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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 Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 22, 2009 767-57A0122 1 of 19
5.0
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 22, 2009 767-57A0122 2 of 19 BOEING SERVICE BULLETIN 767-57A0122
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BLANK PAGE
Table of Contents
Summary5
1. PLANNING INFORMATION9
A. Effectivity9
1. Airplanes9
2. Spares Affected9
B. Concurrent Requirements9
C. Reason ................................................ 1 0 D. Description .............................................. 1 0 E. Compliance .............................................. 1 0 F. Approval ............................................... 1 1 G. Manpower .............................................. 1 1 H. Weight and Balance Changes .................................... 1 1 I. Electrical Load Data ......................................... 1 1 J. References .............................................. 1 2
1. Existing Data .......................................... 1 2
2. Data supplied with this Service Bulletin ............................ 1 2
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 2 K. Publications Affected ........................................ 1 2 L. Interchangeability and Intermixability of Parts ........................... 1 2
2. MATERIAL INFORMATION ........................................ 1 3 A. Material - Price and Availability ................................... 1 3 B. Industry Support Information .................................... 1 3 C. Parts Necessary For Each Airplane ................................. 1 3
1. Kits/Parts ............................................ 1 3
2. Parts and Materials Supplied by the Operator ........................ 1 4
3. Parts Modified and Reidentified ................................ 1 4
4. Parts Removed and Not Replaced .............................. 1 4 D. Parts Necessary to Change Spares ................................. 1 4 E. Special Tooling - Price and Availability ............................... 1 4 F. Special Tooling Necessary to do this Service Bulletin ....................... 1 4
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 5 A. GENERAL INFORMATION ..................................... 1 5 B. WORK INSTRUCTIONS ....................................... 1 5 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
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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
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Commercial Airplanes 767 Service Bulletin ALERT SummaryNumber: 767-57A0122Original 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 HoursTotal Task HoursAirplanes
2.502.50All
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
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BOEING SERVICE BULLETIN 767-57A0122
ALERT ALERT STA 955
INSTALL THE TFE SLEEVE
AND FULL CUSHION CLAMP
ON THE WIRE BUNDLE 1834099 Original Issue: October 22, 2009
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 19
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
ALERTALERT
BLANK PAGE
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.
DESCRIPTIONCONFIGURATIONGROUP 767-300-1 Airplane Models:
767-300 GroupVariable Number 1VS911 - VS912 1VS916
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 ZoneModel 144767-300 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
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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 HoursTask HoursNumber of Persons Task
1.001.001Open Access
0.500.501Figure 1
1.001.001Close Access
2.502.50TOTAL 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
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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 TitleDrawing Number Wire Bundle Installation Wheel Well Area Right, STA 955 Thru 1065288T4570 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