### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Number: 767-57A0122**  Original Issue: October 22, 2009 ATA System: 5710 **SUBJECT:** WINGS - Center Wing - Sleeve and Clamp Installation Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 1 of 19 5.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 2 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION ........................................ 9 A. Effectivity................................................ 9 1. Airplanes ............................................. 9 2. Spares Affected ......................................... 9 B. Concurrent Requirements....................................... 9 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 12 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 14 3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 14 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 FIGURE 1: REAR SPAR - RIGHT MAIN WHEEL WELL - SLEEVE AND CLAMP INSTALLATION . . 17

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 3 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 4 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Summary**  **Number: 767-57A0122** Original Issue: October 22, 2009 ATA System: 5710 **SUBJECT:** WINGS - Center Wing - Sleeve and Clamp Installation THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** Accomplishment of the modifications within this service bulletin will help prevent possible ignition sources in the center auxiliary fuel tank caused by a wiring short. An ignition source in a fuel tank could result in a fire or an explosion. A safety assessment by Boeing identified a certain type of fastener that penetrates the fuel tank wall and has an insufficient electrical bond to the fuel tank structure. These fasteners can be a path for electrical energy to enter the fuel tank if a wiring short occurs in a wire bundle installed along the fuel tank boundary structure. The electrical energy from the wiring short can go through these fasteners because they have an insufficient bond to the fuel tank structure. This energy can be sufficient to cause arcing at the ends of these fasteners in the fuel tank. The necessary changes were incorporated in production by PRRB13421-11. A review of the production records found that three airplanes did not met the production requirements. On these three airplanes, there is one location on the rear spar of the center wing fuel tank where the specified tetrafluoroethylene (TFE 2X) sleeve and clamp change was not accomplished. This Service Bulletin makes these changes at one location on the rear spar of the center wing where a high energy short can occur. A TFE 2X sleeve on the wire bundle gives more protection from chafing. The wire bundle clamps has a design with protection on its metal edges. These changes make sure that the risk of an ignition source in the fuel tank from a short is kept to a minimum. This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". **ACTION** Get access to the rear spar of the center wing in the main wheel well on the right side and install the TFE 2X sleeve and the full cushion wire bundle clamp at one location.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 5 of 19**EFFECTIVITY** 767-300 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 that this service bulletin be incorporated within 5 years after the original issue date on this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of November 18, 2008. Please refer to Paragraph 2.B., Industry Support Information. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  2.50 2.50 All
**MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 6 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 7 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 8 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 767 Service Bulletin **ALERT Number: 767-57A0122**  Original Issue: October 22, 2009 ATA System: 5710 **SUBJECT:** WINGS - Center Wing - Sleeve and Clamp Installation THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below.

**DESCRIPTION CONFIGURATION**  **GROUP** 767-300

- 1

Airplane Models: 767-300 **Group Variable Number**  1 VS911 - VS912 1 VS916 2. Spares Affected None. **B. Concurrent Requirements** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 9 of 19**C. Reason** Accomplishment of the modifications within this service bulletin will help prevent possible ignition sources in the center auxiliary fuel tank caused by a wiring short. An ignition source in a fuel tank could result in a fire or an explosion. A safety assessment by Boeing identified a certain type of fastener that penetrates the fuel tank wall and has an insufficient electrical bond to the fuel tank structure. These fasteners can be a path for electrical energy to enter the fuel tank if a wiring short occurs in a wire bundle installed along the fuel tank boundary structure. The electrical energy from the wiring short can go through these fasteners because they have an insufficient bond to the fuel tank structure. This energy can be sufficient to cause arcing at the ends of these fasteners in the fuel tank. The necessary changes were incorporated in production by PRRB13421-11. A review of the production records found that three airplanes did not met the production requirements. On these three airplanes, there is one location on the rear spar of the center wing fuel tank where the specified tetrafluoroethylene (TFE 2X) sleeve and clamp change was not accomplished. This Service Bulletin makes these changes at one location on the rear spar of the center wing where a high energy short can occur. A TFE 2X sleeve on the wire bundle gives more protection from chafing. The wire bundle clamps has a design with protection on its metal edges. These changes make sure that the risk of an ignition source in the fuel tank from a short is kept to a minimum. This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". **D. Description** Get access to the rear spar of the center wing in the main wheel well on the right side and install the TFE 2X sleeve and the full cushion clamp on the wire bundle at one location. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 144 767-300 **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 that the change given in this service bulletin be done within 5 years after the original issue date on this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 10 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT F. Approval**  This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task hours necessary to do this change for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. **Elapsed Hours Task Hours**  **Number of Per- sons**  **Task**

1.00 1.00 1 Open Access 0.50 0.50 1 Figure 1 1.00 1.00 1 Close Access 2.50 2.50 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 11 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT J. References**  1. Existing Data a. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19 b. 767 Aircraft Maintenance Manual (AMM) 24-22-00, 32-00-15, 32-00-20 c. Engineering Change Memo PRRB13421-11 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin
**Title Drawing Number**  Wire Bundle Installation Wheel Well Area Right, STA 955 Thru 1065 288T4570 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary. **L. Interchangeability and Intermixability of Parts** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 12 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.
**Unit Price thru Apr 31/10**  **ROLT (Weeks)**  **QTY Date**  **Name Kit Number**  $ 189.00 13 3 05/21/2009 Top Kit 015T1842-1 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. Mail to: 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 available for 767 airplanes in warranty as of November 18, 2008. For task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin number and reference the airplane variable numbers in your purchase order. **C. Parts Necessary For Each Airplane** 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. **NOTE:** One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the table below. To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 13 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT Figure Kit**  **1 Top Kit**  1 015T1842-1 **Group 1:**
**KIT 015T1842-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 1**  **QTY** Sleeve - 1 inch I.D. (As supplied 1.5 inch I.D.) 1 005W3281-5

WIRE BUNDLE CLAMP 1 BACC10JU106
2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number/ Specification**  (a) LACING TAPE 3 ft BMS 13-54, TYPE III, CLASS 1, FINISH C, WHITE (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 14 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT 3. ACCOMPLISHMENT INSTRUCTIONS**  **A. GENERAL INFORMATION CAUTION:**  KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:** 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Obey all of the warnings and cautions given in the specified manual sections. 4. 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 – Torque limits to tighten nuts and bolts are in 767 SRM, Chapter 51 5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 6. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. **B. WORK INSTRUCTIONS** 1. Remove electrical power from the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. 2. Install the downlocks on the nose and main landing gear. Refer to 767 AMM 32-00-20 as an accepted procedure. 3. Install the door locks on the nose and main landing gear. Refer to 767 AMM 32-00-15 as an accepted procedure. 4. Get access to the rear spar at the main wheel well on the right side of the airplane. 5. Install the tetrafluoroethylene (TFE 2X) sleeve and clamp in accordance with Figure 1. 6. Remove the door locks on the nose and main landing gear. Refer to 767 AMM 32-00-15 as an accepted procedure.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 15 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT**7. Remove the downlocks on the nose and main landing gear. Refer to 767 AMM 32-00-20 as an accepted procedure. 8. Restore electrical power to the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. 9. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 16 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT FIGURE 1: REAR SPAR - RIGHT MAIN WHEEL WELL - SLEEVE AND CLAMP INSTALLATION**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 17 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT FIGURE 1: REAR SPAR - RIGHT MAIN WHEEL WELL - SLEEVE AND CLAMP INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 18 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT**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 this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  1

- SCREW Remove / Keep 1 1

- WASHER Remove / Keep If a spacer is installed. 1

- SPACER Remove / Keep It is not necessary to remove the nut if it is attached to the bracket. 1

- NUT Remove / Keep

1

- CLAMP Remove 2 Sleeve is TFE 2X. Cut the sleeve to the requirement length is necessary. - - SLEEVE Cut 3

Sleeve is TFE 2X.Cut the sleeve longitudinally for installation on the wire bundle. - - SLEEVE Cut

Sleeve is TFE 2X. 1 005W3281-5 Sleeve - 1 inch I.D. (As supplied 1.5 inch I.D.) Install (New)
Refer to SWPM 20-10-12 as an accepted procedure for installation of wire bundle support clamp. 1 BACC10JU106 WIRE BUNDLE CLAMP Install (New) 4

1

- WASHER Install (Kept) 5 1

- SCREW Install (Kept) 1

- SPACER Install (Kept) 1

- NUT Install (Kept) Install in shadedarea. Refer to SWPM 20-10-11 as an accepted procedureto install a wire harness tie. - BMS 13-54, TYPE III, CLASS 1, FINISH C, WHITE LACING TAPE Install (New) 6

**FIGURE 1: REAR SPAR - RIGHT MAIN WHEEL WELL - SLEEVE AND CLAMP INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 22, 2009 767-57A0122 19 of 19 **BOEING SERVICE BULLETIN 767-57A0122 ALERT**  **ALERT**