# Boeing Alert Service Bulletin 757-53A0108: Revision 1

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- Document: [Boeing Alert Service Bulletin 757-53A0108](https://openairdocs.org/service-documents/boeing/757-53a0108.md)
- Title as filed: SB-757-53A0108-01--BOEING
- Pages: 252
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## Text

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### Page 1

Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-53A0108
Original Issue: November 14, 2016
Revision 1: July 17, 2019
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Body Station 1640 Fuselage Frame Inspection
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 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Unpublished Work.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: November 14, 2016
757-53A0108Revision 1: July 17, 2019
1 of 252
3.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
S u m m a r y  ...................................................... 9
1. PLANNING INFORMATION ........................................ 1 3
A . E f f e c t i v i t y  ............................................... 1 3
1. Airplanes ............................................ 1 3
2 . S p a r e s  A f f e c t e d  ........................................ 1 8
B. Concurrent Requirements ...................................... 1 9
C. Reason ................................................ 1 9
D. Description .............................................. 2 0
E. Compliance .............................................. 2 1
F . A p p r o v a l  ............................................... 8 6
G. Manpower .............................................. 8 7
H. Weight and Balance Changes .................................... 8 8
I. Electrical Load Data ......................................... 8 8
J . R e f e r e n c e s  .............................................. 8 9
1. Existing Data: ......................................... 8 9
2. Data Supplied with this Service Bulletin: ........................... 8 9
3. Installation Drawings Used in the Preparation of this Service  Bulletin: ........... 8 9
K. Publications Affected ........................................ 9 0
L. Interchangeability and Intermixability of Parts ........................... 9 0
M. Software Accomplishment Summary ................................ 9 0
2. MATERIAL INFORMATION ........................................ 9 1
A. Material - Price and Availability ................................... 9 1
B. Industry Support Information .................................... 9 1
C. Parts Necessary for Each Airplane ................................. 9 1
1 . K i t s / P a r t s  ............................................ 9 1
2. Parts and Materials Supplied by the Operator ........................ 9 1
3. Parts Modified and Reidentified ................................ 9 1
4. Parts Removed and Not Replaced .............................. 9 1
D. Parts Necessary to Change Spares ................................. 9 1
E. Special Tooling - Price and Availability ............................... 9 1
F. Special Tooling Necessary to do this Service Bulletin ....................... 9 1
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 9 3
A. GENERAL INFORMATION ..................................... 9 3
B. WORK INSTRUCTIONS ....................................... 9 6
FIGURE 1: LEFT SIDE - STA 1640 FUSELAGE FRAME AT STRINGER S-14 A ND LOWER HINGE
INTERCOSTAL HFEC AND LFEC INSPECTION [Group 1-3] ............... 1 0 7
FIGURE 2: RIGHT SIDE - STA 1640 FUSELAGE FRAME AT STRINGER S-14 AND LOWER HINGE
INTERCOSTAL - HFEC AND LFEC INSPECTION [Group 1-3] .............. 1 1 2
FIGURE 3: LEFT SIDE - STA 1640 FUSELAGE FRAME AT STRINGER S-14 A ND LOWER HINGE
INTERCOSTAL - HFEC INSPECTION [Group 1-3] ..................... 1 1 7
FIGURE 4: RIGHT SIDE - STA 1640 FUSELAGE FRAME AT STRINGER S-14 AND LOWER HINGE
INTERCOSTAL - HFEC INSPECTION [Group 1-3] ..................... 1 2 1
FIGURE 5: LEFT SIDE - STA 1640 FUSELAGE FRAME AT STRINGER S-11 A ND S-13 INTERCOSTAL
AREAS - HFEC INSPECTION [Group 1-3] ......................... 1 2 5
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FIGURE 6: RIGHT SIDE - STA 1640 FUSELAGE FRAME AT STRINGER S-11 AND S-13 INTERCOSTAL
AREAS - HFEC INSPECTION [Group 1-3] ......................... 1 2 9
FIGURE 7: LEFT SIDE - STA 1640 FUSELAGE FRAME AT STRINGER S-14 I NTERCOSTAL AREA -
HFEC AND LFEC INSPECTION [Group 4-5] ........................ 1 3 3
FIGURE 8: RIGHT SIDE - STA 1640 FUSELAGE FRAME AT STRINGER S-14 INTERCOSTAL AREA -
HFEC AND LFEC INSPECTION [Group 4-5] ........................ 1 3 7
FIGURE 9: LEFT SIDE - STA 1640 FUSELAGE FRAME AT STRINGER S-14 I NTERCOSTAL AREA -
HFEC INSPECTION [Group 4-5] ............................... 1 4 1
FIGURE 10: RIGHT SIDE - STA 1640 FUSELAGE FRAME AT STRINGER S-14  INTERCOSTAL AREA -
HFEC INSPECTION [Group 4-5] ............................... 1 4 5
FIGURE 11: LEFT SIDE - STA 1640 FUSELAGE FRAME AT LOWER HINGE INTERCOSTAL, STRINGERS
S-11 AND S-13 - HFEC INSPECTION [Group 4-5] ..................... 1 4 9
FIGURE 12: RIGHT SIDE - STA 1640 FUSELAGE FRAME AT LOWER HINGE INTERCOSTAL, STRINGERS
S-11 AND S-13 - HFEC INSPECTION [Group 4-5] ..................... 1 5 4
FIGURE 13: LEFT SIDE - STA 1640 FUSELAGE FRAME INNER CHORD - DETAILED INSPECTION . 159
FIGURE 14: RIGHT SIDE - STA 1640 FUSELAGE FRAME INNER CHORD - DETAILED INSPECTION . 161
FIGURE 15: LEFT SIDE - STA 1640 FUSELAGE FRAME INNER CHORD FASTENER HOLES AND FLANGE
RADIUS - HFEC INSPECTION ............................... 1 6 3
FIGURE 16: RIGHT SIDE - STA 1640 FUSELAGE FRAME INNER CHORD FAST ENER HOLES AND
FLANGE RADIUS - HFEC INSPECTION .......................... 1 6 7
FIGURE 17: LEFT SIDE - STA 1640 FUSELAGE FRAME INNER CHORD FASTE NER HOLES - HFEC
INSPECTION [Group 1-3] .................................. 1 7 1
FIGURE 18: RIGHT SIDE - STA 1640 FUSELAGE FRAME INNER CHORD FAST ENER HOLES - HFEC
INSPECTION [Group 1-3] .................................. 1 7 4
FIGURE 19: LEFT SIDE - STA 1640 FUSELAGE FRAME INNER CHORD FASTE NER HOLES - HFEC
INSPECTION [Group 4-5] .................................. 1 7 7
FIGURE 20: RIGHT SIDE - STA 1640 FUSELAGE FRAME INNER CHORD FAST ENER HOLES - HFEC
INSPECTION [Group 4-5] .................................. 1 8 0
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 2 [Group 1, Configuration
1 - 2 ]  ............................................... 1 8 3
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 3 [Group 1, Configuration
3 ]  ................................................ 1 9 0
APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 4 [Group 2, Configuration
1 ]  ................................................ 1 9 7
APPENDIX D: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 5 [Group 2, Configuration
2 ]  ................................................ 2 0 4
APPENDIX E: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 6 [Group 3, Configuration
1 - 2 ]  ............................................... 2 1 1
APPENDIX F: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 7 [Group 3, Configuration
3 ]  ................................................ 2 1 8
APPENDIX G: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 8 [Group 4, Configuration
1 ]  ................................................ 2 2 5
APPENDIX H: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 9 [Group 4, Configuration
2 ]  ................................................ 2 3 2
APPENDIX I: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 10 [Group 5, Configuration
1 ]  ................................................ 2 3 9
APPENDIX J: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 11 [Group 5, Configuration
2 ]  ................................................ 2 4 6
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Commercial 
Airplanes
757
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 757-53A0108Original Issue: November 14, 2016
Revision 1: July 17, 2019
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Body Station 1640 Fuselage Frame Inspection
This revision includes all pages of the service bulletin.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2018-06-07 is related to this service bulletin.
Effects of this Revision on airplanes on which Original Issue was previously done:
ActionConditionGroup
Do PART 6 inspection for any crack,
nick or gouge.
Airplanes that have accomplished OPTION 1 PART 2 in-
spections in Service Bulletin 757-53A0108 Original Issue
with no crack found.
Groups 1-5
Do PART 2, PART 7 and PART 8
inspection for any crack.
Do PART 6 inspection for any crack,
nick or gouge.
Airplanes that have accomplished OPTION 2 PART 3 in-
spections in Service Bulletin 757-53A0108 Original Issue
with no crack found. Do PART 3, PART 7 and PART 8
inspections for any crack.
Do PART 6 inspection for any crack,
nick or gouge.
Airplanes that have accomplished the inspections in accor-
dance with Service Bulletin 757-53A0108 Original Issue
and have installed a repair or local frame replacement that
does not contain a reinforcement repair or repair splice
member between S-11 and S-16 and the repair or replace-
ment is Boeing Organization Designation Authorization
(ODA) approved via an FAA form 8100-9.
Do PART 2, PART 7 and PART 8
inspections for any crack.
OR
Do PART 3, PART 7 and PART 8
inspections for any crack.
Contact The Boeing Company for
alternative inspection(s) and do the
inspection(s) and any corrective ac-
tions as applicable.
Airplanes that have accomplished the inspections in accor-
dance with Service Bulletin 757-53A0108 Original Issue
and have installed a repair or local frame replacement that
contains a reinforcement repair or repair splice member
between S-11 and S-16.
Contact The Boeing Company for
alternative inspection(s) and do the
inspection(s) and any corrective ac-
tions as applicable.
Airplanes that have accomplished the inspections in accor-
dance with Service Bulletin 757-53A0108 Original Issue
and have installed a repair or local frame replacement that
is not Boeing Organization Designation Authorization (ODA)
approved.
REASON FOR REVISION
This revision is sent to provide the following:
– Added a reference to Airworthiness Directive AD 2018-06-07
– Added new instructions to do a one time inspection of maintena nce records for any repairs or local frame
replacements installed as a result of damage found during inspections in the original issue of service bulletin
757-53A0108.
– Added a one time Detailed Inspection of the frame inner chord forward return flange edge for cracks, nicks
and gouges.
– Added initial and repetitive High Frequency Eddy Current (HFEC ) inspections around the fasteners of the
frame inner chord, and of the inner chord forward return flange radius.
– Changed Low Frequency Eddy Current (LFEC) inspections for six fasteners in the inner chord from LFEC
to HFEC inspections, and the inspection direction is changed from the outboard side of the frame inner
chord to the inboard side of the frame inner chord.
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– Added LFEC inspections of the frame inner chord around the upp ermost fastener common to the frame
inner chord long strap (Groups 1-3)
These sections were changed:
1. Summary, Illustration, added new detailed and HFEC inspection s.
2. In Paragraph 1.A., Effectivity, updated paragraph that lists airplane minor models, line numbers and
groups.
3. In Paragraph 1.C., Reason, updated paragraph to add new crack  information and reason for revision
statement added.
4. In Paragraph 1.D., Description, added more work table and new  paragraph that includes the new
Detailed and HFEC inspections.
5. In Paragraph 1.E., Compliance, changed existing compliance Ta bles 1-7, added new Tables 8-11,
added Part - Title Index table, and added paragraph to reference Airworthiness Directive (AD).
6. In Paragraph 1.F., Approval, added new AMOC statement.
7. In Paragraph 1.G., Manpower, added manpower for figures 13-18  for Groups 1-3 and figures 13-16
and Figures 19-20 for Groups 4-5.
8. In Paragraph 1.J., References, Airworthiness Directive AD 2018-06-07, Boeing Service Related Problem
757-SRP-53-0594 and Multi-Operator Message MOM-MOM-17-0037-01C.
9. In Paragraph 3.A., General Information, added notes 18 and 19 , and changed notes 9 and 10.
10. In Paragraph 3.B., Work Instructions, Changed existing Part 2 and Part 3 inspections, added new Part
6 detailed inspection and Part 7 and Part 8 HFEC inspections.
11. In Paragraph 3.B., Work Instructions, changed the inspection  areas in Figures 1, 2.
12. In Paragraph 3.B., Work Instructions, removed the HFEC inspe ction from Figures 7, 8.
13. In Paragraph 3.B., Work Instructions, added Figures 13 and 14 for the new Part 6 detailed inspection.
14. In Paragraph 3.B., Work Instructions, added Figures 15 and 1 6 for the new Part 7 HFEC inspections.
15. In Paragraph 3.B., Work Instructions, added Figures 17, 18, 19, 20, for the new Part 8 HFEC inspections.
16. In Appendices A to G, updated logic diagram to incorporate c hanges in the associated Compliance
Tables.
17. In Appendices H, I and J, new logic diagrams added for Compl iance Tables 9, 10 and 11.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
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REVISION HISTORY
November 14, 2016Original Issue:
July 17, 2019Revision 1:
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### Page 9

Commercial 
Airplanes
757
Service Bulletin
ALERT
SummaryNumber: 757-53A0108Original Issue: November 14, 2016
Revision 1: July 17, 2019
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Body Station 1640 Fuselage Frame Inspection
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 provide instructions to do High Frequency Eddy Current (HFEC) and Low Frequency
Eddy Current (LFEC) inspections for any crack in the fuselage frame at Body Station (STA) 1640, between
stringers S-11 and S-16, on the left and right side of the airplane. If the work given in this service bulletin is not
done, such fatigue cracking could adversely affect the structural integrity of the airplane.
One operator reported a crack finding, at 24,607 total flight cycles, in the STA 1640 fuselage frame at stringer
S-14R, adjacent to door stop number 5. The crack had fully severed the inner chord and web of the STA 1640
fuselage frame. The cracking is attributed to fatigue caused by flight loads and pressurization of the fuselage.
During inspections in Service Bulletin 757-53A0108 Original Issue an operator found a STA 1640 frame with a
crack starting from the third fastener below the S-14 intercostal on the right side. The crack was approximately
3 inches long and had grown into an insulation stud hole in the web near the outer chord. The crack was not in
the 757-53A0108 Original Issue inspection area. There have also been instances of cracks found growing out
of the fastener holes in the inner chord in the aft direction, towards the web away from the original inspection
areas.
In addition, after the original issue of this service bulletin, there have been a total of 23 cracks reported in the
STA 1640 frames resulting from SB 757-53A0108 Original Issue inspections. These reports were from airplanes
with 20,500 to 39,850 flight cycles, and with 62,100 to 89,150 flight hours. The crack lengths reported ranged
from 0.10 inch to a completely severed frame with some reporting cracking in the outer chord.
Boeing has determined that the existing inspection programs are not sufficient to detect these cracks because
most of the STA 1640 fuselage frame is obscured by adjacent structure. Accomplishment of this service bulletin
will improve detection of cracking in the STA 1640 fuselage frame and make sure that any crack is found and
repaired before the crack grows to a critical length.
Boeing Fleet Team Digest (FTD) 757 FTD 53-16001 is related to this service bulletin.
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### Page 10

Boeing Service Related Problem (SRP) 757-SRP-53-0525 and 757-SRP-53-0594 are related to this service
bulletin.
Multi-Operator Message (MOM) MOM-MOM-17-0037-01C 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
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
Get access to the Body Station (STA) 1640 fuselage frame, between stringers S-11 and S-16, on the left and
right side of the airplane. Do the one time general visual inspection for repairs and the one-time detailed inspection
for any crack, nick or gouge in the STA 1640 fuselage frame, on the left and right side of the airplane. If any
repair, crack, nick or gouge is found, contact The Boeing Company for alternate inspections, repairs and any
corrective actions as applicable. If no crack, nick or gouge is found, do the High Frequency Eddy Current (HFEC)
inspections and Low Frequency Eddy Current (LFEC) for any crack in the STA 1640 fuselage frame, between
stringers S-11 and S-16, on the left and right side of the airplane. If any crack is found, contact The Boeing
Company for repair instructions and do the repair, and repeat the HFEC and LFEC inspections in unrepaired
areas at the times given in Paragraph 1.E., Compliance. If no crack is found, repeat the HFEC and LFEC
inspections at the times given in Paragraph 1.E., Compliance.
EFFECTIVITY
All 757-200, -200CB, and -300 Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2018-06-07 is related to this service bulletin.
The effective date of AD 2018-06-07 is May 03, 2018.
Refer to Paragraph 1.E., Compliance.
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INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspections given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
None.
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### Page 12 (OCR)

BOEING SERVICE BULLETIN 757-53A0108
ALERT  ALERT
STA
1640
STA
1620
...  - S-8
• S-10
S-11
-DO A ONE TIME GENERAL
VISUAL INSPECTION FOR
REPAIRS
- DO REPEAT HIGH FREQUENCY
EDDY CURRENT (HFEC) AND
LOW FREQUENCY
EDDY CURRENT (LFEC)
INSPECTIONS FOR ANY CRACK  - S-13
- DO A ONE-TIME DETAILED  - LOWER HINGE
INSPECTION FOR ANY CRACK,  • S-14 STRAP  INTERCOSTAL
NICK OR GOUGE
• DO REPEAT HIGH FREQUENCY
EDDY CURRENT (HFEC
NSPECTIONS FOR ANY
CRACK
FWD
LEFT SIDE SHOWN, RIGHT SIDE SIMILAR
2522109
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### Page 13

Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-53A0108
Original Issue: November 14, 2016
Revision 1: July 17, 2019
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Body Station 1640 Fuselage Frame Inspection
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This bulletin is applicable to 757-200, 757-200CB, 757-300 Airplane(s), line number(s) 1-138, 140,
142, 144-146, 148, 150-175, 177-180, 182-183, 185, 187-188, 190, 192, 194, 196, 198, 200-236,
238-257, 259-299, 301-313, 315-317, 319-321, 323-325, 327-329, 331-333, 335-339, 341-394,
396-398, 400-402, 404-406, 408-410, 412-476, 478-480, 482-484, 486-488, 490-492, 494-568,
570-572, 574-576, 578, 580, 582-624, 626-627, 629-630, 632-633, 635, 637, 639, 641, 643, 645,
647-648, 650, 652-653, 655, 657-658, 660-674, 676-678, 680-682, 684-686, 688-690, 692-727,
731-732, 735-754, 756-758, 760-762, 764, 766, 768, 770, 772-773, 775, 777, 779-812, 814,
816-822, 824-878, 880-881, 883-1050 in 5 Group(s). Where the effectivity is presented with hyphens
between line numbers, the airplane applicability means "through" and "inclusive", e.g. line numbers
1-9 means line numbers 1 through 9 inclusive.
Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
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### Page 14

DESCRIPTIONCONFIGURATIONGROUP
757-200 and -200CB airplanes that have a long inner chord strap at
the Body Station (STA) 1640 fuselage frame.
-1
757-200 and -200CB airplanes with less than 32,000 total flight cycles
at the original issue date of this service bulletin that have not
accomplished 757-53A0108 original issue as of the revision 1 date
of this service bulletin.
1
757-200 and -200CB airplanes with 32,000 total flight cycles or more
at the original issue date of this service bulletin that have not
accomplished 757-53A0108 original issue as of the revision 1 date
of this service bulletin
2
757-200 and -200CB airplanes that have accomplished 757-53A0108
original issue as of the revision 1 date of this service bulletin.
3
757-200 Boeing special freighter airplanes (STC ST00916WI-D) that
have a long inner chord strap at the STA 1640 fuselage frame.
-2
Airplanes that have not accomplished 757-53A0108 original issue
as of the revision 1 date of this service bulletin
1
Airplanes that have accomplished 757-53A0108 original issue as of
the revision 1 date of this service bulletin.
2
757-300 airplanes that have a long inner chord strap at STA 1640
fuselage frame.
-3
757-300 airplanes, with less than 16,000 total flight cycles at the
original issue date of this service bulletin that have not accomplished
757-53A0108 original issue as of the revision 1 date of this service
bulletin.
1
757-300 airplanes, with 16,000 total flight cycles or more at the
original issue date of this service bulletin that have not accomplished
757-53A0108 original issue as of the revision 1 date of this service
bulletin
2
757-300 airplanes that have accomplished 757-53A0108 original
issue as of the revision 1 date of this service bulletin.
3
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### Page 15

DESCRIPTIONCONFIGURATIONGROUP
757-200 airplanes that have a short inner chord strap at the STA
1640 fuselage frame.
-4
Airplanes that have not accomplished 757-53A0108 original issue
as of the revision 1 date of this service bulletin
1
Airplanes that have accomplished 757-53A0108 original issue as of
the revision 1 date of this service bulletin.
2
757-200 Boeing special freighter airplanes (STC ST00916WI-D) that
have a short inner chord strap at the STA 1640 fuselage frame.
-5
Airplanes that have not accomplished 757-53A0108 original issue
as of the revision 1 date of this service bulletin
1
Airplanes that have accomplished 757-53A0108 original issue as of
the revision 1 date of this service bulletin.
2
Airplane Models:
757-200, 757-200CB, 757-300
GroupVariable Number
4NA001 - NA021
1NA022 - NA028
4NA191
1NA192 - NA199
5NA201 - NA204
4NA205
5NA206 - NA213
4NA214
2NA215 - NA236
1NA237 - NA239
1NA301 - NA305
1NA341 - NA352
1NA391 - NA399
4NA401 - NA403
1NA404 - NA408
1NA441 - NA447
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GroupVariable Number
4NA501 - NA504
1NA505 - NA586
4NB001
1NB002 - NB004
1NB021 - NB023
1NB036 - NB041
1NB051 - NB053
1NB061 - NB073
1NB079
1NB131 - NB148
1NB161 - NB162
1NB166 - NB168
1NB201 - NB204
1NB221 - NB228
1NB230
1NB236
1NB239
1NB261 - NB267
1NB291 - NB299
1NB301 - NB302
1NB311 - NB312
1NB321 - NB331
1NB421 - NB438
1NB446
1NB451 - NB454
1NB501 - NB523
1NB561
1NB571
1NB581 - NB583
1NC001 - NC033
1NC041 - NC042
1NC051 - NC052
1NC056 - NC062
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GroupVariable Number
1NC066 - NC084
1NC091 - NC094
1NC151
1NC161
1ND001 - ND007
1ND011 - ND059
1ND111 - ND113
1ND161 - ND199
1ND201 - ND203
1ND221 - ND225
1ND241 - ND248
1ND301 - ND322
1ND401
1ND891
1ND895
1NE001 - NE008
1NE011 - NE088
1NE091 - NE094
1NE141 - NE150
1NE161 - NE177
1NE201 - NE204
1NE301 - NE302
1NE311 - NE325
1NJ001 - NJ004
1NJ031 - NJ032
1NJ551 - NJ555
3NL001 - NL002
3NL006 - NL017
3NL101 - NL109
3NL141
3NL601 - NL616
1NN001 - NN002
1NN051 - NN052
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GroupVariable Number
1NP901 - NP904
1NT201 - NT202
1NT231 - NT234
1NT237 - NT240
1NT242
1NT245 - NT248
1NT281 - NT289
1NT341 - NT347
1NT351 - NT360
1NT371 - NT373
1NT375 - NT379
1NT381 - NT386
1NT401 - NT409
1NT411 - NT412
1NT426 - NT427
1NT431 - NT432
1NT436 - NT438
1NT441 - NT442
1NT446
1NT701 - NT769
1NT791 - NT796
1NT861 - NT862
1NT881 - NT885
1NT901 - NT916
1NT971 - NT985
1NU031 - NU038
3NU701 - NU705
3NU721 - NU728
3NU731 - NU732
2. Spares Affected
None.
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B. Concurrent Requirements
None.
C. Reason
This service bulletin is sent to provide instructions to do High Frequency Eddy Current (HFEC) and
Low Frequency Eddy Current (LFEC) inspections for any crack in the fuselage frame at Body Station
(STA) 1640, between stringers S-11 and S-16, on the left and right side of the airplane. If the work
given in this service bulletin is not done, such fatigue cracking could adversely affect the structural
integrity of the airplane.
One operator reported a crack finding, at 24,607 total flight cycles, in the STA 1640 fuselage frame at
stringer S-14R, adjacent to door stop number 5. The crack had fully severed the inner chord and web
of the STA 1640 fuselage frame. The cracking is attributed to fatigue caused by flight loads and
pressurization of the fuselage.
During inspections in Service Bulletin 757-53A0108 Original Issue an operator found the STA 1640
frame with a crack starting from the third fastener below the S-14 intercostal on the right side. The
crack was approximately 3 inches long and had grown into an insulation stud hole in the web near the
outer chord. The crack was not in the 757-53A0108 Original Issue inspection area. There have also
been instances of cracks found growing out of the fastener holes in the inner chord in the aft direction,
towards the web away from the original inspection areas.
Boeing has determined that the existing inspection programs are not sufficient to detect these cracks
because most of the STA 1640 fuselage frame is obscured by adjacent structure. Accomplishment of
this service bulletin will improve detection of cracking in the STA 1640 fuselage frame and make sure
that any crack is found and repaired before the crack grows to a critical length.
Boeing Fleet Team Digest (FTD) 757 FTD 53-16001 is related to this service bulletin.
Boeing Service Related Problem (SRP) 757-SRP-53-0525 and 757-SRP-53-0594 are related to this
service bulletin.
Multi-Operator Message (MOM) MOM-MOM-17-0037-01C is related to this service bulletin.
Revision 1 is sent to provide the following:
– Added a reference to Airworthiness Directive AD 2018-06-07
– Added new instructions to do a one time inspection of maintenance records for any repairs or local
frame replacements installed as a result of damage found during inspections in the original issue
of service bulletin 757-53A0108.
– Added a one time Detailed Inspection of the frame inner chord forward return flange edge for
cracks, nicks and gouges.
– Added initial and repetitive High Frequency Eddy Current (HFEC) inspections around the fasteners
of the frame inner chord, and of the inner chord forward return flange radius.
– Changed Low Frequency Eddy Current (LFEC) inspections for six fasteners in the inner chord
from LFEC to HFEC inspections, and the inspection direction is changed from the outboard side
of the frame inner chord to the inboard side of the frame inner chord.
– Added LFEC inspections of the frame inner chord around the upp ermost fastener common to the
frame inner chord long strap (Groups 1-3)
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### Page 20

D. Description
Get access to the Body Station (STA) 1640 fuselage frame, between stringers S-11 and S-16, on the
left and right side of the airplane. Do the one time general visual inspection for repairs and the one-time
detailed inspection for any crack, nick or gouge in the STA 1640 fuselage frame, on the left and right
side of the airplane. If any repair, crack, nick or gouge is found, contact The Boeing Company for
alternate inspections, repairs and any corrective actions as applicable. If no crack, nick or gouge is
found, do the High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current
(LFEC) for any crack in the STA 1640 fuselage frame, between stringers S-11 and S-16, on the left
and right side of the airplane. If any crack is found, contact The Boeing Company for repair instructions
and do the repair, and repeat the HFEC and LFEC inspections in unrepaired areas at the times given
in Paragraph 1.E., Compliance. If no crack is found, repeat the HFEC and LFEC inspections at the
times given in Paragraph 1.E., Compliance.
Effects of this Revision on airplanes on which Original Issue was previously done:
ActionConditionGroup
Do PART 6 inspection for any crack,
nick or gouge.
Airplanes that have accomplished OPTION 1
PART 2 inspections in Service Bulletin 757-
53A0108 Original Issue with no crack found.
Groups 1-5
Do PART 2, PART 7 and PART 8
inspections for any crack.
Do PART 6 inspection for any crack,
nick or gouge.
Airplanes that have accomplished OPTION 2
PART 3 inspections in Service Bulletin 757-
53A0108 Original Issue with no crack found. Do PART 3, PART 7 and PART 8
inspections for any crack.
Do PART 6 inspection for any crack,
nick or gouge.
Airplanes that have accomplished the inspec-
tions in accordance with Service Bulletin 757-
53A0108 Original Issue and have installed a
repair or local frame replacement that does
not contain a reinforcement repair or repair
splice member between S-11 and S-16 and
the repair or replacement is Boeing Organiza-
tion Designation Authorization (ODA) approved
via an FAA form 8100-9.
Do PART 2, PART 7 and PART 8
inspections for any crack.
OR
Do PART 3, PART 7 and PART 8
inspections for any crack.
Contact The Boeing Company for
alternative inspection(s) and do the
inspection(s) and any corrective ac-
tions as applicable.
Airplanes that have accomplished the inspec-
tions in accordance with Service Bulletin 757-
53A0108 Original Issue and have installed a
repair or local frame replacement that contains
a reinforcement repair or repair splice member
between S-11 and S-16.
Contact The Boeing Company for
alternative inspection(s) and do the
inspection(s) and any corrective ac-
tions as applicable.
Airplanes that have accomplished the inspec-
tions in accordance with Service Bulletin 757-
53A0108 Original Issue and have installed a
repair or local frame replacement that is not
Boeing Organization Designation Authorization
(ODA) approved.
The work in this service bulletin is done in the maintenance zone(s) given below.
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### Page 21

Group 1:
Affected Maintenance Zones
ZoneModel
251, 252757-200, 757-200CB
Group 2, 4-5:
Affected Maintenance Zones
ZoneModel
251, 252757-200
Group 3:
Affected Maintenance Zones
ZoneModel
251, 252757-300
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2018-06-07 is related to this service
bulletin. The effective date of AD 2018-06-07 is May 03, 2018.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX
A, APPENDIX B, APPENDIX C, APPENDIX D, APPENDIX E, APPENDIX F, APPENDIX G, APPENDIX
H, APPENDIX I and APPENDIX J.
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.
CONDITION refers to the STA 1640 frame CONDITION of either or both Left Side and/or Right Side
frames. Both side frames must be in compliance but may be under different CONDITIONS at the same
time on any given airplane.
Table 1: Part - Title Index
DescriptionPART
BODY STATION (STA) 1640 FUSELAGE FRAME AT S-14 AND INTER-
COSTAL AREAS - HIGH FREQUENCY EDDY CURRENT (HFEC) AND
LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS
PART 2
BODY STATION (STA) 1640 FUSELAGE FRAME AT S-14 AND INTER-
COSTAL AREAS - HIGH FREQUENCY EDDY CURRENT (HFEC) IN-
SPECTIONS
PART 3
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### Page 22

Table 1: Part - Title Index
DescriptionPART
BODY STATION (STA) 1640 FUSELAGE FRAME AT S-11, S-13 AND
INTERCOSTAL AREAS - HIGH FREQUENCY EDDY CURRENT (HFEC)
INSPECTION
PART 4
BODY STATION (STA) 1640 FUSELAGE FRAME INNER CHORD RE-
TURN FLANGE - DETAILED INSPECTION
PART 6
BODY STATION (STA) 1640 FUSELAGE FRAME INNER CHORD BE-
LOW S-14 - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
PART 7
BODY STATION (STA) 1640 FUSELAGE FRAME INNER CHORD AD-
JACENT TO S-14 - HIGH FREQUENCY EDDY CURRENT (HFEC) IN-
SPECTION
PART 8
Group 1, Configuration 1-2:
Table 2: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 3,000 Flight
Cycles (FC) after
the original issue
date of this service
bulletin or before
32,500 TFC,
whichever occurs
first.
Before 20,000
TFC.
ACTION 1:
Do a General Visual Inspec-
tion for any existing repairs
in the Body Station (STA)
1640 fuselage frame be-
tween stringer S-11 and S-
16.
Airplanes with less than
32,000 Total Flight Cy-
cles (TFC) at the original
issue date of this service
bulletin.
-Within 2,000 FC
after the revision 1
date of this service
bulletin.
Before 20,000
TFC.
ACTION 2:
Do PART 6 for any crack,
nick or gouge.
-Within 500 FC after the original is-
sue date of this service bulletin.
ACTION 1:
Do a General Visual Inspec-
tion for any existing repairs
in the STA 1640 fuselage
frame between stringer S-11
and S-16.
Airplanes with 32,000
TFC or more at the origi-
nal issue date of this
service bulletin.
-Within 2,000 FC after the revision 1
date of this service bulletin.
ACTION 2:
Do PART 6 for any crack,
nick or gouge.
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### Page 23

Group 1, Configuration 1-2:
Table 2: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Compa-
ny for alternative inspections
to this service bulletin or re-
pairs and do the inspections,
repairs and any corrective
actions as applicable.
ANY EXISTING REPAIR
FOUND
OR
ANY CRACK, NICK OR
GOUGE FOUND
-Before further flight.OPTION 1 (ACTION 2):
Do PART 2 at the unrepaired
areas for any crack.
-Before further flight.OPTION 1 (ACTION 3):
Do PART 4 at the unrepaired
areas for any crack.
-Before further flight.OPTION 1 (ACTION 4):
Do PART 8 at the unrepaired
areas for any crack.
-Within 2,000 FC
after the revision 1
date of this service
bulletin.
Before 20,000
TFC.
OPTION 1 (ACTION 5):
Do PART 7 at the unrepaired
areas for any crack.
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for alternative inspections
to this service bulletin or re-
pairs and do the inspections,
repairs and any corrective
actions as applicable.
-Before further flight.OPTION 2 (ACTION 2):
Do PART 3 at the unrepaired
areas for any crack.
-Before further flight.OPTION 2 (ACTION 3):
Do PART 4 at the unrepaired
areas for any crack.
-Before further flight.OPTION 2 (ACTION 4):
Do PART 8 at the unrepaired
areas for any crack.
-Within 2,000 FC
after the revision 1
date of this service
bulletin.
Before 20,000
TFC.
OPTION 2 (ACTION 5):
Do PART 7 at the unrepaired
areas for any crack.
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### Page 24

Group 1, Configuration 1-2:
Table 2: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 2:
Do PART 2 for any crack.NO EXISTING REPAIR
FOUND
AND -Before further flight.OPTION 1 (ACTION 2):Do PART 4 for any crack.NO CRACK, NICK OR
GOUGE FOUND -Before further flight.OPTION 1 (ACTION 3):
Do PART 8 for any crack.
-Within 2,000 FC
after the revision 1
date of this service
bulletin.
Before 20,000
TFC.
OPTION 1 (ACTION 4):
Do PART 7 for any crack.
-Before further flight.OPTION 2 (ACTION 1):
Do PART 3 for any crack.
-Before further flight.OPTION 2 (ACTION 2):
Do PART 4 for any crack.
-Before further flight.OPTION 2 (ACTION 3):
Do PART 8 for any crack.
-Within 2,000 FC
after the revision 1
date of this service
bulletin.
Before 20,000
TFC.
OPTION 2 (ACTION 4):
Do PART 7 for any crack.
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### Page 25

Group 1, Configuration 1-2:
Table 2: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.OPTION 1 (ACTION1):CONDITION 3:
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
ANY CRACK FOUND
6,000 FC-OPTION 1 (ACTION 2):
Repeat PART 2 for any
crack. (a)(b)
6,000 FC-OPTION 1 (ACTION 3):
Repeat PART 7 for any
crack. (a)
6,000 FC-OPTION 1 (ACTION 4):
Repeat PART 8 for any
crack. (a)
10,400 FC-OPTION 1 (ACTION 5):
Repeat PART 4 for any
crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
2,500 FC-OPTION 2 (ACTION 2):
Repeat PART 3 for any
crack. (a)(b)
2,500 FC-OPTION 2 (ACTION 3):
Repeat PART 7 for any
crack. (a)
2,500 FC-OPTION 2 (ACTION 4):
Repeat PART 8 for any
crack. (a)
10,400 FC-OPTION 2 (ACTION 5):
Repeat PART 4 for any
crack. (a)
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### Page 26

Group 1, Configuration 1-2:
Table 2: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
6,000 FC-OPTION 1 (ACTION 1):CONDITION 4:
Repeat PART 2 for any
crack. (a)(b)
NO CRACK FOUND
6,000 FC-OPTION 1 (ACTION 2):
Repeat PART 7 for any
crack. (a)
6,000 FC-OPTION 1 (ACTION 3):
Repeat PART 8 for any
crack. (a)
10,400 FC-OPTION 1 (ACTION 4):
Repeat PART 4 for any
crack. (a)
2,500 FC-OPTION 2 (ACTION 1):
Repeat PART 3 for any
crack. (a)(b)
2,500 FC-OPTION 2 (ACTION 2):
Repeat PART 7 for any
crack. (a)
2,500 FC-OPTION 2 (ACTION 3):
Repeat PART 8 for any
crack. (a)
10,400 FC-OPTION 2 (ACTION 4):
Repeat PART 4 for any
crack. (a)
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### Page 27

Group 1, Configuration 1-2:
Table 2: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 1):
Do PART 2 for any crack.
CONDITION 5:
STA 1640 frames with a
local frame replacement
that does not include a
reinforcement repair or
repair splice member be-
tween S-11 and S-16
and the local frame re-
placement is Boeing
ODA approved via FAA
form 8100-9.
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 3):
Do PART 7 for any crack.
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 4):
Do PART 8 for any crack.
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 1):
Do PART 3 for any crack.
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 3):
Do PART 7 for any crack.
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 4):
Do PART 8 for any crack.
(a) It is not required to do the inspections in areas where a repair covers the affected inspection zone provided:
1. The repair is the corrective action to the crack condition identified in this service bulletin and in-
stalled after the original issue date of this service bulletin AND
2. The installed repair was approved by the Boeing ODA via a FAA  Form 8100-9.
(b) It is acceptable to change the repeat inspection option from OPTION 1 (PART 2) to OPTION 2 (PART 3),
or from OPTION 2 (PART 3) to OPTION 1 (PART 2), provided the repeat interval for the most recently
accomplished inspection option is complied with.
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### Page 28

Group 1, Configuration 3:
Table 3: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Within 500 Flight Cycles (FC) after
the revision 1 date of this service
bulletin.
Do an inspection of STA
1640 frame maintenance
records for the most recent
inspection OPTION used
and for any reinforcement
repairs or local frame re-
placements installed.
All airplanes
-Within 2,000 FC
after the revision
1 date of this
service bulletin.
Within 16,000
FC after the in-
stallation of the
local frame re-
placement.
Do PART 6 for any crack,
nick or gouge.
CONDITION 1:
STA 1640 frames with a
local frame replacement
that does not include a
reinforcement repair or
repair splice member be-
tween S-11 and S-16 as
a result of inspections
done in accordance with
the original issue of this
service bulletin and the
local frame replacement
is Boeing ODA approved
via FAA form 8100-9.
-Within 500 FC after the revision 1
date of this service bulletin.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tions and any applicable on-
condition actions at the times
specified by The Boeing
Company.
CONDITION 2:
STA 1640 frames that
have installed a local
frame replacement that
includes a reinforcement
repair or repair splice
member between S-11
and S-16 and the repair
or local frame replace-
ment is Boeing ODA ap-
proved via FAA form
8100-9.
-Within 500 FC after the revision 1
date of this service bulletin.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tions and any applicable on-
condition actions at the times
specified by The Boeing
Company.
CONDITION 3:
STA 1640 frames that
have installed a frame
repair or local frame re-
placement that is not
Boeing Organization
Designation Authoriza-
tion (ODA) approved via
FAA form 8100-9.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
28 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 29

Group 1, Configuration 3:
Table 3: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Within 500 FC
after the revision
1 date of this
service bulletin.
Within 3,500 FC
after the previ-
ous OPTION 1
PART 2 inspec-
tion.
Do PART 6 for any crack,
nick or gouge. (a)
CONDITION 4:
STA 1640 frames with no
crack found during the
most recent inspections
that were done using
OPTION 1 in accordance
with Service Bulletin 757-
53A0108 Original Issue.
-Within 500 FC
after the revision
1 date of this
service bulletin.
Within 2,500 FC
after the previ-
ous OPTION 2
PART 3 inspec-
tion.
Do PART 6 for any crack,
nick or gouge. (a)
CONDITION 5:
STA 1640 frames with no
crack found during the
most recent inspections
that were done using
OPTION 2 in accordance
with Service Bulletin 757-
53A0108 Original Issue.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
29 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 30

Group 1, Configuration 3:
Table 3: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 6:
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
ANY CRACK, NICK OR
GOUGE FOUND
-Before further flight.OPTION 1 (ACTION 2):
Do PART 2 for any crack. (a)
-Before further flight.OPTION 1 (ACTION 3):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 1 (ACTION 4):
Do PART 8 for any crack. (a)
-Within 10,400 FC after the previous
PART 4 inspection.
OPTION 1 (ACTION 5):
Do PART 4 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
-Before further flight.OPTION 2 (ACTION 2):
Do PART 3 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 3):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 4):
Do PART 8 for any crack. (a)
-Within 10,400 FC after the previous
PART 4 inspection.
OPTION 2 (ACTION 5):
Do PART 4 for any crack. (a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
30 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 31

Group 1, Configuration 3:
Table 3: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 7:
Do PART 2 for any crack. (a)NO CRACK, NICK OR
GOUGE FOUND -Before further flight.OPTION 1 (ACTION 2):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 1 (ACTION 3):
Do PART 8 for any crack. (a)
-Within 10,400 FC after the previous
PART 4 inspection.
OPTION 1 (ACTION 4):
Do PART 4 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Do PART 3 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 2):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 3):
Do PART 8 for any crack. (a)
-Within 10,400 FC after the previous
PART 4 inspection.
OPTION 2 (ACTION 4):
Do PART 4 for any crack. (a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
31 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 32

Group 1, Configuration 3:
Table 3: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 8:
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
ANY CRACK FOUND
6,000 FC-OPTION 1 (ACTION 2):
Repeat PART 2 for any
crack. (a)(b)
6,000 FC-OPTION 1 (ACTION 3):
Repeat PART 7 for any
crack. (a)
6,000 FC-OPTION 1 (ACTION 4):
Repeat PART 8 for any
crack. (a)
10,400 FC-OPTION 1 (ACTION 5):
Repeat PART 4 for any
crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
2,500 FC-OPTION 2 (ACTION 2):
Repeat PART 3 for any
crack. (a)(b)
2,500 FC-OPTION 2 (ACTION 3):
Repeat PART 7 for any
crack. (a)
2,500 FC-OPTION 2 (ACTION 4):
Repeat PART 8 for any
crack. (a)
10,400 FC-OPTION 2 (ACTION 5):
Repeat PART 4 for any
crack. (a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
32 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 33

Group 1, Configuration 3:
Table 3: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
6,000 FC-OPTION 1 (ACTION 1):CONDITION 9:
Repeat PART 2 for any
crack. (a)(b)
NO CRACK FOUND
6,000 FC-OPTION 1 (ACTION 2):
Repeat PART 7 for any
crack. (a)
6,000 FC-OPTION 1 (ACTION 3):
Repeat PART 8 for any
crack. (a)
10,400 FC-OPTION 1 (ACTION 4):
Repeat PART 4 for any
crack. (a)
2,500 FC-OPTION 2 (ACTION 1):
Repeat PART 3 for any
crack. (a)(b)
2,500 FC-OPTION 2 (ACTION 2):
Repeat PART 7 for any
crack. (a)
2,500 FC-OPTION 2 (ACTION 3):
Repeat PART 8 for any
crack. (a)
10,400 FC-OPTION 2 (ACTION 4):
Repeat PART 4 for any
crack. (a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
33 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 34

Group 1, Configuration 3:
Table 3: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 1):
Do PART 2 for any crack.
CONDITION 10:
STA 1640 frames with a
local frame replacement
that does not include a
reinforcement repair or
repair splice member be-
tween S-11 and S-16 in-
stalled as a result of STA
1640 frame inspections
done in accordance with
revision 1 of this service
bulletin and the local
frame replacement is
Boeing ODA approved
via FAA form 8100-9.
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 3):
Do PART 7 for any crack.
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 4):
Do PART 8 for any crack.
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 1):
Do PART 3 for any crack.
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 3):
Do PART 7 for any crack.
-Within 16,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 4):
Do PART 8 for any crack.
(a) It is not required to do the inspections in areas where a repair covers the affected inspection zone provided
all of the following conditions are met:
1. The repair is the corrective action to the crack condition id entified in this service bulletin and
installed after the original issue date of this service bulletin, AND
2. The installed repair was approved by the Boeing ODA via a FAA  Form 8100-9.
(b) It is acceptable to change the repeat inspection option from OPTION 1 (PART 2) to OPTION 2 (PART
3), or from OPTION 2 (PART 3) to OPTION 1 (PART 2), provided the repeat interval for the most recently
accomplished inspection option is complied with.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
34 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 35

Group 2, Configuration 1:
Table 4: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections
for any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640
fuselage side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 500 FC after the original is-
sue date of this service bulletin.
ACTION 1:
Do a General Visual Inspec-
tion for any existing repairs
in the STA 1640 fuselage
frame between stringer S-11
and S-16.
All Airplanes
-Within 1,900 FC after the revision
1 date of this service bulletin.
ACTION 2:
Do PART 6 for any crack,
nick or gouge.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
35 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 36

Group 2, Configuration 1:
Table 4: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections
for any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640
fuselage side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Compa-
ny for alternative inspections
to this service bulletin or re-
pairs and do the inspections,
repairs and any corrective
actions as applicable.
ANY EXISTING REPAIR
FOUND
OR
ANY CRACK, NICK OR
GOUGE FOUND
-Before further flight.OPTION 1 (ACTION 2):
Do PART 2 at the unrepaired
areas for any crack.
-Before further flight.OPTION 1 (ACTION 3):
Do PART 4 at the unrepaired
areas for any crack.
-Before further flight.OPTION 1 (ACTION 4):
Do PART 8 at the unrepaired
areas for any crack.
-Within 1,900 FC after the revision
1 date of this service bulletin.
OPTION 1 (ACTION 5):
Do PART 7 at the unrepaired
areas for any crack.
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for alternative inspections
to this service bulletin or re-
pairs and do the inspections,
repairs and any corrective
actions as applicable.
-Before further flight.OPTION 2 (ACTION 2):
Do PART 3 at the unrepaired
areas for any crack.
-Before further flight.OPTION 2 (ACTION 3):
Do PART 4 at the unrepaired
areas for any crack.
-Before further flight.OPTION 2 (ACTION 4):
Do PART 8 at the unrepaired
areas for any crack.
-Within 1,900 FC after the revision
1 date of this service bulletin.
OPTION 2 (ACTION 5):
Do PART 7 at the unrepaired
areas for any crack.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
36 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 37

Group 2, Configuration 1:
Table 4: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections
for any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640
fuselage side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 2:
Do PART 2 for any crack.NO EXISTING REPAIR
FOUND
AND -Before further flight.OPTION 1 (ACTION 2):Do PART 4 for any crack.NO CRACK, NICK OR
GOUGE FOUND -Before further flight.OPTION 1 (ACTION 3):
Do PART 8 for any crack.
-Within 1,900 FC after the revision
1 date of this service bulletin.
OPTION 1 (ACTION 4):
Do PART 7 for any crack.
-Before further flight.OPTION 2 (ACTION 1):
Do PART 3 for any crack.
-Before further flight.OPTION 2 (ACTION 2):
Do PART 4 for any crack.
-Before further flight.OPTION 2 (ACTION 3):
Do PART 8 for any crack.
-Within 1,900 FC after the revision
1 date of this service bulletin.
OPTION 2 (ACTION 4):
Do PART 7 for any crack.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
37 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 38

Group 2, Configuration 1:
Table 4: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections
for any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640
fuselage side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 3:
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
ANY CRACK FOUND
2,600 FC-OPTION 1 (ACTION 2):
Repeat PART 2 for any
crack. (a)(b)
2,600 FC-OPTION 1 (ACTION 3):
Repeat PART 7 for any
crack. (a)
2,600 FC-OPTION 1 (ACTION 4):
Repeat PART 8 for any
crack. (a)
4,300 FC-OPTION 1 (ACTION 5):
Repeat PART 4 for any
crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
1,900 FC-OPTION 2 (ACTION 2):
Repeat PART 3 for any
crack. (a)(b)
1,900 FC-OPTION 2 (ACTION 3):
Repeat PART 7 for any
crack. (a)
1,900 FC-OPTION 2 (ACTION 4):
Repeat PART 8 for any
crack. (a)
4,300 FC-OPTION 2 (ACTION 5):
Repeat PART 4 for any
crack. (a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
38 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 39

Group 2, Configuration 1:
Table 4: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections
for any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640
fuselage side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
2,600 FC-OPTION 1 (ACTION 1):CONDITION 4:
Repeat PART 2 for any
crack. (a)(b)
NO CRACK FOUND
2,600 FC-OPTION 1 (ACTION 2):
Repeat PART 7 for any
crack. (a)
2,600 FC-OPTION 1 (ACTION 3):
Repeat PART 8 for any
crack. (a)
4,300 FC-OPTION 1 (ACTION 4):
Repeat PART 4 for any
crack. (a)
1,900 FC-OPTION 2 (ACTION 1):
Repeat PART 3 for any
crack. (a)(b)
1,900 FC-OPTION 2 (ACTION 2):
Repeat PART 7 for any
crack. (a)
1,900 FC-OPTION 2 (ACTION 3):
Repeat PART 8 for any
crack. (a)
4,300 FC-OPTION 2 (ACTION 4):
Repeat PART 4 for any
crack. (a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
39 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 40

Group 2, Configuration 1:
Table 4: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections
for any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640
fuselage side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 1):
Do PART 2 for any crack.
CONDITION 5:
STA 1640 frames with a
local frame replacement
that does not include a
reinforcement repair or
repair splice member be-
tween S-11 and S-16
and the local frame re-
placement is Boeing
ODA approved via FAA
form 8100-9.
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 3):
Do PART 7 for any crack.
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 4):
Do PART 8 for any crack.
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 1):
Do PART 3 for any crack.
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 3):
Do PART 7 for any crack.
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 4):
Do PART 8 for any crack.
(a) It is not required to do the inspections in areas where a repair covers the affected inspection zone provided:
1. The repair is the corrective action to the crack condition id entified in this service bulletin and
installed after the original issue date of this service bulletin AND
2. The installed repair was approved by the Boeing ODA via a FAA  Form 8100-9.
(b) It is acceptable to change the repeat inspection option from OPTION 1 (PART 2) to OPTION 2 (PART
3), or from OPTION 2 (PART 3) to OPTION 1 (PART 2), provided the repeat interval for the most recently
accomplished inspection option is complied with.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
40 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 41

Group 2, Configuration 2:
Table 5: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Within 500 Flight Cycles (FC) after
the revision 1 date of this service
bulletin.
Do an inspection of STA
1640 frame maintenance
records for the most recent
inspection OPTION used
and for any reinforcement
repairs or local frame re-
placements installed.
All airplanes
-Within 2,000 FC
after the revision
1 date of this
service bulletin.
Within 5,000 FC
after the installa-
tion of the local
frame replace-
ment.
Do PART 6 for any crack,
nick or gouge.
CONDITION 1:
STA 1640 frames with a
local frame replacement
that does not include a
reinforcement repair or
repair splice member be-
tween S-11 and S-16 as
a result of inspections
done in accordance with
the original issue of this
service bulletin and the
local frame replacement
is Boeing ODA approved
via FAA form 8100-9.
-Within 500 FC after the revision 1
date of this service bulletin.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tions and any applicable on-
condition actions at the times
specified by The Boeing
Company.
CONDITION 2:
STA 1640 frames that
have installed a local
frame replacement that
includes a reinforcement
repair or repair splice
member between S-11
and S-16 and the repair
or local frame replace-
ment is Boeing ODA ap-
proved via FAA form
8100-9.
-Within 500 FC after the revision 1
date of this service bulletin.
Contact the Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tions and any applicable on-
condition actions at the times
specified by The Boeing
Company.
CONDITION 3:
STA 1640 frames that
have installed a frame
repair or local frame re-
placement that is not
Boeing Organization
Designation Authoriza-
tion (ODA) approved via
FAA form 8100-9.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
41 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 42

Group 2, Configuration 2:
Table 5: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Within 500 FC
after the revision
1 date of this
service bulletin.
Within 2,600 FC
after the previ-
ous OPTION 1
PART 2 inspec-
tion.
Do PART 6 for any crack,
nick or gouge. (a)
CONDITION 4:
STA 1640 frames with no
crack found during the
most recent inspections
that were done using
OPTION 1 in accordance
with Service Bulletin 757-
53A0108 Original Issue.
-Within 500 FC
after the revision
1 date of this
service bulletin.
Within 1,900 FC
after the previ-
ous OPTION 2
PART 3 inspec-
tion.
Do PART 6 for any crack,
nick or gouge. (a)
CONDITION 5:
STA 1640 frames with no
crack found during the
most recent inspections
that were done using
OPTION 2 in accordance
with Service Bulletin 757-
53A0108 Original Issue.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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BOEING SERVICE BULLETIN 757-53A0108
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### Page 43

Group 2, Configuration 2:
Table 5: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 6:
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
ANY CRACK, NICK OR
GOUGE FOUND
-Before further flight.OPTION 1 (ACTION 2):
Do PART 2 for any crack. (a)
-Before further flight.OPTION 1 (ACTION 3):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 1 (ACTION 4):
Do PART 8 for any crack. (a)
-Within 4,300 FC after the previous
PART 4 inspection.
OPTION 1 (ACTION 5):
Do PART 4 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
-Before further flight.OPTION 2 (ACTION 2):
Do PART 3 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 3):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 4):
Do PART 8 for any crack. (a)
-Within 4,300 FC after the previous
PART 4 inspection.
OPTION 2 (ACTION 5):
Do PART 4 for any crack. (a)
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BOEING SERVICE BULLETIN 757-53A0108
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### Page 44

Group 2, Configuration 2:
Table 5: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 7:
Do PART 2 for any crack. (a)NO CRACK, NICK OR
GOUGE FOUND -Before further flight.OPTION 1 (ACTION 2):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 1 (ACTION 3):
Do PART 8 for any crack. (a)
-Within 4,300 FC after the previous
PART 4 inspection.
OPTION 1 (ACTION 4):
Do PART 4 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Do PART 3 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 2):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 3):
Do PART 8 for any crack. (a)
-Within 4,300 FC after the previous
PART 4 inspection.
OPTION 2 (ACTION 4):
Do PART 4 for any crack. (a)
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44 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 45

Group 2, Configuration 2:
Table 5: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 8:
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
ANY CRACK FOUND
2,600 FC-OPTION 1 (ACTION 2):
Repeat PART 2 for any
crack. (a)(b)
2,600 FC-OPTION 1 (ACTION 3):
Repeat PART 7 for any
crack. (a)
2,600 FC-OPTION 1 (ACTION 4):
Repeat PART 8 for any
crack. (a)
4,300 FC-OPTION 1 (ACTION 5):
Repeat PART 4 for any
crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
1,900 FC-OPTION 2 (ACTION 2):
Repeat PART 3 for any
crack. (a)(b)
1,900 FC-OPTION 2 (ACTION 3):
Repeat PART 7 for any
crack. (a)
1,900 FC-OPTION 2 (ACTION 4):
Repeat PART 8 for any
crack. (a)
4,300 FC-OPTION 2 (ACTION 5):
Repeat PART 4 for any
crack. (a)
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BOEING SERVICE BULLETIN 757-53A0108
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### Page 46

Group 2, Configuration 2:
Table 5: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
2,600 FC-OPTION 1 (ACTION 1):CONDITION 9:
Repeat PART 2 for any
crack. (a)(b)
NO CRACK FOUND
2,600 FC-OPTION 1 (ACTION 2):
Repeat PART 7 for any
crack. (a)
2,600 FC-OPTION 1 (ACTION 3):
Repeat PART 8 for any
crack. (a)
4,300 FC-OPTION 1 (ACTION 4):
Repeat PART 4 for any
crack. (a)
1,900 FC-OPTION 2 (ACTION 1):
Repeat PART 3 for any
crack. (a)(b)
1,900 FC-OPTION 2 (ACTION 2):
Repeat PART 7 for any
crack. (a)
1,900 FC-OPTION 2 (ACTION 3):
Repeat PART 8 for any
crack. (a)
4,300 FC-OPTION 2 (ACTION 4):
Repeat PART 4 for any
crack. (a)
Export Controlled ECCN: 9E991 - BOEING
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46 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 47

Group 2, Configuration 2:
Table 5: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 1):
Do PART 2 for any crack.
CONDITION 10:
STA 1640 frames with a
local frame replacement
that does not include a
reinforcement repair or
repair splice member be-
tween S-11 and S-16 in-
stalled as a result of STA
1640 frame inspections
done in accordance with
revision 1 of this service
bulletin and the local
frame replacement is
Boeing ODA approved
via FAA form 8100-9.
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 3):
Do PART 7 for any crack.
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 4):
Do PART 8 for any crack.
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 1):
Do PART 3 for any crack.
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 3):
Do PART 7 for any crack.
-Within 5,000 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 4):
Do PART 8 for any crack.
(a) It is not required to do the inspections in areas where a repair covers the affected inspection zone provided
all of the following conditions are met:
1. The repair is the corrective action to the crack condition id entified in this service bulletin and
installed after the original issue date of this service bulletin, AND
2. The installed repair was approved by the Boeing ODA via a FAA  Form 8100-9.
(b) It is acceptable to change the repeat inspection option from OPTION 1 (PART 2) to OPTION 2 (PART
3), or from OPTION 2 (PART 3) to OPTION 1 (PART 2), provided the repeat interval for the most recently
accomplished inspection option is complied with.
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 48

Group 3, Configuration 1-2:
Table 6: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 1,500 Flight
Cycles (FC) after
the original issue
date of this service
bulletin or before
16,500 TFC,
whichever occurs
first.
Before 10,000
TFC.
ACTION 1:
Do a General Visual Inspec-
tion for any existing repairs
in the Body Station (STA)
1640 fuselage frame be-
tween stringer S-11 and S-
16.
Airplanes with less than
16,000 Total Flight Cy-
cles (TFC) at the original
issue date of this service
bulletin.
-Within 2,000 FC
after the revision 1
date of this service
bulletin.
Before 10,000
TFC.
ACTION 2:
Do PART 6 for any crack,
nick or gouge.
-Within 500 FC after the original is-
sue date of this service bulletin.
ACTION 1:
Do a General Visual Inspec-
tion for any existing repairs
in the STA 1640 fuselage
frame between stringer S-11
and S-16.
Airplanes with 16,000
TFC or more at the origi-
nal issue date of this
service bulletin.
-Within 2,000 FC after the revision 1
date of this service bulletin.
ACTION 2:
Do PART 6 for any crack,
nick or gouge.
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### Page 49

Group 3, Configuration 1-2:
Table 6: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Compa-
ny for alternative inspections
to this service bulletin or re-
pairs and do the inspections,
repairs and any corrective
actions as applicable.
ANY EXISTING REPAIR
FOUND
OR
ANY CRACK, NICK OR
GOUGE FOUND
-Before further flight.OPTION 1 (ACTION 2):
Do PART 2 at the unrepaired
areas for any crack.
-Before further flight.OPTION 1 (ACTION 3):
Do PART 4 at the unrepaired
areas for any crack.
-Before further flight.OPTION 1 (ACTION 4):
Do PART 8 at the unrepaired
areas for any crack.
-Within 2,000 FC
after the revision 1
date of this service
bulletin.
Before 10,000
TFC.
OPTION 1 (ACTION 5):
Do PART 7 at the unrepaired
areas for any crack.
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for alternative inspections
to this service bulletin or re-
pairs and do the inspections,
repairs and any corrective
actions as applicable.
-Before further flight.OPTION 2 (ACTION 2):
Do PART 3 at the unrepaired
areas for any crack.
-Before further flight.OPTION 2 (ACTION 3):
Do PART 4 at the unrepaired
areas for any crack.
-Before further flight.OPTION 2 (ACTION 4):
Do PART 8 at the unrepaired
areas for any crack.
-Within 2,000 FC
after the revision 1
date of this service
bulletin.
Before 10,000
TFC.
OPTION 2 (ACTION 5):
Do PART 7 at the unrepaired
areas for any crack.
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 50

Group 3, Configuration 1-2:
Table 6: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 2:
Do PART 2 for any crack.NO EXISTING REPAIR
FOUND
AND -Before further flight.OPTION 1 (ACTION 2):Do PART 4 for any crack.NO CRACK, NICK OR
GOUGE FOUND -Before further flight.OPTION 1 (ACTION 3):
Do PART 8 for any crack.
-Within 2,000 FC
after the revision 1
date of this service
bulletin.
Before 10,000
TFC.
OPTION 1 (ACTION 4):
Do PART 7 for any crack.
-Before further flight.OPTION 2 (ACTION 1):
Do PART 3 for any crack.
-Before further flight.OPTION 2 (ACTION 2):
Do PART 4 for any crack.
-Before further flight.OPTION 2 (ACTION 3):
Do PART 8 for any crack.
-Within 2,000 FC
after the revision 1
date of this service
bulletin.
Before 10,000
TFC.
OPTION 2 (ACTION 4):
Do PART 7 for any crack.
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BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 51

Group 3, Configuration 1-2:
Table 6: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.OPTION 1 (ACTION1):CONDITION 3:
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
ANY CRACK FOUND
3,200 FC-OPTION 1 (ACTION 2):
Repeat PART 2 for any
crack. (a)(b)
3,200 FC-OPTION 1 (ACTION 3):
Repeat PART 7 for any
crack. (a)
3,200 FC-OPTION 1 (ACTION 4):
Repeat PART 8 for any
crack. (a)
5,300 FC-OPTION 1 (ACTION 5):
Repeat PART 4 for any
crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
2,400 FC-OPTION 2 (ACTION 2):
Repeat PART 3 for any
crack. (a)(b)
2,400 FC-OPTION 2 (ACTION 3):
Repeat PART 7 for any
crack. (a)
2,400 FC-OPTION 2 (ACTION 4):
Repeat PART 8 for any
crack. (a)
5,300 FC-OPTION 2 (ACTION 5):
Repeat PART 4 for any
crack. (a)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 52

Group 3, Configuration 1-2:
Table 6: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
3,200 FC-OPTION 1 (ACTION 1):CONDITION 4:
Repeat PART 2 for any
crack. (a)(b)
NO CRACK FOUND
3,200 FC-OPTION 1 (ACTION 2):
Repeat PART 7 for any
crack. (a)
3,200 FC-OPTION 1 (ACTION 3):
Repeat PART 8 for any
crack. (a)
5,300 FC-OPTION 1 (ACTION 4):
Repeat PART 4 for any
crack. (a)
2,400 FC-OPTION 2 (ACTION 1):
Repeat PART 3 for any
crack. (a)(b)
2,400 FC-OPTION 2 (ACTION 2):
Repeat PART 7 for any
crack. (a)
2,400 FC-OPTION 2 (ACTION 3):
Repeat PART 8 for any
crack. (a)
5,300 FC-OPTION 2 (ACTION 4):
Repeat PART 4 for any
crack. (a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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52 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 53

Group 3, Configuration 1-2:
Table 6: High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for
any crack and Detailed Inspection for any crack, nick or gouge in the Body Station (STA) 1640 fuselage
side frames, between Stringers S-11 and S-16, left and right side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,300 FC after the installation
of the local frame replacement.
OPTION 1 (ACTION 1):
Do PART 2 for any crack.
CONDITION 5
STA 1640 frames with a
local frame replacement
that does not include a
reinforcement repair or
repair splice member be-
tween S-11 and S-16
and the local frame re-
placement is Boeing
ODA approved via FAA
form 8100-9.
-Within 6,300 FC after the installation
of the local frame replacement.
OPTION 1 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 6,300 FC after the installation
of the local frame replacement.
OPTION 1 (ACTION 3):
Do PART 7 for any crack.
-Within 6,300 FC after the installation
of the local frame replacement.
OPTION 1 (ACTION 4):
Do PART 8 for any crack.
-Within 6,300 FC after the installation
of the local frame replacement.
OPTION 2 (ACTION 1):
Do PART 3 for any crack.
-Within 6,300 FC after the installation
of the local frame replacement.
OPTION 2 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 6,300 FC after the installation
of the local frame replacement.
OPTION 2 (ACTION 3):
Do PART 7 for any crack.
-Within 6,300 FC after the installation
of the local frame replacement.
OPTION 2 (ACTION 4):
Do PART 8 for any crack.
(a) It is not required to do the inspections in areas where a repair covers the affected inspection zone provided:
1. The repair is the corrective action to the crack condition identified in this service bulletin and in-
stalled after the original issue date of this service bulletin AND
2. The installed repair was approved by the Boeing ODA via a FAA  Form 8100-9.
(b) It is acceptable to change the repeat inspection option from OPTION 1 (PART 2) to OPTION 2 (PART 3),
or from OPTION 2 (PART 3) to OPTION 1 (PART 2), provided the repeat interval for the most recently
accomplished inspection option is complied with.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
53 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 54

Group 3, Configuration 3:
Table 7: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Within 500 Flight Cycles (FC) after
the revision 1 date of this service
bulletin.
Do an inspection of STA
1640 frame maintenance
records for the most recent
inspection OPTION used
and for any reinforcement
repairs or local frame re-
placements installed.
All airplanes
-Within 2,000 FC
after the revision
1 date of this
service bulletin.
Within 6,300 FC
after the installa-
tion of the local
frame replace-
ment.
Do PART 6 for any crack,
nick or gouge.
CONDITION 1:
STA 1640 frames with a
local frame replacement
that does not include a
reinforcement repair or
repair splice member be-
tween S-11 and S-16 as
a result of inspections
done in accordance with
the original issue of this
service bulletin and the
local frame replacement
is Boeing ODA approved
via FAA form 8100-9.
-Within 500 FC after the revision 1
date of this service bulletin.
Contact the Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tions and any applicable on-
condition actions at the times
specified by The Boeing
Company.
CONDITION 2:
STA 1640 frames that
have installed a local
frame replacement that
includes a reinforcement
repair or repair splice
member between S-11
and S-16 and the repair
or local frame replace-
ment is Boeing ODA ap-
proved via FAA form
8100-9.
-Within 500 FC after the revision 1
date of this service bulletin.
Contact the Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tions and any applicable on-
condition actions at the times
specified by The Boeing
Company.
CONDITION 3:
STA 1640 that have in-
stalled a frame repair or
local frame replacement
that is not Boeing Organi-
zation Designation Autho-
rization (ODA) approved
via FAA form 8100-9.
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BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 55

Group 3, Configuration 3:
Table 7: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Within 500 FC
after the revision
1 date of this
service bulletin.
Within 2,800 FC
after the previ-
ous OPTION 1
PART 2 inspec-
tion.
Do PART 6 for any crack,
nick or gouge. (a)
CONDITION 4:
STA 1640 frames with no
crack found during the
most recent inspections
that were done using
OPTION 1 in accordance
with Service Bulletin 757-
53A0108 Original Issue.
-Within 500 FC
after the revision
1 date of this
service bulletin.
Within 2,200 FC
after the previ-
ous OPTION 2
PART 3 inspec-
tion.
Do PART 6 for any crack,
nick or gouge. (a)
CONDITION 5:
STA 1640 frames with no
crack found during the
most recent inspections
that were done using
OPTION 2 in accordance
with Service Bulletin 757-
53A0108 Original Issue.
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55 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 56

Group 3, Configuration 3:
Table 7: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 6:
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
ANY CRACK, NICK OR
GOUGE FOUND
-Before further flight.OPTION 1 (ACTION 2):
Do PART 2 for any crack. (a)
-Before further flight.OPTION 1 (ACTION 3):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 1 (ACTION 4):
Do PART 8 for any crack. (a)
-Within 5,300 FC after the previous
PART 4 inspection.
OPTION 1 (ACTION 5):
Do PART 4 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
-Before further flight.OPTION 2 (ACTION 2):
Do PART 3 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 3):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 4):
Do PART 8 for any crack. (a)
-Within 5,300 FC after the previous
PART 4 inspection.
OPTION 2 (ACTION 5):
Do PART 4 for any crack. (a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
56 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 57

Group 3, Configuration 3:
Table 7: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 7:
Do PART 2 for any crack. (a)NO CRACK, NICK OR
GOUGE FOUND -Before further flight.OPTION 1 (ACTION 2):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 1 (ACTION 3):
Do PART 8 for any crack. (a)
-Within 5,300 FC after the previous
PART 4 inspection.
OPTION 1 (ACTION 4):
Do PART 4 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Do PART 3 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 2):
Do PART 7 for any crack. (a)
-Before further flight.OPTION 2 (ACTION 3):
Do PART 8 for any crack. (a)
-Within 5,300 FC after the previous
PART 4 inspection.
OPTION 2 (ACTION 4): (a)
Do PART 4 for any crack.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
57 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 58

Group 3, Configuration 3:
Table 7: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):CONDITION 8:
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
ANY CRACK FOUND
3,200 FC-OPTION 1 (ACTION 2):
Repeat PART 2 for any
crack. (a)(b)
3,200 FC-OPTION 1 (ACTION 3):
Repeat PART 7 for any
crack. (a)
3,200 FC-OPTION 1 (ACTION 4):
Repeat PART 8 for any
crack. (a)
5,300 FC-OPTION 1 (ACTION 5):
Repeat PART 4 for any
crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Contact The Boeing Compa-
ny for repair instructions and
do the repair.
2,400 FC-OPTION 2 (ACTION 2):
Repeat PART 3 for any
crack. (a)(b)
2,400 FC-OPTION 2 (ACTION 3):
Repeat PART 7 for any
crack. (a)
2,400 FC-OPTION 2 (ACTION 4):
Repeat PART 8 for any
crack. (a)
5,300 FC-OPTION 2 (ACTION 5):
Repeat PART 4 for any
crack. (a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
58 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 59

Group 3, Configuration 3:
Table 7: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
3,200 FC-OPTION 1 (ACTION 1):CONDITION 9:
Repeat PART 2 for any
crack. (a)(b)
NO CRACK FOUND
3,200 FC-OPTION 1 (ACTION 2):
Repeat PART 7 for any
crack. (a)
3,200 FC-OPTION 1 (ACTION 3):
Repeat PART 8 for any
crack. (a)
5,300 FC-OPTION 1 (ACTION 4):
Repeat PART 4 for any
crack. (a)
2,400 FC-OPTION 2 (ACTION 1):
Repeat PART 3 for any
crack. (a)(b)
2,400 FC-OPTION 2 (ACTION 2):
Repeat PART 7 for any
crack. (a)
2,400 FC-OPTION 2 (ACTION 3):
Repeat PART 8 for any
crack. (a)
5,300 FC-OPTION 2 (ACTION 4):
Repeat PART 4 for any
crack. (a)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
59 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

### Page 60

Group 3, Configuration 3:
Table 7: Inspection of Maintenance Records, Detailed Inspection for any crack, nick or gouge, High
Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack
and in the Body Station (STA) 1640 fuselage side frames, between Stringers S-11 and S-16, left and right
side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs later)
ActionCondition
-Within 6,300 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 1):
Do PART 2 for any crack.
CONDITION 10:
STA 1640 frames with a
local frame replacement
that does not include a
reinforcement repair or
repair splice member be-
tween S-11 and S-16 in-
stalled as a result of STA
1640 frame inspections
done in accordance with
revision 1 of this service
bulletin and the local
frame replacement is
Boeing ODA approved
via FAA form 8100-9.
-Within 6,300 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 6,300 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 3):
Do PART 7 for any crack.
-Within 6,300 FC after the installa-
tion of the local frame replacement.
OPTION 1 (ACTION 4):
Do PART 8 for any crack.
-Within 6,300 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 1):
Do PART 3 for any crack.
-Within 6,300 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 2):
Do PART 4 for any crack. (a)
-Within 6,300 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 3):
Do PART 7 for any crack.
-Within 6,300 FC after the installa-
tion of the local frame replacement.
OPTION 2 (ACTION 4):
Do PART 8 for any crack.
(a) It is not required to do the inspections in areas where a repair covers the affected inspection zone provided
all of the following conditions are met:
1. The repair is the corrective action to the crack condition id entified in this service bulletin and
installed after the original issue date of this service bulletin, AND
2. The installed repair was approved by the Boeing ODA via a FAA  Form 8100-9.
(b) It is acceptable to change the repeat inspection option from OPTION 1 (PART 2) to OPTION 2 (PART
3), or from OPTION 2 (PART 3) to OPTION 1 (PART 2), provided the repeat interval for the most recently
accomplished inspection option is complied with.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0108Revision 1: July 17, 2019
60 of 252
BOEING SERVICE BULLETIN 757-53A0108
ALERTALERT

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