# Boeing Alert Service Bulletin 737-53A1349: No revision named

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- Title as filed: SB-737-53A1349-R00--BOEING
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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Unpublished Work.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
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connection with this document unless provided in writing by Boeing.
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Table of Contents
S u m m a r y  ...................................................... 7
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
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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
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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
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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
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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.
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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 Air-
plane 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
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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.
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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
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### Page 11

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
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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
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### Page 13

DESCRIPTIONCONFIGURATIONGROUP
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.
-15
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.
-16
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.
-17
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.
-18
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 360 and BS
1016. Aft lower lobe skins with unique partially chem-milled pockets.
-19
737-300 Passenger airplane with solid skins below S-10.-20
737-400 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.
-21
737-400 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.
-22
737-400 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.
-23
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### Page 14

DESCRIPTIONCONFIGURATIONGROUP
737-400 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.
-24
737-400 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 360 and BS
1016. Aft lower lobe skins with unique partially chem-milled pockets.
-25
737-400 Passenger airplane with solid skins below S-10.-26
737-500 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 window belt from BS 540 to BS 727.
Aft lower lobe skins with unique partially chem-milled pockets.
-27
737-500 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.
-28
737-500 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.
-29
737-500 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 360 to BS
1016. Aft lower lobe skins with unique partially chem-milled pockets.
-30
737-500 Passenger airplane with solid skins below S-10.-31
Airplane Models:
737-200, 737-200C, 737-300, 737-400, 737-500
GroupVariable Number
1PG584 - PG586
1PH001
1PH011 - PH013
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### Page 15

GroupVariable Number
1PH021 - PH024
1PH743
1PJ003
3PJ004 - PJ009
1PJ105 - PJ109
3PJ110 - PJ119
1PJ201 - PJ219
23PJ301 - PJ302
24PJ551
25PJ552
26PJ553 - PJ561
26PJ601 - PJ603
26PJ811
26PJ816 - PJ817
1PK026 - PK028
3PK029
1PK041 - PK048
3PK049 - PK053
1PK061 - PK067
3PK068 - PK070
1PK081
3PK082
1PK091
3PK092 - PK099
1PK101 - PK103
1PK111 - PK120
1PK141 - PK146
3PK201 - PK204
3PK211 - PK215
4PK216 - PK220
3PK221 - PK223
3PK231 - PK241
3PK251 - PK258
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### Page 16

GroupVariable Number
3PK271 - PK274
3PK281 - PK289
3PK291
3PK301 - PK318
3PK341
3PK351 - PK361
3PK391
3PK431 - PK433
3PK451 - PK452
3PK461 - PK469
3PK495
3PK501 - PK504
3PK511 - PK514
4PK515
4PK519
3PK521 - PK525
4PK526 - PK527
7PK528
3PK541 - PK564
4PK565
3PK581
3PK591 - PK599
3PK601 - PK617
3PK621 - PK637
3PK641 - PK642
3PK661 - PK664
4PK665 - PK666
3PK671 - PK680
4PK681
3PK691 - PK697
3PK711 - PK716
3PK731 - PK749
4PK750 - PK765
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### Page 17

GroupVariable Number
3PK771 - PK779
3PK801 - PK802
4PK803 - PK804
3PK819 - PK826
4PK827
3PK830
3PK861 - PK863
3PK871 - PK874
3PK881 - PK884
3PK901 - PK932
4PK933 - PK938
3PK971 - PK974
1PL001
3PL002 - PL025
4PL026 - PL028
3PL061
3PL081
3PL101 - PL113
3PL151
3PL171 - PL172
3PL201 - PL203
3PL221
3PL401 - PL415
4PL416 - PL417
3PL421
3PL441
3PL451 - PL454
4PL455 - PL456
3PL471
3PL491
3PL501 - PL506
3PL551 - PL562
3PL581
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### Page 18

GroupVariable Number
3PL601
4PL602 - PL603
3PL611
4PL621 - PL625
7PL626
3PL631 - PL632
1PL717 - PL721
3PL722 - PL725
1PL726 - PL730
3PL731 - PL735
1PL736 - PL743
3PL744 - PL745
4PL746
7PL747
1PL756
1PL758
1PL761 - PL766
3PL767 - PL770
1PL781 - PL782
3PL783 - PL787
4PL788
1PL793
3PM001 - PM006
4PM016 - PM017
3PM021 - PM023
3PM051 - PM056
4PM057 - PM066
3PM101 - PM110
4PM111 - PM119
3PM141 - PM142
4PM171
4PM181
4PM251 - PM255
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### Page 19

GroupVariable Number
4PM281 - PM283
10PM381 - PM392
12PM393 - PM395
13PM396 - PM397
14PM398 - PM399
14PM401 - PM406
16PM407 - PM417
16PM541
18PM542
19PM543 - PM547
20PM548 - PM550
23PM551 - PM564
3PN001
4PN002
4PN021 - PN043
4PN081 - PN086
4PN101 - PN117
4PN131 - PN163
4PN401 - PN420
4PN431 - PN433
4PN451 - PN456
4PN471 - PN472
7PN473 - PN474
4PN481
4PN491 - PN492
7PN493
4PN501
7PN502
7PN511 - PN512
7PN521
8PP001 - PP031
10PP032 - PP054
8PP101 - PP126
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### Page 20

GroupVariable Number
10PP127 - PP148
12PP149 - PP150
16PP151 - PP160
8PP161 - PP168
10PP169
8PP181 - PP184
10PP185 - PP199
8PP201 - PP204
10PP205
8PP221
8PP231 - PP243
8PP281 - PP286
8PP301 - PP305
8PP351 - PP352
10PP353
8PP376 - PP384
10PP391 - PP393
8PP401 - PP424
10PP425 - PP440
9PP471 - PP475
9PP501 - PP504
11PP505 - PP510
15PP511 - PP512
17PP513 - PP517
20PP518 - PP520
8PP521 - PP522
8PP631 - PP634
8PP651 - PP652
8PP671 - PP689
9PP690 - PP694
8PP695 - PP699
8PP701 - PP706
9PP707 - PP716
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### Page 21

GroupVariable Number
8PP717 - PP720
10PP721 - PP733
8PP771 - PP777
10PP778 - PP779
8PP801 - PP804
10PP805 - PP808
8PP821 - PP827
8PP831 - PP836
10PP837 - PP845
8PP846 - PP848
8PP851
10PP852
8PP861 - PP870
10PP871 - PP873
16PP874 - PP875
20PP876
8PP891 - PP899
8PP901 - PP905
10PP906 - PP924
12PP925
13PP926 - PP928
14PP929 - PP930
8PP931 - PP934
10PP935 - PP936
8PP946 - PP948
10PP951 - PP952
8PP961 - PP965
10PP966 - PP967
8PP981 - PP982
10PP983 - PP987
12PP988
16PP989 - PP990
8PP991
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### Page 22

GroupVariable Number
10PP993
8PQ001 - PQ012
10PQ013 - PQ016
8PQ026 - PQ037
10PQ038 - PQ041
8PQ051 - PQ061
10PQ062 - PQ073
14PQ074 - PQ077
16PQ078 - PQ085
8PQ086
10PQ087 - PQ092
8PQ101 - PQ110
10PQ111 - PQ198
12PQ199
12PQ201 - PQ202
10PQ221 - PQ229
13PQ230
10PQ231 - PQ236
14PQ237
10PQ241 - PQ243
10PQ251 - PQ255
12PQ256 - PQ257
14PQ258
16PQ259 - PQ267
10PQ281 - PQ286
12PQ287
13PQ288 - PQ289
16PQ290 - PQ296
20PQ297 - PQ299
10PQ301 - PQ305
16PQ306 - PQ307
10PQ331 - PQ332
14PQ341
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### Page 23

GroupVariable Number
16PQ342 - PQ344
20PQ345 - PQ348
13PQ361
14PQ362
16PQ363 - PQ369
20PQ370 - PQ373
20PQ391 - PQ393
14PQ401
16PQ402 - PQ406
18PQ407
19PQ408
20PQ409 - PQ410
14PQ411
16PQ412 - PQ413
20PQ414 - PQ417
14PQ421
20PQ431 - PQ438
20PQ447 - PQ448
20PQ451
18PQ471 - PQ472
19PQ473
20PQ474 - PQ475
18PQ479 - PQ480
16PQ481
16PQ486
18PQ487
16PQ491 - PQ493
16PQ771
20PQ772
16PQ791 - PQ793
16PQ801 - PQ803
18PQ804 - PQ805
18PQ931 - PQ932
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### Page 24

GroupVariable Number
20PQ933 - PQ935
20PQ951
20PQ971 - PQ983
20PQ996
20PR001 - PR006
20PR021 - PR024
20PR031 - PR032
20PR041 - PR044
20PR096
14PS601 - PS605
16PS606 - PS616
20PS617 - PS630
16PS631
14PS636
16PS637 - PS638
10PS641 - PS642
16PS643 - PS644
13PS651 - PS652
14PS653 - PS657
10PS666 - PS668
16PS669
16PS691 - PS692
16PS701 - PS703
20PS704 - PS706
16PS751 - PS756
18PS757 - PS762
20PS763 - PS799
20PS811
20PS836 - PS837
20PS841 - PS846
20PS851 - PS852
20PS856
20PS861 - PS863
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### Page 25

GroupVariable Number
20PS866 - PS868
20PS871
20PS896 - PS897
20PS901 - PS941
20PS956 - PS957
28PT001 - PT011
31PT012 - PT015
27PT021 - PT023
28PT024 - PT027
29PT028
31PT029 - PT031
28PT041 - PT059
29PT060 - PT063
30PT064
27PT101
28PT102 - PT105
27PT121 - PT123
28PT124 - PT125
31PT126 - PT134
27PT146
28PT147 - PT148
28PT161 - PT170
27PT181 - PT182
28PT183 - PT187
31PT188
27PT211 - PT214
28PT215 - PT220
27PT295
28PT301 - PT303
29PT304 - PT306
31PT307 - PT309
28PT331 - PT360
28PT381 - PT399
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### Page 26

GroupVariable Number
28PT401 - PT435
29PT436 - PT438
28PT501 - PT512
31PT513 - PT517
28PT561 - PT565
28PT581 - PT584
31PT585 - PT586
28PT611 - PT621
28PT641 - PT642
31PT643 - PT644
28PT651 - PT655
31PT656
28PT671 - PT672
31PT681 - PT683
28PT701 - PT703
31PT716 - PT717
31PT721 - PT722
31PT801 - PT834
31PT851 - PT853
31PT871 - PT880
31PT901 - PT908
31PT971 - PT973
31PT981 - PT983
31PT996
27PU001 - PU007
28PU008 - PU025
31PU301
21PV001 - PV040
22PV041 - PV055
23PV201 - PV202
24PV203
26PV204 - PV209
26PV226 - PV228
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### Page 27

GroupVariable Number
23PV231 - PV237
23PV271 - PV272
23PV281 - PV282
24PV283
26PV284 - PV287
26PV296
26PV301 - PV302
26PV351
21PW001 - PW036
22PW037 - PW050
21PW051
22PW052 - PW053
23PW054
21PW061 - PW063
22PW064 - PW068
23PW072
26PW086 - PW088
21PW091 - PW093
22PW094
23PW101 - PW102
23PW106
21PW111 - PW117
22PW118 - PW119
23PW120
22PW156
23PW157
21PW161 - PW162
22PW163
23PW164 - PW167
23PW201 - PW223
24PW224 - PW230
23PW231 - PW240
24PW241 - PW244
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### Page 28

GroupVariable Number
25PW245
26PW246 - PW252
22PW261
26PW262
23PW265 - PW268
26PW271 - PW276
24PW278
23PW281
25PW282 - PW284
26PW285 - PW292
23PW293
22PW296
22PW301 - PW312
23PW313 - PW323
24PW324 - PW327
26PW401 - PW404
26PW411 - PW415
26PW421
24PW461 - PW467
21PW501 - PW503
22PW504
21PW511 - PW518
23PW519 - PW520
26PW521 - PW522
26PW524 - PW525
23PW526
26PW527 - PW530
21PW531 - PW535
22PW536 - PW539
23PW540 - PW545
24PW546
26PW547 - PW550
23PW556
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### Page 29

GroupVariable Number
24PW557
21PW561 - PW563
22PW564
21PW571 - PW573
22PW574 - PW576
21PW591 - PW594
22PW595
23PW596
21PW611 - PW615
22PW616 - PW620
26PW621 - PW622
21PW631 - PW632
22PW633
23PW634
26PW635 - PW637
21PW661
22PW662
22PW681 - PW683
22PW701
23PW702
22PW711 - PW716
23PW717
22PW741
23PW742
22PW761
23PW771
26PW831
26PW851 - PW853
2PY022
2PY036 - PY037
2PY046 - PY047
5PY048
2PY051 - PY052
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### Page 30

GroupVariable Number
5PY053
6PY056 - PY057
2PY101 - PY103
2PY111 - PY113
2PY131 - PY133
5PY134 - PY135
2PY141 - PY142
5PY143
5PY151 - PY154
5PY156 - PY157
5PY161 - PY162
5PY166
5PY191
5PY201
5PY221 - PY222
5PY231
5PY241 - PY244
5PY270
2PY271 - PY273
5PY274 - PY275
6PY281
5PY286
5PY401
6PY409 - PY410
5PY411
5PY421 - PY422
5PY441
5PY451
5PY461 - PY462
6PY463
6PY591 - PY595
5PY611 - PY612
5PY621
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### Page 31

GroupVariable Number
5PY631
5PY651
6PY671 - PY672
6PY721
6PY741
2. Spares Affected
B. Concurrent Requirements
None.
C. Reason
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.
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.
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### Page 32

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 737-SRP-53-0218 and 737-SRP-53-0502 are related to this service
bulletin.
D. Description
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 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 any crack, corrosion, or 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,
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.
The work in this service bulletin is done in the maintenance zone(s) given below.
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### Page 33

Group 1, 3-4, 7:
Affected Maintenance Zones
ZoneModel
1-1, 1-2, 1-3, 1-4, 1-7, 1-8, 2-2, 2-5, 2-8, 2-18,
2-20
737-200
Group 2, 5-6:
Affected Maintenance Zones
ZoneModel
1-1, 1-2, 1-3, 1-4, 1-7, 1-8, 2-2, 2-5, 2-8, 2-18,
2-20
737-200C
Group 8-20:
Affected Maintenance Zones
ZoneModel
101, 102, 103, 104, 107, 108, 202, 205, 208,
218, 220
737-300
Group 21-26:
Affected Maintenance Zones
ZoneModel
101, 102, 103, 104, 107, 108, 202, 205, 208,
218, 220
737-400
Group 27-31:
Affected Maintenance Zones
ZoneModel
101, 102, 103, 104, 107, 108, 202, 205, 208,
218, 220
737-500
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-14-06 is related to this service
bulletin. The effective date of AD 2003-14-06 is July 14, 2003.
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.
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### Page 34

When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Logic diagrams showing compliance tasks and compliance times are included as an aid as follows:
GroupTableLogic Diagram
1-11, 27Table 1:APPENDIX A
External Inspection of Fuselage Skin Panels for Any
Crack, Corrosion, Existing Disbond Repair and Disbond
21Table 2:APPENDIX B
External Inspection of Fuselage Skin Panels for Any
Crack, Corrosion, Existing Disbond Repair and Disbond
12-18, 28-29Table 3:APPENDIX C
External Inspection of Fuselage Skin Panels for Any
Crack, Corrosion, Existing Disbond Repair and Disbond
22-24Table 4:APPENDIX D
External Inspection of Fuselage Skin Panels for Any
Crack, Corrosion, Existing Disbond Repair and Disbond
19, 30Table 5:APPENDIX E
External Inspection of Fuselage Skin Panels for Any
Crack, Corrosion, Existing Disbond Repair and Disbond
25Table 6:APPENDIX F
External Inspection of Fuselage Skin Panels for Any
Crack, Corrosion, Existing Disbond Repair and Disbond
20, 31Table 7:APPENDIX G
External Inspection of Fuselage Skin Panels for Any
Crack, Corrosion, Existing Disbond Repair and Disbond
26Table 8:APPENDIX H
External Inspection of Fuselage Skin Panels for Any
Crack, Corrosion, Existing Disbond Repair and Disbond
1-31Table 9:APPENDIX I
Inspection of Replaced Skin Panels Manufactured Prior
to April 01, 1997 and Replaced Skin Panels where the
Manufacture Date is Not Known
1-31Table 10:APPENDIX J
Internal and External Inspection of Fuselage Skin Panels
for any disbond
1-31Table 11:APPENDIX K
Inspection Requirements for Skin Panels with Existing
Disbond Repair or Temporary Disbond Repair
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### Page 35

Group 1-11, 27:
Table 1: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
292 through 610
(c)
(a) (b) (c)
AND
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
611 through 1921 that
have accomplished the
one-time internal inspec-
tion in accordance with
SB 737-53-1179 Revision
2 at the original issue
date of this service bul-
letin
(a) (b) (c)
AND
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
611 through 1921 that
have not accomplished
the one-time internal in-
spection in accordance
with SB 737-53-1179
Revision 2 at the original
issue date of this service
bulletin
OR
Before 20,000 total flight cycles
whichever occurs later.
(a) (b) (c)
AND
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
(a) (b) (c)
4,500 Flight
Cycles.
-Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion.
CONDITION 1:
NO CRACK, CORRO-
SION OR EXISTING
DISBOND REPAIR
FOUND AT A LOCA-
TION INSPECTED IN
ACCORDANCE WITH
PART 1
(a) (b)
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### Page 36

Group 1-11, 27:
Table 1: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Before further flight.Do PART 3: AREA DISBOND IN-
SPECTION for any disbond in the
area of cracking or corrosion.
CONDITION 2:
ANY CRACK OR COR-
ROSION FOUND AT A
LOCATION INSPECTED
IN ACCORDANCE WITH
PART 1
-Before further flight.(ACTION 1)CONDITION 2.1:
Do PART 5: REPAIR for any crack
or corrosion.
NO DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
4,500 Flight
Cycles.
(a) (b)
-(ACTION 2)
Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion at the unre-
paired area of affected panel.
-Before further flight.(ACTION 1)CONDITION 2.2:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
(d) (e)
-Before further flight(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
-Before further flight.Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
CONDITION 3:
ANY EXISTING DIS-
BOND REPAIR FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 1
(d) (e)
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### Page 37

Group 1-11, 27:
Table 1: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-At the times in Table 11 in
Paragraph 1.E., Compliance.
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
CONDITION 3.1:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4
-Before further flight.(ACTION 1)CONDITION 3.2:
Do PART 6: TEMPORARY DIS-
BOND REPAIR in the area of the
disbond.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4 -At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 2)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
-Before further flight.(ACTION 1)CONDITION 4:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 (d) (e)
-Before further flight.(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
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### Page 38

Group 1-11, 27:
Table 1: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
At the Repeat
Intervals be-
low.
-Repeat PART 2: EXTERNAL
HIGH FREQUENCY BOND TEST
inspection for any disbond at lap
splices and butt joints listed below:
CONDITION 5:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 5,000 Flight
Cycles.
-S-4L and S-4R lap splice between
BS 259.50 and BS 1016
(a) (b) (c)S-10L and S-10R lap splice be-
tween BS 259.50 and BS 1016
S-25L and S-25R lap splice be-
tween BS 908 and BS 1016
11,000 Flight
Cycles.
-S-14L and S-14R lap splice be-
tween BS 259.50 and BS 540
(a) (b) (c)S-14L and S-14R lap splice be-
tween BS 727 and BS 1016
S-19L and S-19R lap splice be-
tween BS 259.50 and BS 540
S-20L and S-20R lap splice be-
tween BS 727 and BS 1016
S-24L and S-24R lap splice be-
tween BS 259.50 and BS 360
S-25L and S-25R lap splice be-
tween BS 727 and BS 908
S-26L and S-26R lap splice be-
tween BS 360 and BS 540
47,000 Flight
Cycles.
-BS 360 butt joint between S-10L
and S-10R
(a) (b) (c)BS 908 butt joint between S-10L
and S-10R
22,000 Flight
Cycles.
-BS 540 butt joint between S-10L
and S-10R
(a) (b) (c)BS 727 butt joint between S-10L
and S-10R
(a) If any Boeing ODA approved preventative modification or repair was previously installed via FAA Form
8100-9 or SRM repair (except disbond repair), initial and repeat inspections are not required at the repaired
location only.
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### Page 39

Group 1-11, 27:
Table 1: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
(b) Accomplishment of skin panel replacement using Boeing skin panel manufactured on or after April 01,
1997 is terminating action for all inspections given in this service bulletin at the replaced skin panel only.
(c) Inspection requirements for skin panels replaced with skin panels manufactured by Boeing prior to April
01, 1997 are in Table 9. If the manufacture date is not known, follow the inspection requirements in Table
9.
(d) Any skin panel with existing disbond repair or disbond finding must be inspected at repeat intervals in
accordance with Table 11 until the skin panel is replaced at the compliance time given in Table 11.
(e) Accomplishment of PART 9: SKIN PANEL REPLACEMENT is terminating action to the repeat inspections
at the replaced skin panel only.
Group 21:
Table 2: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
1487 through 1922 that
have accomplished the
one-time internal inspec-
tion in accordance with
SB 737-53-1179 Revision
2 at the original issue
date of this service bul-
letin
(a) (b) (c)
AND
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
1487 through 1922 that
have not accomplished
the one-time internal in-
spection in accordance
with SB 737-53-1179
Revision 2 at the original
issue date of this service
bulletin
OR
Before 20,000 total flight cycles
whichever occurs later.
(a) (b) (c)
AND
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
(a) (b) (c)
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### Page 40

Group 21:
Table 2: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
4,500 Flight
Cycles.
-Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion.
CONDITION 1:
NO CRACK, CORRO-
SION OR EXISTING
DISBOND REPAIR
FOUND AT A LOCA-
TION INSPECTED IN
ACCORDANCE WITH
PART 1
(a) (b)
-Before further flight.Do PART 3: AREA DISBOND IN-
SPECTION for any disbond in the
area of cracking or corrosion.
CONDITION 2:
ANY CRACK OR COR-
ROSION FOUND AT A
LOCATION INSPECTED
IN ACCORDANCE WITH
PART 1
-Before further flight.(ACTION 1)CONDITION 2.1:
Do PART 5: REPAIR for any crack
or corrosion.
NO DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
4,500 Flight
Cycles.
(a) (b)
-(ACTION 2)
Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion at the unre-
paired area of affected panel.
-Before further flight.(ACTION 1)CONDITION 2.2:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
(d) (e)
-Before further flight.(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
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### Page 41

Group 21:
Table 2: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Before further flight.Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
CONDITION 3:
ANY EXISTING DIS-
BOND REPAIR FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 1
(d) (e)
-At the times in Table 11 in
Paragraph 1.E., Compliance.
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
CONDITION 3.1:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4
-Before further flight.(ACTION 1)CONDITION 3.2:
Do PART 6: TEMPORARY DIS-
BOND REPAIR in the area of the
disbond.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4 -At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 2)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
-Before further flight.(ACTION 1)CONDITION 4:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 (d) (e)
-Before further flight.(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
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### Page 42

Group 21:
Table 2: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
At the Repeat
Intervals be-
low.
-Repeat PART 2: EXTERNAL
HIGH FREQUENCY BOND TEST
inspection for any disbond at lap
splices and butt joints listed below:
CONDITION 5:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 5,000 Flight
Cycles.
-S-4L and S-4R lap splice between
BS 259.50 and BS 1016
(a) (b) (c)S-10L and S-10R lap splice be-
tween BS 259.50 and BS 1016
S-25L and S-25R lap splice be-
tween BS 908 and BS 1016
11,000 Flight
Cycles.
-S-14L and S-14R lap splice be-
tween BS 259.50 and BS 540
(a) (b) (c)S-14L and S-14R lap splice be-
tween BS 727 and BS 1016
S-19L and S-19R lap splice be-
tween BS 259.50 and BS 540
S-20L and S-20R lap splice be-
tween BS 727 and BS 1016
S-24L and S-24R lap splice be-
tween BS 259.50 and BS 360
S-25L and S-25R lap splice be-
tween BS 727 and BS 908
S-26L and S-26R lap splice be-
tween BS 360 and BS 540
47,000 Flight
Cycles.
-BS 360 butt joint between S-10L
and S-10R
(a) (b) (c)BS 908 butt joint between S-10L
and S-10R
22,000 Flight
Cycles.
-BS 540 butt joint between S-10L
and S-10R
(a) (b) (c)BS 727 butt joint between S-10L
and S-10R
BS 500C butt joint between S-10L
and S-10R
BS 727G butt joint between S-10L
and S-10R
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
42 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 43

Group 21:
Table 2: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
(a) If any Boeing ODA approved preventative modification or repair that was previously installed via FAA
Form 8100-9 or SRM repair doubler (except disbond repair), initial and repeat inspections are not required
at the repaired location only.
(b) Accomplishment of skin panel replacement using Boeing skin panel manufactured on or after April 01,
1997 is terminating action for all inspections given in this service bulletin at the replaced skin panel only.
(c) Inspection requirements for skin panels replaced with skin panels manufactured by Boeing prior to April
01, 1997 are in Table 9. If the manufacture date is not known, follow the inspection requirements in Table
9.
(d) Any skin panel with existing disbond repair or disbond finding must be inspected at repeat intervals in
accordance with Table 11 until the skin panel is replaced at the compliance time given in Table 11.
(e) Accomplishment of PART 9: SKIN PANEL REPLACEMENT is terminating action to the repeat inspections
at the replaced skin panel only.
Group 12-18, 28-29:
Table 3: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
1923 through 2552 that
have accomplished the
one-time internal inspec-
tion in accordance with
SB 737-53-1179 Revision
2 at the original issue
date of this service bul-
letin
(a) (b) (c)
AND
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
43 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 44

Group 12-18, 28-29:
Table 3: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
1923 through 2552 that
have not accomplished
the one-time internal in-
spection in accordance
with SB 737-53-1179
Revision 2 at the original
issue date of this service
bulletin
OR
Before 20,000 total flight cycles
whichever occurs later.
(a) (b) (c)
AND
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
(a) (b) (c)
4,500 Flight
Cycles.
-Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion.
CONDITION 1:
NO CRACK, CORRO-
SION OR EXISTING
DISBOND REPAIR
FOUND AT A LOCA-
TION INSPECTED IN
ACCORDANCE WITH
PART 1
(a) (b)
-Before further flight.Do PART 3: AREA DISBOND IN-
SPECTION for any disbond in the
area of cracking or corrosion.
CONDITION 2:
ANY CRACK OR COR-
ROSION FOUND AT A
LOCATION INSPECTED
IN ACCORDANCE WITH
PART 1
-Before further flight.(ACTION 1)CONDITION 2.1:
Do PART 5: REPAIR for any crack
or corrosion.
NO DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
4,500 Flight
Cycles.
(a) (b)
-(ACTION 2)
Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion at the unre-
paired area of affected panel.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
44 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 45

Group 12-18, 28-29:
Table 3: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Before further flight.(ACTION 1)CONDITION 2.2:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
(d) (e)
-Before further flight.(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
-Before further flight.Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
CONDITION 3:
ANY EXISTING DIS-
BOND REPAIR FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 1
(d) (e)
-At the times in Table 11 in
Paragraph 1.E., Compliance.
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
CONDITION 3.1:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4
-Before further flight.(ACTION 1)CONDITION 3.2:
Do PART 6: TEMPORARY DIS-
BOND REPAIR in the area of the
disbond.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4 -At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 2)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
45 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 46

Group 12-18, 28-29:
Table 3: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Before further flight.(ACTION 1)CONDITION 4:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 (d) (e)
-Before further flight.(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
46 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 47

Group 12-18, 28-29:
Table 3: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
At the Repeat
Intervals be-
low.
-Repeat PART 2: EXTERNAL
HIGH FREQUENCY BOND TEST
inspection for any disbond at lap
splices and butt joints listed below:
CONDITION 5:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 5,000 Flight
Cycles.
-S-4L and S-4R lap splice between
BS 259.50 and BS 1016
(a) (b) (c)S-10L and S-10R lap splice be-
tween BS 360 and BS 1016
S-25L and S-25R lap splice be-
tween BS 908 and BS 1016
11,000 Flight
Cycles.
-S-14L and S-14R lap splice be-
tween BS 360 and BS 540
(a) (b) (c)S-14L and S-14R lap splice be-
tween BS 727 and BS 1016
S-19L and S-19R lap splice be-
tween BS 360 and BS 540
S-20L and S-20R lap splice be-
tween BS 727 and BS 1016
S-24R lap splice between BS
259.50 and BS 360
S-25L and S-25R lap splice be-
tween BS 727 and BS 908
S-26L and S-26R lap splice be-
tween BS 360 and BS 540
47,000 Flight
Cycles.
-FWD of BS 360 from S-4L to S-4R
and AFT of BS 360 from S-10L to
S-10R (a) (b) (c)
BS 908 butt joint between S-10L
and S-10R
22,000 Flight
Cycles.
-BS 540 butt joint between S-10L
and S-10R
(a) (b) (c)BS 727 butt joint between S-10L
and S-10R
(a) If any Boeing ODA approved preventative modification or repair was previously installed via FAA Form
8100-9 or SRM repair (except disbond repair), initial and repeat inspections are not required at the repaired
location only.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
47 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 48

Group 12-18, 28-29:
Table 3: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
(b) Accomplishment of skin panel replacement using Boeing skin panel manufactured on or after April 01,
1997 is terminating action for all inspections given in this service bulletin at the replaced skin panel only.
(c) Inspection requirements for skin panels replaced with skin panels manufactured by Boeing prior to April
01, 1997 are in Table 9. If the manufacture date is not known, follow the inspection requirements in Table
9.
(d) Any skin panel with existing disbond repair or disbond finding must be inspected at repeat intervals in
accordance with Table 11 until the skin panel is replaced at the compliance time given in Table 11.
(e) Accomplishment of PART 9: SKIN PANEL REPLACEMENT is terminating action to the repeat inspections
at the replaced skin panel only.
Group 22-24:
Table 4: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
1931 through 2551 that
have accomplished the
one-time internal inspec-
tion in accordance with
SB 737-53-1179 Revision
2 at the original issue
date of this service bul-
letin
(a) (b) (c)
AND
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
1931 through 2551 that
have not accomplished
the one-time internal in-
spection in accordance
with SB 737-53-1179
Revision 2 at the original
issue date of this service
bulletin
OR
Before 20,000 total flight cycles
whichever occurs later.
(a) (b) (c)
AND
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
(a) (b) (c)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
48 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 49

Group 22-24:
Table 4: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
4,500 Flight
Cycles.
-Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion.
CONDITION 1:
NO CRACK, CORRO-
SION OR EXISTING
DISBOND REPAIR
FOUND AT A LOCA-
TION INSPECTED IN
ACCORDANCE WITH
PART 1
(a) (b)
-Before further flight.Do PART 3: AREA DISBOND IN-
SPECTION for any disbond in the
area of cracking or corrosion.
CONDITION 2:
ANY CRACK OR COR-
ROSION FOUND AT A
LOCATION INSPECTED
IN ACCORDANCE WITH
PART 1
-Before further flight.(ACTION 1)CONDITION 2.1:
Do PART 5: REPAIR for any crack
or corrosion.
NO DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
4,500 Flight
Cycles.
(a) (b)
-(ACTION 2)
Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion at the unre-
paired area of affected panel.
-Before further flight.(ACTION 1)CONDITION 2.2:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
(d) (e)
-Before further flight.(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
49 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 50

Group 22-24:
Table 4: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Before further flight.Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
CONDITION 3:
ANY EXISTING DIS-
BOND REPAIR FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 1
(d) (e)
-At the times in Table 11 in
Paragraph 1.E., Compliance.
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
CONDITION 3.1:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4
-Before further flight.(ACTION 1)CONDITION 3.2:
Do PART 6: TEMPORARY DIS-
BOND REPAIR in the area of the
disbond.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4 -At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 2)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
-Before further flight.(ACTION 1)CONDITION 4:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 (d) (e)
-Before further flight.(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
50 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 51

Group 22-24:
Table 4: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
At the Repeat
Intervals be-
low.
-Repeat PART 2: EXTERNAL
HIGH FREQUENCY BOND TEST
inspection for any disbond at lap
splices and butt joints listed below:
CONDITION 5:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 5,000 Flight
Cycles.
-S-4L and S-4R lap splice between
BS 259.50 and BS 1016
(a) (b) (c)S-10L and S-10R lap splice be-
tween BS 360 and BS 1016
S-25L and S-25R lap splice be-
tween BS 908 and BS 1016
11,000 Flight
Cycles.
-S-14L and S-14R lap splice be-
tween BS 360 and BS 540
(a) (b) (c)S-14L and S-14R lap splice be-
tween BS 727 and BS 1016
S-19L and S-19R lap splice be-
tween BS 360 and BS 540
S-20L and S-20R lap splice be-
tween BS 727 and BS 1016
S-24R lap splice between BS
259.50 and BS 360
S-25L and S-25R lap splice be-
tween BS 727 and BS 908
S-26L and S-26R lap splice be-
tween BS 360 and BS 540
47,000 Flight
Cycles.
-FWD of BS 360 from S-4L to S-4R
and AFT of BS 360 from S-10L to
S-10R (a) (b) (c)
BS 908 butt joint between S-10L
and S-10R
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
51 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 52

Group 22-24:
Table 4: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
22,000 Flight
Cycles.
-BS 540 butt joint between S-10L
and S-10R
(cont.)
(a) (b) (c)BS 727 butt joint between S-10L
and S-10R
BS 500C butt joint between S-10L
and S-10R
BS 727G butt joint between S-10L
and S-10R
(a) If any Boeing ODA approved preventative modification or repair was previously installed via FAA Form
8100-9 or SRM repair (except disbond repair), initial and repeat inspections are not required at the repaired
location only.
(b) Accomplishment of skin panel replacement using Boeing skin panel manufactured on or after April 01,
1997 is terminating action for all inspections given in this service bulletin at the replaced skin panel only.
(c) Inspection requirements for skin panels replaced with skin panels manufactured by Boeing prior to April
01, 1997 are in Table 9. If the manufacture date is not known, follow the inspection requirements in Table
9.
(d) Any skin panel with existing disbond repair or disbond finding must be inspected at repeat intervals in
accordance with Table 11 until the skin panel is replaced at the compliance time given in Table 11.
(e) Accomplishment of PART 9: SKIN PANEL REPLACEMENT is terminating action to the repeat inspections
at the replaced skin panel only.
Group 19, 30:
Table 5: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
2553 through 2565 that
have accomplished the
one-time internal inspec-
tion in accordance with
SB 737-53-1179 Revision
2 at the original issue
date of this service bul-
letin
(a) (b) (c)
AND
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
52 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 53

Group 19, 30:
Table 5: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
2553 through 2565 that
have not accomplished
the one-time internal in-
spection in accordance
with SB 737-53-1179
Revision 2 at the original
issue date of this service
bulletin
OR
Before 20,000 total flight cycles
whichever occurs later.
(a) (b) (c)
AND
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
(a) (b) (c)
4,500 Flight
Cycles.
-Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion.
CONDITION 1:
NO CRACK, CORRO-
SION OR EXISTING
DISBOND REPAIR
FOUND AT A LOCA-
TION INSPECTED IN
ACCORDANCE WITH
PART 1
(a) (b)
-Before further flight.Do PART 3: AREA DISBOND IN-
SPECTION for any disbond in the
area of cracking or corrosion.
CONDITION 2:
ANY CRACK OR COR-
ROSION FOUND AT A
LOCATION INSPECTED
IN ACCORDANCE WITH
PART 1
-Before further flight.(ACTION 1)CONDITION 2.1:
Do PART 5: REPAIR for any crack
or corrosion.
NO DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
4,500 Flight
Cycles.
(a) (b)
-(ACTION 2)
Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion at the unre-
paired area of affected panel.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
53 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 54

Group 19, 30:
Table 5: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Before further flight.(ACTION 1)CONDITION 2.2:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
(d) (e)
-Before further flight.(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
-Before further flight.Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
CONDITION 3:
ANY EXISTING DIS-
BOND REPAIR FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 1
(d) (e)
-At the times in Table 11 in
Paragraph 1.E., Compliance.
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
CONDITION 3.1:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4
-Before further flight.(ACTION 1)CONDITION 3.2:
Do PART 6: TEMPORARY DIS-
BOND REPAIR in the area of the
disbond.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4 -At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 2)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
54 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 55

Group 19, 30:
Table 5: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Before further flight.(ACTION 1)CONDITION 4:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 (d) (e)
-Before further flight.(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
55 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 56

Group 19, 30:
Table 5: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
At the Repeat
Intervals be-
low.
-Repeat PART 2: EXTERNAL
HIGH FREQUENCY BOND TEST
inspection for any disbond at lap
splices and butt joints listed below:
CONDITION 5:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 5,000 Flight
Cycles.
-S-4L and S-4R lap splice between
BS 259.50 and BS 1016
(a) (b) (c)S-10L and S-10R lap splice be-
tween BS 360 and BS 1016
S-25L and S-25R lap splice be-
tween BS 908 and BS 1016
11,000 Flight
Cycles.
-S-19L lap splice between BS 360
and BS 540
(a) (b) (c)S-20L lap splice between BS 727
and BS 1016
S-19R lap splice between BS 360
and BS 540
S-20R lap splice between BS 727
and BS 1016
S-24R lap splice between BS
259.50 and BS 360
S-25L and S-25R lap splice be-
tween BS 727 and BS 908
S-26L and S-26R lap splice be-
tween BS 360 and BS 540
47,000 Flight
Cycles.
-Butt joint FWD of BS 360 from S-
4L to S-4R and AFT of BS 360
from S-10L to S-10R (a) (b) (c)
BS 908 butt joint between S-10L
and S-10R
22,000 Flight
Cycles.
-BS 540 butt joint between S-10L
and S-10R
(a) (b) (c)BS 727 butt joint between S-10L
and S-10R
(a) If any Boeing ODA approved preventative modification or repair was previously installed via FAA Form
8100-9 or SRM repair (except disbond repair), initial and repeat inspections are not required at the repaired
location only.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
56 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 57

Group 19, 30:
Table 5: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
(b) Accomplishment of skin panel replacement using Boeing skin panel manufactured on or after April 01,
1997 is terminating action for all inspections given in this service bulletin at the replaced skin panel only.
(c) Inspection requirements for skin panels replaced with skin panels manufactured by Boeing prior to April
01, 1997 are in Table 9. If the manufacture date is not known, follow the inspection requirements in Table
9.
(d) Any skin panel with existing disbond repair or disbond finding must be inspected at repeat intervals in
accordance with Table 11 until the skin panel is replaced at the compliance time given in Table 11.
(e) Accomplishment of PART 9: SKIN PANEL REPLACEMENT is terminating action to the repeat inspections
at the replaced skin panel only.
Group 25:
Table 6: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
2560 through 2564 that
have accomplished the
one-time internal inspec-
tion in accordance with
SB 737-53-1179 Revision
2 at the original issue
date of this service bul-
letin
(a) (b) (c)
AND
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 1: EXTERNAL GENER-
AL VISUAL AND DETAILED IN-
SPECTIONS for any crack, corro-
sion or existing disbond repair.
Airplane line numbers
2560 through 2564 that
have not accomplished
the one-time internal in-
spection in accordance
with SB 737-53-1179
Revision 2 at the original
issue date of this service
bulletin
OR
Before 20,000 total flight cycles
whichever occurs later.
(a) (b) (c)
AND
-Within 4,500 Flight Cycles after
the original issue date of this
service bulletin.
Do PART 2: EXTERNAL HIGH
FREQUENCY BOND TEST inspec-
tion for any disbond.
(c)
(a) (b) (c)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: August 23, 2016
737-53A1349
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BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 58

Group 25:
Table 6: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
4,500 Flight
Cycles.
-Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion.
CONDITION 1:
NO CRACK, CORRO-
SION OR EXISTING
DISBOND REPAIR
FOUND AT A LOCA-
TION INSPECTED IN
ACCORDANCE WITH
PART 1
(a) (b)
-Before further flight.Do PART 3: AREA DISBOND IN-
SPECTION for any disbond in the
area of cracking or corrosion.
CONDITION 2:
ANY CRACK OR COR-
ROSION FOUND AT A
LOCATION INSPECTED
IN ACCORDANCE WITH
PART 1
-Before further flight.(ACTION 1)CONDITION 2.1:
Do PART 5: REPAIR for any crack
or corrosion.
NO DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
4,500 Flight
Cycles.
(a) (b)
-(ACTION 2)
Repeat PART 1: EXTERNAL
GENERAL VISUAL AND DE-
TAILED INSPECTIONS for any
crack or corrosion at the unre-
paired area of affected panel.
-Before further flight.(ACTION 1)CONDITION 2.2:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
IN THE AREA OF
CRACKING OR CORRO-
SION, INSPECTED IN
ACCORDANCE WITH
PART 3
(d) (e)
-Before further flight.(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
58 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 59

Group 25:
Table 6: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
-Before further flight.Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
CONDITION 3:
ANY EXISTING DIS-
BOND REPAIR FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 1
(d) (e)
-At the times in Table 11 in
Paragraph 1.E., Compliance.
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
CONDITION 3.1:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4
-Before further flight.(ACTION 1)CONDITION 3.2:
Do PART 6: TEMPORARY DIS-
BOND REPAIR in the area of the
disbond.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 4 -At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 2)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
-Before further flight.(ACTION 1)CONDITION 4:
Do PART 4: SKIN PANEL DIS-
BOND INSPECTION for any dis-
bond at the affected panel.
ANY DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 (d) (e)
-Before further flight.(ACTION 2)
Do PART 6: TEMPORARY DIS-
BOND REPAIR in all areas where
disbond is found.
-At the times in Table 11 in
Paragraph 1.E., Compliance.
(ACTION 3)
Do PART 7: INSPECTION RE-
QUIREMENTS FOR SKIN PAN-
ELS WITH TEMPORARY DIS-
BOND REPAIR OR EXISTING
DISBOND REPAIR for any crack
or corrosion at the affected panel.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
59 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

### Page 60

Group 25:
Table 6: External Inspection of Fuselage Skin Panels for Any Crack, Corrosion, Existing Disbond Repair
and Disbond
Repeat Inter-
val (Not to Ex-
ceed)
Compliance TimeActionCondition
At the Repeat
Intervals be-
low.
-Repeat PART 2: EXTERNAL
HIGH FREQUENCY BOND TEST
inspection for any disbond at lap
splices and butt joints listed below:
CONDITION 5:
NO DISBOND FOUND
ON A SKIN PANEL IN-
SPECTED IN ACCOR-
DANCE WITH PART 2 5,000 Flight
Cycles.
-S-4L and S-4R lap splice between
BS 259.50 and BS 1016
(a) (b) (c)S-10L and S-10R lap splice be-
tween BS 360 and BS 1016
S-25L and S-25R lap splice be-
tween BS 908 and BS 1016
11,000 Flight
Cycles.
-S-19L lap splice between BS 360
and BS 540
(a) (b) (c)S-20L lap splice between BS 727
and BS 1016
S-19R lap splice between BS 360
and BS 540
S-20R lap splice between BS 727
and BS 1016
S-24R lap splice between BS
259.50 and BS 360
S-25L and S-25R lap splice be-
tween BS 727 and BS 908
S-26L and S-26R lap splice be-
tween BS 360 and BS 540
47,000 Flight
Cycles.
-Butt joint FWD of BS 360 from S-
4L to S-4R and AFT of BS 360
from S-10L to S-10R. (a) (b) (c)
BS 908 butt joint between S-10L
and S-10R
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 23, 2016
737-53A1349
60 of 394
BOEING SERVICE BULLETIN 737-53A1349
ALERTALERT

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