service KitSB11280132-7
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts:
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
Group 1:
Kit SB11280132
NotesNameQTYNew Part Number
-3
(a)SCREW73D0005-08-10
(a)SCREW373D0005-08-8
(a)SCREW53D0005-3-22
(a)SCREW83D0005-3-26
(a)SCREW33D0005-3-28
(a)SCREW23D0005-3-8
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Group 1:
Kit SB11280132
NotesNameQTYNew Part Number
-3
(a)TERMINAL LUG 87865D0086-3
(a)TERMINAL LUG 762115D0086-6
(a)SEALING PLUG485D0206-20
IN-LINE FUSE2465053-220
BRACKET ASSEMBLY1ANN0012-1
SOCKET T/C 5243M39029/22-192
COVER ASSEMBLY1MS18029-6S8
RIVET2MS20470AD4-5D
RIVET4MS20470AD5-5D
NUT74MS21042L08
NUT2MS21042L3
CLAMP4MS21919WDG10
CLAMP6MS21919WDG3
CLAMP2MS21919WDG5
CLAMP2MS21919WDG7
TERMINAL BOARD1MS27212-6-8
LOCKWASHER37MS35338-42
LOCKWASHER2MS35338-43
WASHER6NAS1252-10H
WASHER55NAS1252-10L
WASHER7NAS1252-8H
WASHER118NAS1252-8L
SPACER5NAS43DD3-48FC
SPACER8NAS43DD3-64FC
SPACER3NAS43DD3-72FC
WASHER3NAS620A4
BOLT3NAS7700-3
(a)CLAMP1S7934111-2SA
(a)CLAMP21S7934111-3SA
(a)CLAMP5S7934111-4SA
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Group 1:
Kit SB11280132
NotesNameQTYNew Part Number
-3
(a)CLAMP3S7934111-5SA
(a)CLAMP1S7934111-6SA
(a)CLAMP4S7934111-7SA
(a)CLAMP1S7934111-8SA
(a)CLAMP24S7934111-9SA
WIRE KIT1SR11280063-103
WIRE KIT1SR11280063-104
WIRE KIT1SR11280063-105
SLEEVING136 FT X
.166 I.D.
SR11280063-3(DMS
2109, Type 1) or
equivalent
TIE TAPE50 YDSR11280063-7 (DMS
2089) or equivalent
BRACKET1TA4012B12
BRACKET2TA4012F21
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
Group 1:
Wire Kit SR11280063
NotesNameQTYQTYQTYNew Part Number
-105-104-103
SOCKET T/C 1124-1-DC39-20S
WIRE CODE 80114 FT14 FT-DC2426-1C-20NM (DMS 2426)
or equivalent
WIRE CODE 801158 FT-26FTDC2426-1C-22NM (DMS 2426)
or equivalent
SOCKET T/C 5243374M39029/22-192
(a)TERMINAL LUG 8784--5D0086-3
(a)TERMINAL LUG 76229645D0086-6
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
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Group 2-3:
Kit SB11280132
NotesNameQTYNew Part Number
-5
(a)SCREW73D0005-08-10
(a)SCREW13D0005-08-12
(a)SCREW383D0005-08-8
(a)SCREW53D0005-3-22
(a)SCREW83D0005-3-26
(a)SCREW33D0005-3-28
(a)SCREW23D0005-3-8
(a)TERMINAL LUG 87865D0086-3
(a)TERMINAL LUG 762115D0086-6
(a)SEALING PLUG505D0206-20
IN-LINE FUSE2565053-220
(a)STRAP59D0254-1-1-9
BRACKET ASSEMBLY1ANN0012-1
SOCKET T/C 5244M39029/22-192
COVER ASSEMBLY1MS18029-6S8
RIVET4MS20470AD4-5D
RIVET4MS20470AD5-5D
NUT76MS21042L08
NUT2MS21042L3
CLAMP4MS21919WDG10
CLAMP6MS21919WDG3
CLAMP2MS21919WDG5
CLAMP2MS21919WDG7
TERMINAL BOARD1MS27212-6-8
LOCKWASHER37MS35338-42
LOCKWASHER2MS35338-43
WASHER6NAS1252-10H
WASHER55NAS1252-10L
WASHER7NAS1252-8H
WASHER122NAS1252-8L
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Group 2-3:
Kit SB11280132
NotesNameQTYNew Part Number
-5
SPACER5NAS43DD3-48FC
SPACER8NAS43DD3-64FC
SPACER3NAS43DD3-72FC
WASHER3NAS620A4
BOLT3NAS7700-3
(a)CLAMP1NMC1001-2
(a)CLAMP1S7934111-2SA
(a)CLAMP21S7934111-3SA
(a)CLAMP5S7934111-4SA
(a)CLAMP3S7934111-5SA
(a)CLAMP1S7934111-6SA
(a)CLAMP4S7934111-7SA
(a)CLAMP1S7934111-8SA
(a)CLAMP25S7934111-9SA
WIRE KIT1SR11280063-101
WIRE KIT1SR11280063-103
WIRE KIT1SR11280063-104
WIRE KIT1SR11280063-105
SLEEVING136 FT X
.166 I.D.
SR11280063-3(DMS
2109, Type 1) or
equivalent
SLEEVE15 FT X 3/16
I.D.
SR11280063-5 (DMS
2379, Class 4) or
equivalent
TIE TAPE50 YDSR11280063-7 (DMS
2089) or equivalent
BRACKET2TA4012B12
BRACKET2TA4012F21
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
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### Page 20

Group 2-3:
Wire Kit SR11280063
NotesNameQTYQTYQTYQTYNew Part Number
-105-104-103-101
SOCKET T/C 1124-1-1DC39-20S
WIRE CODE 80114 FT14 FT--DC2426-1C-20NM (DMS
2426) or equivalent
WIRE CODE 801158 FT-26 FT2 FTDC2426-1C-22NM (DMS
2426) or equivalent
SOCKET T/C 52433741M39029/22-192
(a)TERMINAL LUG 8784---5D0086-3
(a)TERMINAL LUG 7622964-5D0086-6
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
Group 4:
Kit SB11280132
NotesNameQTYNew Part Number
-7
(a)SCREW73D0005-08-10
(a)SCREW23D0005-08-12
(a)SCREW393D0005-08-8
(a)SCREW53D0005-3-22
(a)SCREW83D0005-3-26
(a)SCREW33D0005-3-28
(a)SCREW23D0005-3-8
(a)TERMINAL LUG 87865D0086-3
(a)TERMINAL LUG 762115D0086-6
(a)SEALING PLUG525D0206-20
IN-LINE FUSE2665053-220
(a)BRACKET29D0062-1-16-10
BRACKET ASSEMBLY1ANN0012-1
SOCKET T/C 5245M39029/22-192
COVER ASSEMBLY1MS18029-6S8
RIVET6MS20470AD4-5D
RIVET4MS20470AD5-5D
NUT78MS21042L08
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### Page 21

Group 4:
Kit SB11280132
NotesNameQTYNew Part Number
-7
NUT2MS21042L3
CLAMP4MS21919WDG10
CLAMP6MS21919WDG3
CLAMP2MS21919WDG4
CLAMP2MS21919WDG5
CLAMP2MS21919WDG7
TERMINAL BOARD1MS27212-6-8
LOCKWASHER37MS35338-42
LOCKWASHER2MS35338-43
WASHER6NAS1252-10H
WASHER55NAS1252-10L
WASHER7NAS1252-8H
WASHER126NAS1252-8L
SPACER5NAS43DD3-48FC
SPACER8NAS43DD3-64FC
SPACER3NAS43DD3-72FC
WASHER3NAS620A4
BOLT3NAS7700-3
(a)CLAMP2NMC1001-2
(a)CLAMP1S7934111-2SA
(a)CLAMP21S7934111-3SA
(a)CLAMP5S7934111-4SA
(a)CLAMP3S7934111-5SA
(a)CLAMP1S7934111-6SA
(a)CLAMP4S7934111-7SA
(a)CLAMP1S7934111-8SA
(a)CLAMP26S7934111-9SA
WIRE KIT1SR11280063-102
WIRE KIT1SR11280063-103
WIRE KIT1SR11280063-104
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### Page 22

Group 4:
Kit SB11280132
NotesNameQTYNew Part Number
-7
WIRE KIT1SR11280063-105
SLEEVING136 FT X
.166 I.D.
SR11280063-3(DMS
2109, Type 1) or
equivalent
SLEEVE15 FT X 3/16
I.D.
SR11280063-5 (DMS
2379, Class 4) or
equivalent
TIE TAPE50 YDSR11280063-7 (DMS
2089) or equivalent
BRACKET1TA4012B12
BRACKET2TA4012F21
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
Group 4:
Wire Kit SR11280063
NotesNameQTYQTYQTYQTYNew Part Number
-105-104-103-102
SOCKET T/C 1124-1-2DC39-20S
WIRE CODE 80114 FT14 FT--DC2426-1C-20NM (DMS
2426) or equivalent
WIRE CODE 801158 FT-26 FT-DC2426-1C-22NM (DMS
2426) or equivalent
WIRE CODE 801-4 FTDC2426-1C-24NM (DMS
2426) or equivalent
SOCKET T/C 52433742M39029/22-192
(a)TERMINAL LUG 8784---5D0086-3
(a)TERMINAL LUG 7622964-5D0086-6
(a) Or approved equivalent, refer to AEPL, Drawing 7595071.
2. Parts and Materials Supplied by the Operator:
None.
3. Parts Modified and Reidentified:
None.
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### Page 23

4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
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 24

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BLANK PAGE

### Page 25

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
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.
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY
ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE
CAN OCCUR.
CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions give the recommended
sequence of steps. The sequence of steps to do this service bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Equivalent parts are listed in the AEPL, Drawing 7595071.
4. Use the approved fastener and process material substitutions, MD-11-1F SRM
51-00-01, and MD-11-1P SRM 51-00-01.
5. Any protrusion of threads is acceptable provided that the threads do not rub or ride
against nearby wire assemblies or components.
6. 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.
7. Refer to these SWPM chapters for applicable operations, as accepted procedures:
OperationChapter
General - Maintenance Safety PracticesSWPM 20-00-00
Electrical Identification and Shop PracticesSWPM 20-00-09
Electrical Wire CodesSWPM 20-00-13
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### Page 26

Electrical Wire End Termination CodesSWPM 20-00-16
Fabricating and Installing Wire Harness -
Commercial
SWPM 20-10-01
Coil and Stow - Maintenance PracticesSWPM 20-10-04
Terminal Blocks - Maintenance PracticesSWPM 20-20-02
General Installation Hardwares - Maintenance
Practices
SWPM 20-20-03
Power Distribution Bus - Maintenance Prac-
tice
SWPM 20-40-01
8. Obey all of the warnings and cautions given in the specified manual sections as
applicable.
9. Review and understand all general notes of Service Rework Drawing SR11280063
sheets 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 3.10 and 7 before start of
modification.
10. These work instructions refer to procedures included on 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.
B. WORK INSTRUCTIONS
Group 1:
1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to
MD-11 AMM 28-14-01 as an accepted procedure.
2. Gain access to area of modification, refer to Table below:
Refer toName/LocationPanel Number
MD-11 AMM 06-35-00Access Panel Left Wing
Leading Edge
516AB, 516DB, 516EB,
518AB, 518BB, 518CB,
518GB, 525DB, 526DB,
526FB, 527AB
MD-11 AMM 06-36-00Access Panel Right Wing
Leading Edge
618BB, 618CB, 618GB,
625DB, 626DB, 627AB
MD-11 AMM 06-28-00Right Main Landing Gear
Wheel Well
Right Main Landing Gear
Door
MD-11 AMM 06-33-00Horizontal Stabilizer/fuel,
jack screw, and motors
311AB
3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices:
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### Page 27

In Accordance with AppendixLocation
AFuel Tank 1
BFuel Tank 2
CFuel Tank 3
DUpper and Lower Auxiliary Fuel Tanks
ETail Fuel Tank
4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix I.
5. Close access to area of modification.
6. Put the airplane back to a serviceable condition.
Group 2:
1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to
MD-11 AMM 28-14-01 as an accepted procedure.
2. Gain access to area of modification, refer to Table below:
Refer toName/LocationPanel Number
MD-11 AMM 06-35-00Access Panel Left Wing
Leading Edge
516AB, 516DB, 516EB,
518AB, 518BB, 518CB,
518GB, 525DB, 526DB,
526FB, 527AB
MD-11 AMM 06-36-00Access Panel Right Wing
Leading Edge
618BB, 618CB, 618GB,
625DB, 626DB, 627AB
MD-11 AMM 06-28-00Right Main Landing Gear
Wheel Well
Right Main Landing Gear
Door
MD-11 AMM 06-33-00Horizontal Stabilizer/fuel,
jack screw, and motors
311AB
MD-11 AMM 06-32-34Cabin Floor Panels Station
979 to 6-70
253GF, 253HF
3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices:
In accordance with AppendixLocation
AFuel Tank 1
BFuel Tank 2
CFuel Tank 3
DUpper and Lower Auxiliary Fuel Tanks
ETail Fuel Tank
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### Page 28

In accordance with AppendixLocation
FForward Auxiliary Fuel Tank
4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix J.
5. Close access to area of modification.
6. Put the airplane back to a serviceable condition.
Group 3:
1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to
MD-11 AMM 28-14-01 as an accepted procedure.
2. Gain access to area of modification, refer to Table below:
Refer toName/LocationPanel Number
MD-11 AMM 06-35-00Access Panel Left Wing
Leading Edge
516AB, 516DB, 516EB,
518AB, 518BB, 518CB,
518GB, 525DB, 526DB,
526FB, 527AB
MD-11 AMM 06-36-00Access Panel Right Wing
Leading Edge
618BB, 618CB, 618GB,
625DB, 626DB, 627AB
MD-11 AMM 06-28-00Right Main Landing Gear
Wheel Well
Right Main Landing Gear
Door
MD-11 AMM 06-33-00Horizontal Stabilizer/fuel,
jack screw, and motors
311AB
MD-11 AMM 06-32-34Cabin Floor Panels Station
979 to 6-70
253GF, 253HF
3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices:
In accordance with AppendixLocation
AFuel Tank 1
BFuel Tank 2
CFuel Tank 3
DUpper and Lower Auxiliary Fuel Tanks
ETail Fuel Tank
GForward Auxiliary Fuel Tank
4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix K.
5. Close access to area of modification.
6. Put the airplane back to a serviceable condition.
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### Page 29

Group 4:
1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to
MD-11 AMM 28-14-01 as an accepted procedure.
2. Gain access to area of modification, refer to Table below:
Refer toName/LocationPanel Number
MD-11 AMM 06-35-00Access Panel Left Wing
Leading Edge
516AB, 516DB, 516EB,
518AB, 518BB, 518CB,
518GB, 525DB, 526DB,
526FB, 527AB
MD-11 AMM 06-36-00Access Panel Right Wing
Leading Edge
618BB, 618CB, 618GB,
625DB, 626DB, 627AB
MD-11 AMM 06-28-00Right Main Landing Gear
Wheel Well
Right Main Landing Gear
Door
MD-11 AMM 06-33-00Horizontal Stabilizer/fuel,
jack screw, and motors
311AB
MD-11 AMM 06-32-34Cabin Floor Panels Station
979 to 6-70
253DF, 253EF, 253GF,
253HF
3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices:
In accordance with AppendixLocation
AFuel Tank 1
BFuel Tank 2
CFuel Tank 3
DUpper and Lower Auxiliary Fuel Tanks
ETail Fuel Tank
HForward Auxiliary Fuel Tanks No. 1 and 2
4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix L.
5. Close access to area of modification.
6. Put the airplane back to a serviceable condition.
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### Page 30

This Appendix applies only to: Group 1-4.
MORE DATADESCRIPTION OF TASKSTEP
In accordance with Drawing SR11280063 sheets
10, 11, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,
9.8, 105.201 and 305.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-119 within
float level switch reference designator
S1-119 wiring.
1
In accordance with Drawing SR11280063 sheets
10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7,
3.8, 9.7, 9.8, 105.201, 305.201 and 306.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-120 within
float level switch reference designator
S1-120 wiring.
2
In accordance with Drawing SR11280063 sheets
10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7,
3.8, 9.7, 9.8, 105.201 and 305.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-121 within
float level switch reference designator
S1-121 wiring.
3
In accordance with Drawing SR11280063 sheets
10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7,
3.8, 9.7, 9.9, 105.201, 305.202 and 306.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-176 within
float level switch reference designator
S1-176 wiring.
4
In accordance with Drawing SR11280063 sheets
10, 14, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,
9.9, 105.201 and 306.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-1391
within float level switch reference desig-
nator S1-1391 wiring.
5
In accordance with Drawing SR11280063 sheets
10, 13, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.9,
105.201 and 305.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-1392
within float level switch reference desig-
nator S1-1392 wiring.
6
In accordance with Drawing SR11280063 sheets
10, 12, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,
9.10, 105.201 and 305.202.
Install fuel tank float level switch In-line
fuse, reference designator F1-735 within
float level switch reference designator
S1-735 wiring.
7
Appendix A: FUEL TANK 1
(SHEET 1 OF 1)
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### Page 31

This Appendix applies only to: Group 1-4.
MORE DATADESCRIPTION OF TASKSTEP
In accordance with Drawing SR11280063
sheets 16, 16.3, 3, 3.1, 3.3, 3.5, 3.6 and 3.8.
Install new Terminal Board, item number
S3-454.
1
In accordance with Drawing SR11280063
sheets 10, 16, 16.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5,
3.6, 3.7, 3.8, 9.7, 9.11, 105.201 and 305.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-90 within
float level switch reference designator S1-
90 wiring.
2
In accordance with Drawing SR11280063
sheets 10, 16, 16.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5,
3.6, 3.7, 3.8, 9.7, 9.11, 105.201 and 305.202.
Install fuel tank float level switch In-line
fuse, reference designator F1-177 within
float level switch reference designator S1-
177 wiring.
3
In accordance with Drawing SR11280063
sheets 10, 16, 16.1, 16.2, 3, 3.1, 3.2, 3.3, 3.4,
3.5, 3.6, 3.7, 9.7, 9.11, 105.201 and 305.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-1363 within
float level switch reference designator S1-
1363 wiring.
4
In accordance with Drawing SR11280063
sheets 10, 16, 16.1, 16.2, 3, 3.1, 3.2, 3.3, 3.4,
3.5, 3.6, 3.7, 3.8, 9.7, 9.12, 105.201 and
305.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-1393 within
float level switch reference designator S1-
1393 wiring.
5
Appendix B: FUEL TANK 2
(SHEET 1 OF 1)
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### Page 32

This Appendix applies only to: Group 1-4.
MORE DATADESCRIPTION OF TASKSTEP
In accordance with Drawing SR11280063 sheets
10, 17, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,
9.13, 105.201 and 305.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-124
within level switch reference designator
S1-124 wiring.
1
In accordance with Drawing SR11280063 sheets
10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8,
9.7, 9.13, 105.201 and 305.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-122
within float level switch reference desig-
nator S1-122 wiring.
2
In accordance with Drawing SR11280063 sheets
10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8,
9.7, 9.13, 105.201 305.201 and 307.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-123
within float level switch reference desig-
nator S1-123 wiring.
3
In accordance with Drawing SR11280063 sheets
10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8,
9.7, 9.14, 105.201, 305.202 and 307.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-178
within float level switch reference desig-
nator S1-178 wiring.
4
In accordance with Drawing SR11280063 sheets
10, 20, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,
9.14, 105.201 and 307.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-1394
within float level switch reference desig-
nator S1-1394 wiring.
5
In accordance with Drawing SR11280063 sheets
10, 19, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,
9.15, 105.201 and 305.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-1395
within float level switch reference desig-
nator S1-1395 wiring.
6
In accordance with Drawing SR11280063 sheets
10, 18, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7,
9.15, 105.201 and 305.202.
Install fuel tank float level switch In-line
fuse, reference designator F1-734
within float level switch reference desig-
nator S1-734 wiring.
7
Appendix C: FUEL TANK 3
(SHEET 1 OF 1)
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### Page 33

This Appendix applies only to: Group 1-4.
MORE DATADESCRIPTION OF TASKSTEP
In accordance with Drawing
SR11280063 sheets 10, 22, 3, 3.1, 3.2,
3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.16,
103.201 and 303.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-1359 within
float level switch reference designator S1-
1359 wiring.
1
In accordance with Drawing
SR11280063 sheets 10, 23, 3, 3.1, 3.2,
3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 9.7, 9.16,
103.201 and 303.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-1360 within
float level switch reference designator S1-
1360 wiring.
2
Appendix D: UPPER AND LOWER AUXILIARY FUEL TANKS
(SHEET 1 OF 1)
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Original Issue: November 25, 2008
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### Page 34

This Appendix applies only to: Group 1-4.
MORE DATADESCRIPTION OF TASKSTEP
In accordance with Drawing SR11280063
sheets 10, 24, 24.1, 3, 3.1, 3.2, 3.3, 3.4,
3.5, 3.6, 3.7, 3.8, 9.7, 9.17, 104.201 and
304.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-1396 within
float level switch reference designator S1-
1396 wiring.
1
In accordance with Drawing SR11280063
sheets 10, 24, 24.2, 3, 3.1, 3.2, 3.4, 3.5,
3.6, 3.7, 3.8, 9.7, 9.17, 104.201 and
304.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-1397 within
float level switch reference designator S1-
1397 wiring.
2
Install fuel tank float level switch In-line
fuse, reference designator F1-1398 within
float level switch reference designator S1-
1398 wiring.
3
In accordance with Drawing SR11280063
sheets 10, 25, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6,
3.7, 3.8, 9.7, 9.18, 104.201 and 304.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-1399 within
float level switch reference designator S1-
1399 wiring.
4
Appendix E: TAIL FUEL TANK
(SHEET 1 OF 1)
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Original Issue: November 25, 2008
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### Page 35

This Appendix applies only to: Group 2.
MORE DATADESCRIPTION OF TASKSTEP
In accordance with Drawing SR11280063
sheets 10, 26, 26.1, 3, 3.1, 3.2, 3.3, 3.4,
3.5, 3.6, 3.7, 3.8, 3.10, 9.7, 9.20, 101.201
and 302.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-631 within
float level switch reference designator
S1-631 wiring.
1
Appendix F: FORWARD AUXILIARY FUEL TANK
(SHEET 1 OF 1)
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Original Issue: November 25, 2008
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### Page 36

This Appendix applies only to: Group 3.
MORE DATADESCRIPTION OF TASKSTEP
In accordance with Drawing SR11280063
sheets 10, 26, 26.1, 3, 3.1, 3.2, 3.3, 3.4,
3.5, 3.6, 3.7, 3.8, 3.10, 9.7, 9.20, 101.201
and 301.201.
Install fuel tank float level switch In-line
fuse, reference designator F1-631 within
float level switch reference designator
S1-631 wiring.
1
Appendix G: FORWARD AUXILIARY FUEL TANK
(SHEET 1 OF 1)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 25, 2008
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36 of 45
BOEING SERVICE BULLETIN MD11-28-132

### Page 37

This Appendix applies only to: Group 4.
MORE DATADESCRIPTION OF TASKSTEP
In accordance with Drawing SR11280063
sheets 10, 27, 27.1, 27.2, 27.3, 3, 3.1, 3.2,
3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.19,
102.201 and 308.201.
Install bracket and fuel tank float level
switch In-line fuse, reference designator
F1-191 within float level switch refer-
ence designator S1-191 wiring.
1
In accordance with Drawing SR11280063
sheets 10, 27, 27.1, 27.2, 27.3, 3, 3.1, 3.2,
3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.19,
102.201 and 308.201.
Install bracket and fuel tank float level
switch In-line fuse, reference designator
F1-243 within float level switch refer-
ence designator S1-243 wiring.
2
Appendix H: FORWARD AUXILIARY FUEL TANK NO. 1 STATION 1044.437 AND NO. 2 STATION 1124.437
(SHEET 1 OF 1)
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Original Issue: November 25, 2008
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37 of 45
BOEING SERVICE BULLETIN MD11-28-132

### Page 38

This Appendix applies only to: Group 1.
RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES
This test can be performed for each float switch circuit independently as the fuse is installed.
REFERENCES (AMM) Tasks:
MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT
This procedure should be used as necessary.
Depower the Fuel system and open the related C/Bs.
After fuse installation do a continuity test as shown in the table below.
Note: For some fuses check continuity between two pins, for others check continuity to ground.
REMARKSPINSTERMINALTEST TYPEFUSE TO BE TESTED
TANK 1
7 & 8S3-450LOOP CONTINUITYF1-176 - TANK 1 DUMP
1 & 6S3-450LOOP CONTINUITYF1-121 Tank 1 4000 lb
4 & 5S3-450LOOP CONTINUITYF1-120 Tank 1 6000 lb
1 & 2S3-1301LOOP CONTINUITYF1-1391 TK 1 INBD FULL
1 & 2S3-1300LOOP CONTINUITYF1-1392 TK 1 OUTBD FULL
1 & 3S3-366LOOP CONT NOT FULLF1-119 TK 1 TIP
VENT BOX1 & 2S3-684LOOP CONTINUITYF1-735 L WING OVERFILL
TANK 3
7 & 8S3-451LOOP CONTINUITYF1-178 - TANK 3 DUMP
6 & 2S3-451LOOP CONTINUITYF1-122 Tank 3 4000 lb
4 & 5S3-451LOOP CONTINUITYF1-123 Tank 3 6000 lb
1 & 2S3-1302LOOP CONTINUITYF1-1394 TK 3 INBD FULL
1 & 2S3-1303LOOP CONTINUITYF1-1395 TK 3 OUTBD FULL
2 & 3S3-452LOOP CONT NOT FULLF1-124 TK 3 TIP
VENT BOX1 & 2S3-683LOOP CONTINUITYF1-734 R WING OVERFILL
TANK 2
1 & 5S3-454LOOP CONTINUITYF1-177 TK 2 DUMP
4 & 6S3-454LOOP CONTINUITYF1-90 TK 2 40000 LB
3S3-454CONT TO GND ON EMPTYF1-1363 TK 2 10000 LB
2 & 7S3-454LOOP CONTINUITYF1-1393 TK 2 FULL
Appendix I: FUEL TESTS
(SHEET 1 OF 2)
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 25, 2008
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38 of 45
BOEING SERVICE BULLETIN MD11-28-132

### Page 39

RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES
TAIL TANK
1 & 3S3-756LOOP CONTINUITYF1-1396 TAIL TK EMPTY
1 & 3S3-758LOOP CONTINUITYF1-1397 TAIL L FULL
2 & 3S3-759LOOP CONTINUITYF1-1398 TAIL R FULL
VENT BOXPIN 1JXS3-739CONT BTW CONNECTF1-1399 Tail Tank Vent box
PIN 3P1-930
AUX TANKS
1 & 2S3-1186LOOP CONTINUITYF1-1359 UPPR AUX FULL
4 & 5S3-805LOOP CONTINUITYF1-1360 LWR AUX FULL
Appendix I: FUEL TESTS
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 25, 2008
MD11-28-132Revision 1 July 06, 2010
39 of 45
BOEING SERVICE BULLETIN MD11-28-132

### Page 40

This Appendix applies only to: Group 2.
RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES
This test can be performed for each float switch circuit independently as the fuse is installed.
REFERENCES (AMM) Tasks:
MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT
This procedure should be used as necessary.
Depower the Fuel system and open the related C/Bs.
After fuse installation do a continuity test as shown in the table below.
Note: For some fuses check continuity between two pins, for others check continuity to ground.
REMARKSPINSTERMINALTEST TYPEFUSE TO BE TESTED
TANK 1
7 & 8S3-450LOOP CONTINUITYF1-176 - TANK 1 DUMP
1 & 6S3-450LOOP CONTINUITYF1-121 Tank 1 4000 lb
4 & 5S3-450LOOP CONTINUITYF1-120 Tank 1 6000 lb
1 & 2S3-1301LOOP CONTINUITYF1-1391 TK 1 INBD FULL
1 & 2S3-1300LOOP CONTINUITYF1-1392 TK 1 OUTBD FULL
1 & 3S3-366LOOP CONT NOT FULLF1-119 TK 1 TIP
VENT BOX1 & 2S3-684LOOP CONTINUITYF1-735 L WING OVERFILL
TANK 3
7 & 8S3-451LOOP CONTINUITYF1-178 - TANK 3 DUMP
6 & 2S3-451LOOP CONTINUITYF1-122 Tank 3 4000 lb
4 & 5S3-451LOOP CONTINUITYF1-123 Tank 3 6000 lb
1 & 2S3-1302LOOP CONTINUITYF1-1394 TK 3 INBD FULL
1 & 2S3-1303LOOP CONTINUITYF1-1395 TK 3 OUTBD FULL
2 & 3S3-452LOOP CONT NOT FULLF1-124 TK 3 TIP
VENT BOX1 & 2S3-683LOOP CONTINUITYF1-734 R WING OVERFILL
TANK 2
1 & 5S3-454LOOP CONTINUITYF1-177 TK 2 DUMP
4 & 6S3-454LOOP CONTINUITYF1-90 TK 2 40000 LB
3S3-454CONT TO GND ON EMPTYF1-1363 TK 2 10000 LB
2 & 7S3-454LOOP CONTINUITYF1-1393 TK 2 FULL
Appendix J: FUEL TESTS
(SHEET 1 OF 2)
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 25, 2008
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40 of 45
BOEING SERVICE BULLETIN MD11-28-132

### Page 41

RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES
TAIL TANK
1 & 3S3-756LOOP CONTINUITYF1-1396 TAIL TK EMPTY
1 & 3S3-758LOOP CONTINUITYF1-1397 TAIL L FULL
2 & 3S3-759LOOP CONTINUITYF1-1398 TAIL R FULL
VENT BOXPIN 1JXS3-739CONT BTW CONNECTF1-1399 Tail Tank Vent box
PIN 3P1-930
AUX TANKS
1 & 2S3-1186LOOP CONTINUITYF1-1359 UPPR AUX FULL
4 & 5S3-805LOOP CONTINUITYF1-1360 LWR AUX FULL
FWD AUX TANK
ER5-448CONT TO GND ON EMPTYF1-631 FWD AUX EMPTY
Appendix J: FUEL TESTS
(SHEET 2 OF 2)
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 25, 2008
MD11-28-132Revision 1 July 06, 2010
41 of 45
BOEING SERVICE BULLETIN MD11-28-132

### Page 42

This Appendix applies only to: Group 3.
RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES
This test can be performed for each float switch circuit independently as the fuse is installed.
REFERENCES (AMM) Tasks:
MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT
This procedure should be used as necessary.
Depower the Fuel system and open the related C/Bs.
After fuse installation do a continuity test as shown in the table below.
Note: For some fuses check continuity between two pins, for others check continuity to ground.
REMARKSPINSTERMINALTEST TYPEFUSE TO BE TESTED
TANK 1
7 & 8S3-450LOOP CONTINUITYF1-176 - TANK 1 DUMP
1 & 6S3-450LOOP CONTINUITYF1-121 Tank 1 4000 lb
4 & 5S3-450LOOP CONTINUITYF1-120 Tank 1 6000 lb
1 & 2S3-1301LOOP CONTINUITYF1-1391 TK 1 INBD FULL
1 & 2S3-1300LOOP CONTINUITYF1-1392 TK 1 OUTBD FULL
1 & 3S3-366LOOP CONT NOT FULLF1-119 TK 1 TIP
VENT BOX1 & 2S3-684LOOP CONTINUITYF1-735 L WING OVERFILL
TANK 3
7 & 8S3-451LOOP CONTINUITYF1-178 - TANK 3 DUMP
6 & 2S3-451LOOP CONTINUITYF1-122 Tank 3 4000 lb
4 & 5S3-451LOOP CONTINUITYF1-123 Tank 3 6000 lb
1 & 2S3-1302LOOP CONTINUITYF1-1394 TK 3 INBD FULL
1 & 2S3-1303LOOP CONTINUITYF1-1395 TK 3 OUTBD FULL
2 & 3S3-452LOOP CONT NOT FULLF1-124 TK 3 TIP
VENT BOX1 & 2S3-683LOOP CONTINUITYF1-734 R WING OVERFILL
TANK 2
1 & 5S3-454LOOP CONTINUITYF1-177 TK 2 DUMP
4 & 6S3-454LOOP CONTINUITYF1-90 TK 2 40000 LB
3S3-454CONT TO GND ON EMPTYF1-1363 TK 2 10000 LB
2 & 7S3-454LOOP CONTINUITYF1-1393 TK 2 FULL
Appendix K: FUEL TESTS
(SHEET 1 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 25, 2008
MD11-28-132Revision 1 July 06, 2010
42 of 45
BOEING SERVICE BULLETIN MD11-28-132

### Page 43

RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES
TAIL TANK
1 & 3S3-756LOOP CONTINUITYF1-1396 TAIL TK EMPTY
1 & 3S3-758LOOP CONTINUITYF1-1397 TAIL L FULL
2 & 3S3-759LOOP CONTINUITYF1-1398 TAIL R FULL
VENT BOXPIN 1JXS3-739CONT BTW CONNECTF1-1399 Tail Tank Vent box
PIN 3P1-930
AUX TANKS
1 & 2S3-1186LOOP CONTINUITYF1-1359 UPPR AUX FULL
4 & 5S3-805LOOP CONTINUITYF1-1360 LWR AUX FULL
FWD AUX TANK
22P10-4410BCONT TO GND ON EMPTYF1-631 FWD AUX EMPTY
Appendix K: FUEL TESTS
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 25, 2008
MD11-28-132Revision 1 July 06, 2010
43 of 45
BOEING SERVICE BULLETIN MD11-28-132

### Page 44

This Appendix applies only to: Group 4.
RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES
This test can be performed for each float switch circuit independently as the fuse is installed.
REFERENCES (AMM) Tasks:
MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT
This procedure should be used as necessary.
Depower the Fuel system and open the related C/Bs.
After fuse installation do a continuity test as shown in the table below.
Note: For some fuses check continuity between two pins, for others check continuity to ground.
REMARKSPINSTERMINALTEST TYPEFUSE TO BE TESTED
TANK 1
7 & 8S3-450LOOP CONTINUITYF1-176 - TANK 1 DUMP
1 & 6S3-450LOOP CONTINUITYF1-121 Tank 1 4000 lb
4 & 5S3-450LOOP CONTINUITYF1-120 Tank 1 6000 lb
1 & 2S3-1301LOOP CONTINUITYF1-1391 TK 1 INBD FULL
1 & 2S3-1300LOOP CONTINUITYF1-1392 TK 1 OUTBD FULL
1 & 3S3-366LOOP CONT NOT FULLF1-119 TK 1 TIP
VENT BOX1 & 2S3-684LOOP CONTINUITYF1-735 L WING OVERFILL
TANK 3
7 & 8S3-451LOOP CONTINUITYF1-178 - TANK 3 DUMP
6 & 2S3-451LOOP CONTINUITYF1-122 Tank 3 4000 lb
4 & 5S3-451LOOP CONTINUITYF1-123 Tank 3 6000 lb
1 & 2S3-1302LOOP CONTINUITYF1-1394 TK 3 INBD FULL
1 & 2S3-1303LOOP CONTINUITYF1-1395 TK 3 OUTBD FULL
2 & 3S3-452LOOP CONT NOT FULLF1-124 TK 3 TIP
VENT BOX1 & 2S3-683LOOP CONTINUITYF1-734 R WING OVERFILL
TANK 2
1 & 5S3-454LOOP CONTINUITYF1-177 TK 2 DUMP
4 & 6S3-454LOOP CONTINUITYF1-90 TK 2 40000 LB
3S3-454CONT TO GND ON EMPTYF1-1363 TK 2 10000 LB
2 & 7S3-454LOOP CONTINUITYF1-1393 TK 2 FULL
Appendix L: FUEL TESTS
(SHEET 1 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 25, 2008
MD11-28-132Revision 1 July 06, 2010
44 of 45
BOEING SERVICE BULLETIN MD11-28-132

### Page 45

RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES
TAIL TANK
1 & 3S3-756LOOP CONTINUITYF1-1396 TAIL TK EMPTY
1 & 3S3-758LOOP CONTINUITYF1-1397 TAIL L FULL
2 & 3S3-759LOOP CONTINUITYF1-1398 TAIL R FULL
VENT BOXPIN 1JXS3-739CONT BTW CONNECTF1-1399 Tail Tank Vent box
PIN 3P1-930
AUX TANKS
1 & 2S3-1186LOOP CONTINUITYF1-1359 UPPR AUX FULL
4 & 5S3-805LOOP CONTINUITYF1-1360 LWR AUX FULL
FWD AUX TANKS
ER5-448CONT TO GND ON EMPTYF1-191 FWD AUX TK 1 LOW
DR5-448CONT TO GND ON EMPTYF1-243 FWD AUX TK 2 LOW
Appendix L: FUEL TESTS
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 25, 2008
MD11-28-132Revision 1 July 06, 2010
45 of 45
BOEING SERVICE BULLETIN MD11-28-132

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