# Boeing Alert Service Bulletin 737-53A1354: No revision named

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- Document: [Boeing Alert Service Bulletin 737-53A1354](https://openairdocs.org/service-documents/boeing/737-53a1354.md)
- Title as filed: SB-737-53A1354-00
- Pages: 59
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## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1354
Original Issue: December 02, 2016
ATA System: 5311 5331
SUBJECT: FUSELAGE - Frames and Bulkheads - Section 41 Lower Lobe Frames - Inspections
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2016 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: December 02, 2016
737-53A1354
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2.0

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### Page 3

Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 25
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 27
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 27
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
FIGURE 1: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES LEFT SIDE FOR ANY CRACK
[Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
FIGURE 2: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES RIGHT SIDE FOR ANY CRACK
[Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42
FIGURE 3: HFEC INSPECTION OF THE STA 312, STA 328 AND STA 344 SECTION 41 LOWER LOBE
FRAMES RIGHT SIDE FOR ANY CRACK [Group 2] . . . . . . . . . . . . . . . . . . . . . 46
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE, TABLE 1: INSPECTION FOR ANY
CRACK IN THE SECTION 41 LOWER LOBE FRAMES, LEFT AND RIGHT SIDE [Group 2]
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE, TABLE 2: INSPECTION FOR ANY
CRACK IN THE STA 312, STA 328 AND STA 344 LOWER LOBE FRAMES, RIGHT SIDE ONLY
[Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56
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APPENDIX C: TYPICAL FRAME CONSTRUCTION AND COMPONENT IDENTIFICATION  [Group 2] . 58
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-53A1354Original Issue: December 02, 2016
ATA System: 5311 5331
SUBJECT: FUSELAGE - Frames and Bulkheads - Section 41 Lower Lobe Frames - Inspections
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin is sent to inspect fuselage Section 41 lower lobe frames between STA 268.25 and STA
360 below S-17 for cracking. Frame cracking is the result of fatigue caused by cyclic pressurization of the
fuselage. If cracks are not detected and repaired, they can grow until the frames sever. Continued operation of
the airplane with multiple adjacent severed frames could result in uncontrolled decompression of the airplane.
Also, the combination of a severed frame and fuselage skin chem-mill cracks in this area can lead to an
uncontrolled decompression of the airplane.
There have been eleven reports of frame web cracking at the STA 344 system penetration holes between S-22L
and S-24L. Findings were between 25,713 and 68,093 total flight cycles and between 55,058 and 76,358 total
flight hours. Crack lengths were from 0.78 inches to 1.57 inches long. Refer to Boeing Service Bulletins
737-53A1323 and 737-53A1064 for reports of other Section 41 lower lobe fuselage frame cracking and required
inspections.
Boeing Service Related Problem (SRP) 737-SRP-53-0515 is related to this service bulletin.
Boeing Fleet Team Digest 737-FTD-53-10004 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 ChangesNoWeight and Balance Change
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### Page 6

ReferenceAffectedPlanning Data
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.
Group 2:
Do Part 2: High Frequency Eddy Current (HFEC), detailed and general visual inspections of the Section 41
lower lobe frames between STA 268.25 and STA 360 left side for any crack and do detailed and general visual
inspections of the Section 41 lower lobe frames between STA 268.25 and STA 360 right side for any crack. If
any crack is found, contact The Boeing Company for repair instructions and do the repair and repeat Part 2
inspections for any crack at the intervals given in Paragraph 1.E., Compliance. If no crack is found, repeat Part
2 inspections for any crack at the intervals given in Paragraph 1.E., Compliance.
Group 2:
Do Part 3: HFEC inspection of the STA 312, STA 328 and STA 344 lower lobe frames, right side for any crack.
If any crack is found, contact The Boeing Company for repair instructions and do the repair and repeat Part 3
inspections for any crack at the intervals given in Paragraph 1.E., Compliance. If no crack is found, repeat Part
3 inspections for any crack at the intervals given in Paragraph 1.E., Compliance.
EFFECTIVITY
737-100/-200/-200C/-300/-400/-500 Airplanes. Refer to Paragraph 1.A., Effectivity, for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
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INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection 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 737-53A1354
ALERT  ALERT
STA
GROUP 2:  294.5
DO PART 3: HIGH FREQUENCY EDDY
CURRENT (HFEC) INSPECTION OF THE
STA 312, STA 328 AND STA 344 LOWER
LOBE FRAMES RIGHT SIDE FOR ANY
CRACK
S-17R
S-19R -
S-22R
STA
| 259.5
STA
BL-O  STA  344
380 |  STA
STA  312
360
GROUP 2:
DO PART 2: DETAILED AND GENERAL VISUAL INSPECTIONS OF
THE SECTION 41 LOWER LOBE FRAMES BETWEEN STA 268.25
AND STA 360 RIGHT SIDE FOR ANY CRACK
GROUP 2:
DO PART 2: HIGH FREQUENCY EDDY CURRENT
(HFEC), DETAILED AND GENERAL VISUAL
STA  INSPECTIONS OF THE SECTION 41 LOWER LOBE
294.5  FRAMES BETWEEN STA 268.25 AND STA 360 LEFT
SIDE FOR ANY CRACK
AIRSTAIR CUTOUT
IS OPTIONAL
S-17L
STA
259.5
STA
277  STA  BL-O
STA  360
312 STA STA  344  380  2501520
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### Page 9

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1354
Original Issue: December 02, 2016
ATA System: 5311 5331
SUBJECT: FUSELAGE - Frames and Bulkheads - Section 41 Lower Lobe Frames - Inspections
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is applicable to 737-100/-200/-200C/-300/-400/-500 airplanes, line numbers
1-2565 in two groups. The Variable Numbers and Group Information for the applicable airplanes
is given below.
DESCRIPTIONCONFIGURATIONGROUP
737-100/-200/-200C airplanes, line numbers 1-291.-1
737-200/-200C/-300/-400/-500 airplanes, line numbers 292-2565.-2
Airplane Models:
737-100, 737-200, 737-200C, 737-300, 737-400, 737-500
GroupVariable Number
1PA001 - PA022
1PA099
1PA231 - PA232
1PC001 - PC005
1PG001 - PG075
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GroupVariable Number
1PG199
1PG201 - PG230
1PG251 - PG255
1PG271 - PG279
1PG301 - PG314
1PG331 - PG332
1PG351 - PG356
1PG375
1PG401 - PG403
1PG431 - PG442
1PG471 - PG475
1PG501 - PG505
1PG571 - PG583
2PG584 - PG586
1PG621 - PG630
1PG651 - PG652
1PG701 - PG705
2PH001
2PH011 - PH013
2PH021 - PH024
1PH701 - PH715
1PH731 - PH732
1PH741 - PH742
2PH743
1PJ001 - PJ002
2PJ003 - PJ009
1PJ031 - PJ032
1PJ071 - PJ072
1PJ101 - PJ104
2PJ105 - PJ119
2PJ201 - PJ219
2PJ301 - PJ302
2PJ551 - PJ552
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GroupVariable Number
2PK026 - PK029
2PK041 - PK053
2PK061 - PK070
2PK081 - PK082
2PK091 - PK099
2PK101 - PK103
2PK111 - PK120
2PK141 - PK146
2PK201 - PK204
2PK211 - PK223
2PK231 - PK241
2PK251 - PK258
2PK271 - PK274
2PK281 - PK289
2PK291
2PK301 - PK318
2PK341
2PK351 - PK361
2PK391
2PK431 - PK433
2PK451 - PK452
2PK461 - PK469
2PK495
2PK501 - PK504
2PK511 - PK515
2PK519
2PK521 - PK528
2PK541 - PK565
2PK581
2PK591 - PK599
2PK601 - PK617
2PK621 - PK637
2PK641 - PK642
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GroupVariable Number
2PK661 - PK666
2PK671 - PK681
2PK691 - PK697
2PK711 - PK716
2PK731 - PK765
2PK771 - PK779
2PK801 - PK804
2PK819 - PK827
2PK830
2PK861 - PK863
2PK871 - PK874
2PK881 - PK884
2PK901 - PK938
2PK971 - PK974
2PL001 - PL028
2PL061
2PL081
2PL101 - PL113
2PL151
2PL171 - PL172
2PL201 - PL203
2PL221
2PL401 - PL417
2PL421
2PL441
2PL451 - PL456
2PL471
2PL491
2PL501 - PL506
2PL551 - PL562
2PL581
2PL601 - PL603
2PL611
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GroupVariable Number
2PL621 - PL626
2PL631 - PL632
1PL711 - PL712
1PL716
2PL717 - PL747
2PL756
2PL758
2PL761 - PL770
2PL781 - PL788
2PL793
1PL801 - PL803
2PM001 - PM006
2PM016 - PM017
2PM021 - PM023
2PM051 - PM066
2PM101 - PM119
2PM141 - PM142
2PM171
2PM181
2PM251 - PM255
2PM281 - PM283
2PM381 - PM399
2PM401 - PM417
2PM541 - PM547
2PM551 - PM564
2PN001 - PN002
2PN021 - PN043
2PN081 - PN086
2PN101 - PN117
2PN131 - PN163
2PN401 - PN420
2PN431 - PN433
2PN451 - PN456
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GroupVariable Number
2PN471 - PN474
2PN481
2PN491 - PN493
2PN501 - PN502
2PN511 - PN512
2PN521
2PP001 - PP054
2PP101 - PP169
2PP181 - PP199
2PP201 - PP205
2PP221
2PP231 - PP243
2PP281 - PP286
2PP301 - PP305
2PP351 - PP353
2PP376 - PP384
2PP391 - PP393
2PP401 - PP440
2PP471 - PP475
2PP501 - PP517
2PP521 - PP522
2PP631 - PP634
2PP651 - PP652
2PP671 - PP699
2PP701 - PP733
2PP771 - PP779
2PP801 - PP808
2PP821 - PP827
2PP831 - PP848
2PP851 - PP852
2PP861 - PP875
2PP891 - PP899
2PP901 - PP936
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GroupVariable Number
2PP946 - PP948
2PP951 - PP952
2PP961 - PP967
2PP981 - PP991
2PP993
2PQ001 - PQ016
2PQ026 - PQ041
2PQ051 - PQ092
2PQ101 - PQ199
2PQ201 - PQ202
2PQ221 - PQ237
2PQ241 - PQ243
2PQ251 - PQ267
2PQ281 - PQ296
2PQ301 - PQ307
2PQ331 - PQ332
2PQ341 - PQ344
2PQ361 - PQ369
2PQ401 - PQ408
2PQ411 - PQ413
2PQ421
2PQ471 - PQ473
2PQ479 - PQ481
2PQ486 - PQ487
2PQ491 - PQ493
2PQ771
2PQ791 - PQ793
2PQ801 - PQ805
2PQ931 - PQ932
2PS601 - PS616
2PS631
2PS636 - PS638
2PS641 - PS644
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GroupVariable Number
2PS651 - PS657
2PS666 - PS669
2PS691 - PS692
2PS701 - PS703
2PS751 - PS762
2PT001 - PT011
2PT021 - PT028
2PT041 - PT064
2PT101 - PT105
2PT121 - PT125
2PT146 - PT148
2PT161 - PT170
2PT181 - PT187
2PT211 - PT220
2PT295
2PT301 - PT306
2PT331 - PT360
2PT381 - PT399
2PT401 - PT438
2PT501 - PT512
2PT561 - PT565
2PT581 - PT584
2PT611 - PT621
2PT641 - PT642
2PT651 - PT655
2PT671 - PT672
2PT701 - PT703
2PU001 - PU025
2PV001 - PV055
2PV201 - PV203
2PV231 - PV237
2PV271 - PV272
2PV281 - PV283
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GroupVariable Number
2PW001 - PW054
2PW061 - PW068
2PW072
2PW091 - PW094
2PW101 - PW102
2PW106
2PW111 - PW120
2PW156 - PW157
2PW161 - PW167
2PW201 - PW245
2PW261
2PW265 - PW268
2PW278
2PW281 - PW284
2PW293
2PW296
2PW301 - PW327
2PW461 - PW467
2PW501 - PW504
2PW511 - PW520
2PW526
2PW531 - PW546
2PW556 - PW557
2PW561 - PW564
2PW571 - PW576
2PW591 - PW596
2PW611 - PW620
2PW631 - PW634
2PW661 - PW662
2PW681 - PW683
2PW701 - PW702
2PW711 - PW717
2PW741 - PW742
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GroupVariable Number
2PW761
2PW771
1PX071
1PX701
1PY001 - PY008
1PY021
2PY022
1PY031
2PY036 - PY037
2PY046 - PY048
2PY051 - PY053
2PY056 - PY057
2PY101 - PY103
2PY111 - PY113
2PY131 - PY135
2PY141 - PY143
2PY151 - PY154
2PY156 - PY157
2PY161 - PY162
2PY166
2PY191
2PY201
2PY221 - PY222
2PY231
2PY241 - PY244
2PY270 - PY275
2PY281
2PY286
1PY301 - PY304
1PY321 - PY323
1PY341 - PY346
1PY361 - PY362
1PY381
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GroupVariable Number
2PY401
2PY409 - PY411
2PY421 - PY422
2PY441
2PY451
2PY461 - PY463
2PY591 - PY595
2PY611 - PY612
2PY621
2PY631
2PY651
2PY671 - PY672
2PY721
2PY741
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin is sent to inspect fuselage Section 41 lower lobe frames between STA 268.25 and
STA 360 below S-17 for cracking. Frame cracking is the result of fatigue caused by cyclic pressurization
of the fuselage. If cracks are not detected and repaired, they can grow until the frames sever. Continued
operation of the airplane with multiple adjacent severed frames could result in uncontrolled
decompression of the airplane. Also, the combination of a severed frame and fuselage skin chem-mill
cracks in this area can lead to an uncontrolled decompression of the airplane.
There have been eleven reports of frame web cracking at the STA 344 system penetration holes
between S-22L and S-24L. Findings were between 25,713 and 68,093 total flight cycles and between
55,058 and 76,358 total flight hours. Crack lengths were from 0.78 inches to 1.57 inches long. Refer
to Boeing Service Bulletins 737-53A1323 and 737-53A1064 for reports of other Section 41 lower lobe
fuselage frame cracking and required inspections.
Boeing Service Related Problem (SRP) 737-SRP-53-0515 is related to this service bulletin.
Boeing Fleet Team Digest 737-FTD-53-10004 is related to this service bulletin.
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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.
Group 2:
Do Part 2: High Frequency Eddy Current (HFEC), detailed and general visual inspections of the Section
41 lower lobe frames between STA 268.25 and STA 360 left side for any crack and do detailed and
general visual inspections of the Section 41 lower lobe frames between STA 268.25 and STA 360 right
side for any crack. If any crack is found, contact The Boeing Company for repair instructions and do
the repair and repeat Part 2 inspections for any crack at the intervals given in Paragraph 1.E.,
Compliance. If no crack is found, repeat Part 2 inspections for any crack at the intervals given in
Paragraph 1.E., Compliance.
Group 2:
Do Part 3: HFEC inspection of the STA 312, STA 328 and STA 344 lower lobe frames, right side for
any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair
and repeat Part 3 inspections for any crack at the intervals given in Paragraph 1.E., Compliance. If no
crack is found, repeat Part 3 inspections for any crack 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
2-2737-100, 737-200, 737-200C
Group 2:
Affected Maintenance Zones
ZoneModel
2-2737-200, 737-200C
Group 2:
Affected Maintenance Zones
ZoneModel
202, 205737-300, 737-400, 737-500
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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.
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.
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.
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.
Group 2:
Table 1: Inspection in the Section 41 Lower Lobe Frames between STA 268.25 and STA 360, left and
right side for any crack.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 4,500
flight cycles af-
ter the original
issue date of
this service bul-
letin.
Before 35,000
total flight cy-
cles.
Do PART 2: HIGH FRE-
QUENCY EDDY CUR-
RENT (HFEC), DE-
TAILED AND GENERAL
VISUAL INSPECTIONS
OF THE SECTION 41
LOWER LOBE FRAMES
BETWEEN STA 268.25
AND STA 360, LEFT
SIDE AND DETAILED
AND GENERAL VISUAL
INSPECTIONS OF THE
LOWER LOBE FRAMES
BETWEEN STA 268.25
AND STA 360, RIGHT
SIDE for any crack. (a)
All Airplanes.
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Group 2:
Table 1: Inspection in the Section 41 Lower Lobe Frames between STA 268.25 and STA 360, left and
right side for any crack.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 1 (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.
-CONDITION 1 (ACTION
2): Repeat PART 2: HIGH
FREQUENCY EDDY
CURRENT (HFEC), DE-
TAILED AND GENERAL
VISUAL INSPECTIONS
OF THE SECTION 41
LOWER LOBE FRAMES
BETWEEN STA 268.25
AND STA 360, LEFT
SIDE AND DETAILED
AND GENERAL VISUAL
INSPECTIONS OF THE
LOWER LOBE FRAMES
BETWEEN STA 268.25
AND STA 360, RIGHT
SIDE for any crack. (a)
12,000 flight cy-
cles.
-Repeat PART 2: HIGH
FREQUENCY EDDY
CURRENT (HFEC), DE-
TAILED AND GENERAL
VISUAL INSPECTIONS
OF THE SECTION 41
LOWER LOBE FRAMES
BETWEEN STA 268.25
AND STA 360, LEFT
SIDE AND DETAILED
AND GENERAL VISUAL
INSPECTIONS OF THE
LOWER LOBE FRAMES
BETWEEN STA 268.25
AND STA 360, RIGHT
SIDE for any crack. (a)
CONDITION 2: NO
CRACK FOUND.
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Group 2:
Table 1: Inspection in the Section 41 Lower Lobe Frames between STA 268.25 and STA 360, left and
right side for any crack.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
(a) PART 2 HFEC inspections are not required at the 1.0 inch diameter holes in the STA 336 or STA 344
frame web at the repaired location only, provided:
1. The repair is the corrective action for the crack condition at the 1.0 inch diameter holes identified
in this service bulletin and the repair does not re-install any open hole, AND
2. The installed repair is approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
Group 2:
Table 2: Inspection in the STA 312, STA 328 and STA 344 Lower Lobe Frames, right side for any crack.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 4,500
flight cycles af-
ter the original
issue date of
this service bul-
letin.
Before 35,000
total flight cy-
cles.
Do PART 3: HIGH FRE-
QUENCY EDDY CUR-
RENT (HFEC) INSPEC-
TION OF THE STA 312,
STA 328 and STA 344
LOWER LOBE FRAMES,
RIGHT SIDE for any
crack. (a) (b)
All Airplanes
-Before further flight.CONDITION 3 (ACTION
1): Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 3: ANY
CRACK FOUND.
4,500 flight cycles.-CONDITION 3 (ACTION
2): Repeat PART 3: HIGH
FREQUENCY EDDY
CURRENT (HFEC) IN-
SPECTION OF THE STA
312, STA 328 and STA
344 LOWER LOBE
FRAMES, RIGHT SIDE
for any crack. (a) (b)
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Group 2:
Table 2: Inspection in the STA 312, STA 328 and STA 344 Lower Lobe Frames, right side for any crack.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
4,500 flight cycles.-Repeat PART 3: HIGH
FREQUENCY EDDY
CURRENT (HFEC) IN-
SPECTION OF THE STA
312, STA 328 and STA
344 LOWER LOBE
FRAMES, RIGHT SIDE
for any crack. (a) (b)
CONDITION 4: NO
CRACK FOUND.
(a) PART 3 HFEC inspection is not required at STA 328 frame, if STA 328 was repaired in accordance with
SB 737-53A1323, Accomplishment Instructions 3.B.6.
(b) PART 3 HFEC inspections are not required at an open hole in the STA 328 frame web provided:
1. There is an installed repair that plugs or removes the open hole between stringers S-20R and
S-22R identified in this service bulletin, AND
2. The installed repair is approved by The Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
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.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools
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Elapsed HoursTask HoursNumber of PersonsTask
4.258.502Open Access
26.0052.002FIGURE 1
20.0040.002FIGURE 2
5.005.001FIGURE 3
4.258.502Close Access
59.50114.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Weight and Balance changes affected by incorporation of this service bulletin are dependent on the
type, number and location of repairs done on each particular airplane. Weight and Balance are to be
calculated by the operator by weighing parts installed or removed. Operators should make necessary
revisions to the appropriate weight and balance report.
I. Electrical Load Data
Not applicable.
J. References
1. Existing Data:
a. Boeing Service Bulletin 737-53A1064, 737-53A1323
b. Boeing Service Letter 737-SL-51-042
c. Boeing Service Related Problem (SRP) 737-SRP-53-0515
d. Service Bulletin Index D6-19567
e. Fleet Team Digest (FTD) 737-FTD-53-10004
f. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00 Procedure 1, 4, 11, 16, 23
g. 737-100/200 Aircraft Maintenance Manual (AMM) 25-51-00, 25-52-100, 52-31-00, 52-48-41
h. 737-300/400/500 Aircraft Maintenance Manual (AMM) 25-51-00, 25-52-81, 52-31-00, 52-48-41
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
FRAME AND BEAM INSTL - STA 27765-45805
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TitleDrawing Number
FRAME INSTL - LOWER LOBE - STA 268.25 AND STA 285.6265-45806
BULKHEAD INSTL - STA 294.565-45808
FRAME INSTL - STA 303.965-17684
FRAME INSTL - STA 31265-45810
FRAME INSTL - STA 32065-45811
FRAME INSTL - STA 32865-45812
FRAME INSTL - AFT, FWD GALLEY DOOR - STA 332.1065-45813
FRAME INSTL - STA 33665-45814
FRAME INSTL - STA 34465-45815
FRAME INSTL - STA 323.765-45816
FRAME INSTL - STA 351.265-45817
CARRIAGE TRACK INSTL - AIRSTAIR DOOR STA 325.38 AND
STA 330.62
65-45885
FRAME AND INTERCOSTAL INSTL - STA 36065-54960
FRAME INSTL - STA 36065-58280
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 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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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.
— Values for airframe maintenance tasks are included in Chapter 20 of 737
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 737
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. 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.
5. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure or irregularity.
This level of inspection is made from within touching distance unless otherwise
specified. A mirror may be necessary to enhance visual access to all exposed surfaces
in the inspection area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may
require removal or opening of access panels or doors. Stands, ladders or platforms
may be required to gain proximity to the area being checked.
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6. 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.
7. 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.
8. 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.
9. Refer to APPENDIX C for TYPICAL FRAME CONSTRUCTION AND COMPONENT
IDENTIFICATION.
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. 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.
14. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
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. If a step or sub-step is labeled 'RC
Exempt' then the RC requirement is removed from that step or sub-step. An Alternative
Method of Compliance (AMOC) is required for any deviations to RC steps, including
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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
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 1: GET ACCESS TO THE SECTION 41 LOWER LOBE FRAMES BETWEEN STA
268.25 AND STA 360, LEFT AND RIGHT SIDE.
2. RC - Do PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC), DETAILED AND GENERAL
VISUAL INSPECTIONS OF THE SECTION 41 LOWER LOBE FRAMES BETWEEN STA 268.25
AND STA 360, LEFT SIDE AND DETAILED AND GENERAL VISUAL INSPECTIONS OF THE
SECTION 41 LOWER LOBE FRAMES BETWEEN STA 268.25 AND STA 360, RIGHT SIDE for
any crack.
NOTE: PART 2 HFEC inspections are not required at the 1.0 inch diameter holes in the STA 336
or STA 344 frame web at the repaired location only, provided:
1. The repair is the corrective action for the crack condition at the 1.0 inch diameter
holes identified in this service bulletin and the repair does not re-install any open
hole, AND
2. The installed repair is approved by the Boeing Organization Designation
Authorization (ODA) via a FAA Form 8100-9.
a. CONDITION 1: ANY CRACK FOUND.
(1) CONDITION 1 (ACTION 1): Contact The Boeing Company for repair instructions and do
the repair.
(2) CONDITION 1 (ACTION 2): Repeat PART 2: HIGH FREQUENCY EDDY CURRENT
(HFEC), DETAILED AND GENERAL VISUAL INSPECTIONS OF THE SECTION 41
LOWER LOBE FRAMES BETWEEN STA 268.25 AND STA 360, LEFT SIDE AND
DETAILED AND GENERAL VISUAL INSPECTIONS OF THE SECTION 41 LOWER
LOBE FRAMES BETWEEN STA 268.25 AND STA 360, RIGHT SIDE for any crack at
the time specified in Paragraph 1.E., Compliance.
NOTE: PART 2 HFEC inspections are not required at the 1.0 inch diameter holes in the
STA 336 or STA 344 frame web at the repaired location only, provided:
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1. The repair is the corrective action for the crack condition at the 1.0 inch
diameter holes identified in this service bulletin and the repair does not
re-install any open hole, AND
2. The installed repair is approved by the Boeing Organization Designation
Authorization (ODA) via a FAA Form 8100-9.
b. CONDITION 2: NO CRACK FOUND.
(1) Repeat PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC), DETAILED AND
GENERAL VISUAL INSPECTIONS OF THE SECTION 41 LOWER LOBE FRAMES
BETWEEN STA 268.25 AND STA 360, LEFT SIDE AND DETAILED AND GENERAL
VISUAL INSPECTIONS OF THE SECTION 41 LOWER LOBE FRAMES BETWEEN STA
268.25 AND STA 360, RIGHT SIDE for any crack at the time specified in Paragraph 1.E.,
Compliance.
NOTE: PART 2 HFEC inspections are not required at the 1.0 inch diameter holes in the
STA 336 or STA 344 frame web at the repaired location only, provided:
1. The repair is the corrective action for the crack condition at the 1.0 inch
diameter holes identified in this service bulletin and the repair does not
re-install any open hole, AND
2. The installed repair is approved by the Boeing Organization Designation
Authorization (ODA) via a FAA Form 8100-9.
3. RC - Do PART 3: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE STA
312, STA 328 and STA 344 LOWER LOBE FRAMES, RIGHT SIDE for any crack.
NOTE: PART 3 HFEC inspection is not required at STA 328 frame, if STA 328 was repaired in
accordance with SB 737-53A1323, Accomplishment Instructions 3.B.6.
NOTE: PART 3 HFEC inspections are not required at an open hole in the STA 328 frame web
provided:
1. There is an installed repair that plugs or removes the open hole between stringers
S-20R and S-22R identified in this service bulletin, AND
2. The installed repair is approved by the Boeing Organization Designation
Authorization (ODA) via a FAA Form 8100-9.
a. CONDITION 3: ANY CRACK FOUND.
(1) CONDITION 3 (ACTION 1): Contact The Boeing Company for repair instructions and do
the repair.
(2) CONDITION 3 (ACTION 2): Repeat PART 3: HIGH FREQUENCY EDDY CURRENT
(HFEC) INSPECTIONS OF THE STA 312, STA 328 and STA 344 LOWER LOBE
FRAMES, RIGHT SIDE for any crack at the time specified in Paragraph 1.E., Compliance.
NOTE: PART 3 HFEC inspection is not required at STA 328 frame, if STA 328 was
repaired in accordance with SB 737-53A1323, Accomplishment Instructions
3.B.6.
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ALERTALERT

### Page 33

NOTE: PART 3 HFEC inspections are not required at an open hole in the STA 328
frame web provided:
1. There is an installed repair that plugs or removes the open hole between
stringers S-20R and S-22R identified in this service bulletin, AND
2. The installed repair is approved by the Boeing Organization Designation
Authorization (ODA) via a FAA Form 8100-9.
b. CONDITION 4: NO CRACK FOUND.
(1) Repeat PART 3: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE
STA 312, STA 328 and STA 344 LOWER LOBE FRAMES, RIGHT SIDE for any crack
at the time specified in Paragraph 1.E., Compliance.
NOTE: PART 3 HFEC inspection is not required at STA 328 frame, if STA 328 was
repaired in accordance with SB 737-53A1323, Accomplishment Instructions
3.B.6.
NOTE: PART 3 HFEC inspections are not required at an open hole in the STA 328
frame web provided:
1. There is an installed repair that plugs or removes the open hole between
stringers S-20R and S-22R identified in this service bulletin, AND
2. The installed repair is approved by the Boeing Organization Designation
Authorization (ODA) via a FAA Form 8100-9.
4. Do PART 4: CLOSE ACCESS TO THE SECTION 41 LOWER LOBE FRAMES BETWEEN STA
268.25 AND STA 360, LEFT AND RIGHT SIDE.
5. Put the airplane back to a serviceable condition.
Group 2:
PART 1: GET ACCESS TO THE SECTION 41 LOWER LOBE FRAMES BETWEEN STA 268.25 AND
STA 360, LEFT AND RIGHT SIDE
1. Open the electronic equipment access door to get access to the electronic equipment compartment.
Refer to 737-100/200 AMM 52-48-41 or 737-300/400/500 AMM 52-48-41 as an accepted procedure.
2. Remove and keep the insulation blankets in the electronic equipment compartment to get access
to the forward and aft sides of the frames between STA 268.25 and STA 360. Refer to 737-100/200
AMM 25-51-00 or 737-300/400/500 AMM 25-51-00 as an accepted procedure.
3. Open the forward cargo door to get access to forward cargo compartment. Refer to 737-100/200
AMM 52-31-00 or 737-300/400/500 AMM 52-31-00 as an accepted procedure.
4. Remove and keep forward cargo compartment forward bulkhead lining. Refer to 737-100/200
AMM 25-52-100 or 737-300/400/500 AMM 25-52-81 as an accepted procedure.
Group 2:
PART 2: HIGH FREQUENCY EDDY CURRENT (HFEC), DETAILED AND GENERAL VISUAL
INSPECTIONS OF THE SECTION 41 LOWER LOBE FRAMES BETWEEN STA 268.25 AND STA
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### Page 34

360, LEFT SIDE AND DETAILED AND GENERAL VISUAL INSPECTIONS OF THE LOWER LOBE
FRAMES BETWEEN STA 268.25 AND STA 360, RIGHT SIDE for any crack.
1. Do High Frequency Eddy Current (HFEC), detailed and general visual inspections of the Section
41 lower lobe frames, left side for any crack in accordance with FIGURE 1.
2. Do detailed and general visual inspections of the Section 41 lower lobe frames, right side for any
crack in accordance with FIGURE 2.
Group 2:
PART 3: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE STA 312, STA 328
AND STA 344 LOWER LOBE FRAMES, RIGHT SIDE for any crack.
1. Do a High Frequency Eddy Current (HFEC) inspection of the STA 312, STA 328 and STA 344
lower lobe frames, right side for any crack in accordance with FIGURE 3.
NOTE: PART 3 HFEC inspection is not required at STA 328 frame, if STA 328 was repaired in
accordance with SB 737-53A1323, Accomplishment Instructions 3.B.6.
NOTE: PART 3 HFEC inspections are not required at an open hole in the STA 328 frame web
provided:
1. There is an installed repair that plugs or removes the open hole between stringers
S-20R and S-22R identified in this service bulletin, AND
2. The installed repair is approved by the Boeing Organization Designation
Authorization (ODA) via a FAA Form 8100-9.
Group 2:
PART 4: CLOSE ACCESS TO SECTION 41 LOWER LOBE FRAMES BETWEEN STA 268.25 AND
STA 360, LEFT AND RIGHT SIDE
1. Install the kept forward cargo compartment forward bulkhead lining. Refer to 737-100/200 AMM
25-52-100 or 737-300/400/500 AMM 25-52-81 as an accepted procedure.
2. Close the forward cargo compartment access door. Refer to 737-100/200 AMM 52-31-00 or
737-300/400/500 AMM 52-31-00 as an accepted procedure.
3. Install the kept insulation blankets in the electronic equipment compartment to the forward and aft
frames between STA 268.25 and STA 360. Refer to 737-100/200 AMM 25-51-00 or 737-300/400/500
AMM 25-51-00 as an accepted procedure.
4. Close the electronic equipment access door to the electronic equipment compartment. Refer to
737-100/200 AMM 52-48-41 or 737-300/400/500 AMM 52-48-41 as an accepted procedure.
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ALERTALERT

### Page 35 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
This Figure applies only to: Group 2.
STA
294.5
AIRSTAIR CUTOUT IS
OPTIONAL
S-17L
STA
EWD  268.25 STA
259.5
STA  STA
259.5  285.62 STA
STA
277  STA  BL-O  STA
312 STA  STA  360  STA  294.5
344  380
S-17L
S-18L
S-19L
S-20L -
S-21L -
S-221 -
S-23L
S-24L -
S-25L
S-26L
LBL 16.0
INSPECTION ZONE  2501494
FIGURE 1: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES LEFT SIDE FOR ANY CRACK
(SHEET 1 OF 7)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
STA
OPTIONAL AIRSTAIR  303.9
CUTOUT
STA
STA  320
330.62
STA  STA
S-17L  344  STA  325.38
336
S-18L
S-19L'
S-20L
WL 181.37
S-21L
S-22L
S-23L
S-24L
STA
294.5
S-25L
S-26L  STA  312
STA
S-27L  323.7
S-28L
INSPECTION ZONE
STA
LBLO  STA  351.2
360
2484356
FIGURE 1: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES LEFT SIDE FOR ANY CRACK
(SHEET 2 OF 7)
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
FRAME WEB
LBL
45.48
S-22L
1.0 INCH DIAMETER HOLE
WL
169.6
LBL
40
1.0 INCH DIAMETER HOLE
CRACK
(TYPICAL)
S-23L  WL
164.85
CRACK
(TYPICAL)
HFEC INSPECTION ZONE
S-24L
INBD
STA 344 FRAME WEB SYSTEM PENETRATION HOLES
(VIEW LOOKING FWD)  A-A  2501503
FIGURE 1: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES LEFT SIDE FOR ANY CRACK
(SHEET 3 OF 7)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
FRAME WEB
• LBL
44.36
S-22L  1.0 INCH DIAMETER HOLE
WL
169.02
S-23L
HFEC INSPECTION ZONE
INBD
STA 336 FRAME WEB SYSTEM PENETRATION HOLE
(VIEW LOOKING FWD)
B-B  2501502
FIGURE 1: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES LEFT SIDE FOR ANY CRACK
(SHEET 4 OF 7)
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### Page 39 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
STRINGER CLIP
FRAME WEB
FRAME INTEGRAL
SHEAR TIE
- STRINGER
FRAME INTEGRAL
SHEAR TIE
INBD
HFEC INSPECTION ZONE
STA 360 FRAME STRINGER CUTOUT AT S-24L
(VIEW LOOKING AFT)
C-C
2501504
FIGURE 1: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES LEFT SIDE FOR ANY CRACK
(SHEET 5 OF 7)
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### Page 40

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a) (b) (g) (h)1STA 294.5, S-17L TO
BL-0
BULKHEAD FRAMEInspect1
(b) (c) (g) (h)1STA 268.25, S-23L TO
LBL 16.0
FRAMEInspect2
(b) (c) (g) (h)1STA 277, S-17L TO
LBL 16.0
FRAMEInspect
(b) (c) (g) (h)1STA 285.62, S-23L TO
LBL 16.0
FRAMEInspect
(b) (c) (g) (h)1STA 303.9, S-17L TO
S-23L
FRAMEInspect
(b) (c) (g) (h)1STA 312, WL 181.37
TO BL-0
FRAMEInspect
(b) (c) (g) (h)1STA 320, WL 181.37
TO S-23L
FRAMEInspect
(b) (c) (g) (h)1STA 323.7, S-26L TO
BL-0
FRAMEInspect
(b) (c) (g) (h)1STA 325.38, WL
181.37 TO S-28L
FRAMEInspect
(b) (c) (g) (h)1STA 330.62, WL
181.37 TO S-28L
FRAMEInspect
(b) (c) (g) (h)1STA 336, WL 181.37
TO S-23L
FRAMEInspect
(b) (c) (g) (h)1STA 344, WL 181.37
TO S-28L
FRAMEInspect
(b) (c) (g) (h)1STA 351.2, S-17L TO
S-23L
FRAMEInspect
(b) (c) (g) (h)1STA 351.2, S-26L TO
BL-0
FRAMEInspect
(b) (c) (g) (h)1STA 360, S-17L TO BL-
0
FRAMEInspect
(d) (i)1STA 344, S-22L TO S-
24L
FRAME WEBInspect3
(e) (i)1STA 336, S-22L TO S-
23L
FRAME WEBInspect4
(f)1STA 360, S-24LFRAME WEBInspect5
FIGURE 1: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES LEFT SIDE FOR ANY CRACK
(SHEET 6 OF 7)
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ALERTALERT

### Page 41

More DataQtyIdentificationNameTaskStep
(a) Do a general visual inspection of the bulkhead frame web from the forward and aft side for any crack.
Inspect around all open hole locations, at all stringer cutout locations and at all fastener attachments in-
cluding at the failsafe chord, shear ties and stringer clips. Do a general visual inspection of the frame inboard
chord, integral inboard chord and failsafe chord for any crack.
(b) Do a general visual inspection of the frame shear ties and integral shear ties for any crack. Inspect the
bend radius and all fastener attachment locations.
(c) Do a detailed inspection of the frame web from the forward and aft side for any crack. Inspect around all
open hole locations, at all stringer cutout locations and at all fastener attachments including at the failsafe
chord, shear ties and stringer clips. Do a detailed inspection of the frame inboard chord, integral inboard
chord and failsafe chord for any crack.
(d) Do a surface HFEC inspection of the frame web around the edge of the 1.0 inch diameter system pene-
tration hole from the aft side for any crack in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure
4 or 737 NDT Manual Part 6, 51-00-00, Procedure 23.
(e) Do a surface HFEC inspection of the frame web around the edge of the 1.0 inch diameter system pene-
tration hole from the forward side for any crack in accordance with 737 NDT Manual Part 6, 51-00-00,
Procedure 4 or 737 NDT Manual Part 6, 51-00-00, Procedure 23.
(f) Do a surface HFEC inspection of the frame web at the stringer cutout on both sides of the stringer clip.
Inspect the frame web from the forward side for any crack in accordance with 737 NDT Manual Part 6,
51-00-00, Procedure 4 or 737 NDT Manual Part 6, 51-00-00, Procedure 23.
(g) Refer to APPENDIX C for typical frame construction and component identification.
(h) If structure, existing repairs, or systems hardware attached to the frame covers a structural detail that is
to be inspected, then it is only necessary to inspect the area of the structural detail that is visible. It is not
necessary to remove structure, existing repairs, or systems hardware attached to the frame to do the in-
spection.
(i) PART 2 HFEC inspections are not required at the 1.0 inch diameter holes in the STA 336 or STA 344
frame web at the repaired location only, provided:
1. The repair is the corrective action for the crack condition at the 1.0 inch diameter holes identified
in this service bulletin and the repair does not re-install any open hole, AND
2. The installed repair is approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
FIGURE 1: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES LEFT SIDE FOR ANY CRACK
(SHEET 7 OF 7)
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ALERTALERT

### Page 42 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
This Figure applies only to: Group 2.
STA
294.5
S-17R
259.5  STA 268.25  STA  259.5  STA
SIA  277  285.62  STA  BL-O  STA  STA  277
360  STA
294.5  STA  STA STA 312
380  344
S-17R
S-18R
• S- 19R
• S-20R
— S-21R
S-22R
S-23R
~ S-24R
S-25R
S-26R
RBL 16.0
INSPECTION ZONE  2501507
FIGURE 2: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 1 OF 4)
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### Page 43 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
SIA
294.5
SIA  312  STA  328
STA
332.1
STA
344
STA
360
- S-17R
-S-18R
S-19R
S-20R
S-21R
S-22R
S-23R
• S-24R
• S-25R
STA
323.7  • S-26R
• S-27R
STA  S-28R
351.2  LBLO
INSPECTION ZONE
2501508
FIGURE 2: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 2 OF 4)
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### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a) (b) (d) (e)1STA 294.5, S-17R TO
BL-0
BULKHEAD FRAMEInspect1
(b) (c) (d) (e)1STA 268.25, S-23R TO
RBL 16.0
FRAMEInspect2
(b) (c) (d) (e)1STA 277, S-17R TO
RBL 16.0
FRAMEInspect
(b) (c) (d) (e)1STA 285.62, S-23R TO
RBL 16.0
FRAMEInspect
(b) (c) (d) (e)1STA 312, S-17R TO
BL-0
FRAMEInspect
(b) (c) (d) (e)1STA 323.7, S-25R TO
BL-0
FRAMEInspect
(b) (c) (d) (e) (f)1STA 328, S-17R TO S-
27R
FRAMEInspect
(b) (c) (d) (e)1STA 332.1, S-17R TO
S-19R
FRAMEInspect
(b) (c) (d) (e) (f)1STA 344, S-17R TO S-
27R
FRAMEInspect
(b) (c) (d) (e)1STA 351.2, S-25R TO
BL-0
FRAMEInspect
(b) (c) (d) (e)1STA 360, S-17R TO
BL-0
FRAMEInspect
(a) Do a general visual inspection of the bulkhead frame web from the forward and aft side for any crack.
Inspect around all open hole locations, at all stringer cutout locations and at all fastener attachments in-
cluding at the failsafe chord, shear ties and stringer clips. Do a general visual inspection of the frame inboard
chord, integral inboard chord and failsafe chord for any crack.
(b) Do a general visual inspection of the frame shear ties and integral shear ties for any crack. Inspect the
bend radius and all fastener attachment locations.
(c) Do a detailed inspection of the frame web from the forward and aft side for any crack. Inspect around all
open hole locations, at all stringer cutout locations and at all fastener attachments including at the failsafe
chord, shear ties and stringer clips. Do a detailed inspection of the frame inboard chord, integral inboard
chord and failsafe chord for any crack.
(d) Refer to APPENDIX C for typical frame construction and component identification.
(e) If structure, existing repairs, or systems hardware attached to the frame covers a structural detail that is
to be inspected, then it is only necessary to inspect the area of the structural detail that is visible. It is not
necessary to remove structure, existing repairs, or systems hardware attached to the frame to do the in-
spection.
FIGURE 2: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 3 OF 4)
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BOEING SERVICE BULLETIN 737-53A1354
ALERTALERT

### Page 45

More DataQtyIdentificationNameTaskStep
(f) Inspect the joggle in the frame inboard chord below S-26R.
FIGURE 2: INSPECTION OF THE SECTION 41 LOWER LOBE FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 4 OF 4)
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ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
This Figure applies only to: Group 2.
STA
294.5
S-18R
S-19R
S-22R
STA
294.5
STA  BL-O  STA  360  ISTA
328  STA  STA  312
332.1  STA
STA  344  328
STA
360
S-18R
- S-19R
S-20R
S-21R
S-22R
→523R
~ S-24R
S-25R
STA
323.7  ' S-26R
' S-27R
351.2  STA  • S-28R  2501512
• RBL O
FIGURE 3: HFEC INSPECTION OF THE STA 312, STA 328 AND STA 344 SECTION 41 LOWER LOBE
FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 1 OF 8)
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
S-19R
INSULATION ATTACHMENT HOLES
(HOLE LOCATIONS ARE
APPROXIMATE)
S-20R
× <
STRAP
ELECTRICAL
RACEWAY  FRAME
WEB
S-21R
1 TOOLING HOLE
ELECTRICAL RACEWAY
SUPPORT BRACKET
LOWER
FRAME
WEB  INBD
S-22R
STA 312
(VIEW LOOKING FORWARD)  A-A  2501513
FIGURE 3: HFEC INSPECTION OF THE STA 312, STA 328 AND STA 344 SECTION 41 LOWER LOBE
FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 2 OF 8)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
FASTENER
(TYPICAL)
ELECTRICAL
RACEWAY  3 EDGE OF
SUPPORT  ELECTRICAI
BRACKET  RACEWAY
SUPPORT
BRACKET
FRAME
WEB
LOWER
FRAME
WEB
HFEC INSPECTION ZONE  INBD
STA 312
(VIEW LOOKING FORWARD)
2501516
FIGURE 3: HFEC INSPECTION OF THE STA 312, STA 328 AND STA 344 SECTION 41 LOWER LOBE
FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 3 OF 8)
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### Page 49 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
S-19R
STRAP
• S-20R
ECS
DUCT
FRAME
WEB
INSULATION ATTACHMENT HOLES
(HOLE LOCATIONS ARE
TOOLING HOLE 5  APPROXIMATE)
ELECTRICAL  S-21R
RACEWAY
AUXILIARY ECS SUPPORT BRACKET
(BRACKET MAY NOT BE INSTALLED)
ELECTRICAL RACEWAY
SUPPORT BRACKET
INBD
S-22R
HFEC INSPECTION ZONE  (VIEW LOOKING FORWARD)  STA 328  2501517
B-B
FIGURE 3: HFEC INSPECTION OF THE STA 312, STA 328 AND STA 344 SECTION 41 LOWER LOBE
FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 4 OF 8)
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### Page 50 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
— S-19R
ECS
DUCT  — S-20R
FRAME
WEB
STRAP
ELECTRICAL
RACEWAY  S-21R
6) (HOLE LOCATIONS AR  INSULATION ATTACHMENT HOLE
ELECTRICAL RACEWAY  APPROXIMATE)
SUPPORT BRACKET
LOWER
FRAME
WEB
S-22R
INBD
STA 344
(VIEW LOOKING FORWARD)
C-C  2501518
FIGURE 3: HFEC INSPECTION OF THE STA 312, STA 328 AND STA 344 SECTION 41 LOWER LOBE
FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 5 OF 8)
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### Page 51 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
FASTENER
(TYPICAL)
ELECTRICAL RACEWAY
SUPPORT BRACKET
1 TOOLING HOLE
0.1 INCH
(TYPICAL)
' LOWER FRAME
WEB
• FRAME WEB
EDGE OF ELECTRICAL
RACEWAY SUPPORT
HFEC INSPECTION ZONE  BRACKET
INBD
STA 344
(VIEW LOOKING FORWARD)
2501519
FIGURE 3: HFEC INSPECTION OF THE STA 312, STA 328 AND STA 344 SECTION 41 LOWER LOBE
FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 6 OF 8)
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### Page 52

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)1STA 312, S-19R TO S-
22R
FRAME WEBInspect1
(b)1STA 312, S-21R TO S-
22R
FRAME WEBInspect2
(c)1STA 312, S-21R TO S-
22R
FRAME WEBInspect3
(a) (e) (f)1STA 328, S-20R TO S-
22R
FRAME WEBInspect4
(d) (e) (f)1STA 328, S-21R TO S-
22R
FRAME WEBInspect5
(a)1STA 344, S-20R TO S-
22R
FRAME WEBInspect6
(d)1STA 344, S-21R TO S-
22R
FRAME WEBInspect7
(b)1STA 344, S-21R TO S-
22R
FRAME WEBInspect8
(c)1STA 344, S-21R TO S-
22R
FRAME WEBInspect9
(a) Do an open hole High Frequency Eddy Current (HFEC) inspection at the insulation attachment holes
between S-19R and S-22R for any crack in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure
1, or 737 NDT Manual Part 6, 51-00-00, Procedure 11 or 737 NDT Manual Part 6, 51-00-00, Procedure
16. A typical tooling hole has a 0.247 - 0.260 inch diameter. A typical insulation blanket attachment hole
has a 0.154 - 0.166 inch diameter or 0.180 - 0.192 inch diameter. The location and quantity of insulation
attachment holes may vary.
(b) Do a surface HFEC inspection of the lower frame web for any crack around the fastener in accordance
with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 737 NDT Manual Part 6, 51-00-00, Procedure
23.
(c) Do a surface HFEC inspection of the lower frame web for any crack along the electrical raceway support
bracket in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 737 NDT Manual Part 6,
51-00-00, Procedure 23.
(d) Do a surface HFEC inspection of the frame web for any crack around the tooling hole from the forward
side in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 737 NDT Manual Part 6, 51-
00-00, Procedure 23.
(e) PART 3 HFEC inspection is not required at STA 328 frame, if STA 328 was repaired in accordance with
SB 737-53A1323, Accomplishment Instructions 3.B.6.
FIGURE 3: HFEC INSPECTION OF THE STA 312, STA 328 AND STA 344 SECTION 41 LOWER LOBE
FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 7 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 02, 2016
737-53A1354
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BOEING SERVICE BULLETIN 737-53A1354
ALERTALERT

### Page 53

More DataQtyIdentificationNameTaskStep
(f) PART 3 HFEC inspections are not required at an open hole in the STA 328 frame web provided:
1. There is an installed repair that plugs or removes the open hole between stringers S-20R and
S-22R identified in this service bulletin, AND
2. The installed repair is approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
FIGURE 3: HFEC INSPECTION OF THE STA 312, STA 328 AND STA 344 SECTION 41 LOWER LOBE
FRAMES RIGHT SIDE FOR ANY CRACK
(SHEET 8 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 02, 2016
737-53A1354
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BOEING SERVICE BULLETIN 737-53A1354
ALERTALERT

### Page 54

This Appendix applies only to: Group 2.
Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
HIGH FREQUENCY EDDY CURRENT (HFEC), DETAILED AND GENERAL
VISUAL INSPECTIONS OF THE SECTION 41 LOWER LOBE FRAMES
BETWEEN STA 268.25 AND STA 360, LEFT SIDE AND DETAILED AND
GENERAL VISUAL INSPECTIONS OF THE SECTION 41 LOWER LOBE
FRAMES BETWEEN STA 268.25 AND STA 360, RIGHT SIDE for any crack.
PART 2
ANY CRACK FOUND.CONDITION 1
NO CRACK FOUND.CONDITION 2
(a) PART 2 HFEC inspections are not required at the 1.0 inch diameter holes in the STA 336 or STA 344
frame web at the repaired location only, provided:
1. The repair is the corrective action for the crack condition at the 1.0 inch diameter holes identified
in this service bulletin and the repair does not re-install any open hole, AND
2. The installed repair is approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
APPENDIX A:  LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE, TABLE 1: INSPECTION FOR ANY
CRACK IN THE SECTION 41 LOWER LOBE FRAMES, LEFT AND RIGHT SIDE
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: December 02, 2016
737-53A1354
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BOEING SERVICE BULLETIN 737-53A1354
ALERTALERT

### Page 55 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
WHICHEVER OCCURS LATER
WITHIN 4,500 FLIGHT
BEFORE 35,000 TOTAL  FLIGHT CYCLES  CYCLES AFTER THE  ORIGINAL ISSUE DATE  OF THIS SERVICE
BULLETIN
(a) → DO PART 2
CONDITION 1  CONDITION 2
BEFORE FURTHER  NOT TO EXCEED 12,000
FLIGHT  FLIGHT CYCLES
ACTION 1:
CONTACT THE BOEING  a)  › REPEAT PART 2
COMPANY FOR THE
REPAIR INSTRUCTIONS
AND DO THE REPAIR
NOT TO EXCEED 12,000
FLIGHT CYCLES
(a)
ACTION 2:
REPEAT PART 2
INSPECTIONS OF THE
SECTION 41 LOWER LOBE
FRAMES FOR ANY CRACK
2501490
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE, TABLE 1: INSPECTION FOR ANY
CRACK IN THE SECTION 41 LOWER LOBE FRAMES, LEFT AND RIGHT SIDE
(SHEET 2 OF 2)
Original Issue: December 02, 2016
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### Page 56

This Appendix applies only to: Group 2.
Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE STA
312, STA 328 AND STA 344 LOWER LOBE FRAMES, RIGHT SIDE ONLY
for any crack.
PART 3
ANY CRACK FOUND.CONDITION 3
NO CRACK FOUND.CONDITION 4
(a) PART 3 HFEC inspection is not required at STA 328 frame, if STA 328 was repaired in accordance with
SB 737-53A1323, Accomplishment Instructions 3.B.6.
(b) PART 3 HFEC inspections are not required at an open hole in the STA 328 frame web provided:
1. There is an installed repair that plugs or removes the open hole between stringers S-20R and
S-22R identified in this service bulletin, AND
2. The installed repair is approved by the Boeing Organization Designation Authorization (ODA)
via a FAA Form 8100-9.
APPENDIX B:  LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE, TABLE 2: INSPECTION FOR ANY
CRACK IN THE STA 312, STA 328 AND STA 344 LOWER LOBE FRAMES, RIGHT SIDE ONLY
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: December 02, 2016
737-53A1354
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BOEING SERVICE BULLETIN 737-53A1354
ALERTALERT

### Page 57 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
WHICHEVER OCCURS LATER
WITHIN 4,500 FLIGHT
FLIGHT CYCLES  BEFORE 35,000 TOTAL  CYCLES AFTER THE  ORIGINAL ISSUE DATE  OF THIS SERVICE
BULLETIN
(a)
DO PART 3
CONDITION 3  CONDITION 4
BEFORE FURTHER  NOT TO EXCEED 4,500
FLIGHT  FLIGHT CYCLES
CONTACT THE BOEING  ACTION 1:  - (b
COMPANY FOR THE  REPEAT PART 3
REPAIR INSTRUCTIONS
AND DO THE REPAIF
NOT TO EXCEED 4,500
FLIGHT CYCLES
a)  (b)
ACTION 2:
REPEAT PART 3
INSPECTIONS OF THE
SECTION 41 LOWER LOBE
FRAMES FOR ANY CRACK
2501491
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE, TABLE 2: INSPECTION FOR ANY
CRACK IN THE STA 312, STA 328 AND STA 344 LOWER LOBE FRAMES, RIGHT SIDE ONLY
(SHEET 2 OF 2)
Original Issue: December 02, 2016
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-53A1354
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### Page 58 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
This Appendix applies only to: Group 2.
• S-18R
FRAME
DOUBLER _
— *
1$19R
INSULATION
ATTACHMENT
HOLE
FRAME INTEGRAL  7в
INBOARD CHORD
FAILSAFE CHORD  SHEAR TIE
TOOLING HOLE
S-20R
STRINGER CUTOUT
FRAME
WEB  FRAME INTEGRAL
SHEAR TIE
INBD
• STRINGER CLIP
S-21R
STA 360  2501492
(VIEW LOOKING FWD)
APPENDIX C: TYPICAL FRAME CONSTRUCTION AND COMPONENT IDENTIFICATION
(SHEET 1 OF 2)
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### Page 59 (OCR)

BOEING SERVICE BULLETIN 737-53A1354
ALERT  ALERT
FRAME INTEGRAL
INBOARD CHORD
INBOARD
FRAME WEB  CHORD
FRAME WEB
FAILSAFE
CHORD'
BEND
RADIUS
BEND  FAILSAFE
RADIUS  CHORD
SHEAR TIE
-WD
FRAME INTEGRAL SHEAR TIE
(SKIN ATTACHMENT FLANGE)
STA 360 AND ALL
STA 360  OTHER FRAME LOCATIONS
WITH SEPARATE SHEAR TIE
AND INBOARD CHORD
A-A  B-B
2501493
APPENDIX C: TYPICAL FRAME CONSTRUCTION AND COMPONENT IDENTIFICATION
(SHEET 2 OF 2)
Original Issue: December 02, 2016
Export Controlled ECCN: 9E991 - BOEING  737-53A1354
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  59 of 59

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