August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 58 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 Shut off, All Tanks - Install Electrical Bonding Jumper 

## BOEING PROPRIETARY, CONFID ENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document on ly to the extent that the page contains copyrightable subject matter.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 Compan y, 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 intellectua l property license (express or implied) is granted in connection with this document or otherwise.BLANK PAGE August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 2 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

BLANK PAGETable of Contents August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 58 

### 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 Intermix ability 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 Spar es . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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 ELECTR ICAL BONDING JUMPER LOWER AUXILIARY TANK . . . . . . . . . 35 FIGURE 5: INSTALL ELECTR ICAL BONDING JUMPER UPPER AUXILIARY TANK . . . . . . . . . 43 FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK . . . . . . . . . . . . . . . . . 51Table of Contents August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 4 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

BLANK PAGEAugust 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 58 

### 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 Shut off, All Tanks - Install Electrical Bonding Jumper

This Revision includes all pages of the service bulletin.
COMPLIANCE INFORM ATION RELATED TO THIS REVISION No more work is necessary on airplanes changed as shown in the original issu e of this service bulletin.
REASON FOR REVISION This revision is sent to incorporate engineering released s ubsequent to the original iss ue of this service bulletin, which relocates ground brackets and jumpers due to in terference with airplane co mponents/structure. Noted changes are based on findings discovered as a result of se rvice 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., Materi al - 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, remove d function test work instruction. 8. Figures 1 through 6 changed to reflec t accessibility issues found as a re sult of service bulletin validation.August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 6 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

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, exce pt in Paragraph 1.A., Effectiv ity, 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, 2008August 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 Shut off, All Tanks - Install Electrical Bonding Jumper

CONCURRENT REQUIREMENTS

None.
BACKGROUND Boeing investigation a nd analysis revealed that fill valve controlle r installations had in adequate electrical bonding. This could allow point-of-co ntact arcing or filament heating da mage in the fuel tanks. Installing electrical bonding jumpers from the fill valve controllers to airplane stru cture will provide a gr ounding 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 fuse lage number 625 had this modification inco rporated at t he 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 instructio ns to install electrical bonding jumpers from right/left/center wing tanks, upper and lower auxiliary tanks and tail tank fill valv e controllers to t he 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 (F AA) will possibly release an Airworthin ess Directive related to this service bulletin. The Airworthiness Directiv e will make the compliance tasks and ti mes 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.August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 8 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

MANPOWER

MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragr aph 2.A., Material - Price and Availability. Airplanes Total Task Hours Elapsed Hours MD-11 and MD-11F 27.5 27.5

INSTALL ELECTRICAL BONDING JUMPER1361439August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 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 Shut off, 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 th is modification incorporated at the operators facility as an installation verification in accordance with Dr awing SR1 1280059-7001.

Airplane models:

MD-11 MD-11F
IDENTIFICATION BY CUSTOMER, CUSTOM ER 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.August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 10 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

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 509August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

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 f ill valve controller insta llations had inadequate electrical bonding. This could allow point-of-contact arcing or filament heating damage in the fuel tanks. Installing electrical bondin g jumpers from the fill valve contro llers to airplane structure will provide a grounding path in the event of a fault curr ent occurrence in the f ill 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 Dr awing SR1 1280059-7001. Fuselage Group 447–449 1 451–464 1 466–489 1 491–517 1 519–552 1 554–646 1August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 12 of 58 

### 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 re leased 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 fi ndings discovered as a result of service bulletin installation verification don e at an airline facility. D. Description This service bulletin provid es instructions to install electrical bonding jumpers from left/right/center wing tanks, upper and lower auxiliary tanks and tail tank fill valve cont rollers to the ai rplane structure. Revision - 1 No more work is necessary on airplane s changed as shown in the original issue of this service bulletin. E. Compliance

The Federal Aviation Admini stration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airwor thiness Directive will ma ke the compliance tas ks 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, F AA 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 expe rienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not includ e 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.August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

H. Weight and Balance Changes

None.
I. Electrical Load Data Not changed.
J. References 1. Existing Data: a. MD-11-1F Structural Repair Manual (S RM) 51-00-01, 51-31-01, 51-33-01, 51-41-01 b. MD-11-1P Structural Repair Manual (S RM) 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 Manu al (SWPM) 20-20-01, 20-50-01 2. Data supplied with this Service Bulletin:

None.

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

This drawing was used to prepare this service bulletin. This drawin g 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 EAugust 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 14 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

K. Publications Affected

L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not af fect interchangeability or intermixability of parts. Publication Chapter-Section Illustrated Parts Catalog 28-21August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

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 av ailable parts, a supply se quence 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 conditi ons of the Boeing standard purchase order acknowledgment. After the Unit Price date, new pr ice and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your pur chase 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 $2,698.00August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 16 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

C. Parts Necessary For Each Airplane
1. Kits/Parts: To get the kits/parts shown below, refer to Pa ragraph 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)August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

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 83574August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 18 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

BLANK PAGEAugust 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

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 WH EN 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 acrony ms. 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 wash ers called for in this service bulletin is the maximum thickness which may be used u nder 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 ConnectionsAugust 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 20 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

7. These work instructions refer to procedures included on other Being documents. When the words “refer to” are used and the operat or 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 sequenc e of steps to do this service bulletin can be changed. 10. Unless shown differently, these di mensions 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 re fer to SRM, Chapter 51 as an accepted procedure. — Torque limits to tighten nuts and bolts re fer to SRM, Chapter 51 as an accepted procedure. 11. Cover Fill Valve Controller to protect it from any debris during sh roud assembly rework. Fill Valve Controller may be re moved 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 3August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

3. If the fill shutoff valve controller was removed, do a function test of upper, lower auxiliary tanks, and tail tank fill shutoff valv e 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 Au xiliary Fuel Tank 4 Center Wing Upper Au xiliary Fuel Tank 5 Tail Tank Horizontal Stabilizer Front Spar 6 Location In Accordance with FigureFIGURE 1: INSTALL ELECTR ICAL BONDING JUMPER, TANK 1 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 22 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

FIGURE 1: INSTALL ELECTR ICAL 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 A SEE1361440

(SHEET 1 OF 5)FIGURE 1: INSTALL ELECTRICAL BONDING JUMPER, TANK 1 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 58 

### 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 UP1361441

(SHEET 2 OF 5)FIGURE 1: INSTALL ELECTR ICAL BONDING JUMPER, TANK 1 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 24 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

C-C 5 6



### D-D 7

51361442

(SHEET 3 OF 5)FIGURE 1: INSTALL ELECTRICAL BONDING JUMPER, TANK 1 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 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 Bolt - - Remove/Keep Washer - - 2 Drill BRACKET ASSY ABN7210-539 - L ocate, 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 ELECTR ICAL BONDING JUMPER, TANK 1 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 26 of 58 

### 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 2: INSTALL ELECTRICAL BONDING JUMPER TANK 2 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

FIGURE 2: INSTALL ELECTRIC AL BONDING JUMPER TANK 2

INBD UP

Xfs=-227.00 RIGHT SIDE LOOKING AFT AT FRONT SPAR B B 1

A SEE1361443

(SHEET 1 OF 3)FIGURE 2: INSTALL ELECTRICAL BONDING JUMPER TANK 2 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 28 of 58 

### 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

0.701361444

(SHEET 2 OF 3)FIGURE 2: INSTALL ELECTRICAL BONDING JUMPER TANK 2 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 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 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 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 30 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

FIGURE 3: INSTALL ELECTRIC AL BONDING JUMPER TANK 3

INBD UP B B Xfs=-918.000

2

RIGHT SIDE LOOKING AFT AT FRONT SPAR 

### BEFORE A 1 A SEE

4.50 1.501361445

(SHEET 1 OF 5)FIGURE 3: INSTALL ELECTRICAL BONDING JUMPER TANK 3 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 58 

### 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) 2 31361446

(SHEET 2 OF 5)FIGURE 3: INSTALL ELECTRICAL BONDING JUMPER TANK 3 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 32 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

D-D C-C 6

5 5 71361447

(SHEET 3 OF 5)FIGURE 3: INSTALL ELECTRICAL BONDING JUMPER TANK 3 August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 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 Bolt - - Remove/Keep Washer - - 2 Drill BRACKET ASSY ABN7210-539 - L ocate, 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 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 34 of 58 

### 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 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

FIGURE 4: INSTALL ELECTRICAL BO NDING JUMPER LOWER AUXILIARY TANK

UP

OUTBD A SEE

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

11361448

(SHEET 1 OF 8)FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 36 of 58 

### 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 71361449

(SHEET 2 OF 8)FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

FWD



### D 10 9 X=0.000

3.70 3.10

6.00 5.001361450

(SHEET 3 OF 8)FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 38 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

A

LOOKING FORWARD 

### AFTER F E

F E 11

121361451

(SHEET 4 OF 8)FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

F-F 10 10 11

11


### E-E 12

101361452

(SHEET 5 OF 8)FIGURE 4: INSTALL ELECTRICAL BONDING JUMPER LOWER AUXILIARY TANK August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 40 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

The step numbers shown below agree with the numbers sh own in the circle symbols in the figure. The QTY numbers shown below are the number of pa rts 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 - Loc ate, 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 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 58 

### 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 - Loca te 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 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 42 of 58 

### 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 f ill 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 f ill 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 RC11307-10 SS4 - Acceptable to form jumper lug to contour of f ill 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 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

FIGURE 5: INSTALL EL ECTRICAL 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 A SEE

B B1361454

(SHEET 1 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 © U npublished Work - See page 1 for details. 44 of 58 

### 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=1370.0001361455

(SHEET 2 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. 45 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

FWD



### D 7 6 X=0.000

1.00 3.70 3.101361456

(SHEET 3 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 © U npublished Work - See page 1 for details. 46 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

A
AFTER LOOKING FORWARD E

F E F 9 81361457

(SHEET 4 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. 47 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

F-F 7 7 8

8


### E-E 9

71361458

(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 © U npublished Work - See page 1 for details. 48 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

The step numbers shown below agree with the numbers sh own in the circle symbols in the figure. The QTY numbers shown below are the number of pa rts 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 - Locat e, 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 - Loc ate 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 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 58 

### 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 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 50 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

9 Install (Kept) Bolt - - Install (Kept) Washer - - Install (Kept) CABLE, JUMPER RC11307-10 SS4 - Acceptable to form jumper lug to contour of f ill 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 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

FIGURE 6: INSTALL ELECTRIC AL BONDING JUMPER TAIL TANK

UP

OUTBD A SEE

LOOKING AFT TAIL FUEL TANK 

### A BEFORE Xch=10.000 Xch=0.000

1.50 0.10 D SEE

1 B B1361459

(SHEET 1 OF 8)FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 52 of 58 

### 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 (2 LOCATIONS) 31361460

(SHEET 2 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. 53 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

FWD


### D Xch=6.000

8 7 3.70 3.10

6.00 5.001361461

(SHEET 3 OF 8)FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 54 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

UP

OUTBD LOOKING AFT TAIL FUEL TANK 

### AFTER F E

F E



### A Xch=10.000 Xch=0.000

10 91361462

(SHEET 4 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. 55 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

F-F 8 8 9

9


### E-E 10

81361463

(SHEET 5 OF 8)FIGURE 6: INSTALL ELECTRICAL BONDING JUMPER TAIL TANK August 08, 2007 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © U npublished Work - See page 1 for details. 56 of 58 

### BOEING SERVICE BULLETIN MD11-28-135

The step numbers shown below agree with the numbers sh own in the circle symbols in the figure. The QTY numbers shown below are the number of pa rts 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 - Loc ate, 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 Revision 1: November 06, 2008 MD11-28-135 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 58 

### 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 - Loca te 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 © U npublished 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 RC11307-10 SS4 - Acceptable to form jumper lug to contour of f ill 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

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