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.

ECCN: 9E991

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Unpublished Work - All Rights Reserved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

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2.0
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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 18

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 21

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 26

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

FIGURE 1: SELF-ADHERING, HIGH-TEMPERATURE ELECTRICAL INSULATION TAPE INSTALLATION

AND WIRE SUPPORT - INSPECTION/CHANGE [Group 1, Configuration 2] . . . . . . . . 33

FIGURE 2: WIRE SUPPORT - CHANGE [Group 2, Configuration 2] . . . . . . . . . . . . . . . . . . . 35

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT

BLANK PAGE
Commercial 

Airplanes MD11

Service Bulletin

ALERT

Revision Transmittal Sheet 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 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

Original Issue: June 17, 2009

Revision 1: August 24, 2010

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Commercial 

Airplanes MD11

Service Bulletin

ALERT

Summary 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.

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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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT

BLANK PAGE
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.

GROUP CONFIGURATION DESCRIPTION

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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GROUP CONFIGURATION DESCRIPTION

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

Fuselage Num- Group

ber

447 - 449 2

451 - 460 2

461 - 464 1

466 - 489 1

491 - 517 1

519 - 552 1

554 - 646 1

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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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
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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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
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

Model Zone

MD-11, MD-11F 311

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
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:

Number of Task Hours Elapsed Hours

Persons

Task

Condition 1 Condition 2 Condition 1 Condition 2

Open Access 2 1.0 1.0 0.5 0.5

Removal 1 2.0 2.0 2.0 2.0

Inspection 1 0.5 0.5 0.5 0.5

Repair 1 6.0 6.0

Change 2 16.0 16.0 8.0 8.0

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Group 1, Configuration 1:

Number of Task Hours Elapsed Hours

Persons

Task

Condition 1 Condition 2 Condition 1 Condition 2

Close Access 2 1.0 1.0 0.5 0.5

TOTAL FOR EACH AIRPLANE 20.5 28.0 11.5 17.5

NOTE:

Group 1, Configuration 2:

Elapsed

Hours

Number of Task Hours

Persons

Task

Open Access 2 1.0 0.5

Inspect 1 0.3 0.3

Figure 1 1 1.0 1.0

Close Access 2 1.0 0.5

TOTAL FOR EACH AIRPLANE 3.3 2.3

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:

Number of Task Hours Elapsed Hours

Persons

Task

Condition 1 Condition 2 Condition 1 Condition 2

Open Access 2 1.0 1.0 0.5 0.5

Removal 1 2.0 2.0 2.0 2.0

Inspection 1 0.5 0.5 0.5 0.5

Repair 1 6.0 6.0

Change 2 10.0 16.0 5.0 8.0

Close Access 2 1.0 1.0 0.5 0.5

TOTAL FOR EACH AIRPLANE 14.5 22.0 8.5 16.0

Group 2, Configuration 2:

Elapsed

Hours

Number of Task Hours

Persons

Task

Open Access 2 1.0 0.5

Figure 2 1 1.0 1.0

Close Access 2 1.0 0.5

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Group 2, Configuration 2:

Elapsed

Hours

Number of Task Hours

Persons

Task

TOTAL FOR EACH AIRPLANE 3.0 2.0

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

Condition 1 2147.6 +9.0 +19,328.4

Condition 2 2154.0 +13.8 +29,725.2

Group 2:

Moment Change

(MEW) IN.-LBS

Mfr's Empty

Weight (MEW)

LBS Increase

Approximate Station (Inches)Airplane

MD-11 and MD-11F

Condition 1 2147.1 +8.5 +18,250.4

Condition 2 2154.0 +13.2 +28,432.8

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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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
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:

Drawing No Title Sheet DCN/REV ADCN

SR11280052 Alert - Tail Fuel Tank Wire Installation DWG H -

3. Installation Drawings Used in the Preparation of this Service Bulletin:

None.

K. Publications Affected

1. Publications:

Publication Chapter-Section

Illustrated Parts Catalog 55-11

Special Compliance Item Report MDC-02K1003 (ALI 20-2)

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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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
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 Service Bulletin (US

Dollars)

ROLT as of the

Revision 01 date

of this Service

Bulletin (Calendar

Days)

Kit Number Name

SA11280124-7 Service Kit 90 $11,829.00

SA11280124-9 Supplemental Kit 30 9.00

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

Existing Part Notes

Number

New Part Number QTY Name

-7

3D0005-3-12 1 SCREW (a)

3D0005-3-22 1 SCREW (a)

3D0005-3-30 1 SCREW (a)

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Group 1-2, Configuration 1:

Kit SA11280124

Existing Part Notes

Number

New Part Number QTY Name

-7

3D0005-3-8 9 SCREW (a)

3D0039-14 9 NUT-CLIP (a)

3D0039-16 3 NUT-CLIP (a)

9D0230-3L080824 6 BRACKET

9D0230-3L080832 3 BRACKET

9D0254-1-1-9 21 STRAP (a)

AAP8000-539 1 BRACKET

AAP8004-1103 1 BRACKET ALN8600-551 (b)

HL326-5-4 2 PIN

MS21042L08 2 NUT

MS21042L3 3 NUT

MS21919WDG10 1 CLAMP

NAS1096-3-12 1 SCREW

NAS1096-3-10 6 SCREW

NAS1096-3-8 1 SCREW

NAS1252-10L 27 WASHER

NAS1252-416H 2 WASHER

NAS1252-8L 2 WASHER

NAS1801-4-11 2 SCREW

NAS43DD3-16FC 1 SPACER (a)

NAS43DD3-48FC 1 SPACER (a)

NAS43DD3-72FC 1 SPACER (a)

S7934111-10SA 6 CLAMP (a)

S7934111-14SA 5 CLAMP (a)

S7934111-24SA 1 CLAMP (a)

S7934111-4SA 3 CLAMP (a)

S7934111-6SA 7 CLAMP (a)

S7934111-7SA 1 CLAMP (a)

SR11280052-13 1 BRACKET

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Group 1-2, Configuration 1:

Kit SA11280124

Existing Part Notes

Number

New Part Number QTY Name

-7

EXTRUDED

CHANNEL

SR11280052-17 8

SR11280052-29 1 BRACKET

SR11280052-31 1 BRACKET

SR11280052-33 1 BRACKET

(a) Or approved Equivalent. Refer to AEPL, Drawing 7595071.

(b) Discard the existing part.

Group 1-2, Configuration 2:

Supplemental Kit SA11280124

Existing Part Notes

Number

New Part Number QTY Name

-9

S7934111-4SA 2 CLAMP (a)

NAS1801-4-11 2 SCREW

(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

Part Number / Specifi- QTY Name Notes

cation

80 FT x 1.0 TAPE (ELASTOMER) (a) (e)

Inch Width

SR11280052-11

(DMS 2186 Type 2)

or

T2/600T Series

Alodine 1500 As Required COATING CHEMICAL FILM, LIQUID (b) (e)

(DPM 5089-1)

515X347 Base with 4 Oz. PRIMER, FR (c)

910X527 Catalyst

(DMS 1786)

or

Equivalent

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Group 1, Configuration 1:

Condition 1: No Wire Damage Found

Part Number / Specifi- QTY Name Notes

cation

ENAMEL, HIGH SOLIDS EPOXY TOP- (d)

COAT, GLOSS WHITE

446-21-7507 Base 1 Oz.

DN7507 White with X530 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, California 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

Part Number / Specifi- QTY Name Notes

cation

80 FT x 1.0 Inch TAPE (ELASTOMER) (a) (i)

Width

SR11280052-11

(DMS 2186 Type 2)

or

T2/600T Series

SLEEVE (BRAIDED, EXPANDABLE (b)

ARAMID FIBER/PPS, MONOFILAMENT, PREFORMED WRAPAROUND)

SR11280052-21 10 FT x 1.187 I.D.

(DMS 2379 Type 5,

Class 4)

or

5678103007S

36 YARDS x 1.0 TAPE (ELASTOMER) (a) (i)

Inch Width

SR11280052-23

(DMS 2186 Type 1)

or

T3/SA Series

TAPE (POLYURETHANE NUMBER (c)

8672, TRANSPARENT)

36 YARDS x 1.0

Inch Width

SR11280052-25

(DPM 5777-6)

Alodine 1500 As Required COATING CHEMICAL FILM, LIQUID (d) (i)

(DPM 5089-1)

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Group 1, Configuration 1:

Condition 2: Wire Damage Found

Part Number / Specifi- QTY Name Notes

cation

515X347 Base with 4 Oz. PRIMER, FR (g)

910X527 Catalyst

(DMS 1786)

or

Equivalent

ENAMEL, HIGH SOLIDS EPOXY TOP- (h)

COAT, GLOSS WHITE

446-21-7507 Base 1 Oz.

DN7507 White with X530 Activator

(DMS 2433-2C)

or

Equivalent

M85049/93-10 5 SPLIT FERRULE (e)

9D0180-1 10 CLAMP, LOOP (f)

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, 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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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Group 2, Configuration 1:

Condition 1: No Wire Damage Found

Part Number / Specifi- QTY Name Notes

cation

Alodine 1500 As Required COATING CHEMICAL FILM, LIQUID (a) (d)

(DPM 5089-1)

515X347 Base with 4 Oz. PRIMER, FR (b)

910X527 Catalyst

(DMS 1786)

or

Equivalent

ENAMEL, HIGH SOLIDS EPOXY TOP- (c)

COAT, GLOSS WHITE

446-21-7507 Base 1 Oz.

DN7507 White with X530 Activator

(DMS 2433-2C)

or

Equivalent

(a) Can be purchased from: Zip-Chem Products, 400 Jarvis Drive, Suite A, Morgan Hill, California 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

Part Number / Specifi- QTY Name Notes

cation

SLEEVE (BRAIDED, EXPANDABLE (a)

ARAMID FIBER/PPS, MONOFILAMENT, PREFORMED WRAPAROUND)

10 FT x 1.187

I.D.

SR11280052-21

(DMS 2379 Type 5,

Class 4)

or

5678103007S

36 YARDS x TAPE (ELASTOMER) (b) (i)

1.0 Inch Width

SR11280052-23

(DMS 2186 Type 1)

or

T3/SA Series

TAPE (POLYURETHANE NUMBER (c)

8672, TRANSPARENT)

36 YARDS x

1.0 Inch Width

SR11280052-25

(DPM 5777-6)

Alodine 1500 As Required COATING CHEMICAL FILM, LIQUID (d) (i)

(DPM 5089-1)

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Group 2, Configuration 1:

Condition 2: Wire Damage Found

Part Number / Specifi- QTY Name Notes

cation

515X347 Base with 4 Oz. PRIMER, FR (g)

910X527 Catalyst

(DMS 1786)

or

Equivalent

ENAMEL, HIGH SOLIDS EPOXY TOP- (h)

COAT, GLOSS WHITE

446-21-7507 Base 1 Oz.

DN7507 White with X530 Activator

(DMS 2433-2C)

or

Equivalent

M85049/93-10 5 SPLIT FERRULE (e)

9D0180-1 10 CLAMP, LOOP (f)

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, 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,

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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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Group 1, Configuration 2:

Part Number / Specifi- QTY Name Notes

cation

5 FT x 1.0 Inch TAPE (ELASTOMER) (a) (b) (c)

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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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
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:

SWPM 20-00-03 Identification of Electrical Wire - Commercial

SWPM 20-00-09 General Maintenance Practices - Electrical

SWPM 20-00-13 Electrical Wire Codes

SWPM 20-10-01 Wiring Installation - Maintenance Practices

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
SWPM 20-10-10 Wire Harness and Component Cleaning

SWPM 20-10-17 Braided Electrical Wire Bundles

SWPM 20-50-01 Electrical Bonding - Maintenance Practices

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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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Access Door Location Refer to:

311AB Lower Aft Fuselage MD-11 AMM 06-33-00.

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:

Access Door Location Refer to:

311AB Lower Aft Fuselage MD-11 AMM 06-33-00.

316AB

14. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
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:

Access Door Location Refer to:

311AB Lower Aft Fuselage MD-11 AMM 06-33-00.

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:

Access Door Location Refer to:

311AB Lower Aft Fuselage MD-11 AMM 06-33-00.

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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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
Access Door Location Refer to:

311AB Lower Aft Fuselage MD-11 AMM 06-33-00.

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:

Access Door Location Refer to:

311AB Lower Aft Fuselage MD-11 AMM 06-33-00.

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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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
5. Gain access to the tail tank fuel system wire assembly installation by opening access doors that

follow:

Access Door Location Refer to:

311AB Lower Aft Fuselage MD-11 AMM 06-33-00.

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:

Access Door Location Refer to:

311AB Lower Aft Fuselage MD-11 AMM 06-33-00.

316AB

8. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
This Figure applies only to: Group 1, Configuration 2.

FIGURE 1: SELF-ADHERING, HIGH-TEMPERATURE ELECTRICAL INSULATION TAPE INSTALLATION

AND WIRE SUPPORT - INSPECTION/CHANGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN MD11-28A124

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Inspect Tape SR11280052-11 - (a)

2 Remove/Keep Nut - -

Washer - -

Screw - -

Remove Clamp - 1

3 Install (New) Clamp S7934111-4SA 1

Install (Kept) Washer - -

Screw - -

Nut - -

4 Remove/Keep Screw - -

Washer - -

Remove Clamp - 1

5 Install (New) Clamp S7934111-4SA 1

Install (Kept) Washer - -

Screw - -

6 Change Clamp S7934111-4SA 1 Barrel facing aft.

7 Remove Screw 3D0005-4-6 2

Remove/Keep Washer NAS1252-416H 2

8 Install/Kept Washer NAS1252-416H 2

Install (New) Screw NAS1801-4-11 2

(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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Original Issue: June 17, 2009

Revision 1 August 24, 2010 MD11-28A124

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BOEING SERVICE BULLETIN MD11-28A124

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This Figure applies only to: Group 2, Configuration 2.

FIGURE 2: WIRE SUPPORT - CHANGE

(SHEET 1 OF 2)

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Original Issue: June 17, 2009

Revision 1 August 24, 2010 MD11-28A124

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BOEING SERVICE BULLETIN MD11-28A124

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep Nut - -

Washer - -

Screw - -

Remove Clamp - 1

2 Install (New) Clamp S7934111-4SA 1

Install (Kept) Screw - -

Washer - -

Nut - -

3 Remove/Keep Screw - -

Washer - -

Remove Clamp - 1

4 Install (New) Clamp S7934111-4SA 1

Install (Kept) Washer - -

Screw - -

5 Change Clamp S7934111-4SA 1 Barrel facing aft.

6 Remove Screw 3D0005-4-6 2

Remove/Keep Washer NAS1252-416H 2

7 Install/Kept Washer NAS1252-416H 2

Install (New) Screw NAS1801-4-11 2

(a) Adjust tape installation as necessary to achieve noted dimensions.

FIGURE 2: WIRE SUPPORT - CHANGE

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: June 17, 2009

Revision 1 August 24, 2010 MD11-28A124

36 of 36

BOEING SERVICE BULLETIN MD11-28A124

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