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Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1339 Original Issue: August 12, 2014 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Upper Frame To Side Frame Splice at STA 360 Between Stringer 13 and Stringer 14 - Inspection, Repair or Optional Preventative Modification 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 © 2014 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Unpublished Work.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: August 12, 2014 737-53A1339 1 of 146
4.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 12, 2014 737-53A1339 2 of 146 BOEING SERVICE BULLETIN 737-53A1339
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Table of Contents
Summary5
1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 5 B. Concurrent Requirements ...................................... 1 5 C. Reason ................................................ 1 5 D. Description .............................................. 1 5 E. Compliance .............................................. 1 6 F. Approval ............................................... 1 9 G. Manpower .............................................. 1 9 H. Weight and Balance Changes .................................... 2 0 I. Electrical Load Data ......................................... 2 1 J. References .............................................. 2 1
1. Existing Data: ......................................... 2 1
2. Data Supplied with this Service Bulletin: ........................... 2 1
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 1 K. Publications Affected ........................................ 2 2 L. Interchangeability and Intermixability of Parts ........................... 2 2 M. Software Accomplishment Summary ................................ 2 2
2. MATERIAL INFORMATION ........................................ 2 3 A. Material - Price and Availability ................................... 2 3 B. Industry Support Information .................................... 2 3 C. Parts Necessary for Each Airplane ................................. 2 3
1. Kits/Parts: ........................................... 2 3
2. Parts and Materials Supplied by the Operator: ........................ 2 3
3. Parts Modified and Reidentified: ............................... 2 7
4. Parts Removed and Not Replaced: .............................. 2 7 D. Parts Necessary to Change Spares ................................. 2 7 E. Special Tooling - Price and Availability ............................... 2 7 F. Special Tooling Necessary to do this Service Bulletin ....................... 2 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 9 A. GENERAL INFORMATION ..................................... 2 9 B. WORK INSTRUCTIONS ....................................... 3 0 FIGURE 1: LEFT SIDE - INSPECT UPPER FRAME TO SIDE FRAME SPLICE ............ 3 6 FIGURE 2: RIGHT SIDE - INSPECT UPPER FRAME TO SIDE FRAME SPLICE ........... 3 9 FIGURE 3: LEFT SIDE - CUT FAIL SAFE CHORD ............................ 4 2 FIGURE 4: RIGHT SIDE - CUT FAIL SAFE CHORD ........................... 4 6 FIGURE 5: LEFT SIDE - REMOVAL SECTION OF UPPER FRAME ................... 5 0 FIGURE 6: RIGHT SIDE - REMOVAL SECTION OF UPPER FRAME .................. 5 6 FIGURE 7: LEFT SIDE - INSPECT FRAME ................................ 6 0 FIGURE 8: RIGHT SIDE - INSPECT FRAME ............................... 6 2 FIGURE 9: LEFT SIDE - MAKE REPLACEMENT SECTION - UPPER FRAME, INTERCOSTAL CLIP AND REPAIR ANGLES ....................................... 6 4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 10: RIGHT SIDE - MAKE REPLACEMENT SECTION - UPPER FRAME AND REPAIR ANGLES .................................................. 6 9 FIGURE 11: LEFT SIDE - LOCATE REPLACEMENT FRAME SECTION AND REPAIR ANGLES . . . 73 FIGURE 12: RIGHT SIDE - LOCATE REPLACEMENT FRAME SECTION AND REPAIR ANGLES . . 80 FIGURE 13: LEFT SIDE - INSTALLATION OF REPLACEMENT FRAME SECTION AND REPAIR ANGLES .................................................. 8 6 FIGURE 14: RIGHT SIDE - INSTALLATION OF REPLACEMENT FRAME SECTION AND REPAIR ANGLES .................................................. 9 3 FIGURE 15: LEFT SIDE - INSPECT FRAME ................................ 9 8 FIGURE 16: RIGHT SIDE - INSPECT FRAME .............................. 1 0 1 FIGURE 17: LEFT SIDE - MAKE MODIFICATION ANGLE AND INTERCOSTAL CLIP ......... 1 0 3 FIGURE 18: RIGHT SIDE - MAKE MODIFICATION ANGLE ....................... 1 0 6 FIGURE 19: LEFT SIDE - LOCATE MODIFICATION ANGLE AND INTERCOSTAL CLIP ....... 1 0 8 FIGURE 20: RIGHT SIDE - LOCATE MODIFICATION ANGLE ..................... 1 1 3 FIGURE 21: LEFT SIDE - INSTALLATION OF UPPER FRAME TO SIDE FRAME SPLICE, MODIFICATION ANGLE ............................................ 1 1 6 FIGURE 22: RIGHT SIDE - INSTALLATION OF UPPER FRAME TO SIDE FRAME SPLICE, MODIFICATION ANGLE ............................................ 1 2 5 FIGURE 23: LEFT SIDE - POST-REPAIR INSPECT UPPER FRAME TO SIDE FRAME SPLICE . . . 129 FIGURE 24: RIGHT SIDE - POST-REPAIR INSPECT UPPER FRAME TO SIDE FRAME SPLICE . . 133 FIGURE 25: LEFT SIDE - POST-PREVENTATIVE MODIFICATION INSPECT UPPER FRAME TO SIDE FRAME SPLICE ........................................ 1 3 7 FIGURE 26: RIGHT SIDE - POST-PREVENTATIVE MODIFICATION INSPECT UPPER FRAME TO SIDE FRAME SPLICE ........................................ 1 4 3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-53A1339Original Issue: August 12, 2014 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Upper Frame To Side Frame Splice at STA 360 Between Stringer 13 and Stringer 14 - Inspection, Repair or Optional Preventative Modification
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 to do an inspection for cracks on the upper frame, originating from the upper end fastener hole of the frame splice common to the fail safe chord at Station 360, left and right side, between stringer S-13 and stringer S-14. This service bulletin also gives instructions to do a frame repair or an optional preventative modification. Undetected cracks in the left or right side upper frame can grow in size and result in a severed frame. A severed frame combined with fuselage skin chem mill cracks, window corner cutout skin cracks or skin lap joint cracks can affect the structural integrity of the airplane and lead to an uncontrolled decompression event. Accomplishment of the inspections in accordance with this service bulletin will make sure that cracks in the frames are found. Repair of any cracks found will make sure the frame maintains structural integrity. Installation of the optional preventative modification will prevent cracks from occurring in the frame splice joints. If not corrected, frame cracks at Station 360 could adversely affect the structural integrity of the airplane.
Certain line numbers of 737 airplanes have fuselage frame configurations (Station 360 to Station 907 inclusive) that are prone to cracking at the same location on the upper frame, between stringer S-13 and stringer S-14.
The fuselage frame splice cracks were addressed in Boeing Service Bulletin 737-53A1261 for line numbers 1 to 1919.
Three operators reported cracks at frame Station 360 between stringer S-13 and stringer S-14 on airplanes with 37,826 to 42,986 flight cycles. The reported cracks ranged from 0.35 inches to 1.5 inches in length. This service bulletin is being released to address fuselage frames at Station 360, for line numbers 1920 to 2565.
Boeing Fleet Team Digest 737 FTD 53-02001 is related to this service bulletin.
Boeing Multi Operator Message (MOM) MOM-12-0937-01B is related to this service bulletin.
Boeing Service Related Problem 737-SRP-53-0387 is related to this service bulletin.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 12, 2014 737-53A1339 5 of 146
This 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 Airplane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/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 On the left and right side fuselage frames, between stringer S-13 and stringer S-14, at Station 360, do a Medium Frequency Eddy Current (MFEC) inspection or accomplish the optional preventative modification in accordance with this service bulletin. If any crack is found on the upper frame, originating from the upper end fastener hole of the frame splice common to the fail safe chord during the MFEC inspection or optional preventative modification, do the repair in accordance with this service bulletin. If no crack is found, continue with the installation of the optional preventative modification if you choose to do the optional preventative modification or continue to do the repeat inspections. The optional preventative modification may be accomplished at any time.
EFFECTIVITY 737-300/400/500 Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
COMPLIANCE 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.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection, repair or optional preventative modification given in this service bulletin.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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MANPOWER Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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BOEING SERVICE BULLETIN 737-53A1339
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OPPEF STA FRAME 360 STA 360 S-13L_ CRACK (TYPICAL) S-14L
DO A MEDIUM FREQUENCY EDDY
CURRENT INSPECTION FOR ANY CRACK ON THE UPPER FRAME AT STATION 360 BETWEEN STRINGER S-13L AND STRINGER S-14L, ORIGINATING FROM THE UPPER
END FASTENER HOLE OF THE FRAME
SPLICE, COMMON TO THE SIDE FRAME
AND FAIL SAFE CHORD
FAIL SAFE CHORI
SIDE FRAME NOTE: DOOR SURROUND STRUCTURE NOT 2260272
SHOWN FOR CLARITY Original Issue: August 12, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1339 Work - See page 1 for details. 8 of 146
BOEING SERVICE BULLETIN 737-53A1339
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STA UPPER 360 FRAME
- S-13R CRACK (TYPICAL) S-14R
DO A MEDIUM FREQUENCY EDDY
CURRENT INSPECTION FOR ANY CRACK ON THE UPPER FRAME AT STATION 360, BETWEEN STRINGER S-13R AND STRINGER S-14R, ORIGINATING FROM THE
UPPER END FASTENER HOLE OF THE
FRAME SPLICE, COMMON TO THE SIDE
FRAME AND FAIL SAFE CHORD
SIDE FRAME
• FAIL SAFE CHORD 2267939 Original Issue: August 12, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 737-53A1339 Work - See page 1 for details. 9 of 146
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1339 Original Issue: August 12, 2014 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Upper Frame To Side Frame Splice at STA 360 Between Stringer 13 and Stringer 14 - Inspection, Repair or Optional Preventative Modification
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 Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
This service bulletin is for the airplane(s) shown below.
DESCRIPTIONCONFIGURATIONGROUP Line Number 1920 to 2565-1 Airplane Models:
737-300, 737-400, 737-500 GroupVariable Number 1PJ301 - PJ302 1PJ551 - PJ552 1PM393 - PM399 1PM401 - PM417 1PM541 - PM547 1PM551 - PM564 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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GroupVariable Number 1PP149 - PP160 1PP511 - PP517 1PP874 - PP875 1PP925 - PP930 1PP988 - PP990 1PQ074 - PQ085 1PQ198 - PQ199 1PQ201 - PQ202 1PQ230 1PQ237 1PQ256 - PQ267 1PQ287 - PQ296 1PQ306 - PQ307 1PQ341 - PQ344 1PQ361 - PQ369 1PQ401 - PQ408 1PQ411 - PQ413 1PQ421 1PQ471 - PQ473 1PQ479 - PQ481 1PQ486 - PQ487 1PQ491 - PQ493 1PQ771 1PQ791 - PQ793 1PQ801 - PQ805 1PQ931 - PQ932 1PS601 - PS616 1PS631 1PS636 - PS638 1PS643 - PS644 1PS651 - PS657 1PS669 1PS691 - PS692 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 12, 2014 737-53A1339 12 of 146 BOEING SERVICE BULLETIN 737-53A1339