# Boeing Alert Service Bulletin 737-53A1352: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2016-5034; AD 2016-22-13 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-53A1352](https://openairdocs.org/service-documents/boeing/737-53a1352.md)
- Title as filed: SB-737-53A1352 R0
- Pages: 49
- PDF: https://openairdocs.org/files/sha256/70/bb/70bb7f5ba57df41adbb1428b882650bf8c9bd8bf3a99f50e708e26c9ba0a3d8c
- Page: https://openairdocs.org/service-documents/boeing/737-53a1352/file/70bb7f5ba57d

## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1352
Original Issue: October 02, 2015
ATA System: 5331
SUBJECT: FUSELAGE - Skin - S-14 Lap Splice Lower Fastener Row 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Unpublished Work.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.
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737-53A1352
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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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 32
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
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: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW [Group 1] . . . . . 40
FIGURE 2: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW [Group 2] . . . . . 43
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: INSPECTION FOR ANY
CRACK AT S-14 LAP SPLICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 2: INSPECTION FOR ANY
CRACK AT S-14 LAP SPLICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-53A1352Original Issue: October 02, 2015
ATA System: 5331
SUBJECT: FUSELAGE - Skin - S-14 Lap Splice Lower Fastener Row 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
Widespread Fatigue Damage (WFD) analysis of the 737NG, as required by 14 CFR 26.21(b), has resulted in
the conclusion that the existing 737-600/700/800/900 MPD Section 9, Airworthiness Limitation Instruction (ALI)
inspection program is not sufficient to preclude the occurrence of WFD in the S-14L and S-14R lap splice, lower
fastener rows between STA 360-540 and STA 727-887 as the airplane ages. These lap splices have multiple
adjacent identical details which have the potential for Multi-Site Damage (MSD) 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). Boeing has not received any
in-service fleet reports of cracks in these lap splices. Accomplishment of the inspections described in this service
bulletin will enable detection and repair of cracks if they should occur, at these lap splices. 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.
This Service Bulletin provides more frequent external inspection of the S-14 lap splices in order to prevent WFD
out to the LOV.
The fuselage skin S-14L and S-14R lap splice lower fastener row between STA 360 to STA 540 and STA 727
to STA 887 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-53-00471 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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### Page 6

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
Group 1:
1. Do PART 1: Low Frequency Eddy Current (LFEC) Inspection for any crack on the S-14L and S-14R
lap splice, lower fastener row, between STA 360 to STA 540 and STA 727 to STA 887. If no crack is
found, repeat PART 1: LFEC INSPECTION at the repeat interval in Paragraph 1.E., Compliance. If
any crack is found, contact The Boeing Company to get instructions for S-14 lap splice crack repair
and do the repair.
Group 2:
1. Do PART 1: Low Frequency Eddy Current (LFEC) Inspection for any crack on S-14L lap splice, lower
fastener row, between STA 500 to STA 540 and STA 727 to STA 887 and S-14R lap splice, lower
fastener row, between STA 360 to STA 540 and STA 727 to STA 887. If no crack is found, repeat
PART 1: LFEC INSPECTION at the repeat interval in Paragraph 1.E., Compliance. If any crack is
found, contact The Boeing Company for repair instructions and do the repair.
EFFECTIVITY
All 737-600/-700/-700C/-800/-900/-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.
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This service bulletin affects Principle Structural Element (PSE) 53-30-04-6, 53-30-04-6a, 53-60-04-6 and
53-60-04-6a of Subsection B, Airworthiness Limitations-Structural Inspections of 737-600/700/800/900 MPD
Section 9, 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 procedures given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
None.
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### Page 8 (OCR)

BOEING SERVICE BULLETIN 737-53A1352
ALERT  ALERT
STA
887
STA 540
STA
360
S-14L
S-14R
UPPER SKIN
STRINGER
TYPICAL CRACK
S-14
GROUP 1  - LOWER SKIN
DO PART 1 LOW FREQUENCY EDDY CURRENT (LFEC)
INSPECTION FOR ANY CRACK ON THE S-14L AND
S-14R LAP SPLICE, LOWER FASTENER ROW, BETWEEN
STA 360 TO STA 540 AND STA 727 TO STA 887
GROUP 2
DO PART 1 LOW FREQUENCY EDDY CURRENT (LFEC)
INSPECTION FOR ANY CRACK ON THE S-14L LAP
SPLICE, LOWER FASTENER ROW, BETWEEN STA 500
STA 540 AND STA 727 TO STA 887 AND S-14R LAP
SPLICE, LOWER FASTENER ROW, BETWEEN STA 360
TO STA 540 AND STA 727 TO STA 887  RIGHT SIDE SHOWN LEFT SIDE OPPOSITE  2387015
Original Issue: October 02, 2015
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1352
Original Issue: October 02, 2015
ATA System: 5331
SUBJECT: FUSELAGE - Skin - S-14 Lap Splice Lower Fastener Row 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 all 737-600/-700/-700C/-800/-900/-900ER Airplanes, line
numbers 1-99999 in 2 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/-800/-900/-900ER Passenger airplane.-1
737-700C Convertible airplane.-2
Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER
GroupVariable Number
1YA001 - YA099
1YA101 - YA199
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GroupVariable Number
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
1YA751 - YA756
1YA801 - YA803
1YA809
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GroupVariable Number
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
1YB901 - YB903
1YB911
1YB961 - YB975
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GroupVariable Number
1YB981
1YB986 - YB998
1YC001 - YC030
1YC051 - YC084
1YC091 - YC095
1YC101 - YC104
1YC111 - YC113
1YC121
1YC126 - YC127
1YC136 - YC141
1YC146 - YC147
1YC151 - YC156
1YC166 - YC171
1YC176 - YC179
1YC186 - YC190
1YC201 - YC203
1YC206 - YC207
1YC301 - YC305
1YC321 - YC387
1YC391 - YC394
1YC396
1YC401 - YC417
1YC421 - YC422
1YC426 - YC428
1YC436 - YC439
1YC441 - YC448
1YC451 - YC455
1YC459
1YC461 - YC467
1YC471 - YC499
1YC501 - YC526
1YC571 - YC583
1YC587 - YC589
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GroupVariable Number
1YC591 - YC593
1YC601 - YC655
1YC681 - YC696
1YC701 - YC715
1YC720 - YC725
1YC727 - YC752
1YC761 - YC770
1YC781 - YC793
1YC801 - YC892
1YC901 - YC907
1YC921 - YC922
1YC931 - YC932
1YC941 - YC951
1YC971 - YC978
1YC981 - YC983
1YD001 - YD007
1YD021 - YD025
1YD041 - YD057
1YD081 - YD084
1YD101 - YD117
1YD121 - YD126
1YD151 - YD159
1YD171 - YD172
1YD201 - YD203
1YD206 - YD209
1YD216 - YD219
1YD251 - YD254
1YD256 - YD257
1YD261
1YD301 - YD334
1YD391
1YD401 - YD410
1YD412 - YD422
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GroupVariable Number
1YD481 - YD485
1YD491 - YD499
1YD501 - YD512
1YD531 - YD535
1YD541 - YD547
1YD561 - YD564
1YD571 - YD572
1YD591 - YD595
1YD601 - YD612
1YD651 - YD655
1YE001 - YE020
1YE051
1YE101 - YE109
1YE151 - YE157
1YE171 - YE172
1YE201 - YE206
1YE301 - YE305
1YE321 - YE326
1YE371 - YE383
1YF001 - YF011
1YF021 - YF049
1YF051 - YF080
1YF086 - YF087
1YF106 - YF107
1YF111 - YF114
1YF116 - YF119
1YF121 - YF132
1YF176 - YF178
1YF191 - YF192
1YF201 - YF276
1YF401 - YF402
1YF431 - YF432
1YF436 - YF437
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GroupVariable Number
1YF441 - YF442
1YF451 - YF460
1YF501 - YF599
1YF601 - YF682
1YF701 - YF707
1YF801 - YF805
1YF831 - YF832
1YF836 - YF838
1YF871 - YF872
1YF901 - YF905
1YF921 - YF928
1YF951 - YF954
1YG001 - YG044
1YG061 - YG064
1YG066 - YG089
1YG091 - YG099
1YG101 - YG104
1YG111 - YG114
1YG116 - YG143
1YG146
1YG201 - YG205
1YG211 - YG214
1YG221 - YG224
1YG251 - YG252
2YG501 - YG513
2YG515
2YG601 - YG602
2YG701
2YG711
2YG721 - YG722
1YH001 - YH012
1YH031 - YH055
1YH071 - YH080
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GroupVariable Number
1YH101 - YH132
1YH201 - YH202
1YH206 - YH207
1YH301 - YH306
1YH321 - YH322
1YH501 - YH542
1YH551 - YH594
1YH601 - YH606
1YH611 - YH620
1YH631 - YH632
1YH636 - YH637
1YH641
1YH681 - YH683
1YH701 - YH732
1YH735 - YH742
1YH751 - YH754
1YH801 - YH843
1YH851 - YH858
1YH901 - YH908
1YH911 - YH915
1YH951 - YH952
1YJ001 - YJ013
1YJ021
1YJ471 - YJ480
1YJ501 - YJ517
1YJ531 - YJ579
1YJ591 - YJ599
1YJ631 - YJ632
1YJ671 - YJ694
1YJ801 - YJ867
1YJ871 - YJ880
1YJ901 - YJ904
1YJ908 - YJ929
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GroupVariable Number
1YJ931 - YJ937
1YJ941 - YJ956
1YJ961
1YJ976 - YJ977
1YK001 - YK007
1YK101 - YK104
1YK111 - YK112
1YK121 - YK122
1YK131 - YK133
1YK136 - YK139
1YK141 - YK142
1YK146 - YK148
1YK151 - YK154
1YK161 - YK167
1YK171
1YK176 - YK177
1YK186
1YK191
1YK196
1YK201 - YK202
1YK301 - YK314
1YK321 - YK340
1YK361 - YK378
1YK401 - YK406
1YK426 - YK427
1YK431 - YK450
1YK456 - YK467
1YK471 - YK473
1YK476
1YK480 - YK487
1YK491 - YK493
1YK495 - YK499
1YK511 - YK516
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GroupVariable Number
1YK521 - YK530
1YK551 - YK571
1YK576 - YK577
1YK580 - YK585
1YK601 - YK602
1YK606 - YK607
1YK611 - YK616
1YK621 - YK634
1YK641 - YK644
1YK651 - YK665
1YK671 - YK672
1YK676 - YK677
1YK681 - YK686
1YK691
1YK695 - YK699
1YK701 - YK713
1YK716 - YK719
1YK721 - YK741
1YK751 - YK770
1YK776 - YK778
1YK781 - YK785
1YK791 - YK792
1YK796 - YK797
1YK801 - YK899
1YK901 - YK912
1YK918 - YK919
1YK921 - YK929
1YK941 - YK999
1YL001 - YL005
1YL011 - YL016
1YL021 - YL024
1YL051 - YL052
1YL056 - YL057
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GroupVariable Number
1YL061
1YL066 - YL069
1YL076 - YL077
1YL101 - YL137
1YL201 - YL237
1YL241 - YL242
1YL271 - YL272
1YL281 - YL284
1YL301 - YL303
1YL311 - YL314
1YL316 - YL321
1YL351 - YL353
1YL371 - YL374
1YL401
1YL421 - YL429
1YL431 - YL444
1YL461 - YL478
1YL501 - YL509
1YL531 - YL534
1YL541 - YL551
1YL561 - YL579
1YL591 - YL598
1YL601 - YL606
1YL611 - YL612
1YL616 - YL617
1YL621
1YL626
1YL631 - YL634
1YL636 - YL637
1YL661 - YL664
1YL676 - YL691
1YL696 - YL697
1YL701 - YL707
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GroupVariable Number
1YL731
1YL751 - YL752
1YL756 - YL757
1YL761 - YL780
1YL796 - YL797
1YL801 - YL815
1YL901 - YL910
1YL921 - YL940
1YL951 - 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
1YN061
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GroupVariable Number
1YN071 - YN082
1YN091 - YN092
1YN101 - YN112
1YN121
1YN126
1YN201 - YN202
1YN211 - YN219
1YN231 - YN236
1YN261
1YN501
1YN531 - YN534
1YN551 - YN564
1YN581 - YN585
1YN591 - YN592
1YN601 - YN606
1YN651 - YN653
1YN701 - YN702
1YN741 - YN746
1YN756
1YQ001 - YQ003
1YQ011 - YQ021
1YQ026 - YQ029
1YQ036 - YQ045
1YQ201 - YQ207
1YQ231
1YQ241 - YQ251
1YQ281 - YQ284
1YQ291 - YQ296
1YQ301 - YQ302
1YQ321 - YQ324
1YQ331 - YQ334
1YQ346 - YQ347
1YQ351
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GroupVariable Number
1YQ354 - YQ355
1YQ362
1YQ371
1YQ401 - YQ403
1YQ451 - YQ454
1YQ456
1YQ461
1YQ471
1YQ501 - YQ520
1YR001 - YR043
1YR045
1YR051 - YR087
1YR090 - YR098
1YR101 - YR105
1YR111 - YR124
1YR126 - YR144
1YR166 - YR182
1YR186 - YR198
1YR201 - YR205
1YR231 - YR294
1YR296 - YR297
1YR301 - YR334
1YR338 - YR341
1YR361 - YR366
1YR371 - YR373
1YR376
1YR381 - YR382
1YR386 - YR388
1YR391
1YR396 - YR398
1YR401 - YR405
1YR411 - YR413
1YR416 - YR418
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GroupVariable Number
1YR421 - YR424
1YR426 - YR455
1YR457 - YR499
1YR501 - YR506
1YR511 - YR520
1YR526 - YR544
1YR546 - YR551
1YR556 - YR562
1YR571 - YR582
1YR591 - YR592
1YR601 - YR605
1YR616 - YR658
1YR661 - YR663
1YR671 - YR672
1YR676 - YR678
1YR681 - YR682
1YR701 - YR769
1YR771 - YR799
1YR801 - YR816
1YR831 - YR838
1YR841 - YR898
1YR901 - YR903
1YR931 - YR934
1YR938 - YR944
1YR951 - YR979
1YR981 - YR996
1YS001 - YS002
1YS006 - YS009
1YS031 - YS032
1YS051 - YS073
1YS101 - YS120
1YS126 - YS138
1YS149 - YS160
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GroupVariable Number
1YS166 - YS194
1YS196 - YS197
1YS201 - YS209
1YS221 - YS225
1YS231 - YS236
1YS271 - YS287
1YS301 - YS334
1YS343 - YS347
1YS351 - YS365
1YS369
1YS371 - YS374
1YS377
1YS381 - YS383
1YS401
1YS451
1YS456 - YS457
1YS462
1YS467
1YS501 - YS502
1YS506
1YS511 - YS513
1YS515 - YS516
1YS531
1YS538
1YS541
1YS551 - YS553
1YS556
1YS561 - YS578
1YS581 - YS595
1YS601 - YS690
1YS701 - YS708
1YS721 - YS759
1YS761 - YS762
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GroupVariable Number
1YS771 - YS780
1YS806 - YS810
1YS816 - YS818
1YS823 - YS825
1YS851 - YS860
1YS876
1YS881 - YS883
1YS901 - YS909
1YS911 - YS928
1YS938 - YS939
1YS951
1YS956 - YS957
1YS961 - YS965
1YS981 - YS983
1YS991 - YS998
1YT001 - YT004
1YT006
1YT026 - YT027
1YT031 - YT032
1YT036 - YT038
1YT061 - YT068
1YT101 - YT112
1YT115 - YT117
1YT126 - YT130
1YT136 - YT138
1YT176 - YT181
1YT191
1YT196 - YT199
1YT201
1YT206 - YT207
1YT211 - YT213
1YT251 - YT271
1YT278 - YT287
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GroupVariable Number
1YT301 - YT304
1YT306 - YT307
1YT311 - YT312
1YT321 - YT328
1YT340 - YT342
1YT381
1YT391
1YT395
1YT401 - YT403
1YT411 - YT415
1YT427
1YT461 - YT471
1YT475
1YT491 - YT492
1YT501 - YT504
1YT516 - YT521
1YT551
1YT556
1YT558 - YT561
1YT563
1YT571 - YT572
1YT601 - YT606
1YT701 - YT702
1YT705 - YT706
1YT761 - YT780
1YT791
1YT796
1YT801 - YT804
1YT811 - YT813
1YT831
1YT852
1YT856 - YT862
1YT891 - YT894
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GroupVariable Number
1YT901 - YT908
1YT915 - YT925
1YU001 - YU046
1YU053 - YU054
1YU201 - YU212
1YV001
1YV045
1YV081
1YV083
1YV101 - YV106
1YV115 - YV121
1YV351 - YV353
1YV356 - YV358
1YV381
1YV383
1YV501
1YV521
1YV571
1YV575
1YV651 - YV654
1YV695
1YV741 - YV743
1YV781
1YV801 - YV802
1YW011 - YW040
1YW261
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
Widespread Fatigue Damage (WFD) analysis of the 737NG, as required by 14 CFR 26.21(b), has
resulted in the conclusion that the existing 737-600/700/800/900 MPD Section 9, Airworthiness Limitation
Instruction (ALI) inspection program is not sufficient to preclude the occurrence of WFD in the S-14L
and S-14R lap splice, lower fastener rows between STA 360-540 and STA 727-887 as the airplane
ages. These lap splices have multiple adjacent identical details which have the potential for Multi-Site
Damage (MSD) 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). Boeing has not received any in-service fleet reports of cracks in these
lap splices. Accomplishment of the inspections described in this service bulletin will enable detection
and repair of cracks if they should occur, at these lap splices. 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.
This Service Bulletin gives a more frequent inspection for the S-14 lap splices to prevent WFD out to
the LOV.
The fuselage skin S-14L and S-14R lap splice lower fastener row between STA 360 to STA 540 and
STA 727 to STA 887 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 737NG-SRP-53-00471 is related to this service bulletin.
D. Description
Group 1:
1. Do PART 1: Low Frequency Eddy Current (LFEC) Inspection for any crack on the S-14L and
S-14R lap splice, lower fastener row, between STA 360 to STA 540 and STA 727 to STA 887. If
no crack is found, repeat PART 1: LFEC INSPECTION at the repeat interval in Paragraph 1.E.,
Compliance. If any crack is found, contact The Boeing Company for repair instructions and do the
repair.
Group 2:
1. Do PART 1: Low Frequency Eddy Current (LFEC) Inspection for any crack on the S-14L lap splice,
lower fastener row, between STA 500 to STA 540 and STA 727 to STA 887 and S-14R lap splice,
lower fastener row, between STA 360 to STA 540 and STA 727 to STA 887. If no crack is found,
repeat PART 1: LFEC INSPECTION at the repeat interval in Paragraph 1.E., Compliance. If any
crack is found, contact The Boeing Company for repair instructions and do the repair.
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, 737-800,
737-900, 737-900ER
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Group 2:
Affected Maintenance Zones
ZoneModel
231, 232, 241, 242737-700C
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.
For airplanes which have not incorporated Boeing Business Jet Lower Cabin Altitude (LCA) 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)
53-30-04-6, 53-30-04-6a, 53-60-04-6, and 53-60-04-6a of Subsection B, Airworthiness
Limitations-Structural Inspections of 737-600/700/800/900 MPD Section 9 C626A001-CMR Table 9-2,
which is mandated by AD 2013-19-23.
For airplanes which have incorporated Boeing Business Jet Lower Cabin Altitude (LCA) 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)
53-30-04-6 and 53-60-04-6 of Subsection B, Airworthiness Limitations-Structural Inspections of
737-600/700/800/900 MPD Section 9 626A001-CMR Table 9-3, which is mandated by AD 2013-19-23.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX
A and APPENDIX B.
Table 1: Inspection For Any Crack at S-14 Lap Splice
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before 54,000 To-
tal Flight Cycles.
Do PART 1: LFEC IN-
SPECTION for any crack.
Airplanes that have not ac-
complished Boeing Service
Bulletin 737-21-1149.
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Table 1: Inspection For Any Crack at S-14 Lap Splice
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further
flight.
ACTION 1:
Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 1:
ANY CRACK FOUND
12,000 Flight Cy-
cles.
-ACTION 2:
Repeat PART 1: LFEC
INSPECTION for any
crack at the unrepaired
areas.
12,000 Flight Cy-
cles.
-Repeat PART 1: LFEC
INSPECTION for any
crack.
CONDITION 2:
NO CRACK FOUND
Table 2: Inspection For Any Crack at S-14 Lap Splice
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before 41,000 To-
tal Flight Cycles.
Do PART 1: LFEC IN-
SPECTION for any crack.
Airplanes that have accom-
plished Boeing Service
Bulletin 737-21-1149.
-Before further
flight.
ACTION 1:
Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 1:
ANY CRACK FOUND
8,800 Flight Cy-
cles.
-ACTION 2:
Repeat PART 1: LFEC
INSPECTION for any
crack at the unrepaired
areas.
8,800 Flight Cy-
cles.
-Repeat PART 1: LFEC
INSPECTION for any
crack.
CONDITION 3:
NO CRACK FOUND
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.
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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.
In addition, for airplanes which have incorporated Boeing Business Jet Lower Cabin Altitude (LCA)
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 Manager of the FAA Seattle Aircraft
Certification Office (SACO) approves the accomplishment of the inspections defined in this Service
Bulletin (SB) along with the corresponding compliance times specified in Paragraph 1.E., Compliance,
of this SB, Original Issue as an Alternative Method of Compliance (AMOC) to the inspections, defined
in D626A001-DTR for PSEs 53-30-04-6 and 53-60-04-6, and 737-600/700/800/900 MPD Section 9,
D626A001-CMR Table 9-3, required by paragraph (g) and (h) of Airworthiness Directive (AD) AD
2013-19-23. This AMOC is only applicable after accomplishment of the initial inspections specified in
Paragraph 1.E., Compliance of this service bulletin. All provisions of AD 2013-19-23 that are not
specifically referenced in this paragraph remain fully applicable and must be complied with accordingly.
In addition, for airplanes which have not incorporated Boeing Business Jet Lower Cabin Altitude (LCA)
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 Manager of the FAA Seattle Aircraft
Certification Office (SACO) approves the accomplishment of the inspections defined in this Service
Bulletin (SB) along with the corresponding compliance times specified in Paragraph 1.E., Compliance,
of this SB, Original Issue as an Alternative Method of Compliance (AMOC) to the inspections, defined
in D626A001-DTR for PSEs 53-30-04-6, 53-30-04-6a, 53-60-04-6, and 53-60-04-6a, and
737-600/700/800/900 MPD Section 9 D626A001-CMR Table 9-2, required by paragraph (g) and (h)
of Airworthiness Directive (AD) AD 2013-19-23. This AMOC is only applicable after accomplishment
of the initial inspections specified in Paragraph 1.E., Compliance of this service bulletin. All provisions
of AD 2013-19-23 that are not specifically referenced in this paragraph remain fully applicable and
must be complied with accordingly.
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.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
42.0084.002Figure 1
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Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
42.0084.00TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
32.5065.002Figure 2
32.5065.00TOTAL FOR EACH AIRPLANE
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 Letter 737-SL-51-042
c. Boeing Service Related Problem (SRP) 737NG-SRP-53-00471
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2013-19-23
e. Service Bulletin Index D6-19567
f. Standard Overhaul Practices Manual (SOPM) 20-50-01
g. 737 Non-Destructive Testing (NDT) Manual Part 6, 53-30-50
h. 737-600/700/800/900 Maintenance Planning Data (MPD) Section 9
i. 737NG Fleet Team Digest (FTD) 53-14001
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Skin Installation - STA 259.5 to STA 540, S-24L to S-4R142A3000
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TitleDrawing Number
Skin Installation - S-10 to S-14, STA 360 to 540143A3150
Skin Installation - STA 360 to 540, S-14L to S-24L143A3210
Skin Installation - STA 360 to 540, S-14R to S-24R143A3250
Skin Installation, S-10 to S-14, Station 727-888146A3150
Skin Installation, S-14L to S-23L, Station 727-888146A3200
Skin Installation, S-14R to S-23R, Station 727-888146A3250
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
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.
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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2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection procedures 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 the change in this service bulletin. But maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
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.
— Values for airframe maintenance tasks are included in Chapter 20 of 737
Aircraft Maintenance Manual (AMM).
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
6. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
7. 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.
8. 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.
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9. Refer to APPENDIX A and APPENDIX B for logic diagram. 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.
10. 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.
11. 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.
12. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
13. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
14. The CONDITIONS, ACTIONS and OPTIONS shown apply to each S-14 Lap Splice
independently.
15. 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. Airplanes that have not accomplished Boeing Service Bulletin 737-21-1149, Boeing Business Jet
Lower Cabin Altitude (LCA) Supplemental Type Certificate ST01697SE (6,500 feet maximum
cabin altitude in lieu of 8,000 feet).
a. Do PART 1: LFEC INSPECTION for any crack.
(1) CONDITION 1: ANY CRACK FOUND.
(a) ACTION 1: Contact The Boeing Company for repair instructions and do the repair.
(b) ACTION 2: Repeat PART 1: LFEC INSPECTION for any crack at the unrepaired
areas at the repeat interval in Paragraph 1.E., Compliance.
(2) CONDITION 2: NO CRACK FOUND.
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(a) Repeat PART 1: LFEC INSPECTION for any crack at the repeat interval in Paragraph
1.E., Compliance.
2. Airplanes that have accomplished Boeing Service Bulletin 737-21-1149, Boeing Business Jet
Lower Cabin Altitude (LCA) Supplemental Type Certificate ST01697SE (6,500 feet maximum
cabin altitude in lieu of 8,000 feet).
a. Do PART 1: LFEC INSPECTION for any crack.
(1) CONDITION 1: ANY CRACK FOUND.
(a) ACTION 1:Contact The Boeing Company for repair instructions and do the repair.
(b) ACTION 2: Repeat PART 1: LFEC INSPECTION for any crack at the unrepaired
areas at the repeat interval in Paragraph 1.E., Compliance.
(2) CONDITION 3: NO CRACK FOUND.
(a) Repeat PART 1: LFEC INSPECTION for any crack at the repeat interval in Paragraph
1.E., Compliance.
3. Put the airplane back to a serviceable condition.
PART 1: LFEC INSPECTION
1. RC - Do Low Frequency Eddy Current (LFEC) inspection for any crack at S-14L and S-14R lap
splice for any crack at lower fastener row in accordance with 737 NDT Manual Part 6, 53-30-50
and the table below:
FigureGroup
FIGURE 11
FIGURE 22
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BOEING SERVICE BULLETIN 737-53A1352
ALERT  ALERT
This Figure applies only to: Group 1.
STA STA  STA  887
727
540
STA
360
STA  STA
360  540
— BL O
-S-14R
6000  0000 0
— S-4R
- S-4L
00000000
-S-14L
• S-14 LAP SPLICE
INSPECTION AREA
S-14 LAP SPLICE LOCATIONS
2387075
FIGURE 1: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW
(SHEET 1 OF 3)
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### Page 41 (OCR)

BOEING SERVICE BULLETIN 737-53A1352
ALERT  ALERT
STA
727  STA
887
BL O
S-14R -  000  0000c
S-4R -
S-4L
00000  00000
S-14L
BL O
ANN S-14 LAP SPLICE
INSPECTION AREA
S-14 LAP SPLICE LOCATIONS
2387114
FIGURE 1: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW
(SHEET 2 OF 3)
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### Page 42

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are by location identification provided.
More
Data
LocationNameTaskStep
(a)Between STA 360 to STA 540S-14L Lap
Splice
Inspect1
(a)Between STA 360 to STA 540S-14R Lap
Splice
Inspect
(a)Between STA 727 to STA 887S-14L Lap
Splice
Inspect2
(a)Between STA 727 to STA 887S-14R Lap
Splice
Inspect
(a) In accordance with 737 NDT Manual Part 6, 53-30-50.
FIGURE 1: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 737-53A1352
ALERT  ALERT
This Figure applies only to: Group 2.
STA STA  STA  887
727
540
STA
360  STA
540
STA
360
00
- S-14R
2000000000
-S-4R
-S-4L
- S-14L
— BL O
MAIN DECK
CARGO DOOR
STA
\ S-14 LAP SPLICE  500
INSPECTION AREA
S-14 LAP SPLICE LOCATIONS
2387145
FIGURE 2: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW
(SHEET 1 OF 3)
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### Page 44 (OCR)

BOEING SERVICE BULLETIN 737-53A1352
ALERT  ALERT
STA  727  STA  887
BLO —  ___  - --
S-14R -  0000000000000
S-4R
S-4L
00000
S-14L
BL 0
• S-14 LAP SPLICE
INSPECTION AREA
S-14 LAP SPLICE LOCATIONS
2387146
FIGURE 2: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW
(SHEET 2 OF 3)
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### Page 45

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are by location identification provided.
More
Data
LocationNameTaskStep
(a)Between STA 500 and STA 540S-14L Lap
Splice
Inspect1
(a)Between STA 360 and STA 540S-14R Lap
Splice
Inspect
(a)Between STA 727 and STA 887S-14L Lap
Splice
Inspect2
(a)Between STA 727 and STA 887S-14R Lap
Splice
Inspect
(a) In accordance with 737 NDT Manual Part 6, 53-30-50.
FIGURE 2: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW
(SHEET 3 OF 3)
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### Page 46

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.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
LFEC INSPECTION for any crack.PART 1:
ANY CRACK FOUNDCONDITION 1:
Contact The Boeing Company for repair instructions and do the repair.ACTION 1:
Repeat PART 1: LFEC INSPECTION for any crack at the unrepaired areas.ACTION 2:
NO CRACK FOUNDCONDITION 2:
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: INSPECTION FOR ANY
CRACK AT S-14 LAP SPLICE
(SHEET 1 OF 2)
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BOEING SERVICE BULLETIN 737-53A1352
ALERT  ALERT
FIGHT SCLES.  WITHIN 54,000
DO PART 1
CONDITION 1  CONDITION 2
BEFORE FURTHER  12,000 FLIGHT
FLIGHT  CYCLES
ACTION 1:
CONTACT BOEING  REPEAT PART 1
12,000 FLIGHT
CYCLES
ACTION 2:
REPEAT PART 1
2387791
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: INSPECTION FOR ANY
CRACK AT S-14 LAP SPLICE
(SHEET 2 OF 2)
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### Page 48

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.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
LFEC INSPECTION for any crack.PART 1:
ANY CRACK FOUNDCONDITION 1:
Contact The Boeing Company for repair instructions and do the repair.ACTION 1:
Repeat PART 1: LFEC INSPECTION for any crack at the unrepaired areas.ACTION 2:
NO CRACK FOUNDCONDITION 3:
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 2: INSPECTION FOR ANY
CRACK AT S-14 LAP SPLICE
(SHEET 1 OF 2)
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BOEING SERVICE BULLETIN 737-53A1352
ALERT  ALERT
FLIGHT CYCLES  WITHIN 41,000
DO PART 1
CONDITION 1  CONDITION 3
BEFORE FURTHER  8,800 FLIGHT
FLIGHT  CYCLES
ACTION 1:
CONTACT BOEING  REPEAT PART 1
8,800 FLIGHT
CYCLES
ACTION 2:
REPEAT PART 1
2426192
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 2: INSPECTION FOR ANY
CRACK AT S-14 LAP SPLICE
(SHEET 2 OF 2)
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