# Boeing Alert Service Bulletin 737-53A1350: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2016-8186; AD 2017-02-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-53A1350](https://openairdocs.org/service-documents/boeing/737-53a1350.md)
- Title as filed: Boeing Service Bulletin 737-53A1350, dated May 6, 2016.
- Pages: 123
- PDF: https://openairdocs.org/files/sha256/31/c6/31c6a07e8a5954ab50b6e3d8b6507846184839fa943c5fe6f1c3206355c0326a
- Page: https://openairdocs.org/service-documents/boeing/737-53a1350/file/31c6a07e8a59

## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1350
Original Issue: May 06, 2016
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Upper and Lower Corners of Aft Doorways Inspection and Repair
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2016 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
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connection with this document unless provided in writing by Boeing.
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### Page 3

Table of Contents
S u m m a r y  ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A . E f f e c t i v i t y  ................................................ 9
1. Airplanes ............................................. 9
2 . S p a r e s  A f f e c t e d  ........................................ 2 2
B. Concurrent Requirements ...................................... 2 2
C. Reason ................................................ 2 3
D. Description .............................................. 2 3
E. Compliance .............................................. 2 5
F . A p p r o v a l  ............................................... 2 9
G. Manpower .............................................. 2 9
H. Weight and Balance Changes .................................... 3 2
I. Electrical Load Data ......................................... 3 2
J . R e f e r e n c e s  .............................................. 3 2
1. Existing Data: ......................................... 3 2
2. Data Supplied with this Service Bulletin: ........................... 3 3
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 3
K. Publications Affected ........................................ 3 3
L. Interchangeability and Intermixability of Parts ........................... 3 3
M. Software Accomplishment Summary ................................ 3 4
2. MATERIAL INFORMATION ........................................ 3 5
A. Material - Price and Availability ................................... 3 5
B. Industry Support Information .................................... 3 5
C. Parts Necessary for Each Airplane ................................. 3 5
1 . K i t s / P a r t s  ............................................ 3 5
2. Parts and Materials Supplied by the Operator ........................ 3 5
3. Parts Modified and Reidentified ................................ 3 5
4. Parts Removed and Not Replaced .............................. 3 5
D. Parts Necessary to Change Spares ................................. 3 5
E. Special Tooling - Price and Availability ............................... 3 5
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 7
A. GENERAL INFORMATION ..................................... 3 7
B. WORK INSTRUCTIONS ....................................... 3 9
FIGURE 1: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND
DETAILED INSPECTIONS [Group 5] ............................. 4 8
FIGURE 2: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND
DETAILED INSPECTIONS [Group 3] ............................. 5 4
FIGURE 3: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND
DETAILED INSPECTIONS [Group 4] ............................. 6 0
FIGURE 4: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND
DETAILED INSPECTIONS [Group 6] ............................. 6 6
FIGURE 5: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND
DETAILED INSPECTIONS [Group 7] ............................. 7 2
FIGURE 6: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND
DETAILED INSPECTIONS [Group 8] ............................. 7 8
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FIGURE 7: AFT GALLEY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND
DETAILED INSPECTIONS [Group 2-4] ............................ 8 4
FIGURE 8: AFT GALLEY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND
DETAILED INSPECTIONS [Group 5-6, 8] .......................... 9 0
FIGURE 9: AFT GALLEY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND
DETAILED INSPECTIONS [Group 7] ............................. 9 6
F I G U R E  1 0 : A F T  E N T R Y  D O O R W A Y  R A I N  G U T T E R  -  R E M O V A L  [ G r o u p  4 - 5 ,  7 - 8 ]  .......... 1 0 2
FIGURE 11: AFT ENTRY DOORWAY RAIN GUTTER - INSTALLATION [Group 4-5, 7-8] ....... 1 0 4
FIGURE 12: AFT ENTRY DOORWAY RAIN GUTTER - REMOVAL [Group 3, 6] ............ 1 0 6
FIGURE 13: AFT ENTRY DOORWAY RAIN GUTTER - INSTALLATION [Group 3, 6] ......... 1 0 8
FIGURE 14: AFT GALLEY DOORWAY RAIN GUTTER - REMOVAL [Group 2-8] ........... 1 1 0
FIGURE 15: AFT GALLEY DOORWAY RAIN GUTTER - INSTALLATION [Group 2-8] ......... 1 1 2
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: AFT ENTRY AND AFT
GALLEY DOORWAY CORNERS - INSPECTION AND REPAIR [Group 3-8] ....... 1 1 4
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 2: AFT GALLEY DOORWAY
CORNERS - INSPECTION AND REPAIR. [Group 2] .................... 1 1 7
APPENDIX C: SCUFF PLATE - REMOVAL  [Group 2-4] .......................... 1 1 9
APPENDIX D: SCUFF PLATE - INSTALLATION [Group 2-4] ........................ 1 2 1
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### Page 5

Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-53A1350Original Issue: May 06, 2016
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Upper and Lower Corners of Aft Doorways Inspection and Repair
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
Accomplishment of the work in this service bulletin will make sure that any crack at the corners of the aft entry
and aft galley doorway is detected and repaired. If the work given in this service bulletin is not accomplished, a
crack in the aft entry or aft galley doorway may go undetected and grow in length. An undetected crack could
result in a possible decompression and loss of structural integrity of the airplane.
The cracks are caused by fatigue from cyclic pressurization of the fuselage combined with increased stress
concentration due to the proximity of fastener holes to the corners of the doorways. The cracks typically originate
at the fastener holes and grow towards the corners of the doorways.
There have been more than 240 reports of skin cracking at the corners of aft entry and aft galley doorways.
Findings have been primarily on the 737-300 but have been reported on the 737-200 and to a lesser extent on
the 737-400 and 737-500. Cracks are most common at the lower forward corners and the upper aft corners of
the doorways. Where crack lengths have been reported, these lengths range from 0.25 to 4.50 inches. At the
time of crack detection the airplanes had accumulated between 26,896 and 73,655 total flight cycles.
Boeing service bulletin 737-53-1149 provides inspection, preventive modification and repair instructions for the
upper forward and aft corners of the aft entry and aft galley doorways for all 737-100 and -200 airplanes. Multiple
cracks have been reported common to the skin and bear strap at the upper corners of aft doorways on 737
airplanes that are beyond the effectivity of service bulletin 737-53-1149. More reliable Low Frequency Eddy
Current (LFEC) inspections have been added to this service bulletin for cracks at the upper corners of the aft
doorways for all airplanes within the effectivity of service bulletin 737-53-1149. After accomplishing the inspections
in accordance with this service bulletin, operators do not need to accomplish service bulletin 737-53-1149
inspections for the upper corners of the aft doorways.
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Boeing service bulletin 737-53-1074, Revision 3, provides inspection, preventive modification and repair
instructions for the lower forward and aft corners of the aft entry and aft galley doorways for 737-100 and -200
airplanes, line numbers 1 to 1014. Multiple cracks have been reported common to the skin and bear strap at
the lower corners of the aft doorways on 737 airplane line numbers 1015 to 3132 that are beyond the effectivity
of service bulletin 737-53-1074, Revision 3. More reliable LFEC inspections have been added to this service
bulletin for cracks at the lower corners of the aft doorways for all airplanes within the effectivity of service bulletin
737-53-1074, Revision 3. After accomplishing the inspections in accordance with this service bulletin, operators
do not need to accomplish service bulletin 737-53-1074, Revision 3 inspections for the lower corners of the aft
doorways.
Boeing Service Related Problems (SRP) 737-SRP-53-0389 and 737-SRP-53-0393 are related to this service
bulletin.
Boeing Fleet Team Digest (FTD) 737 FTD 53-11004 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
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications 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:
The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and recommends immediate
and permanent removal from service of any airplanes upon reaching the LOV, whether or not it is operated
under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance instructions for airplanes
that have accumulated flight cycles beyond the LOV. Airplanes in Group 1 (line number 1-291) have accumulated
flight cycles beyond the LOV of the maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of
an airplane beyond its LOV.
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Group 2:
Remove the scuff plate at the lower corners of the aft galley doorway. If the rain gutter interferes with the Low
Frequency Eddy Current (LFEC) inspection, remove it from above the aft galley doorway. At the upper and lower
corners of the aft galley doorway, do an external LFEC inspection of the skin assembly and bear strap for any
crack around fasteners and do an external detailed inspection of the skin assembly for any crack. If any crack
is found in the skin assembly or bear strap, install a repair in accordance with Structural Repair Manual (SRM).
If no crack is found, do the repeat inspections at the intervals given in Paragraph 1.E., Compliance.
Group 3-8:
Remove the scuff plates at the lower corners of the aft entry doorway and aft galley doorway. If the rain gutters
interfere with the Low Frequency Eddy Current Inspection (LFEC), remove them from above the aft entry doorway
and aft galley doorway. At the upper and lower corners of the aft entry doorway and aft galley doorway, do an
external LFEC inspection of the skin assembly and the bear strap for any crack around fasteners and do an
external detailed inspection of the skin assembly for any crack. If any crack is found in the skin assembly or
bear strap, install a repair in accordance with Structural Repair Manual (SRM). If no crack is found, do the repeat
inspections at the intervals given in Paragraph 1.E., Compliance.
EFFECTIVITY
All 737-100/-200/-200C/-300/-400/-500 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected
airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive (AD) related to this
service bulletin. The AD will make the compliance tasks and times given in this service bulletin mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspections and/or repair procedures given in this service
bulletin.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
--Group 1
8.008.00Group 2
8.0016.00Group 3-8
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
None.
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### Page 8 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
DO AN EXTERNAL LFEC INSPECTION OF THE
SKIN ASSEMBLY AND THE BEAR STRAP FOR
ANY CRACK AROUND FASTENERS. DO A
DETAILED INSPECTION OF THE SKIN ASSEMBLY
FOR ANY CRACK. IF ANY CRACK IS FOUND, DO
THE REPAIR. IF NO CRACK IS FOUND, DO
REPEAT INSPECTIONS.
STA  STA  STA  STA
1016  992.8  951  908
- S-6R
- S-8R
-S-10R
BEAR STRAP
- S-14R
— S-17R
- S-20R
AFT GALLEY DOORWAY SHOWN  FWD
AFT ENTRY DOORWAY SIMILAR
INSPECTION AREA  2399738
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### Page 9

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1350
Original Issue: May 06, 2016
ATA System: 5331
SUBJECT: FUSELAGE - Skin - Upper and Lower Corners of Aft Doorways Inspection and Repair
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
This service bulletin is applicable to all 737-100, -200, -200C, -300, -400 and -500 airplanes, in 8
Groups. The Variable Numbers and Group Information for the applicable airplanes are given below.
Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
737-100/-200/-200C airplanes, line numbers 1-291.-1
737-200 airplanes without aft entry doors.-2
737-200/-200C airplanes with aft entry doors with airstairs.-3
737-200/-200C airplanes with aft entry doors that do not have airstairs.-4
737-300/-400/-500 airplanes, line numbers 1001-1072 and 1074-2552.-5
737-300 airplane, line number 1073.-6
737-300/-400/-500 airplanes, line numbers 2553-2565.-7
737-300/-400/-500 airplanes, line numbers 2566-3132.-8
Airplane Models:
737-100, 737-200, 737-200C, 737-300, 737-400, 737-500
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GroupVariable Number
1PA001 - PA022
1PA099
1PA231 - PA232
1PC001 - PC005
1PG001 - PG075
1PG199
1PG201 - PG230
1PG251 - PG255
1PG271 - PG279
1PG301 - PG314
1PG331 - PG332
1PG351 - PG356
1PG375
1PG401 - PG403
1PG431 - PG442
1PG471 - PG475
1PG501 - PG505
1PG571 - PG583
4PG584 - PG586
1PG621 - PG630
1PG651 - PG652
1PG701 - PG705
4PH001
4PH011 - PH013
4PH021 - PH024
1PH701 - PH715
1PH731 - PH732
1PH741 - PH742
4PH743
1PJ001 - PJ002
4PJ003 - PJ009
1PJ031 - PJ032
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GroupVariable Number
1PJ071 - PJ072
1PJ101 - PJ104
4PJ105 - PJ119
2PJ201 - PJ219
5PJ301 - PJ302
5PJ551
7PJ552
8PJ553 - PJ561
8PJ601 - PJ615
8PJ811
8PJ816 - PJ817
4PK026 - PK029
4PK041 - PK053
4PK061 - PK067
3PK068 - PK070
4PK081 - PK082
4PK091 - PK099
4PK101 - PK103
4PK111 - PK120
4PK141 - PK146
4PK201 - PK204
4PK211 - PK223
4PK231 - PK241
4PK251 - PK258
4PK271 - PK274
4PK281 - PK289
4PK291
4PK301 - PK318
4PK341
4PK351 - PK361
4PK391
4PK431 - PK433
4PK451 - PK452
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GroupVariable Number
4PK461 - PK469
4PK495
4PK501 - PK504
4PK511 - PK515
3PK519
4PK521 - PK528
4PK541 - PK565
4PK581
4PK591 - PK599
4PK601 - PK617
4PK621 - PK637
4PK641 - PK642
4PK661 - PK666
4PK671 - PK681
4PK691 - PK697
4PK711 - PK716
4PK731 - PK765
4PK771 - PK779
4PK801 - PK804
4PK819 - PK827
4PK830
4PK861 - PK863
4PK871 - PK874
4PK881 - PK884
4PK901 - PK938
4PK971 - PK974
4PL001 - PL028
4PL061
4PL081
4PL101 - PL113
4PL151
4PL171 - PL172
4PL201 - PL203
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GroupVariable Number
4PL221
4PL401 - PL417
4PL421
4PL441
4PL451 - PL456
4PL471
4PL491
4PL501 - PL506
4PL551 - PL562
4PL581
4PL601 - PL603
4PL611
4PL621 - PL626
4PL631 - PL632
1PL711 - PL712
1PL716
4PL717 - PL747
4PL756
3PL758
4PL761 - PL770
4PL781 - PL788
4PL793
1PL801 - PL803
4PM001 - PM006
4PM016 - PM017
4PM021 - PM023
4PM051 - PM066
4PM101 - PM119
4PM141 - PM142
4PM171
4PM181
4PM251 - PM255
4PM281 - PM283
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GroupVariable Number
5PM381 - PM399
5PM401 - PM417
5PM541 - PM542
7PM543 - PM547
8PM548 - PM550
5PM551 - PM564
4PN001 - PN002
4PN021 - PN043
4PN081 - PN086
4PN101 - PN117
4PN131 - PN163
4PN401 - PN420
4PN431 - PN433
4PN451 - PN456
4PN471 - PN474
4PN481
4PN491 - PN493
4PN501 - PN502
4PN511 - PN512
4PN521
5PP001 - PP054
5PP101 - PP169
5PP181 - PP199
5PP201 - PP205
6PP221
5PP231 - PP243
5PP281 - PP286
5PP301 - PP305
5PP351 - PP353
5PP376 - PP384
5PP391 - PP393
5PP401 - PP440
5PP471 - PP475
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GroupVariable Number
5PP501 - PP517
8PP518 - PP520
5PP521 - PP522
5PP631 - PP634
5PP651 - PP652
5PP671 - PP699
5PP701 - PP733
5PP771 - PP779
5PP801 - PP808
5PP821 - PP827
5PP831 - PP848
5PP851 - PP852
5PP861 - PP875
8PP876 - PP877
5PP891 - PP899
5PP901 - PP936
5PP946 - PP948
5PP951 - PP952
5PP961 - PP967
5PP981 - PP991
5PP993
5PQ001 - PQ016
5PQ026 - PQ041
5PQ051 - PQ092
5PQ101 - PQ199
5PQ201 - PQ202
5PQ221 - PQ237
5PQ241 - PQ243
5PQ251 - PQ267
5PQ281 - PQ296
8PQ297 - PQ299
5PQ301 - PQ307
5PQ331 - PQ332
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GroupVariable Number
5PQ341 - PQ344
8PQ345 - PQ348
5PQ361 - PQ369
8PQ370 - PQ373
8PQ391 - PQ395
5PQ401 - PQ407
7PQ408
8PQ409 - PQ410
5PQ411 - PQ413
8PQ414 - PQ418
5PQ421
8PQ431 - PQ438
8PQ447 - PQ448
8PQ451
8PQ454
5PQ471 - PQ472
7PQ473
8PQ474 - PQ475
5PQ479 - PQ481
5PQ486 - PQ487
5PQ491 - PQ493
5PQ771
8PQ772
5PQ791 - PQ793
5PQ801 - PQ805
5PQ931 - PQ932
8PQ933 - PQ935
8PQ951
8PQ971 - PQ997
8PR001 - PR017
8PR021 - PR034
8PR041 - PR045
8PR061 - PR072
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GroupVariable Number
8PR077 - PR082
8PR091 - PR092
8PR096
8PR101
8PR121 - PR122
8PR131 - PR132
8PR141 - PR143
8PR161 - PR172
8PR181
5PS601 - PS616
8PS617 - PS630
5PS631
5PS636 - PS638
5PS641 - PS644
5PS651 - PS657
5PS666 - PS669
5PS691 - PS692
5PS701 - PS703
8PS704 - PS706
5PS751 - PS762
8PS763 - PS799
8PS811
8PS836 - PS837
8PS841 - PS846
8PS851 - PS852
8PS856
8PS861 - PS863
8PS866 - PS868
8PS871 - PS874
8PS896 - PS897
8PS901 - PS941
8PS956 - PS957
8PS961 - PS963
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GroupVariable Number
8PS971 - PS978
5PT001 - PT011
8PT012 - PT015
5PT021 - PT028
8PT029 - PT031
5PT041 - PT063
7PT064
5PT101 - PT105
5PT121 - PT125
8PT126 - PT138
5PT146 - PT148
5PT161 - PT170
5PT181 - PT187
8PT188
5PT211 - PT220
5PT295
5PT301 - PT306
8PT307 - PT309
5PT331 - PT360
5PT381 - PT399
5PT401 - PT438
5PT501 - PT512
8PT513 - PT517
5PT561 - PT565
5PT581 - PT584
8PT585 - PT586
5PT611 - PT621
5PT641 - PT642
8PT643 - PT644
5PT651 - PT655
8PT656
5PT671 - PT672
8PT681 - PT685
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GroupVariable Number
5PT701 - PT703
8PT716 - PT717
8PT721 - PT725
8PT801 - PT834
8PT851 - PT854
8PT871 - PT886
8PT901 - PT930
8PT971 - PT973
8PT981 - PT985
8PT996
5PU001 - PU025
8PU301
8PU311 - PU313
5PV001 - PV055
5PV201 - PV203
8PV204 - PV209
8PV226 - PV229
5PV231 - PV237
5PV271 - PV272
5PV281 - PV283
8PV284 - PV287
8PV296
8PV301 - PV302
8PV351
8PV356 - PV357
5PW001 - PW054
5PW061 - PW068
5PW072
8PW086 - PW088
5PW091 - PW094
5PW101 - PW102
5PW106
5PW111 - PW120
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GroupVariable Number
5PW156 - PW157
5PW161 - PW167
8PW168 - PW171
5PW201 - PW244
7PW245
8PW246 - PW252
5PW261
8PW262 - PW264
5PW265 - PW268
8PW271 - PW276
5PW278
5PW281
7PW282 - PW284
8PW285 - PW292
5PW293
5PW296
5PW301 - PW327
8PW401 - PW408
8PW411 - PW418
8PW421 - PW424
8PW431 - PW435
8PW441 - PW450
5PW461 - PW467
5PW501 - PW504
5PW511 - PW520
8PW521 - PW522
8PW524 - PW525
5PW526
8PW527 - PW530
5PW531 - PW546
8PW547 - PW550
5PW556 - PW557
5PW561 - PW564
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GroupVariable Number
5PW571 - PW576
5PW591 - PW596
5PW611 - PW620
8PW621 - PW622
5PW631 - PW634
8PW635 - PW637
5PW661 - PW662
5PW681 - PW683
5PW701 - PW702
5PW711 - PW717
5PW741 - PW742
5PW761
5PW771
8PW831
8PW851 - PW856
1PX071
1PX701
1PY001 - PY008
1PY021
3PY022
1PY031
3PY036 - PY037
3PY046 - PY048
4PY051 - PY053
3PY056 - PY057
4PY101 - PY103
3PY111 - PY113
3PY131 - PY135
4PY141 - PY143
3PY151 - PY154
3PY156 - PY157
3PY161 - PY162
3PY166
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GroupVariable Number
3PY191
4PY201
4PY221 - PY222
4PY231
4PY241 - PY244
4PY270 - PY275
4PY281
4PY286
1PY301 - PY304
1PY321 - PY323
1PY341 - PY346
1PY361 - PY362
1PY381
3PY401
3PY409 - PY411
3PY421 - PY422
3PY441
3PY451
3PY461 - PY463
3PY591 - PY595
4PY611 - PY612
4PY621
4PY631
4PY651
4PY671 - PY672
4PY721
4PY741
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
Accomplishment of the work in this service bulletin will make sure that any crack at the corners of the
aft entry and aft galley doorway is detected and repaired. If the work given in this service bulletin is not
accomplished, a crack in the aft entry or aft galley doorway may go undetected and grow in length. An
undetected crack could result in a possible decompression and loss of structural integrity of the airplane.
The cracks are caused by fatigue from cyclic pressurization of the fuselage combined with increased
stress concentration due to the proximity of fastener holes to the corners of the doorways. The cracks
typically originate at the fastener holes and grow towards the corners of the doorways.
There have been more than 240 reports of skin cracking at the corners of aft entry and aft galley
doorways. Findings have been primarily on the 737-300 but have been reported on the 737-200 and
to a lesser extent on the 737-400 and 737-500. Cracks are most common at the lower forward corners
and the upper aft corners of the doorways. Where crack lengths have been reported, these lengths
range from 0.25 to 4.50 inches. At the time of crack detection the airplanes had accumulated between
26,896 and 73,655 total flight cycles.
Boeing service bulletin 737-53-1149 provides inspection, preventive modification and repair instructions
for the upper forward and aft corners of the aft entry and aft galley doorways for all 737-100 and -200
airplanes. Multiple cracks have been reported common to the skin and bear strap at the upper corners
of aft doorways on 737 airplanes that are beyond the effectivity of service bulletin 737-53-1149. More
reliable Low Frequency Eddy Current (LFEC) inspections have been added to this service bulletin for
cracks at the upper corners of the aft doorways for all airplanes within the effectivity of service bulletin
737-53-1149. After accomplishing the inspections in accordance with this service bulletin, operators
do not need to accomplish service bulletin 737-53-1149 inspections for the upper corners of the aft
doorways.
Boeing service bulletin 737-53-1074, Revision 3, provides inspection, preventive modification and repair
instructions for the lower forward and aft corners of the aft entry and aft galley doorways for 737-100
and -200 airplanes, line numbers 1 to 1014. Multiple cracks have been reported common to the skin
and bear strap at the lower corners of the aft doorways on 737 airplane line numbers 1015 to 3132
that are beyond the effectivity of service bulletin 737-53-1074, Revision 3. More reliable LFEC inspections
have been added to this service bulletin for cracks at the lower corners of the aft doorways for all
airplanes within the effectivity of service bulletin 737-53-1074, Revision 3. After accomplishing the
inspections in accordance with this service bulletin, operators do not need to accomplish service bulletin
737-53-1074, Revision 3 inspections for the lower corners of the aft doorways.
Boeing Service Related Problems (SRP) 737-SRP-53-0389 and 737-SRP-53-0393 are related to this
service bulletin.
Boeing Fleet Team Digest (FTD) 737 FTD 53-11004 is related to this service bulletin.
D. Description
Group 1:
The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and recommends
immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or
not it is operated under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance
instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1
(line number 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14
CFR 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV.
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Group 2:
Remove the scuff plate at the lower corners of the aft galley doorway. If the rain gutter interferes with
the Low Frequency Eddy Current (LFEC) inspection, remove it from above the aft galley doorway. At
the upper and lower corners of the aft galley doorway, do an external LFEC inspection of the skin
assembly and bear strap for any crack around fasteners and do an external detailed inspection of the
skin assembly for any crack. If any crack is found in the skin assembly or bear strap, install a repair in
accordance with Structural Repair Manual (SRM). If no crack is found, do the repeat inspections at the
intervals given in Paragraph 1.E., Compliance.
Group 3-8:
Remove the scuff plates at the lower corners of the aft entry doorway and aft galley doorway. If the
rain gutters interfere with the Low Frequency Eddy Current Inspection (LFEC), remove them from
above the aft entry doorway and aft galley doorway. At the upper and lower corners of the aft entry
doorway and aft galley doorway, do an external LFEC inspection of the skin assembly and the bear
strap for any crack around fasteners and do an external detailed inspection of the skin assembly for
any crack. If any crack is found in the skin assembly or bear strap, install a repair in accordance with
Structural Repair Manual (SRM). If no crack is found, do the repeat inspections at the intervals given
in Paragraph 1.E., Compliance.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
1-8737-100, 737-200, 737-200C
Group 2:
Affected Maintenance Zones
ZoneModel
1-8737-200
Group 3-4:
Affected Maintenance Zones
ZoneModel
1-8737-200, 737-200C
Group 5, 7-8:
Affected Maintenance Zones
ZoneModel
108737-300, 737-400, 737-500
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Group 6:
Affected Maintenance Zones
ZoneModel
108737-300
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive (AD) related
to this service bulletin. The AD will make the compliance tasks and times given in this service bulletin
mandatory.
Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX
A and APPENDIX B.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
Post repair Damage Tolerance Inspections (DTI) for the Structural Repair Manual (SRM) repairs
referenced in this service bulletin are specified within each of the SRM repairs.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Group 1:
The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and recommends
immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or
not it is operated under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance
instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1
(line number 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14
CFR 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV.
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Group 3-8:
Table 1: Aft Entry and Aft Galley Doorway Corners - Inspection and Repair
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Oc-
curs Later)
ActionCondition
-Within 4,500 flight
cycles after the
original issue date
of this service bul-
letin.
Before 27,000 to-
tal flight cycles.
Do PART 2: LOW FRE-
QUENCY EDDY CUR-
RENT (LFEC) AND DE-
TAILED INSPECTIONS
OF AFT ENTRY DOOR-
WAY CORNERS for any
crack.
All airplanes.
(a)
Do PART 6: LOW FRE-
QUENCY EDDY CUR-
RENT (LFEC) AND DE-
TAILED INSPECTIONS
OF AFT GALLEY
DOORWAY CORNERS
for any crack. (a)
-Before further flight.CONDITION 1 (ACTION
1): Do PART 3: REPAIR.
(b)
CONDITION 1: ANY
CRACK FOUND IN
THE AFT ENTRY
DOORWAY COR-
NERS. 4,500 flight cycles.-CONDITION 1 (ACTION2): Repeat PART 2: LOW
FREQUENCY EDDY
CURRENT (LFEC) AND
DETAILED INSPEC-
TIONS OF AFT ENTRY
DOORWAY CORNERS
for any crack at unre-
paired and unmodified
doorway corner locations.
4,500 flight cycles.-Repeat PART 2: LOW
FREQUENCY EDDY
CURRENT (LFEC) AND
DETAILED INSPEC-
TIONS OF AFT ENTRY
DOORWAY CORNERS
for any crack.
CONDITION 2: NO
CRACK FOUND IN
THE AFT ENTRY
DOORWAY COR-
NERS.
(a)
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Group 3-8:
Table 1: Aft Entry and Aft Galley Doorway Corners - Inspection and Repair
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Oc-
curs Later)
ActionCondition
-Before further flight.CONDITION 3 (ACTION
1): Do PART 3: REPAIR.
(c)
CONDITION 3: ANY
CRACK FOUND IN
THE AFT GALLEY
DOORWAY COR-
NERS. 4,500 flight cycles.-CONDITION 3 (ACTION2): Repeat PART 6: LOW
FREQUENCY EDDY
CURRENT (LFEC) AND
DETAILED INSPEC-
TIONS OF AFT GALLEY
DOORWAY CORNERS
for any crack at unre-
paired and unmodified
doorway corner locations.
4,500 flight cycles.-Repeat PART 6: LOW
FREQUENCY EDDY
CURRENT (LFEC) AND
DETAILED INSPEC-
TIONS OF AFT GALLEY
DOORWAY CORNERS
for any crack.
CONDITION 4: NO
CRACK FOUND IN
THE AFT GALLEY
DOORWAY COR-
NERS.
(a)
(a) It is not required to inspect the skin and bear strap at a cutout corner location with an existing external
repair or modification if one of the following conditions is met:
1. The installed repair or modification was approved by a Boeing Company authorized representative
who was authorized by the FAA to make such findings, and the installed repair extends a minimum
of three rows of fasteners on each side of the crack trimout and each layer of the repair extends
a minimum of three fastener rows past the doorway cutout corner radius tangent point.
2. The repair or modification was accomplished in accordance with instructions and/or drawings
provided in service bulletin 737-53-1074, Revision 3 or 737-53-1149.
3. The repair was installed in accordance with 737-100/200 SRM 53-30-03 Figure 24 or 46, 737-
300 SRM 53-60-01 Repair 3, 737-300 SRM 53-00-01 Repair 32, 737-400 SRM 53-00-01 Repair
32 or 737-500 SRM 53-00-01 Repair 32.
(b) Accomplishment of PART 3: REPAIR in accordance with this service bulletin is terminating action for the
repeat inspections specified in PART 2: LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS OF AFT ENTRY DOORWAY CORNERS of this service bulletin at the repaired doorway
corner location only.
(c) Accomplishment of PART 3: REPAIR in accordance with this service bulletin is terminating action for the
repeat inspections specified in PART 6: LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS OF AFT GALLEY DOORWAY CORNERS of this service bulletin at the repaired doorway
corner location only.
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Group 2:
Table 2: Aft Galley Doorway Corners - Inspection and Repair
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Oc-
curs Later)
ActionCondition
-Within 4,500 flight
cycles after the
original issue date
of this service bul-
letin.
Before 27,000 to-
tal flight cycles.
Do PART 6: LOW FRE-
QUENCY EDDY CUR-
RENT (LFEC) AND DE-
TAILED INSPECTIONS
OF AFT GALLEY
DOORWAY CORNERS
for any crack.
All airplanes.
(a)
-Before further flight.CONDITION 3 (ACTION
1): Do PART 3: REPAIR.
(b)
CONDITION 3: ANY
CRACK FOUND IN
THE AFT GALLEY
DOORWAY COR-
NERS. 4,500 flight cycles.-CONDITION 3 (ACTION2): Repeat PART 6: LOW
FREQUENCY EDDY
CURRENT (LFEC) AND
DETAILED INSPEC-
TIONS OF AFT GALLEY
DOORWAY CORNERS
for any crack at unre-
paired and unmodified
doorway corner locations.
4,500 flight cycles.-Repeat PART 6: LOW
FREQUENCY EDDY
CURRENT (LFEC) AND
DETAILED INSPEC-
TIONS OF AFT GALLEY
DOORWAY CORNERS
for any crack.
CONDITION 4: NO
CRACK FOUND IN
THE AFT GALLEY
DOORWAY COR-
NERS.
(a)
(a) It is not required to inspect the skin and bear strap at a cutout corner location with an existing external
repair or modification if one of the following conditions is met:
1. The installed repair or modification was approved by a Boeing Company authorized representative
who was authorized by the FAA to make such findings, and the installed repair extends a minimum
of three rows of fasteners on each side of the crack trimout and each layer of the repair extends
a minimum of three fastener rows past the doorway cutout corner radius tangent point.
2. The repair or modification was accomplished in accordance with instructions and/or drawings
provided in service bulletin 737-53-1074, Revision 3 or 737-53-1149.
3. The repair was installed in accordance with 737-100/200 SRM 53-30-03 Figure 24 or 46.
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Group 2:
Table 2: Aft Galley Doorway Corners - Inspection and Repair
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Oc-
curs Later)
ActionCondition
(b) Accomplishment of PART 3: REPAIR in accordance with this service bulletin is terminating action for the
repeat inspections specified in PART 6: LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS OF AFT GALLEY DOORWAY CORNERS of this service bulletin at the repaired doorway
corner location only.
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.
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.
The SRM repairs defined in this service bulletin may be subject to Federal Aviation Administration
(FAA) Airworthiness Directive (AD) AD 98-11-04 R1, AD 2008-08-23, and AD 2008-09-13. Refer to the
specified SRM repair used to determine if any SSI listed in the Supplemental Structural Inspection
Documents (SSID) D6-37089 or D6-82669 may have been affected. An evaluation of these SRM repairs
has been accomplished, and any effects on SSID inspections are contained in the SRM repair.
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 2:
Elapsed HoursTask HoursNumber of PersonsTask
1.501.501Open Access
1.501.501FIGURE 14
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Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
2.505.002FIGURE 7
1.501.501FIGURE 15
1.501.501Close Access
8.5011.00TOTAL FOR EACH AIRPLANE
Group 3:
Elapsed HoursTask HoursNumber of PersonsTask
1.503.002Open Access
1.501.501FIGURE 12
2.505.002FIGURE 2
1.501.501FIGURE 13
1.501.501FIGURE 14
2.505.002FIGURE 7
1.501.501FIGURE 15
1.503.002Close Access
14.0022.00TOTAL FOR EACH AIRPLANE
Group 4:
Elapsed HoursTask HoursNumber of PersonsTask
1.503.002Open Access
1.501.501FIGURE 10
2.505.002FIGURE 3
1.501.501FIGURE 11
1.501.501FIGURE 14
2.505.002FIGURE 7
1.501.501FIGURE 15
1.503.002Close Access
14.0022.00TOTAL FOR EACH AIRPLANE
Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
1.503.002Open Access
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Group 5:
Elapsed HoursTask HoursNumber of PersonsTask
1.501.501FIGURE 10
2.505.002FIGURE 1
1.501.501FIGURE 11
1.501.501FIGURE 14
2.505.002FIGURE 8
1.501.501FIGURE 15
1.503.002Close Access
14.0022.00TOTAL FOR EACH AIRPLANE
Group 6:
Elapsed HoursTask HoursNumber of PersonsTask
1.503.002Open Access
1.501.501FIGURE 12
2.505.002FIGURE 4
1.501.501FIGURE 13
1.501.501FIGURE 14
2.505.002FIGURE 8
1.501.501FIGURE 15
1.503.002Close Access
14.0022.00TOTAL FOR EACH AIRPLANE
Group 7:
Elapsed HoursTask HoursNumber of PersonsTask
1.503.002Open Access
1.501.501FIGURE 10
2.505.002FIGURE 5
1.501.501FIGURE 11
1.501.501FIGURE 14
2.505.002FIGURE 9
1.501.501FIGURE 15
1.503.002Close Access
14.0022.00TOTAL FOR EACH AIRPLANE
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Group 8:
Elapsed HoursTask HoursNumber of PersonsTask
1.503.002Open Access
1.501.501FIGURE 10
2.505.002FIGURE 6
1.501.501FIGURE 11
1.501.501FIGURE 14
2.505.002FIGURE 8
1.501.501FIGURE 15
1.503.002Close Access
14.0022.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
The weight of each repair will depend on the length of any crack found. Get access to the Weight and
Balance Manual (WBM) to calculate the change in moment for each repair.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin 737-53-1074, Revision 3, 737-53-1149
b. Boeing Service Related Problem (SRP) 737-SRP-53-0389, 737-SRP-53-0393
c. Service Bulletin Index D6-19567
d. Standard Overhaul Practices Manual (SOPM) 20-50-01, 20-50-11, 20-50-19
e. 737 Fleet Team Digest (FTD) 53-11004
f. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-26
g. 737-100/200 Aircraft Maintenance Manual (AMM) 52-13-00, 52-14-00, 52-41-00
h. 737-100/200 Structural Repair Manual (SRM) 53-30-03
i. 737-300/400/500 Aircraft Maintenance Manual (AMM) 52-13-00, 52-41-00, 53-13-01
j. 737-300 Structural Repair Manual (SRM) 53-00-01, 53-60-01
k. 737-400 Structural Repair Manual (SRM) 53-00-01
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### Page 33

l. 737-500 Structural Repair Manual (SRM) 53-00-01
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
SKIN PANEL INSTL - AFT GALLEY DOOR, STA 908 - STA 1016,
S-4R TO S-25R
65C35778
SKIN PANEL INSTL - AFT GALLEY DOOR, STA 908 - STA 1016,
S-4R TO S-25R
65-45778
SKIN PANEL INSTL - AFT GALLEY DOOR, STA 908 - STA 1016,
S-4R TO S-25R
65C27756
SKIN PANEL INSTL - AFT ENTRY DOOR, STA 908 - STA 1016,
S-4L TO S-25L
65-45777
SKIN PANEL INSTL - AFT ENTRY DOOR, STA 908 - STA 1016,
S-4L TO S-25L
65-52988
SKIN PANEL INSTL - AFT ENTRY DOOR, STA 908 - STA 1016,
S-4L TO S-25L
65C27755
SKIN PANEL INSTL - AFT ENTRY DOOR, STA 908 - STA 1016,
S-4L TO S-25L
65C35777
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. DTI requirements for the structure affected
are contained in 737-100/200 SRM 53-30-03 Figure 24 or 46, 737-300 SRM 53-60-01 Repair 3,
737-300 SRM 53-00-01 Repair 32, 737-400 SRM 53-00-01 Repair 32, and 737-500 SRM 53-00-01
Repair 32.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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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 configuration changes, inspections and/or repair
procedures given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
No special parts or materials are necessary to do the repair in this service bulletin. But, parts and
materials in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator
part and material supply to make sure all necessary parts and materials are available.
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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### 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.
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.
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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.
9. Refer to APPENDIX A and APPENDIX B 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.
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. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
13. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
14. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
15. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
16. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
17. 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.
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B. WORK INSTRUCTIONS
Group 1:
1. RC - The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and
recommends immediate and permanent removal from service of any airplanes upon reaching the
LOV, whether or not it is operated under FAA jurisdiction. As such, The Boeing Company no longer
provides maintenance instructions for airplanes that have accumulated flight cycles beyond the
LOV. Airplanes in Group 1 (line number 1-291) have accumulated flight cycles beyond the LOV
of the maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of an airplane
beyond its LOV.
Group 2:
1. Do PART 5: ACCESS AFT GALLEY DOOR.
2. RC - Do PART 6: LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED INSPECTIONS
OF AFT GALLEY DOORWAY CORNERS for any crack.
NOTE: It is not required to inspect the skin and bear strap at a cutout corner location with an
existing external repair or modification if one of the following conditions is met:
1. The installed repair or modification was approved by a Boeing Company
authorized representative who was authorized by the FAA to make such findings,
and the installed repair extends a minimum of three rows of fasteners on each
side of the crack trimout and each layer of the repair extends a minimum of three
fastener rows past the doorway cutout corner radius tangent point.
2. The repair or modification was accomplished in accordance with instructions
and/or drawings provided in service bulletin 737-53-1074, Revision 3 or
737-53-1149.
3. The repair was installed in accordance with 737-100/200 SRM 53-30-03 Figure
24 or 46.
a. CONDITION 3: ANY CRACK FOUND IN THE AFT GALLEY DOORWAY CORNERS.
(1) CONDITION 3 (ACTION 1): Do PART 3: REPAIR.
NOTE: Accomplishment of PART 3: REPAIR in accordance with this service bulletin is
terminating action for the repeat inspections specified in PART 6: LOW
FREQUENCY EDDY CURRENT (LFEC) AND DETAILED INSPECTIONS OF
AFT GALLEY DOORWAY CORNERS of this service bulletin at the repaired
doorway corner location only.
(2) CONDITION 3 (ACTION 2): Repeat PART 6: LOW FREQUENCY EDDY CURRENT
(LFEC) AND DETAILED INSPECTIONS OF AFT GALLEY DOORWAY CORNERS for
any crack at unrepaired and unmodified doorway corner locations.
b. CONDITION 4: NO CRACK FOUND IN THE AFT GALLEY DOORWAY CORNERS.
(1) Repeat PART 6: LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS OF AFT GALLEY DOORWAY CORNERS for any crack.
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NOTE: It is not required to inspect the skin and bear strap at a cutout corner location
with an existing external repair or modification if one of the following conditions
is met:
1. The installed repair or modification was approved by a Boeing Company
authorized representative who was authorized by the FAA to make
such findings, and the installed repair extends a minimum of three rows
of fasteners on each side of the crack trimout and each layer of the
repair extends a minimum of three fastener rows past the doorway
cutout corner radius tangent point.
2. The repair or modification was accomplished in accordance with
instructions and/or drawings provided in service bulletin 737-53-1074,
Revision 3 or 737-53-1149.
3. The repair was installed in accordance with 737-100/200 SRM 53-30-03
Figure 24 or 46.
3. Do PART 7: CLOSE ACCESS AFT GALLEY DOOR.
4. Put the airplane back to a serviceable condition.
Group 3-8:
1. Do PART 1: ACCESS AFT ENTRY DOOR.
2. RC - Do PART 2: LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED INSPECTIONS
OF AFT ENTRY DOORWAY CORNERS for any crack.
NOTE: It is not required to inspect the skin and bear strap at a cutout corner location with an
existing external repair or modification if one of the following conditions is met:
1. The installed repair or modification was approved by a Boeing Company
authorized representative who was authorized by the FAA to make such findings,
and the installed repair extends a minimum of three rows of fasteners on each
side of the crack trimout and each layer of the repair extends a minimum of three
fastener rows past the doorway cutout corner radius tangent point.
2. The repair or modification was accomplished in accordance with instructions
and/or drawings provided in service bulletin 737-53-1074, Revision 3 or
737-53-1149.
3. The repair was installed in accordance with 737-100/200 SRM 53-30-03 Figure
24 or 46, 737-300 SRM 53-60-01 Repair 3, 737-300 SRM 53-00-01 Repair 32,
737-400 SRM 53-00-01 Repair 32 or 737-500 SRM 53-00-01 Repair 32.
a. CONDITION 1: ANY CRACK FOUND IN THE AFT ENTRY DOORWAY CORNERS.
(1) CONDITION 1 (ACTION 1): Do PART 3: REPAIR.
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NOTE: Accomplishment of PART 3: REPAIR in accordance with this service bulletin is
terminating action for the repeat inspections specified in PART 2: LOW
FREQUENCY EDDY CURRENT (LFEC) AND DETAILED INSPECTIONS OF
AFT ENTRY DOORWAY CORNERS of this service bulletin at the repaired
doorway corner location only.
(2) CONDITION 1 (ACTION 2): Repeat PART 2: LOW FREQUENCY EDDY CURRENT
(LFEC) AND DETAILED INSPECTIONS OF AFT ENTRY DOORWAY CORNERS for
any crack at unrepaired and unmodified doorway corner locations.
b. CONDITION 2: NO CRACK FOUND IN THE AFT ENTRY DOORWAY CORNERS.
(1) Repeat PART 2: LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS OF AFT ENTRY DOORWAY CORNERS for any crack.
NOTE: It is not required to inspect the skin and bear strap at a cutout corner location
with an existing external repair or modification if one of the following conditions
is met:
1. The installed repair or modification was approved by a Boeing Company
authorized representative who was authorized by the FAA to make
such findings, and the installed repair extends a minimum of three rows
of fasteners on each side of the crack trimout and each layer of the
repair extends a minimum of three fastener rows past the doorway
cutout corner radius tangent point.
2. The repair or modification was accomplished in accordance with
instructions and/or drawings provided in service bulletin 737-53-1074,
Revision 3 or 737-53-1149.
3. The repair was installed in accordance with 737-100/200 SRM 53-30-03
Figure 24 or 46, 737-300 SRM 53-60-01 Repair 3, 737-300 SRM
53-00-01 Repair 32, 737-400 SRM 53-00-01 Repair 32 or 737-500
SRM 53-00-01 Repair 32.
3. Do PART 4: CLOSE ACCESS AFT ENTRY DOOR.
4. Do PART 5: ACCESS AFT GALLEY DOOR.
5. RC - Do PART 6: LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED INSPECTIONS
OF AFT GALLEY DOORWAY CORNERS for any crack.
NOTE: It is not required to inspect the skin and bear strap at a cutout corner location with an
existing external repair or modification if one of the following conditions is met:
1. The installed repair or modification was approved by a Boeing Company
authorized representative who was authorized by the FAA to make such findings,
and the installed repair extends a minimum of three rows of fasteners on each
side of the crack trimout and each layer of the repair extends a minimum of three
fastener rows past the doorway cutout corner radius tangent point.
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2. The repair or modification was accomplished in accordance with instructions
and/or drawings provided in service bulletin 737-53-1074, Revision 3 or
737-53-1149.
3. The repair was installed in accordance with 737-100/200 SRM 53-30-03 Figure
24 or 46, 737-300 SRM 53-60-01 Repair 3, 737-300 SRM 53-00-01 Repair 32,
737-400 SRM 53-00-01 Repair 32 or 737-500 SRM 53-00-01 Repair 32.
a. CONDITION 3: ANY CRACK FOUND IN THE AFT GALLEY DOORWAY CORNERS.
(1) CONDITION 3 (ACTION 1): Do PART 3: REPAIR.
NOTE: Accomplishment of PART 3: REPAIR in accordance with this service bulletin is
terminating action for the repeat inspections specified in PART 6: LOW
FREQUENCY EDDY CURRENT (LFEC) AND DETAILED INSPECTIONS OF
AFT GALLEY DOORWAY CORNERS of this service bulletin at the repaired
doorway corner location only.
(2) CONDITION 3 (ACTION 2): Repeat PART 6: LOW FREQUENCY EDDY CURRENT
(LFEC) AND DETAILED INSPECTIONS OF AFT GALLEY DOORWAY CORNERS for
any crack at unrepaired and unmodified doorway corner locations.
b. CONDITION 4: NO CRACK FOUND IN THE AFT GALLEY DOORWAY CORNERS.
(1) Repeat PART 6: LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS OF AFT GALLEY DOORWAY CORNERS for any crack.
NOTE: It is not required to inspect the skin and bear strap at a cutout corner location
with an existing external repair or modification if one of the following conditions
is met:
1. The installed repair or modification was approved by a Boeing Company
authorized representative who was authorized by the FAA to make
such findings, and the installed repair extends a minimum of three rows
of fasteners on each side of the crack trimout and each layer of the
repair extends a minimum of three fastener rows past the doorway
cutout corner radius tangent point.
2. The repair or modification was accomplished in accordance with
instructions and/or drawings provided in service bulletin 737-53-1074,
Revision 3 or 737-53-1149.
3. The repair was installed in accordance with 737-100/200 SRM 53-30-03
Figure 24 or 46, 737-300 SRM 53-60-01 Repair 3, 737-300 SRM
53-00-01 Repair 32, 737-400 SRM 53-00-01 Repair 32 or 737-500
SRM 53-00-01 Repair 32.
6. Do PART 7: CLOSE ACCESS AFT GALLEY DOOR.
7. Put the airplane back to a serviceable condition.
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Group 3-8:
PART 1: ACCESS AFT ENTRY DOOR
1. Group 3:
a. Open the aft entry door. Refer to 737-100/200 AMM 52-14-00 as an accepted procedure.
b. Remove and keep the scuff plate from the aft entry doorway. Refer to APPENDIX C as an
accepted procedure.
c. If the rain gutter interferes with the Low Frequency Eddy Current (LFEC) inspection, remove
and keep the rain gutter from the aft entry doorway in accordance with FIGURE 12.
d. Get access to the external side of the aft entry doorway.
2. Group 4:
a. Open the aft entry door. Refer to 737-100/200 AMM 52-13-00 as an accepted procedure.
b. Remove and keep the scuff plate from the aft entry doorway. Refer to APPENDIX C as an
accepted procedure.
c. If the rain gutter interferes with the Low Frequency Eddy Current (LFEC) inspection, remove
and keep the rain gutter from the aft entry doorway in accordance with FIGURE 10.
d. Get access to the external side of the aft entry doorway.
3. Group 5, 7-8:
a. Open the aft entry door. Refer to 737-300/400/500 AMM 52-13-00 as an accepted procedure.
b. Remove and keep the scuff plate from the aft entry doorway. Refer to 737-300/400/500 AMM
53-13-01 as an accepted procedure.
c. If the rain gutter interferes with the Low Frequency Eddy Current (LFEC) inspection, remove
and keep the rain gutter from the aft entry doorway in accordance with FIGURE 10.
d. Get access to the external side of the aft entry doorway.
4. Group 6:
a. Open the aft entry door. Refer to 737-300/400/500 AMM 52-13-00 as an accepted procedure.
b. Remove and keep the scuff plate from the aft entry doorway. Refer to 737-300/400/500 AMM
53-13-01 as an accepted procedure.
c. If the rain gutter interferes with the Low Frequency Eddy Current (LFEC) inspection, remove
and keep the rain gutter from the aft entry doorway in accordance with FIGURE 12.
d. Get access to the external side of the aft entry doorway.
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Group 3-8:
PART 2: LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED INSPECTIONS OF AFT
ENTRY DOORWAY CORNERS
1. Group 3:
a. Do Low Frequency Eddy Current (LFEC) and detailed inspections for any crack in accordance
with FIGURE 2.
2. Group 4:
a. Do Low Frequency Eddy Current (LFEC) and detailed inspections for any crack in accordance
with FIGURE 3.
3. Group 5:
a. Do Low Frequency Eddy Current (LFEC) and detailed inspections for any crack in accordance
with FIGURE 1.
4. Group 6:
a. Do Low Frequency Eddy Current (LFEC) and detailed inspections for any crack in accordance
with FIGURE 4.
5. Group 7:
a. Do Low Frequency Eddy Current (LFEC) and detailed inspections for any crack in accordance
with FIGURE 5.
6. Group 8:
a. Do Low Frequency Eddy Current (LFEC) and detailed inspections for any crack in accordance
with FIGURE 6.
Group 2-8:
PART 3: REPAIR
1. Group 2-4:
a. Repair any crack in the skin or bear strap in accordance with 737-100/200 SRM 53-30-03
Figure 46.
2. Group 5-8:
a. Repair any crack in the skin or bear strap in accordance with 737-300 SRM 53-60-01 Repair
3 or 737-300 SRM 53-00-01 Repair 32 or 737-400 SRM 53-00-01 Repair 32 or 737-500 SRM
53-00-01 Repair 32.
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Group 3-8:
PART 4: CLOSE ACCESS AFT ENTRY DOOR
1. Group 3:
a. Install the kept scuff plate to the aft entry doorway. Refer to APPENDIX D as an accepted
procedure.
b. If removed, install the kept rain gutter to the aft entry doorway in accordance with FIGURE
13.
c. Close the aft entry door. Refer to 737-100/200 AMM 52-14-00 as an accepted procedure.
2. Group 4:
a. Install the kept scuff plate to the aft entry doorway. Refer to APPENDIX D as an accepted
procedure.
b. If removed, install the kept rain gutter to the aft entry doorway in accordance with FIGURE
11.
c. Close the aft entry door. Refer to 737-100/200 AMM 52-13-00 as an accepted procedure.
3. Group 5, 7-8:
a. Install the kept scuff plate to the aft entry doorway. Refer to 737-300/400/500 AMM 53-13-01
as an accepted procedure.
b. If removed, install the kept rain gutter to the aft entry doorway in accordance with FIGURE
11.
c. Close the aft entry door. Refer to 737-300/400/500 AMM 52-13-00 as an accepted procedure.
4. Group 6:
a. Install the kept scuff plate to the aft entry doorway. Refer to 737-300/400/500 AMM 53-13-01
as an accepted procedure.
b. If removed, install the kept rain gutter to the aft entry doorway in accordance with FIGURE
13.
c. Close the aft entry door. Refer to 737-300/400/500 AMM 52-13-00 as an accepted procedure.
Group 2-8:
PART 5: ACCESS AFT GALLEY DOOR
1. Group 2-4:
a. Open the aft galley door. Refer to 737-100/200 AMM 52-41-00 as an accepted procedure.
b. Remove and keep the scuff plate from the aft galley doorway. Refer to APPENDIX C as an
accepted procedure.
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c. If the rain gutter interferes with the Low Frequency Eddy Current (LFEC) inspection, remove
and keep the rain gutter from the aft galley doorway in accordance with FIGURE 14.
d. Get access to the external side of the aft galley doorway.
2. Group 5-8:
a. Open the aft galley door. Refer to 737-300/400/500 AMM 52-41-00 as an accepted procedure.
b. Remove and keep the scuff plate from the aft galley doorway. Refer to 737-300/400/500 AMM
53-13-01 as an accepted procedure.
c. If the rain gutter interferes with the Low Frequency Eddy Current (LFEC) inspection, remove
and keep the rain gutter from the aft galley doorway in accordance with FIGURE 14.
d. Get access to the external side of the aft galley doorway.
Group 2-8:
PART 6: LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED INSPECTIONS OF AFT
GALLEY DOORWAY CORNERS
1. Group 2-4:
a. Do Low Frequency Eddy Current (LFEC) and detailed inspections for any crack in accordance
with FIGURE 7.
2. Group 5-6, 8:
a. Do Low Frequency Eddy Current (LFEC) and detailed inspections for any crack in accordance
with FIGURE 8.
3. Group 7:
a. Do Low Frequency Eddy Current (LFEC) and detailed inspections for any crack in accordance
with FIGURE 9.
Group 2-8:
PART 7: CLOSE ACCESS AFT GALLEY DOOR
1. Group 2-4:
a. Install the kept scuff plate to the aft galley doorway. Refer to APPENDIX D as an accepted
procedure.
b. If removed, install the kept rain gutter to the aft galley doorway in accordance with FIGURE
15.
c. Close the aft galley door. Refer to 737-100/200 AMM 52-41-00 as an accepted procedure.
2. Group 5-8:
a. Install the kept scuff plate to the aft galley doorway. Refer to 737-300/400/500 AMM 53-13-01
as an accepted procedure.
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### Page 47

b. If removed, install the kept rain gutter to the aft galley doorway in accordance with FIGURE
15.
c. Close the aft galley door. Refer to 737-300/400/500 AMM 52-41-00 as an accepted procedure.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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BOEING SERVICE BULLETIN 737-53A1350
ALERTALERT

### Page 48 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
This Figure applies only to: Group S.
STA  STA  STA
908  992.8  1016
S-6L -
S-10L
BEAR STRAP
S-14L -
S-20L -  ID
2439238
FIGURE 1: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 1 OF 6)
Original Issue: May 06, 2016
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PROPRIETARY - Copyright @ Unpublished
Work - See page 1 for details.  48 of 123

### Page 49 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
STA  STA
951  REVEAL  967
S-6L
UPPER DOOR
+  SILL
S-7L-
BEAR  TYPICAL
STRAP  CRACK
S-8L
-SUPPORT FRAME
SUPPORT FITTING
DETAILED INSPECTION AREA
DETAILED INSPECTION AND
LOW FREQUENCY EDDY  CURRENT INSPECTION AREA  2444280
FIGURE 1: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 2 OF 6)
Original Issue: May 06, 2016
Export Controlled ECCN: 9E991 - BOEING  737-53A1350
PROPRIETARY - Copyright © Unpublished  Work - See page 1 for details.  49 of 123

### Page 50 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
STA  STA
986.50  992.80
• S-6L
UPPER
DOOR SILL
REVEAL
• S-7L
TYPICAL CRACK
BEAR STRAP
• S-8L
WD
DETAILED INSPECTION AREA
DETAILED INSPECTION AND LOW FREQUENCY  2439257
EDDY CURRENT INSPECTION AREA
FIGURE 1: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 3 OF 6)
Original Issue: May 06, 2016
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-53A1350
Work - See page 1 for details.  50 of 123

### Page 51 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
SUPPORT  FITTING  FRAME  SUPPORT FRAME
S-16L  TYPICAL CRACK
LOWER DOOR  SILL  SCUFF PLATE  LOCATION OF REMOVED
DOOR CUTOUT
S-17L
S-18L
BEAR STRAP
STA  STA
951  967
DETAILED INSPECTION AREA
- DETAILED INSPECTION AND LOW FREQUENCY  2439263
4 EDDY CURRENT INSPECTION AREA
FIGURE 1: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 4 OF 6)
Original Issue: May 06, 2016
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Work - See page 1 for details.  51 of 123

### Page 52 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
- S-16L
LOCATION OF REMOVED
SCUFF PLATE  TYPICAL
CRACK  - S-17AL
DOOR CUTOUT
LOWER
DOOR SILL
• S-17L
- S-19L
BEAR STRAP
STA  STA
986.5  992.8
DETAILED INSPECTION AREA
DETAILED INSPECTION AND LOW FREQUENCY  2439272
EDDY CURRENT INSPECTION AREA
FIGURE 1: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 5 OF 6)
Original Issue: May 06, 2016
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  737-53A1350
Work - See page 1 for details.  52 of 123

### Page 53

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a) (c) (d)--Skin assemblyInspect1
(a) (c) (d)--Bear strapInspect
(b) (c)--Skin assemblyInspect2
(a) (c) (d)--Skin assemblyInspect3
(a) (c) (d)--Bear strapInspect
(b) (c)--Skin assemblyInspect4
(a) (c) (d)--Skin assemblyInspect5
(a) (c) (d)--Bear strapInspect
(b) (c)--Skin assemblyInspect6
(a) (c) (d)--Skin assemblyInspect7
(a) (c) (d)--Bear strapInspect
(b) (c)--Skin assemblyInspect8
(a) Do an external Low Frequency Eddy Current (LFEC) inspection of the skin assembly and the bear strap
for any crack around the fasteners in accordance with 737 NDT Manual Part 6, 51-00-26. For both upper
and lower corners, the thicknesses in inches are: Skin = 0.036, Doubler = 0.036, Bear strap = 0.09.
(b) Do an external detailed inspection of the skin assembly for any crack.
(c) It is not required to inspect the skin and bear strap at a cutout corner location with an existing external
repair or modification if one of the following conditions is met:
1. The installed repair or modification was approved by a Boeing Company authorized representative
who was authorized by the FAA to make such findings, and the installed repair extends a minimum
of three rows of fasteners on each side of the crack trimout and each layer of the repair extends
a minimum of three fastener rows past the doorway cutout corner radius tangent point.
2. The repair was installed in accordance with 737-300 SRM 53-60-01 Repair 3, 737-300 SRM 53-
00-01 Repair 32, 737-400 SRM 53-00-01 Repair 32 or 737-500 SRM 53-00-01 Repair 32.
(d) Cracks typically originate at the fastener holes and grow towards the corners of the doorways.
FIGURE 1: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 06, 2016
737-53A1350
53 of 123
BOEING SERVICE BULLETIN 737-53A1350
ALERTALERT

### Page 54 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
This Figure applies only to: Group 3.
STA  STA  STA  STA
908  947.5  992.8  1016
S-6L -
S-10L
BEAR STRAP
S-14L -
S-20L -  ID
2439401
FIGURE 2: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 1 OF 6)
Original Issue: May 06, 2016
Export Controlled ECCN: 9E991 - BOEING  737-53A1350
PROPRIETARY - Copyright @ Unpublished
Work - See page 1 for details.  54 of 123

### Page 55 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
STA
947.5
S-6L
UPPER
DOOR SILL
TYPICAL CRACK
REVEAL
BEAR STRAP.
S-8L
DETAILED INSPECTION AREA
• DETAILED INSPECTION AND LOW FREQUENCY  2444302
EDDY CURRENT INSPECTION AREA
FIGURE 2: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 2 OF 6)
Original Issue: May 06, 2016
Export Controlled ECCN: 9E991 - BOEING  737-53A1350
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  55 of 123

### Page 56 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
986.5  STA  992.8  STA  UPPER DOOR  SILL
- S-6L
- BEAR STRAP
- S-7L
- REVEAL
TYPICAL
CRACK
- S-8L
VD
DETAILED INSPECTION AREA
DETAILED INSPECTION AND LOW FREQUENCY  EDDY CURRENT INSPECTION AREA  2439260
FIGURE 2: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 3 OF 6)
Original Issue: May 06, 2016
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright @ Unpublished  737-53A1350
Work - See page 1 for details.  56 of 123

### Page 57 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
STA
947.5
REVEAL
S-16L -
BEAR
STRAP
CORNER FITTING
LOWER
DOOR SILL
TYPICAL CRACK
DOOR CUTOUT
S-17L
S-18L
FWD
DETAILED INSPECTION AREA
DETAILED INSPECTION AND LOW FREQUENCY  2443150
EDDY CURRENT INSPECTION AREA
FIGURE 2: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 4 OF 6)
Original Issue: May 06, 2016
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Work - See page 1 for details.  57 of 123

### Page 58 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
_ REVEAL
- S-16L
BEAR
SUPPORT  STRAP
FITTING
TYPICAL
CRACK
- S-17AL
DOOR  FITTING  CORNER  LOWER  DOOR SILL
- S-17L
STA  STA
986.5  992.8
DETAILED INSPECTION AREA
DETAILED INSPECTION AND LOW FREQUENCY  2439275
EDDY CURRENT INSPECTION AREA
FIGURE 2: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 5 OF 6)
Original Issue: May 06, 2016
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-53A1350
Work - See page 1 for details.  58 of 123

### Page 59

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a) (c) (d)--Skin assemblyInspect1
(a) (c) (d)--Bear strapInspect
(b) (c)--Skin assemblyInspect2
(a) (c) (d)--Skin assemblyInspect3
(a) (c) (d)--Bear strapInspect
(b) (c)--Skin assemblyInspect4
(a) (c) (d)--Skin assemblyInspect5
(a) (c) (d)--Bear strapInspect
(b) (c)--Skin assemblyInspect6
(a) (c) (d)--Skin assemblyInspect7
(a) (c) (d)--Bear strapInspect
(b) (c)--Skin assemblyInspect8
(a) Do an external Low Frequency Eddy Current (LFEC) inspection of the skin assembly and the bear strap
for any crack around the fasteners in accordance with 737 NDT Manual Part 6, 51-00-26. For both upper
and lower corners, the thicknesses in inches are: Skin = 0.036, Doubler = 0.036, Bear strap = 0.10.
(b) Do an external detailed inspection of the skin assembly for any crack.
(c) It is not required to inspect the skin and bear strap at a cutout corner location with an existing external
repair or modification if one of the following conditions is met:
1. The installed repair or modification was approved by a Boeing Company authorized representative
who was authorized by the FAA to make such findings, and the installed repair extends a minimum
of three rows of fasteners on each side of the crack trimout and each layer of the repair extends
a minimum of three fastener rows past the doorway cutout corner radius tangent point.
2. The repair or modification was accomplished in accordance with instructions and/or drawings
provided in service bulletin 737-53-1074, Revision 3 or 737-53-1149.
3. The repair was installed in accordance with 737-100/200 SRM 53-30-03 Figure 24 or 46.
(d) Cracks typically originate at the fastener holes and grow towards the corners of the doorways.
FIGURE 2: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: May 06, 2016
737-53A1350
59 of 123
BOEING SERVICE BULLETIN 737-53A1350
ALERTALERT

### Page 60 (OCR)

BOEING SERVICE BULLETIN 737-53A1350
ALERT  ALERT
This Figure applies only to: Group 4.
STA  STA  STA  STA
908  951  992.8  1016
S-6L -
S-10L
BEAR STRAP
S-14L -
S-20L -  ID
2439239
FIGURE 3: AFT ENTRY DOORWAY CORNERS - LOW FREQUENCY EDDY CURRENT (LFEC) AND DETAILED
INSPECTIONS
(SHEET 1 OF 6)
Original Issue: May 06, 2016
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  737-53A1350
Work - See page 1 for details.  60 of 123

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