Boeing ASB 747-53A2559: Revision 1, text

TextPartly OCR

Some pages are OCR from a scan. OCR can misread letters and numbers.

Query with SQL

duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
  FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
  WHERE p.file_sha256 = 'ea02825ddfdd3d8794ea543bdc88af97079d419edb775f2289a6ca61dd7b6bce'
  ORDER BY p.page"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
WHERE p.file_sha256 = 'ea02825ddfdd3d8794ea543bdc88af97079d419edb775f2289a6ca61dd7b6bce'
ORDER BY p.page

Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.

Page 1Open in PDF

Commercial Airplanes 747 Service Bulletin Number: 747-53A2559 Original Issue: January 08, 2009 Revision 1: August 04, 2011 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 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.

9E991ECCN:

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: January 08, 2009 747-53A2559Revision 1: August 04, 2011 1 of 957

3.0

Page 2Open in PDF

Original Issue: January 08, 2009 747-53A2559Revision 1: August 04, 2011 2 of 957 BOEING SERVICE BULLETIN 747-53A2559

BLANK PAGE

Page 3Open in PDF

Table of Contents

Revision Transmittal Sheet7

Summary9

1. PLANNING INFORMATION ........................................ 1 3 A. Effectivity ............................................... 1 3

1. Airplanes ............................................ 1 3

2. Spares Affected ........................................ 1 8 B. Concurrent Requirements ...................................... 1 8 C. Reason ................................................ 1 8 D. Description .............................................. 1 9 E. Compliance .............................................. 2 0 F. Approval ............................................... 2 2 G. Manpower .............................................. 2 2 H. Weight and Balance Changes .................................... 3 0 I. Electrical Load Data ......................................... 3 1 J. References .............................................. 3 1

1. Existing Data: ......................................... 3 1

2. Data supplied with this Service Bulletin: ........................... 3 1

3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 3 K. Publications Affected ........................................ 3 3 L. Interchangeability and Intermixability of Parts ........................... 3 4

2. MATERIAL INFORMATION ........................................ 3 5 A. Material - Price and Availability ................................... 3 5 B. Industry Support Information .................................... 3 7 C. Parts Necessary For Each Airplane ................................. 3 7

1. Kits/Parts: ........................................... 3 7

2. Parts and Materials Supplied by the Operator: ....................... 1 5 8

3. Parts Modified and Reidentified: ............................... 1 5 9

4. Parts Removed and Not Replaced: ............................. 1 5 9 D. Parts Necessary to Change Spares ................................ 1 5 9 E. Special Tooling - Price and Availability .............................. 1 5 9 F. Special Tooling Necessary to do this Service Bulletin ...................... 1 5 9

3. ACCOMPLISHMENT INSTRUCTIONS ................................. 1 6 1 A. GENERAL INFORMATION .................................... 1 6 1 B. WORK INSTRUCTIONS ...................................... 1 6 3 FIGURE 1: REMOVE SHEAR PANEL - LEFT SIDE [Group 1-2] .................... 1 7 0 FIGURE 2: REMOVE SHEAR PANEL - RIGHT SIDE [Group 1-2] ................... 1 7 6 FIGURE 3: STA 1120 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 1-2] ............................................... 1 8 2 FIGURE 4: STA 1120 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 1-2] .......................................... 1 9 1 FIGURE 5: STA 1120 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 1-2] .... 2 0 0 FIGURE 6: STA 1120 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 1-2] .... 2 1 4 FIGURE 7: STA 1120 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 1-2] . 228 FIGURE 8: STA 1120 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 1-2] . 235

Original Issue: January 08, 2009 747-53A2559Revision 1: August 04, 2011 3 of 957 BOEING SERVICE BULLETIN 747-53A2559

Page 4Open in PDF

FIGURE 9: STA 1140 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 2 , 4 ] .............................................. 2 4 2 FIGURE 10: STA 1140 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 2, 4] .......................................... 2 5 2 FIGURE 11: STA 1140 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 1 , 3 , 5 ] ............................................. 2 6 2 FIGURE 12: STA 1140 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 1, 3, 5] ......................................... 2 7 2 FIGURE 13: STA 1140 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 1-2] .... 2 8 2 FIGURE 14: STA 1140 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 1-2] .... 2 9 7 FIGURE 15: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 2] . . 312 FIGURE 16: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 2] . 320 FIGURE 17: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 1] . . 328 FIGURE 18: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 1] . 335 FIGURE 19: STA 1160 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 1-2] ............................................... 3 4 2 FIGURE 20: STA 1160 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 1-2] .......................................... 3 5 0 FIGURE 21: STA 1160 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 1-2] .... 3 5 8 FIGURE 22: STA 1160 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 1-2] .... 3 7 2 FIGURE 23: STA 1160 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 1-2] . 386 FIGURE 24: STA 1160 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 1-2] . 393 FIGURE 25: STA 1180 - THIS FIGURE IS DELETED (REVISION 1) .................. 4 0 0 FIGURE 26: STA 1180 - THIS FIGURE IS DELETED (REVISION 1) .................. 4 0 1 FIGURE 27: STA 1180 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE . 402 FIGURE 28: STA 1180 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE ................................................. 4 1 0 FIGURE 29: STA 1180 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 1-5] .... 4 1 8 FIGURE 30: STA 1180 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 1-5] .... 4 2 8 FIGURE 31: STA 1180 - THIS FIGURE IS DELETED (REVISION 1) .................. 4 3 8 FIGURE 32: STA 1180 - THIS FIGURE IS DELETED (REVISION 1) .................. 4 3 9 FIGURE 33: STA 1180 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE ........ 4 4 0 FIGURE 34: STA 1180 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE ....... 4 4 8 FIGURE 35: STA 1200 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 1-2] ............................................... 4 5 5 FIGURE 36: STA 1200 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 1-2] .......................................... 4 6 2 FIGURE 37: STA 1200 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 1-2] .... 4 6 9 FIGURE 38: STA 1200 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 1-2] .... 4 8 1 FIGURE 39: STA 1200 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 1-2] . 493 FIGURE 40: STA 1200 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 1-2] . 500 FIGURE 41: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 1-2] ............................................... 5 0 7 FIGURE 42: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 1-2] .......................................... 5 1 8 FIGURE 43: STA 1220 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 1-2] .... 5 2 9 FIGURE 44: STA 1220 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 1-2] .... 5 4 5 FIGURE 45: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 1-2] . 560

Original Issue: January 08, 2009 747-53A2559Revision 1: August 04, 2011 4 of 957 BOEING SERVICE BULLETIN 747-53A2559

Page 5Open in PDF

FIGURE 46: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 1-2] . 568 FIGURE 47: SHEAR PANEL INSTALLATION - LEFT SIDE [Group 1-2] ................. 5 7 6 FIGURE 48: SHEAR PANEL INSTALLATION - RIGHT SIDE [Group 1-2] ................ 5 8 5 FIGURE 49: STA 1120 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 3-5] ............................................... 5 9 4 FIGURE 50: STA 1120 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 3-5] .......................................... 6 0 2 FIGURE 51: STA 1120 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 3-5] .... 6 1 0 FIGURE 52: STA 1120 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 3-5] .... 6 2 4 FIGURE 53: STA 1120 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 3-5] . 638 FIGURE 54: STA 1120 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 3-5] . 646 FIGURE 55: STA 1140 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 3-5] .... 6 5 4 FIGURE 56: STA 1140 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 3-5] .... 6 6 7 FIGURE 57: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 3, 5] . 680 FIGURE 58: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 3, 5] . 687 FIGURE 59: STA 1160 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 3-5] ............................................... 6 9 4 FIGURE 60: STA 1160 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 3-5] .......................................... 7 0 2 FIGURE 61: STA 1160 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 3-5] .... 7 1 0 FIGURE 62: STA 1160 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 3-5] .... 7 2 4 FIGURE 63: STA 1160 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 3-5] . 738 FIGURE 64: STA 1160 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 3-5] . 745 FIGURE 65: STA 1200 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 3-5] ............................................... 7 5 2 FIGURE 66: STA 1200 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 3-5] .......................................... 7 5 9 FIGURE 67: STA 1200 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 3-5] .... 7 6 6 FIGURE 68: STA 1200 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 3-5] .... 7 7 8 FIGURE 69: STA 1200 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 3-5] . 790 FIGURE 70: STA 1200 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 3-5] . 798 FIGURE 71: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 3-4] ............................................... 8 0 6 FIGURE 72: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 3-4] .......................................... 8 1 7 FIGURE 73: STA 1220 - INSTALLATION - NEW FRAME SECTION - LEFT SIDE [Group 3-5] .... 8 2 8 FIGURE 74: STA 1220 - INSTALLATION - NEW FRAME SECTION - RIGHT SIDE [Group 3-5] .... 8 4 3 FIGURE 75: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 3-4] . 858 FIGURE 76: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 3-4] . 866 FIGURE 77: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - LEFT SIDE [Group 5 ] ................................................ 8 7 4 FIGURE 78: STA 1220 - REMOVE EXISTING TENSION TIE AND FRAME STRUCTURE - RIGHT SIDE [Group 5] ............................................ 8 8 5 FIGURE 79: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 5] . . 896 FIGURE 80: STA 1220 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 5] . 904 FIGURE 81: POST MODIFICATION INSPECTION - LEFT SIDE [Group 1-2] .............. 9 1 2 FIGURE 82: POST MODIFICATION INSPECTION - RIGHT SIDE [Group 1-2] ............. 9 1 9

Original Issue: January 08, 2009 747-53A2559Revision 1: August 04, 2011 5 of 957 BOEING SERVICE BULLETIN 747-53A2559

Page 6Open in PDF

FIGURE 83: POST MODIFICATION INSPECTION - LEFT SIDE [Group 3-5] .............. 9 2 6 FIGURE 84: POST MODIFICATION INSPECTION - RIGHT SIDE [Group 3-5] ............. 9 3 3 FIGURE 85: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - LEFT SIDE [Group 4] . . 940 FIGURE 86: STA 1140 - INSTALLATION - NEW TENSION TIE SECTION - RIGHT SIDE [Group 4] . 948 Appendix A: METHOD TO DISCONNECT TENSION TIES ........................ 9 5 6

Original Issue: January 08, 2009 747-53A2559Revision 1: August 04, 2011 6 of 957 BOEING SERVICE BULLETIN 747-53A2559

Page 7Open in PDF

Commercial Airplanes 747 Service Bulletin Revision Transmittal SheetNumber: 747-53A2559Original Issue: January 08, 2009 Revision 1: August 04, 2011 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) Notice of Proposed Rule Making NPRM 2009-NM-024-AD is related to this service bulletin.

Federal Aviation Administration (FAA) Airworthiness Directives 2004-07-22 R1, 2007-16-19, and 2007-23-18 are related to this service bulletin.

No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin.

REASON FOR REVISION This revision 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.

The following sections were changed:

1. Throughout the service bulletin: Appearance, location, and format of some text and information has changed as a result of new service bulletin standards and requirements. These changes do not affect the technical content of the service bulletin and are considered minor. Therefore, these changes are not identified with a vertical line on the left edge of the page.

2. In Summary, Compliance, added a reference to the FAA NPRM.

3. In paragraph 1.A., Effectivity: Moved twenty-one (21) airplanes from Group 2 to Group 4 because they have been modified to Boeing Converted Freighter.

4. In paragraph 1.D., Description: Added maintenance zone data.

5. In paragraph 1.E., Compliance: Added a reference to the FAA NPRM and note (a) to clarify that the Part 2 inspections are required after the modification has been accomplished.

6. In paragraph 1.J.1., Existing Data, updated the reference list to add the FAA NPRM.

7. In paragraph 1.J.2., Data supplied with this Service Bulletin: Updated revision level of 624U0065, sheets 2, 6, 12, 16, 40, 44, 48, and 54.

Original Issue: January 08, 2009 747-53A2559Revision 1: August 04, 2011 7 of 957

Page 8Open in PDF

8. In paragraph 2.A., Material Price and Availability: Updated price and availability information for top kits.

Also, revised the top kit number for Group 4 airplanes. The -43 top kit has been replaced by the -53.

9. In paragraph 2.C.2., Parts and Materials Supplied by the Operator: Deleted BACS40R008C037F and associated note (d). Shim BACS40R008C037F is supplied in the Boeing Top Kit. Added BACW10BP4DP, BACW10BP32DP, BACR15GF7D( ), and note (f). Also, added supplemental parts that may be needed for Group 4 airplanes if 015U1803-43 top kit was previously purchased.

10. In paragraph 3.A., General Information: Corrected general refinish instructions for steel parts and aluminum parts.

11. In paragraph 3.B., Work Instructions - Access and Restoration: Revised the AMM reference for removal/installation of insulation.

12. In paragraph 3.B., Work Instructions - Part 1, Step 9: Corrected figure callout for Group 1-2 right side frame structure installation at STA 1140 (Figure 14 was Figure 16). Also, corrected figure callouts for Group 1, 3, and 5 left and right side tension tie structure installation at STA 1180 (Figures 27, 28, 33, and 34 were Figures 25, 26, 31, and 32, respectively).

13. In Figure 1 and 2: Corrected hole diameter for rivet installation.

14. In Figure 7, 8, 15, 16, 17, 18, 23, 24, 33, 34, 39, 40, 45, 46, 53, 54, 57, 58, 63, 64, 69, 70, 75, 76, 79, 80, 85, and 86: Changed BACW10BP4NDP and BACW10BP32NDP washers to BACW10BP4DP and BACW10BP32DP, respectively. Boeing recommends installation of "DP" washers under the nuts common to BACB30US bolts in order to ensure proper clamp-up. However, previous installations with "NDP" washers are satisfactory.

15. In Figure 25, 26, 31, and 32: These Figures are deleted. Figures 27, 28, 33, and 34 are now identified as the correct figures for Group 1, 3, and 5 tension tie removal and installation at STA 1180.

16. In Figure 51 and 52: Added unused fastener code letter "E" to comply with new service bulletin format requirements.

17. In Figure 53 and 54: Corrected quantity of BACB30US4K15.

18. In Figure 73 and 74: Corrected bolt part number (BACB30NW6K6X was BACB30NW6K5X).

19. In Appendix A: Added description for Method 1 for disconnecting tension ties. Deleted Method 2 for disconnecting tension ties. Method 1 ensures that the shape of the fuselage contour is maintained.

The data given in Information Notice 747-53A2559 IN 01 is included in this revision.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY January 08, 2009Original Issue:

August 04, 2011Revision 1:

Original Issue: January 08, 2009 747-53A2559Revision 1: August 04, 2011 8 of 957 BOEING SERVICE BULLETIN 747-53A2559

Page 9Open in PDF

Commercial Airplanes 747 Service Bulletin SummaryNumber: 747-53A2559Original Issue: January 08, 2009 Revision 1: August 04, 2011 ATA System: 5312 SUBJECT: FUSELAGE - Main Frame - Center Section - Tension Tie and Frame - Modification - Stretched Upper Deck Airplanes

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-53-088A.

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. Accomplishment of the modification in this service bulletin terminates the repeat inspection requirement of Service Bulletin 747-53A2507.

Federal Aviation Administration (FAA) Airworthiness Directive 2007-23-18 is related to Service Bulletin 747-53A2507.

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) Airworthiness Directive 2007-16-19 is related to Service Bulletin 747-53A2610.

Boeing Service Related Problem (SRP) 747-SRP-53-0215 is related to this service bulletin.

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.

Original Issue: January 08, 2009 747-53A2559Revision 1: August 04, 2011 9 of 957

Page 10Open in PDF

After modification, do initial and repeat detailed inspections of the modified tension ties and the modified frame structure at the compliance 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, Effectivity.

NOTE: For 747-200B airplanes, only airplanes that have been modified to Stretched Upper Deck are affected.

COMPLIANCE Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2009-NM-024-AD is related to this service bulletin.

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.

Federal Aviation Administration (FAA) Airworthiness Directives 2004-07-22 R1, 2007-16-19, and 2007-23-18 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.

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.

Original Issue: January 08, 2009 747-53A2559Revision 1: August 04, 2011 10 of 957 BOEING SERVICE BULLETIN 747-53A2559

Page 11OCROpen in PDF

BOEING SERVICE BULLETIN 747-53A2559 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 1120 NOD2008000 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 Revision 1: August 04, 2011 747-53A2559

Page 12Open in PDF

Original Issue: January 08, 2009 747-53A2559Revision 1: August 04, 2011 12 of 957 BOEING SERVICE BULLETIN 747-53A2559

BLANK PAGE

Pages 13–24 of 957