# Boeing Alert Service Bulletin 757-57A0064: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2010-0698; AD 2011-05-04 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 757-57A0064](https://openairdocs.org/service-documents/boeing/757-57a0064.md) - Title as filed: Boeing - Service Bulletin - Pages: 444 - PDF: https://openairdocs.org/files/sha256/7a/15/7a15d9368ce78688ba676e0ae910f9ea7fc4ca4d94f96960a44e826fcb65275a - Page: https://openairdocs.org/service-documents/boeing/757-57a0064/file/7a15d9368ce7 ## Text This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OCR) Commercial DEDEING Airplanes 757 Service Bulletin - ALERT Number: 757-57A0064 Original Issue: July 16, 2007 Revision 1: October 05, 2009 ATA System: 5710 5720 SUBJECT: WINGS - Center and Outer Wing - Fastener Sealing and Wire Bundle Support Inspection and Modification 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by all export ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, 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. Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 1 of 442 6.0 ### Page 2 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT BLANK PAGE Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 2 of 442 ### Page 3 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Table of Contents Revision Transmittal Sheet 7 Summary . 11 1. PLANNING INFORMATION 15 A. Effectivity 15 1. Airplanes 15 2. Spares Affected 21 B. Concurrent Requirements 21 C. Reason 21 D. Description 22 Compliance 23 F Approval 24 G. Manpower 25 H. Weight and Balance Changes. 35 Electrical Load Data 35 J. References . 35 Existing Data: 35 2 Data supplied with this Service Bulletin 35 3. Installation Drawings Used in the Preparation of this Service Bulletin: 35 K. Publications Affected 36 L Interchangeability and Intermixability of Parts 36 2. MATERIAL INFORMATION. 37 A. Material - Price and Availability. 37 B. Industry Support Information. 37 C. Parts Necessary For Each Airplane 37 Kits/Parts: 37 2. Parts and Materials Supplied by the Operator: 37 3. Parts Modified and Reidentified: 45 4. Parts Removed and Not Replaced: 46 D. Parts Necessary to Change Spares. 46 E. Special Tooling - Price and Availability 46 F. Special Tooling Necessary to do this Service Bulletin. 46 3. 47 GENERAL INFORMATION 47 WORK INSTRUCTIONS. 49 FIGURE 1: GROUPS 1-2 - LEFT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 1-2] • 76 FIGURE 2: GROUPS 1-2 - RIGHT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 1-2] . FIGURE 3: GROUPS 3-4 - LEFT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 3-4] . FIGURE 4: GROUPS 3-4 - RIGHT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 3-4] . FIGURE 5: GROUPS 5-7 - LEFT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 5-7] • FIGURE 6: GROUPS 5-7 - RIGHT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 5-7] FIGURE 7: GROUPS 8-10 - LEFT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 8-10] . FIGURE 8: GROUPS 8-10 - RIGHT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 8-10]. FIGURE 9: GROUPS 11-12 - LEFT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 11-12] . FIGURE 10: GROUPS 11-12 - RIGHT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 11-12] Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 3 of 442 ### Page 4 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT FIGURE 11: GROUPS 13-14 - LEFT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 13-14] . 212 FIGURE 12: GROUPS 13-14 - RIGHT SIDE - REAR SPAR - LOCATION OF FASTENERS [Group 13-14] FIGURE 13: GROUPS 1-5 - LEFT SIDE - FRONT SPAR - LOCATION OF FASTENERS [Group 1-5] . 240 FIGURE 14: GROUPS 1-5 - RIGHT SIDE - FRONT SPAR - LOCATION OF FASTENERS [Group 1-5] . 248 FIGURE 15: GROUPS 6-7, GROUPS 11-12 - LEFT SIDE - FRONT SPAR - LOCATION OF FASTENERS [Group 6-7, 11-12] FIGURE 16: GROUPS 6-7, GROUPS 11-12 - RIGHT SIDE - FRONT SPAR - LOCATION OF FASTENERS [Group 6-7, 11-12] FIGURE 17: GROUPS 8-10, GROUPS 13-14 - LEFT SIDE - FRONT SPAR - LOCATION OF FASTENERS [Group 8-10, 13-14] . FIGURE 18: GROUPS 8-10, GROUPS 13-14 - RIGHT SIDE - FRONT SPAR - LOCATION OF FASTENERS [Group 8-10, 13-14] FIGURE 19: GROUP 1, GROUP 3, GROUPS 5-7, GROUPS 11-12 - CENTER TANK - LOCATION OF FASTENERS [Group 1, 3, 5-7, 11-12] 286 FIGURE 20: GROUP 2, GROUP 4 - CENTER TANK - LOCATION OF FASTENERS [Group 2, 4] 293 FIGURE 21: GROUPS 8-10, GROUPS 13-14 - CENTER TANK - LOCATION OF FASTENERS [Group 8-10, 13-14] 300 FIGURE 22: GROUPS 1-7, GROUPS 11-12 - LEFT SIDE - EQUIPMENT COOLING SYSTEM (ECS) BAY - WIRE BUNDLES SUPPORT - GENERAL VISUAL INSPECTION [Group 1-7, 11-12] FIGURE 23: GROUPS 1-7, GROUPS 11-12 - RIGHT SIDE - EQUIPMENT COOLING SYSTEM (ECS) BAY - WIRE BUNDLES SUPPORT - GENERAL VISUAL INSPECTION [Group 1-7, 11-12] FIGURE 24: GROUPS 8-10, GROUPS 13-14 - LEFT SIDE - EQUIPMENT COOLING SYSTEM (ECS) BAY - WIRE BUNDLES SUPPORT - GENERAL VISUAL INSPECTION [Group 8-10, 13-14] . 314 FIGURE 25: GROUPS 8-10, GROUPS 13-14 - RIGHT SIDE - EQUIPMENT COOLING SYSTEM (ECS) BAY - WIRE BUNDLES SUPPORT - GENERAL VISUAL INSPECTION [Group 8-10, 13-14] . 318 FIGURE 26: GROUPS 1-7, GROUPS 11-12 - LEFT SIDE - EQUIPMENT COOLING SYSTEM (ECS) BAY - WIRE BUNDLES - CLAMP REPLACMENT AND/OR SLEEVE INSTALLATION [Group 1-7, 322 FIGURE 27: GROUPS 1-7, GROUPS 11-12 - RIGHT SIDE - EQUIPMENT COOLING SYSTEM (ECS) BAY - WIRE BUNDLES - CLAMP REPLACEMENT AND/OR SLEEVE INSTALLATION [Group 1-7, 11-12] FIGURE 28: GROUPS 8-10, GROUPS 13-14 - LEFT SIDE - EQUIPMENT COOLING SYSTEM (ECS) BAY - WIRE BUNDLES - CLAMP REPLACEMENT AND/OR SLEEVE INSTALLATION [Group 8-10, FIGURE 29: GROUPS 8-10, GROUPS 13-14 - RIGHT SIDE - EQUIPMENT COOLING SYSTEM (ECS) BAY - WIRE BUNDLES - CLAMP REPLACEMENT AND/OR SLEEVE INSTALLATION [Group 8-10, FIGURE 30: ALL GROUPS - LEFT SIDE - REAR SPAR - WIRE BUNDLES SUPPORT - GENERAL VISUAL INSPECTION [Group 1-14] 342 FIGURE 31: ALL GROUPS - RIGHT SIDE - REAR SPAR - WIRE BUNDLES SUPPORT - GENERAL VISUAL INSPECTION [Group 1-14] FIGURE 32: ALL GROUPS - LEFT SIDE - REAR SPAR - WIRE BUNDLES - CLAMP REPLACEMENT AND/OR SLEEVE INSTALLATION [Group 1-14] FIGURE 33: ALL GROUPS - RIGHT SIDE - REAR SPAR - WIRE BUNDLES - CLAMP REPLACEMENT AND/OR SLEEVE INSTALLATION [Group 1-14] FIGURE 34: GROUPS 7-8, GROUP 12, GROUP 14 - LEFT SIDE - FRONT SPAR - WIRE BUNDLES SUPPORT - GENERAL VISUAL INSPECTION [Group 7-8, 12, 14] FIGURE 35: GROUPS 7-8, GROUP 12, GROUP 14 - RIGHT SIDE - FRONT SPAR - WIRE BUNDLES SUPPORT - GENERAL VISUAL INSPECTION [Group 7-8, 12, 14] Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 4 of 442 ### Page 5 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT FIGURE 36: GROUP 9, GROUP 11, GROUP 13 - LEFT SIDE - FRONT SPAR - WIRE BUNDLES SUPPORT - GENERAL VISUAL INSPECTION [Group 9, 11, 13] 375 FIGURE 37: GROUP 9, GROUP 11, GROUP 13 - RIGHT SIDE - FRONT SPAR - WIRE BUNDLES SUPPORT - GENERAL VISUAL INSPECTION [Group 9, 11, 13] 380 FIGURE 38: GROUPS 1-6, GROUP 10 - LEFT SIDE - FRONT SPAR - WIRE BUNDLES SUPPORT GENERAL VISUAL INSPECTION [Group 1-6, 10] 384 FIGURE 39: GROUPS 1-6, GROUP 10 - RIGHT SIDE - FRONT SPAR - WIRE BUNDLES SUPPORT - GENERAL VISUAL INSPECTION [Group 1-6, 10] 389 FIGURE 40: GROUPS 7-8, GROUP 12, GROUP 14 - LEFT SIDE - FRONT SPAR - WIRE BUNDLES CLAMP REPLACEMENT AND/OR SLEEVE INSTALLATION [Group 7-8, 12, 14] 393 FIGURE 41: GROUPS 7-8, GROUP 12, GROUP 14 - RIGHT SIDE - FRONT SPAR - WIRE BUNDLES CLAMP REPLACEMENT AND/OR SLEEVE INSTALLATION [Group 7-8, 12, 14] 399 FIGURE 42: GROUP 9, GROUP 11, GROUP 13 - LEFT SIDE - FRONT SPAR - WIRE BUNDLES - CLAMP REPLACEMENT AND/OR SLEEVE INSTALLATION [Group 9, 11, 13] . 403 FIGURE 43: GROUP 9, GROUP 11, GROUP 13 - RIGHT SIDE - FRONT SPAR - WIRE BUNDLES - CLAMP REPLACEMENT AND/OR SLEEVE INSTALLATION [Group 9, 11, 13] . 409 FIGURE 44: GROUPS 1-6, GROUP 10 - LEFT SIDE - FRONT SPAR - WIRE BUNDLES - CLAMP REPLACEMENT AND/OR SLEEVE INSTALLATION [Group 1-6, 10]. . 414 FIGURE 45: GROUPS 1-6, GROUP 10 - RIGHT SIDE - FRONT SPAR - WIRE BUNDLES - CLAMP REPLACEMENT AND/OR SLEEVE INSTALLATION [Group 1-6, 10]. 420 FIGURE 46: ALL GROUPS - REAR SPAR, FRONT SPAR AND CENTER TANK FASTENERS - APPLICATION OF SEALANT [Group 1-14] . 425 FIGURE 47: GROUPS 1-10 LEFT SIDE - REAR SPAR - LOCATION OF FASTENERS. 427 FIGURE 48: GROUPS 1-10 RIGHT SIDE - REAR SPAR - LOCATION OF FASTENERS 431 FIGURE 49: GROUPS 11- 14 LEFT SIDE - REAR SPAR - LOCATION OF FASTENERS 435 FIGURE 50: GROUPS 11-14 - RIGHT SIDE - REAR SPAR - LOCATION OF FASTENERS 439 Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 5 of 442 ### Page 6 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT BLANK PAGE Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 6 of 442 ### Page 7 (OCR) Commercial OBOEING Airplanes 757 Service Bulletin - ALERT Number: 757-57A0064 Revision Transmittal Sheet Original Issue: July 16, 2007 Revision 1: October 05, 2009 ATA System: 5710 5720 SUBJECT: WINGS - Center and Outer Wing - Fastener Sealing and Wire Bundle Support Inspection and Modification This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2008-23-19, is related to this service bulletin. More work is necessary as shown in the original issue of this service bulletin. Operators that have done the work in accordance with the original issue must do the additional fastener sealing in accordance with Part 11 of this service bulletin. REASON FOR REVISION This revision is sent to: Add requirements to seal 20 additional fasteners in the main fuel tanks (left and right sides) for lightning strike protection. - Allow the installation of TFE-2X Teflon sleeve on the breakout wire separately from main bundle at locations where the wire break out is within 1.5 inches of the clamp. - Allow the use of Teflon tape to wrap around TFE-2X Teflon sleeve on wire bundle for smooth transition and cover any gaps at locations where the bend radius of the wire bundle is too small to allow the proper installation of Teflon sleeves. Replace BACC10JU-101 and BACC10JU-102 full cushion clamps with BACC10GU-101 and BACC10GU-102 due to availability. Clarify required length of Teflon sleeve protruding beyond the clamp at 0.5 inch minimum (both ends). - Allow the use of alternate size clamps and to note existing wire bundle may differ from those shown in this service bulletin. - Correct names of fuel tank access doors that were not named correctly. - Correct the warranty information in Industry Support Information in the Summary to match exiting warranty information in Paragraph 2.B of the service bulletin. The data given in Information Notice 757-57A0064 IN 01 and 757-57A0064 IN 02 is included in this revision. Original issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY 757-57A0064 •Copyright © Unpublished Work - See page 1 for details. 7 of 442 ### Page 8 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT These sections were changed: 1. In the Summary section, the background was revised, added reference to the AD and updated the warrant and manpower sections. 2. In Paragraph 1.C., Reason, clarified and formated reason statement to be Airworthiness Directive Friendly. 3. In Paragraph 1.D., Description, added Maintenance Zone tables. 4. In Paragraph 1.E., Compliance, changed as follows: a. Federal Aviation Administration (FAA) Airworthiness Directive AD 2008-23-19. b. Revised compliance times to within 5 years after December 30, 2008, was within 5 years after issue date on this Service Bulletin, to match effective date in Federal Aviation Administration (FAA) Airworthiness Directive AD 2008-23-19. 5. In Paragraph 1.F., Approval, added an Alternative Methods of Compliance statement. 6. In Paragraph 1.G., Manpower, changed as follows: a. Changed task hours for Figures 1 through 10, to increase hours for additional fasteners to be sealed. b. Added task hour tables for Figures 47 through 50, for groups 1 through 14. 7. In Paragraph 1.K., Publications Affected, added the Damage Tolerance statement. 8. In Paragraph 2.C.2., Parts and Material Supplied by the Operator, for all groups change as follows: a. Changed Full Cushion Clamp part number in parts tables to BACC10GU-101 and BACC10GU-102 was BACC10JU-101 and BACC10JU-102. b. Added Teflon tape and associated notes (f) and (g). 9. In Paragraph 3.A., General Information, changed as follows: a. Added note 10 to note existing fasteners that have been sealed previously are acceptable. b. Added note 11 to note quantity of fasteners shown are approximate and to seal additional fasteners as required. c. Added notes 12 and 13 to explain operator applicability of Parts 1 through 11. d. Added note 14 to allow approved wire bundle support installation deviations 10. In Paragraph 3.B., Work Instructions, Part 1, for all groups corrected access door names as follows: Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 8 of 442 ### Page 9 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT a. In steps (2) and (14) changed name of 531AB, 531BB, and 531CB to center fuel tank access door, was left main fuel tank access door. b. In steps (4) and (16) changed name of 631AB, 631BB, and 631CB to center fuel tank access door, was right main fuel tank access door. c. In steps (6) and (12) changed name of 134BZ, 134CZ and 134DZ to fuel bay baffle door, was center fuel fuel tank access door. 11. In Paragraph 3.B., Work Instructions, Part 2 through Part 10, for all groups, changed instructions; from replace Teflon tape to install TFE-2X sleeve. 12. In Paragraph 3.B., Work Instructions, added Part 11 work instructions for operators that has done the work of the original issue of this service bulletin 13. In Figures 1 through 12, changed as follows: a. Changed view B to show 21 fasteners was 22. b. Changed work step 1 to locate 21 fasteners was 22. c. Added requirements to seal additional fasteners in areas between rib numbers 14 and 15, and between rib numbers 18 and 19. 14. In Figures 3 and 4, work step 7, changed quantity to 7 was 9. 15. IN Figures 5 and 6, work step 8, changed quantity to 7 was 9. 16. In Figures 23 and 27, revised wire harness (W2506) routing to better match actual aircraft configuration. 17. In Figures 22 through 45, added notes to: a. Allow the installation of TFE-2X Teflon sleeve on the breakout wire separately from main bundle at locations where the wire break out is within 1.5 inches of the clamp D. Allow the use of Teflon tape to wrap around TFE-2X Teflon sleeve on wire bundle for smooth transition and cover any gaps at locations where the bend radius of the wire bundle is too small to allow the proper installation of Teflon sleeves 18. In Figures 26 through 29, 32, 33 and 40 through 45, added view to show 0.5 inch minimum sleeve protruding beyond ends of clamp added note to show the same. 19. In Figures 27, 28, 29, 32, 33, 40, 41, 42, 43, 44, and 45 changed quantity of Teflon Sleeve in illustration to match quantity in step table. 20. In Figures 40, 42 and 44, added note to advice operators that to remove clamps between IFSS 119.21 and IFSS 132.98 surrounding pneumatic ducts may have to be removed. 21. Added Figures 47, 48, 49 and 50 to seal an additional 20 fasteners in the main fuel tank (left and right side) for operators that have done the work of the original issues of this service bulletin. Pages with no vertical lines have no important changes Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 9 of 442 ### Page 10 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. REVISION HISTORY Original Issue: July 16, 2007 Revision 1: October 05, 2009 Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 10 of 442 ### Page 11 (OCR) Commercial CADEING Airplanes 757 Service Bulletin - ALERT Number: 757-57A0064 Summary Original Issue: July 16, 2007 Revision 1: October 05, 2009 ATA System: 57 10 5720 SUBJECT: WINGS - Center and Outer Wing - Fastener Sealing and Wire Bundle Support Inspection and Modification 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 A review by Boeing has found it possible for some fuel tank fasteners, in the event of a fault current, to become an ignition source. Sealing fuel tank fasteners, general inspection of wire support bundles, replacing clamps and installing a Teflon sleeve where required may reduce the risk of fuel tank fasteners becoming an ignition source. Replacing clamps and installing Teflon sleeve provides for additional layers of protection against hot shorts. Accomplishment of the this service bulletin will help prevent certain ignition sources within the fuel tanks. If not corrected, in the event of a fault current, ignition sources within the fuel tanks may possibly result in fire or explosion. This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88,iFuel Tank System Fault Tolerance Evaluation Requirementsi ACTION Purge the left and right main fuel tanks. Get access to the left and right main fuel tanks. Seal fasteners on the front and rear spars, left and right side. Purge the center fuel tanks. Get access to the center fuel tank. Seal fasteners on the center tank lower panel. In the left and right Equipment Cooling System (ECS) bay, do a general visual inspection of the wire bundle clamps. Along the left and right side front and rear spars, do a general visual inspection of the wire bundle clamps. If the wire bundle support installation is not as shown in this service bulletin, get access to and change the wire bundle support hardware. The airplanes are divided into 14 groups because of variations in the fasteners to be sealed and the wire bundle clamps to be inspected. EFFECTIVITY All 757-200, 757-200CB, 757-200PF., and 757-300 series airplanes. See Service Bulletin Paragraph 1.A.1 for effectivity. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 442 ### Page 12 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2008-23-19 is related to this service bulletin. See Service Bulletin Paragraph 1.E. for compliance information. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are available for 757 airplanes in warranty as of May 17, 2005. Please refer to Paragraph 2.B Industry Support Information. MANPOWER Total hours for Parts 1 through 10: Group Total Total Group Total Total Group Total Total Task Elapsed Task Elapsed Task Elapsed Hours Hours Hours Hours Hours Hours 1 642.94 128.43 6 652.94 131.67 11 659.17 133.03 643.68 130.42 7 654.53 132.21 12 658.53 132.71 646.18 127.41 8 645.39 126.93 13 653.27 127.49 4 648.44 131.68 9 646.03 127.25 14 652.63 127.17 5 646.94 128.93 10 | 643.80 126.39 Part 11: Group Task Elapsed Hours Hours 1-14 48.00 14.25 MATERIAL INFORMATION Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability. Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 12 of 442 ### Page 13 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT SEAL FASTENERS IN CENTER FUEL TANK, DO A GENERAL VISUAL INSPECTION OF THE LOWER PANEL WIRE BUNDLE SUPPORT INSTALLATION ON FRONT SPAR THE FRONT AND REAR SPAR, LEFT AND RIGHT SIDE REPLACE AS NECESSARY REAR SPAR SEAL FASTENERS ON THE FRONT AND REAR SPAR INSIDE LEFT AND RIGHT MAIN FUEL TANKS DO A GENERAL VISUAL INSPECTION OF THE WIRE BUNDLE SUPPORT INSTALLATIONS INSIDE LEFT J72723 AND RIGHT ECS BAYS. REPLACE AS NECESSARY Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 442 ### Page 14 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT BLANK PAGE Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 442 ### Page 15 (OCR) Commercial BOEING Airplanes 757 Service Bulletin - ALERT: Number: 757-57A0064 Original Issue: July 16, 2007 Revision 1: October 05, 2009 ATA System: 5710 5720 SUBJECT: WINGS - Center and Outer Wing - Fastener Sealing and Wire Bundle Support Inspection and Modification 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 D624N001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. GROUP CONFIGURATION DESCRIPTION 757-200 and 757-200CB series airplanes that require 688 fasteners to be sealed in the center and main fuel tanks, and 94 clamps to be inspected (general visual inspection) on the left and right main spars and ECS bays. 2 757-200PF series airplanes that require 690 fasteners to be sealed in the center and main fuel tanks, and 94 clamps to be inspected (general visual inspection) on the left and right main spars and ECS bays. 3 757-200 series airplanes that require 692 fasteners to be sealed in the center and main fuel tanks, and 94 clamps to be inspected (general visual inspection) on the left and right main spars and ECS bays. Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 15 of 442 ### Page 16 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT GROUP CONFIGURATION DESCRIPTION 4 757-200PF series airplanes that require 694 fasteners to be sealed in the center and main fuel tanks, and 94 clamps to be inspected (general visual inspection) on the left and right main spars and ECS 5 757-200 series airplanes that require 696 fasteners to be sealed in the center and main fuel tanks, and 94 clamps to be inspected (general visual inspection) on the left and right main spars and ECS bays. 6 757-200 series airplanes that require 706 fasteners to be sealed in the center and main fuel tanks, and 94 clamps to be inspected (general visual inspection) on the left and right main spars and ECS bays. 7 757-200 series airplanes that require 706 fasteners to be sealed in the center and main fuel tanks, and 90 clamps to be inspected (general visual inspection) on the left and right main spars and ECS bays. 8 757-300 series airplanes that require 692 fasteners to be sealed in the center and main fuel tanks, and 86 clamps to be inspected (general visual inspection) on the left and right main spars and ECS bays. 9 757-300 series airplanes that require 692 fasteners to be sealed in the center and main fuel tanks, and 88 clamps to be inspected (general visual inspection) on the left and right main spars and ECS 10 757-300 series airplanes that require 692 fasteners to be sealed in the center and main fuel tanks, and 90 clamps to be inspected (general visual inspection) on the left and right main spars and ECS bays. 11 757-200 series airplanes that require 710 fasteners to be sealed in the center and main fuel tanks, and 92 clamps to be inspected (general visual inspection) on the left and right main spars and ECS Days. 12 757-200 series airplanes that require 710 fasteners to be sealed in the center and main fuel tanks, and 90 clamps to be inspected (general visual inspection) on the left and right main spars and ECS 13 757-300 series airplanes that require 690 fasteners to be sealed in the center and main fuel tanks, and 88 clamps to be inspected (general visual inspection) on the left and right main spars and ECS Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details 16 of 442 ### Page 17 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT GROUP CONFIGURATION IDESCRIPTION 14 757-300 series airplanes that require 690 fasteners to be sealed in the center and main fuel tanks, and 86 clamps to be inspected (general visual inspection) on the left and right main spars and ECS bays. Airplane Models: 757-200, 757-200CB, 757-200PF, 757-300 Variable Number Group NA001 - NẠ028 NA191 - NA199 NA201 - NA236 NA237 - NA239 3 NA301 - NA305 : 1 NA341 - NA352 NA391 - NA399 NA401 - NA408 NA441 - NA447 NA501 - NA584 NA585 - NA586 3 NB001 - NB004 NB021 - NB023 NB036 - NB041 NB051 - NB053 NB061 - NB073 NB079 NB131 - NB147 NB148 NB161 - NB162 NB166 - NB167 1 NB168 3 NB201 - NB204 : 1 NB221 - NB228 NB230 Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 442 ### Page 18 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Variable Number Group NB236 3 NB239 1 NB261 - NB264 1 NB265 - NB267 3 NB291 - NB292 1 NB293 - NB299 3 NB301 - NB302 NB311 - NB312 1 NB321 - NB329 1 NB330 - NB331 3 NB421 - NB430 NB431 - NB438 3 NB446 3 NB451 - NB452 1 NB453 - NB454 3 NB501 - NB507 NB508 - NB523 NB561 3 NB571 NB581 - NB583 NC001 - NC033 1 NC041 - NC042 1 NC051 - NC052 1 NC056 - NC057 1 NC058 - NC062 3 NC066 1 NC067 - NC084 3 NC091 - NC094 NC151 3 NC161 3 NC901 - NC930 2 NC931 3 NC932 - NC933 4 Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details 18 of 442 ### Page 19 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Variable Number Group NC934 : 3 NC935 - NC950 NC951 2 NC971 2 NC972 NC973 - NC974 2 ND001 - ND007 ND011 - ND059 1 ND111 - ND113 ND161 - ND182 ND183 - ND199 ND201 - ND203 ND221 :1 ND222 - ND225 • 3 ND241 ND242 - ND248 ND301 - ND322 3 ND401 3 ND891 ND895 NE001 - NE003 1 NE004 - NE008 NE011 - NE082 NE083 - NE088 NE091 - NE094 3 NE141 - NE150 NE161 - NE176 : 1 NE177 3 NE201 - NE204 1 NE301 - NE302 NE311 - NE325 :3 NJ001 - NJ004 . 12 NJ031 - NJ032 12 Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 19 of 442 ### Page 20 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Variable Number Group NJ551 - NJ555 11 NL001 - NL002 8 NL006 - NL011 8 NL012 - NL015 10 NL016 - NL017 13 NL101 - NL104 8 NL105 - NL109 14 NL141 8 NL601 - NL603 9 NL604 - NL616 13 NN001 - NN002 3 NN051 - NN052 5 NP901 - NP904 3 NS601 - NS616 4 NT001 - NT009 4 NT201 - NT202 3 NT231 - NT234 3 NT237 - NT240 3 NT242 3 NT245 - NT248 3 NT281 - NT289 3 NT341 - NT345 3 NT346 5 NT347 6 NT351 - NT360 3 NT371 - NT373 NT375 - NT379 3 NT381 - NT385 3 NT386 6 NT401 - NT409 3 NT411 - NT412 3 NT426 - NT427 3 NT431 - NT432 3 Original Issue: July 16, 2007 Revision 1: October 05, 2009 190029-29 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. ZE 10 0Z ### Page 21 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Variable Number Group NT436 - NT438 NT441 - NT442 NT446 3 NT701 - NT769 NT791 - NT796 NT861 - NT862 3 NT881 - NT885 NT901 - NT916 NT971 - NT972 NT973 - NT984 5 NT985 NU031 - NU034 3 NU035 5 NU036 - NU038 7 NU701 - NU705 NU721 - NU728 NU731 - NU732 8 2. Spares Affected None. B. Concurrent Requirements None. C. Reason A review by Boeing has found it possible for some fuel tank fasteners, in the event of a fault current, to become an ignition source. Sealing fuel tank fasteners, general inspection of wire support bundles, replacing clamps and installing a Teflon sleeve where required may reduce the risk of fuel tank fasteners becoming an ignition source. Replacing clamps and installing Teflon sleeve provides for additional layers of protection against hot shorts. Accomplishment of the this service bulletin will help prevent certain ignition sources within the fuel tanks, If not corrected, in the event of a fault current, ignition sources within the fuel tanks may possibly result in fire or explosion. This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements" Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details 21 of 442 ### Page 22 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT D. Description Purge the left and right main fuel tanks. Get access to the left and right main fuel tanks. Seal fasteners on the front and rear spars, left and right side. Purge the center fuel tanks. Get access to the center fuel tank. Seal fasteners on the center tank lower panel. In the left and right Equipment Cooling System (ECS) bay, do a general visual inspection of the wire bundle clamps. Along the left and right side front and rear spars, do a general visual inspection of the wire bundle clamps. If the wire bundle support installation is not as shown in this service bulletin, get access to and change the wire bundle support hardware. The airplanes are divided into 14 groups because of variations in the fasteners to be sealed The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones Model Zone 757-200, 757-200CB, 757- 531, 541, 542, 561, 631, 641, 642, 661 200PF Group 2, 4: Affected Maintenance Zones Model Zone 757-200PF 531, 541, 542, 561, 631, 641, 642, 661 Group 3: Affected Maintenance Zones Model Zone 757-200, 757-200PF 531, 541, 542, 561, 631, 641, 642, 661 Group 5-7, 11-12: Affected Maintenance Zones Model Zone 757-200 531, 541, 542, 561, 631, 641, 642, 661 Group 8-10, 13-14: Affected Maintenance Zones Model Zone 757-300 531, 541, 542, 561, 631, 641, 642, 661 Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 442 ### Page 23 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT E. Compliance Federal Aviation Administration (FAA) Airworthiness Directive AD 2008-23-19 is related to this service bulletin. Group 1-14: Table 1. Fastener Sealing, Wire Bundle Support General Visual Inspection, Clamp Replacement and Teflon Tape Installation Condition Action Compliance Time All Airplanes Seal the fasteners inside the center and Within 5 years after main fuel tanks as given in Accomplish- December 30, 2008. ment Instructions Paragraph 3.B.1., Part All Airplanes Do a General Visual Inspection of the wire Within 5 years after bundle support installation in the ECS bay December 30, 2008. as given in Accomplishment Instructions Paragraph 3.B.2., Part 2. Incorrect clamps found in the Replace the clamps as given in Accom- Within 5 years after LEFT ECS bay. plishment Instructions Paragraph 3.B.3., December 30, 2008. Part 3. Teflon sleeving not installed Install the Teflon sleeving as given in Ac- Within 5 years after in the LEFT ECS bay. complishment Instructions Paragraph December 30, 2008. 3.B.3., Part 3. Incorrect clamps found in the Replace the clamps as given in Accom- Within 5 years after RIGHT ECS bay. plishment Instructions Paragraph 3.B.4., December 30, 2008. Part 4. Teflon sleeving not installed Install the Teflon sleeving as given in Ac- Within 5 years after in the RIGHT ECS bay. complishment Instructions Paragraph December 30, 2008. 3.B.4., Part 4. All Airplanes Do a General Visual Inspection of the wire Within 5 years after bundle support installation on the Rear December 30, 2008. Spar as given in Accomplishment Instruc- tions Paragraph 3.B.5., Part 5. Incorrect clamps found on Replace the clamps as given in Accom- Within 5 years after the LEFT side Rear Spar. plishment Instructions Paragraph 3.B.6., December 30, 2008. Part 6. Teflon sleeving not installed Install the Teflon sleeving as given in Ac- Within 5 years after on the LEFT side Rear Spar. complishment Instructions Paragraph December 30, 2008.. 3.B.6., Part 6. Incorrect clamps found on Replace the clamps as given in Accom- Within 5 years after the RIGHT side Rear Spar. plishment Instructions Paragraph 3.B.7., December 30, 2008. Part 7. Teflon sleeving not installed Install the Teflon sleeving as given in Ac- Within 5 years after on the RIGHT side Rear complishment Instructions Paragraph December 30, 2008.. Spar. 3.B.7., Part 7: Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 23 of 442 ### Page 24 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 1-14: Table 1. Fastener Sealing, Wire Bundle Support General Visual Inspection, Clamp Replacement and Teflon Tape Installation Condition Action Compliance Time All Airplanes Do a General Visual Inspection of the wire Within 5 years after bundle support installation on the Front December 30, 2008. Spar as given in Accomplishment Instruc- tions Paragraph 3.B.8., Part 8. incorrect clamps found on Replace the clamps as given in Accom- Within 5 years after the LEFT side Front Spar. plishment Instructions Paragraph 3.B.9., December 30, 2008. Part 9. Teflon sleeving not installed Install the Teflon sleeving as given in Ac- Within 5 years after on the LEFT side Front Spar. complishment Instructions Paragraph December 30, 2008.. 3.B.9., Part 9. Incorrect clamps found on Replace the clamps as given in Accom- Within 5 years after the RIGHT side Front Spar. plishment Instructions Paragraph 3.B.10., December 30, 2008. Part 10. Teflon sleeving not installed Install the Teflon sleeving as given in Ac- Within 5 years after on the RIGHT side Front complishment Instructions Paragraph December 30, 2008. Spar. 3.B.10., Part 10. Airplanes that have done the Seal the fasteners inside the main fuel Within 5 years after work of the original issue of tanks as given in Accomplishment Instruc- December 30, 2008. service bulletin 757- tions Paragraph 3.B.1., Part 11 57A0064. 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 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. This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (f) of AD 2008-23-19. All provisions of AD 2008-23-19 that are not specifically referenced in the above statement remain fully applicable and must be complied with. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 442 ### Page 25 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT G. Manpower The table below shows an estimate of the task-hours necessary to do this change for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task-hour data if necessary. The estimate does not include lost time. These are some examples of lost time: Time to adjust to the workplace Time to schedule the work Time to examine the work Time to cure the materials Time to make the parts Time to find the tools. Group 1: Part 1: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Preparation 2 24.0 12.0 Open Access 4 18.5 4.62 Figure 1 8 114.00 (a) 14.25 Figure 2 114.00 (a) 14.25 Figure 13 8 129.75 (a) 14.22 Figure 14 8 123.75 (a) 15.47 Figure 19 2 51.00 (a) 23.50 Close Access 4 23.5 5.88 TOTAL FOR EACH AIRPLANE 598.50 104.19 (a) Includes time to apply but not cure BMS 5-45 sealant. Cure time can change because of heat and humidity. Group 1, 4-7, 11-12: Part 2: ECS Bay - Number of Per- Task-Hours Elapsed Hours Clamp Inspection sons Open Access .30 .30 Figure 22 0.08 0.08 Figure 23 0.08 0.08 Close Access 0.30 0.30 TOTAL FOR EACH AIRPLANE 0.76 0.76 Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 25 of 442 ### Page 26 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 1-7, 11-12: Part 3: Left Side ECS Number of Per- Task-Hours Elapsed Hours Bay - Clamp Replace- ment Open Access 2 1.5 0.75 Figure 26 2 5.12 2.56 Close Access 2 1.75 0.87 TOTAL FOR EACH AIRPLANE 8.37 4.18 Group 1, 4-7, 11-12: Part 4: Right Side Number of Per- Task-Hours Elapsed Hours ECS Bay - Clamp sons Replacement Open Access 2 1.50 0.75 Figure 27 2 3.84 1.92 Close Access 2 1.75 0.87 TOTAL FOR EACH AIRPLANE 7.09 3.54 Group 1, 4-7, 11-12: Part 5: Rear Spar - Number of Per- Task-Hours Elapsed Hours Clamp Inspection sons Open Access 2 0.75 0.37 Figure 30 0.08 0.08 Figure 31 1 0.08 0.08 Close Access 2 0.75 0.75 TOTAL FOR EACH AIRPLANE 1.66 1.66 Group 1-14: Part 6: Left Side Rear Number of Per- Task-Hours Elapsed Hours Spar - Clamp Replace- sons ment Figure 32 5.12 2.56 Close Access 0.50 0.50 TOTAL FOR EACH AIRPLANE 5.62 3.06 Group 1-14: Part 7: Right Side Number of Per- Task-Hours Elapsed Hours Rear Spar - Clamp sons Replacement Figure 33 2 5.12 2.56 Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 26 of 442 ### Page 27 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 1-14: Part 7: Right Side Number of Per- Task-Hours Elapsed Hours Rear Spar - Clamp sons Replacement Close Access 0.50 0.50 TOTAL FOR EACH AIRPLANE 5.62 3.06 Group 1-6, 10: Part 8: Front Spar - Number of Per- Task-Hours Elapsed Hours Clamp Inspection sons Open Access 2 2.50 1.25 Figure 38 0.08 0.08 Figure 39 1 0.08 0.08 Close Access 2.75 1.37 TOTAL FOR EACH AIRPLANE 5.41 2.78 Group 1-6, 10: Part 9: Left Side Front Number of Per- Task-Hours Elapsed Hours Spar - Clamp Replace- sons ment Figure 44 2 3.50 1.75 Close Access 0.50 0.50 TOTAL FOR EACH AIRPLANE 4.0 2.25 Group 1-6, 10: Part 10: Right Side Number of Per- Task-Hours Elapsed Hours Front Spar - Clamp sons Replacement Figure 45 2 4.16 2.08 Close Access 2 1:75 .87 TOTAL FOR EACH AIRPLANE 5.91 2.95 Group 2: Part 1: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Preparation 2 24.0 12.0 Open Access 4 18.5 4.62 Figure 1 8 114.00 (a) 14.25 Figure 2 8 114.00 (a) 14.25 Figure 13 8 129.75 (a) 16.22 Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 442 ### Page 28 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 2: Part 1: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Figure 14 8 123.75 (a) 15.47 Figure 20 52.5 (a) 26.25 Close Access 4 23.5 6.12 TOTAL FOR EACH AIRPLANE 600.00 106.94 (a) Includes time to apply but not cure BMS 5-45 sealant. Cure time can change because of heat and humidity. Group 2: Part 4: Right Side Number of Per- Task-Hours Elapsed Hours ECS Bay - Clamp sons Replacement Open Access 2 1.50 0.75 Figure 27 2 3.84 1.92 Close Access 2 1.75 0.87 TOTAL FOR EACH AIRPLANE 7.09 3.54 Group 2: Part 5: Rear Spar - Number of Per- Task-Hours Elapsed Hours Clamp Inspection sons Open Access 2 0.75 0.37 Figure 30 1 0.08 0.08 Figure 31 1 0.08 0.08 Close Access 2 0.75 0.75 TOTAL FOR EACH AIRPLANE 1.66 1.66 Group 3: Part 1: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Preparation 2 24.0 12.0 Open Access 4 18.5 4.62 Figure 3 8 116.00 (a) 14.50 Figure 4 8 116.00 (a) 14.50 Figure 13 8 129.75 (a) 16.22 Figure 14 8 123.75 (a) 15.47 Figure 19 2 51.0 (a) 25.5 Close Access 2 23.5 11.75 Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 28 of 442 ### Page 29 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 3: Part 1: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons TOTAL FOR EACH AIRPLANE 602.50 104.69 (a) Includes time to apply but not cure BMS 5-45 sealant. Cure time can change because of heat and humidity. Group 3: Part 4: Right Side Number of Per- Task-Hours Elapsed Hours ECS Bay - Clamp sons Replacement Open Access 2 1.50 0.75 Figure 27 2 3.84 1.92 Close Access 2 1.75 0.87 TOTAL FOR EACH AIRPLANE 7.09 3.54 Group 3: Part 5: Rear Spar - Number of Per- Task-Hours Elapsed Hours Clamp Inspection sons Open Access 2 0.75 0.37 Figure 30 0.08 0.08 Figure 31 0.08 0.08 Close Access 2 0.75 0.37 TOTAL FOR EACH AIRPLANE 1.66 0.90 Group 4: Part 1 Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Preparation 2 24.0 12.0 Open Access 4 18.5 4.62 Figure 3 8 116.00 (a) 14.50 Figure 4 8 116.00 (a) 14.50 Figure 13 8 129.75 (a) 14.22 Figure 14 8 123.75 (a) 15.47 Figure 20 2 52.5 (a) 26.25 Close Access 2 23.5 11.75 TOTAL FOR EACH AIRPLANE 604.00 107.44 (a) Includes time to apply but not cure BMS 5-45 sealant. Cure time can change because of heat and humidity. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 442 ### Page 30 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 5: Part 1: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Preparation 2 24.0 12.0 Open Access 4 18.5 4.62 Figure 5 8 116.00 (a) 14.50 Figure 6 8 116.00 (a) 14.50 Figure 13 8 129.75 (a) 16.22 Figure 14 8 123.75 (a) 15.47 Figure 19 2 51.0 (a) 23.5 Close Access 2 23.5 11.75 TOTAL FOR EACH AIRPLANE 602.50 104.69 (a) Includes time to apply but not cure BMS 5-45 sealant. Cure time can change because of heat and humidity. Group 6-7: Part 1: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Preparation 2 24.0 12.0 Open Access 4 18.5 4.62 Figure 5 8 116.00 (a) 14.50 Figure 6 8 116.00 (a) 14.50 Figure 15 8 133.5 (a) 16.68 Figure 16 8 126.0 (a) 15.75 Figure 19 2 51.0 (a) 25.5 Close Access 2 23.5 11.75 TOTAL FOR EACH AIRPLANE 608.50 107.43 (a) Includes time to apply but not cure BMS 5-45 sealant. Cure time can change because of heat and humidity. Group 7-8, 12, 14: Part 8: Front Spar - Number of Per- Task-Hours Elapsed Hours Clamp Inspection sons Open Access 2 2.5 1.25 Figure 34 0.08 0.08 Figure 35 1 0.08 0.08 Close Access 2 2.75 1.37 TOTAL FOR EACH AIRPLANE 5.41 2.78 Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 30 of 442 ### Page 31 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 7-8, 12, 14: Part 9: Left Side Front Number of Per- Task-Hours Elapsed Hours Spar - Clamp Replace- sons ment Figure 40 2 4.50 2.25 Close Access 2 1.75 0.87 TOTAL FOR EACH AIRPLANE 6.25 3.12 Group 7-8, 12, 14: Part 10: Right Side Number of Per- Task-Hours Elapsed Hours Front Spar - Clamp sons Replacement Figure 41 2 3.50 1.75 Close Access 2 1:75 0.87 TOTAL FOR EACH AIRPLANE 5.25 2.62 Group 8-10: Part 1: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Preparation 2 24.0 12.0 Open Access 4 18.5 4.62 Figure 7 8 120.00 (a) 15.00 Figure 8 8 120.00 (a) 15.00 Figure 17 8 132.0 (a) 16.5 Figure 18 8 126.0 (a) 15.75 Figure 21 2 •36.0 (a) 18.0 Close Access 2 23.5 11.75 TOTAL FOR EACH AIRPLANE 600.00 102.75 (a) Includes time to apply but not cure BMS 5-45 sealant. Cure time can change because of heat and humidity. Group 8-10, 13-14: Part 2: ECS Bay - Number of Per- Task-Hours Elapsed Hours Clamp Inspection sons Open Access 0.30 0.30 Figure 24 0.08 0.08 Figure 25 1 0.08 0.08 Close Access 1 0.30 0.30 TOTAL FOR EACH AIRPLANE 0.76 0.76 Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 442 ### Page 32 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 8-10, 13-14: Part 3: Left Side ECS Number of Per- Task-Hours Elapsed Hours Bay - Clamp Replace- ment Open Access 2 1.50 0.75 Figure 28 2 4.16 2.08 Close Access 2 1.75 0.87 TOTAL FOR EACH AIRPLANE 7.41 3.70 Group 8-10, 13-14: Part 4: Right Side Number of Per- Task-Hours Elapsed Hours ECS Bay - Clamp sons Replacement Open Access 1.50 0.75 Figure 29 2 5.12 2.56 Close Access 2 1.75 0.87 TOTAL FOR EACH AIRPLANE 7.41 4.18 Group 8-10, 13-14: Part 5: Rear Spar - Number of Per- Task-Hours Elapsed Hours Clamp Inspection sons Open Access 2 0.75 0.37 Figure 30 1 0.08 0.08 Figure 31 1 0.08 0.08 Close Access 2 0.75 0.37 TOTAL FOR EACH AIRPLANE 1.66 0.90 Group 9, 11, 13: Part 8: Front Spar - Number of Per- Task-Hours Elapsed Hours Clamp Inspection sons Open Access 2 2.5 1.25 Figure 36 0.08 0.08 Figure 37 1 0.08 0.08 Close Access 2 2.75 1.37 TOTAL FOR EACH AIRPLANE 5.41 2.78 Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 Copyright © Unpublished Work - See page 1 for details. BOEING PROPRIETARY - 32 of 442 ### Page 33 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 9, 11, 13: Part 9: Left Side Front Number of Per- Task-Hours Elapsed Hours Spar - Clamp Replace- sons ment Figure 42 2 4.8 2.40 Close Access 2 1,75 0.87 TOTAL FOR EACH AIRPLANE 6.55 3.27 Group 9, 11, 13: Part 10: Right Side Number of Per- Task-Hours Elapsed Hours Front Spar - Clamp sons Replacement Figure 43 2 3.84 1.92 Close Access 2 1.75 0.87 TOTAL FOR EACH AIRPLANE 5.59 2.79 Group 11-12: Part 1: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Preparation 2 24.0 12.0 Open Access 4 18.5 4.62 Figure 9 8 118.00 (a) 14.75 Figure 10 8 118.00 (a) 14.75 Figure 15 133.5 (a) 16.68 Figure 16 8 126.0 (a) 15.75 Figure 19 2 51.0 (a) 25.5 Close Access 2 23.5 11.75 TOTAL FOR EACH AIRPLANE 612.50 107.93 (a) Includes time to apply but not cure BMS 5-45 sealant. Cure time can change because of heat and humidity. Group 13-14: Part 1: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Preparation 2 24.0 12.0 Open Access 4 18.5 4.62 Figure 11 8 124.00 (a) 15.50 Figure 12 8 124.00 (a) 15.50 Figure 17 8 132.0 (a). 16.5 Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 33 of 442 ### Page 34 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 13-14: Part 1: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Figure 18 8 126.0 (a) 15.75 Figure 21 2 36.0 (a) 18.0 Close Access 2 23.5 11.75 TOTAL FOR EACH AIRPLANE 608.00 103.75 (a) Includes time to apply but not cure BMS 5-45 sealant. Cure time can change because of heat and humidity. Part 11 is only applicable for those airplanes that have had the work done in accordance with the original issue of this service bulletin. Group 1-10: Part 11: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons * Preparation 4 9.0 2.25 Open Access 2.0 1.00 Figure 47 4 15.00 (a) 3.75 Figure 48 2 15.00 (a) 3.75 Close Access 2 7.00 3.50 TOTAL FOR EACH AIRPLANE 48.00 14.25 (a) Includes time to apply but not cure BMS 5-45 sealant. Cure time can change because of heat and humidity. Group 11-14: Part 11: Fastener Number of Per- Task-Hours Elapsed Hours Sealing sons Preparation 4 9.00 2.25 Open Access 2 2.00 1.00 Figure 49 4 15.00 (a) 3.75 Figure 50 4 15.00 (a) 3.75 Close Access 2 7.00 3.50 TOTAL FOR EACH AIRPLANE 48.00 14.25 (a) Includes time to apply but not cure BMS 5-45 sealant. Cure time can change because of heat and humidity. Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 34 of 442 ### Page 35 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT H. Weight and Balance Changes Airplane Change in Weight Change in Moment (Pounds) (Pound-Inches) 757-200/-200CB/-200PF/300 + 8.0 8800 Electrical Load Data Not changed. J. References 1. Existing Data: a. 757 Aircraft Maintenance Manual (AMM) 06-41-00, 06-44-00, 21-51-02, 27-61-00, 27-81-00, 27-81-07, 28-11-00, 28-11-01, 28-11-02, 28-11-07 b. 757-200/-200CB/-200PF/-300 Structural Repair Manual Chapter 51. c. Boeing Drawing 65-88700. d. Standard Overhaul Practices Manual (SOPM) 20-30-93. e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: Drawing Number Title 288N4473 Wire Bundle Instl. - Left Lower Stub, Keel Beam and Body STA 900 - 1040 288N4474 Wire Bundle Instl. - Right Lower Stub, Keel Beam and Body STA 900 - 1040 288N1401 Wire Bundle Instl. - Left Leading Edge and Front Spar BBL 70.5 - ISS 285.18 288N1402 Wire Bundle Instl. - Right Leading Edge and Front Spar BBL 70.5 - ISS 285.18 288N1317 Wire Bundle Instl. - Left Rear Spar IRSS 325 - WS 836.55 288N1318 Wire Bundle Instl. - Right Rear Spar IRSS 325 - WS 836.55 111N4001 Panel Instl. - Lower, Wing Center Section 112N1002 Spar Assy - Rear, Sect 12, Wing 113N1400 Support Instl. - Spoiler No. 1 thru 5, Wing Trailing Edge Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 442 ### Page 36 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Drawing Number Title 113N1305 Fitting Instl., Rear Spar Flap Track Support, W.S. 438.70 and W.S. 442.30 112N2002 Spar InstI - Front, Sect 12, Wing 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 affects FCS but no new DTIs are necessary. L. Interchangeability and Intermixability of Parts Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability information. Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 36 of 442 ### Page 37 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT 2. MATERIAL INFORMATION A. Material - Price and Availability The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary For Each Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and supply data. B. Industry Support Information Boeing warranty remedies are available for 757 airplanes in warranty as of May 17, 2005. For man-hour and material reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. C. Parts Necessary For Each Airplane 1. Kits/Parts: None. 2. Parts and Materials Supplied by the Operator: Group 1-6: Part Number / Specification QTY Name Notes BACC10GU-101 2 Full Cushion Clamp (a) (c) BACC10GU-102 5 BACC10JU-103 14 (a) (c) (d) BACC10JU-105 14 BACC10JU-106 24 BACC10JU-109 8 BACC10JU-111 4 BACC10JU-112 23 P-421 Teflon Tape, 1/2 inch wide (f) (g) or Mil--23594, Type, Class 4 TFE-2X, 3/4 Inch Diameter, Standard Wall 24 Feet Teflon Sleeving (b) (e) Thickness, Natural BMS 13-54, Type III, Class 1, Finish C, Black 240 Feet Lacing Tape (a) (b) BMS 5-45, Class A-2, Grade 1 or Grade 2 70 oz Sealant (a) BMS 5-45, Class B-2 70 oz Sealant BMS 15-5, Class A, Wiper, Absorbent, Process 60 Wiper Cleaning BMS 11-7 25 oz Solvent Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 442 ### Page 38 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 1-6: Part Number / Specification QTY Name Notes (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) The quantity shown is the maximum amount that may be necessary if the verification shows the clamps to be missing. (c) The clamp sizes shown are approximate and to be determined on installation. The total quantity is the maximum that may be necessary if the verification shows the clamps to be missing. (d) At locations where the wire bundle is too large or too small to use BACC10JU-() clamps, it is per- mitted to use BACC10GU-() clamps. (e) May be purchased from: Zeus Industrial Products, (V6Y609), 501 Blvd. S.E., P.O. Box 2167, Or- angeburg, South Carolina 29116. May substitute with any equivalent Teflon Tape. Quantity is as required. (9) • May be purchased from: Permacel Corporation (V99742) - US Highway 1, P.O. Box 671 North Brunswick, New Jersey 08902. Group 7: Part Number / Specification QTY Name Notes BACC10GU-101 2 Full Cushion Clamp (a) (c) BACC10GU-102 5 BACC10JU-103 11 (a) (c) (d) BACC10JU-105 8 BACC10JU-106 24 BACC10JU-109 8 BACC10JU-111 4 BACC10JU-112 25 P-421 Teflon Tape (f) (g) or Mil-I-23594, Type 1, Class 4 TFE-2X, 3/4 Inch Diameter, Standard Wall 24 Feet Teflon Sleeving (b) (e) Thickness, Natural BMS 13-54, Type III, Class 1, Finish C, Black 240 Feet Lacing Tape (a) (b) BMS 5-45, Class A-2, Grade 1 or Grade 2 70 oz Sealant (a) BMS 5-45, Class B-2 70 oz Sealant BMS 15-5, Class A, Wiper, Absorbent, Process Wiper Cleaning BMS 11-7 25 oz Solvent (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 442 ### Page 39 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 7: Part Number / Specification QTY Name Notes (b) The quantity shown is the maximum amount that may be necessary if the verification shows the clamps to be missing. (c) The clamp sizes shown are approximate and to be determined on installation. The total quantity is the maximum that may be necessary if the verification shows the clamps to be missing. (d) At locations where the wire bundle is too large or too small to use BACC10JU-() clamps, it is per- mitted to use BACC 10GU-() clamps. (e) May be purchased from: Zeus Industrial Products, (V6Y609), 501 Blvd. S.E., P.O. Box 2167, Or- angeburg, South Carolina 29116. May substitute with any equivalent Teflon Tape. Quantity is as required (g) May be purchased from: Permacel Corporation (V99742) - US Highway 1, P.O. Box 671 North Brunswick, New Jersey 08902. Group 8: Part Number / Specification QTY Name Notes BACC10GU-101 2 Full Cushion Clamp (a) (c) BACC10GU-102 5 BACC10JU-103 12 (a) (c) (d) BACC10JU-105 6 BACC10JU-106 24 BACC10JU-109 8 BACC10JU-111 4 BACC 10JU-112 25 P-421 Teflon Tape (f) (g) or Mil--23594, Type I, Class 4 TFE-2X, 3/4 Inch Diameter, Standard Wall 24 Feet Teflon Sleeving (b) (e) Thickness, Natural BMS 13-54, Type III, Class 1, Finish C, Black 240 Feet Lacing Tape (a) (b) BMS 5-45, Class A-2, Grade 1 or Grade 2 70 oz Sealant (a) BMS 5-45, Class B-2 70 oz Sealant BMS 15-5, Class A, Wiper, Absorbent, Process 60 Wiper Cleaning BMS 11-7 25 oz Solvent (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) The quantity shown is the maximum amount that may be necessary if the verification shows the clamps to be missing. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 442 ### Page 40 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 8: Part Number / Specification QTY Name Notes (c) The clamp sizes shown are approximate and to be determined on installation. The total quantity is the maximum that may be necessary if the verification shows the clamps to be missing. (d) At locations where the wire bundle is too large or too small to use BACC10JU-() clamps, it is per- mitted to use BACC10GU-() clamps. (e) May be purchased from:Zeus Industrial Products, (V6Y609), 501 Blvd. S.E., P.O. Box 2167, Or- angeburg, South Carolina 29116. (f) May substitute with any equivalent Teflon Tape. Quantity is as required. (g) May be purchased from: Permacel Corporation (V99742) - US Highway 1, P.O. Box 671 North Brunswick, New Jersey 08902. Group 9: Part Number / Specification QTY Name Notes BACC10GU-101 2 Full Cushion Clamp (a) (c) BACC10GU-102 5 BACC10JU-103 12 (a) (c) (d) BACC10JU-105 9 BACC10JU-106 24 BACC10JU-109 8 BACC10JU-111 6 BACC10JU-112 23 P-421 Teflon Tape (1) (g) or Mil-I-23594, Type I, Class 4 TFE-2X, 3/4 Inch Diameter, Standard Wall 24 Feet Teflon Sleeving (b) (e) Thickness, Natural BMS 13-54, Type III, Class 1, Finish C, Black 240 Feet Lacing Tape (a) (b) BMS 5-45, Class A-2, Grade 1 or Grade 2 70 oz Sealant (a) BMS 5-45, Class B-2 70 oz Sealant BMS 15-5, Class A, Wiper, Absorbent, Process 60 Wiper Cleaning BMS 11-7 25 oz Solvent (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) The quantity shown is the maximum amount that may be necessary if the verification shows the clamps to be missing. (c) The clamp sizes shown are approximate and to be determined on installation. The total quantity is the maximum that may be necessary if the verification shows the clamps to be missing. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 442 ### Page 41 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 9: Part Number / Specification QTY Name Notes (d) At locations where the wire bundle is too large or too small to use BACC10JU-() clamps, it is per- mitted to use BACC10GU-() clamps. (e) May be purchased from: Zeus Industrial Products, (V6Y609), 501 Blvd. S.E., P.O. Box 2167, Or- angeburg, South Carolina 29116. (f) May substitute with any equivalent Teflon Tape. Quantity is as required. (g) May be purchased from: Permace, Corporation (V99742) - US Highway 1, P.O. Box 671 North Brunswick, New Jersey 08902. Group 10: Part Number / Specification QTY Name Notes BACC10GU-101 2 Full Cushion Clamp (a) (c) BACC 10GU-102 4 BACC10JU-103 12 (a) (c) (d) BACC 10JU-105 12 BACC10JU-106 24 BACC 10JU-109 8 BACC10JU-111 4 BACC10JU-112 23 P-421 Teflon Tape (f) (g) or Mil-1-23594, Type I, Class 4 TFE-2X, 3/4 Inch Diameter, Standard Wall 24 Feet • Teflon Sleeving (b) (e) Thickness, Natural BMS 13-54, Type III, Class 1, Finish C, Black 240 Feet Lacing Tape (a) (b) BMS 5-45, Class A-2, Grade 1 or Grade 2 70 oz Sealant (a) BMS 5-45, Class B-2 70 oz Sealant BMS 15-5, Class A, Wiper, Absorbent, Process 60 Wiper Cleaning BMS 11-7 25 oz Solvent (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) The quantity shown is the maximum amount that may be necessary if the verification shows the clamps to be missing. (c) The clamp sizes shown are approximate and to be determined on installation. The total quantity is the maximum that may be necessary if the verification shows the clamps to be missing. (d) At locations where the wire bundle is too large or too small to use BACC10JU-() clamps, it is per- mitted to use BACC 10GU-() clamps Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY . Copyright © Unpublished Work - See page 1 for details. 41 of 442 ### Page 42 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 10: Part Number / Specification | QTY Name Notes (e) May be purchased from: Zeus Industrial Products, (V6Y609), 501 Blvd. S.E., P.O. Box 2167, Or- angeburg, South Carolina 29116. (T) May substitute with any equivalent Teflon Tape. Quantity is as required. (g) May be purchased from: Permacel Corporation (V99742) - US Highway 1, P.O. Box 671 North Brunswick, New Jersey 08902. Group 11: Part Number / Specification QTY Name Notes BACC10GU-101 2 Full Cushion Clamp (a) (c) BACC10GU-102 5 BACC10JU-103 14 (a) (c) (d) BACC10JU-105 8 BACC10JU-106 24 BACC10JU-109 18 BACC10JU-111 BACC10JU-112 13 P-421 Teflon Tape (f) (g) or Mil-I-23594, Type I, Class 4 TFE-2X, 3/4 Inch Diameter, Standard Wall 24 Feet Teflon Sleeving (b) (e) Thickness, Natural BMS 13-54, Type III, Class 1, Finish C, Black 240 Feet Lacing Tape (a) (b) BMS 5-45, Class A-2, Grade 1 or Grade 2 70 oz Sealant (a) BMS 5-45, Class B-2 70 oz Sealant BMS 15-5, Class A, Wiper, Absorbent, Process 60 Wiper Cleaning BMS 11-7 25 oz Solvent (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) The quantity shown is the maximum amount that may be necessary if the verification shows the clamps to be missing. (c) The clamp sizes shown are approximate and to be determined on installation. The total quantity is the maximum that may be necessary if the verification shows the clamps to be missing. (d) At locations where the wire bundle is too large or too small to use BACC10JU-() clamps, it is per- mitted to use BACC10GU-() clamps. (e) May be purchased from: Zeus Industrial Products, (V6Y609), 501 BIvd. S.E., P.O. Box 2167, Or- angeburg, South Carolina 29116. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 42 of 442 ### Page 43 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 11: Part Number / Specification QTY Name Notes May substitute with any equivalent Teflon Tape. Quantity is as required. (g) May be purchased from: Permacel Corporation (V99742) - US Highway 1, P.O. Box 671 North Brunswick, New Jersey 08902. Group 12: Part Number / Specification QTY Name Notes BACC10GU-101 2 Full Cushion Clamp (a) (c) BACC10GU-102 5 BACC10JU-103 14 (a) (c) (d) BACC10J0-105 15 BACC 10JU-106 17 BACC10JU-109 8 BACC10JU-111 4 BACC10JU-112 25 P-421 Teflon Tape (f) (g) or Mil-1-23594, Type I, Class 4 TFE-2X, 3/4 Inch Diameter, Standard Wall 24 Feet Teflon Sleeving (b) (e) Thickness, Natural BMS 13-54, Type III, Class 1, Finish C, Black 240 Feet Lacing Tape (a) (b) BMS 5-45, Class A-2, Grade 1 or Grade 2 70 oz Sealant (a) BMS 5-45, Class B-2 70 oz Sealant BMS 15-5, Class A, Wiper, Absorbent, Process 60 Wiper Cleaning BMS 11-7 25 oz Solvent (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) The quantity shown is the maximum amount that may be necessary if the verification shows the clamps to be missing (c) The clamp sizes shown are approximate and to be determined on installation. The total quantity is the maximum that may be necessary if the verification shows the clamps to be missing. (d) At locations where the wire bundle is too large or too small to use BACC10JU-() clamps, it is per- mitted to use BACC 10GU-() clamps. (e) May be purchased from: Zeus Industrial Products, (V6Y609), 501 Blvd. S.E., P.O. Box 2167, Or- angeburg, South Carolina 29116. May substitute with any equivalent Teflon Tape. Quantity is as required. Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 43 of 442 ### Page 44 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 12: Part Number / Specification QTY Name Notes (g) May be purchased from: Permacel Corporation (V99742) - US Highway 1, P.O. Box 671 North Brunswick, New Jersey 08902. Group 13: Part Number / Specification QTY Name Notes BACC10GU-101 2 Full Cushion Clamp (a) (c) BACC10GU-102 5 BACC10JU-103 12 (a) (c) (d) BACC10JU-105 6 BACC10JU-106 24 BACC10JU-109 8 BACC10JU-111 8 BACC10JU-112 23 P-421 Teflon Tape (t) (g) or Mil-I-23594, Type I, Class 4 TFE-2X, 3/4 Inch Diameter, Standard Wall 24 Feet Teflon Sleeving (b) (e) Thickness, Natural BMS 13-54, Type III, Class 1, Finish C, Black 240 Feet Lacing Tape (a) (b) BMS 5-45, Class A-2, Grade 1 or Grade 2 70 oz Sealant (a) BMS 5-45, Class B-2 70 oz Sealant BMS 15-5, Class A, Wiper, Absorbent, Process 60 Wiper Cleaning BMS 11-7 25 oz Solvent (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) The quantity shown is the maximum amount that may be necessary if the verification shows the clamps to be missing. (c) The clamp sizes shown are approximate and to be determined on installation. The total quantity is the maximum that may be necessary if the verification shows the clamps to be missing. (d) At locations where the wire bundle is too large or too small to use BACC10JU-() clamps, it is per- mitted to use BACC10GU-() clamps. (e) May be purchased from: Zeus Industrial Products, (V6Y609), 501 Blvd. S.E., P.O. Box 2167, Or- angeburg, South Carolina 29116. May substitute with any equivalent Teflon Tape. Quantity is as required. (g) May be purchased from: Permacel Corporation (V99742) - US Highway 1, P.O. Box 671 North Brunswick, New Jersey 08902. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 442 ### Page 45 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT Group 14: Part Number / Specification QTY Name Notes BACC10GU-101 2 Full Cushion Clamp (a) (c) BACC 10GU-102 5 BACC10JU-103 12 (a) (c) (d) BACC10JU-105 6 BACC 10JU-106 24 BACC10JU-109 8 BACC10JU-111 4 BACC 10JU-112 25 P-421 Teflon Tape (f) (g) or Mil-I-23594, Type I, Class 4 TFE-2X, 3/4 Inch Diameter, Standard Wall 24 Feet Teflon Sleeving (b) (e) Thickness, Natural BMS 13-54, Type III, Class 1, Finish C, Black 240 Feet Lacing Tape (a) (b) BMS 5-45, Class A-2, Grade 1 or Grade 2 70 oz Sealant (a) BMS 5-45, Class B-2 70 oz Sealant BMS 15-5, Class A, Wiper, Absorbent, Process 60 Wiper Cleaning BMS 11-7 25 oz Solvent (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) The quantity shown is the maximum amount that may be necessary if the verification shows the clamps to be missing. (c) The clamp sizes shown are approximate and to be determined on installation. The total quantity is the maximum that may be necessary if the verification shows the clamps to be missing. (d) At locations where the wire bundle is too large or too small to use BACC10JU-() clamps, it is per- mitted to use BACC10GU-() clamps. (e) May be purchased from: Zeus Industrial Products, (V6Y609), 501 Blvd. S.E., P.O. Box 2167, Or- angeburg, South Carolina 29116. May substitute with any equivalent Teflon Tape. (g) May be purchased from: Permacel Corporation (V99742) - US Highway 1, P.O. Box 671 North Brunswick, New Jersey 08902. 3. Parts Modified and Reidentified: None. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 442 ### Page 46 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT 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. Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 46 of 442 ### Page 47 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT 3. 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. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2 The instructions identified in Paragraph 3.B. Work Instructions and the Figure(s) give recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 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. 5. 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. 6 For approved fastener and process material substitutions, refer to 757 Structural Repair Manual, Chapter 51. Alternate fasteners are given in 757 Structural Repair Manual Chapter 51 and Boeing Drawing 65-88700. 7. Refer to the Boeing Standard Wiring Practices Manuals SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures. 8. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise elve minor no specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normal available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. 9. These work instructions refer to procedures included on other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "as given in" are included in the instruction, the procedure in the Boeing document must Original Issue: July 16, 2007 Revision 1: October 05, 2009 • BOEING PROPRIETARY 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 47 of 442 ### Page 48 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT 10. For any fasteners that are previously sealed to the specifications of this service bulletin, it is not required for the existing seal to be removed and fastener sealed again. These sealed fasteners are acceptable as is and no further work is necessary 11. Location and quantity of existing fasteners shown in Figures are approximate, and may differ from your airplane configuration, seal additional fasteners as required. 12. Operators that have not done the work in accordance with the original issue of service bulletin 757-57A0064 must do Parts 1 through 10 of this service bulletin. 13. Part 11 of this service bulletin is only applicable to operators that have done the work in accordance with the original release of service bulletin. 14. Approved wire bundle support installation deviations: • Removal of ECS / Heat Exchanger components are optional and as required to gain access for inspection and wire bundle support installation. Clamps sizes called out in Figures maybe changed to get a better fit. Refer to SWPM 20-10-12 as an accepted procedure. Locations where tandem clamps are shown in Figures, single clamps may exists for your airplane configuration and are acceptable as is Location and quantity of existing clamps shown in Figures are approximate, and may differ from your airplane contiguration. Orientation of existing clamps shown in Figures are for reference only, and may differ from your airplane configuration. Wire bundles and routing shown in this service bulletin may differ from what is on the airplane. Existing wire bundle configuration is acceptable it installed (clamp size, routing and bend radii) to the standards of SWPM 20-10-11 and SWPM 20-10-12 and the clamps and Teflon sleeves are in accordance with the requirements of this service bulletin. Wire bundle support installation with brackets) that has a grounding stud instead of a clamp, no sleeve or clamp replacement will be necessary at that location. Wire bundles that are protected by existing Convolex tubing, installation of the new TFE-2X Teflon sleeve may end at the start of the Convolex tubing. Wire bundles that are protected by existing BMS13-52 expando sleeving need to be covered with TFE-2X Teflon Sleeving Wire bundle segments that are supported by 2 or more clamps may use a continuous piece of TFE-2X Teflon sleeve in place of separate 3 inch sleeves as long as sleeve is smooth and without gaps. Install sleeves and lacing tape in accordance with associated Figure(s), and refer to SWPM 20-20-11 as an accepted procedure. . Wire bundle segments with sharp bends (small radius) near a clamp or other interference, may deviate from centering of the Teflon sleeve to the clamp. Acceptable to center the 3 inch Teflon sleeve as close as possible to the clamp. Locations where a break out is within 1.5 inches of the clamp, it is acceptable to install TFE-2X Teflon sleeve on the breakout wire separately from main bundle. TFE-2X Teflon sleeve is required on the remaining wire bundle at clamp location. Locations where a wire bundle or wire break out with sharp bends (small radius) near a clamp and not allowing for proper installation of the TFE-2X Teflon sleeve, it is acceptable to wrap Teflon tape around the TFE-2X Teflon sleeve installation for smooth transition and cover any gaps. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 48 of 442 ### Page 49 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT FULL CUSHION CLAMP FULL CUSHION CLAMP TEFLON SLEEVING TEFLON TAPE TEFLON SLEEVING (LOCATIONS WITH WIRE (LOCATIONS WITH WIRE BUNDLE/WIRE BREAKOUT BREAKOUT WITHIN 1.5 WITH SMALL BEND RADIUS) INCHES OF CLAMP) B. WORK INSTRUCTIONS 1. PART 1: FUEL TANKS - FASTENER SEALING a. Group 1: Seal fasteners in the center and main fuel tanks as follows: (1) Purge the center and main fuel tanks. Refer to 757 AMM 28-11-00 as an accepted procedure. (2) Remove and keep the center fuel tank access doors 531AB, 531BB and 531CB, and remove and keep the left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (3) Remove and keep the left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (4) Remove and keep the center fuel tank access doors 631AB, 631BB and 631CB, and remove and keep the right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (5) Remove and keep the right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (6) Remove and keep the center fuel tank access door 134AZ, and remove and keep the fuel bay baffle doors 134BZ, 134CZ and 134DZ. Refer to 757 AMM 28-11-02 as an accepted procedure. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 442 ### Page 50 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT (7) Locate and seal the fasteners on the left side rear spar as given in Figure 1 and Figure 46. (8) Locate and seal the fasteners on the right side rear spar as given in Figure 2 and Figure 46. (9) Locate and seal the fasteners on the left side front spar as given in Figure 13 and Figure 46. (10) Locate and seal the fasteners on the right side front spar as given in Figure 14 and Figure 46. (11) Locate and seal the fasteners in the center fuel tank as given in Figure 19 and Figure 46. CAUTION: MAKE SURE YOU REMOVE ALL UNWANTED PARTICLES AND MATERIALS FROM THE FUEL TANKS. UNWANTED MATERIALS CAN COLLECT IN THE FUEL TANKS, WHICH CAN CAUSE BLOCKAGE OR INCORRECT SYSTEM OPERATION. (12) Close access to the center tank. Install kept fuel bay baffle doors 134BZ, 134CZ and 134DZ and install the center fuel tank access door 134AZ, Refer to 757 AMM 28-11-02 as an accepted procedure. (13) Install kept left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (14) Install kept center fuel tank access doors 531AB, 531BB and 531CB, and install kept left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (15) Install kept right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (16) Install kept center fuel tank access doors 631AB, 631BB and 631CB, and install kept right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (17) Make sure that all removed and installed fuel tank access doors do not leak. Refer to 757 AMM 28-11-00 as an accepted procedure. b. Group 2: Seal fasteners in the center and main fuel tanks as follows: Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 50 of 442 ### Page 51 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT (1) Purge the center and main fuel tanks. Refer to 757 AMM 28-11-00 as an accepted procedure. (2) Remove and keep the center fuel tank access doors 531AB, 531BB and 531CB, and remove and keep the left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (3) Remove and keep the left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (4) Remove and keep the center fuel tank access doors 631AB, 631BB and 631CB, and remove and keep the right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (5) Remove and keep the right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (6) Remove and keep the center tank access door 134AZ, and remove and keep the fuel bay baffle doors 134BZ, 134CZ and 134DZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (7) Locate and seal the fasteners on the left side rear spar as given in Figure 1 and Figure 46. (8) Locate and seal the fasteners on the right side rear spar as given in Figure 2 and Figure 46 (9) Locate and seal the fasteners on the left side front spar as given in Figure 13 and Figure 46. (10) Locate and seal the fasteners on the right side front spar as given in Figure 14 and Figure 46. (11) Locate and seal the fasteners in the center tank as given in Figure 20 and Figure 46. CAUTION: MAKE SURE YOU REMOVE ALL UNWANTED PARTICLES AND MATERIALS FROM THE FUEL TANKS. UNWANTED MATERIALS CAN COLLECT IN THE FUEL TANKS, WHICH CAN CAUSE BLOCKAGE OR INCORRECT SYSTEM OPERATION (12) Close access to the center tank. Install kept fuel bay baffle doors 134BZ, 134CZ and 134DZ, and install the kept center fuel tank access door 134AZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (13) Install kept left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (14) Install kept center fuel tank access doors 531AB, 531BB and 531CB, and install kept left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 51 of 442 ### Page 52 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT (15) Install kept right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (16) Install kept center fuel tank access doors 631AB, 631BB and 631CB, and install kept right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (17) Make sure that all removed and installed fuel tank access doors do not leak. Refer to 757 AMM 28-11-00 as an accepted procedure. c. Group 3: Seal fasteners in the center and main fuel tanks as follows: (1) Purge the center and main fuel tanks. Refer to 757 AMM 28-11-00 as an accepted procedure. (2) Remove and keep the center fuel tank access doors 531AB, 531BB and 531CB, and remove and keep the left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (3) Remove and keep the left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (4) Remove and keep the center fuel tank access doors 631AB, 631BB and 631CB, and remove and keep the right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (5) Remove and keep the right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (6) Remove and keep the center tank access door 134AZ, and remove and keep the fuel bay baffle doors134BZ, 134CZ and 134DZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (7) Locate and seal the fasteners on the left side rear spar as given in Figure 3 and Figure 46. (8) Locate and seal the fasteners on the right side rear spar as given in Figure 4 and Figure 46. (9) Locate and seal the fasteners on the left side front spar as given in Figure 13 and Figure 46. (10) Locate and seal the fasteners on the right side front spar as given in Figure 14 and Figure 46. (11) Locate and seal the fasteners in the center tank as given in Figure 19 and Figure 46. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 442 ### Page 53 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT CAUTION: MAKE SURE YOU REMOVE ALL UNWANTED PARTICLES AND MATERIALS FROM THE FUEL TANKS. UNWANTED MATERIALS CAN COLLECT IN THE FUEL TANKS, WHICH CAN CAUSE BLOCKAGE OR INCORRECT SYSTEM OPERATION (12) Close access to the center tank. Install kept fuel bay baffle doors 134BZ, 134CZ and 134DZ, and install the kept center fuel tank access door 134AZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (13) Install kept left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (14) Install kept center fuel tank access doors 531AB, 531BB and 531CB, and install kept left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (15) Install kept right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (16) Install kept center fuel tank access doors 631AB, 631BB and 631CB, and install kept right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (17) Make sure that all removed and installed fuel tank access doors do not leak. Refer to 757 AMM 28-11-00 as an accepted procedure. d. Group 4: Seal fasteners in the center and main fuel tanks as follows: (1) Purge the center and main fuel tanks. Refer to 757 AMM 28-11-00 as an accepted procedure. (2) Remove and keep the center fuel tank access doors 531AB, 531BB and 531CB, and remove and keep the left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (3) Remove and keep the left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (4) Remove and keep the center fuel tank access doors 631AB, 631BB and 631CB, and remove and keep the left main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (5) Remove and keep the right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (6) Remove and keep the center fuel tank access door 134AZ, and remove and keep the fuel bay baffle doors 134BZ, 134CZ and 134DZ. Refer to 757 AMM 28-11-02 as an accepted procedure. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 •BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 442 ### Page 54 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT (7) Locate and seal the fasteners on the left side rear spar as given in Figure 3 and Figure 46. (8) Locate and seal the fasteners on the right side rear spar as given in Figure 4 and Figure 46. (9) Locate and seal the fasteners on the left side front spar as given in Figure 13 and Figure 46. (10) Locate and seal the fasteners on the right side front spar as given in Figure 14 and Figure 46. (11) Locate and seal the fasteners in the center tank as given in Figure 20 and Figure 46. CAUTION: MAKE SURE YOU REMOVE ALL UNWANTED PARTICLES AND MATERIALS FROM THE FUEL TANKS. UNWANTED MATERIALS CAN COLLECT IN THE FUEL TANKS, WHICH CAN CAUSE BLOCKAGE OR INCORRECT SYSTEM OPERATION. (12) Close access to the center tank. Install kept fuel bay baffle doors 134BZ, 134CZ and 134DZ and install the kept center fuel tank access door 134AZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (13) Install kept left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (14) Install kept center fuel tank access doors 531AB, 531BB and 531CB, and install kept left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (15) Install kept right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (16) Install the kept center fuel tank access doors 631AB, 631BB and 631CB, and install the kept right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (17) Make sure that all removed and installed fuel tank access doors do not leak. Refer to 757 AMM 28-11-00 as an accepted procedure. e. Group 5: Seal fasteners in the center and main fuel tanks as follows: Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 54 of 442 ### Page 55 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT (1) Purge the center and main fuel tanks. Refer to 757 AMM 28-11-00 as an accepted proceaure. (2) Remove and keep the center fuel tank access doors 531AB, 531BB, and 531CB, and remove and keep the left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (3) Remove and keep the left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (4) Remove and keep the center fuel tank access doors 631AB, 631BB and 631CB, and remove and keep the right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (5) Remove and keep the right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (6) Remove and keep the center tank access door 134AZ, and remove and keep the fuel bay baffle doors 134BZ, 134CZ and 134DZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (7) Locate and seal the fasteners on the left side rear spar as given in Figure 5 and Figure 46. (8) Locate and seal the fasteners on the right side rear spar as given in Figure 6 and Figure 46. (9) Locate and seal the fasteners on the left side front spar as given in Figure 13 and Figure 46. (10) Locate and seal the fasteners on the right side front spar as given in Figure 14 and Figure 46. (11) Locate and seal the fasteners in the center tank as given in Figure 19 and Figure 46. CAUTION: MAKE SURE YOU REMOVE ALL UNWANTED PARTICLES AND MATERIALS FROM THE FUEL TANKS, UNWANTED MATERIALS CAN COLLECT IN THE FUEL TANKS, WHICH CAN CAUSE BLOCKAGE OR INCORRECT SYSTEM OPERATION (12) Close access to the center tank. Install the kept fuel bay baffle doors 134BZ, 134CZ and 134DZ, and install the kept center tank access door 134AZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (13) Install kept left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (14) Install the kept center fuel tank access doors 531AB, 531BB and 531CB, and install the kept left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 • BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 442 ### Page 56 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT (15) Install kept right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (16) Install the kept center fuel tank access doors 631AB, 631BB and 631CB, and install the kept right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (17) Make sure that all removed and installed fuel tank access doors do not leak. Refer to 757 AMM 28-11-00 as an accepted procedure. f. Group 6-7: Seal fasteners in the center and main fuel tanks as follows: (1) Purge the center and main fuel tanks. Refer to 757 AMM 28-11-00 as an accepted procedure. (2) Remove and keep the center fuel tank access doors 531AB, 531BB and 531CB, and remove and keep the left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (3) Remove and keep the left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (4) Remove and keep the center fuel tank access doors 631AB, 631BB and 631CB, and remove and keep the right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (5) Remove and keep the right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (6) Remove and keep the center tank access door 134AZ, and remove and keep the fuel bay baffle doors 134BZ, 134CZ and 134DZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (7) Locate and seal the fasteners on the left side rear spar as given in Figure 5 and Figure 46. (8) Locate and seal the fasteners on the right side rear spar as given in Figure 6 and Figure 46. (9) Locate and seal the fasteners on the left side front spar as given in Figure 15 and Figure 46. (10) Locate and seal the fasteners on the right side front spar as given in Figure 16 and Figure 46. (11) Locate and seal the fasteners in the center tank as given in Figure 19 and Figure 46. Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 56 of 442 ### Page 57 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT CAUTION: MAKE SURE YOU REMOVE ALL UNWANTED PARTICLES AND MATERIALS FROM THE FUEL TANKS. UNWANTED MATERIALS CAN COLLECT IN THE FUEL TANKS, WHICH CAN CAUSE BLOCKAGE OR INCORRECT SYSTEM OPERATION (12) Close access to the center tank. Install kept fuel bay baffle doors 134BZ, 134CZ and 134DZ, and install the kept center tank access door 134AZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (13) Install kept left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (14) Install the kept center fuel tank access doors 531AB, 531BB and 531CB, and install the kept left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (15) Install kept right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (16) Install kept center fuel tank access doors 631AB, 631BB and 631CB, and install the kept right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (17) Make sure that all removed and installed fuel tank access doors do not leak. Refer to 757 AMM 28-11-00 as an accepted procedure. g. Group 8-10: Seal fasteners in the center and main fuel tanks as follows: (1) Purge the center and main fuel tanks. Refer to 757 AMM 28-11-00 as an accepted procedure, (2) Remove and keep the center fuel tank access doors 531AB, 531BB and 531CB, and remove and keep the left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (3) Remove and keep the left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (4) Remove and keep the center fuel tank access doors 631AB, 631BB and 631CB, and remove and keep the right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (5) Remove and keep the right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (6) Remove and keep the center tank access door 134AZ, and remove and keep the fuel bay baffle doors 134BZ, 134CZ and 134DZ. Refer to 757 AMM 28-11-02 as an accepted procedure. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 442 ### Page 58 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT (7) Locate and seal the fasteners on the left side rear spar as given in Figure 7 and Figure 46. (8) Locate and seal the fasteners on the right side rear spar as given in Figure 8 and Figure 46. (9) Locate and seal the fasteners on the left side front spar as given in Figure 17 and Figure 46. (10) Locate and seal the fasteners on the right side front spar as given in Figure 18 and Figure 46. (11) Locate and seal the fasteners in the center tank as given in Figure 21 and Figure 46. CAUTION: MAKE SURE YOU REMOVE ALL UNWANTED PARTICLES AND MATERIALS FROM THE FUEL TANKS. UNWANTED MATERIALS CAN COLLECT IN THE FUEL TANKS, WHICH CAN CAUSE BLOCKAGE OR INCORRECT SYSTEM OPERATION. (12) Close access to the center tank. Install the kept fuel bay baffle doors 134BZ, 134CZ and 134DZ, and install the kept center tank access door 134AZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (13) Install kept left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (14) Install the kept center fuel tank access doors 531AB, 531BB and 531CB, and install the kept left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (15) Install kept right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (16) Install the kept center fuel tank access doors 631AB, 631BB and 631CB, and install the kept right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (17) Make sure that all removed and installed fuel tank access doors do not leak. Refer to 757 AMM 28-11-00 as an accepted procedure. h. Group 11-12: Seal fasteners in the center and main fuel tanks as follows: Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOEING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 58 of 442 ### Page 59 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT (1) Purge the center and main fuel tanks. Refer to 757 AMM 28-11-00 as an accepted procedure. (2) Remove and keep the center fuel tank access doors 531AB, 531BB and 531CB, and remove and keep the left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (3) Remove and keep the left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (4) Remove and keep the center fuel tank access doors 631AB, 631BB and 631CB, and remove and keep the right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (5) Remove and keep the right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (6) Remove and keep the center tank access door 134AZ, and remove and keep the fuel bay baffle doors 134BZ, 134CZ and 134DZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (7) Locate and seal the fasteners on the left side rear spar as given in Figure 9 and Figure 46. (8) Locate and seal the fasteners on the right side rear spar as given in Figure 10 and Figure 46. (9) Locate and seal the fasteners on the left side front spar as given in Figure 15 and Figure 46. (10) Locate and seal the fasteners on the right side front spar as given in Figure 16 and Figure 46. (11) Locate and seal the fasteners in the center tank as given in Figure 19 and Figure 46. CAUTION: MAKE SURE YOU REMOVE ALL UNWANTED PARTICLES AND MATERIALS FROM THE FUEL TANKS. UNWANTED MATERIALS CAN COLLECT IN THE FUEL TANKS, WHICH CAN CAUSE BLOCKAGE OR INCORRECT SYSTEM OPERATION (12) Close access to the center tank. Install the kept fuel bay baffle doors 134BZ, 134CZ and 134DZ, and install the kept center tank access door 134AZ. Refer to 757 AMM 28-11-02 as an accepteo procedure. (13) Install kept left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (14) Install the kept center fuel tank access doors 531AB, 531BB and 531CB, and install the kept left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. Original Issue: July 16, 2007 Revision 1: October 05, 2009 BOẸING PROPRIETARY - 757-57A0064 Copyright © Unpublished Work - See page 1 for details. 59 of 442 ### Page 60 (OCR) BOEING SERVICE BULLETIN 757-57A0064 ALERT ALERT (15) Install kept right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (16) Install the kept center fuel tank access doors 631AB, 631BB and 631CB, and install the kept right main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (17) Make sure that all removed and installed fuel tank access doors do not leak. Refer to 757 AMM 28-11-00 as an accepted procedure. Group 13-14: Seal fasteners in the center and main fuel tanks as follows: (1) Purge the center and main fuel tanks. Refer to 757 AMM 28-11-00 as an accepted procedure. (2) Remove and keep the center fuel tank access doors 531AB, 531BB and 531CB, and remove and keep the left main fuel tank access doors 541AB, 541BB, 541EB, 541FB, 541HB, 541JB, 541KB, 541LB, 541MB, 542AB, 542CB and 542DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (3) Remove and keep the left wing dry bay access doors 532BZ, 532DZ and 532FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (4) Remove and keep the center fuel tank access doors 631AB, 631BB, and 631CB and remove and keep the left main fuel tank access doors 641AB, 641BB, 641EB, 641FB, 641HB, 641JB, 641KB, 641LB, 641MB, 642AB, 642CB and 642DB. Refer to 757 AMM 28-11-01 and 757 AMM 28-11-02 as an accepted procedure. (5) Remove and keep the right wing dry bay access doors 632BZ, 632DZ and 632FZ. Refer to 757 AMM 28-11-07 as an accepted procedure. (6) Remove and keep the center tank access door 134AZ, and remove and keep the fuel bay baffle doors 134BZ, 134CZ and 134DZ. Refer to 757 AMM 28-11-02 as an accepted procedure. (7) Locate and seal the fasteners on the left side rear spar as given in Figure 11 and Figure 46. (8) Locate and seal the fasteners on the right side rear spar as given in Figure 12 and Figure 46. (9) Locate and seal the fasteners on the left side front spar as given in Figure 17 and Figure 46. (10) Locate and seal the fasteners on the right side front spar as given in Figure 18 and Figure 46. (11) Locate and seal the fasteners in the center tank as given in Figure 21 and Figure 46. Original Issue: July 16, 2007 Revision 1: October 05, 2009 757-57A0064 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 60 of 442 The text continues at https://openairdocs.org/service-documents/boeing/757-57a0064/file/7a15d9368ce7.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.