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 = '197a64a52da079483e4e5657e9b859d9f5d328242868b0b2e98a0d6a5f0c0f9c' 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 = '197a64a52da079483e4e5657e9b859d9f5d328242868b0b2e98a0d6a5f0c0f9c' 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.
Commercial Airplanes 737 Service Bulletin Number: 737-53A1293 Original Issue: August 13, 2008 Revision 2: August 10, 2011 ATA System: 5331 SUBJECT: FUSELAGE - Skin - Stringer S-1 and Stringer S-2R, Station 400 to Station 460 Inspection and Repair Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 13, 2008 737-53A1293Revision 2: August 10, 2011 1 of 105
4.0
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 13, 2008 737-53A1293Revision 2: August 10, 2011 2 of 105 BOEING SERVICE BULLETIN 737-53A1293
BLANK PAGE
Table of Contents
Revision Transmittal Sheet5
Summary7
1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 8 B. Concurrent Requirements ...................................... 1 8 C. Reason ................................................ 1 9 D. Description .............................................. 2 0 E. Compliance .............................................. 2 1 F. Approval ............................................... 4 3 G. Manpower .............................................. 4 3 H. Weight and Balance Changes .................................... 4 4 I. Electrical Load Data ......................................... 4 5 J. References .............................................. 4 5
1. Existing Data .......................................... 4 5
2. Data supplied with this Service Bulletin ............................ 4 6
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 4 6 K. Publications Affected ........................................ 4 6 L. Interchangeability and Intermixability of Parts ........................... 4 6
2. MATERIAL INFORMATION ........................................ 4 7 A. Material - Price and Availability ................................... 4 7 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 ........................ 4 7
3. Parts Modified and Reidentified ................................ 4 8
4. Parts Removed and Not Replaced .............................. 4 9 D. Parts Necessary to Change Spares ................................. 4 9 E. Special Tooling - Price and Availability ............................... 4 9 F. Special Tooling Necessary to do this Service Bulletin ....................... 4 9
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 5 1 A. GENERAL INFORMATION ..................................... 5 1 B. WORK INSTRUCTIONS ....................................... 5 2 FIGURE 1: THIS FIGURE DELETED AT REVISION 1 [Group 1] ..................... 5 9 FIGURE 2: EXTERNAL FUSELAGE SKIN CHEM-MILL INSPECTION - STRINGERS S-1 AND S-2R, STA 400 - STA 460 [Group 1] .................................... 6 0 FIGURE 3: THIS FIGURE DELETED AT REVISION 1 [Group 2] ..................... 6 2 FIGURE 4: EXTERNAL FUSELAGE SKIN CHEM-MILL INSPECTION - STRINGERS S-1 AND S-2R, STA 400 - STA 460 [Group 2] .................................... 6 3 FIGURE 5: FUSELAGE SKIN - CRACK REMOVAL [Group 1] ...................... 6 5 FIGURE 6: 737-300,737-400 SERIES AIRPLANE - REPAIR DOUBLER FABRICATION AND INSTALLATION [Group 1] ............................................ 6 8 FIGURE 7: EXTERNAL FUSELAGE SKIN CHEM-MILL INSPECTION AFTER REPAIR - STRINGERS S-1 AND S-2R, STA 400 - STA 460 [Group 1] .......................... 7 8
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 13, 2008 737-53A1293Revision 2: August 10, 2011 3 of 105 BOEING SERVICE BULLETIN 737-53A1293
FIGURE 8: 737-500 SERIES AIRPLANES - REPAIR DOUBLER FABRICATION AND INSTALLATION [Group 1] ............................................ 8 0 FIGURE 9: EXTERNAL FUSELAGE SKIN CHEM-MILL INSPECTION AFTER REPAIR - STRINGERS S-1 AND S-2R, STA 400 - STA 460 [Group 2] .......................... 9 1 FIGURE 10: FUSELAGE SKIN - CRACK REMOVAL [Group 2] ...................... 9 3 FIGURE 11: REPAIR DOUBLER FABRICATION AND INSTALLATION [Group 2] ............ 9 6 FIGURE 12: POST REPAIR - CRITICAL FASTENER ROW INSPECTION [Group 2] .......... 1 0 2 APPENDIX A: CHEM-MILL STEP CRACK DAMAGE CUT-OUT AND REPORT ............. 1 0 4 APPENDIX B: CHEM-MILL STEP CRACK DAMAGE REPORT ...................... 1 0 5
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 13, 2008 737-53A1293Revision 2: August 10, 2011 4 of 105 BOEING SERVICE BULLETIN 737-53A1293
Commercial Airplanes 737 Service Bulletin Revision Transmittal SheetNumber: 737-53A1293Original Issue: August 13, 2008 Revision 2: August 10, 2011 ATA System: 5331 SUBJECT: FUSELAGE - Skin - Stringer S-1 and Stringer S-2R, Station 400 to Station 460 Inspection and Repair This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION No more work is necessary on the airplanes changed in accordance with Revision 1 of this service bulletin.
REASON FOR REVISION This revision is sent to revise the group 1 repair figures and add the group 2 repair instructions and post repair inspection.
These sections were changed:
1. Summary Background information Revised.
2. Summary Action Group 1 and Group 2 information revised.
3. Summary Industry Support Information, warranty statement revised.
4. Summary Material Information revised.
5. Paragraph 1.A.1., Airplanes, paragraph added.
6. Paragraph 1.C., Reason, information revised and revision 2 reason added.
7. Paragraph 1.D., Description, Group 1 and Group 2 repair instructions revised.
8. Paragraph 1.E., Compliance, Table 1, Table 2 and Table 3 Condition column revised and note (c) added.
Table 4 Action column revised. Table 5 Condition column revised and repair compliance details, note (a) was revised and note (c) added. Table 6 added.
9. Paragraph 1.F., Approval, AMOC statement revised.
10. Paragraph 1.G., Manpower, Group 2 table revised to add repair and post repair inspection information.
11. Paragraph 1.H., Weight and Balance Changes, Table replaced with equating statement.
12. Paragraph 1.J.1., Existing Data, book references revised.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 13, 2008 737-53A1293Revision 2: August 10, 2011 5 of 105
13. Paragraph 2.A., Material - Price and Availability, paragraph added.
14. Paragraph 2.B., Industry Support Information, warranty statement revised.
15. Paragraph 2.C.2., Parts and Materials Supplied by the Operator, Group 2 table added.
16. Paragraph 3.A., General information, notes revised.
17. Paragraph 3.B., Work instructions, changed as follows:
a. PART 1 - step 5.d. and 6.d. added.
b. PART 2 - step 3 revised.
c. PART 3 - step 4.d. and 5.d. added.
d. PART 5 - caution deleted. Step 5 revised and step 6 added.
e. PART 6 - step 4 revised and step 5 added.
f. PART 7 and PART 8 added.
18. Figure 5 revised to show crack removal information only. View A and B deleted. Flag note table deleted.
View C, now view A, revised to show crack information only. Step 1 and 2 deleted. New step 2 added. Foot notes (a), (b), (c), and (d) deleted. New foot notes (a) and (d) revised.
19. Figure 6, new illustration added, new step 1 and footnotes (g) thru (j) added.
20. Figure 8, new illustration added, new step 1 and footnotes (g) thru (j)added.
21. Figure 10, Figure 11 and Figure 12 added.
22. Appendix A, Group reference deleted.
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 August 13, 2008Original Issue:
July 07, 2010Revision 1:
August 10, 2011Revision 2:
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 13, 2008 737-53A1293Revision 2: August 10, 2011 6 of 105 BOEING SERVICE BULLETIN 737-53A1293
Commercial Airplanes 737 Service Bulletin SummaryNumber: 737-53A1293Original Issue: August 13, 2008 Revision 2: August 10, 2011 ATA System: 5331 SUBJECT: FUSELAGE - Skin - Stringer S-1 and Stringer S-2R, Station 400 to Station 460 Inspection and Repair
CONCURRENT REQUIREMENTS None
BACKGROUND Accomplishment of the inspections in this service bulletin will make sure that fuselage skin cracks at stringers S-1 and S-2R, between Body Stations STA 400 and STA 460 are found and repaired. An Air Traffic Control (ATC) antenna was installed at this location at delivery on the affected airplanes. All airplanes listed in this service bulletin require inspection even if the ATC antenna has been removed. This action is necessary to find and repair fatigue cracks of the skin panels at the chem-mill steps. Continued operation with undetected skin cracks could cause unscheduled down time for repairs or possibly a decompression of the airplane.
Boeing has received several reports from multiple operators regarding fuselage skin cracks adjacent to the ATC antenna.
A total of 60 cracks have been found on Group 1 airplanes (10 inch tear strap bays); cracks have been found at both S-1 and S-2R; the affected airplanes had accumulated between 40,080 and 67,032 total flight cycles.
A total of 3 cracks have been found on Group 2 airplanes (20 inch tear strap bays); cracks have only been found at S-1, but similar cracking is possible at S-2R; the affected airplanes had accumulated between 43,565 and 44,700 total flight cycles.
Analysis by Boeing indicates that the cracks are caused by fatigue due to high tension stresses and local bending at the edge of the chem-mill pockets of the bonded skin. The cracks initiate at the inner surface of the skin and typically originate at multiple sites along the chem-mill step. Multiple site originations can result in several adjacent partial-thickness cracks. These adjacent partial-thickness cracks can be subsequently linked together before propagating through the full-thickness of the skin.
Accomplishment of the work given in this service bulletin will make sure that cracks in the fuselage skin at stringers S-1 and S-2R, between STA 400 and STA 460 are detected and repaired.
Boeing Service Related Problem (SRP) 737-SRP-53-0334 is related to this service bulletin.
Multi-Operator Message (MOM) MOM-MOM-09-0807-01B (R1) is related to this service bulletin.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 13, 2008 737-53A1293Revision 2: August 10, 2011 7 of 105
ACTION
1. Get external access to the area around the ATC antenna at stringers S-1 and S-2R, between STA 400 and STA 460.
2. Do external Detailed Inspection (DI) for cracks in the fuselage skin along the chem-mill steps at stringers S-1 and S-2R, between STA 400 and STA 460.
3. Do external Non Destructive Inspections (NDI) for cracks in the fuselage skin along the chem-mill steps at stringers S-1 and S-2R, between STA 400 and STA 460. The NDI's that can be used are Medium Frequency Eddy Current (MFEC), Magneto Optical Imaging (MOI), C-Scan or Ultrasonic Phased Array (UTPA).
4. If no crack is found, do repeat external DI and NDI for cracks in the fuselage skin along the chem-mill steps at stringers S-1 and S-2R, between STA 400 and STA 460 at intervals in accordance with Paragraph 1.E., Compliance.
5. Group 1:
If any of the following is found as a result of the external DI and NDI, contact Boeing for repair instructions, do the repair and do external DI and NDI of the fuselage skin chem-mill steps (not covered by a repair) for cracks in accordance with Paragraph 1.E., Compliance
a. Crack(s) found before 35,000 total flight cycles.
b. Crack(s) found in four or more tear strap bays.
c. Crack(s) found longer than 5 inches.
d. Crack(s) found are not contained within the skin cut-out.
If all of the following is found as a result of the external DI and NDI, do the repair, the critical fastener row inspection and repeat external DI and NDI for cracks in the fuselage skin along the chem-mill steps not covered by a repair at intervals specified in Paragraph 1.E., Compliance.
a. Crack(s) found at or after 35,000 total flight cycles.
b. Crack(s) found in three or less strap bays.
c. Crack(s) found 5 inches or shorter.
d. Crack(s) found are contained within the skin cut-out.
6. Group 2:
If any of the following is found as a result of the external DI and NDI, contact Boeing for repair instructions, do the repair and do external DI and NDI of the fuselage skin chem-mill steps (not covered by a repair) for cracks in accordance with Paragraph 1.E., Compliance.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 13, 2008 737-53A1293Revision 2: August 10, 2011 8 of 105 BOEING SERVICE BULLETIN 737-53A1293
a. Crack(s) found before 33,000 total flight cycles.
b. Crack(s) found between STA 400 and STA 420.
c. Crack(s) found between STA 440 and STA 460.
d. Crack(s) found longer than 12.5 inches.
e. Crack(s) found are not contained within the skin cut-out.
If all of the following are found as a result of the external DI and NDI, do the repair, the critical fastener row inspection and repeat external DI and NDI for cracks in the fuselage skin along the chem-mill steps not covered by a repair, at intervals specified in Paragraph 1.E., Compliance.
a. Crack(s) found at or after 33,000 total flight cycles.
b. Crack(s) found between STA 420 and STA 440.
c. Crack(s) found 12.5 inches or shorter.
d. Crack(s) found are contained within the skin cut-out.
EFFECTIVITY 737-300/-400/-500 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2008-19-03 is related to this service bulletin.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection,and repair procedures given in this service bulletin.
MANPOWER Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 13, 2008 737-53A1293Revision 2: August 10, 2011 9 of 105 BOEING SERVICE BULLETIN 737-53A1293
BOEING SERVICE BULLETIN 737-53A1293 STA 460 ... . STA 400 1000
DO DETAILED INSPECTION AND DO MFEC INSPECTION
OR MOI INSPECTION OR C-SCAN OR ULTRASONIC
PHASE ARRAY INSPECTION FOR CRACKS IN THE FUSELAGE SKIN ALONG THE CHEM-MILL STEPS.
TYPICAL CRACKS
- S-1 [LAi TER -=→ S-2R
STA STA STA STA STA STA STA 460 450 440 430 420 410 400
ATC ANTENNA
INSPECTION AREA 10 INCH TEAR STRAP BAY CONFIGURATION SHOWN 1579184 20 INCH TEAR STRAP BAY CONFIGURATION SIMILAF Original Issue: August 13, 2008 Revision 2: August 10, 2011 BOEING PROPRIETARY - 737-53A1293 Copyright © Unpublished Work - See page 1 for details. 10 of 105
Commercial Airplanes 737 Service Bulletin Number: 737-53A1293 Original Issue: August 13, 2008 Revision 2: August 10, 2011 ATA System: 5331 SUBJECT: FUSELAGE - Skin - Stringer S-1 and Stringer S-2R, Station 400 to Station 460 Inspection and Repair
1. PLANNING INFORMATION A. Effectivity
1. Airplanes Refer to Service Bulletin Index Document D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP 737 - 300/-400/-500 Airplanes, line numbers 1001 thru 2552, which had an ATC antenna installed at STA 430 at delivery, with 10 inch tear strap bays.
-1 Airplanes not inspected in accordance with the original issue of this service bulletin.
1 Airplanes inspected in accordance with the original issue of this service bulletin and the last inspection was a Detailed Inspection procedure.
2 Airplanes inspected in accordance with the original issue of this service bulletin and the last inspection was a MFEC or MOI or C-Scan Non-Destructive Inspection procedure.
3 Airplanes inspected in accordance with Boeing Multi-Operator-Message MOM-MOM-09-0807-01B (R1), dated 15-Dec-2009 and the last inspection was a Detailed Inspection procedure.
4 Airplanes inspected in accordance with Boeing Multi-Operator-Message MOM-MOM-09-0807-01B (R1), dated 15-Dec-2009 and the last inspection was a MFEC or MOI or C-Scan Non-Destructive Inspection procedure.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 13, 2008 737-53A1293Revision 2: August 10, 2011 11 of 105
DESCRIPTIONCONFIGURATIONGROUP 737 - 300/-400/-500 Airplanes, line numbers 2553 thru 3132, all of which had an ATC antenna installed at STA 430 at delivery, with 20 inch tear strap bays.
-2 Airplane Models:
737-300, 737-400, 737-500 GroupVariable Number 1PJ301 - PJ302 1PJ551 2PJ552 - PJ561 2PJ601 - PJ615 2PJ811 2PJ816 - PJ817 1PM389 - PM399 1PM401 - PM417 1PM541 - PM542 2PM543 - PM550 1PM551 - PM564 1PP048 - PP054 1PP140 - PP160 1PP198 - PP199 1PP221 1PP508 - PP517 2PP518 - PP520 1PP805 - PP808 1PP874 - PP875 2PP876 - PP877 1PP910 - PP930 1PP951 - PP952 1PP966 - PP967 1PP984 - PP990 1PP993 1PQ013 - PQ016
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 13, 2008 737-53A1293Revision 2: August 10, 2011 12 of 105 BOEING SERVICE BULLETIN 737-53A1293