# Boeing Alert Service Bulletin 747-53A2559: Revision 2

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- Document: [Boeing Alert Service Bulletin 747-53A2559](https://openairdocs.org/service-documents/boeing/747-53a2559.md)
- Title as filed: SB-747-53A2559-02
- Pages: 1014
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### Page 1

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Unpublished Work.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

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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PROPRIETARY - Copyright © Unpublished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
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ALERTALERT
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Table of Contents
Revision Transmittal Sheet ............................................ 9
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
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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
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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
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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
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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 TIES ....................... 1007
APPENDIX B: RE-INSTALLATION OF WIRE BRACKETS IN TENSION TIE SPLICE AREAS ..... 1009
APPENDIX C: REPLACEMENT OF NYLON WIRE SUPPORTS IN TENSION TIE SPLICE AREAS . . 1011
APPENDIX D: PROCEDURE FOR ALTERNATE TENSION TIE SPLICE NEAR BL 0 .......... 1013
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### Page 9

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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### Page 10

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.
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REVISION HISTORY
January 08, 2009Original Issue:
August 04, 2011Revision 1:
May 13, 2014Revision 2:
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Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
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### Page 13

Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 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 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
This service bulletin gives instructions for modification of upper deck tension ties and adjacent frame structure
on stretched upper deck (SUD) airplanes. The tension ties have been determined to be structure that is susceptible
to Widespread Fatigue Damage (WFD). WFD can cause tension ties to become severed or disconnected from
the frames. Severed or disconnected tension ties and/or frames at multiple locations could result in rapid in-flight
decompression.
For more information about WFD, refer to Boeing Service Letter 747-SL-53-088.
Service Bulletin 747-53A2507 recommends initial and repeat inspection of SUD airplane tension ties from body
station (STA) 1120 to STA 1220. Service Bulletin 747-53A2507 was issued to address multiple reports of cracks
found in tension ties and adjacent frame structure.
Additionally, for airplanes that have not already terminated the repeat inspection requirement of Service Bulletin
747-53A2610 "FUSELAGE - Main Frame - Center Section - Tension Tie Inspection, Repair, and Modification -
Stretched Upper Deck (SUD) Special Freighters", accomplishment of the modification given in this service
bulletin terminates the repeat inspection requirement of Service Bulletin 747-53A2610 for the modified areas.
Federal Aviation Administration (FAA) AD 2007-16-19 is related to Service Bulletin 747-53A2610.
Boeing Service Related Problem (SRP) 747-SRP-53-0215 and 747-SRP-53-0433 are related to this service
bulletin.
Boeing Fleet Team Digest articles 747 FTD 53-01001, 747 FTD 53-03010, and 747 FTD 53-13002 are related
to this service bulletin.
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### Page 14

The following table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION (PRR 85901-53RS)
Get access to the frame to tension tie joints at STA 1120 through STA 1220. At each station, disconnect and
remove a section of the tension tie between the frame and approximate Buttock Line (BL) 36 . For each frame,
remove a specified section of the frame above and below the tension tie attach point. After the existing frame
and tension tie structure has been removed and discarded, install new frame and tension tie structure. Do the
modification on both sides of the airplane. Do a surface high frequency eddy current (HFEC) inspection of the
unmodified center section of each tension tie where fastener holes are not zero-timed during modification.
After modification, do initial and repeat detailed inspections of the modified tension ties and the frame structure.
Also do initial and repeat eddy current inspections of the modified tension ties. Do these post-modification
inspections at the times specified in Paragraph 1.E., Compliance.
EFFECTIVITY
747-100B SUD, 747-200B, 747-300, 747-400, and 747-400D airplanes. Refer to paragraph 1.A.1, Airplanes,
for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directives AD 2004-07-22 R1, AD 2007-16-19, and AD
2012-15-13  are related to this service bulletin.
Refer to paragraph 1.E, Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspections and modifications given in this service bulletin.
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ALERTALERT

### Page 15

MANPOWER
Modification
Elapsed HoursTotal Task HoursAirplanes
149.0298.0Group 1
149.5299.0Group 2
136.5273.0Group 3
138.5277.0Group 4
139.0278.0Group 5
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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ALERTALERT

### Page 16 (OCR)

BOEING SERVICE BULLETIN 747-53A2559
ALERT  ALERT
STA
1220
STA
1120
AT THE ENDS OF EACH TENSION TIE, REMOVE AND REPLACE THE TENSION TIE
STRUCTURE OUTBOARD OF APPROXIMATE BUTTOCK LINE 36.0. DO
POST-MODIFICATION INSPECTIONS OF THE REPLACED TENSION TIE STRUCTURE AT
THE COMPLIANCE TIMES SPECIFIED IN PARAGRAPH 1.E., COMPLIANCE
STA
JNDD900080  1120
002002000
FWD
STA
1220
REMOVE AND REPLACE THE
SHEAR PANEL STRUCTURE
AT EACH TENSION TIE ATTACH JOINT, REMOVE AND REPLACE A
SECTION OF THE FRAME STRUCTURE. DO POST MODIFICATION  INSPECTIONS OF REPLACED FRAME STRUCTURE AT THE COMPLIANCE  1443791
TIMES SPECIFIED IN PARAGRAPH 1.E., COMPLIANCE
Original Issue: January 08, 2009
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### Page 17

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
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
This service bulletin is for the airplanes shown below. Refer to PRR 85901-53RS for data about
this change.
Refer to Service Bulletin Index Document D6-30300 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
NOTE: Some airplanes were delivered with Extended Upper Deck Modifications that installed
floor beams aft of STA 740. These airplanes are not the same as airplanes delivered with
a Stretched Upper Deck (SUD), which includes 747-300, 747-400 passenger airplanes,
and some 747-100 and 747-200 SUD modified airplanes.
DESCRIPTIONCONFIGURATIONGROUP
747-100B SUD/-200B/-300 Stretched Upper Deck passenger
airplanes that have not been converted by Boeing to Special Freighter
(SF) configuration. These airplanes have stow bin support fittings
installed on the STA 1140 and STA 1180 tension ties.
-1
Airplanes not modified as given in the Original Issue or Revision 1
of this service bulletin.
1
Airplanes that were modified as given in the Original Issue or Revision
1 of this service bulletin.
2
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### Page 18

DESCRIPTIONCONFIGURATIONGROUP
747-400/-400D airplanes that have not been converted by Boeing to
Boeing Converted Freighter (BCF) configuration. These airplanes
have stow bin support fittings installed on the STA 1180 tension tie.
-2
Airplanes not modified as given in the Original Issue or Revision 1
of this service bulletin.
1
Airplanes that were modified as given in the Original Issue or Revision
1 of this service bulletin.
2
747-300 airplanes that have been converted by Boeing to SF
configuration. These airplanes have stow bin support fittings installed
on the STA 1140 and STA 1180 tension ties.
-3
Airplanes not modified as given in the Original Issue or Revision 1
of this service bulletin.
1
Airplanes that were modified as given in the Original Issue or Revision
1 of this service bulletin.
2
747-400 airplanes that have been converted by Boeing to BCF
configuration as of 1/18/2013. These airplanes have stow bin support
fittings installed on the STA 1180 tension tie.
-4
Airplanes not modified as given in the Original Issue or Revision 1
of this service bulletin.
1
Airplanes that were modified as given in the Original Issue or Revision
1 of this service bulletin.
2
747-200B airplanes that were converted by Boeing to Stretched
Upper Deck configuration, then subsequently converted by Boeing
to SF configuration. These airplanes have stow bin support fittings
installed on the STA 1140 and STA 1180 tension ties.
-5
Airplanes not modified as given in the Original Issue or Revision 1
of this service bulletin.
1
Airplanes that were modified as given in the Original Issue or Revision
1 of this service bulletin.
2
Airplane Models:
747-100B SUD, 747-200B, 747-300, 747-400, 747-400D
GroupVariable Number
1RD381 - RD383
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ALERTALERT

### Page 19

GroupVariable Number
5RD601 - RD602
1RD603 - RD607
1RD721 - RD722
2RF001 - RF006
2RM001 - RM007
2RM010 - RM013
2RM021 - RM024
2RM026 - RM030
2RM036 - RM045
2RM051 - RM053
2RM071
2RM081 - RM084
2RM091
2RM096 - RM097
2RM116 - RM117
2RM126 - RM127
4RM128
2RM129 - RM132
2RM136 - RM147
2RM156 - RM158
2RM166 - RM177
2RM191 - RM192
2RM231 - RM233
2RM241 - RM246
2RM261 - RM264
2RM316 - RM318
2RM331 - RM333
2RM341
2RM351 - RM355
2RM366 - RM367
2RM401 - RM403
2RM426
2RM431
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ALERTALERT

### Page 20

GroupVariable Number
2RM441 - RM443
2RM445
2RM801 - RM803
2RM811 - RM813
1RS001 - RS002
1RS201
1RS211 - RS212
1RS221 - RS222
1RS231 - RS241
1RS251 - RS259
1RS263
1RS265 - RS268
1RS271 - RS276
1RS291 - RS292
1RS301 - RS306
1RS311 - RS320
1RS331 - RS333
1RS341 - RS342
1RS699
1RS701 - RS703
1RS711 - RS713
3RS721 - RS722
1RS731 - RS732
3RS741
1RS742
3RS743
1RS751 - RS752
1RS761
3RS762
3RS771
1RS781 - RS782
3RS786
2RT001 - RT014
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ALERTALERT

### Page 21

GroupVariable Number
4RT021 - RT022
4RT031 - RT033
2RT034 - RT035
2RT041 - RT047
4RT061
4RT071 - RT072
2RT073 - RT074
4RT075
2RT101 - RT103
2RT121
2RT131 - RT137
2RT151 - RT152
4RT161
2RT162 - RT163
4RT164
2RT165 - RT168
2RT401 - RT412
2RT431 - RT447
2RT451 - RT455
4RT456
2RT457 - RT460
4RT461
2RT462 - RT469
2RT471 - RT499
4RT501
2RT502 - RT505
4RT506 - RT510
2RT511 - RT512
4RT513
2RT514 - RT515
4RT516
2RT517
4RT518 - RT520
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ALERTALERT

### Page 22

GroupVariable Number
2RT521 - RT523
4RT524
2RT525
4RT526
2RT527
4RT528
2RT529
4RT530
2RT531 - RT535
2RT551 - RT568
2RT571
4RT572 - RT579
2RT580 - RT591
2RT601 - RT630
2RT633 - RT641
4RT642
2RT643 - RT653
4RT654 - RT657
2RT671 - RT673
2RT681 - RT682
4RT691 - RT692
2RT693 - RT699
2RT701 - RT704
2RT711 - RT717
2RT741 - RT742
2RT744 - RT750
4RT751 - RT752
2RT753 - RT757
2RT776 - RT777
4RT781 - RT782
2RT783 - RT784
2RT801 - RT803
2RT811 - RT814
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ALERTALERT

### Page 23

GroupVariable Number
2RT831 - RT836
4RT837
2RT861 - RT864
2RT877 - RT880
2RT931 - RT932
2RT945 - RT949
2RT951 - RT955
2RT966
4RT967
2RU001 - RU006
2RU016 - RU017
2RU031 - RU032
2RU051 - RU052
2RU059 - RU062
2RU081 - RU083
2RU101 - RU102
2RU121 - RU132
2RU801 - RU809
2RU831 - RU841
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions for modification of upper deck tension ties and adjacent frame
structure on stretched upper deck (SUD) airplanes. The tension ties have been determined to be
structure that is susceptible to Widespread Fatigue Damage (WFD). WFD can cause tension ties to
become severed or disconnected from the frames. Severed or disconnected tension ties and/or frames
at multiple locations could result in rapid in-flight decompression.
For more information about WFD, refer to Boeing Service Letter 747-SL-53-088.
Service Bulletin 747-53A2507 recommends initial and repeat inspection of SUD airplane tension ties
from body station (STA) 1120 to STA 1220. Service Bulletin 747-53A2507 was issued to address
multiple reports of cracks found in tension ties and adjacent frame structure.
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ALERTALERT

### Page 24

Additionally, for airplanes that have not already terminated the repeat inspection requirement of Service
Bulletin 747-53A2610 "FUSELAGE - Main Frame - Center Section - Tension Tie Inspection, Repair,
and Modification - Stretched Upper Deck (SUD) Special Freighters", accomplishment of the modification
given in this service bulletin terminates the repeat inspection requirement of Service Bulletin
747-53A2610 for the modified areas.
Federal Aviation Administration (FAA) AD 2007-16-19 is related to Service Bulletin 747-53A2610.
Boeing Service Related Problem (SRP) 747-SRP-53-0215 and 747-SRP-53-0433 are related to this
service bulletin.
Boeing Fleet Team Digest articles 747 FTD 53-01001, 747 FTD 53-03010, and 747 FTD 53-13002 are
related to this service bulletin.
Revision 1 is sent to correct the service bulletin figure that is called out for Group 1-2 modification at
STA 1140, change the washers that are required at BACB30US bolt locations, correct refinish instructions
for aluminum and steel parts, and revise the top kit for Group 4 airplanes. Several other changes have
also been made. A detailed list of changes is given in the Revision Transmittal Sheet section of Revision
1.
Subsequent to the release of Revision 1 of this service bulletin, Boeing has determined that additional
inspections are required in the center sections of the tension ties where the tension tie channels are
not replaced and where fastener holes are not zero-timed during modification.
Revision 2 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.
D. Description
Get access to the frame to tension tie joints at STA 1120 through STA 1220. At each station, disconnect
and remove a section of the tension tie between the frame and approximate Buttock Line (BL) 36 . For
each frame, remove a specified section of the frame above and below the tension tie attach point. After
the existing frame and tension tie structure has been removed and discarded, install new frame and
tension tie structure. Do the modification on both sides of the airplane. Do a surface high frequency
eddy current (HFEC) inspection of the unmodified center section of each tension tie where fastener
holes are not zero-timed during modification.
After modification, do initial and repeat detailed inspections of the modified tension ties and the frame
structure. Also do initial and repeat eddy current inspections of the modified tension ties. Do these
post-modification inspections at the times specified in Paragraph 1.E., Compliance.
Revision 1 - No more work is necessary on airplanes changed as given in the original issue of this
service bulletin.
Revision 2 - More work is necessary on airplanes modified as given in the original issue or Revision 1
of this service bulletin. Airplanes previously modified as given in 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.
The work in this service bulletin is done in the maintenance zone(s) given below.
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ALERTALERT

### Page 25

Group 1:
Affected Maintenance Zones
ZoneModel
243, 244747-100B SUD, 747-200B, 747-
300
Group 2:
Affected Maintenance Zones
ZoneModel
243, 244747-400, 747-400D
Group 3:
Affected Maintenance Zones
ZoneModel
243, 244747-300
Group 4:
Affected Maintenance Zones
ZoneModel
243, 244747-400
Group 5:
Affected Maintenance Zones
ZoneModel
243, 244747-200B
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directives AD 2004-07-22 R1, AD 2007-16-19,
and AD 2012-15-13  are related to this service bulletin.
The effective date of AD 2012-15-13 is September 12, 2012.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
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ALERTALERT

### Page 26

Group 1-5, Configuration 1:
Table 1: Tension Tie and Frame - Inspection and Modification - STA 1120 to STA 1220.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles after
the effective date
of AD 2012-15-
13.
Before 17,000
total flight cycles.
Do the tension tie and frame
structure modification from STA
1120 to STA 1220 as given in
Paragraph 3.B., Work Instruc-
tions, PART 1.
All airplanes.
(a)
AND
-Within 3,000
flight cycles after
the Revision 2
date of this ser-
vice bulletin.
Concurrently
with modification
as given in Para-
graph 3.B., Work
Instructions,
PART 1.
Do surface high frequency eddy
current (HFEC) inspections for
cracks in the tension tie center
sections as given in Paragraph
3.B., Work Instructions, PART 4.
-Before further flight.Contact Boeing for repair instruc-
tions, and do the repair.
Any crack found.
-At the times specified in Paragraph
1.E., Compliance, Table 2.
Do post-modification inspections
as given in Paragraph 1.E., Com-
pliance, Table 2.
-At the times specified in Paragraph
1.E., Compliance, Table 2.
Do post-modification inspections
as given in Paragraph 1.E., Com-
pliance, Table 2.
No crack found
and modification
has been done.
(a) Refer to compliance Table 4 for alternative compliance time for Special Freighter (SF) and Boeing Con-
verted Freighter (BCF) airplanes on which "Station (STA) 1120, 1160, 1200, and 1220 Alternative Inspec-
tions" are done in accordance with Service Bulletin 747-53A2507, Revision 2 or later FAA approved revi-
sion.
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### Page 27

Table 2: Post-Modification Inspections of Tension Ties and Frames - STA 1120 to STA 1220.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 1,000
flight cycles af-
ter the effective
date of AD
2012-15-13.
Within 8,000
flight cycles af-
ter modification
was done as
given in Para-
graph 3.B.,
Work Instruc-
tions, PART 1.
At each station location
from STA 1120 to STA
1220, do a detailed in-
spection of the entire ten-
sion tie and modified
frame structure for cracks
as given in Paragraph
3.B., Work Instructions,
PART 2. (a) (b)
Modification has been done
as given in Paragraph 3.B.,
Work Instructions, PART 1
of this service bulletin.
-Within 1,000
flight cycles af-
ter the Revision
2 date of this
service bulletin.
Within 14,000
flight cycles af-
ter modification
as given in
Paragraph 3.B.,
Work Instruc-
tions, PART 1.
Do eddy current inspec-
tions for cracks in all ar-
eas of the modified ten-
sion ties as given in
Paragraph 3.B., Work In-
structions, PART 3. (a)
-Before further flight.Contact Boeing for repair
instructions, and do the
repair.
Any crack found.
3,000 flight cycles.-At each station location
from STA 1120 to STA
1220, repeat the detailed
inspection of the entire
tension tie and modified
frame structure for cracks
as given in Paragraph
3.B., Work Instructions,
PART 2. (a) (b)
No crack found during
PART 2 inspection, or re-
pair has been done.
3,000 flight cycles.-Repeat the eddy current
inspections for cracks in
all areas of the tension
ties as given in Para-
graph 3.B., Work Instruc-
tions, PART 3. (a)
No crack found during
PART 3 inspection, or re-
pair has been done.
(a) These inspections are required only after the modification has been accomplished. Inspections before
modification should be done as given in Service Bulletin 747-53A2507.
(b) The requirement to do PART 2 inspections does not end when PART 3 inspections begin.
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### Page 28

Group 1-5, Configuration 2:
Table 3: Surface HFEC Inspection of Tension Tie Center Sections (More Work)
Compliance Time (Whichever Occurs
Later)
ActionCondition
Within 2,200
flight cycles after
the Revision 2
date of this ser-
vice bulletin.
Within 3,000 flight cycles
after accomplishment of
the modification as given
in Paragraph 3.B., Work
Instructions, PART 1.
At each station location from STA 1120
to STA 1220, do a surface HFEC inspec-
tion for cracks in the forward and aft
tension tie channels as given in Para-
graph 3.B., Work Instructions, PART 4.
All airplanes.
-Before further flight.Contact Boeing for repair instructions,
and do the repair.
Any crack found.
--No further action is required until you
begin inspections as given in Paragraph
1.E., Compliance, Table 2.
No crack found.
Group 3-5, Configuration 1:
Table 4: Tension Tie and Frame - Inspection and Modification - STA 1120 to STA 1220 - Alternative
Compliance Time
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles after
the effective date
of AD 2012-15-
13.
Within 17,000
flight cycles after
conversion to
Boeing Special
Freighter or Boe-
ing Converted
Freighter.
Do the tension tie and frame
structure modification from STA
1120 to STA 1220 as given in
Paragraph 3.B., Work Instruc-
tions, PART 1.
Airplanes on which
"Station (STA)
1120, 1160, 1200,
and 1220 Alterna-
tive Inspections"
are done in accor-
dance with Service
Bulletin 747-
53A2507, Revision
2 or later FAA ap-
proved revision.
AND
-Within 3,000
flight cycles after
the Revision 2
date of this ser-
vice bulletin.
Concurrently
with modification
as given in Para-
graph 3.B., Work
Instructions,
PART 1.
Do surface high frequency eddy
current (HFEC) inspections for
cracks in the tension tie center
sections as given in Paragraph
3.B., Work Instructions, PART 4.
-Before further flight.Contact Boeing for repair instruc-
tions, and do the repair.
Any crack found.
-At the times specified in Paragraph
1.E., Compliance, Table 2.
Do post-modification inspections
as given in Paragraph 1.E., Com-
pliance, Table 2.
-At the times specified in Paragraph
1.E., Compliance, Table 2.
Do post-modification inspections
as given in Paragraph 1.E., Com-
pliance, Table 2.
No crack found
and modification
has been done.
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F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle ACO
approves the accomplishment of the inspection and modification procedures with corresponding
compliance times specified in Tables 1-4 (as applicable) under Paragraph 1.E., "Compliance", of Service
Bulletin 747-53A2559, Revision 2, as an alternative method of compliance (AMOC) to accomplishment
of the corresponding inspection and repair requirements of Structural Significant Item (SSI) F-19A of
Supplemental Structural Inspection Document (SSID) D6-35022, Revision G, dated December 2000,
required by paragraphs (h) and (i) of AD 2004-07-22 R1. This AMOC only applies to the areas modified
as given in this service bulletin. When this service bulletin specifies contacting Boeing for repair
instructions, the repair instructions must be approved by the FAA in accordance with paragraph (l) of
the AD. All provisions of AD 2004-07-22 R1 that are not specifically referenced in this paragraph remain
fully applicable and must be complied with accordingly.
The Manager of the FAA Seattle ACO also approves the accomplishment of the inspection and
modification procedures with the corresponding compliance times specified in Tables 1-4 (as applicable)
under Paragraph 1.E., "Compliance", of Service Bulletin 747-53A2559, Revision 2, as an AMOC to
accomplishment of the inspection and corrective action requirements with corresponding compliance
times required by paragraphs (g), (h), (i), (j), (l), (m), (n) and (p) of AD 2012-15-13. This AMOC only
applies to the areas modified as given in this service bulletin. When this service bulletin specifies
contacting Boeing for repair instructions, the repair instructions must be approved by the FAA in
accordance with paragraph (r) of the AD. All provisions of AD 2012-15-13 that are not specifically
referenced in this paragraph remain fully applicable and must be complied with accordingly.
The Manager of the FAA Seattle ACO also approves the accomplishment of the inspection and
modification procedures with the corresponding compliance times specified in Tables 1-4 (as applicable)
under Paragraph 1.E., "Compliance", of Service Bulletin 747-53A2559, Revision 2, as an AMOC to the
accomplishment of the inspection and corrective action requirements with the corresponding compliance
times specified in paragraph 1.E., "Compliance", of Service Bulletin 747-53A2610, dated May 10, 2007,
required by paragraph (f) of AD 2007-16-19. This AMOC only applies to the areas modified in accordance
with this service bulletin. When this service bulletin specifies contacting Boeing for repair instructions,
the repair instructions must be approved by the FAA in accordance with paragraph (j) of the AD. All
provisions of AD 2007-16-19 that are not specifically referenced in this paragraph remain fully applicable
and must be complied with accordingly.
G. Manpower
The table below shows an estimate of the task hours necessary to do the modification and
post-modification inspection 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:
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— Time to adjust to the workplace
— Time to schedule the work
— Time to inspect the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Elapsed HoursTask HoursNumber of Per-
sons
Task
3.256.502Access
4.759.502Restoration
8.0016.00TOTAL FOR EACH AIRPLANE
Group 1-2:
Shear Panel Removal/Installation
Elapsed HoursTask HoursNumber of Per-
sons
Task
---Remove Shear Panels
2.505.002Figure 1
2.505.002Figure 2
---Install Shear Panels
2.505.002Figure 47
2.505.002Figure 48
10.0020.00TOTAL FOR EACH AIRPLANE
Group 1-2:
STA 1120 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1120 Modification - Left Side
3.006.002Figure 3
6.0012.002Figure 5
2.505.002Figure 7
---STA 1120 Modification - Right Side
3.006.002Figure 4
6.0012.002Figure 6
2.505.002Figure 8
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Group 1-2:
STA 1120 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
23.0046.00TOTAL FOR EACH AIRPLANE
Group 3-5:
STA 1120 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1120 Modification - Left Side
3.006.002Figure 49
6.0012.002Figure 51
2.254.502Figure 53
---STA 1120 Modification - Right Side
3.006.002Figure 50
6.0012.002Figure 52
2.254.502Figure 54
22.5045.00TOTAL FOR EACH AIRPLANE
Group 1:
STA 1140 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1140 Modification - Left Side
3.757.502Figure 11
6.0012.002Figure 13
3.006.002Figure 17
---STA 1140 Modification - Right Side
3.757.502Figure 12
6.0012.002Figure 14
3.006.002Figure 18
25.5051.00TOTAL FOR EACH AIRPLANE
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Group 2:
STA 1140 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1140 Modification - Left Side
3.507.002Figure 9
6.0012.002Figure 13
2.505.002Figure 15
---STA 1140 Modification - Right Side
3.507.002Figure 10
6.0012.002Figure 14
2.505.002Figure 16
24.0048.00TOTAL FOR EACH AIRPLANE
Group 3, 5:
STA 1140 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1140 Modification - Left Side
3.757.502Figure 11
6.0012.002Figure 55
2.505.002Figure 57
---STA 1140 Modification - Right Side
3.757.502Figure 12
6.0012.002Figure 56
2.505.002Figure 58
24.5049.00TOTAL FOR EACH AIRPLANE
Group 4:
STA 1140 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1140 Modification - Left Side
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Group 4:
STA 1140 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
3.507.002Figure 9
6.0012.002Figure 55
2.505.002Figure 85
---STA 1140 Modification - Right Side
3.507.002Figure 10
6.0012.002Figure 56
2.505.002Figure 86
24.5049.00TOTAL FOR EACH AIRPLANE
Group 1-2:
STA 1160 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1160 Modification - Left Side
3.006.002Figure 19
6.0012.002Figure 21
2.254.502Figure 23
---STA 1160 Modification - Right Side
3.006.002Figure 20
6.0012.002Figure 22
2.254.502Figure 24
22.5045.00TOTAL FOR EACH AIRPLANE
Group 3-5:
STA 1160 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1160 Modification - Left Side
3.006.002Figure 59
6.0012.002Figure 61
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Group 3-5:
STA 1160 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.254.502Figure 63
---STA 1160 Modification - Right Side
3.006.002Figure 60
6.0012.002Figure 62
2.254.502Figure 64
22.5045.00TOTAL FOR EACH AIRPLANE
STA 1180 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1180 Modification - Left Side
3.006.002Figure 27
4.509.002Figure 29
3.006.002Figure 33
---STA 1180 Modification - Right Side
3.006.002Figure 28
4.509.002Figure 30
3.006.002Figure 34
21.0042.00TOTAL FOR EACH AIRPLANE
Group 1-2:
STA 1200 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1200 Modification - Left Side
2.505.002Figure 35
4.759.502Figure 37
2.254.502Figure 39
---STA 1200 Modification - Right Side
2.505.002Figure 36
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Group 1-2:
STA 1200 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
4.759.502Figure 38
2.254.502Figure 40
19.0038.00TOTAL FOR EACH AIRPLANE
Group 3-5:
STA 1200 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1200 Modification - Left Side
2.505.002Figure 65
4.759.502Figure 67
2.254.502Figure 69
---STA 1200 Modification - Right Side
2.505.002Figure 66
4.759.502Figure 68
2.254.502Figure 70
19.0038.00TOTAL FOR EACH AIRPLANE
Group 1-2:
STA 1220 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1220 Modification - Left Side
4.258.502Figure 41
4.509.002Figure 43
2.254.502Figure 45
---STA 1220 Modification - Right Side
4.258.502Figure 42
4.509.002Figure 44
2.254.502Figure 46
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Group 1-2:
STA 1220 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
22.0044.00TOTAL FOR EACH AIRPLANE
Group 3-4:
STA 1220 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1220 Modification - Left Side
3.757.502Figure 71
4.509.002Figure 73
2.254.502Figure 75
---STA 1220 Modification - Right Side
3.757.502Figure 72
4.509.002Figure 74
2.254.502Figure 76
21.0042.00TOTAL FOR EACH AIRPLANE
Group 5:
STA 1220 Inspection and Modification
Elapsed HoursTask HoursNumber of Per-
sons
Task
2.5010.004Figure 87 (Inspection)
---STA 1220 Modification - Left Side
4.258.502Figure 77
4.509.002Figure 73
3.006.002Figure 79
---STA 1220 Modification - Right Side
4.258.502Figure 78
4.509.002Figure 74
3.006.002Figure 80
23.5047.00TOTAL FOR EACH AIRPLANE
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Group 1-2:
Post-Modification Inspection - Detailed
Elapsed HoursTask HoursNumber of Per-
sons
Task
---Inspection - Left Side
1.503.002Figure 81
---Inspection - Right Side
1.503.002Figure 82
3.006.00TOTAL FOR EACH AIRPLANE
Group 3-5:
Post-Modification Inspection - Detailed
Elapsed HoursTask HoursNumber of Per-
sons
Task
---Inspection - Left Side
1.503.002Figure 83
---Inspection - Right Side
1.503.002Figure 84
3.006.00TOTAL FOR EACH AIRPLANE
Group 1-2:
Post-Modification Inspection - Eddy Current
Elapsed HoursTask HoursNumber of Per-
sons
Task
---Inspection - Left Side
4.5018.004Figure 88
4.5018.004Figure 92
4.5018.004Figure 96
4.5018.004Figure 100
4.5018.004Figure 102
4.5018.004Figure 106
---Inspection - Right Side
4.5018.004Figure 89
4.5018.004Figure 93
4.5018.004Figure 97
4.5018.004Figure 101
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Group 1-2:
Post-Modification Inspection - Eddy Current
Elapsed HoursTask HoursNumber of Per-
sons
Task
4.5018.004Figure 103
4.5018.004Figure 107
54.00216.00TOTAL FOR EACH AIRPLANE
Group 3-4:
Post-Modification Inspection - Eddy Current
Elapsed HoursTask HoursNumber of Per-
sons
Task
---Inspection - Left Side
4.5018.004Figure 90
4.5018.004Figure 94
4.5018.004Figure 98
4.5018.004Figure 100
4.5018.004Figure 104
4.5018.004Figure 108
---Inspection - Right Side
4.5018.004Figure 91
4.5018.004Figure 95
4.5018.004Figure 99
4.5018.004Figure 101
4.5018.004Figure 105
4.5018.004Figure 109
54.00216.00TOTAL FOR EACH AIRPLANE
Group 5:
Post-Modification Inspection - Eddy Current
Elapsed HoursTask HoursNumber of Per-
sons
Task
---Inspection - Left Side
4.5018.004Figure 90
4.5018.004Figure 94
4.5018.004Figure 98
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Group 5:
Post-Modification Inspection - Eddy Current
Elapsed HoursTask HoursNumber of Per-
sons
Task
4.5018.004Figure 100
4.5018.004Figure 104
4.5018.004Figure 110
---Inspection - Right Side
4.5018.004Figure 91
4.5018.004Figure 95
4.5018.004Figure 99
4.5018.004Figure 101
4.5018.004Figure 105
4.5018.004Figure 111
54.00216.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Group 1-2:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+28515.2+25.46STA 1120 modification
+26824.2+23.53STA 1140 modification
+22121.2+19.07STA 1160 modification
+22054.2+18.69STA 1180 modification
+23580.0+19.65STA 1200 modification
+20935.2+17.16STA 1220 modification
+144030.0+123.56TOTAL FOR EACH AIRPLANE
Group 3-4:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+30755.2+27.46STA 1120 modification
+26345.4+23.11STA 1140 modification
+31818.8+27.43STA 1160 modification
+22054.2+18.69STA 1180 modification
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Group 3-4:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+30900.0+25.75STA 1200 modification
+34623.6+28.38STA 1220 modification
+176497.2+123.56TOTAL FOR EACH AIRPLANE
Group 5:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+28515.2+25.46STA 1120 modification
+26824.2+23.53STA 1140 modification
+22121.2+19.07STA 1160 modification
+22054.2+18.69STA 1180 modification
+23580.0+19.65STA 1200 modification
+39759.8+32.59STA 1220 modification
+181633.4+155.03TOTAL FOR EACH AIRPLANE
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Engineering Change Memo PRR 85901-53RS
b. Boeing Service Bulletin 747-53A2507, 747-53A2610
c. Boeing Service Letter 747-SL-51-048, 747-SL-53-088
d. Boeing Service Related Problem (SRP) 747-SRP-53-0215, 747-SRP-53-0433
e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2004-07-22 R1, 2007-16-19,
2012-15-13
f. Standard Overhaul Practices Manual (SOPM) 20-41-01, 20-41-02, 20-41-05, 20-43-03
g. 747 Fleet Team Digest (FTD) 53-01001, 53-03010, 53-13002
h. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Part 6, 51-00-26
i. 747-100/200/300 Aircraft Maintenance Manual (AMM) 24-22-00, 25-21-04, 25-22-04, 25-25-01
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j. 747-100/200/300 Structural Repair Manual (SRM) 51-10-01, 51-30-09
k. 747-400 Aircraft Maintenance Manual (AMM) 24-22-00, 25-21-04, 25-22-04, 25-25-01
l. 747-400 Structural Repair Manual (SRM) 51-10-02, 51-40-09
2. Data Supplied with this Service Bulletin:
a. Drawings:
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ADCNDCN/REVSheetTitleDrawing No
--1FUSELAGE - STRETCHED UPPER DECK
TENSION TIE MODIFICATION
624U0065
-A10
--11
-A12
--13
--14
--15
-A16
--19
-A2
--20
--21
--22
--23
--24
--25
--26
-A27
-A28
--29
--3
--30
--31
--32
--33
--34
--35
--36
--37
--38
--39
--4
-A40
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ADCNDCN/REVSheetTitleDrawing No
41 - -
--42
--43
-A44
--45
--46
--47
-A48
--49
--5
--50
--51
--52
--53
-A54
--55
--56
--57
--58
--59
-A6
--60
--61
--62
--63
--64
--65
--66
--67
--68
--69
--7
--70
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ADCNDCN/REVSheetTitleDrawing No
71 - -
--72
--73
--74
--75
--76
--77
--78
--8
--9
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Fuselage - Stretched Upper Deck Tension Tie Modification144U0061
Tension Tie Instl - STA 880 - STA 1220, MOD657U7304
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. DTI requirements for the structure affected
are contained in Paragraph 1.E., Compliance of this service bulletin.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST
RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE
INFORMATION.
Group 1:
Unit Price as of
the Revision 1
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
Revision 1 date of
this Service Bul-
letin (Calendar
Days)
QTYDateNameKit Number
$576,584.006694Nov 27/07TOPKIT - TENSION
TIE MODIFICATION -
STRETCHED UPPER
DECK - (Passenger)
015U1803-2
Group 2:
Unit Price as of
the Revision 1
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
Revision 1 date of
this Service Bul-
letin (Calendar
Days)
QTYDateNameKit Number
$576,584.006694Nov 27/07TOPKIT - TENSION
TIE MODIFICATION -
STRETCHED UPPER
DECK - (Passenger)
015U1803-3
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Group 3:
Unit Price as of
the Revision 1
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
Revision 1 date of
this Service Bul-
letin (Calendar
Days)
QTYDateNameKit Number
$534,693.00669--TOPKIT - TENSION
TIE MODIFICATION -
STRETCHED UPPER
DECK - (-300 Special
Freighter)
015U1803-42
Group 4:
Unit Price as of
the Revision 1
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
Revision 1 date of
this Service Bul-
letin (Calendar
Days)
QTYDateNameKit Number
(a)(a)(a)(a)TOPKIT - TENSION
TIE MODIFICATION -
STRETCHED UPPER
DECK - (-400 Boeing
Converted Freighter)
015U1803-43
$534,693.00669--TOPKIT - TENSION
TIE MODIFICATION -
STRETCHED UPPER
DECK - (-400 Boeing
Converted Freighter)
015U1803-53
(a) 015U1803-43 topkit is no longer available. If 015U1803-43 topkit has been purchased, then the supple-
mental parts identified in paragraph 2.C.2., "Parts and Materials Supplied by the Operator" are necessary.
Group 5:
Unit Price as of
the Revision 1
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
Revision 1 date of
this Service Bul-
letin (Calendar
Days)
QTYDateNameKit Number
$537,244.00669--TOPKIT - TENSION
TIE MODIFICATION -
STRETCHED UPPER
DECK - (-200B Special
Freighter)
015U1803-55
NOTE: Due to the limited number of kits available and the long ROLT, Boeing recommends that
operators submit purchase orders 18 months in advance of performing the modification.
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
46 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 47

B. Industry Support Information
Boeing warranty remedies are not available for the inspection or modification procedures given in this
service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for
each installation figure shown in the table below.
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
Figure Kit
876521Top Kit
111111015U1803-2
111111015U1803-3
------015U1803-42
------015U1803-53
------015U1803-55
Figure Kit
181716151413Top Kit
11--11015U1803-2
--1111015U1803-3
------015U1803-42
------015U1803-53
------015U1803-55
Figure Kit
302924232221Top Kit
111111015U1803-2
111111015U1803-3
11----015U1803-42
11----015U1803-53
11----015U1803-55
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
47 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 48

Figure Kit
403938373433Top Kit
111111015U1803-2
111111015U1803-3
----11015U1803-42
----11015U1803-53
----11015U1803-55
Figure Kit
484746454443Top Kit
111111015U1803-2
111111015U1803-3
------015U1803-42
------015U1803-53
------015U1803-55
Figure Kit
565554535251Top Kit
------015U1803-2
------015U1803-3
111111015U1803-42
111111015U1803-53
111111015U1803-55
Figure Kit
646362615857Top Kit
------015U1803-2
------015U1803-3
111111015U1803-42
1111--015U1803-53
111111015U1803-55
Figure Kit
747370696867Top Kit
------015U1803-2
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
48 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 49

Figure Kit
747370696867Top Kit
------015U1803-3
111111015U1803-42
111111015U1803-53
111111015U1803-55
Figure Kit
868580797675Top Kit
------015U1803-2
------015U1803-3
----11015U1803-42
11--11015U1803-53
--11--015U1803-55
Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
876521
QTY
FLAT DOUBLER11144U0062-11
FLAT TRIPLER11144U0062-12
ALUMINUM
STRAP
1144U0062-13
ALUMINUM
STRAP
1144U0062-14
STEEL STRAP11144U0062-15
STEEL STRAP11144U0062-16
STEEL STRAP11144U0062-17
FILLER11144U0062-18
FILLER11144U0062-7
STRAP11144U0062-8
REPLACEMENT
FRAME SECTION
1144U0063-1
LOWER SPLICE
ANGLE
1144U0063-10
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
49 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 50

Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
876521
QTY
STIFFENER11144U0063-11
FWD SHEAR TIE,
S-10 TO S-10A
11144U0063-12
AFT SHEAR TIE,
S-10 TO S-10A
11144U0063-13
FWD SHEAR TIE,
S-10A TO S-11
11144U0063-14
AFT SHEAR TIE,
S-10A TO S-11
11144U0063-15
FAILSAFE CHORD
SPLICE
11144U0063-16
REPLACEMENT
CHORD
1144U0063-19
REPLACEMENT
FRAME SECTION
1144U0063-2
REPLACEMENT
CHORD
1144U0063-20
STIFFENER11144U0063-21
STIFFENER11144U0063-22
ANGLED DOU-
BLER #1
1144U0063-3
ANGLED DOU-
BLER #1
1144U0063-4
ANGLED DOU-
BLER #2
1144U0063-5
ANGLED DOU-
BLER #2
1144U0063-6
TENSION TIE
SPLICE
22144U0063-69
LOWER SPLICE
ANGLE
1144U0063-9
SHEAR TIE TEE,
S-7 TO S-8
11144U0064-1
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
50 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 51

Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
876521
QTY
SHEAR TIE TEE,
S-8 TO S-9
11144U0064-2
SHEAR TIE TEE,
S-9 TO S-10
11144U0064-4
REPLACEMENT
SPLICE TEE, S-11
TO S-12
11144U0064-5
STRINGER CLIP
TEE
22144U0064-6
TENSION TIE
STOCK SEGMENT
22144U0064-66
STRINGER CLIP
TEE
22144U0064-7
STRINGER CLIP
TEE
33144U0064-8
STRINGER CLIP
TEE
33144U0064-9
BOLT, 100 DEG
HEX DR
1313BACB30NW6K5X
BOLT-CSK. HEAD11BACB30NW6K9
HEX DRIVE BOLT1155BACB30NX6K10
BOLT44BACB30NX6K11
BOLT, PROTRUD-
ING HD
11BACB30NX6K12
BOLT, PROTRUD-
ING HD
2424BACB30NX6K3
BOLT, PROTRUD-
ING HD
33BACB30NX6K3X
BOLT, PROTRUD-
ING HD
2423BACB30NX6K4
BOLT, PROTRUD-
ING HD
1717BACB30NX6K4X
BOLT, PROTRUD-
ING HD
22BACB30NX6K4Y
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
51 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 52

Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
876521
QTY
BOLT5555BACB30NX6K5
BOLT, PROTRUD-
ING HD
1011BACB30NX6K5X
BOLT667474BACB30NX6K6
BOLT, PROTRUD-
ING HD
44BACB30NX6K6X
BOLT, PROTRUD-
ING HD
1111BACB30NX6K6Y
HI-LOK113737BACB30NX6K7
BOLT, PROTRUD-
ING HD
1010BACB30NX6K7X
BOLT, PROTRUD-
ING HD
2323BACB30NX6K8
BOLT, PROTRUD-
ING HD
34BACB30NX6K8Y
BOLT77BACB30NX6K9
BOLT, PROTRUD-
ING HD
11BACB30NX6K9X
HI-LOK5151BACB30NX8K3
HI-LOK3737BACB30NX8K4
HI LOK2626BACB30NX8K5
BOLT55BACB30NX8K6
BOLT, HEX DRIVE1414BACB30NX8K7
BOLT55BACB30US3K13Y
BOLT11BACB30US3K14Y
BOLT11BACB30US3K16Y
BOLT11BACB30US3K17Y
BOLT, 12 PT
HEAD
66BACB30US4K14
BOLT, 12 PT
HEAD
33BACB30US4K15
BOLT3031BACB30VT6K5
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
52 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 53

Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
876521
QTY
BOLT1516BACB30VT6K6
COLLAR1515BACC30AC6
COLLAR99289289BACC30BH6
COLLAR133133BACC30BH8
COLLAR4444BACC30BL6
COLLAR1414BACC30M6
FILLER11BACF3F009E020NN
FILLER11BACF3F010L036NN
FILLER, FLAT11BACF3F010T019NN
FILLER, RECTAN-
GULAR
11BACF3H09JH051HN
TAPERED FILLER44BACF3T01A10-40
SELF-LOCKING
NUT
44BACN10HR3CD
NUT66BACN10HR4CD
RIVET, UNIVER-
SAL HD
1111BACR15BB6AD4C
RIVET, UNIVER-
SAL HD
2121BACR15FT5D4C
RIVET, UNIVER-
SAL HD
2121BACR15FT5D5C
RIVET, UNIVER-
SAL HD
1313BACR15FT6D4C
RIVET1313BACR15FT6D5C
RIVET1111BACR15GF6D5
RIVET, 100 DEG4242BACR15GF6D9
RIVET, 100 DEG1313BACR15GF8D9
SHIM, LAMINAT-
ED
22BACS40R008A036F
SHIM, LAMINAT-
ED
44BACS40R008B051F
WASHER, PLAIN44BACW10BP32CD
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
53 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 54

Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
876521
QTY
WASHER, PLAIN66BACW10BP32DP
WASHER44BACW10BP32NDP
WASHER66BACW10BP4CD
WASHER99BACW10BP4DP
WASHER66BACW10BP4NDP
Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
222118171413
QTY
DOUBLER11144U0062-21
DOUBLER11144U0062-22
STRUCTURAL
STRAP
11144U0062-23
FILLER11144U0062-24
STRAP1144U0062-25
STRAP1144U0062-26
STRAP11144U0062-27
STRAP11144U0062-28
STRAP11144U0062-29
REINFORCING
STRAP
11144U0062-30
REINFORCING
STRAP
11144U0062-31
RADIUS STRAP11144U0062-32
SPACER11144U0062-33
REPLACEMENT
DOUBLER SEC-
TION
11144U0062-34
FILLER11144U0062-47
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
54 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 55

Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
222118171413
QTY
STRAP11144U0062-48
FILLER11144U0062-50
FLAT DOUBLER11144U0062-51
FLAT TRIPLER11144U0062-52
STRAP11144U0062-70
FAILSAFE CHORD
SPLICE
11144U0063-16
STIFFENER22144U0063-21
STIFFENER22144U0063-22
FWD SHEAR TIE,
S-10 TO S-10A
11144U0063-25
AFT SHEAR TIE,
S-10 TO S-10A
11144U0063-26
FWD SHEAR TIE,
S-10A TO S-11
11144U0063-27
AFT SHEAR TIE,
S-10A TO S-11
11144U0063-28
DOUBLER1144U0063-29
DOUBLER1144U0063-30
REPLACEMENT
FAILSAFE CHORD
11144U0063-31
TENSION TIE
SPLICE
22144U0063-32
STIFFENER22144U0063-33
REINFORCING
ANGLE
1144U0063-35
REINFORCING
ANGLE
1144U0063-36
REPLACEMENT
FRAME SECTION
1144U0063-37
REPLACEMENT
FRAME SECTION
1144U0063-38
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
55 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 56

Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
222118171413
QTY
REPLACEMENT
FRAME SECTION
1144U0063-41
REPLACEMENT
FRAME SECTION
1144U0063-42
ANGLED DOU-
BLER #1
1144U0063-43
ANGLED DOU-
BLER #1
1144U0063-44
ANGLED DOU-
BLER #2
1144U0063-45
ANGLED DOU-
BLER #2
1144U0063-46
AFT SHEAR TIE,
S-10A TO S-11
11144U0063-51
AFT SHEAR TIE,
S-10 TO S-10A
11144U0063-52
FWD SHEAR TIE,
S-10A TO S-11
11144U0063-53
FWD SHEAR TIE,
S-10 TO S-10A
11144U0063-54
REPLACEMENT
CHORD
1144U0063-55
REPLACEMENT
CHORD
1144U0063-56
LOWER SPLICE
ANGLE
1144U0063-57
LOWER SPLICE
ANGLE
1144U0063-58
TENSION TIE
SEGMENT STOCK
22144U0064-23
STRINGER CLIP
TEE
55144U0064-25
STRINGER CLIP
TEE
55144U0064-26
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
56 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 57

Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
222118171413
QTY
SHEAR TIE TEE,
S-8 TO S-9
11144U0064-27
SHEAR TIE TEE,
S-9 TO S-10
11144U0064-28
SHEAR TIE TEE,
S-7 TO S-8
11144U0064-41
SHEAR TIE TEE,
S-8 TO S-9
11144U0064-42
SHEAR TIE TEE,
S-9 TO S-10
11144U0064-43
REPLACEMENT
SPLICE TEE, S-11
TO S-12
1144U0064-45
REPLACEMENT
SPLICE TEE, S-11
TO S-12
1144U0064-46
STRINGER CLIP
TEE
44144U0064-6
STRINGER CLIP
TEE
44144U0064-7
STRINGER CLIP
TEE
22144U0064-8
STRINGER CLIP
TEE
22144U0064-9
BOLT, 100 DEG
HEX DR
1313BACB30NW6K7X
HEX DRIVE BOLT441919BACB30NX6K10
BOLT, PROTRUD-
ING HD
1111BACB30NX6K10X
BOLT, PROTRUD-
ING HD
11BACB30NX6K10Y
BOLT3344BACB30NX6K11
BOLT, PROTRUD-
ING HD
11BACB30NX6K11X
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 08, 2009
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57 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 58

Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
222118171413
QTY
BOLT, PROTRUD-
ING HD
33BACB30NX6K11Y
BOLT, PROTRUD-
ING HD
1144BACB30NX6K12
BOLT, PROTRUD-
ING HD
33BACB30NX6K12Y
BOLT, PROTRUD-
ING HD
33BACB30NX6K2X
BOLT, PROTRUD-
ING HD
23231818BACB30NX6K3
BOLT, PROTRUD-
ING HD
4433BACB30NX6K3X
BOLT, PROTRUD-
ING HD
30301515BACB30NX6K4
BOLT, PROTRUD-
ING HD
19194141BACB30NX6K4X
BOLT, PROTRUD-
ING HD
2222BACB30NX6K4Y
BOLT383811BACB30NX6K5
BOLT, PROTRUD-
ING HD
121345BACB30NX6K5X
BOLT, PROTRUD-
ING HD
33BACB30NX6K5Y
BOLT93945151BACB30NX6K6
BOLT, PROTRUD-
ING HD
3411BACB30NX6K6X
BOLT, PROTRUD-
ING HD
141422BACB30NX6K6Y
HI-LOK32327676BACB30NX6K7
BOLT, PROTRUD-
ING HD
8833BACB30NX6K7X
BOLT, PROTRUD-
ING HD
1133BACB30NX6K7Y
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 08, 2009
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58 of 1014
BOEING SERVICE BULLETIN 747-53A2559
ALERTALERT

### Page 59

Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
222118171413
QTY
BOLT, PROTRUD-
ING HD
18181616BACB30NX6K8
BOLT, PROTRUD-
ING HD
22BACB30NX6K8Y
BOLT1415BACB30NX6K9
BOLT, PROTRUD-
ING HD
1111BACB30NX6K9X
BOLT, PROTRUD-
ING HD
3322BACB30NX6K9Y
BOLT, PROTRUD-
ING HD
5860BACB30NX8K2
HI-LOK1616BACB30NX8K3
HI-LOK3030BACB30NX8K4
BOLT, PROTRUD-
ING HD
11BACB30NX8K4X
HI LOK1212BACB30NX8K5
BOLT, PROTRUD-
ING HD
1188BACB30NX8K5X
BOLT45BACB30NX8K6
BOLT, HEX DRIVE1414BACB30NX8K7
BOLT, PROTRUD-
ING HD
11BACB30NX8K7X
BOLT1212BACB30NX8K8
BOLT33BACB30US3K14Y
BOLT11BACB30US3K15Y
BOLT, 12 PT
HEAD
22BACB30US4K10
BOLT, 12 PT
HEAD
55BACB30US4K11
BOLT, 12 PT
HEAD
23BACB30US4K12
BOLT, 12 PT
HEAD
12BACB30US4K13
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 08, 2009
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ALERTALERT

### Page 60

Group 1:
KIT 015U1803-2
NOTES
Existing Part
NumberName
Figure
New Part Number
222118171413
QTY
BOLT, 12 PT
HEAD
33BACB30US4K14
BOLT1717BACB30VT6K5
BOLT2828BACB30VT6K6
HI-LOK2929BACB30VT6K7
COLLAR20201919BACC30AC6
COLLAR299299250250BACC30BH6
COLLAR111441461010BACC30BH8
COLLAR44443131BACC30BL6
COLLAR1313BACC30M6
FILLER11BACF3F010L036NN
FILLER, FLAT11BACF3F010M040NN
FILLER, RA-
DIUSED EDGE
1111BACF3H07RH010HN
FILLER, RECTAN-
GULAR
11BACF3H09JH053HN
TAPERED FILLER44BACF3T01A10-40
SELF-LOCKING
NUT
33BACN10HR3CD
NUT99BACN10HR4CD
RIVET, UNIVER-
SAL HD
13131111BACR15BB6AD4C
RIVET13131111BACR15GF6D5
RIVET, 100 DEG49493333BACR15GF6D8
RIVET, 100 DEG991313BACR15GF8D9
SHIM, LAMINAT-
ED
44BACS40R007B050F
SHIM, LAMINAT-
ED
22BACS40R008A036F
WASHER, PLAIN33BACW10BP32CD
WASHER, PLAIN55BACW10BP32DP
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 08, 2009
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