August 08, 2007

Revision 1: November 06, 2008 MD11-28-135

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 58

Commercial McDonnell Douglas

Airplane

Group MD-11

Service Bulletin

Number: MD11-28-135

Date: August 08, 2007

Revision 1: November 06, 2008

ATA System: 2821

SUBJECT: FUEL - Controller, Fill Shutoff, All Tanks - Install Electrical Bonding Jumper

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2007 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Unpublished Work - All Rights Reserved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, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, 

MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or 

its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document 

or otherwise.
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 Table of Contents

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BOEING SERVICE BULLETIN MD11-28-135

Table of Contents

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

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

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 13

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 13

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 14

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

1. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 16

2. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

3. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 17

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

FIGURE 1: INSTALL ELECTRICAL BONDING JUMPER, TANK 1 . . . . . . . . . . . . . . . . . . . 22

FIGURE 2: INSTALL ELECTRICAL BONDING JUMPER TANK 2 . . . . . . . . . . . . . . . . . . . 27

FIGURE 3: INSTALL ELECTRICAL BONDING JUMPER TANK 3 . . . . . . . . . . . . . . . . . . . 30

FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK . . . . . . . . . 35

FIGURE 5: INSTALL ELECTRICAL BONDING JUMPER UPPER AUXILIARY TANK . . . . . . . . . 43

FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK . . . . . . . . . . . . . . . . . 51
 Table of Contents

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Revision 1: November 06, 2008 MD11-28-135

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Commercial McDonnell Douglas

Airplane

Group MD-11

Service Bulletin

Number: MD11-28-135 Revision Transmittal Sheet

Date: August 08, 2007

Revision 1: November 06, 2008

ATA System: 2821

SUBJECT: FUEL - Controller, Fill Shutoff, All Tanks - Install Electrical Bonding Jumper

This Revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on airplanes changed as shown in the original issue of this service bulletin.

REASON FOR REVISION

This revision is sent to incorporate engineering released subsequent to the original issue of this service bulletin, 

which relocates ground brackets and jumpers due to interference with airplane components/structure. Noted 

changes are based on findings discovered as a result of service bulletin installation verification done at an airline 

facility. 

This revision removes the “No Work” condition given in Information Notice MD11-28-135 IN 01.

These sections were changed:

1. In Paragraph 1.A.1., Effectivity, added airplane validation statement.

2. In Paragraph 1.C., Reason, added airplane validation statements.

3. In Paragraph 1.J.3., References, changed Drawing revision level. 

4. In Paragraph 2.A., Material - Price and Availability, changed kit price. 

5. In Paragraph 2.C.1., Kits/Parts, changed kit. 

6. In Paragraph 3.A., General Information, added notes 9, 10, and 11. 

7. In Paragraph 3.B., Work Instructions, removed function test work instruction.

8. Figures 1 through 6 changed to reflect accessibility issues found as a result of service bulletin validation.
 

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Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity 

paragraph for changes.

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: August 8, 2007

Revision 1: November 06, 2008
August 08, 2007

Revision 1: November 06, 2008 MD11-28-135

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 58

Commercial McDonnell Douglas

Airplane

Group MD-11

Service Bulletin

Number: MD11-28-135 Summary

Date: August 08, 2007

Revision 1: November 06, 2008

ATA System: 2821

SUBJECT: FUEL - Controller, Fill Shutoff, All Tanks - Install Electrical Bonding Jumper

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Boeing investigation and analysis revealed that fill valve controller installations had inadequate electrical 

bonding. This could allow point-of-contact arcing or filament heating damage in the fuel tanks. Installing 

electrical bonding jumpers from the fill valve controllers to airplane structure will provide a grounding path in the 

event of a fault current occurrence in the fill valve controller. If not corrected, a high current occurrence can result 

in a potential ignition source.

Airplane manufacturer’s fuselage number 625 had this modification incorporated at the operators facility as an 

installation verification in accordance with Drawing SR11280059-7001.

This service bulletin is the result of the safety assessments conducted by Boeing under Special Federal Aviation 

Regulation (SFAR) 88, “Fuel Tank System Fault Tolerance Evaluation Requirements”.

ACTION

This service bulletin provides instructions to install electrical bonding jumpers from right/left/center wing tanks, 

upper and lower auxiliary tanks and tail tank fill valve controllers to the airplane structure.

EFFECTIVITY

MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. 

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service 

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin 

mandatory.

Boeing recommends operators do this service bulletin within 5 years after the date on this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
 

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MANPOWER

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

Airplanes Total Task Hours Elapsed Hours

MD-11 and MD-11F 27.5 27.5

INSTALL ELECTRICAL 

BONDING JUMPER

1361439
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Commercial McDonnell Douglas

Airplane

Group MD-11

Service Bulletin

Number: MD11-28-135

Date: August 08, 2007

Revision 1: November 06, 2008

ATA System: 2821

SUBJECT: FUEL - Controller, Fill Shutoff, All Tanks - Install Electrical Bonding Jumper

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below. 

Airplane manufacturer’s fuselage number 625 had this modification incorporated at the operators 

facility as an installation verification in accordance with Drawing SR11280059-7001.

Airplane models:

MD-11 MD-11F

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND FUSELAGE NUMBER

AEROFLOT (ARO)

1 520 528 548

ALITALIA (ALI)

1 468 471 474 500

508

CENTURION AIR CARGO (CHA)

1 476

CHINA CARGO (CIQ)

1 461 475 496 512

522 541

EVA AIR (EVA)

1 570 587 589 619–620

630–631 633–634

GROUP CONFIGURATION DESCRIPTION

1 - Applicable to MD-11 and MD-11F Airplanes.
 

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FEDEX (FED)

1 447–449 451–452 458 462

464 469–470 477 482–483

486 492–493 497 499

503–504 507 510 513–515

517 519 521 526–527

530–531 535–538 540 542

545–546 549–551 555 558

560 562 594–595 598

602 604–605 607 622

635–636 638

FINNAIR (FIN)

1 455 479 529 564

600 608 624

GEMINI AIR CARGO (GMN)

1 454

KLM - ROYAL DUTCH AIRLINES (KLM)

1 557 561 569 573

575 578 585 591

593 612

LUFTHANSA CARGO (LUB)

1 488 491 534 565

567 625–629 637 639–646

MARTINAIR HOLLAND (MTH)

1 460 577 581 584

586 606 632

SAUDI ARABIAN AIRLINES (SVA)

1 609 616–618

SAUDI ROYAL FLIGHT (SRF)

1 532 544

SHANGHAI AIRLINES CARGO (CIX)

1 572 576 580

TAM (TPR)

1 603 613 615

TRANSMILE AIR SERVICES (TML)

1 459 463 502 509
 

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UPS (UPS)

1 466–467 472–473 480–481 484–485

487 489 494 498

501 505 511 523–524

533 543 547 552

554 556 559 566

568 571 574 583

588 592 596 599

601 610–611 614 621

VARIG LOGISTICA S.A. (VRG)

1 457 495

WORLD AIRWAYS, INC. (WLD)

1 453 456 478 506

516 525 539 563

579 582 590 597

623

IDENTIFICATION BY FUSELAGE NUMBER

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

Boeing investigation and analysis revealed that fill valve controller installations had inadequate 

electrical bonding. This could allow point-of-contact arcing or filament heating damage in the fuel 

tanks. Installing electrical bonding jumpers from the fill valve controllers to airplane structure will 

provide a grounding path in the event of a fault current occurrence in the fill valve controller. If not 

corrected, a high current occurrence can result in a potential ignition source.

Airplane manufacturer’s fuselage number 625 had this modification incorporated at the operators 

facility as an installation verification in accordance with Drawing SR11280059-7001.

Fuselage Group

447–449 1

451–464 1

466–489 1

491–517 1

519–552 1

554–646 1
 

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BOEING SERVICE BULLETIN MD11-28-135

This service bulletin is the result of the safety assessments conducted by Boeing under Special 

Federal Aviation Regulation (SFAR) 88, “Fuel Tank System Fault Tolerance Evaluation 

Requirements”.

This revision is sent to incorporate engineering released subsequent to the original issue of this 

service bulletin, which relocates ground brackets and jumpers due to interference with airplane 

components/structure. Noted changes are based on findings discovered as a result of service bulletin 

installation verification done at an airline facility. 

D. Description

This service bulletin provides instructions to install electrical bonding jumpers from left/right/center 

wing tanks, upper and lower auxiliary tanks and tail tank fill valve controllers to the airplane structure.

Revision - 1 No more work is necessary on airplanes changed as shown in the original issue of this 

service bulletin.

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to 

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in 

this service bulletin mandatory.

Boeing recommends operators do this service bulletin within 5 years after the date on this service 

bulletin.

F. Approval

The resultant modification described in Paragraph 1.D has been shown to comply with the applicable 

Federal Aviation Regulations and Revision 1 is approved by the Manager, Los Angeles Aircraft 

Certification Office, FAA Northwest Mountain Region, on _________2008.

G. Manpower

The table below shows an estimate of the task hours necessary to do this for each airplane. This 

estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task 

hour data if necessary. The estimate does not include lost time. These are some examples of lost time:

— Time to adjust to the workplace

— Time to schedule the work

— Time to inspect the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.
 

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H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. MD-11-1F Structural Repair Manual (SRM) 51-00-01, 51-31-01, 51-33-01, 51-41-01

b. MD-11-1P Structural Repair Manual (SRM) 51-00-01, 51-31-01, 51-33-01, 51-41-01

c. MD-11 Aircraft Maintenance Manual (AMM) 06-33-00, 06-35-00, 06-36-00, 06-37-00, 

28-21-02

d. Standard Wiring Practices Manual (SWPM) 20-20-01, 20-50-01

2. Data supplied with this Service Bulletin:

None.

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

This drawing was used to prepare this service bulletin. This drawing is not necessary to make the 

specified changes, and is not supplied with this service bulletin. This drawing may not be 

applicable to all airplane configurations or operators.

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 3.0 3.0

Figure 1 1 3.0 3.0

Figure 2 1 2.0 2.0

Figure 3 1 3.0 3.0

Figure 4 1 4.0 4.0

Figure 5 1 4.0 4.0

Figure 6 1 4.0 4.0

Test 1 1.5 1.5

Close Access 1 3.0 3.0

TOTAL FOR EACH AIRPLANE 27.5 27.5

Document Number Title Change

SR11280059 Bonding Improvement - Fill Valve 

Controller, Fuel System, MD-11

E
 

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K. Publications Affected

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

Publication Chapter-Section

Illustrated Parts Catalog 28-21
 

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2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown 

below. If there is a limit to the quantity (QTY) of available parts, a supply sequence is given by Spares. 

More parts become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from 

the date Boeing gets the purchase order.

The kits are subject to the terms and conditions of the Boeing standard purchase order 

acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in 

United States dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of the methods that follow: 

1. Order on-line via ATA Spec 2000 or Boeing Part Page.

2. Fax to (206) 662-7145.

3. Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

Kit Number Name QTY

ROLT 

(Weeks)

Unit Price thru 

December 31, 2008

SB11280135-3 Service Kit 1 17 $2,698.00
 

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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.

Parts and Materials Supplied by the Operator:

Figure Kit

Top Kit 1 2 3 4 5 6

SB11280135-3 1 1 1 1 1 1

Kit SB11280135-3 - Group 1: 

New Part 

Number

Figure

Name

123456

QTY

ABN7210-539 1 - 1 - - 1 BRACKET ASSY

ABN7294-793 - - - - 1 - BRACKET

HL326-6-2 2 1 2 2 2 2 PIN

MS21042L3 2 1 2 4 3 3 NUT

MS35338-43 1 - 1 - 1 1 LOCKWASHER

NAS1149F0332P 3 2 3 6 5 5 WASHER

NAS1801-08-10 - - - - 1 - SCREW

NAS1801-3-9 1 - 1 2 1 2 SCREW

RC11307-10SS4 - 1 - 1 1 1 CABLE, JUMPER

RC11307-10SS6 1 - 1 - - - CABLE, JUMPER

RC11309-10SS4 - - - - 1 - CABLE, JUMPER

S2891103-10SS4 - - - - - 1 JUMPER (a)

S2891103-10SS6 - - - 1 - - JUMPER (a)

(a) May be purchased 

from:

Frameatome Connectors USA, Incorporated 

55 Walls Drive Suite 304 

Farfield, Connecticut, 06824-5163

CAGE 

3BZ92

or

Sourian USA, Incorporated 

25 Grumbacher 

Road York, Pennsylvania 17406-8417

CAGE 

09922

Part Number / 

Specification QTY Name Notes

PR-1776 B-2 

(DMS 2427 B-2) 

OR EQUIVALENT 

1 Tube 

6.12 Oz.

Fillet Sealing Compound, 

Lower Specific Gravity

(a)
 

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2. Parts Modified and Reidentified:

None.

3. 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.

(a) May be purchased from: PRC-DeSoto International, Incorporated 

5430 San Fernando Road 

Glendale, California 91203-1521

CAGE 

83574
 

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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. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for 

definition of the acronyms.

2. Refer to the following Standard Wiring Practices Manual (SWPM) chapters for 

applicable operations, as accepted procedures:

3. Use the approved fastener and process material substitutions, refer to Structural Repair 

Manual MD-11-1F SRM 51-00-01, and MD-11-1P SRM 51-00-01.

4. If the length of any fastener specified in this service bulletin does not meet the 

installation standards in SRM Chapter 51, then a fastener of the same specification, or 

an approved substitute, with a length which meets the installation standards in SRM 

Chapter 51 may be used.

5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is the 

maximum thickness which may be used under fastener head or nut to counteract 

accumulation of tolerances.

EXCEPTION: When the available fastener length increments are greater than 1/16-inch, 

a 3/16-inch thick stack of the same type washers may be used. 

6. Obey all of the warnings and cautions given in the specified manual sections.

Chapter Title

SWPM 20-20-01 Terminals - Maintenance Practices

SWPM 20-50-01 Electrical Bonding Connections
 

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7. These work instructions refer to procedures included on other Being documents. When 

the words “refer to” are used and the operator has an accepted alternative procedure, 

the accepted alternative can be used. When the words “In accordance with” are included 

in the instructions, the procedure in the Boeing document must be used.

8. Equivalent parts are listed in the AEPL, Drawing 7595071.

9. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s) give 

the recommended sequence of steps. The sequence of steps to do this service bulletin 

can be changed. 

10. Unless shown differently, these dimensions and tolerances are used:

— Linear dimensions are in inches 

— Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or 

minus 0.03 inch.

— Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

— Hole dimensions for standard solid rivets refer to SRM, Chapter 51 as an accepted 

procedure.

— Torque limits to tighten nuts and bolts refer to SRM, Chapter 51 as an accepted 

procedure.

11. Cover Fill Valve Controller to protect it from any debris during shroud assembly rework. 

Fill Valve Controller may be removed and reinstalled for ease of rework at operator's 

option.

B. WORK INSTRUCTIONS

1. Gain access to area of change by opening and keeping the following panels and associated 

hardware:

2. Install electrical bonding jumper as follows:

Panel Number Name/Location Refer to

526FB Left Wing Outboard Leading 

Edge and Slats, Bottom 

MD-11 AMM 06-35-00

615DB Right Wing Inboard Leading 

Edge and Slats, Bottom 

MD-11 AMM 06-36-00

626FB Right Wing Outboard Leading 

Edge and Slats, Bottom 

MD-11 AMM 06-36-00

721AL Center Landing Gear Door Left MD-11 AMM 06-37-00

722AR Center Landing Gear Door 

Right 

311AB Horizontal Stabilizer/Fuel 

Tank, Jack Screw, and Motors 

MD-11 AMM 06-33-00

Location In Accordance with Figure 

Left Wing Outboard Leading Edge 1

Right Wing Inboard Leading Edge 2

Right Wing Outboard Leading Edge 3
 

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3. If the fill shutoff valve controller was removed, do a function test of upper, lower auxiliary tanks, 

and tail tank fill shutoff valve controllers in accordance with MD-11 AMM 28-21-02. 

4. Close access.

5. Put the airplane back to a serviceable condition.

Center Wing Lower Auxiliary Fuel Tank 4

Center Wing Upper Auxiliary Fuel Tank 5

Tail Tank Horizontal Stabilizer Front Spar 6

Location In Accordance with Figure 
 FIGURE 1: INSTALL ELECTRICAL BONDING JUMPER, TANK 1

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

FIGURE 1: INSTALL ELECTRICAL BONDING JUMPER, TANK 1 

OUTBD

UP

B B

4.50

1.50

Xfs=918.000

LEFT SIDE

LOOKING AFT AT FRONT SPAR

BEFORE

2

A 1

SEE A

1361440

(SHEET 1 OF 5)
 FIGURE 1: INSTALL ELECTRICAL BONDING JUMPER, TANK 1

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

OUTBD

UP

OUTBD

FWD

B-B

0.44

2

D D

Xfs=918.000

C C

LEFT SIDE

LOOKING AFT AT FRONT SPAR

AFTER

A

4

0.50

(2 LOCATIONS)

3

LOOKING UP

1361441

(SHEET 2 OF 5)
 FIGURE 1: INSTALL ELECTRICAL BONDING JUMPER, TANK 1

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

C-C

5

6

D-D

7

5

1361442

(SHEET 3 OF 5)
 FIGURE 1: INSTALL ELECTRICAL BONDING JUMPER, TANK 1

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep Bolt - -

Remove/Keep Washer - -

2 Drill BRACKET ASSY ABN7210-539 - Locate, drill and process for 

HL326-6 Pin (2 places). Refer 

to MD-11-1P SRM 51-31-01, 

MD-11-1F SRM 51-31-01, 

MD-11-1F SRM 51-33-01 and 

MD-11-1P SRM 51-33-01 as 

accepted procedures.

3 Apply - BOND - Faying surfaces common to 

bracket and structure for fault 

current path return protection. 

Refer to SWPM 20-50-01 as 

an accepted procedure.

4 Install (New) BRACKET ASSY ABN7210-539 1

Install (New) PIN HL326-6-2 2 Refer to MD-11-1P SRM 

51-33-01 and MD-11-1F SRM 

51-33-01 as accepted 

procedures.

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

5 Apply - BOND - Faying surfaces common to 

jumper terminals, bracket, and 

valve housing for fault current 

path return protection. Refer to 

SWPM 20-50-01 as an 

accepted procedure.

6 Install (New) CABLE, JUMPER RC11307-10SS6 1 Terminal of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

Install (New) SCREW NAS1801-3-9 1

Install (New) LOCKWASHER MS35338-43 1

Install (New) WASHER NAS1149F0332P 1

(SHEET 4 OF 5)
 FIGURE 1: INSTALL ELECTRICAL BONDING JUMPER, TANK 1

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7 Install (Kept) Bolt - -

Install (Kept) Washer - -

Install (New) CABLE, JUMPER RC11307-10SS6 - Terminal of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 5 OF 5)
 FIGURE 2: INSTALL ELECTRICAL BONDING JUMPER TANK 2

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BOEING SERVICE BULLETIN MD11-28-135

FIGURE 2: INSTALL ELECTRICAL BONDING JUMPER TANK 2

INBD

UP

Xfs=-227.00

RIGHT SIDE

LOOKING AFT AT FRONT SPAR

B B

1

SEE A

1361443

(SHEET 1 OF 3)
 FIGURE 2: INSTALL ELECTRICAL BONDING JUMPER TANK 2

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

FWD

UP

FWD

C

C

B-B

5

3

4

3

2

0.60

4

EXISTING

BRACKET

EXISTING

BRACKET

C-C

A

Xfs=-227.000

0.70

1361444

(SHEET 2 OF 3)
 FIGURE 2: INSTALL ELECTRICAL BONDING JUMPER TANK 2

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep Bolt - -

Remove/Keep Washer - -

2 Drill Structure - - Locate, drill and process for 

HL326-6 Pin. Refer to 

MD-11-1F SRM 51-33-01 and 

MD-11-1P SRM 51-33-01 as 

accepted procedures.

3 Apply - BOND - Faying surfaces common to 

jumper terminals, structure and 

valve housing for current path 

return protection. Refer to 

SWPM 20-50-01 as an 

accepted procedure.

4 Install (New) PIN HL326-6-2 1 Refer to MD-11-1F SRM 

51-33-01 and MD-11-1P SRM 

51-33-01 as accepted 

procedures.

Install (New) WASHER NAS1149F0332P 2

Install (New) CABLE, JUMPER RC11307-10SS4 1 Terminal lug of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

Install (New) NUT MS21042L3 1

5 Install (Kept) Bolt - -

Install (Kept) Washer - -

Install (New) CABLE, JUMPER RC11307-10SS4 - Terminal lug of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

(SHEET 3 OF 3)
 FIGURE 3: INSTALL ELECTRICAL BONDING JUMPER TANK 3

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BOEING SERVICE BULLETIN MD11-28-135

FIGURE 3: INSTALL ELECTRICAL BONDING JUMPER TANK 3 

INBD

UP

B B

Xfs=-918.000

2

RIGHT SIDE

LOOKING AFT AT FRONT SPAR

BEFORE

A 1

SEE A

4.50

1.50

1361445

(SHEET 1 OF 5)
 FIGURE 3: INSTALL ELECTRICAL BONDING JUMPER TANK 3

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

INBD

UP

INBD

FWD B-B

0.44

4

RIGHT SIDE

LOOKING AFT AT FRONT SPAR

AFTER

A

Xfs=-918.00

C C

D D

LOOKING UP

0.50 

(2 LOCATIONS)

3 2

1361446

(SHEET 2 OF 5)
 FIGURE 3: INSTALL ELECTRICAL BONDING JUMPER TANK 3

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

C-C D-D

6

5

5

7

1361447

(SHEET 3 OF 5)
 FIGURE 3: INSTALL ELECTRICAL BONDING JUMPER TANK 3

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep Bolt - -

Remove/Keep Washer - -

2 Drill BRACKET ASSY ABN7210-539 - Locate, drill and process for 

HL326-6 Pin (2 places). Refer 

to MD-11-1P SRM 51-31-01, 

MD-11-1F SRM 51-31-01, 

MD-11-1F SRM 51-33-01 and 

MD-11-1P SRM 51-33-01 as 

accepted procedures.

3 Apply - BOND - Faying surfaces common to 

bracket and structure for fault 

current path return protection. 

Refer to SWPM 20-50-01 as 

an accepted procedure.

4 Install (New) BRACKET ASSY ABN7210-539 1

Install (New) PIN HL326-6-2 2 Refer to MD-11-1F SRM 

51-33-01 and MD-11-1P SRM 

51-33-01 as accepted 

procedures.

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

5 Apply - BOND - Faying surfaces common to 

jumper terminals, and valve 

housing for fault current path 

return protection. Refer to 

SWPM 20-50-01 as an 

accepted procedure.

6 Install (New) CABLE, JUMPER RC11307-10SS6 1 Terminal of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

Install (New) SCREW NAS1801-3-9 1

Install (New) LOCKWASHER MS35338-43 1

Install (New) WASHER NAS1149F0332P 1

(SHEET 4 OF 5)
 FIGURE 3: INSTALL ELECTRICAL BONDING JUMPER TANK 3

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

7 Install (Kept) Bolt - -

Install (Kept) Washer - -

Install (New) CABLE, JUMPER RC11307-10SS6 - Terminal of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 5 OF 5)
 FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK

UP

OUTBD

SEE A

LOOKING FORWARD AT REAR SPAR

STATION Y=1370.000

LOWER AUXILIARY FUEL TANK

A

BEFORE

X=0.000

AIRPLANE CENTERLINE

SEE D

B

B

Zcw=0.000

1

1361448

(SHEET 1 OF 8)
 FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

FWD

UP

FWD

UP

0.88

0.47

C C

B-B

BEFORE

B-B

AFTER

C-C

5

2

2 4

7 8

8

5

STA

Y=1370.000

STA

Y=1370.000

1.70

3

6

7

1361449

(SHEET 2 OF 8)
 FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

FWD

D

10

9

X=0.000

3.70

3.10

6.00

5.00

1361450

(SHEET 3 OF 8)
 FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

A

LOOKING FORWARD

AFTER

F

E

F

E

11

12

1361451

(SHEET 4 OF 8)
 FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

F-F

10

10

11

11

E-E

12

10

1361452

(SHEET 5 OF 8)
 FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK

August 08, 2007

Revision 1: November 06, 2008 MD11-28-135

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BOEING SERVICE BULLETIN MD11-28-135

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep Cover - - In accordance with MD-11 

AMM 28-21-02.

Remove/Keep Bolt - -

Remove/Keep Washer - -

2 Remove/Keep Bracket ANL7132-1 1 Clamp and associated 

hardware.

3 Fill Plug - - Plug existing lower rivet hole in 

stiffener with AD material. 

4 Drill Bracket ANL7132-1 - Step drill (1) hole on bracket. 

Refer to MD-11-1P SRM 

51-31-01 and MD-11-1F SRM 

51-31-01 as accepted 

procedures.

5 Apply - BOND - Faying surfaces common to 

jumper terminals and bracket, 

and bracket to structure for 

fault current path return 

protection. Refer to SWPM 

20-50-01 as an accepted 

procedure.

6 Drill Bracket ANL7132-1 - Locate, drill and process for 

HL326-6 Pin (2 places). Refer 

to MD-11-1P SRM 51-31-01, 

MD-11-1F SRM 51-31-01, 

MD-11-1F SRM 51-33-01 and 

MD-11-1P SRM 51-33-01 as 

accepted procedures.

7 Install (Kept) Bracket ANL7132-1 1 Clamp and associated 

hardware.

Install (New) PIN HL326-6-2 2 Refer to MD-11-1F SRM 

51-33-01 and MD-11-1P SRM 

51-33-01 as accepted 

procedures.

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

(SHEET 6 OF 8)
 FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

8 Install (New) JUMPER S2891103-10SS6 1 Terminal lug of jumper (Bracket 

Assembly) may be bent for 

ease of installation. Refer to 

SWPM 20-20-01 as an 

accepted procedure. 

Acceptable to locate screw 

head and bonding jumper 

terminal lug on outboard side 

(flat side) of ANL7132-1. Make 

sure jumper Does Not rest 

against fuel pipes, fuel tank, 

cables or moving parts. 

Install (New) SCREW NAS1801-3-9 1

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 1

9 Drill Shroud ANL7131-1 - Locate and drill (.218/.229) 

diameter hole. Refer to 

MD-11-1P SRM 51-31-01 and 

MD-11-1F SRM 51-31-01 as 

accepted procedures.

10 Apply - BOND - Faying surfaces common to 

jumper terminals, shroud (both 

sides), and valve housing for 

current path return protection. 

Refer to SWPM 20-50-01 as 

an accepted procedure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 7 OF 8)
 FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

11 Install (New) SCREW NAS1801-3-9 1

Install (New) WASHER NAS1149F0332P 2

Install (New) JUMPER S2891103-10SS6 - Acceptable to form jumper lug 

to contour of fill valve controller 

shroud to achieve maximum 

faying surface contact with fill 

valve controller shroud. 

Terminal lug of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

Install (New) CABLE, JUMPER RC11307-10SS4 1 Acceptable to form jumper lug 

to contour of fill valve controller 

shroud to achieve maximum 

faying surface contact with fill 

valve controller shroud. 

Terminal lug of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

Install (New) NUT MS21042L3 1 Encapsulate seal. Refer to 

MD-11-1F SRM 51-41-01 and 

MD-11-1P SRM 51-41-01 as 

accepted procedures. 

12 Install (Kept) Bolt - -

Install (Kept) Washer - -

Install (Kept) CABLE, JUMPER RC11307-10SS4 - Acceptable to form jumper lug 

to contour of fill valve controller 

shroud to achieve maximum 

faying surface contact with fill 

valve controller shroud. 

Terminal lug of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

Install (Kept) Cover - - In accordance with MD-11 

AMM 28-21-02.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 8 OF 8)
 FIGURE 5: INSTALL ELECTRICAL BONDING JUMPER UPPER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

FIGURE 5: INSTALL ELECTRICAL BONDING JUMPER UPPER AUXILIARY TANK

UP

OUTBD

LOOKING FORWARD AT REAR SPAR 

STATION Y=1370.000

UPPER AUXILIARY FUEL TANK

A

BEFORE

X=0.000

AIRPLANE CENTERLINE

Zcw=10.000

SEE D

1

SEE A

B

B

1361454

(SHEET 1 OF 8)
 FIGURE 5: INSTALL ELECTRICAL BONDING JUMPER UPPER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

FWD

UP

FWD

B-B

C C

2

3

Zcw=15.2

(APPROX)

5

3

C-C

0.80

LOOKING DOWN

0.50

(2 LOCATIONS)

1.50

0.20

4

STA

Y=1370.000

STA

Y=1370.000

1361455

(SHEET 2 OF 8)
 FIGURE 5: INSTALL ELECTRICAL BONDING JUMPER UPPER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

FWD

D

7

6

X=0.000

1.00

3.70

3.10

1361456

(SHEET 3 OF 8)
 FIGURE 5: INSTALL ELECTRICAL BONDING JUMPER UPPER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

A

AFTER

LOOKING FORWARD

E

F

E

F

9

8

1361457

(SHEET 4 OF 8)
 FIGURE 5: INSTALL ELECTRICAL BONDING JUMPER UPPER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

F-F

7

7

8

8

E-E

9

7

1361458

(SHEET 5 OF 8)
 FIGURE 5: INSTALL ELECTRICAL BONDING JUMPER UPPER AUXILIARY TANK

August 08, 2007

Revision 1: November 06, 2008 MD11-28-135

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 48 of 58

BOEING SERVICE BULLETIN MD11-28-135

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep Cover - - In accordance with MD-11 

AMM 28-21-02.

Remove/Keep Bolt - -

Remove/Keep Washer - -

2 Drill BRACKET ABN7294-793 - Locate, drill and process for 

HL326-6 Pin (2 places). Refer 

to MD-11-1P SRM 51-31-01, 

MD-11-1F SRM 51-31-01, 

MD-11-1F SRM 51-33-01 and 

MD-11-1P SRM 51-33-01 as 

accepted procedures.

3 Apply - BOND - Faying surfaces common to 

jumper terminals, and bracket 

for fault current path return 

protection. Refer to SWPM 

20-50-01 as an accepted 

procedure.

4 Install (New) BRACKET ABN7294-793 1

Install (New) PIN HL326-6-2 2 Refer to MD-11-1F SRM 

51-33-01 and MD-11-1P SRM 

51-33-01 as accepted 

procedures.

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

5 Install (New) SCREW NAS1801-08-10 1

Install (New) LOCKWASHER MS35338-43 1

Install (New) WASHER NAS1149F0332P 1

Install (New) CABLE, JUMPER RC11309-10SS4 1 Terminal lug of jumper (Bracket 

Assembly) may be bent for 

ease of installation. Refer to 

SWPM 20-20-01 as an 

accepted procedure. 

Acceptable to locate screw 

head and terminal lug on 

outboard side (flat side) of 

bracket. Make sure jumper 

Does Not rest against fuel 

pipes, fuel tank, cables or 

moving parts.

6 Drill Shroud ANL7131-1 - Locate and drill (.218/.229) 

diameter hole. Refer to 

MD-11-1P SRM 51-31-01 and 

MD-11-1F SRM 51-31-01 as 

accepted procedures.

(SHEET 6 OF 8)
 FIGURE 5: INSTALL ELECTRICAL BONDING JUMPER UPPER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

7 Apply - BOND - Faying surfaces common to 

jumper terminals, shroud (both 

sides), and valve housing for 

fault current path return 

protection. Refer to SWPM 

20-50-01 as an accepted 

procedure.

8 Install (New) SCREW NAS1801-3-9 1

Install (New) WASHER NAS1149F0332P 2

Install (New) CABLE, JUMPER RC11309-10SS4 - Acceptable to form jumper lug 

to contour of fill valve controller 

shroud to achieve maximum 

faying surface contact with fill 

valve controller shroud. 

Terminal lug of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

Install (New) CABLE, JUMPER RC11307-10SS4 1 Acceptable to form jumper lug 

to contour of fill valve controller 

shroud to achieve maximum 

faying surface contact with fill 

valve controller shroud. 

Terminal lug of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

Install (New) NUT MS21042L3 1 Encapsulate seal. Refer to 

MD-11-1F SRM 51-41-01, 

MD-11-1P SRM 51-41-01 as 

accepted procedures.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 7 OF 8)
 FIGURE 5: INSTALL ELECTRICAL BONDING JUMPER UPPER AUXILIARY TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

9 Install (Kept) Bolt - -

Install (Kept) Washer - -

Install (Kept) CABLE, JUMPER RC11307-10SS4 - Acceptable to form jumper lug 

to contour of fill valve controller 

shroud to achieve maximum 

faying surface contact with fill 

valve controller shroud. 

Terminal lug of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

Install (Kept) Cover - - In accordance with MD-11 

AMM 28-21-02.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 8 OF 8)
 FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK

UP

OUTBD

SEE A

LOOKING AFT

TAIL FUEL TANK

A

BEFORE

Xch=0.000 Xch=10.000

1.50

0.10

SEE D

1

B B

1361459

(SHEET 1 OF 8)
 FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

OUTBD

FWD

UP

FWD

FWD

OUTBD

LOOKING UP

C-C

B-B

0.44

2 4

LOOKING DOWN

C

C

5

6

3

LOOKING INBOARD

0.50

3 (2 LOCATIONS)

1361460

(SHEET 2 OF 8)
 FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

FWD

D

Xch=6.000

8

7

3.70

3.10

6.00

5.00

1361461

(SHEET 3 OF 8)
 FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

UP

OUTBD

LOOKING AFT

TAIL FUEL TANK

AFTER

F

E

F

E

A

Xch=0.000 Xch=10.000

10 9

1361462

(SHEET 4 OF 8)
 FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

F-F

8

8

9

9

E-E

10

8

1361463

(SHEET 5 OF 8)
 FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep Cover - - In accordance with MD-11 

AMM 28-21-02.

Remove/Keep Bolt - -

Remove/Keep Washer - -

2 Drill BRACKET ASSY ABN7210-539 - Locate, drill and process for 

HL326-6 Pin (2 places). Refer 

to MD-11-1P SRM 51-31-01, 

MD-11-1F SRM 51-31-01, 

MD-11-1F SRM 51-33-01 and 

MD-11-1P SRM 51-33-01 as 

accepted procedures.

3 Apply - BOND - Faying surfaces common to 

jumper terminals, and bracket 

for fault current path return 

protection. Refer to SWPM 

20-50-01 as an accepted 

procedure.

4 Install (New) BRACKET ASSY ABN7210-539 1

Install (New) PIN HL326-6-2 2 Refer to MD-11-1F SRM 

51-33-01 and MD-11-1P SRM 

51-33-01 as accepted 

procedures.

Install (New) WASHER NAS1149F0332P 2

Install (New) NUT MS21042L3 2

5 Apply - BOND - Faying surfaces common to 

jumper terminals, shroud (both 

sides), and valve housing for 

fault current path return 

protection. Refer to SWPM 

20-50-01 as an accepted 

procedure.

(SHEET 6 OF 8)
 FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK

August 08, 2007

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BOEING SERVICE BULLETIN MD11-28-135

6 Install (New) SCREW NAS1801-3-9 1

Install (New) LOCKWASHER MS35338-43 1

Install (New) WASHER NAS1149F0332P 1

Install (New) JUMPER S2891103-10SS4 1 Terminal lug of jumper (Bracket 

Assembly) may be bent for 

ease of installation. Refer to 

SWPM 20-20-01 as an 

accepted procedure. 

Acceptable to locate screw 

head and terminal lug on 

outboard side (flat side) of 

bracket. Make sure jumper 

Does Not rest against fuel 

pipes, fuel tank, cables or 

moving parts.

7 Drill Shroud ANL7131-1 - Locate and drill (.218/.229) 

diameter hole. Refer to 

MD-11-1P SRM 51-31-01 and 

MD-11-1F SRM 51-31-01 as 

accepted procedures.

8 Apply - BOND - Faying surfaces common to 

jumper terminals, shroud (both 

sides), and valve housing for 

fault current path return 

protection. Refer to SWPM 

20-50-01 as an accepted 

procedure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 7 OF 8)
 FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK

August 08, 2007

Revision 1: November 06, 2008 MD11-28-135

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 58

BOEING SERVICE BULLETIN MD11-28-135

9 Install (New) SCREW NAS1801-3-9 1

Install (New) WASHER NAS1149F0332P 2

Install (New) JUMPER S2891103-10SS4 - Terminal lug of jumper (Bracket 

Assembly) may be bent for 

ease of installation. Refer to 

SWPM 20-20-01 as an 

accepted procedure. 

Acceptable to locate screw 

head and terminal lug on 

outboard side (flat side) of 

bracket. Make sure jumper 

Does Not rest against fuel 

pipes, fuel tank, cables or 

moving parts.

Install (New) CABLE, JUMPER RC11307-10SS4 1 Terminal lug of jumper (Bracket 

Assembly) may be bent for 

ease of installation. Refer to 

SWPM 20-20-01 as an 

accepted procedure. 

Acceptable to locate screw 

head and terminal lug on 

outboard side (flat side) of 

bracket. Make sure jumper 

Does Not rest against fuel 

pipes, fuel tank, cables or 

moving parts.

Install (New) NUT MS21042L3 1 Encapsulate seal. Refer to 

MD-11-1F SRM 51-41-01 and 

MD-11-1P SRM 51-41-01 as 

accepted procedures.

10 Install (Kept) Bolt - -

Install (Kept) Washer - -

Install (Kept) CABLE, JUMPER RC11307-10SS4 - Acceptable to form jumper lug 

to contour of fill valve controller 

shroud to achieve maximum 

faying surface contact with fill 

valve controller shroud. 

Terminal lug of jumper may be 

bent for ease of installation. 

Refer to SWPM 20-20-01 as 

an accepted procedure. Make 

sure jumper does not rest 

against fuel pipes, fuel tank, 

cables or moving parts.

Install (Kept) Cover - - In accordance with MD-11 

AMM 28-21-02.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 8 OF 8)