# Boeing Alert Service Bulletin MD11-28A124: Revision 1

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- Document: [Boeing Alert Service Bulletin MD11-28A124](https://openairdocs.org/service-documents/boeing/md11-28a124.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin
- Pages: 36
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## Text

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### Page 1

Commercial 
Airplanes
MD11
Service Bulletin
ALERT
Number: MD11-28A124
Original Issue: June 17, 2009
Revision 1: August 24, 2010
ATA System: 2820
SUBJECT: FUEL - Distribution - Inspection/Change of the Tail Tank Fuel System Wire Assembly
Installation
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Unpublished Work - All Rights Reserved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
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 2
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 2
D. Description .............................................. 1 3
E. Compliance .............................................. 1 5
F. Approval ............................................... 1 5
G. Manpower .............................................. 1 5
H. Weight and Balance Changes .................................... 1 7
I. Electrical Load Data ......................................... 1 7
J. References .............................................. 1 7
1. Existing Data: ......................................... 1 7
2. Data supplied with this Service Bulletin: ........................... 1 8
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 8
K. Publications Affected ........................................ 1 8
L. Interchangeability and Intermixability of Parts ........................... 1 8
2. MATERIAL INFORMATION ........................................ 1 9
A. Material - Price and Availability ................................... 1 9
B. Industry Support Information .................................... 1 9
C. Parts Necessary For Each Airplane ................................. 1 9
1. Kits/Parts: ........................................... 1 9
2. Parts and Materials Supplied by the Operator: ........................ 2 1
3. Parts Modified and Reidentified: ............................... 2 6
4. Parts Removed and Not Replaced: .............................. 2 6
D. Parts Necessary to Change Spares ................................. 2 6
E. Special Tooling - Price and Availability ............................... 2 6
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 6
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 7
A. GENERAL INFORMATION ..................................... 2 7
B. WORK INSTRUCTIONS ....................................... 2 8
FIGURE 1: SELF-ADHERING, HIGH-TEMPERATURE ELECTRICAL INSULATION TAPE INSTALLATION
AND WIRE SUPPORT - INSPECTION/CHANGE [Group 1, Configuration 2] ........ 3 3
FIGURE 2: WIRE SUPPORT - CHANGE [Group 2, Configuration 2] ................... 3 5
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Commercial 
Airplanes
MD11
Service Bulletin
ALERT
Revision Transmittal SheetNumber: MD11-28A124Original Issue: June 17, 2009
Revision 1: August 24, 2010
ATA System: 2820
SUBJECT: FUEL - Distribution - Inspection/Change of the Tail Tank Fuel System Wire Assembly
Installation
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2009-NM-252-AD, is related
to this service bulletin.
More work is necessary on airplanes changed in accordance with the original issue of this service bulletin. The
more work does a General Visual Inspection (GVI) of the self-adhering, high-temperature electrical insulation
tape for correct installation and changes wire supports.
REASON FOR REVISION
This revision is sent to incorporate engineering released subsequent to the original issue of this service bulletin
which clarifies the work instructions, does a GVI of the self-adhering, high-temperature electrical insulation tape
for correct installation and changes wire supports.
This revision incorporates the changes given in Information Notice MD11-28A124 IN 01 and corrects the no-work
condition given in Information Notice MD11-28A124 IN 02 and is included in this revision.
An additional 3.3 task hours for Group 1 Configuration 2 and 3.0 task hours for Group 2 Configuration 2 are
required.
These sections were changed:
1. In Paragraph 1.D., Description, added Group/Configuration data.
2. In Paragraph 1.E., Compliance, added NPRM information.
3. In Paragraph 1.G., Manpower, added Group/Configuration data.
4. In Paragraph 1.H., Weight and Balance Changes, changed information.
5. In Paragraph 1.J.1.e., Existing Data, added NPRM information.
6. In Paragraph 1.J.2.a., Drawings, changed drawing revision level.
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7. In Paragraph 2.A., Materials - Price and Availability, changed kits information.
8. In Paragraph 2.B., Industry Support Information, changed information.
9. In Paragraph 2.C.1., Kits/Parts, changed kits information and added Group/Configuration data.
10. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added Group/Configuration data.
11. In Paragraph 3.A., General Information, changed notes.
12. In Paragraph 3.B., Work Instructions, added Group/Configurations data.
13. Added Figures 1 and 2.
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
June 17, 2009Original Issue:
August 24, 2010Revision 1:
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Commercial 
Airplanes
MD11
Service Bulletin
ALERT
SummaryNumber: MD11-28A124Original Issue: June 17, 2009
Revision 1: August 24, 2010
ATA System: 2820
SUBJECT: FUEL - Distribution - Inspection/Change of the Tail Tank Fuel System Wire Assembly
Installation
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
None.
BACKGROUND
An investigation by Boeing has determined that tail tank fuel system wire assemblies routed together and in
close proximity to the upper surface of the tail tank are a potential ignition source should wire damage occur.
Also, during normal maintenance, wire damage may be caused when maintenance personnel working in the
tail tank area inadvertently step on the wire assemblies causing contact with the tail tank upper surface and/or
where the wire assemblies transition down the front spar horizontal stabilizer. Inspecting the tail tank wiring for
damage and repair/replacing if required and providing protection of the wires, will minimize the possibility of wire
damage in the tail tank area. If not corrected, in a case of wire damage, there is a possibility of burn-through on
the upper surface of the tail tank that could potentially result in an explosion.
This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation
Regulation (SFAR) 88, "Fuel Tank System Fault Tolerance Evaluation Requirements".
Airworthiness Limitation Instruction (ALI) 20-2 from Report MDC-02K1003 affects airplane maintenance
documents.
ACTION
Refer to Paragraph 1.D., Description.
EFFECTIVITY
MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
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COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2009-NM-252-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 inspection/change given in this service bulletin be done within 5 years after the
original issue date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection, configuration changes and/or repair procedures
given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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Commercial 
Airplanes
MD11
Service Bulletin
ALERT
Number: MD11-28A124
Original Issue: June 17, 2009
Revision 1: August 24, 2010
ATA System: 2820
SUBJECT: FUEL - Distribution - Inspection/Change of the Tail Tank Fuel System Wire Assembly
Installation
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
Applicable to airplanes that require additional wire separation and is
affected by Service Rework Drawing/Configuration
SR11280052-7001.
-1
Applicable to operators who have not accomplished the original issue
service bulletin.
1
Applicable to operators who have accomplished the original issue
service bulletin and have more work.
2
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DESCRIPTIONCONFIGURATIONGROUP
Applicable to airplanes that do not require additional wire separation
and is affected by Service Rework Drawing/Configuration
SR11280052-7003.
-2
Applicable to operators who have not accomplished the original issue
service bulletin.
1
Applicable to operators who have accomplished the original issue
service bulletin and have more work.
2
Airplane Models:
MD-11, MD-11F
GroupFuselage Num-
ber
2447 - 449
2451 - 460
1461 - 464
1466 - 489
1491 - 517
1519 - 552
1554 - 646
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
An investigation by Boeing has determined that tail tank fuel system wire assemblies routed together
and in close proximity to the upper surface of the tail tank are a potential ignition source should wire
damage occur. Also, during normal maintenance, wire damage may be caused when maintenance
personnel working in the tail tank area inadvertently step on the wire assemblies causing contact with
the tail tank upper surface and/or where the wire assemblies transition down the front spar horizontal
stabilizer. Inspecting the tail tank wiring for damage and repair/replacing if required and providing
protection of the wires, will minimize the possibility of wire damage in the tail tank area. If not corrected,
in a case of wire damage, there is a possibility of burn-through on the upper surface of the tail tank that
could potentially result in an explosion.
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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".
Airworthiness Limitation Instruction (ALI) 20-2 from Report MDC-02K1003 affects airplane maintenance
documents.
Revision 1 is sent to incorporate engineering released subsequent to the original issue of this service
bulletin which clarifies the work instructions, does a GVI of the self-adhering, high-temperature electrical
insulation tape for correct installation and changes wire supports.
Revision 1 incorporates the changes given in Information Notice MD11-28A124 IN 01 and corrects the
no-work condition given in Information Notice MD11-28A124 IN 02 and is included in this revision.
An additional 3.3 task hours for Group 1 Configuration 2 and 3.0 task hours for Group 2 Configuration
2 are required.
D. Description
Group 1, Configuration 1:
1. This service bulletin does a General Visual Inspection (GVI) of the tail tank fuel system wire
assembly installation for damage and does as follows:
Condition 1: No Wire Damage Found
a. Separates wire assemblies and individually wraps each with self-adhering, high-temperature
electrical insulation tape.
b. Installs wire assembly support brackets/routes wire assemblies.
c. Installs a wire protection bracket.
Condition 2: Wire Damage Found
a. Repairs or replaces wires.
b. Separates wire assemblies and individually wraps each with self-adhering, high-temperature
electrical insulation tape.
c. Installs wire assembly support brackets/routes wire assemblies.
d. Installs a wire protection bracket.
2. Puts the airplane back to a serviceable condition.
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Group 2, Configuration 1:
1. This service bulletin does a GVI of the tail tank fuel system wire assembly installation for damage
and does as follows:
Condition 1: No Wire Damage Found
a. Installs wire assembly support brackets/routes wire assemblies.
b. Installs a wire protection bracket.
Condition 2: Wire Damage Found
a. Repairs or replaces wires.
b. Installs wire assembly support brackets/routes wire assemblies.
c. Installs a wire protection bracket.
2. Puts the airplane back to a serviceable condition.
Group 1, Configuration 2:
1. Does a GVI of the self-adhering, high-temperature electrical insulation tape for correct installation,
and changes wire supports.
2. Puts the airplane back to a serviceable condition.
Group 2, Configuration 2:
1. Changes wire supports.
2. Puts the airplane back to a serviceable condition.
Revision 1 - More work is necessary on airplanes changed in accordance with the original issue of this
service bulletin. The more work does a GVI of the self-adhering, high-temperature electrical insulation
tape for correct installation and changes wire supports.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
311MD-11, MD-11F
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E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2009-NM-252-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 inspection/change given in this service bulletin be done within 5 years
after the original issue date of 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.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Group 1, Configuration 1:
Elapsed HoursTask HoursNumber of
Persons
Task
Condition 2Condition 1Condition 2Condition 1
0.50.51.01.02Open Access
2.02.02.02.01Removal
0.50.50.50.51Inspection
6.06.01Repair
8.08.016.016.02Change
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Group 1, Configuration 1:
Elapsed HoursTask HoursNumber of
Persons
Task
Condition 2Condition 1Condition 2Condition 1
0.50.51.01.02Close Access
17.511.528.020.5TOTAL FOR EACH AIRPLANE
NOTE:
Group 1, Configuration 2:
Elapsed
Hours
Task HoursNumber of
Persons
Task
0.51.02Open Access
0.30.31Inspect
1.01.01Figure 1
0.51.02Close Access
2.33.3TOTAL FOR EACH AIRPLANE
NOTE: Maximum total task hours and elapsed hours are given per airplane. Actual task hours and
elapsed hours are contingent upon inspection findings and are to be estimated by the operator.
Group 2, Configuration 1:
Elapsed HoursTask HoursNumber of
Persons
Task
Condition 2Condition 1Condition 2Condition 1
0.50.51.01.02Open Access
2.02.02.02.01Removal
0.50.50.50.51Inspection
6.06.01Repair
8.05.016.010.02Change
0.50.51.01.02Close Access
16.08.522.014.5TOTAL FOR EACH AIRPLANE
Group 2, Configuration 2:
Elapsed
Hours
Task HoursNumber of
Persons
Task
0.51.02Open Access
1.01.01Figure 2
0.51.02Close Access
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Group 2, Configuration 2:
Elapsed
Hours
Task HoursNumber of
Persons
Task
2.03.0TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Group 1:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS Increase
Approximate Station
(Inches)
Airplane
MD-11 and MD-11F
+19,328.4+9.02147.6Condition 1
+29,725.2+13.82154.0Condition 2
Group 2:
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS Increase
Approximate Sta-
tion (Inches)
Airplane
MD-11 and MD-11F
+18,250.4+8.52147.1Condition 1
+28,432.8+13.22154.0Condition 2
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin MD11-28-102.
b. MD-11 Structural Repair Manual (SRM) 51.
c. Standard Wiring Practices Manual (SWPM) 20-00-03, 20-00-09, 20-00-13, 20-10-01, 20-10-10,
20-10-17, and 20-50-01.
d. MD-11 Aircraft Maintenance Manual (AMM) 06-33-00, 24-40-00, 27-40-00, and 29-00-00.
e. FAA Notice of Proposed Rule Making (NPRM) 2009-NM-252-AD.
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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
-HDWGAlert - Tail Fuel Tank Wire InstallationSR11280052
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
55-11Illustrated Parts Catalog
MDC-02K1003 (ALI 20-2)Special Compliance Item Report
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated 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
the Revision 01
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
Revision 01 date
of this Service
Bulletin (Calendar
Days)
NameKit Number
$11,829.0090Service KitSA11280124-7
9.0030Supplemental KitSA11280124-9
B. Industry Support Information
Boeing warranty remedies are not available for the inspection, configuration changes and/or 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.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
Group 1-2, Configuration 1:
Kit SA11280124
NotesExisting Part
Number
NameQTYNew Part Number
-7
(a)SCREW13D0005-3-12
(a)SCREW13D0005-3-22
(a)SCREW13D0005-3-30
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Group 1-2, Configuration 1:
Kit SA11280124
NotesExisting Part
Number
NameQTYNew Part Number
-7
(a)SCREW93D0005-3-8
(a)NUT-CLIP93D0039-14
(a)NUT-CLIP33D0039-16
BRACKET69D0230-3L080824
BRACKET39D0230-3L080832
(a)STRAP219D0254-1-1-9
BRACKET1AAP8000-539
(b)ALN8600-551BRACKET1AAP8004-1103
PIN2HL326-5-4
NUT2MS21042L08
NUT3MS21042L3
CLAMP1MS21919WDG10
SCREW1NAS1096-3-12
SCREW6NAS1096-3-10
SCREW1NAS1096-3-8
WASHER27NAS1252-10L
WASHER2NAS1252-416H
WASHER2NAS1252-8L
SCREW2NAS1801-4-11
(a)SPACER1NAS43DD3-16FC
(a)SPACER1NAS43DD3-48FC
(a)SPACER1NAS43DD3-72FC
(a)CLAMP6S7934111-10SA
(a)CLAMP5S7934111-14SA
(a)CLAMP1S7934111-24SA
(a)CLAMP3S7934111-4SA
(a)CLAMP7S7934111-6SA
(a)CLAMP1S7934111-7SA
BRACKET1SR11280052-13
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### Page 21

Group 1-2, Configuration 1:
Kit SA11280124
NotesExisting Part
Number
NameQTYNew Part Number
-7
EXTRUDED
CHANNEL
8SR11280052-17
BRACKET1SR11280052-29
BRACKET1SR11280052-31
BRACKET1SR11280052-33
(a) Or approved Equivalent. Refer to AEPL, Drawing 7595071.
(b) Discard the existing part.
Group 1-2, Configuration 2:
Supplemental Kit SA11280124
NotesExisting Part
Number
NameQTYNew Part Number
-9
(a)CLAMP2S7934111-4SA
SCREW2NAS1801-4-11
(a) Or approved Equivalent. Refer to AEPL, Drawing 7595071.
2. Parts and Materials Supplied by the Operator:
Group 1, Configuration 1:
Condition 1: No Wire Damage Found
NotesNameQTYPart Number / Specifi-
cation
(a) (e)TAPE (ELASTOMER)80 FT x 1.0
Inch Width
SR11280052-11
(DMS 2186 Type 2)
or
T2/600T Series
(b) (e)COATING CHEMICAL FILM, LIQUIDAs RequiredAlodine 1500
(DPM 5089-1)
(c)PRIMER, FR4 Oz.515X347 Base with
910X527 Catalyst
(DMS 1786)
or
Equivalent
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### Page 22

Group 1, Configuration 1:
Condition 1: No Wire Damage Found
NotesNameQTYPart Number / Specifi-
cation
(d)ENAMEL, HIGH SOLIDS EPOXY TOP-
COAT, GLOSS WHITE
1 Oz.446-21-7507 Base
DN7507 White with X-
530 Activator
(DMS 2433-2C)
or
Equivalent
(a) Can be purchased from: Arlon Silicone Technologies, 1100 Governor Lea Road, Bear,
Delaware 19701, CAGE 52869
(b) Can be purchased from: Zip-Chem Products, 400 Jarvis Drive, Suite A, Morgan Hill, Cal-
ifornia 95037, CAGE 1KQX9
(c) Can be purchased from: PRC-DeSoto International, Incorporated, 11601 United Street,
Mojave, California 93501-7048, CAGE 85570
(d) Can be purchased from: Integral Products, Incorporated, 24030 Frampton Avenue, Harbor
City, California 90710-2102, CAGE 1KSU0
(e) Or approved Equivalent.
Group 1, Configuration 1:
Condition 2: Wire Damage Found
NotesNameQTYPart Number / Specifi-
cation
(a) (i)TAPE (ELASTOMER)80 FT x 1.0 Inch
Width
SR11280052-11
(DMS 2186 Type 2)
or
T2/600T Series
(b)SLEEVE (BRAIDED, EXPANDABLE
ARAMID FIBER/PPS, MONOFILA-
MENT, PREFORMED WRAP-
AROUND)
10 FT x 1.187 I.D.SR11280052-21
(DMS 2379 Type 5,
Class 4)
or
5678103007S
(a) (i)TAPE (ELASTOMER)36 YARDS x 1.0
Inch Width
SR11280052-23
(DMS 2186 Type 1)
or
T3/SA Series
(c)TAPE (POLYURETHANE NUMBER
8672, TRANSPARENT)
36 YARDS x 1.0
Inch Width
SR11280052-25
(DPM 5777-6)
(d) (i)COATING CHEMICAL FILM, LIQUIDAs RequiredAlodine 1500
(DPM 5089-1)
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### Page 23

Group 1, Configuration 1:
Condition 2: Wire Damage Found
NotesNameQTYPart Number / Specifi-
cation
(g)PRIMER, FR4 Oz.515X347 Base with
910X527 Catalyst
(DMS 1786)
or
Equivalent
(h)ENAMEL, HIGH SOLIDS EPOXY TOP-
COAT, GLOSS WHITE
1 Oz.446-21-7507 Base
DN7507 White with X-
530 Activator
(DMS 2433-2C)
or
Equivalent
(e)SPLIT FERRULE5M85049/93-10
(f)CLAMP, LOOP109D0180-1
or
A10086
(a) Can be purchased from: Arlon Silicone Technologies, 1100 Governor Lea Road, Bear,
Delaware 19701, CAGE 52869
(b) Can be purchased from: Federal Mogul Corporation, 1277 Joe Battle Boulevard, El Paso,
Texas 79936-0966, CAGE 81851
(c) Can be purchased from: 3M Company, 3M Center, Saint Paul, Minnesota 55144-1000, CAGE
0KHE3
(d) Can be purchased from: Zip-Chem Products, 400 Jarvis Drive, Suite A, Morgan Hill, California
95037, CAGE 1KQX9
(e) Can be purchased from: Glenair, Incorporated, 1211 Air Way, Glendale, California 91201-
2405, CAGE 06324
(f) Can be purchased from: Band-It-Idex, Incorporated, 4799 Dahlia Street, Denver, Colorado
80216-3222, CAGE 3BBM2
(g) Can be purchased from: PRC-DeSoto International, Incorporated, 11601 United Street, Mo-
jave, California 93501-7048, CAGE 85570
(h) Can be purchased from: Integral Products, Incorporated, 24030 Frampton Avenue, Harbor
City, California 90710-2102, CAGE 1KSU0
(i) Or approved Equivalent.
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### Page 24

Group 2, Configuration 1:
Condition 1: No Wire Damage Found
NotesNameQTYPart Number / Specifi-
cation
(a) (d)COATING CHEMICAL FILM, LIQUIDAs RequiredAlodine 1500
(DPM 5089-1)
(b)PRIMER, FR4 Oz.515X347 Base with
910X527 Catalyst
(DMS 1786)
or
Equivalent
(c)ENAMEL, HIGH SOLIDS EPOXY TOP-
COAT, GLOSS WHITE
1 Oz.446-21-7507 Base
DN7507 White with X-
530 Activator
(DMS 2433-2C)
or
Equivalent
(a) Can be purchased from: Zip-Chem Products, 400 Jarvis Drive, Suite A, Morgan Hill, Cal-
ifornia 95037, CAGE 1KQX9
(b) Can be purchased from: PRC-DeSoto International, Incorporated, 11601 United Street,
Mojave, California 93501-7048, CAGE 85570
(c) Can be purchased from: Integral Products, Incorporated, 24030 Frampton Avenue, Harbor
City, California 90710-2102, CAGE 1KSU0
(d) Or approved Equivalent.
Group 2, Configuration 1:
Condition 2: Wire Damage Found
NotesNameQTYPart Number / Specifi-
cation
(a)SLEEVE (BRAIDED, EXPANDABLE
ARAMID FIBER/PPS, MONOFILA-
MENT, PREFORMED WRAP-
AROUND)
10 FT x 1.187
I.D.
SR11280052-21
(DMS 2379 Type 5,
Class 4)
or
5678103007S
(b) (i)TAPE (ELASTOMER)36 YARDS x
1.0 Inch Width
SR11280052-23
(DMS 2186 Type 1)
or
T3/SA Series
(c)TAPE (POLYURETHANE NUMBER
8672, TRANSPARENT)
36 YARDS x
1.0 Inch Width
SR11280052-25
(DPM 5777-6)
(d) (i)COATING CHEMICAL FILM, LIQUIDAs RequiredAlodine 1500
(DPM 5089-1)
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### Page 25

Group 2, Configuration 1:
Condition 2: Wire Damage Found
NotesNameQTYPart Number / Specifi-
cation
(g)PRIMER, FR4 Oz.515X347 Base with
910X527 Catalyst
(DMS 1786)
or
Equivalent
(h)ENAMEL, HIGH SOLIDS EPOXY TOP-
COAT, GLOSS WHITE
1 Oz.446-21-7507 Base
DN7507 White with X-
530 Activator
(DMS 2433-2C)
or
Equivalent
(e)SPLIT FERRULE5M85049/93-10
(f)CLAMP, LOOP109D0180-1
or
A10086
(a) Can be purchased from: Federal Mogul Corporation, 1277 Joe Battle Boulevard, El Paso,
Texas 79936-0966, CAGE 81851
(b) Can be purchased from: Arlon Silicone Technologies, 1100 Governor Lea Road, Bear,
Delaware 19701, CAGE 52869
(c) Can be purchased from: 3M Company, 3M Center, Saint Paul, Minnesota 55144-1000,
CAGE 0KHE3
(d) Can be purchased from: Zip-Chem Products, 400 Jarvis Drive, Suite A, Morgan Hill, Cal-
ifornia 95037, CAGE 1KQX9
(e) Can be purchased from: Glenair, Incorporated, 1211 Air Way, Glendale, California 91201-
2405, CAGE 06324
(f) Can be purchased from: Band-It-Idex, Incorporated, 4799 Dahlia Street, Denver, Colorado
80216-3222, CAGE 3BBM2
(g) Can be purchased from: PRC-DeSoto International, Incorporated, 11601 United Street,
Mojave, California 93501-7048, CAGE 85570
(h) Can be purchased from: Integral Products, Incorporated, 24030 Frampton Avenue, Harbor
City, California 90710-2102, CAGE 1KSU0
(i) Or approved Equivalent.
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### Page 26

Group 1, Configuration 2:
NotesNameQTYPart Number / Specifi-
cation
(a) (b) (c)TAPE (ELASTOMER)5 FT x 1.0 Inch
Width
SR11280052-11
(DMS 2186 Type 2)
or
T2/600T Series
(a) Can be purchased from: Arlon Silicone Technologies, 1100 Governor Lea Road, Bear,
Delaware 19701, CAGE 52869
(b) As required based on inspection findings.
(c) Or approved Equivalent.
Group 2, Configuration 2:
None.
3. Parts Modified and Reidentified:
None.
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 27

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY
ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE
CAN OCCUR.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions give the recommended
sequences of steps. The sequences 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. For equivalent parts, refer to AEPL, Drawing 7595071.
4. If the length of any fastener specified in this service bulletin does not meet installation
standards given in Structural Repair Manual (SRM) Chapter 51, then a fastener of
the same specification, or an approved substitute, with a length which meets the
installation standards given in SRM Chapter 51 may be used. In addition, washers
may be installed for fastener grip length in accordance with SRM Chapter 51.
5. Locate/position clamps as required to clear airplane structure/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 Standard Wiring Practices Manual (SWPM) Chapters for applicable
operations as accepted procedures:
Identification of Electrical Wire - CommercialSWPM 20-00-03
General Maintenance Practices - ElectricalSWPM 20-00-09
Electrical Wire CodesSWPM 20-00-13
Wiring Installation - Maintenance PracticesSWPM 20-10-01
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### Page 28

Wire Harness and Component CleaningSWPM 20-10-10
Braided Electrical Wire BundlesSWPM 20-10-17
Electrical Bonding - Maintenance PracticesSWPM 20-50-01
8. Obey all of the warnings and cautions given in the specified manual sections.
9. A General Visual Inspection (GVI) is defined as: A visual examination of an interior
or exterior area, installation or assembly to detect obvious damage, failure or
irregularity. This level of inspection is made from within touching distance unless
otherwise specified. A mirror may be necessary to ensure visual access to all surfaces
in the inspection area. This level of inspection is made under normal available lighting
conditions such as daylight, hangar lighting, flashlight or drop-light and may require
removal or opening of access panels or doors. Stands, ladders or platforms may be
required to gain proximity to the area being checked.
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.
11. Review and understand all general notes of Service Rework Drawing SR11280052,
Sheets 3 through 3.18 before starting modification.
12. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
The removed part can be discarded if a new or serviceable part is installed.
13. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
B. WORK INSTRUCTIONS
Group 1, Configuration 1:
1. Pressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure.
2. Position horizontal stabilizer between 3 and 14 Degrees Aircraft Nose Up, (ANU) to provide
maximum clearance in the work area. Refer to MD-11 AMM 27-40-00 as an accepted procedure.
3. Depressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure.
4. Remove electrical power from the airplane. Refer to MD-11 AMM 24-40-00 as an accepted
procedure.
5. Gain access to the tail tank fuel system wire assembly installation by opening access doors that
follow:
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### Page 29

Refer to:LocationAccess Door
MD-11 AMM 06-33-00.Lower Aft Fuselage311AB
316AB
6. Remove clamps and keep attaching hardware from wire assemblies in accordance with Service
Rework Drawing SR11280052, Sheets 6 and 6.1.
7. Separate AJS9013 and AJS9014 wire assemblies in accordance with Service Rework Drawing
SR11280052, Sheet 6.
8. Do a GVI of the AJS9013, AJS9014, AJS9015, and AGS9124 wire assemblies in accordance with
Service Rework Drawing SR11280052, Sheet 3.4 and do as follows:
Condition 1: No Wire Assembly Damage Found
a. Continue at Step 9.
Condition 2: Wire Assembly Damage Found
a. Repair or replace wire assemblies in accordance with Service Rework Drawing SR11280052,
Sheets 3.4 through 3.17.
b. Continue at Step 9.
9. Apply self-adhering, high-temperature electrical insulation tape on AJS9013 and AJS9014 wire
assemblies in accordance with Service Rework Drawing SR11280052, Sheets 6 and 6.1.
10. Install wire assembly support brackets and route wire assemblies AJS9013 and AJS9014 in
accordance with Service Rework Drawing SR11280052, Sheets 6.0, 6.1, 6.2, 7.1, and 7.3.
11. Install extruded channel wire supports in accordance with Service Rework Drawing SR11280052,
Sheet 6.
12. Install bracket in accordance with Service Rework Drawing SR11280052, Sheet 7.
13. Close access to the tail tank fuel system wire assembly installation by closing the following access
panels:
Refer to:LocationAccess Door
MD-11 AMM 06-33-00.Lower Aft Fuselage311AB
316AB
14. Put the airplane back to a serviceable condition.
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### Page 30

Group 1, Configuration 2:
1. Pressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure.
2. Position horizontal stabilizer between 3 and 14 Degrees Aircraft Nose Up, (ANU) to provide
maximum clearance in the work area. Refer to MD-11 AMM 27-40-00 as an accepted procedure.
3. Depressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure.
4. Remove electrical power from the airplane. Refer to MD-11 AMM 24-40-00 as an accepted
procedure.
5. Gain access to the tail tank fuel system wire assembly installation by opening access doors that
follow:
Refer to:LocationAccess Door
MD-11 AMM 06-33-00.Lower Aft Fuselage311AB
316AB
6. Do a GVI of the self-adhering, high-temperature electrical insulation tape for correct installation
and change wire supports in accordance with Figure 1.
7. Close access to the tail tank fuel system wire assembly installation by closing the following access
panels:
Refer to:LocationAccess Door
MD-11 AMM 06-33-00.Lower Aft Fuselage311AB
316AB
8. Put the airplane back to a serviceable condition.
Group 2, Configuration 1:
1. Pressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure.
2. Position horizontal stabilizer between 3 and 14 Degrees Aircraft Nose Up, (ANU) to provide
maximum clearance in the work area. Refer to MD-11 AMM 27-40-00 as an accepted procedure.
3. Depressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure.
4. Remove electrical power from the airplane. Refer to MD-11 AMM 24-40-00 as an accepted
procedure.
5. Gain access to the tail tank fuel system wire assembly installation by opening the following access
panels:
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### Page 31

Refer to:LocationAccess Door
MD-11 AMM 06-33-00.Lower Aft Fuselage311AB
316AB
6. Remove clamps and keep attaching hardware from wire assemblies in accordance with Service
Rework Drawing SR11280052, Sheets 6.3 and 6.4.
7. Do a GVI of the AJS9013, AJS9014, AJS9015, and AGS9124 wire assemblies in accordance with
Service Rework Drawing SR11280052, Sheet 3.4 and do as follows:
Condition 1: No Wire Assembly Damage Found
a. Continue at Step 8.
Condition 2: Wire Assembly Damage Found
a. Repair or replace wire assemblies in accordance with Service Rework Drawing SR11280052,
Sheets 3.4 through 3.17.
b. Continue at Step 8.
8. Install wire assembly support brackets and route wire assemblies AJS9013 and AJS9014 in
accordance with Service Rework Drawing SR11280052, Sheets 6.2, 6.3, 6.4, 7.1, and 7.3.
9. Install extruded channel wire supports in accordance with Service Rework Drawing SR11280052,
Sheet 6.3.
10. Install bracket in accordance with Service Rework Drawing SR11280052, Sheet 7.
11. Close access to the tail tank fuel system wire assembly installation by closing the following access
panels:
Refer to:LocationAccess Door
MD-11 AMM 06-33-00.Lower Aft Fuselage311AB
316AB
12. Put the airplane back to a serviceable condition.
Group 2, Configuration 2:
1. Pressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure.
2. Position horizontal stabilizer between 3 and 14 Degrees Aircraft Nose Up, (ANU) to provide
maximum clearance in the work area. Refer to MD-11 AMM 27-40-00 as an accepted procedure.
3. Depressurize hydraulic systems. Refer to MD-11 AMM 29-00-00 as an accepted procedure.
4. Remove electrical power from the airplane. Refer to MD-11 AMM 24-40-00 as an accepted
procedure.
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### Page 32

5. Gain access to the tail tank fuel system wire assembly installation by opening access doors that
follow:
Refer to:LocationAccess Door
MD-11 AMM 06-33-00.Lower Aft Fuselage311AB
316AB
6. Change wire supports in accordance with Figure 2.
7. Close access to the tail tank fuel system wire assembly installation by closing the following access
panels:
Refer to:LocationAccess Door
MD-11 AMM 06-33-00.Lower Aft Fuselage311AB
316AB
8. Put the airplane back to a serviceable condition.
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### Page 33 (OCR)

BOEING SERVICE BULLETIN MD11-28A124
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 2.
B-B
AJS9014  AJS9014
AJS9013
,0.75/1.25
AJS9014
0.75/1.25
0.75/1.25
0.75/1.25
FWD  2000397
FIGURE 1: SELF-ADHERING, HIGH-TEMPERATURE ELECTRICAL INSULATION TAPE INSTALLATION
AND WIRE SUPPORT - INSPECTION/CHANGE
(SHEET 1 OF 2)
Original Issue: June 17, 2009
Revision 1 August 24, 2010  Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  MD11-28A124  33 of 36

### Page 34

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)-SR11280052-11TapeInspect1
--NutRemove/Keep2
--Washer
--Screw
1-ClampRemove
1S7934111-4SAClampInstall (New)3
--WasherInstall (Kept)
--Screw
--Nut
--ScrewRemove/Keep4
--Washer
1-ClampRemove
1S7934111-4SAClampInstall (New)5
--WasherInstall (Kept)
--Screw
Barrel facing aft.1S7934111-4SAClampChange6
23D0005-4-6ScrewRemove7
2NAS1252-416HWasherRemove/Keep
2NAS1252-416HWasherInstall/Kept8
2NAS1801-4-11ScrewInstall (New)
(a) Adjust tape installation as necessary to achieve noted dimensions.
FIGURE 1: SELF-ADHERING, HIGH-TEMPERATURE ELECTRICAL INSULATION TAPE INSTALLATION
AND WIRE SUPPORT - INSPECTION/CHANGE
(SHEET 2 OF 2)
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### Page 35 (OCR)

BOEING SERVICE BULLETIN MD11-28A124
ALERT  ALERT
This Figure applies only to: Group 2, Configuration 2.
D 00000
B-B
AJS9014
AJS9013
AJS9014
AJS9014
FWD  2000398
FIGURE 2: WIRE SUPPORT - CHANGE
(SHEET 1 OF 2)
Original Issue: June 17, 2009
Revision 1 August 24, 2010  Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  MD11-28A124  35 of 36

### Page 36

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
--NutRemove/Keep1
--Washer
--Screw
1-ClampRemove
1S7934111-4SAClampInstall (New)2
--ScrewInstall (Kept)
--Washer
--Nut
--ScrewRemove/Keep3
--Washer
1-ClampRemove
1S7934111-4SAClampInstall (New)4
--WasherInstall (Kept)
--Screw
Barrel facing aft.1S7934111-4SAClampChange5
23D0005-4-6ScrewRemove6
2NAS1252-416HWasherRemove/Keep
2NAS1252-416HWasherInstall/Kept7
2NAS1801-4-11ScrewInstall (New)
(a) Adjust tape installation as necessary to achieve noted dimensions.
FIGURE 2: WIRE SUPPORT - CHANGE
(SHEET 2 OF 2)
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ALERTALERT

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