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Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1349 Original Issue: August 23, 2016 ATA System: 5331 SUBJECT: FUSELAGE - Skin - Inspection, Repair, and Replacement of Disbonded Fuselage Skin Panels 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 © 2016 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Unpublished Work.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.
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3.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Table of Contents
S u m m a r y7
1. PLANNING INFORMATION ........................................ 1 1 A . E f f e c t i v i t y ............................................... 1 1
1. Airplanes ............................................ 1 1 2 . S p a r e s A f f e c t e d ........................................ 3 1 B. Concurrent Requirements ...................................... 3 1 C. Reason ................................................ 3 1 D. Description .............................................. 3 2 E. Compliance .............................................. 3 3 F . A p p r o v a l ............................................... 8 4 G. Manpower .............................................. 8 5 H. Weight and Balance Changes .................................... 8 6 I. Electrical Load Data ......................................... 8 6 J . R e f e r e n c e s .............................................. 8 6
1. Existing Data: ......................................... 8 6
2. Data Supplied with this Service Bulletin: ........................... 8 6
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 8 7 K. Publications Affected ........................................ 8 7 L. Interchangeability and Intermixability of Parts ........................... 8 8 M. Software Accomplishment Summary ................................ 8 8
2. MATERIAL INFORMATION ........................................ 8 9 A. Material - Price and Availability ................................... 8 9 B. Industry Support Information .................................... 8 9 C. Parts Necessary for Each Airplane ................................. 8 9 1 . K i t s / P a r t s ............................................ 8 9
2. Parts and Materials Supplied by the Operator ........................ 8 9
3. Parts Modified and Reidentified ................................ 9 0
4. Parts Removed and Not Replaced .............................. 9 0 D. Parts Necessary to Change Spares ................................. 9 0 E. Special Tooling - Price and Availability ............................... 9 0 F. Special Tooling Necessary to do this Service Bulletin ....................... 9 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 9 1 A. GENERAL INFORMATION ..................................... 9 1 B. WORK INSTRUCTIONS ....................................... 9 3 FIGURE 1: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 1] .................................... 1 0 7 FIGURE 2: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 2] .................................... 1 1 1 FIGURE 3: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 3-4] ................................... 1 1 5 FIGURE 4: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 5-6] ................................... 1 1 9 FIGURE 5: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 7] .................................... 1 2 3 FIGURE 6: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 8-9] ................................... 1 2 7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 7: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 10-11] .................................. 1 3 1 FIGURE 8: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 12-13] .................................. 1 3 5 FIGURE 9: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 14-18] .................................. 1 3 9 FIGURE 10: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 19] ................................... 1 4 3 FIGURE 11: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 20] ................................... 1 4 7 FIGURE 12: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 21] ................................... 1 5 0 FIGURE 13: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 22] ................................... 1 5 4 FIGURE 14: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 23-24] .................................. 1 5 8 FIGURE 15: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 25] ................................... 1 6 2 FIGURE 16: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 26] ................................... 1 6 6 FIGURE 17: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 27] ................................... 1 6 9 FIGURE 18: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 28-29] .................................. 1 7 3 FIGURE 19: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 30] ................................... 1 7 7 FIGURE 20: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS AND HIGH FREQUENCY BOND TEST [Group 31] ................................... 1 8 1 FIGURE 21: OPEN HOLE INSPECTION FOR ANY CRACK AND CORROSION ON SKIN PANEL WITH D I S B O N D........................................... 1 8 4 FIGURE 22: ULTRASONIC DISBOND INSPECTION [Group 1] ..................... 1 8 9 FIGURE 23: ULTRASONIC DISBOND INSPECTION [Group 2] ..................... 1 9 2 FIGURE 24: ULTRASONIC DISBOND INSPECTION [Group 3] ..................... 1 9 5 FIGURE 25: ULTRASONIC DISBOND INSPECTION [Group 4] ..................... 1 9 8 FIGURE 26: ULTRASONIC DISBOND INSPECTION [Group 5] ..................... 2 0 3 FIGURE 27: ULTRASONIC DISBOND INSPECTION [Group 6] ..................... 2 0 6 FIGURE 28: ULTRASONIC DISBOND INSPECTION [Group 7] ..................... 2 1 1 FIGURE 29: ULTRASONIC DISBOND INSPECTION [Group 8] ..................... 2 1 6 FIGURE 30: ULTRASONIC DISBOND INSPECTION [Group 9] ..................... 2 2 1 FIGURE 31: ULTRASONIC DISBOND INSPECTION [Group 10] .................... 2 2 6 FIGURE 32: ULTRASONIC DISBOND INSPECTION [Group 11] .................... 2 3 1 FIGURE 33: ULTRASONIC DISBOND INSPECTION [Group 12] .................... 2 3 6 FIGURE 34: ULTRASONIC DISBOND INSPECTION [Group 13] .................... 2 4 1 FIGURE 35: ULTRASONIC DISBOND INSPECTION [Group 14] .................... 2 4 6 FIGURE 36: ULTRASONIC DISBOND INSPECTION [Group 15] .................... 2 5 0 FIGURE 37: ULTRASONIC DISBOND INSPECTION [Group 16] .................... 2 5 4 FIGURE 38: ULTRASONIC DISBOND INSPECTION [Group 17] .................... 2 5 8 FIGURE 39: ULTRASONIC DISBOND INSPECTION [Group 18] .................... 2 6 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 40: ULTRASONIC DISBOND INSPECTION [Group 19] .................... 2 6 6 FIGURE 41: ULTRASONIC DISBOND INSPECTION [Group 20] .................... 2 7 0 FIGURE 42: ULTRASONIC DISBOND INSPECTION [Group 21] .................... 2 7 2 FIGURE 43: ULTRASONIC DISBOND INSPECTION [Group 22] .................... 2 7 7 FIGURE 44: ULTRASONIC DISBOND INSPECTION [Group 23] .................... 2 8 2 FIGURE 45: ULTRASONIC DISBOND INSPECTION [Group 24] .................... 2 8 6 FIGURE 46: ULTRASONIC DISBOND INSPECTION [Group 25] .................... 2 9 0 FIGURE 47: ULTRASONIC DISBOND INSPECTION [Group 26] .................... 2 9 4 FIGURE 48: ULTRASONIC DISBOND INSPECTION [Group 27] .................... 2 9 6 FIGURE 49: ULTRASONIC DISBOND INSPECTION [Group 28] .................... 3 0 0 FIGURE 50: ULTRASONIC DISBOND INSPECTION [Group 29] .................... 3 0 4 FIGURE 51: ULTRASONIC DISBOND INSPECTION [Group 30] .................... 3 0 8 FIGURE 52: ULTRASONIC DISBOND INSPECTION [Group 31] .................... 3 1 2 FIGURE 53: WINDOW BELT ULTRASONIC DISBOND INSPECTION [Group 1-18, 21-24, 27-29] . . 314 FIGURE 54: INTERNAL DETAILED SKIN INSPECTION USING A FEELER GAUGE ......... 3 1 9 FIGURE 55: WINDOW BELT AREA DISBOND REPAIR [Group 1-18, 21-24, 27-29] .......... 3 2 2 FIGURE 56: INSPECTION REQUIREMENTS FOR SKIN PANELS WITH TEMPORARY DISBOND REPAIR OR EXISTING DISBOND REPAIR .............................. 3 2 7 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: EXTERNAL INSPECTION
OF FUSELAGE SKIN PANELS FOR ANY CRACK, CORROSION, EXISTING DISBOND REPAIR AND DISBOND [Group 1-11, 27] ............................... 3 3 2 APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 2: EXTERNAL INSPECTION
OF FUSELAGE SKIN PANELS FOR ANY CRACK, CORROSION, EXISTING DISBOND REPAIR AND DISBOND [Group 21] ................................. 3 3 8 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 3: EXTERNAL INSPECTION
OF FUSELAGE SKIN PANELS FOR ANY CRACK, CORROSION, EXISTING DISBOND REPAIR AND DISBOND [Group 12-18, 28-29] ............................ 3 4 4 APPENDIX D: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 4: EXTERNAL INSPECTION
OF FUSELAGE SKIN PANELS FOR ANY CRACK, CORROSION, EXISTING DISBOND REPAIR AND DISBOND [Group 22-24] ................................ 3 5 0 APPENDIX E: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 5: EXTERNAL INSPECTION
OF FUSELAGE SKIN PANELS FOR ANY CRACK, CORROSION, EXISTING DISBOND REPAIR AND DISBOND [Group 19, 30] ............................... 3 5 6 APPENDIX F: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 6: EXTERNAL INSPECTION
OF FUSELAGE SKIN PANELS FOR ANY CRACK, CORROSION, EXISTING DISBOND REPAIR AND DISBOND [Group 25] .................................. 3 6 2 APPENDIX G: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 7: EXTERNAL INSPECTION
OF FUSELAGE SKIN PANELS FOR ANY CRACK, CORROSION, EXISTING DISBOND REPAIR AND DISBOND [Group 20, 31] ................................ 3 6 8 APPENDIX H: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 8: EXTERNAL INSPECTION
OF FUSELAGE SKIN PANELS FOR ANY CRACK, CORROSION, EXISTING DISBOND REPAIR AND DISBOND [Group 26] ................................. 3 7 4 APPENDIX I: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 9: INSPECTION OF REPLACED SKIN PANELS MANUFACTURED PRIOR TO APRIL 01, 1997 AND REPLACED S K I N P A N E L S W H E R E T H E M A N U F A C T U R E D A T E I S N O T K N O W N ......... 3 8 0 APPENDIX J: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 10: INTERNAL AND EXTERNAL INSPECTION OF FUSELAGE SKIN PANELS FOR ANY DISBOND .... 3 8 7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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APPENDIX K: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 11: INSPECTION
REQUIREMENTS FOR SKIN PANELS WITH EXISTING DISBOND REPAIR OR TEMPORARY DISBOND REPAIR ...................................... 3 8 9 APPENDIX L: GROUP - FIGURE MATRIX ................................. 3 9 1 APPENDIX M: SURVEY - BOEING PART DEMAND INTENT ....................... 3 9 4 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: 737-53A1349Original Issue: August 23, 2016 ATA System: 5331 SUBJECT: FUSELAGE - Skin - Inspection, Repair, and Replacement of Disbonded Fuselage Skin Panels
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 Operators have reported skin doublers disbonded from their skin panels on several 737 airplanes. The bonded skin doublers are part of the back-up structure for the skin panels and are installed from Body Station (BS)
259.50 to 1016 on both sides of the airplane. Boeing has attributed the root cause of disbonded skin doublers to improper processing during the phosphoric acid anodization (PAA) phase of skin panel manufacturing.
Disbonding of the skin panel reduces the capability to resist cracks in the countersunk fastened joints and can lead to fuselage skin cracking, and multi-site damage (MSD) predominantly in the lap splices and butt joints. If not corrected, fuselage skin cracking resulting from disbonded skin panels can result in possible rapid decompression and loss of structural integrity.
Boeing Service Bulletin 737-53-1179 was issued in response to the discovery of improper processing during the manufacturing of skin panel assemblies. It inspects for any disbond of the fuselage skin/doubler and cracking that can result from the disbonding on 737-200/-300/-400/-500 airplanes delivered with original production skin panels (Line Numbers 611-2725). It also inspects airplanes where skin panels have been replaced with new skin panels that were manufactured prior to April 01, 1997 (Line Numbers 611-2869).
On July 2003, a 737-300 operator reported a severely disbonded fuselage skin panel assembly, between stringer S-4L and stringer S-10L, and from BS 360 to BS 540. The disbond between the doubler and skin was discovered during an investigation of a fuselage skin crack located in an area common to the upper row of fasteners in the stringer S-10L lap splice. In one area, cracks originating at multiple fastener holes had connected, resulting in a crack length of eight inches. The cracking at the lap splice was attributed to the countersink knife edge condition in the disbonded outer skin. Subsequently, other operators have recently reported additional occurrences of cracking of disbonded fuselage skin panels.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 23, 2016 737-53A1349 7 of 394
This service bulletin supersedes Boeing Service Bulletin 737-53-1179 and expands the effectivity to 292-2947 to inspect for any disbond of the fuselage skin/doubler and cracking that can result from the disbonding on 737-200/-300/-400/-500 airplanes. This service bulletin changes the one time terminating inspection to a repeat inspection, provides an alternate inspection method and adds new repeat disbond inspection requirements for lap splices, and butt joints. Any skin panel with an existing disbond repair or disbond finding must be repetitively inspected until the skin panel is replaced.
This service bulletin contains similar actions to, but does not supersede, existing Boeing Service Bulletins 737-53-1124, 737-53-1076, 737-53-1078, and 737-53A1039. Boeing Service Bulletins 737-53-1124, 737-53-1076, 737-53-1078, and 737-53A1039 remain fully applicable and must be accomplished in addition to the actions in this service bulletin.
Boeing Fleet Team Digest 737 FTD 53-03008 is related to this service bulletin.
Boeing Multi Operator Message (MOM) 1-146890376-1 and 1-148349744-1 are related to this service bulletin.
Boeing Service Related Problem (SRP) 737-SRP-53-0218 and 737-SRP-53-0502 are related to this service bulletin.
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 AffectedYesPublications 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
1. Do PART 1: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS for any crack, corrosion, or existing disbond repair. If any crack or corrosion is found during PART 1 inspection, do PART 3:
AREA DISBOND INSPECTION for disbonding in the area of crack or corrosion. If any disbond is found during PART 3 inspection, do PART 4: SKIN PANEL DISBOND INSPECTION of the entire affected skin panel for additional disbond, and do PART 6: TEMPORARY DISBOND REPAIR. If no disbond is found during PART 3 inspection, do PART 5: REPAIR for the crack or corrosion found during PART 1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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inspection. If an existing disbond repair is found during PART 1 inspection, do PART 4: SKIN PANEL DISBOND INSPECTION of the entire affected panel for additional disbond, and do PART 6:
TEMPORARY DISBOND REPAIR. If no crack, corrosion, or existing disbond repair is found during PART 1 inspection, repeat PART 1: EXTERNAL GENERAL VISUAL AND DETAILED INSPECTIONS at the repeat interval in Paragraph 1.E., Compliance
2. Do PART 2: EXTERNAL HIGH FREQUENCY BOND TEST inspection for any disbond at the lap splices and butt joints. If any disbond is found during PART 2 inspection, do PART 4: SKIN PANEL DISBOND INSPECTION of the entire affected skin panel for additional disbond, and do PART 6: TEMPORARY DISBOND REPAIR. If no disbond is found, repeat PART 2: EXTERNAL HIGH FREQUENCY BOND TEST inspection at the repeat interval in Paragraph 1.E., Compliance.
3. Do PART 8: ULTRASONIC DISBOND INSPECTION AND INTERNAL DETAILED SKIN INSPECTION USING A FEELER GAUGE for any disbond. If any disbond is found do PART 6: TEMPORARY DISBOND REPAIR. If no disbond is found, repeat PART 8: ULTRASONIC DISBOND INSPECTION AND INTERNAL DETAILED SKIN INSPECTION USING A FEELER GAUGE at the repeat interval in Paragraph 1.E., Compliance.
4. If any disbonding is found on a skin panel during PART 2, PART 3, PART 4, or PART 8 inspections or if an existing disbond repair is found during PART 1 inspections, that skin panel is considered susceptible to disbonding and must be inspected in accordance with PART 7: INSPECTION REQUIREMENTS FOR SKIN PANELS WITH TEMPORARY DISBOND REPAIR OR EXISTING DISBOND REPAIR and then replaced in accordance with PART 9: SKIN PANEL REPLACEMENT at the compliance times in Paragraph 1.E., Compliance.
EFFECTIVITY 737-200/-200C/-300/-400/-500 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
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 available for 737 airplanes in warranty as of November 17, 1994. Please refer to Paragraph 2.B., Industry Support Information. Warranty remedies will expire after November 26, 2020.
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 737-53A1349
ALERT ALERT STA 1016 STA DO PART 1: 540
EXTERNAL VISUAL
INSPECTION FOR ANY
CRACK, CORROSION
OR EXISTING
DISBOND REPAIR DO PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST FOR
STA ANY DISBOND AT ALL THE LAP 259 SPLICES AND BUTT JOINTS (TYPICAL LOCATION SHOWN) DO PART 8: ULTRASONIC DISBOND
INSPECTION AND INTERNAL DETAILED
SKIN INSPECTION VIA FEELER GAUGE
FOR ANY DISBOND Original Issue: August 23, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1349 Work - See page 1 for details. 10 of 394
Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1349 Original Issue: August 23, 2016 ATA System: 5331 SUBJECT: FUSELAGE - Skin - Inspection, Repair, and Replacement of Disbonded Fuselage Skin Panels
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.
1. PLANNING INFORMATION A. Effectivity
1. Airplanes This service bulletin is applicable to 737-200/-200C/-300/-400/-500 Airplanes, line numbers 292-2947 in 31 Groups. The Variable Numbers and Group Information for the applicable airplanes is given below.
Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP 737-200 Passenger airplane with solid skin at S-26L to S-26R from BS 360 to 540 and S-25L to S-25R from BS 727 to 1016. The solid skins were installed per service bulletin 737-53A1042.
-1 737-200C Cargo airplane with solid skin at S-26L to S-26R from BS 360 to 540 and S-25L to S-25R from BS 727 to 1016. The solid skins were installed per service bulletin 737-53A1042.
-2 737-200 Passenger airplane with solid skin at S-26L to S-26R from BS 360 to 540 and S-25L to S-25R from BS 727 to 1016.
-3 737-200 Passenger airplane with solid skin at S-26L to S-26R from BS 360 to 540 and S-25L to S-25R from BS 727 to 1016. Aft lower lobe skins with partially chem-milled pockets.
-4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 23, 2016 737-53A1349 11 of 394
DESCRIPTIONCONFIGURATIONGROUP 737-200C Cargo airplane with solid skin at S-26L to S-26R from BS 360 to 540 and S-25L to S-25R from BS 727 to 1016.
-5 737-200C Cargo airplane with solid skin at S-26L to S-26R from BS 360 to 540 and S-25L to S-25R from BS 727 to 1016. Aft lower lobe skins with partially chem-milled pockets.
-6 737-200 Passenger airplane with solid skin at S-26L to S-26R from BS 360 to 540, S-25L to S-25R from BS 727 to 1016 and S-24L to S-24R from BS 259.50 to BS 360. Aft lower lobe skins with partially chem-milled pockets.
-7 737-300 Passenger airplane with solid skin at S-26L to S-26R from BS 360 to 540 and S-25L to S-25R from BS 727 to 1016. Aft lower lobe skins with unique partially chem-milled pockets.
-8 737-300 Passenger airplane with solid skin at S-26L to S-26R from BS 360 to 540 and S-25L to S-25R from BS 727 to 1016. Aft lower lobe skins with unique partially chem-milled pockets.
-9 737-300 Passenger airplane with solid skin at S-24L to S-24R from BS 259.50 to BS 360, S-26L to S-26R from BS 360 to 540 and S-25L to S-25R from BS 727 to 1016. Aft lower lobe skins with unique partially chem-milled pockets.
-10 737-300 Passenger airplane with solid skin at S-24L to S-24R from BS 259.50 to BS 360, S-26L to S-26R from BS 360 to 540 and S-25L to S-25R from BS 727 to 1016. Aft lower lobe skins with unique partially chem-milled pockets.
-11 737-300 Passenger airplane with solid skin at S-24L to S-24R from BS 259.50 to BS 360, S-26L to S-26R from BS 360 to 540, S-25L to S-25R from BS 727 to 1016 and S-4L to S-24L and S-4R to S-19R between BS 259 and BS 360. Aft lower lobe skins with unique partially chem-milled pockets.
-12 737-300 Passenger airplane with solid skin at S-24L to S-24R from BS 259.50 to BS 360, S-26L to S-26R from BS 360 to 540, S-25L to S-25R from BS 727 to 1016 and S-4L to S-24L and S-4R to S-19R between BS 259 and BS 360. Aft lower lobe skins with unique partially chem-milled pockets.
-13 737-300 Passenger airplane with solid skin at S-24L to S-24R from BS 259.50 to BS 360, S-26L to S-26R from BS 360 to 540, S-25L to S-25R from BS 727 to 1016, S-4L to S-24L and S-4R to S-19R between BS 259 and BS 360 and window belt from BS 540 to BS
727. Aft lower lobe skins with unique partially chem-milled pockets.
-14 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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