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Commercial Airplanes 747 Service Bulletin ALERT Number: 747-53A2559 Original Issue: January 08, 2009 Revision 2: May 13, 2014 ATA System: 5312 SUBJECT: FUSELAGE - Main Frame - Center Section - Tension Tie and Frame - Modification - Stretched Upper Deck Airplanes Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2009 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company.
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, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries 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: January 08, 2009 747-53A2559Revision 2: May 13, 2014 1 of 1014
6.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 08, 2009 747-53A2559Revision 2: May 13, 2014 2 of 1014 BOEING SERVICE BULLETIN 747-53A2559
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Table of Contents
Revision Transmittal Sheet9
Summary ..................................................... 1 3
1. PLANNING INFORMATION ........................................ 1 7 A. Effectivity ............................................... 1 7
1. Airplanes ............................................ 1 7
2. Spares Affected ........................................ 2 3 B. Concurrent Requirements ...................................... 2 3 C. Reason ................................................ 2 3 D. Description .............................................. 2 4 E. Compliance .............................................. 2 5 F. Approval ............................................... 2 9 G. Manpower .............................................. 2 9 H. Weight and Balance Changes .................................... 3 9 I. Electrical Load Data ......................................... 4 0 J. References .............................................. 4 0
1. Existing Data: ......................................... 4 0
2. Data Supplied with this Service Bulletin: ........................... 4 1
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 4 K. Publications Affected ........................................ 4 4 L. Interchangeability and Intermixability of Parts ........................... 4 4 M. Software Accomplishment Summary ................................ 4 4
2. MATERIAL INFORMATION ........................................ 4 5 A. Material - Price and Availability ................................... 4 5 B. Industry Support Information .................................... 4 7 C. Parts Necessary for Each Airplane ................................. 4 7
1. Kits/Parts: ........................................... 4 7
2. Parts and Materials Supplied by the Operator: ....................... 1 6 8
3. Parts Modified and Reidentified: ............................... 1 6 9
4. Parts Removed and Not Replaced: ............................. 1 6 9 D. Parts Necessary to Change Spares ................................ 1 7 0 E. Special Tooling - Price and Availability .............................. 1 7 0 F. Special Tooling Necessary to do this Service Bulletin ...................... 1 7 0
3. ACCOMPLISHMENT INSTRUCTIONS ................................. 1 7 1 A. GENERAL INFORMATION .................................... 1 7 1 B. WORK INSTRUCTIONS ...................................... 1 7 3 FIGURE 1: REMOVE SHEAR PANEL - LEFT SIDE [Group 1-2] .................... 1 8 4 FIGURE 2: REMOVE SHEAR PANEL - RIGHT SIDE [Group 1-2] ................... 1 9 0 FIGURE 3: STA 1120 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 1-2] ............................................... 1 9 6 FIGURE 4: STA 1120 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 1-2] .......................................... 2 0 4 FIGURE 5: STA 1120 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 1-2] .... 2 1 2 FIGURE 6: STA 1120 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 1-2] .... 2 2 6 FIGURE 7: STA 1120 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 1-2] . 240 FIGURE 8: STA 1120 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 1-2] . 247 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 9: STA 1140 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 2 , 4 ] .............................................. 2 5 3 FIGURE 10: STA 1140 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 2, 4] .......................................... 2 6 3 FIGURE 11: STA 1140 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 1 , 3 , 5 ] ............................................. 2 7 3 FIGURE 12: STA 1140 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 1, 3, 5] ......................................... 2 8 3 FIGURE 13: STA 1140 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 1-2] .... 2 9 3 FIGURE 14: STA 1140 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 1-2] .... 3 0 8 FIGURE 15: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 2] . . 323 FIGURE 16: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 2] . 331 FIGURE 17: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 1] . . 338 FIGURE 18: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 1] . 345 FIGURE 19: STA 1160 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 1-2] ............................................... 3 5 2 FIGURE 20: STA 1160 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 1-2] .......................................... 3 6 0 FIGURE 21: STA 1160 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 1-2] .... 3 6 8 FIGURE 22: STA 1160 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 1-2] .... 3 8 2 FIGURE 23: STA 1160 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 1-2] . 396 FIGURE 24: STA 1160 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 1-2] . 403 FIGURE 25: STA 1180 - THIS FIGURE IS DELETED (REVISION 1) .................. 4 0 9 FIGURE 26: STA 1180 - THIS FIGURE IS DELETED (REVISION 1) .................. 4 1 0 FIGURE 27: STA 1180 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE . 411 FIGURE 28: STA 1180 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE ................................................. 4 1 9 FIGURE 29: STA 1180 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE ........... 4 2 7 FIGURE 30: STA 1180 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE .......... 4 3 7 FIGURE 31: STA 1180 - THIS FIGURE IS DELETED (REVISION 1) .................. 4 4 7 FIGURE 32: STA 1180 - THIS FIGURE IS DELETED (REVISION 1) .................. 4 4 8 FIGURE 33: STA 1180 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE ........ 4 4 9 FIGURE 34: STA 1180 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE ....... 4 5 7 FIGURE 35: STA 1200 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 1-2] ............................................... 4 6 4 FIGURE 36: STA 1200 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 1-2] .......................................... 4 7 1 FIGURE 37: STA 1200 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 1-2] .... 4 7 8 FIGURE 38: STA 1200 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 1-2] .... 4 9 1 FIGURE 39: STA 1200 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 1-2] . 504 FIGURE 40: STA 1200 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 1-2] . 511 FIGURE 41: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 1-2] ............................................... 5 1 8 FIGURE 42: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 1-2] .......................................... 5 2 9 FIGURE 43: STA 1220 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 1-2] .... 5 4 0 FIGURE 44: STA 1220 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 1-2] .... 5 5 6 FIGURE 45: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 1-2] . 571 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 46: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 1-2] . 579 FIGURE 47: SHEAR PANEL INSTALLATION - LEFT SIDE [Group 1-2] ................. 5 8 7 FIGURE 48: SHEAR PANEL INSTALLATION - RIGHT SIDE [Group 1-2] ................ 5 9 6 FIGURE 49: STA 1120 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 3-5] ............................................... 6 0 5 FIGURE 50: STA 1120 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 3-5] .......................................... 6 1 3 FIGURE 51: STA 1120 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 3-5] .... 6 2 1 FIGURE 52: STA 1120 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 3-5] .... 6 3 5 FIGURE 53: STA 1120 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 3-5] . 649 FIGURE 54: STA 1120 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 3-5] . 656 FIGURE 55: STA 1140 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 3-5] .... 6 6 3 FIGURE 56: STA 1140 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 3-5] .... 6 7 6 FIGURE 57: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 3, 5] . 689 FIGURE 58: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 3, 5] . 696 FIGURE 59: STA 1160 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 3-5] ............................................... 7 0 3 FIGURE 60: STA 1160 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 3-5] .......................................... 7 1 1 FIGURE 61: STA 1160 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 3-5] .... 7 1 9 FIGURE 62: STA 1160 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 3-5] .... 7 3 3 FIGURE 63: STA 1160 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 3-5] . 747 FIGURE 64: STA 1160 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 3-5] . 754 FIGURE 65: STA 1200 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 3-5] ............................................... 7 6 1 FIGURE 66: STA 1200 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 3-5] .......................................... 7 6 8 FIGURE 67: STA 1200 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 3-5] .... 7 7 5 FIGURE 68: STA 1200 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 3-5] .... 7 8 8 FIGURE 69: STA 1200 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 3-5] . 800 FIGURE 70: STA 1200 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 3-5] . 807 FIGURE 71: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 3-4] ............................................... 8 1 4 FIGURE 72: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 3-4] .......................................... 8 2 5 FIGURE 73: STA 1220 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 3-5] .... 8 3 6 FIGURE 74: STA 1220 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 3-5] .... 8 5 0 FIGURE 75: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 3-4] . 864 FIGURE 76: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 3-4] . 872 FIGURE 77: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 5 ] ................................................ 8 7 9 FIGURE 78: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 5] ............................................ 8 9 0 FIGURE 79: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 5] . . 901 FIGURE 80: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 5] . 909 FIGURE 81: POST-MODIFICATION DETAILED INSPECTION - LEFT SIDE [Group 1-2] ....... 9 1 7 FIGURE 82: POST-MODIFICATION DETAILED INSPECTION - RIGHT SIDE [Group 1-2] ...... 9 2 3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 83: POST-MODIFICATION DETAILED INSPECTION - LEFT SIDE [Group 3-5] ....... 9 2 9 FIGURE 84: POST-MODIFICATION DETAILED INSPECTION - RIGHT SIDE [Group 3-5] ...... 9 3 5 FIGURE 85: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 4] . . 941 FIGURE 86: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 4] . 949 FIGURE 87: SURFACE HFEC INSPECTION OF TENSION TIE CENTER SECTIONS - STA 1120 TO STA 1220 .............................................. 9 5 7 FIGURE 88: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1120 - LEFT SIDE [Group 1-2] ................................................. 9 5 9 FIGURE 89: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1120 - RIGHT SIDE [Group 1-2] ............................................... 9 6 1 FIGURE 90: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1120 - LEFT SIDE [Group 3-5] ................................................. 9 6 3 FIGURE 91: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1120 - RIGHT SIDE [Group 3-5] ............................................... 9 6 5 FIGURE 92: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1140 - LEFT SIDE [Group 1-2] ................................................. 9 6 7 FIGURE 93: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1140 - RIGHT SIDE [Group 1-2] ............................................... 9 6 9 FIGURE 94: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1140 - LEFT SIDE [Group 3-5] ................................................. 9 7 1 FIGURE 95: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1140 - RIGHT SIDE [Group 3-5] ............................................... 9 7 3 FIGURE 96: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1160 - LEFT SIDE [Group 1-2] ................................................. 9 7 5 FIGURE 97: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1160 - RIGHT SIDE [Group 1-2] ............................................... 9 7 7 FIGURE 98: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1160 - LEFT SIDE [Group 3-5] ................................................. 9 7 9 FIGURE 99: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1160 - RIGHT SIDE [Group 3-5] ............................................... 9 8 1 FIGURE 100: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1180 - LEFT SIDE . . . 983 FIGURE 101: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1180 - RIGHT SIDE . . 985 FIGURE 102: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1200 - LEFT SIDE [Group 1-2] ................................................. 9 8 7 FIGURE 103: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1200 - RIGHT SIDE [Group 1-2] ............................................... 9 8 9 FIGURE 104: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1200 - LEFT SIDE [Group 3-5] ................................................. 9 9 1 FIGURE 105: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1200 - RIGHT SIDE [Group 3-5] ............................................... 9 9 3 FIGURE 106: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1220 - LEFT SIDE [Group 1-2] ................................................. 9 9 5 FIGURE 107: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1220 - RIGHT SIDE [Group 1-2] ............................................... 9 9 7 FIGURE 108: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1220 - LEFT SIDE [Group 3-4] ................................................. 9 9 9 FIGURE 109: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1220 - RIGHT SIDE [Group
3-4]1001
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 110: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1220 - LEFT SIDE [Group 5]
.1003
FIGURE 111: POST-MODIFICATION EDDY CURRENT INSPECTIONS - STA 1220 - RIGHT SIDE [Group 5]
.1005
APPENDIX A: METHOD TO DISCONNECT TENSION TIES1007
APPENDIX B: RE-INSTALLATION OF WIRE BRACKETS IN TENSION TIE SPLICE AREAS1009
APPENDIX C: REPLACEMENT OF NYLON WIRE SUPPORTS IN TENSION TIE SPLICE AREAS . . 1011
APPENDIX D: PROCEDURE FOR ALTERNATE TENSION TIE SPLICE NEAR BL 01013
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 08, 2009 747-53A2559Revision 2: May 13, 2014 7 of 1014 BOEING SERVICE BULLETIN 747-53A2559
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Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 08, 2009 747-53A2559Revision 2: May 13, 2014 8 of 1014 BOEING SERVICE BULLETIN 747-53A2559
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Commercial Airplanes 747 Service Bulletin ALERT Revision Transmittal SheetNumber: 747-53A2559Original Issue: January 08, 2009 Revision 2: May 13, 2014 ATA System: 5312 SUBJECT: FUSELAGE - Main Frame - Center Section - Tension Tie and Frame - Modification - Stretched Upper Deck Airplanes This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-15-13 is related to this service bulletin.
More work is necessary on airplanes modified in accordance with the original issue or Revision 1 of this service bulletin. Airplanes previously modified in accordance with this service bulletin will require surface high frequency eddy current (HFEC) inspection for cracks in the forward and aft tension tie channels around fasteners in unmodified areas where fastener holes were not zero-timed during modification. Refer to Paragraph 1.E., Compliance for compliance information related to the additional inspection. No additional modification is necessary.
REASON FOR REVISION This revision is sent to add the requirement to do surface high frequency eddy current (HFEC) inspection where fastener holes are not zero-timed during modification. Revision 2 also adds instructions for post-modification eddy current inspections of modified tension ties.
These sections were changed:
1. In the Summary: Updated the Background section with new Service Related Problem (SRP), Fleet Team Digest (FTD), and Planning Data information. Also, updated the Action section, and revised Compliance section with current Airworthiness Directive (AD) information.
2. In Paragraph 1.A., Effectivity: Revised the Group/Configuration table to specify configurations for airplanes that were previously modified, or not previously modified, in accordance with this service bulletin. Also, removed RT743 from the effectivity because it has been converted to Large Cargo Freighter.
3. In Paragraph 1.C., Reason: Added reason for Revision 2. Updated SRP and FTD information.
4. In Paragraph 1.D., Description: Added "more work" statement related to Revision 2. Also, added description of new or revised actions.
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Original Issue: January 08, 2009 747-53A2559Revision 2: May 13, 2014 9 of 1014
5. In Paragraph 1.E., Compliance: Updated Airworthiness Directive information. Revised compliance Table 1 to apply only to initial inspection and modification. Added new compliance Table 2 for Post-Modification inspections. Added new compliance Table 3 for additional (more work) inspection requirements on airplanes that had the tension tie and frame modification accomplished in accordance with a previous revision of this service bulletin. Added new compliance Table 4 for alternative compliance time for Group 3-5 airplanes on which "Station (STA) 1120, 1160, 1200, and 1220 Alternative Inspections" are done in accordance with Service Bulletin 747-53A2507, Revision 2 or later FAA approved revision.
6. In Paragraph 1.F., Approval: Updated Alternative Method of Compliance (AMOC) statements for AD 2004-07-22 R1 and 2007-16-19. Added new AMOC statements for AD 2012-15-13 (which superseded AD 2007-23-18).
7. In Paragraph 1.G., Manpower: Updated existing manpower tables to include inspection during modification. Added new manpower estimates for post-modification eddy current inspections.
8. In Paragraph 1.J.2., Data Supplied with this Service Bulletin: Added drawings required for post-modification inspections.
9. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Added parts and materials that could be necessary for re-installation of wire bundles or wire bundle brackets at a tension tie splice after modification. Also, added parts and materials that could be necessary for re-locating a tension tie splice if an existing SRM repair interferes with the modification splice.
10. In Paragraph 3.A., General Information: Added notes 21 through 28.
11. In Paragraph 3.B., Work Instructions: In ACCESS and RESTORATION, added optional provisions for re-installation of wire bundles or wire bundle brackets that could be necessary at a tension tie splice after modification. In PART 1, added optional provision to re-locate a tension tie splice if an existing SRM repair interferes with the modification splice. Added PART 3 to give instructions for new post-modification inspection requirements. Added PART 4 to give instructions for inspection of the unmodified tension tie center sections. PART 4 is a "more work" requirement for airplanes that had the tension tie and frame modification accomplished as given in the Original Issue, or Revision 1 of this service bulletin.
12. Figure 87: This new figure has been added for surface HFEC inspection of the tension tie center sections.
13. Figures 88 through 111: These new figures have been added for post-modification eddy current inspections.
14. Appendix B and C: Have been added for optional provisions for re-installation of wire bundles or wire bundle brackets that could be necessary at a tension tie splice after modification.
15. Appendix D: Has been added for the optional provision to re-locate a tension tie splice if an existing SRM repair interferes with the modification splice.
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.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 08, 2009 747-53A2559Revision 2: May 13, 2014 10 of 1014 BOEING SERVICE BULLETIN 747-53A2559
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REVISION HISTORY January 08, 2009Original Issue:
August 04, 2011Revision 1:
May 13, 2014Revision 2:
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 08, 2009 747-53A2559Revision 2: May 13, 2014 11 of 1014 BOEING SERVICE BULLETIN 747-53A2559
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Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 08, 2009 747-53A2559Revision 2: May 13, 2014 12 of 1014 BOEING SERVICE BULLETIN 747-53A2559