# Boeing Alert Service Bulletin 737-53A1351: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2016-5042; AD 2016-20-14 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-53A1351](https://openairdocs.org/service-documents/boeing/737-53a1351.md)
- Title as filed: U.S. DOT/FAA - SB-737-53A1351
- Pages: 53
- PDF: https://openairdocs.org/files/sha256/1d/80/1d80fa2b8de7a6409d08eb4fc44cef70c7fe5a47ff416bd1eb612bb3ac67db6a
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## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1351
Original Issue: July 08, 2015
ATA System: 5330
SUBJECT: FUSELAGE - Skin - Window Corner Inspection
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 © 2015 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: July 08, 2015
737-53A1351
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3.0

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PROPRIETARY - Copyright © Unpublished
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### Page 3

Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 33
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 35
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 35
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38
FIGURE 1: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,
STA 360 TO STA 540 LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40
FIGURE 2: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,
STA 360 TO STA 540 RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42
FIGURE 3: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,
STA 727 TO STA 887 LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44
FIGURE 4: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,
STA 727 TO STA 887 RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 1: WINDOW CORNER
EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887
[Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 2: WINDOW CORNER
EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887
[Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50
APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 3: WINDOW CORNER
EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887
[Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-53A1351Original Issue: July 08, 2015
ATA System: 5330
SUBJECT: FUSELAGE - Skin - Window Corner Inspection
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions to inspect for any crack in the skin around fasteners in window corners
from STA 360 to STA 540 and from STA 727 to STA 887, left and right side between stringers S-10 and S-14.
Widespread Fatigue Damage (WFD) analysis of the 737NG, as required by 14 CFR 26.21(b), has resulted in
the conclusion that the existing MPD Section 9, Airworthiness Limitation Instruction (ALI) inspection program is
not sufficient to preclude the occurrence of WFD in the window corner surround structure from STA 360 to STA
540 and from STA 727 to STA 887, left and right sides between S-10 and S-14, as the airplane ages. The window
corner surround structure has multiple adjacent identical details which have the potential for Multi-Element
Damage (MED) and the potential for WFD. 14 CFR 26.21 requires evaluation of such designs for the potential
for WFD and implementation of the appropriate service actions to ensure that WFD is precluded out to the Limit
of Validity (LOV). Accomplishment of the inspections described in this service bulletin will enable detection and
repair of cracks if they should occur, at the window corner surround structure. Boeing has not received any
in-service fleet reports of cracks in the window corner surround structure. If widespread fatigue cracking is not
found and repaired, the cracks can rapidly link up and can result in possible rapid decompression and loss of
structural integrity.
The window corner surround structure from STA 360 to STA 540 and from STA 727 to STA 887, left and right
sides between S-10 and S-14, has been determined to be structure that is susceptible to WFD.
Boeing Fleet Team Digest 737NG FTD 53-14001 is related to this service bulletin
Boeing Service Related Problem (SRP) 737NG-SRP-53-0474 is 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
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ReferenceAffectedPlanning Data
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
NoOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Do an external High Frequency Eddy Current (HFEC) inspection of the skin around fasteners in window corners
from STA 360 to STA 540 and from STA 727 to STA 887. If no crack is found, do repeat inspections. If any
crack is found, contact The Boeing Company for work instructions and do the work.
EFFECTIVITY
All 737-600, -700, -700C, -800, -900, and -900ER 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.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-19-23 is related to this service bulletin.
The effective date of AD 2013-19-23 is November 7, 2013.
This service bulletin affects Principle Structural Element (PSE) 53-30-05-1, 53-30-05-2, 53-30-05-3, 53-60-05-1,
53-60-05-2, and 53-60-05-3 of Subsection B, Airworthiness Limitations-Structural Inspections of Section 9 of
the 737-600/700/800/900 MPD 626A001-CMR, which is mandated by AD 2013-19-23.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
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### Page 7 (OCR)

BOEING SERVICE BULLETIN 737-53A1351
ALERT  ALERT
MATERIAL INFORMATION
None.
STA
887
STA STA
540  727
S-10L
STA
360
S-10L
- S-14L
DO EXTERNAL HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTIONS OF THE SKIN
AT UPPER AFT AND LOWER FORWARD
WINDOW CORNERS FROM STA 727 TO STA 887.
STA 727-887
(TYPICAL)
S-14L-
DO EXTERNAL HFEC INSPECTIONS OF THE SKIN
AT LOWER AFT AND UPPER FORWARD WINDOW
CORNERS FROM STA 360 TO STA 540.
STA 360-540  2391335
(TYPICAL)
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Export Controlled ECCN: 9E991 - BOEING
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1351
Original Issue: July 08, 2015
ATA System: 5330
SUBJECT: FUSELAGE - Skin - Window Corner Inspection
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is applicable to 737-600/-700/-700C/-800/-900/-900ER Airplanes, line numbers
1-99999 in 3 Groups. The Variable Numbers and Group Information for the applicable airplanes
is given below.
NOTE: The Variable Number table below includes all affected airplanes up to Line Number 6060.
Affected airplanes after Line Number 6060 will be added to the service bulletin's
MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet
Profile Page.
DESCRIPTIONCONFIGURATIONGROUP
737-600/700 airplanes.-1
737-700C/900 airplanes.-2
737-800/900ER airplanes.-3
Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER
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GroupVariable Number
1YA001 - YA099
1YA101 - YA199
1YA201 - YA211
1YA221
1YA231 - YA242
1YA251 - YA256
1YA271 - YA272
1YA291
1YA301 - YA302
1YA311 - YA314
1YA321 - YA323
1YA336 - YA345
1YA351
1YA356 - YA357
1YA366 - YA367
1YA371 - YA377
1YA501 - YA536
1YA541 - YA552
1YA571 - YA578
1YA601 - YA615
1YA621 - YA622
1YA626 - YA631
1YA635 - YA636
1YA641 - YA642
1YA645 - YA650
1YA656 - YA659
1YA666 - YA667
1YA671 - YA672
1YA681 - YA691
1YA701 - YA710
1YA721 - YA722
1YA731 - YA734
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GroupVariable Number
1YA751 - YA756
1YA801 - YA803
1YA809
1YA811 - YA814
1YA831 - YA835
1YA841 - YA862
1YA881 - YA882
1YA891 - YA892
1YA961 - YA978
1YB001 - YB006
1YB101 - YB132
1YB151 - YB153
1YB156 - YB158
1YB161 - YB164
1YB171 - YB172
1YB181 - YB184
1YB201 - YB208
1YB271
1YB276
1YB301 - YB310
1YB371 - YB392
1YB501 - YB502
1YB521 - YB526
1YB541 - YB544
1YB551
1YB561 - YB598
1YB601 - YB636
1YB651
1YB656
1YB671 - YB672
1YB851 - YB863
1YB871 - YB874
1YB881 - YB893
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GroupVariable Number
1YB901 - YB903
1YB911
1YB961 - YB975
1YB981
1YB986 - YB998
3YC001 - YC030
3YC051 - YC084
3YC091 - YC095
3YC101 - YC104
3YC111 - YC113
3YC121
3YC126 - YC127
3YC136 - YC141
3YC146 - YC147
3YC151 - YC156
3YC166 - YC171
3YC176 - YC179
3YC186 - YC190
3YC201 - YC203
3YC206 - YC207
3YC301 - YC305
3YC321 - YC387
3YC391 - YC394
3YC396
3YC401 - YC417
3YC421 - YC422
3YC426 - YC428
3YC436 - YC439
3YC441 - YC448
3YC451 - YC455
3YC459
3YC461 - YC467
3YC471 - YC499
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GroupVariable Number
3YC501 - YC526
3YC571 - YC583
3YC587 - YC589
3YC591 - YC593
3YC601 - YC655
3YC681 - YC696
3YC701 - YC715
3YC720 - YC725
3YC727 - YC752
3YC761 - YC770
3YC781 - YC793
3YC801 - YC892
3YC901 - YC907
3YC921 - YC922
3YC931 - YC932
3YC941 - YC951
3YC971 - YC978
3YC981 - YC983
3YD001 - YD007
3YD021 - YD025
3YD041 - YD057
3YD081 - YD084
3YD101 - YD117
3YD121 - YD126
3YD151 - YD159
3YD171 - YD172
3YD201 - YD203
3YD206 - YD209
3YD216 - YD219
3YD251 - YD254
3YD256 - YD257
3YD261
3YD301 - YD334
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GroupVariable Number
3YD391
3YD401 - YD410
3YD412 - YD422
3YD481 - YD485
3YD491 - YD499
2YD501 - YD512
2YD531 - YD535
2YD541 - YD547
2YD561 - YD564
2YD571 - YD572
2YD591 - YD595
2YD601 - YD612
2YD651 - YD655
1YE001 - YE020
1YE051
1YE101 - YE109
1YE151 - YE157
1YE171 - YE172
1YE201 - YE206
1YE301 - YE305
1YE321 - YE326
1YE371 - YE383
3YF001 - YF011
3YF021 - YF049
3YF051 - YF080
3YF086 - YF087
3YF106 - YF107
3YF111 - YF114
3YF116 - YF119
3YF121 - YF132
3YF176 - YF178
3YF191 - YF192
3YF201 - YF276
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GroupVariable Number
3YF401 - YF402
3YF431 - YF432
3YF436 - YF437
3YF441 - YF442
3YF451 - YF460
3YF501 - YF599
3YF601 - YF685
3YF691 - YF695
3YF701 - YF707
3YF801 - YF805
3YF831 - YF832
3YF836 - YF838
3YF871 - YF872
3YF901 - YF905
3YF921 - YF928
3YF951 - YF954
1YG001 - YG044
1YG061 - YG064
1YG066 - YG089
1YG091 - YG099
1YG101 - YG104
1YG111 - YG114
1YG116 - YG146
1YG201 - YG205
1YG211 - YG214
1YG221 - YG224
1YG251 - YG252
2YG501 - YG515
2YG601 - YG602
2YG701
2YG711
2YG721 - YG722
3YH001 - YH012
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GroupVariable Number
3YH031 - YH055
3YH071 - YH080
3YH101 - YH132
3YH201 - YH202
3YH206 - YH207
3YH301 - YH307
3YH321 - YH322
3YH501 - YH542
3YH551 - YH594
3YH601 - YH606
3YH611 - YH620
3YH631 - YH632
3YH636 - YH637
3YH641
3YH681 - YH683
3YH701 - YH740
3YH751 - YH755
3YH801 - YH856
3YH901 - YH908
3YH911 - YH915
3YH951 - YH952
3YJ001 - YJ013
3YJ021
3YJ471 - YJ480
3YJ501 - YJ517
3YJ531 - YJ579
3YJ591 - YJ599
3YJ631 - YJ632
3YJ671 - YJ694
3YJ801 - YJ867
3YJ871 - YJ880
3YJ901 - YJ904
3YJ908 - YJ929
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GroupVariable Number
3YJ931 - YJ937
3YJ941 - YJ956
3YJ961
3YJ976 - YJ977
3YK001 - YK007
3YK101 - YK104
3YK111 - YK112
3YK121 - YK122
3YK131 - YK133
3YK136 - YK139
3YK141 - YK142
3YK146 - YK148
3YK151 - YK154
3YK161 - YK167
3YK171
3YK176 - YK177
3YK186
3YK191
3YK196
3YK201 - YK202
3YK301 - YK314
3YK321 - YK340
3YK361 - YK378
3YK401 - YK406
3YK426 - YK427
3YK431 - YK450
3YK456 - YK467
3YK471 - YK473
3YK476
3YK478
3YK480 - YK487
3YK491 - YK493
3YK495 - YK499
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GroupVariable Number
3YK511 - YK516
3YK521 - YK530
3YK551 - YK571
3YK576 - YK577
3YK580 - YK585
3YK601 - YK602
3YK606 - YK607
3YK611 - YK616
3YK621 - YK634
3YK641 - YK644
3YK651 - YK665
3YK671 - YK672
3YK676 - YK677
3YK681 - YK686
3YK691
3YK695 - YK699
3YK701 - YK713
3YK716 - YK719
3YK721 - YK741
3YK751 - YK770
3YK776 - YK778
3YK781 - YK785
3YK791 - YK792
3YK796 - YK797
3YK801 - YK899
3YK901 - YK912
3YK918 - YK919
3YK921 - YK929
3YK941 - YK999
3YL001 - YL005
3YL011 - YL016
3YL021 - YL024
3YL051 - YL052
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GroupVariable Number
3YL056 - YL057
3YL061
3YL066 - YL069
3YL076 - YL077
3YL101 - YL137
3YL201 - YL237
3YL241 - YL242
3YL271 - YL272
3YL281 - YL284
3YL301 - YL303
3YL311 - YL314
3YL316 - YL321
3YL351 - YL353
3YL371 - YL374
3YL401
3YL421 - YL429
3YL431 - YL444
3YL461 - YL478
3YL501 - YL509
3YL531 - YL534
3YL541 - YL551
3YL561 - YL579
3YL591 - YL598
3YL601 - YL606
3YL611 - YL612
3YL616 - YL617
3YL621
3YL626
3YL631 - YL634
3YL636 - YL637
3YL661 - YL664
3YL676 - YL691
3YL696 - YL697
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GroupVariable Number
3YL701 - YL707
3YL731
3YL751 - YL752
3YL756 - YL757
3YL761 - YL780
3YL796 - YL797
3YL801 - YL815
3YL901 - YL910
3YL921 - YL940
3YL951 - YL968
1YM101 - YM103
1YM201 - YM244
1YM251 - YM299
1YM301 - YM399
1YM401 - YM415
1YM471
1YM481 - YM484
1YM501 - YM515
1YM521 - YM522
1YM541
1YM551 - YM553
1YM571 - YM572
1YM581 - YM582
1YM591 - YM599
1YM631 - YM634
1YM641 - YM652
1YM671 - YM674
1YM691 - YM699
1YM701 - YM710
1YM761 - YM765
1YM771 - YM779
1YN001 - YN016
1YN021 - YN024
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GroupVariable Number
1YN061
1YN071 - YN082
1YN091 - YN092
1YN101 - YN112
1YN121
1YN126
1YN201 - YN202
1YN211 - YN219
1YN231 - YN236
1YN261
1YN501
1YN531 - YN534
1YN551 - YN566
1YN581 - YN585
1YN591 - YN592
1YN601 - YN606
1YN651 - YN653
1YN701 - YN702
1YN741 - YN746
1YN756
3YQ001 - YQ003
3YQ011 - YQ021
3YQ026 - YQ029
3YQ036 - YQ045
3YQ201 - YQ207
3YQ231
3YQ241 - YQ251
3YQ281 - YQ284
3YQ291 - YQ296
3YQ301 - YQ302
3YQ321 - YQ324
3YQ331 - YQ334
3YQ346 - YQ347
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GroupVariable Number
3YQ351 - YQ362
3YQ371
3YQ401 - YQ403
3YQ451 - YQ454
3YQ456
3YQ461
3YQ471
3YQ501 - YQ520
3YR001 - YR044
3YR051 - YR098
3YR101 - YR105
3YR111 - YR124
3YR126 - YR144
3YR166 - YR182
3YR186 - YR198
3YR201 - YR204
3YR231 - YR294
3YR296 - YR297
3YR301 - YR334
3YR338 - YR341
3YR361 - YR366
3YR371 - YR373
3YR376 - YR377
3YR381 - YR382
3YR386 - YR388
3YR391
3YR396 - YR398
3YR401 - YR405
3YR411 - YR413
3YR416 - YR418
3YR421 - YR424
3YR426 - YR455
3YR457 - YR499
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GroupVariable Number
3YR501 - YR506
3YR511 - YR520
3YR526 - YR544
3YR546 - YR551
3YR556 - YR562
3YR571 - YR582
3YR591 - YR592
3YR601 - YR605
3YR616 - YR658
3YR661 - YR663
3YR671 - YR672
3YR676 - YR678
3YR681 - YR682
3YR701 - YR769
3YR771 - YR799
3YR801 - YR820
3YR831 - YR838
3YR841 - YR899
3YR901 - YR903
3YR931 - YR934
3YR938 - YR944
3YR951 - YR976
3YR981 - YR996
3YS001 - YS002
3YS006 - YS009
3YS031 - YS032
3YS051 - YS073
3YS101 - YS120
3YS126 - YS142
3YS146 - YS148
3YS151 - YS160
3YS166 - YS194
3YS196 - YS197
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GroupVariable Number
3YS201 - YS209
3YS221 - YS225
3YS231 - YS236
3YS271 - YS288
3YS301 - YS346
3YS351 - YS368
3YS371 - YS377
3YS381 - YS383
3YS401
3YS451
3YS456 - YS457
3YS462
3YS467
3YS501 - YS502
3YS506
3YS511 - YS516
3YS531
3YS536 - YS538
3YS541
3YS551 - YS556
3YS561 - YS578
3YS581 - YS595
3YS601 - YS690
3YS701 - YS708
3YS721 - YS762
3YS771 - YS780
3YS806 - YS810
3YS816 - YS818
3YS823 - YS825
3YS851 - YS861
3YS876
3YS881 - YS883
3YS901 - YS909
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GroupVariable Number
3YS911 - YS939
3YS951
3YS956 - YS957
3YS961 - YS965
3YS981 - YS987
3YS991 - YS998
3YT001 - YT004
3YT006
3YT026 - YT027
3YT031 - YT032
3YT036 - YT038
3YT061 - YT068
3YT101 - YT117
3YT126 - YT131
3YT136 - YT138
3YT176 - YT181
3YT191
3YT196 - YT199
3YT201
3YT206 - YT207
3YT211 - YT213
3YT251 - YT283
3YT301 - YT307
3YT311 - YT312
3YT321 - YT341
3YT381
3YT391 - YT395
3YT401 - YT403
3YT411 - YT417
3YT427
3YT461 - YT474
3YT491 - YT492
3YT501 - YT520
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GroupVariable Number
3YT551 - YT552
3YT556 - YT559
3YT561 - YT563
3YT571
3YT601 - YT606
3YT701 - YT706
3YT761 - YT780
3YT791 - YT793
3YT796 - YT797
3YT801 - YT804
3YT811 - YT813
3YT826 - YT827
3YT831 - YT832
3YT851 - YT852
3YT856 - YT859
3YT891 - YT895
3YT901 - YT925
3YU001 - YU054
3YU201 - YU212
3YV001 - YV002
3YV006 - YV008
3YV041 - YV042
3YV045 - YV047
3YV081
3YV083
3YV097
3YV101 - YV119
3YV301 - YV305
3YV351 - YV356
3YV381 - YV382
3YV431 - YV433
3YV501
3YV521
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GroupVariable Number
3YV571 - YV574
3YV601 - YV605
3YV651 - YV654
3YV711
3YV741
3YV781
3YV801
3YV881 - YV883
3YW001
3YW011 - YW032
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to inspect for any crack in the skin around fasteners in window
corners from STA 360 to STA 540 and from STA 727 to STA 887, left and right side between stringers
S-10 and S-14. Widespread Fatigue Damage (WFD) analysis of the 737NG, as required by 14 CFR
26.21(b), has resulted in the conclusion that the existing MPD Section 9, Airworthiness Limitation
Instruction (ALI) inspection program is not sufficient to preclude the occurrence of WFD in the window
corner surround structure from STA 360 to STA 540 and from STA 727 to STA 887, left and right sides
between S-10 and S-14, as the airplane ages. The window corner surround structure has multiple
adjacent identical details which have the potential for Multi-Element Damage (MED) and the potential
for WFD. 14 CFR 26.21 requires evaluation of such designs for the potential for WFD and implementation
of the appropriate service actions to ensure that WFD is precluded out to the Limit of Validity (LOV).
Accomplishment of the inspections described in this service bulletin will enable detection and repair of
cracks if they should occur, at the window corner surround structure. Boeing has not received any
in-service fleet reports of cracks in the window corner surround structure. If widespread fatigue cracking
is not found and repaired, the cracks can rapidly link up and can result in possible rapid decompression
and loss of structural integrity.
The window corner surround structure from STA 360 to STA 540 and from STA 727 to STA 887, left
and right sides between S-10 and S-14, has been determined to be structure that is susceptible to
WFD.
Boeing Fleet Team Digest 737NG FTD 53-14001 is related to this service bulletin
Boeing Service Related Problem (SRP) 737NG-SRP-53-0474 is related to this service bulletin.
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D. Description
Do an external High Frequency Eddy Current (HFEC) inspection of the skin around fasteners in window
corners from STA 360 to STA 540 and from STA 727 to STA 887. If no crack is found, do repeat
inspections. If any crack is found, contact The Boeing Company for work instructions and do the work.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
231, 232, 241, 242737-600, 737-700
Group 2:
Affected Maintenance Zones
ZoneModel
231, 232, 241, 242737-700C, 737-900
Group 3:
Affected Maintenance Zones
ZoneModel
231, 232, 241, 242737-800, 737-900ER
E. 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.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-19-23 is related to this service
bulletin. The effective date of AD 2013-19-23 is November 7, 2013.
Logic diagrams showing compliance times and compliance tasks are included as an aid in Appendix
A, B, and C.
For airplanes which have incorporated Boeing Business Jet Lower Cabin Altitude Supplemental Type
Certificate ST01697SE (6,500 feet maximum cabin altitude in lieu of 8,000 feet) as referenced in Boeing
Service Bulletin 737-21-1149, the flight cycle related compliance times are different from those specified
in this service bulletin. The initial compliance time (threshold) for 737-700 airplanes must be reduced
to 46,000 total flight cycles and the repeat interval must be reduced to 3,400 flight cycles. The initial
compliance time (threshold) for 737-800, -900ER airplanes must be reduced to 39,000 total flight cycles
and the repeat interval must be reduced to 3,400 flight cycles.
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For airplanes that have not incorporated Boeing Business Jet Lower Cabin Altitude Supplemental Type
Certificate ST01697SE (6,500 feet maximum cabin altitude in lieu of 8,000 feet) as referenced in Boeing
Service Bulletin 737-21-1149: This service bulletin affects PSE 53-30-05-2 and 53-60-05-2 of Subsection
B, Airworthiness Limitations-Structural Inspections of Section 9 of the 737-600/700/800/900 MPD
626A001-CMR Table 9-2, which is mandated by AD 2013-19-23. The inspections in this bulletin are
for the skin surrounding the passenger window frame at two of the four corners and must be
accomplished in addition to the 737-600/700/800/900 MPD D626A001-CMR inspections (which apply
only to the window frames), beginning at the threshold identified in section E of this bulletin.
For airplanes which have incorporated Boeing Business Jet Lower Cabin Altitude Supplemental Type
Certificate ST01697SE (6,500 feet maximum cabin altitude in lieu of 8,000 feet) as referenced in Boeing
Service Bulletin 737-21-1149: This service bulletin affects Principle Structural Element (PSE) 53-30-05-1,
53-30-05-2, 53-30-05-3, 53-60-05-1, 53-60-05-2, and 53-60-05-3 of Subsection B, Airworthiness
Limitations-Structural Inspections of Section 9 of the 737-600/700/800/900 MPD 626A001-CMR Table
9-3, which is mandated by AD 2013-19-23. The inspections in this bulletin are for the skin surrounding
the passenger window frames at two of the four corners and must be accomplished in addition to the
737-600/700/800/900 MPD D626A001-CMR inspections beginning at the threshold identified in section
E of this bulletin. 737-600/700/800/900 MPD D626A001-CMR PSE number 53-30-05-3 and 53-60-05-3
inspections apply to the skin completely surrounding the passenger window frames. 737-600/700/800/900
MPD D626A001-CMR PSE number 53-30-05-1, 53-60-05-1, 53-30-05-2 and 53-60-05-2 inspections
apply only to the window frames.
Do the required actions in accordance with Paragraph 3., Accomplishment Instructions.
Group 1:
Table 1: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before 64,000 total flight cycles.Do PART 1: WINDOW
CORNER EXTERNAL
HFEC INSPECTION
FROM STA 360 TO STA
540 AND FROM STA 727
TO STA 887, LEFT AND
RIGHT SIDE for any
crack.
All Airplanes
4,600 flight cycles.-Repeat PART 1: WIN-
DOW CORNER EXTER-
NAL HFEC INSPECTION
FROM STA 360 TO STA
540 AND FROM STA 727
TO STA 887, LEFT AND
RIGHT SIDE for any
crack.
CONDITION 1: NO
CRACK FOUND
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Group 1:
Table 1: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before Further Flight.ACTION 1:CONDITION 2: ANY
CRACK FOUND Contact The Boeing
Company for repair in-
structions and do the re-
pair.
4,600 flight cycles.-ACTION 2:
Repeat PART 1: WIN-
DOW CORNER EXTER-
NAL HFEC INSPECTION
FROM STA 360 TO STA
540 AND FROM STA 727
TO STA 887, LEFT AND
RIGHT SIDE for any
crack at the unrepaired
areas.
Group 2:
Table 2: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before 58,000 total flight cycles.Do PART 1: WINDOW
CORNER EXTERNAL
HFEC INSPECTION
FROM STA 360 TO STA
540 AND FROM STA 727
TO STA 887, LEFT AND
RIGHT SIDE for any
crack.
All Airplanes
4,600 flight cycles.-Repeat PART 1: WIN-
DOW CORNER EXTER-
NAL HFEC INSPECTION
FROM STA 360 TO STA
540 AND FROM STA 727
TO STA 887, LEFT AND
RIGHT SIDE for any
crack.
CONDITION 1: NO
CRACK FOUND
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Group 2:
Table 2: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before Further Flight.ACTION 1:CONDITION 2: ANY
CRACK FOUND Contact The Boeing
Company for repair in-
structions and do the re-
pair.
4,600 flight cycles.-ACTION 2:
Repeat PART 1: WIN-
DOW CORNER EXTER-
NAL HFEC INSPECTION
FROM STA 360 TO STA
540 AND FROM STA 727
TO STA 887, LEFT AND
RIGHT SIDE for any
crack at the unrepaired
areas.
Group 3:
Table 3: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before 53,000 total flight cycles.Do PART 1: WINDOW
CORNER EXTERNAL
HFEC INSPECTION
FROM STA 360 TO STA
540 AND FROM STA 727
TO STA 887, LEFT AND
RIGHT SIDE for any
crack.
All Airplanes
4,600 flight cycles.-Repeat PART 1: WIN-
DOW CORNER EXTER-
NAL HFEC INSPECTION
FROM STA 360 TO STA
540 AND FROM STA 727
TO STA 887, LEFT AND
RIGHT SIDE for any
crack.
CONDITION 1: NO
CRACK FOUND
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Group 3:
Table 3: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before Further Flight.ACTION 1:CONDITION 2: ANY
CRACK FOUND Contact The Boeing
Company for repair in-
structions and do the re-
pair.
4,600 flight cycles.-ACTION 2:
Repeat PART 1: WIN-
DOW CORNER EXTER-
NAL HFEC INSPECTION
FROM STA 360 TO STA
540 AND FROM STA 727
TO STA 887, LEFT AND
RIGHT SIDE for any
crack at the unrepaired
areas.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
This service bulletin is also approved for airplanes having FAA Aviation Partners Boeing (APB)
Supplemental Type Certificate (STC) number ST00830SE installed (not including any areas affected
by the split scimitar winglet configuration).
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools.
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Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Inspect
0.500.50TOTAL FOR EACH WINDOW (a)
(a) Estimate for each window, multiply number of windows to be inspected by the
estimate given to arrive at the total for each aircraft.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not applicable.
J. References
1. Existing Data:
a. Boeing Service Bulletin 737-21-1149
b. Boeing Service Related Problem (SRP) 737NG-SRP-53-0474
c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2013-19-23
d. Service Bulletin Index D6-19567
e. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00
f. 737-600/700/800/900 Maintenance Planning Data (MPD)
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
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### Page 34

L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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### Page 35

2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
None.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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BLANK PAGE

### Page 37

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 737 Structural Repair Manual,
Chapter 51.
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
6. Boeing Service Letter 737-SL-51-042, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
7. Refer to Appendix A, B, and C for logic diagrams. Logic diagrams are provided as
an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information in Paragraph 3.B., Work Instructions is the
primary source for tasks required for compliance.
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### Page 38

8. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
9. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
10. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
11. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
12. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
13. The CONDITIONS, ACTIONS and OPTIONS shown apply to each inspection location
independently.
14. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. An Alternative Method of
Compliance (AMOC) is required for any deviations to RC steps, including sub-steps
and identified figures. Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection program without
obtaining approval of an AMOC. This is provided that the RC steps, including
sub-steps and identified figures, can still be done as specified, and the airplane can
be put back in an airworthy condition.
B. WORK INSTRUCTIONS
1. RC - Do PART 1: WINDOW CORNER EXTERNAL HFEC INSPECTION FROM STA 360 TO STA
540 AND FROM STA 727 TO STA 887, LEFT AND RIGHT SIDE for any crack.
a. CONDITION 1: NO CRACK FOUND.
(1) RC - Repeat PART 1: WINDOW CORNER EXTERNAL SURFACE HFEC INSPECTION
FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887 for any crack at the
repeat interval in Paragraph 1.E., Compliance.
b. CONDITION 2: ANY CRACK FOUND.
(1) RC - ACTION 1: Contact The Boeing Company for repair instructions and do the repair.
(2) RC - ACTION 2: Repeat PART 1: WINDOW CORNER EXTERNAL HFEC INSPECTION
FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887, LEFT AND RIGHT
SIDE for any crack at the unrepaired areas.
2. Put the airplane back to a serviceable condition.
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### Page 39

PART 1: WINDOW CORNER EXTERNAL HFEC INSPECTION FROM STA 360 TO STA 540 AND
FROM STA 727 TO STA 887, LEFT AND RIGHT SIDE
1. Do the following inspections:
NOTE: If a Boeing ODA approved repair via FAA Form 8100-9 was installed to eliminate cracking
that was previously found, inspections in the window corner are not required at the repaired
location only.
Group 2:
NOTE: For 737-700C airplanes, inspections are not required at the windows in the main deck
cargo door located between STA 360 and STA 540.
a. Do an external High Frequency Eddy Current (HFEC) inspection for any crack in the skin at
the upper forward and lower aft corners of each left side window from STA 360 to STA 540
in accordance with FIGURE 1.
b. Do an external HFEC inspection for any crack in the skin at the upper forward and lower aft
corners of each right side window from STA 360 to STA 540 in accordance with FIGURE 2.
c. Do an external HFEC inspection for any crack in the skin at the lower forward and upper aft
corners of each left side window from STA 727 to STA 887 in accordance with FIGURE 3.
d. Do an external HFEC inspection for any crack in the skin at the lower forward and upper aft
corners of each right side window from STA 727 to STA 887 in accordance with FIGURE 4.
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### Page 40 (OCR)

BOEING SERVICE BULLETIN 737-53A1351
ALERT  ALERT
STA
360
S-10L-
•
12 LOCATIONS 1
12 LOCATIONS
S-14L -
FWD
STA 360-540  2391513
(TYPICAL)
FIGURE 1: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,
STA 360 TO STA 540 LEFT SIDE
(SHEET 1 OF 2)
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### Page 41

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)--SkinInspect1
(a) Do an external HFEC inspection for any crack in the skin around the fasteners in window corners in
accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 23.
FIGURE 1: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,
STA 360 TO STA 540 LEFT SIDE
(SHEET 2 OF 2)
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### Page 42 (OCR)

BOEING SERVICE BULLETIN 737-53A1351
ALERT  ALERT
STA
540
STA
360
- S-10R
1) 12 LOCATIONS
12 LOCATIONS
1 - 8-141
FWD
STA 360-540  2391548
(TYPICAL)
FIGURE 2: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,
STA 360 TO STA 540 RIGHT SIDE
(SHEET 1 OF 2)
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### Page 43

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)--SkinInspect1
(a) Do an external HFEC inspection for any crack in the skin around the fasteners in window corners in
accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 23.
FIGURE 2: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,
STA 360 TO STA 540 RIGHT SIDE
(SHEET 2 OF 2)
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### Page 44 (OCR)

BOEING SERVICE BULLETIN 737-53A1351
ALERT  ALERT
STA
887
STA
727
------ -S-10L
12 LOCATIONS
12 LOCATIONS
EFFEER337333321-S10L
FWD
STA 727-887  2391582
(TYPICAL)
FIGURE 3: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,
STA 727 TO STA 887 LEFT SIDE
(SHEET 1 OF 2)
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### Page 45

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)--SkinInspect1
(a) Do an external HFEC inspection for any crack in the skin around the fasteners in window corners in
accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 23.
FIGURE 3: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,
STA 727 TO STA 887 LEFT SIDE
(SHEET 2 OF 2)
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### Page 46 (OCR)

BOEING SERVICE BULLETIN 737-53A1351
ALERT  ALERT
STA
887
727
S-10R -
ЕІІІІøоооот777
TO O
•
•
_ 12 LOCATIONS
S-14R -
......
FWD
STA 727-887  2391570
(TYPICAL)
FIGURE 4: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,
STA 727 TO STA 887 RIGHT SIDE
(SHEET 1 OF 2)
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### Page 47

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)--SkinInspect1
(a) Do an external HFEC inspection for any crack in the skin around the fasteners in window corners in
accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 23.
FIGURE 4: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,
STA 727 TO STA 887 RIGHT SIDE
(SHEET 2 OF 2)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN 737-53A1351
ALERT  ALERT
This Appendix applies only to: Group 1.
Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
BEFORE 64,000 TOTAL
FLIGHT CYCLES
DO PART 1
CONDITION 1  CONDITION 2
4,600 FLIGHT  BEFORE FURTHER
CYCLES  FLIGHT
REPEAT  ACTION 1: CONTACT THE
PART 1  BOEING COMPANY FOR
REPAIR INSTRUCTIONS
AND DO THE REPAIR
4,600 FLIGHT
CYCLES
ACTION 2: REPEAT
PART 1 AT THE
UNREPAIRED AREAS
2394946
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 1: WINDOW CORNER
EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887
(SHEET 1 OF 2)
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### Page 49

1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
WINDOW CORNER EXTERNAL HFEC INSPECTION FROM STA 360 TO
STA 540 AND FROM STA 727 TO STA 887, LEFT AND RIGHT SIDE
PART 1
NO CRACK FOUNDCONDITION 1
ANY CRACK FOUNDCONDITION 2
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 1: WINDOW CORNER
EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887
(SHEET 2 OF 2)
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### Page 50 (OCR)

BOEING SERVICE BULLETIN 737-53A1351
ALERT  ALERT
This Appendix applies only to: Group 2.
Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
BEFORE 58,000 TOTAL
FLIGHT CYCLES
DO PART 1
CONDITION 1  CONDITION 2
4,600 FLIGHT  BEFORE FURTHER
CYCLES  FLIGHT
REPEAT  ACTION 1: CONTACT THE
PART 1  BOEING COMPANY FOR
REPAIR INSTRUCTIONS
AND DO THE REPAIR
4,600 FLIGHT
CYCLES
ACTION 2: REPEAT
PART 1 AT THE
UNREPAIRED AREAS
2394952
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 2: WINDOW CORNER
EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887
(SHEET 1 OF 2)
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### Page 51

1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
WINDOW CORNER EXTERNAL HFEC INSPECTION FROM STA 360 TO
STA 540 AND FROM STA 727 TO STA 887, LEFT AND RIGHT SIDE
PART 1
NO CRACK FOUNDCONDITION 1
ANY CRACK FOUNDCONDITION 2
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 2: WINDOW CORNER
EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887
(SHEET 2 OF 2)
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### Page 52 (OCR)

BOEING SERVICE BULLETIN 737-53A1351
ALERT  ALERT
This Appendix applies only to: Group 3.
Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
BEFORE 53,000 TOTAL
FLIGHT CYCLES
→
DO PART 1
CONDITION 1  CONDITION 2
4,600 FLIGHT  BEFORE FURTHER
CYCLES  FLIGHT
REPEAT  PART 1  ACTION 1: CONTACT THE  BOEING COMPANY FOR
REPAIR INSTRUCTIONS
AND DO THE REPAIR
4,600 FLIGHT
CYCLES
ACTION 2: REPEAT
PART 1 AT THE
UNREPAIRED AREAS
2394961
APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 3: WINDOW CORNER
EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887
(SHEET 1 OF 2)
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### Page 53

1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
WINDOW CORNER EXTERNAL HFEC INSPECTION FROM STA 360 TO
STA 540 AND FROM STA 727 TO STA 887, LEFT AND RIGHT SIDE
PART 1
NO CRACK FOUNDCONDITION 1
ANY CRACK FOUNDCONDITION 2
APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 3: WINDOW CORNER
EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887
(SHEET 2 OF 2)
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---
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