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Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1360 Original Issue: June 21, 2018 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Station 277 to Station 520 and Station 727A to Station 1006, between Stringer S-10 and Stringer S-17, Inspections 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 © 2018 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Unpublished Work.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: June 21, 2018 737-53A1360 1 of 319
2.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 21, 2018 737-53A1360 2 of 319 BOEING SERVICE BULLETIN 737-53A1360
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Table of Contents
S u m m a r y9
1. PLANNING INFORMATION ........................................ 1 5 A . E f f e c t i v i t y ............................................... 1 5
1. Airplanes ............................................ 1 5 2 . S p a r e s A f f e c t e d ........................................ 2 7 B. Concurrent Requirements ...................................... 2 7 C. Reason ................................................ 2 7 D. Description .............................................. 2 8 E. Compliance .............................................. 3 1 F . A p p r o v a l ............................................... 4 5 G. Manpower .............................................. 4 6 H. Weight and Balance Changes .................................... 5 3 I. Electrical Load Data ......................................... 5 3 J . R e f e r e n c e s .............................................. 5 3
1. Existing Data: ......................................... 5 3
2. Data Supplied with this Service Bulletin: ........................... 5 4
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 5 4 K. Publications Affected ........................................ 5 6 L. Interchangeability and Intermixability of Parts ........................... 5 6 M. Software Accomplishment Summary ................................ 5 6
2. MATERIAL INFORMATION ........................................ 5 7 A. Material - Price and Availability ................................... 5 7 B. Industry Support Information .................................... 5 7 C. Parts Necessary for Each Airplane ................................. 5 7 1 . K i t s / P a r t s ............................................ 5 7
2. Parts and Materials Supplied by the Operator ........................ 5 7
3. Parts Modified and Reidentified ................................ 5 7
4. Parts Removed and Not Replaced .............................. 5 8 D. Parts Necessary to Change Spares ................................. 5 8 E. Special Tooling - Price and Availability ............................... 5 8 F. Special Tooling Necessary to do this Service Bulletin ....................... 5 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 5 9 A. GENERAL INFORMATION ..................................... 5 9 B. WORK INSTRUCTIONS ....................................... 6 2 FIGURE 1: FRAME WEB, LEFT SIDE - UPPER FRAME, SIDE FRAME AND FAI L-SAFE CHORD - INSPECTION [Group 2] .................................... 8 7 FIGURE 2: FRAME WEB, RIGHT SIDE - UPPER FRAME, SIDE FRAME AND FA IL-SAFE CHORD - INSPECTION [Group 2] .................................... 9 0 FIGURE 3: FRAME WEB, LEFT SIDE - UPPER FRAME, SIDE FRAME AND FAI L-SAFE CHORD - INSPECTION [Group 3] .................................... 9 3 FIGURE 4: FRAME WEB, RIGHT SIDE - UPPER FRAME, SIDE FRAME AND FA IL-SAFE CHORD - INSPECTION [Group 3] .................................... 9 5 FIGURE 5: FRAME WEB, LEFT SIDE - UPPER FRAME, SIDE FRAME AND FAI L-SAFE CHORD - INSPECTION [Group 4, 7] ................................... 9 8 FIGURE 6: FRAME WEB, RIGHT SIDE - UPPER FRAME, SIDE FRAME AND FA IL-SAFE CHORD - INSPECTION [Group 4, 7] .................................. 1 0 1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 7: FRAME WEB, LEFT SIDE - UPPER FRAME, SIDE FRAME AND FAI L-SAFE CHORD - INSPECTION [Group 5, 8] .................................. 1 0 4 FIGURE 8: FRAME WEB, RIGHT SIDE - UPPER FRAME, SIDE FRAME AND FA IL-SAFE CHORD - INSPECTION [Group 5, 8] .................................. 1 0 7 FIGURE 9: FRAME WEB, LEFT SIDE - UPPER FRAME, SIDE FRAME AND FAI L-SAFE CHORD - INSPECTION [Group 6, 9] .................................. 1 1 0 FIGURE 10: FRAME WEB, RIGHT SIDE - UPPER FRAME, SIDE FRAME AND F AIL-SAFE CHORD - INSPECTION [Group 6, 9] .................................. 1 1 3 FIGURE 11: UPPER FRAME WEB, LEFT SIDE - UPPERMOST FASTENER OF TH E FRAME SPLICE - INSPECTION [Group 7] .................................... 1 1 6 FIGURE 12: UPPER FRAME WEB, RIGHT SIDE - UPPERMOST FASTENER OF T HE FRAME SPLICE - INSPECTION [Group 7] .................................... 1 1 8 FIGURE 13: UPPER FRAME WEB, LEFT SIDE - UPPERMOST FASTENER OF TH E FRAME SPLICE - INSPECTION [Group 8] .................................... 1 2 0 FIGURE 14: UPPER FRAME WEB, RIGHT SIDE - UPPERMOST FASTENER OF T HE FRAME SPLICE - INSPECTION [Group 8] .................................... 1 2 3 FIGURE 15: UPPER FRAME WEB, LEFT SIDE - UPPERMOST FASTENER OF TH E FRAME SPLICE - INSPECTION [Group 9] .................................... 1 2 6 FIGURE 16: UPPER FRAME WEB, RIGHT SIDE - UPPERMOST FASTENER OF T HE FRAME SPLICE - INSPECTION [Group 9] .................................... 1 2 8 FIGURE 17: FRAME WEB, LEFT SIDE - STRINGER CUTOUT - INSPECTION [ Group 2, 4-5, 7-8] . . 130 FIGURE 18: FRAME WEB, LEFT SIDE - STRINGER CUTOUT - INSPECTION [ Group 2-9] ...... 1 3 3 FIGURE 19: FRAME WEB, RIGHT SIDE - STRINGER CUTOUT - INSPECTION [Group 2-5, 7-8] . . 136 FIGURE 20: FRAME WEB, RIGHT SIDE - STRINGER CUTOUT - INSPECTION [Group 2, 4-5, 7-8] . 139 FIGURE 21: FRAME WEB, RIGHT SIDE - STRINGER CUTOUT - INSPECTION [ G r o u p 6 , 9 ] .... 1 4 2 FIGURE 22: FRAME WEB, LEFT SIDE - STRINGER CUTOUT - INSPECTION [ G r o u p 6 , 9 ] ..... 1 4 5 FIGURE 23: FRAME WEB, RIGHT SIDE - STRINGER CUTOUT - INSPECTION [ G r o u p 6 , 9 ] .... 1 4 8 FIGURE 24: FRAME WEB, RIGHT SIDE - STRINGER CUTOUT - INSPECTION [Group 2, 4-9] . . . 151 FIGURE 25: FRAME WEB, LEFT SIDE - STRINGER CLIP ATTACHMENTS, REINFORCEMENT DOUBLER
END FASTENER ATTACHMENTS, FAIL-SAFE CHORD AT STRINGER FLANGE
ATTACHMENTS AND STRINGER FLANGE AT FAIL-SAFE CHORD ATTACHMENTS - INSPECTION [Group 2, 4-5, 7-8] ............................... 1 5 4 FIGURE 26: FRAME WEB, RIGHT SIDE - STRINGER CLIP ATTACHMENTS, REINFORCEMENT DOUBLER
END FASTENER ATTACHMENTS, FAIL-SAFE CHORD AT STRINGER FLANGE
ATTACHMENTS AND STRINGER FLANGE AT FAIL-SAFE CHORD ATTACHMENTS - INSPECTION [Group 2, 4-5, 7-8] ............................... 1 5 8 FIGURE 27: FRAME WEB, RIGHT SIDE - STRINGER CLIP ATTACHMENTS, REINFORCEMENT DOUBLER
END FASTENER ATTACHMENTS, FAIL-SAFE CHORD AT STRINGER FLANGE
ATTACHMENTS AND STRINGER FLANGE AT FAIL-SAFE CHORD ATTACHMENTS - INSPECTION [Group 2-5, 7-8] ................................ 1 6 1 FIGURE 28: FRAME WEB, LEFT SIDE - STRINGER CLIP ATTACHMENTS, REINFORCEMENT DOUBLER
END FASTENER ATTACHMENTS, FAIL-SAFE CHORD AT STRINGER FLANGE
ATTACHMENTS AND STRINGER FLANGE AT FAIL-SAFE CHORD ATTACHMENTS - INSPECTION [Group 6, 9] .................................. 1 6 5 FIGURE 29: FRAME WEB, RIGHT SIDE - STRINGER CLIP ATTACHMENTS, REINFORCEMENT DOUBLER
END FASTENER ATTACHMENTS, FAIL-SAFE CHORD AT STRINGER FLANGE
ATTACHMENTS AND STRINGER FLANGE AT FAIL-SAFE CHORD ATTACHMENTS - INSPECTION [Group 6, 9] .................................. 1 6 8 FIGURE 30: FRAME WEB, LEFT SIDE - OPEN TOOLING HOLE BETWEEN STRI NGER S-14 AND S-15 - INSPECTION [Group 2, 4-9] ................................. 1 7 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 21, 2018 737-53A1360 4 of 319 BOEING SERVICE BULLETIN 737-53A1360
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FIGURE 31: FRAME WEB, RIGHT SIDE - OPEN TOOLING HOLE BETWEEN STR INGER S-14 AND S-15
- INSPECTION [Group 2, 4-9] ................................ 1 7 4 FIGURE 32: FRAME WEB, LEFT SIDE - OPEN TOOLING HOLE BETWEEN STRI NGER S-14 AND S-15 - INSPECTION [Group 2] .................................... 1 7 6 FIGURE 33: FRAME WEB, LEFT SIDE - OPEN TOOLING HOLE BETWEEN STRI NGER S-14 AND S-15 - INSPECTION [Group 3] .................................... 1 7 8 FIGURE 34: FRAME WEB, RIGHT SIDE - OPEN TOOLING HOLE BETWEEN STR INGER S-14 AND S-15
- INSPECTION [Group 2-3] .................................. 1 8 0 FIGURE 35: FRAME WEB, LEFT SIDE - OPEN TOOLING HOLE BETWEEN STRI NGER S-14 AND S-15 - INSPECTION [Group 4] .................................... 1 8 2 FIGURE 36: FRAME WEB, RIGHT SIDE - OPEN TOOLING HOLE BETWEEN STR INGER S-14 AND S-15
- INSPECTION [Group 4] ................................... 1 8 4 FIGURE 37: FRAME WEB, LEFT SIDE - OPEN TOOLING HOLE BETWEEN STRI NGER S-14 AND S-15 - INSPECTION [Group 5] .................................... 1 8 6 FIGURE 38: FRAME WEB, RIGHT SIDE - OPEN TOOLING HOLE BETWEEN STR INGER S-14 AND S-15
- INSPECTION [Group 5] ................................... 1 8 8 FIGURE 39: FRAME WEB, LEFT SIDE - OPEN TOOLING HOLE BETWEEN STRI NGER S-14 AND S-15 - INSPECTION [Group 6] .................................... 1 9 0 FIGURE 40: FRAME WEB, RIGHT SIDE - OPEN TOOLING HOLE BETWEEN STR INGER S-14 AND S-15
- INSPECTION [Group 6] ................................... 1 9 2 FIGURE 41: FRAME WEB, LEFT SIDE - OPEN TOOLING HOLE BETWEEN STRI NGER S-14 AND S-15 - PREVENTATIVE MODIFICATION [Group 2-9] ....................... 1 9 4 FIGURE 42: FRAME WEB, RIGHT SIDE - OPEN TOOLING HOLE BETWEEN STR INGER S-14 AND S-15
- PREVENTATIVE MODIFICATION [Group 2-9] ...................... 1 9 6 FIGURE 43: FRAME WEB, LEFT SIDE - OPEN TOOLING HOLE BETWEEN STRI NGER S-14 AND S-15 - INSPECTION [Group 5] .................................... 1 9 8 FIGURE 44: FRAME WEB, RIGHT SIDE - OPEN TOOLING HOLE BETWEEN STR INGER S-14 AND S-15
- INSPECTION [Group 5] ................................... 2 0 0 FIGURE 45: FRAME WEB, LEFT SIDE - OPEN TOOLING HOLE BETWEEN STRI NGER S-14 AND S-15 - INSPECTION [Group 7] .................................... 2 0 2 FIGURE 46: FRAME WEB, RIGHT SIDE - OPEN TOOLING HOLE BETWEEN STR INGER S-14 AND S-15
- INSPECTION [Group 7] ................................... 2 0 4 FIGURE 47: FRAME WEB, LEFT SIDE - OPEN TOOLING HOLE BETWEEN STRI NGER S-14 AND S-15 - INSPECTION [Group 8] .................................... 2 0 6 FIGURE 48: FRAME WEB, RIGHT SIDE - OPEN TOOLING HOLE BETWEEN STR INGER S-14 AND S-15
- INSPECTION [Group 8] ................................... 2 0 8 FIGURE 49: FRAME WEB, LEFT SIDE - OPEN TOOLING HOLE BETWEEN STRI NGER S-14 AND S-15 - INSPECTION [Group 9] .................................... 2 1 0 FIGURE 50: FRAME WEB, RIGHT SIDE - OPEN TOOLING HOLE BETWEEN STR INGER S-14 AND S-15
- INSPECTION [Group 9] ................................... 2 1 2 FIGURE 51: UPPER FRAME WEB, LEFT SIDE - UPPERMOST FASTENER OF FRAME SPLICE BETWEEN STRINGER S-13 AND S-14 - INSPECTION [Group 7] ................... 2 1 4 FIGURE 52: UPPER FRAME WEB, RIGHT SIDE - UPPERMOST FASTENER OF FRAME SPLICE BETWEEN STRINGER S-13 AND S-14 - INSPECTION [Group 7] ................... 2 1 6 FIGURE 53: UPPER FRAME WEB, LEFT SIDE - UPPERMOST FASTENER OF TH E FRAME SPLICE BETWEEN STRINGER S-13 AND S-14 - INSPECTION [Group 8] ............ 2 1 8 FIGURE 54: UPPER FRAME WEB, RIGHT SIDE - UPPERMOST FASTENER OF T HE FRAME SPLICE BETWEEN STRINGER S-13 AND S-14 - INSPECTION [Group 8] ............ 2 2 1 FIGURE 55: UPPER FRAME WEB, LEFT SIDE - UPPERMOST FASTENER OF TH E FRAME SPLICE BETWEEN STRINGER S-13 AND S-14 - INSPECTION [Group 9] ............ 2 2 4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 21, 2018 737-53A1360 5 of 319 BOEING SERVICE BULLETIN 737-53A1360
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FIGURE 56: UPPER FRAME WEB, RIGHT SIDE - UPPERMOST FASTENER OF T HE FRAME SPLICE BETWEEN STRINGER S-13 AND S-14 - INSPECTION [Group 9] ............ 2 2 6 FIGURE 57: FRAME WEB, LEFT SIDE - STRINGER CUTOUT - INSPECTION [ G r o u p 2 ] ....... 2 2 8 FIGURE 58: FRAME WEB, RIGHT SIDE - STRINGER CUTOUT - INSPECTION [Group 2] ...... 2 3 2 FIGURE 59: FRAME WEB, LEFT SIDE - STRINGER CUTOUT - INSPECTION [ G r o u p 3 ] ....... 2 3 6 FIGURE 60: FRAME WEB, RIGHT SIDE - STRINGER CUTOUT - INSPECTION [Group 3] ...... 2 4 0 FIGURE 61: FRAME WEB, LEFT SIDE - STRINGER CUTOUT - INSPECTION [ Group 4-9] ...... 2 4 4 FIGURE 62: FRAME WEB, RIGHT SIDE - STRINGER CUTOUT - INSPECTION [Group 4-9] ..... 2 4 8 FIGURE 63: FRAME WEB, LEFT SIDE - STRINGER CUTOUT - INSPECTION [ Group 4-5, 7-8] . . . 252 FIGURE 64: FRAME WEB, RIGHT SIDE - STRINGER CUTOUT - INSPECTION [Group 4-5, 7-8] . . 255 FIGURE 65: FRAME, RIGHT SIDE - INTEGRAL INBOARD CHORD AND WEB - INSPECTION [Group 3] ................................................. 2 5 8 FIGURE 66: FRAME, LEFT SIDE - INTEGRAL INBOARD CHORD AT MOP-SILL ATTACHMENT - INSPECTION [Group 2, 4-9] ................................. 2 6 0 FIGURE 67: FRAME, RIGHT SIDE - INTEGRAL INBOARD CHORD AT MOP-SIL L ATTACHMENT - INSPECTION [Group 2, 4-9] ................................. 2 6 2 FIGURE 68: FRAME, LEFT SIDE - INTEGRAL INBOARD CHORD AT MOP-SILL ATTACHMENT - INSPECTION [Group 3] .................................... 2 6 4 FIGURE 69: FRAME, RIGHT SIDE - INTEGRAL INBOARD CHORD AT MOP-SIL L ATTACHMENT - INSPECTION [Group 3] .................................... 2 6 6 FIGURE 70: FRAME WEB, LEFT SIDE - FASTENER LOCATIONS COMMON TO T HE CREASE BEAM CLIPS AT STRINGER S-17 - INSPECTION [Group 2, 4-9] ................. 2 6 8 FIGURE 71: FRAME WEB, RIGHT SIDE - FASTENER LOCATIONS COMMON TO THE CREASE BEAM CLIPS AT STRINGER S-17 - INSPECTION [Group 2, 4-9] ................. 2 7 3 FIGURE 72: FRAME WEB, LEFT SIDE - FASTENER LOCATIONS COMMON TO T HE CREASE BEAM CLIPS AT STRINGER S-17 - INSPECTION [Group 3] ................... 2 7 8 FIGURE 73: FRAME WEB, RIGHT SIDE - FASTENER LOCATIONS COMMON TO THE CREASE BEAM CLIPS AT STRINGER S-17 - INSPECTION [Group 3] ................... 2 8 3 APPENDIX A: TYPICAL FRAME CONSTRUCTION AND COMPONENT IDENTIFICATI O N ...... 2 8 8 APPENDIX B: LOGIC DIAGRAM FOR TABLE 2 OF PARAGRAPH 1.E. COMPLIANCE: INSPECTION OF THE
FUSELAGE UPPER FRAME, SIDE FRAME AND FAIL-SAFE CHORD, BETWEEN STRINGER S-10 AND S-17, LEFT AND RIGHT SIDE [Group 2-9] ................... 2 9 2 APPENDIX C: LOGIC DIAGRAM FOR TABLE 3 OF PARAGRAPH 1.E. COMPLIANCE: INSPECTION OF THE FUSELAGE FRAME WEB STRINGER CUTOUT AT STA 277 AND FROM STA 360 TO STA 500, LEFT AND RIGHT SIDE [Group 2-9] ......................... 2 9 4 APPENDIX D: LOGIC DIAGRAM FOR TABLE 4 OF PARAGRAPH 1.E. COMPLIANCE: INSPECTION OF THE
FUSELAGE FRAME WEB AT STRINGER CLIP, REINFORCEMENT DOUBLER AND STRINGER FLANGE ATTACHMENTS FROM STA 360 TO STA 500, LEFT AND RIGHT SIDE [Group 2-9] ................................................. 2 9 8 APPENDIX E: LOGIC DIAGRAM FOR TABLE 5 OF PARAGRAPH 1.E. COMPLIANCE: INSPECTION OF THE FUSELAGE FRAME WEB AT THE OPEN TOOLING HOLE BETWEEN STRINGER S-14 AND S-15 FROM STA 360 TO STA 520, LEFT AND RIGHT SIDE, FOR ANY CRACK. [Group 2-9] ................................................. 3 0 1 APPENDIX F: LOGIC DIAGRAM FOR TABLE 6 OF PARAGRAPH 1.E. COMPLIANCE: INSPECTION OF THE FUSELAGE FRAME WEB AT THE TOOLING HOLE BETWEEN STRINGER S-14 AND S-15, FROM STA 380 TO STA 520, LEFT AND RIGHT SIDE FOR ANY CRACK. [Group 5, 7-9] . 303 APPENDIX G: LOGIC DIAGRAM FOR TABLE 7 OF PARAGRAPH 1.E. COMPLIANCE: INSPECTION OF
FUSELAGE UPPER FRAME WEB UPPERMOST FASTENER OF FRAME SPLICE BETWEEN STRINGER S-13 AND S-14 FROM STA 380 TO STA 520, LEFT AND RIGHT SIDE, FOR ANY CRACK. [Group 7-9] ..................................... 3 0 5 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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APPENDIX H: LOGIC DIAGRAM FOR TABLE 8 OF PARAGRAPH 1.E. COMPLIANCE: INSPECTION OF THE FUSELAGE FRAME WEB STRINGER CUTOUT FROM STA 727A TO STA 747, LEFT AND RIGHT SIDE, FOR ANY CRACK. [Group 2-9] ....................... 3 0 8 APPENDIX I: LOGIC DIAGRAM FOR TABLE 9 OF PARAGRAPH 1.E. COMPLIANCE: INSPECTION OF THE FUSELAGE FRAME INTEGRAL INBOARD CHORD FROM STA 360 TO STA 400, RIGHT
S I D E , F O R A N Y C R A C K O R A N Y D E N T [ G r o u p 3 ]312
APPENDIX J: LOGIC DIAGRAM FOR TABLE 10 OF PARAGRAPH 1.E. COMPLIANCE: INSPECTION OF
THE FUSELAGE FRAME INTEGRAL INBOARD CHORD AT THE MOP-SILL ATTACHMENT FROM STA 727A TO STA 727B, LEFT AND RIGHT SIDE, FOR ANY CRACK. [Group 2-9] . 314 APPENDIX K: LOGIC DIAGRAM FOR TABLE 11 OF PARAGRAPH 1.E. COMPLIANCE: INSPECTION OF THE FUSELAGE FRAME WEB AT THE CREASE BEAM CLIP FROM STA 867 TO STA 907, L E F T A N D R I G H T S I D E , F O R A N Y C R A C K . [ G r o u p 2 - 9 ] ................. 3 1 7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 21, 2018 737-53A1360 7 of 319 BOEING SERVICE BULLETIN 737-53A1360
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Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 21, 2018 737-53A1360 8 of 319 BOEING SERVICE BULLETIN 737-53A1360
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Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-53A1360Original Issue: June 21, 2018 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Station 277 to Station 520 and Station 727A to Station 1006, between Stringer S-10 and Stringer S-17, Inspections
THIS DOCUMENT 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 DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER.
CONCURRENT REQUIREMENTS None.
BACKGROUND This service bulletin is sent to inspect the frames in the fuselage from STA 277 to STA 520 and STA 727A to STA 1006, between stringer S-10 and S-17 for any crack. Accomplishment of this service bulletin will mitigate the safety issue associated with frame cracking and make sure that any crack is found and repaired before reaching the critical length. Frame cracking is the result of fatigue caused by cyclic pressurization of the fuselage and flight loads. If cracks are not detected and repaired, they can grow until the frame severs. Continued operation of the airplane with multiple adjacent severed frames or the combination of a severed frame adjacent to fuselage skin chem-mill cracks could result in an uncontrolled decompression of the airplane and loss of structural integrity.
Fleet data indicates cracking is occurring in the frame web, frame integral inboard chord and fail-safe chord on multiple 737CL airplanes, multiple frame locations and multiple fatigue details. The frame cracking issues addressed in this service bulletin are summarized below.
In the frame web corner radii at the stringer cutouts for stringer S-14, S-15, S-16 and S-17, there has been 72 reports of cracking at multiple frame locations occurring between 24,802 and 73,655 total flight cycles. The cracks were 0.10 inches to 2.10 inches long.
In the frame web at the open tooling hole between stringer S-14 and S-15, there has been 1 report of cracking at STA 500D and 5 reports of cracking at STA 520 occurring between 31,624 and 65,504 total flight cycles. The cracks were 1.40 inches to 2.00 inches long.
In the frame web at the stringer clip fastener attachment at stringer S-15 and S-16, there has been 3 reports of cracking at STA 380 and 1 report of cracking at STA 500 occurring between 61,294 and 63,988 total flight cycles.
The cracks were 0.18 inches to 0.75 inches long.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 21, 2018 737-53A1360 9 of 319
In the upper frame web at the uppermost frame splice fastener between stringer S-13 and S-14 right, there has been 1 report of cracking at STA 380 occurring at 38,050 total flight cycles. The crack was 0.35 inches long.
This is the first crack reported for this frame splice configuration which is not addressed in Service Bulletin 737-53A1261. The inspections in this service bulletin will mitigate safety and address Widespread Fatigue Damage (WFD) concerns for cracking in the upper frame web at the frame splice. Refer to Boeing Service Bulletins 737-53A1261 and 737-53A1339 for reports of similar frame splice cracking and inspection requirements for the 737CL airplanes not addressed in this service bulletin.
In the frame web at the reinforcement doubler end fastener between stringer S-16 and S-17 left, there has been 1 report of cracking at STA 380 occurring at 65,083 total flight cycles. The crack was 0.60 inches long.
In the fail-safe chord flange at the fastener attachment to stringer S-16 left, there has been 1 report of cracking at STA 400 occurring at 66,286 total flight cycles. The crack was 0.34 inches long.
In the frame integral inboard chord at the mop-sill fastener attachment at stringer S-17, there has been 2 reports of cracking at STA 727A and 1 report of cracking at STA 1006 occurring between 41,107 and 63,667 total flight cycles. The cracks were from 0.10 inches to 0.75 inches long.
In the frame web at the crease beam clip fastener attachment at stringer S-17 right, there has been 1 report of cracking at STA 887 occurring at 65,804 total flight cycles. The crack was 0.37 inches long.
In the frame integral inboard chord at stringer S-16 right, there has been 1 report of cracking at STA 380 on a 737-200C airplane with 53,158 total flight cycles. The frame integral inboard chord locations opposite of the 737-200C main deck cargo door are susceptible to cargo handling loads resulting in dent and crack damage.
The crack was 3.50 inches long emanating from the dent.
In addition Boeing has received reports of cracking that has been determined not to be a safety issue but are included in the visual inspection program of this service bulletin. These crack reports are summarized below:
– In the frame shear tie bend radius and skin attachment flange between stringers S-14 and S-16 there have been numerous reports of cracking from STA 277 to STA 500 occurring between 29,485 and 68,315 total flight cycles.
– In the stringer flange at fastener attachments to the frame fa il-safe chord at stringer S-15 there has been 8 reports of cracking at STA 380 and STA 400 occurring between 40,989 and 73,386 total flight cycles.
Refer to Boeing Service Bulletins 737-53A1108, 737-53A1241, 737-53A1261 and 737-53A1339 for other reports of frame cracking and required inspections that are not addressed in this service bulletin.
Boeing Fleet Team Digest (FTD) 737-FTD-53-10004 is related to this service bulletin.
Boeing Service Related Problem (SRP) 737-SRP-53-0504 is related to this service bulletin.
The fuselage frame splices addressed in this service bulletin from STA 380 to STA 520 and STA 727A to STA 907 between stringer S-13 and S-14 have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD).
This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 21, 2018 737-53A1360 10 of 319 BOEING SERVICE BULLETIN 737-53A1360
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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 ChangesNoWeight 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 Group 1:
The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and recommends immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or not it is operated under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1 (line number 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV.
Group 2-9:
Do PART 2: Detailed and General Visual inspections of the fuselage upper frame, side frame and fail-safe chord between Stringer S-10 and S-17, from STA 277 to STA 294.5, STA 360 to STA 520, STA 727A to STA 907 and STA 1006, left and right side for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair and repeat PART 2: Detailed and General Visual inspection for any crack. If no crack is found, repeat PART 2: Detailed and General Visual inspection for any crack.
Group 2-9:
Do a general visual inspection to determine if there are any repairs in the PART 3 eddy current inspection zones.
For any repairs found contact The Boeing Company for alternative inspection(s) to this service bulletin and do the inspections(s) and any corrective actions as applicable. Do PART 3: High Frequency Eddy Current (HFEC) surface inspection at the unrepaired areas of the fuselage frame web stringer cutouts at STA 277 and from STA 360 to STA 500, left and right side for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair and repeat PART 3: HFEC surface inspection for any crack. If no crack is found, repeat PART 3: HFEC surface inspection for any crack.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 21, 2018 737-53A1360 11 of 319 BOEING SERVICE BULLETIN 737-53A1360
ALERTALERT
Group 2-9:
Do a general visual inspection to determine if there are any repairs in the PART 4 eddy current inspection zones.
For any repairs found contact The Boeing Company for alternative inspection(s) to this service bulletin and do the inspections(s) and any corrective actions as applicable. Do PART 4: Eddy Current inspection at the unrepaired areas of the fuselage frame web at stringer clip attachments, reinforcement doubler end fastener attachments, fail-safe chord at stringer flange attachments and detailed inspection of the stringer flange at the fail-safe chord attachments from STA 360 to STA 500, left and right side for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair and repeat PART 4: Eddy Current inspection for any crack.
If no crack is found, repeat PART 4: Eddy Current inspection for any crack.
Group 2-9:
Do PART 5: General Visual inspection for open tooling hole in the frame web between Stringer S-14 and S-15 from STA 360 to STA 520, left and right side. If the tooling hole is not open, contact The Boeing Company for alternative inspection(s) to this service bulletin and do the inspection(s) and any corrective actions applicable.
If the tooling hole is open, do PART 6: Open hole High Frequency Eddy Current (HFEC) inspection of the frame web at the affected open tooling hole between Stringer S-14 and S-15, left and right side, for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair and repeat PART 6: Open hole HFEC inspection for any crack. As an option, operators can do PART 7: Preventative Modification to terminate repeat inspections.
Group 5, 7-9:
Do PART 8: General Visual inspection for open tooling hole in the frame web between Stringer S-14 and S-15 from STA 380 to STA 520, left and right side. If the tooling hole is not open, no further action is required. If the tooling hole is open, contact The Boeing Company for alternative inspection(s) to this service bulletin and do the inspection(s) and any corrective actions as applicable.
Group 7-9:
Do a general visual inspection to determine if there are any repairs in the PART 9 eddy current inspection zones.
For any repairs found contact The Boeing Company for alternative inspection(s) to this service bulletin and do the inspections(s) and any corrective actions as applicable. Do PART 9: High Frequency Eddy Current (HFEC) surface inspection at the unrepaired areas of the upper frame web around the uppermost fastener of the frame splice between Stringer S-13 and S-14, from STA 380 to STA 520 and STA 727A to STA 907, left and right side, for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair and repeat PART 9: HFEC inspection for any crack. If no crack is found, repeat PART 9: HFEC inspection for any crack.
Group 2-9:
Do a general visual inspection to determine if there are any repairs in the PART 10 eddy current inspection zones. For any repairs found contact The Boeing Company for alternative inspection(s) to this service bulletin and do the inspections(s) and any corrective actions as applicable. Do PART 10: High Frequency Eddy Current (HFEC) surface inspection at the unrepaired areas of the fuselage frame web stringer cutout from STA 727A to STA 747, left and right side, for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair and repeat PART 10: HFEC inspection for any crack. If no crack is found, repeat PART 10: HFEC inspection for any crack.
Group 3:
Do PART 11: Detailed inspection of the fuselage frame integral inboard chord and web from STA 360 to STA 400, right side, for any crack or any dent If any crack or dent is found, contact The Boeing Company for repair instructions and do the repair and repeat PART 11: Detailed inspection for any crack or any dent If no crack or dent is found, repeat PART 11: Detailed inspection for any crack or any dent Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 21, 2018 737-53A1360 12 of 319 BOEING SERVICE BULLETIN 737-53A1360