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Commercial Airplanes 737 Service Bulletin Number: 737-57A1302 Original Issue: December 15, 2008 Revision 1: October 18, 2010 ATA System: 5754 SUBJECT: WINGS - Leading Edge Slats- Main Track Down Stop Modification and Detailed Inspection Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 15, 2008 737-57A1302Revision 1: October 18, 2010 1 of 42
7.0
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Table of Contents
Revision Transmittal Sheet5
Summary7
1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 2 0 B. Concurrent Requirements ...................................... 2 0 C. Reason ................................................ 2 1 D. Description .............................................. 2 2 E. Compliance .............................................. 2 2 F. Approval ............................................... 2 3 G. Manpower .............................................. 2 3 H. Weight and Balance Changes .................................... 2 4 I. Electrical Load Data ......................................... 2 4 J. References .............................................. 2 4
1. Existing Data .......................................... 2 4
2. Data supplied with this Service Bulletin ............................ 2 4
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 2 4 K. Publications Affected ........................................ 2 5 L. Interchangeability and Intermixability of Parts ........................... 2 5
2. MATERIAL INFORMATION ........................................ 2 7 A. Material - Price and Availability ................................... 2 7 B. Industry Support Information .................................... 2 7 C. Parts Necessary For Each Airplane ................................. 2 7
1. Kits/Parts ............................................ 2 7
2. Parts and Materials Supplied by the Operator ........................ 2 8
3. Parts Modified and Reidentified ................................ 2 8
4. Parts Removed and Not Replaced .............................. 2 8 D. Parts Necessary to Change Spares ................................. 2 8 E. Special Tooling - Price and Availability ............................... 2 9 F. Special Tooling Necessary to do this Service Bulletin ....................... 2 9
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 1 A. GENERAL INFORMATION ..................................... 3 1 B. WORK INSTRUCTIONS ....................................... 3 1 FIGURE 1: SHRINK-FIT BUSHING INSTALLATION ........................... 3 5 FIGURE 2: SHRINK-FIT BUSHING REAMING .............................. 3 6 FIGURE 3: SLAT MAIN TRACK DOWN STOP AND AFT SIDE GUIDE MODIFICATION ....... 3 7
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Commercial Airplanes 737 Service Bulletin Revision Transmittal SheetNumber: 737-57A1302Original Issue: December 15, 2008 Revision 1: October 18, 2010 ATA System: 5754 SUBJECT: WINGS - Leading Edge Slats- Main Track Down Stop Modification and Detailed Inspection This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directive FAA AD 2007-18-52 is related to this service bulletin.
REASON FOR REVISION This revision is sent to add clarification to this service bulletin.
Changes to this service bulletin include:
– Added borescope inspection option for the slat main track and in the slat can.
– Updated Industry Support Information with the applicable Boeing Program Letter.
– Added Damage Tolerance Information to Publications Affected.
– Added optional stainless steel lockwire to Operator Supplied Parts table and Figure 3.
– Updated Special Tooling - Price and Availability section, with Boeing's offer of two free optional toolkits to all operators, and removed toolkit rental option.
– Added HAND reaming recommendation in the event interference occurs between the new down stop assembly bolt and the hole in the slat main track, in the Accomplishment Instructions.
– Added the option to remove the wing anti-icing duct elbows near the down stop assembly in the right wing near the fuel metering manifold in order to gain easier access, in the Accomplishment Instructions. If the duct is disassembled a leak test is required.
– Added reference to Aircraft Maintenance Manual 737-600/700/800/900 AMM 57-41-02 when reinstalling lower leading edge wing panels at the end of the Accomplishment Instructions.
– Changed lower hole tolerance limit to 0.4375 inches in the event a bushing repair becomes necessary for the slat main track, in Figure 2.
– Added step to apply corrosion preventive compound, MIL-C-11796, Class 3, to new aft side guide bolts upon installation, in Figure 3.
The data given in Information Notice 737-57A1302 IN 01 is included in this revision.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.
Pages with no vertical lines have no important changes.
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Original Issue: December 15, 2008 737-57A1302Revision 1: October 18, 2010 5 of 42
REVISION HISTORY December 15, 2008Original Issue:
October 18, 2010Revision 1:
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Original Issue: December 15, 2008 737-57A1302Revision 1: October 18, 2010 6 of 42 BOEING SERVICE BULLETIN 737-57A1302
Commercial Airplanes 737 Service Bulletin SummaryNumber: 737-57A1302Original Issue: December 15, 2008 Revision 1: October 18, 2010 ATA System: 5754 SUBJECT: WINGS - Leading Edge Slats- Main Track Down Stop Modification and Detailed Inspection
CONCURRENT REQUIREMENTS None.
BACKGROUND Recently, a fuel leak and a subsequent fire resulted from loose down stop assembly hardware being pushed through the slat can while the slats were being retracted. FAA Airworthiness Directive FAA AD 2007-18-52 was initiated to inspect the 737NG fleet and re-torque the down stop assemblies as a result of this fire. Several issues were found including missing hardware, low torque, and improper assembly. This service bulletin requires 1) removal of the existing down stop assemblies and installation of a new down stop assembly on all 16 slat main tracks, and 2) removal of the existing aft side guide attach bolts at all 64 locations and replacement with identical bolts with drilled heads that are lock wired together on the ribs of the leading edge of the wing. Failure to incorporate this service bulletin could lead to conditions that allow the down stop assembly to fall off, or the aft side guides to become loose, and fall into the slat can. If the down stop assembly comes apart inside the slat can or the aft side guide falls into the slat can, then the slat main track may trap a down stop assembly component between the slat can and slat main track causing a puncture of the fuel tank creating a fuel leak and the risk of fire.
As a part of a service bulletin validation program, this change was completed on airplane YC578 by Service Bulletin 737-57A1302 Original Issue before the release of Revision 1 of this service bulletin. The change completed on airplane YC578 by Service Bulletin 737-57A1302 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane YC578 has the configuration of a Group 1 airplane.
Boeing Service Related Problem (SRP) 737-SRP-57-0209 is related to this service bulletin.
ACTION (PRR 38275-136S) Remove the existing down stop assembly hardware from the slat main tracks of slats one through eight. Install the new down stop assembly hardware in the correct order and torque the nut. Install the cotter pin after all other hardware has been installed and bend the legs of the cotter pin. Remove the bolts which secure the aft side guides to the leading edge slat track ribs and replace them with the new drilled head bolts. Install the lock wire on the aft side guide boltheads. After the changes are done, do a detailed inspection or borescope inspection for debris on the slat main track and in the slat can.
Special tooling is available from Boeing to assist with the installation of the down stop assembly hardware.
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EFFECTIVITY 737-600, 700, 700C, 800, 900, 900ER airplanes. See Paragraph 1.A.1., Airplanes, for effectivity.
COMPLIANCE Refer to Paragraph 1.E., Compliance.
Federal Aviation Administration (FAA) Airworthiness Directive FAA AD 2007-18-52 is related to this service bulletin.
INDUSTRY SUPPORT INFORMATION Boeing Industry Support information is provided in Program Letter BPL 6-1151-737-PGM-190, dated March 9, 2009 . Additional copies of program letters are available from Boeing Warranty and Product Assurance Contracts.
MANPOWER Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability
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Original Issue: December 15, 2008 737-57A1302Revision 1: October 18, 2010 8 of 42 BOEING SERVICE BULLETIN 737-57A1302
BOEING SERVICE BULLETIN 737-57A1302
LEFT WING SHOWN (RIGHT WING IS EQUIVALENT)
REMOVE AND REPLACE BOLT,
INSTALL LOCKWIRE AT EACH
MAIN TRACK (4 LOCATIONS)
REMOVE AND REPLACE DOWNSTOP.
DO A DETAILED
INSPECTION FOR DEBRIS
ON THE SLAT MAIN TRACK AND IN THE SLAT CAN.
SLAT NUMBER 3 SHOWN 1571129 TYPICAL 16 LOCATIONS Original Issue: December 15, 2008 Revision 1: October 18, 2010 737-57A1302
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Commercial Airplanes 737 Service Bulletin Number: 737-57A1302 Original Issue: December 15, 2008 Revision 1: October 18, 2010 ATA System: 5754 SUBJECT: WINGS - Leading Edge Slats- Main Track Down Stop Modification and Detailed Inspection
1. PLANNING INFORMATION A. Effectivity
1. Airplanes Refer to Service Bulletin Index Document D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 38275-136S for data about this change.
DESCRIPTIONCONFIGURATIONGROUP 737-600/700/700C/800/900/900ER airplanes line numbers 1 through 2699 -1 Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER GroupVariable Number 1YA001 - YA099 1YA101 - YA199 1YA201 - YA211 1YA221 1YA231 - YA242 1YA251 - YA256 1YA271 - YA272 1YA291 1YA301 - YA302
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GroupVariable Number 1YA311 - YA314 1YA321 - YA323 1YA336 - YA345 1YA351 1YA356 - YA357 1YA366 - YA367 1YA371 - YA377 1YA501 - YA536 1YA541 - YA552 1YA571 - YA578 1YA601 - YA615 1YA621 - YA622 1YA626 - YA631 1YA635 - YA636 1YA641 - YA642 1YA645 - YA650 1YA656 - YA659 1YA666 - YA667 1YA671 - YA672 1YA681 - YA691 1YA701 - YA710 1YA721 - YA722 1YA731 - YA734 1YA751 - YA756 1YA801 - YA803 1YA809 1YA811 - YA814 1YA831 - YA835 1YA841 - YA862 1YA881 - YA882 1YA891 - YA892 1YA961 - YA978 1YB001 - YB006
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