# Boeing Alert Service Bulletin 757-53A0100: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2017-0519; AD 2017-26-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 757-53A0100](https://openairdocs.org/service-documents/boeing/757-53a0100.md)
- Title as filed: SB-757-53A0100-Rev01
- Pages: 188
- PDF: https://openairdocs.org/files/sha256/c6/57/c6574bb4a357f2b20764faa50cba32e772c11e9445be463852863b60d9456ab7
- Page: https://openairdocs.org/service-documents/boeing/757-53a0100/file/c6574bb4a357

## Text

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### Page 1

Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-53A0100
Original Issue: November 14, 2016
Revision 1: September 14, 2017
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Body Station 1681 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Unpublished Work.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
757-53A0100Revision 1: September 14, 2017
1 of 188
2.0

### Page 2

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ALERTALERT
BLANK PAGE

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Table of Contents
Revision Transmittal Sheet ............................................ 7
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 7
B. Concurrent Requirements ...................................... 1 7
C. Reason ................................................ 1 7
D. Description .............................................. 1 8
E. Compliance .............................................. 1 9
F . A p p r o v a l  ............................................... 5 0
G. Manpower .............................................. 5 0
H. Weight and Balance Changes .................................... 5 6
I. Electrical Load Data ......................................... 5 6
J . R e f e r e n c e s  .............................................. 5 6
1. Existing Data: ......................................... 5 6
2. Data Supplied with this Service Bulletin: ........................... 5 6
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 5 6
K. Publications Affected ........................................ 5 7
L. Interchangeability and Intermixability of Parts ........................... 5 7
M. Software Accomplishment Summary ................................ 5 7
2. MATERIAL INFORMATION ........................................ 5 9
A. Material - Price and Availability ................................... 5 9
B. Industry Support Information .................................... 5 9
C. Parts Necessary for Each Airplane ................................. 5 9
1 . K i t s / P a r t s  ............................................ 5 9
2. Parts and Materials Supplied by the Operator ........................ 5 9
3. Parts Modified and Reidentified ................................ 6 0
4. Parts Removed and Not Replaced .............................. 6 0
D. Parts Necessary to Change Spares ................................. 6 0
E. Special Tooling - Price and Availability ............................... 6 0
F. Special Tooling Necessary to do this Service Bulletin ....................... 6 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 6 1
A. GENERAL INFORMATION ..................................... 6 1
B. WORK INSTRUCTIONS ....................................... 6 2
FIGURE 1: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - FORWARD
INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] .......... 7 7
FIGURE 2: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - FORWARD
INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] .......... 8 0
FIGURE 3: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER
AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1,
Configuration 1] ......................................... 8 3
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### Page 4

FIGURE 4: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER
AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1,
Configuration 1] ......................................... 8 6
FIGURE 5: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER
CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration
2-3; Group 2] .......................................... 8 9
FIGURE 6: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER
CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration
2-3; Group 2] .......................................... 9 2
FIGURE 7: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - FORWARD
AND AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND
LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 1] . 95
FIGURE 8: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - FORWARD
AND AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND
LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 1] . 99
FIGURE 9: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - FORWARD
AND AFT INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW
FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2]
................................................. 1 0 3
FIGURE 10: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - FORWARD
AND AFT INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW
FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2]
................................................. 1 0 7
FIGURE 11: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR -AFT INNER
AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 1] ............ 1 1 1
FIGURE 12: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR -AFT INNER
AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 1] ............ 1 1 5
FIGURE 13: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - AFT INNER
CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] ......... 1 1 9
FIGURE 14: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - AFT INNER
CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] ......... 1 2 3
FIGURE 15: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER
AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND OPEN HOLE HFEC
INSPECTION [Group 1, Configuration 1] .......................... 1 2 7
FIGURE 16: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER
AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND OPEN HOLE HFEC
INSPECTION [Group 1, Configuration 1] .......................... 1 3 0
FIGURE 17: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER
CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND OPEN HOLE HFEC INSPECTION
[Group 1, Configuration 2-3; Group 2] ............................ 1 3 3
FIGURE 18: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER
CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND OPEN HOLE HFEC INSPECTION
[Group 1, Configuration 2-3; Group 2] ............................ 1 3 6
FIGURE 19: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - AFT INNER
AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND OPEN HOLE HFEC
INSPECTION [Group 1, Configuration 1] .......................... 1 3 9
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FIGURE 20: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - AFT INNER
AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND OPEN HOLE HFEC
INSPECTION [Group 1, Configuration 1] .......................... 1 4 3
FIGURE 21: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - AFT INNER
CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND OPEN HOLE HFEC INSPECTION
[Group 1, Configuration 2-3; Group 2] ............................ 1 4 7
FIGURE 22: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - AFT INNER
CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND OPEN HOLE HFEC INSPECTION
[Group 1, Configuration 2-3; Group 2] ............................ 1 5 1
APPENDIX A: LOGIC DIAGRAM FOR COMPLIANCE TABLE 1: BODY STATION (STA) 1681 FUSELAGE
FRAME HIGH FREQUENCY EDDY CURRENT (HFEC), LOW FREQUENCY EDDY CURRENT
(LFEC) AND OPEN HOLE HFEC INSPECTION FOR ANY CRACK [Group 1, Configuration 1]
................................................. 1 5 5
APPENDIX B: LOGIC DIAGRAM FOR COMPLIANCE TABLE 2: BODY STATION (STA) 1681 FUSELAGE
FRAME HIGH FREQUENCY EDDY CURRENT (HFEC), LOW FREQUENCY EDDY CURRENT
(LFEC) AND OPEN HOLE HFEC INSPECTION FOR ANY CRACK [Group 1, Configuration 2]
................................................. 1 6 1
APPENDIX C: LOGIC DIAGRAM FOR COMPLIANCE TABLE 3: BODY STATION (STA) 1681 FUSELAGE
FRAME HIGH FREQUENCY EDDY CURRENT (HFEC), LOW FREQUENCY EDDY CURRENT
(LFEC) AND OPEN HOLE HFEC INSPECTION FOR ANY CRACK [Group 1, Configuration 3]
................................................. 1 6 8
APPENDIX D: LOGIC DIAGRAM FOR COMPLIANCE TABLE 4: BODY STATION (STA) 1681 FUSELAGE
FRAME HIGH FREQUENCY EDDY CURRENT (HFEC), LOW FREQUENCY EDDY CURRENT
(LFEC) AND OPEN HOLE HFEC INSPECTION FOR ANY CRACK [Group 2, Configuration 1]
................................................. 1 7 5
APPENDIX E: LOGIC DIAGRAM FOR COMPLIANCE TABLE 5: BODY STATION (STA) 1681 FUSELAGE
FRAME HIGH FREQUENCY EDDY CURRENT (HFEC), LOW FREQUENCY EDDY CURRENT
(LFEC) AND OPEN HOLE HFEC INSPECTION FOR ANY CRACK [Group 2, Configuration 2]
................................................. 1 8 2
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: November 14, 2016
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ALERTALERT

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Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
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ALERTALERT
BLANK PAGE

### Page 7

Commercial 
Airplanes
757
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 757-53A0100Original Issue: November 14, 2016
Revision 1: September 14, 2017
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Body Station 1681 Fuselage Frame Inspection
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2017-NM-001-AD, is related to this
service bulletin.
Effects of this Revision on airplanes on which Original Issue was previously done:
None.
REASON FOR REVISION
This revision is sent to provide the operator with an option for Open Hole High Frequency Eddy Current (HFEC)
inspections on the critical fasteners in order to extend repeat inspection intervals for the frames at Body Station
(STA) 1681. This revision is also sent to correct fasteners to rivets in Figures 1 thru 6 and to correct conditions
in the logic diagrams.
The data given in Information Notice 757-53A0100 IN 01 is included in this revision.
These sections were changed:
1. In Summary, Background, added Open Hole HFEC inspections.
2. In Summary, Action, added Open Hole HFEC inspections.
3. In Summary, Compliance, added NPRM reference.
4. In Summary, revised the summary illustration.
5. In Paragraph 1.C., Reason, added Open Hole HFEC inspections, reason for revision and Information
Notice (IN) information.
6. In Paragraph 1.D., Description, added Open Hole HFEC inspections and no more work statement.
7. In Paragraph 1.E., Compliance, added options for Open Hole HFEC inspections and NPRM reference.
8. In Paragraph 1.G., Manpower, revised and added tables.
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9. In Paragraph 1.J., References, added NPRM and SRM references.
10. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added parts and footnote.
11. In Paragraph 3.B., Work Instructions, changed as follows:
a. Updated work instructions.
b. Added options for Open Hole HFEC inspections.
c. Added PART 6 and PART 7.
12. In Figures 1 thru 8, 11 and 12, revised illustrations and step tables.
13. In Figures 9 thru 12, revised figure title.
14. Added Figures 15 thru 22, Open Hole HFEC inspection figures and fastener installation figures.
15. In Appendix A thru E, revised logic diagrams and tables.
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.
REVISION HISTORY
November 14, 2016Original Issue:
September 14, 2017Revision 1:
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

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Commercial 
Airplanes
757
Service Bulletin
ALERT
SummaryNumber: 757-53A0100Original Issue: November 14, 2016
Revision 1: September 14, 2017
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Body Station 1681 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 provides instructions to do High Frequency Eddy Current (HFEC), Low Frequency Eddy
Current (LFEC) and Open Hole HFEC inspections for any crack in the fuselage frame at Body Station (STA)
1681, in the area around stringer S-17, on the left and right side of the airplane. If the work given in this service
bulletin is not done, undetected cracking in the fuselage frame at STA 1681 could adversely affect the structural
integrity of the airplane.
One operator reported a six inch long crack in the fuselage frame web at STA 1681, below the floor line at
stringer S-17L, during a routine maintenance visit. Boeing analysis has determined that the crack was caused
by fatigue. The crack was not easily detected because it was significantly hidden by adjacent structure.
Accomplishment of the work given in this service bulletin will mitigate the safety issue associated with cracking
in the STA 1681 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 53-14002 is related to this service bulletin.
Boeing Service Related Problem (SRP) 757-SRP-53-0489 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
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ReferenceAffectedPlanning Data
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator 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) 1681 fuselage frame, between stringer S-16 and S-18, on the left and
right side of the airplane. Inspect for any existing frame repair and for any existing floor beam repair common
to the STA 1681 frame inspection area. If any existing frame repair is found common to the STA 1681 fuselage
frame inspection area, contact The Boeing Company for repair evaluation and inspection instructions and do
the instructions.
In areas with no existing frame repair, do High Frequency Eddy Current (HFEC) or do HFEC and Open Hole
HFEC inspections for any crack in the STA 1681 fuselage frame, in the area above the floor around stringer
S-17.
In areas with no existing floor beam repair, do HFEC and Low Frequency Eddy Current (LFEC) inspections or
do HFEC and Open Hole HFEC inspections, from the forward and aft side of the frame, for any crack in the STA
1681 fuselage frame, in the area under the floor around stringer S-17.
In areas with any existing floor beam repair, do HFEC and LFEC inspections or do HFEC and Open Hole HFEC
inspection from the aft side of the frame only, for any crack in the STA 1681 fuselage frame, in the area under
the floor around stringer S-17.
If any crack is found, contact The Boeing Company for repair instructions and do the repair, and repeat the
inspections in areas with no existing frame repair at the times specified in Paragraph 1.E., Compliance.
If no crack is found, repeat the inspections at the times specified in Paragraph 1.E., Compliance.
EFFECTIVITY
757-200, -200CB and -300 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2017-NM-001-AD, is related to this
service bulletin.
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
Operator Supplied Parts/Materials.
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ALERTALERT

### Page 12 (OCR)

BOEING SERVICE BULLETIN 757-53A0100
ALERT  ALERT
DO HIGH FREQUENCY EDDY CURRENT
INSPECTION (HFEC), HFEC AND LOW
FREQUENCY EDDY CURRENT (LFEC
INSPECTIONS OR DO HFEC AND OPÉN HOLE
TA 1681 FUSELAGE FRAME IN THE ARNATHE
AROUND STRINGER S-17.
STA
1681
S-17L -
S-18L -
FWD
LEFT SIDE SHOWN
RIGHT SIDE IS SIMILAR
2538018
Original Issue: November 14, 2016
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### Page 13

Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-53A0100
Original Issue: November 14, 2016
Revision 1: September 14, 2017
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Body Station 1681 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 service bulletin is applicable to 757-200, -200CB and -300 Airplanes, line numbers 1-1050 in
2 Groups. The Variable Numbers and Group Information for the applicable airplanes is given below.
Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
757-200 airplanes, line numbers 1-89.-1
757-200 airplanes that have not accomplished Boeing Service Bulletin
(SB) 757-53-0024.
1
757-200 airplanes with less than 31,000 total flight cycles at the
original issue date of this service bulletin, that have accomplished
SB 757-53-0024.
2
757-200 airplanes with 31,000 total flight cycles or more at the original
issue date of this service bulletin, that have accomplished SB
757-53-0024.
3
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### Page 14

DESCRIPTIONCONFIGURATIONGROUP
757-200, -200CB and -300 airplanes, line numbers 90-1050.-2
757-200, -200CB and -300 airplanes with less than 31,000 total flight
cycles at the original issue date of this service bulletin.
1
757-200, -200CB and -300 airplanes with 31,000 total flight cycles
or more at the original issue date of this service bulletin.
2
Airplane Models:
757-200, 757-200CB, 757-300
GroupVariable Number
1NA001 - NA023
2NA024 - NA028
1NA191 - NA192
2NA193 - NA199
1NA201 - NA223
2NA224 - NA239
2NA301 - NA305
2NA341 - NA352
1NA391
2NA392 - NA399
1NA401 - NA404
2NA405 - NA408
2NA441 - NA447
1NA501 - NA515
2NA516 - NA586
1NB001 - NB004
1NB021 - NB023
2NB036 - NB041
2NB051 - NB053
2NB061 - NB073
2NB079
2NB131 - NB148
2NB161 - NB162
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GroupVariable Number
2NB166 - NB168
2NB201 - NB204
2NB221 - NB228
2NB230
2NB236
2NB239
2NB261 - NB267
2NB291 - NB299
2NB301 - NB302
2NB311 - NB312
2NB321 - NB331
2NB421 - NB438
2NB446
2NB451 - NB454
2NB501 - NB523
2NB561
2NB571
2NB581 - NB583
1NC001 - NC014
2NC015 - NC033
2NC041 - NC042
2NC051 - NC052
2NC056 - NC062
2NC066 - NC084
2NC091 - NC094
2NC151
2NC161
2ND001 - ND007
2ND011 - ND059
2ND111 - ND113
2ND161 - ND199
2ND201 - ND203
2ND221 - ND225
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GroupVariable Number
2ND241 - ND248
2ND301 - ND322
2ND401
2ND891
2ND895
2NE001 - NE008
2NE011 - NE088
2NE091 - NE094
2NE141 - NE150
2NE161 - NE177
2NE201 - NE204
2NE301 - NE302
2NE311 - NE325
2NJ001 - NJ004
2NJ031 - NJ032
2NJ551 - NJ555
2NL001 - NL002
2NL006 - NL017
2NL101 - NL109
2NL141
2NL601 - NL616
2NN001 - NN002
2NN051 - NN052
2NP901 - NP904
2NT201 - NT202
2NT231 - NT234
2NT237 - NT240
2NT242
2NT245 - NT248
2NT281 - NT289
2NT341 - NT347
2NT351 - NT360
2NT371 - NT373
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### Page 17

GroupVariable Number
2NT375 - NT379
2NT381 - NT386
2NT401 - NT409
2NT411 - NT412
2NT426 - NT427
2NT431 - NT432
2NT436 - NT438
2NT441 - NT442
2NT446
2NT701 - NT769
2NT791 - NT796
2NT861 - NT862
2NT881 - NT885
2NT901 - NT916
2NT971 - NT985
2NU031 - NU038
2NU701 - NU705
2NU721 - NU728
2NU731 - NU732
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin provides instructions to do High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspections for any crack in the fuselage frame at Body
Station (STA) 1681, in the area around stringer S-17, on the left and right side of the airplane. If the
work given in this service bulletin is not done, undetected cracking in the fuselage frame at STA 1681
could adversely affect the structural integrity of the airplane.
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### Page 18

One operator reported a six inch long crack in the fuselage frame web at STA 1681, below the floor
line at stringer S-17L, during a routine maintenance visit. Boeing analysis has determined that the crack
was caused by fatigue. The crack was not easily detected because it was significantly hidden by
adjacent structure. Accomplishment of the work given in this service bulletin will mitigate the safety
issue associated with cracking in the STA 1681 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 53-14002 is related to this service bulletin.
Boeing Service Related Problem (SRP) 757-SRP-53-0489 is related to this service bulletin.
Revision 1 is sent to provide the operator with an option for Open Hole HFEC inspections on the critical
fasteners in order to extend repeat inspection intervals for the frames at Body Station (STA) 1681. This
revision is also sent to correct fasteners to rivets in Figures 1 thru 6 and to correct conditions in the
logic diagrams.
The data given in Information Notice 757-53A0100 IN 01 is included in this revision.
D. Description
Get access to the Body Station (STA) 1681 fuselage frame, between stringer S-16 and S-18, on the
left and right side of the airplane. Inspect for any existing frame repair and for any existing floor beam
repair common to the STA 1681 frame inspection area. If any existing frame repair is found common
to the STA 1681 fuselage frame inspection area, contact The Boeing Company for repair evaluation
and inspection instructions and do the instructions.
In areas with no existing frame repair, do High Frequency Eddy Current (HFEC) or do HFEC and Open
Hole HFEC inspections for any crack in the STA 1681 fuselage frame, in the area above the floor
around stringer S-17.
In areas with no existing floor beam repair, do HFEC and Low Frequency Eddy Current (LFEC)
inspections or do HFEC and Open Hole HFEC inspections, from the forward and aft side of the frame,
for any crack in the STA 1681 fuselage frame, in the area under the floor around stringer S-17.
In areas with any existing floor beam repair, do HFEC and LFEC inspections or do HFEC and Open
Hole HFEC inspection from the aft side of the frame only, for any crack in the STA 1681 fuselage frame,
in the area under the floor around stringer S-17.
If any crack is found, contact The Boeing Company for repair instructions and do the repair, and repeat
the inspections in areas with no existing frame repair at the times specified in Paragraph 1.E.,
Compliance.
If no crack is found, repeat the inspections at the times specified in Paragraph 1.E., Compliance.
Effects of this Revision on airplanes on which Original Issue was previously done:
None.
The work in this service bulletin is done in the maintenance zone(s) given below.
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### Page 19

Group 1:
Affected Maintenance Zones
ZoneModel
165, 166757-200
Group 2:
Affected Maintenance Zones
ZoneModel
165, 166757-200, 757-200CB, 757-300
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2017-NM-001-AD, is related
to this service bulletin.
Accomplish the required actions, based on the applicable conditions in Tables 1 through 5, in accordance
with Paragraph 3. Accomplishment Instructions.
A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX
A, APPENDIX B, APPENDIX C, APPENDIX D and APPENDIX E.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
Group 1, Configuration 1:
Table 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 300 flight cycles after the
original issue date of this service
bulletin.
Inspect for any existing frame repair
and for any existing floor beam re-
pair common to the STA 1681 frame
inspection area.
All airplanes.
-Before further flight.Contact The Boeing Company for
repair evaluation and inspection in-
structions and do the instructions.
CONDITION 1:
ANY EXISTING
FRAME REPAIR
COMMON TO
THE STA 1681
FUSELAGE
FRAME INSPEC-
TION AREA
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### Page 20

Group 1, Configuration 1:
Table 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 300 flight cycles after the
original issue date of this service
bulletin.
OPTION 1: Do PART 3: AFT SIDE
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
CONDITION 2:
NO EXISTING
FRAME REPAIR
COMMON TO
THE STA 1681
FUSELAGE
FRAME INSPEC-
TION AREA (a) -Within 300 flight cycles after theoriginal issue date of this service
bulletin.
OPTION 2: Do PART 6: AFT SIDE
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair.
-Within 300 flight cycles after the
original issue date of this service
bulletin.
OPTION 1: Do PART 4: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair and no ex-
isting floor beam repair.
CONDITION 3:
NO EXISTING
FLOOR BEAM
REPAIR COM-
MON TO THE
STA 1681 FUSE-
LAGE FRAME IN-
SPECTION AREA
(a)
-Within 300 flight cycles after the
original issue date of this service
bulletin.
OPTION 2: Do PART 7: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND OPEN HOLE HFEC
INSPECTIONS for any crack in ar-
eas with no existing frame repair
and no existing floor beam repair.
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### Page 21

Group 1, Configuration 1:
Table 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 300 flight cycles after the
original issue date of this service
bulletin.
OPTION 1: Do PART 5: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair.
CONDITION 4:
ANY EXISTING
FLOOR BEAM
REPAIR COM-
MON TO THE
STA 1681 FUSE-
LAGE FRAME IN-
SPECTION AREA
(a) -Within 300 flight cycles after the
original issue date of this service
bulletin.
OPTION 2: Do PART 7: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND OPEN HOLE HFEC
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 7:
ANY CRACK
FOUND DURING
PART 3 OR PART
6 INSPECTIONS 3,200 flight cy-cles.-(ACTION 2) OPTION 1: RepeatPART 3: AFT SIDE BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) INSPECTIONS for
any crack in areas with no existing
frame repair. (b)
3,200 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 6: AFT SIDE BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair. (b)
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### Page 22

Group 1, Configuration 1:
Table 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
3,200 flight cy-
cles.
-OPTION 1: Repeat PART 3: AFT
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
(b)
CONDITION 8:
NO CRACK
FOUND DURING
PART 3 OR PART
6 INSPECTION
3,200 flight cy-
cles.
-OPTION 2: Repeat PART 6: AFT
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair. (b)
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 9:
ANY CRACK
FOUND DURING
PART 4 OR PART
7 INSPECTIONS 3,200 flight cy-cles.-(ACTION 2) OPTION 1: RepeatPART 4: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair and no existing floor
beam repair. (c)
3,200 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 7: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair and no ex-
isting floor beam repair. (c)
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### Page 23

Group 1, Configuration 1:
Table 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
3,200 flight cy-
cles.
-OPTION 1: Repeat PART 4: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND LOW FRE-
QUENCY EDDY CURRENT (LFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair
and no existing floor beam repair.
(c)
CONDITION 10:
NO CRACK
FOUND DURING
PART 4 OR PART
7 INSPECTION
3,200 flight cy-
cles.
-OPTION 2: Repeat PART 7: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair and no existing floor beam re-
pair. (c)
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 11:
ANY CRACK
FOUND DURING
PART 5 OR PART
7 INSPECTIONS 1,600 flight cy-cles.-(ACTION 2)OPTION 1: RepeatPART 5: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair. (d)
3,200 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 7: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair. (d)
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### Page 24

Group 1, Configuration 1:
Table 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
1,600 flight cy-
cles.
-OPTION 1: Repeat PART 5: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND LOW FRE-
QUENCY EDDY CURRENT (LFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
(d)
CONDITION 12:
NO CRACK
FOUND DURING
PART 5 OR PART
7 INSPECTION
3,200 flight cy-
cles.
-OPTION 2: Repeat PART 7: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair. (d)
(a) More than one CONDITION can be applicable in areas with no existing frame repair.
(b) It is acceptable to change the repeat inspection method between PART 3 and PART 6, provided the repeat
interval for the previously accomplished inspection method is complied with.
(c) It is acceptable to change the repeat inspection method between PART 4 and PART 7, provided the repeat
interval for the previously accomplished inspection method is complied with.
(d) It is acceptable to change the repeat inspection method between PART 5 and PART 7, provided the repeat
interval for the previously accomplished inspection method is complied with.
Group 1, Configuration 2:
Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
Inspect for any existing frame repair
and for any existing floor beam re-
pair common to the STA 1681 frame
inspection area.
757-200 airplanes
with less than
31,000 total flight
cycles at the origi-
nal issue date of
this service bul-
letin, that have ac-
complished SB
757-53-0024.
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### Page 25

Group 1, Configuration 2:
Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.Contact The Boeing Company for
repair evaluation and inspection in-
structions and do the instructions.
CONDITION 1:
ANY EXISTING
FRAME REPAIR
COMMON TO
THE STA 1681
FUSELAGE
FRAME INSPEC-
TION AREA
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 1: Do PART 2: FORWARD
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair.
CONDITION 2:
NO EXISTING
FRAME REPAIR
COMMON TO
THE STA 1681
FUSELAGE
FRAME INSPEC-
TION AREA (a)
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 2: Do PART 3: AFT SIDE
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 3: Do PART 6: AFT SIDE
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair.
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### Page 26

Group 1, Configuration 2:
Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 1: Do PART 4: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair and no ex-
isting floor beam repair.
CONDITION 3:
NO EXISTING
FLOOR BEAM
REPAIR COM-
MON TO THE
STA 1681 FUSE-
LAGE FRAME IN-
SPECTION AREA
(a)
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 2: Do PART 7: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND OPEN HOLE HFEC
INSPECTIONS for any crack in ar-
eas with no existing frame repair
and no existing floor beam repair.
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 1: Do PART 5: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair.
CONDITION 4:
ANY EXISTING
FLOOR BEAM
REPAIR COM-
MON TO THE
STA 1681 FUSE-
LAGE FRAME IN-
SPECTION AREA
(a)
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 2: Do PART 7: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND OPEN HOLE HFEC
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
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### Page 27

Group 1, Configuration 2:
Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 5:
ANY CRACK
FOUND DURING
PART 2, PART 3
OR PART 6 IN-
SPECTION
1,300 flight cy-
cles.
-(ACTION 2) OPTION 1: Repeat
PART 2: FORWARD SIDE BODY
STATION (STA) 1681 FUSELAGE
FRAME HIGH FREQUENCY EDDY
CURRENT (HFEC) AND LOW
FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS for any crack
in areas with no existing frame re-
pair. (b)
5,800 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 3: AFT SIDE BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) INSPECTIONS for
any crack in areas with no existing
frame repair. (b)
6,600 flight cy-
cles.
-(ACTION 2) OPTION 3: Repeat
PART 6: AFT SIDE BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair. (b)
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### Page 28

Group 1, Configuration 2:
Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
1,300 flight cy-
cles.
-OPTION 1: Repeat PART 2: FOR-
WARD SIDE BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair. (b)
CONDITION 6:
NO CRACK
FOUND DURING
PART 2, PART 3
OR PART 6 IN-
SPECTIONS
5,800 flight cy-
cles.
-OPTION 2: Repeat PART 3: AFT
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
(b)
6,600 flight cy-
cles.
-OPTION 3: Repeat PART 6: AFT
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair. (b)
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BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 29

Group 1, Configuration 2:
Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 9:
ANY CRACK
FOUND DURING
PART 4 OR PART
7 INSPECTIONS 4,100 flight cy-cles.-(ACTION 2) OPTION 1: RepeatPART 4: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair and no existing floor
beam repair. (c)
6,600 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 7: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair and no ex-
isting floor beam repair. (c)
4,100 flight cy-
cles.
-OPTION 1: Repeat PART 4: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND LOW FRE-
QUENCY EDDY CURRENT (LFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair
and no existing floor beam repair.
(c)
CONDITION 10:
NO CRACK
FOUND DURING
PART 4 OR PART
7 INSPECTION
6,600 flight cy-
cles.
-OPTION 2: Repeat PART 7: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair and no existing floor beam re-
pair. (c)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
29 of 188
BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 30

Group 1, Configuration 2:
Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 11:
ANY CRACK
FOUND DURING
PART 5 OR PART
7 INSPECTIONS 3,000 flight cy-cles.-(ACTION 2) OPTION 1: RepeatPART 5: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair. (d)
6,600 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 7: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair. (d)
3,000 flight cy-
cles.
-OPTION 1: Repeat PART 5: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND LOW FRE-
QUENCY EDDY CURRENT (LFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
(d)
CONDITION 12:
NO CRACK
FOUND DURING
PART 5 OR PART
7 INSPECTION
6,600 flight cy-
cles.
-OPTION 2: Repeat PART 7: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair. (d)
(a) More than one CONDITION can be applicable in areas with no existing frame repair.
(b) It is acceptable to change the repeat inspection method between PART 2, PART 3 and PART 6, provided
the repeat interval for the previously accomplished inspection method is complied with.
(c) It is acceptable to change the repeat inspection method between PART 4 and PART 7, provided the repeat
interval for the previously accomplished inspection method is complied with.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
30 of 188
BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 31

Group 1, Configuration 2:
Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
(d) It is acceptable to change the repeat inspection method between PART 5 and PART 7, provided the repeat
interval for the previously accomplished inspection method is complied with.
Group 1, Configuration 3:
Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 500 flight cycles after the
original issue date of this service
bulletin.
Inspect for any existing frame repair
and for any existing floor beam re-
pair common to the STA 1681 frame
inspection area.
757-200 airplanes
with 31,000 total
flight cycles or
more at the origi-
nal issue date of
this service bul-
letin, that have ac-
complished SB
757-53-0024.
-Before further flight.Contact The Boeing Company for
repair evaluation and inspection in-
structions and do the instructions.
CONDITION 1:
ANY EXISTING
FRAME REPAIR
COMMON TO
THE STA 1681
FUSELAGE
FRAME INSPEC-
TION AREA
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
31 of 188
BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 32

Group 1, Configuration 3:
Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 1: Do PART 2: FORWARD
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair.
CONDITION 2:
NO EXISTING
FRAME REPAIR
COMMON TO
THE STA 1681
FUSELAGE
FRAME INSPEC-
TION AREA (a)
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 2: Do PART 3: AFT SIDE
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 3: Do PART 6: AFT SIDE
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair.
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 1: Do PART 4: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair and no ex-
isting floor beam repair.
CONDITION 3:
NO EXISTING
FLOOR BEAM
REPAIR COM-
MON TO THE
STA 1681 FUSE-
LAGE FRAME IN-
SPECTION AREA
(a)
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 2: Do PART 7: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND OPEN HOLE HFEC
INSPECTIONS for any crack in ar-
eas with no existing frame repair
and no existing floor beam repair.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
32 of 188
BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 33

Group 1, Configuration 3:
Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 1: Do PART 5: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair.
CONDITION 4:
ANY EXISTING
FLOOR BEAM
REPAIR COM-
MON TO THE
STA 1681 FUSE-
LAGE FRAME IN-
SPECTION AREA
(a) -Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 2: Do PART 7: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND OPEN HOLE HFEC
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 5:
ANY CRACK
FOUND DURING
PART 2, PART 3
OR PART 6 IN-
SPECTIONS
1,300 flight cy-
cles.
-(ACTION 2) OPTION 1: Repeat
PART 2: FORWARD SIDE BODY
STATION (STA) 1681 FUSELAGE
FRAME HIGH FREQUENCY EDDY
CURRENT (HFEC) AND LOW
FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS for any crack
in areas with no existing frame re-
pair. (b)
5,800 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 3: AFT SIDE BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) INSPECTIONS for
any crack in areas with no existing
frame repair. (b)
6,600 flight cy-
cles.
-(ACTION 2) OPTION 3: Repeat
PART 6: AFT SIDE BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair. (b)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
33 of 188
BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 34

Group 1, Configuration 3:
Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
1,300 flight cy-
cles.
-OPTION 1: Repeat PART 2: FOR-
WARD SIDE BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair. (b)
CONDITION 6:
NO CRACK
FOUND DURING
PART 2, PART 3
OR PART 6 IN-
SPECTIONS
5,800 flight cy-
cles.
-OPTION 2: Repeat PART 3: AFT
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
(b)
6,600 flight cy-
cles.
-OPTION 3: Repeat PART 6: AFT
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair. (b)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
34 of 188
BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 35

Group 1, Configuration 3:
Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 9:
ANY CRACK
FOUND DURING
PART 4 OR PART
7 INSPECTIONS 4,100 flight cy-cles.-(ACTION 2) OPTION 1: RepeatPART 4: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair and no existing floor
beam repair. (c)
6,600 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 7: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair and no ex-
isting floor beam repair. (c)
4,100 flight cy-
cles.
-OPTION 1: Repeat PART 4: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND LOW FRE-
QUENCY EDDY CURRENT (LFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair
and no existing floor beam repair.
(c)
CONDITION 10:
NO CRACK
FOUND DURING
PART 4 OR PART
7 INSPECTION
6,600 flight cy-
cles.
-OPTION 2: Repeat PART 7: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair and no existing floor beam re-
pair. (c)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
35 of 188
BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 36

Group 1, Configuration 3:
Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 11:
ANY CRACK
FOUND DURING
PART 5 OR PART
7 INSPECTIONS 3,000 flight cy-cles.-(ACTION 2) OPTION 1: RepeatPART 5: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair. (d)
6,600 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 7: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair. (d)
3,000 flight cy-
cles.
-OPTION 1: Repeat PART 5: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND LOW FRE-
QUENCY EDDY CURRENT (LFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
(d)
CONDITION 12:
NO CRACK
FOUND DURING
PART 5 OR PART
7 INSPECTION
6,600 flight cy-
cles.
-OPTION 2: Repeat PART 7: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair. (d)
(a) More than one CONDITION can be applicable in areas with no existing frame repair.
(b) It is acceptable to change the repeat inspection method between PART 2, PART 3 and PART 6, provided
the repeat interval for the previously accomplished inspection method is complied with.
(c) It is acceptable to change the repeat inspection method between PART 4 and PART 7, provided the repeat
interval for the previously accomplished inspection method is complied with.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
36 of 188
BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 37

Group 1, Configuration 3:
Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
(d) It is acceptable to change the repeat inspection method between PART 5 and PART 7, provided the repeat
interval for the previously accomplished inspection method is complied with.
Group 2, Configuration 1:
Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
Inspect for any existing frame repair
and for any existing floor beam re-
pair common to the STA 1681 frame
inspection area.
757-200, -200CB
and -300 airplanes
with less than
31,000 total flight
cycles at the origi-
nal issue date of
this service bul-
letin.
-Before further flight.Contact The Boeing Company for
repair evaluation and inspection in-
structions and do the instructions.
CONDITION 1:
ANY EXISTING
FRAME REPAIR
COMMON TO
THE STA 1681
FUSELAGE
FRAME INSPEC-
TION AREA
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
37 of 188
BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 38

Group 2, Configuration 1:
Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 1: Do PART 2: FORWARD
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair.
CONDITION 2:
NO EXISTING
FRAME REPAIR
COMMON TO
THE STA 1681
FUSELAGE
FRAME INSPEC-
TION AREA (a)
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 2: Do PART 3: AFT SIDE
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 3: Do PART 6: AFT SIDE
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
38 of 188
BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 39

Group 2, Configuration 1:
Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 1: Do PART 4: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair and no ex-
isting floor beam repair.
CONDITION 3:
NO EXISTING
FLOOR BEAM
REPAIR COM-
MON TO THE
STA 1681 FUSE-
LAGE FRAME IN-
SPECTION AREA
(a)
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 2: Do PART 7: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND OPEN HOLE HFEC
INSPECTIONS for any crack in ar-
eas with no existing frame repair
and no existing floor beam repair.
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 1: Do PART 5: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair.
CONDITION 4:
ANY EXISTING
FLOOR BEAM
REPAIR COM-
MON TO THE
STA 1681 FUSE-
LAGE FRAME IN-
SPECTION AREA
(a)
-Within 3,000
flight cycles after
the original issue
date of this ser-
vice bulletin, or
before 31,500 to-
tal flight cycles,
whichever oc-
curs first.
Before 25,000
total flight cycles.
OPTION 2: Do PART 7: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND OPEN HOLE HFEC
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
757-53A0100Revision 1: September 14, 2017
39 of 188
BOEING SERVICE BULLETIN 757-53A0100
ALERTALERT

### Page 40

Group 2, Configuration 1:
Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 5:
ANY CRACK
FOUND DURING
PART 2, PART 3
OR PART 6 IN-
SPECTION
2,200 flight cy-
cles.
-(ACTION 2) OPTION 1: Repeat
PART 2: FORWARD SIDE BODY
STATION (STA) 1681 FUSELAGE
FRAME HIGH FREQUENCY EDDY
CURRENT (HFEC) AND LOW
FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS for any crack
in areas with no existing frame re-
pair. (b)
6,700 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 3: AFT SIDE BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) INSPECTIONS for
any crack in areas with no existing
frame repair. (b)
12,000 flight cy-
cles.
-(ACTION 2) OPTION 3: Repeat
PART 6: AFT SIDE BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair. (b)
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### Page 41

Group 2, Configuration 1:
Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
2,200 flight cy-
cles.
-OPTION 1: Repeat PART 2: FOR-
WARD SIDE BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair. (b)
CONDITION 6:
NO CRACK
FOUND DURING
PART 2, PART 3
OR PART 6 IN-
SPECTION
6,700 flight cy-
cles.
-OPTION 2: Repeat PART 3: AFT
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
(b)
12,000 flight cy-
cles.
-OPTION 3: Repeat PART 6: AFT
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair. (b)
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### Page 42

Group 2, Configuration 1:
Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 9:
ANY CRACK
FOUND DURING
PART 4 OR PART
7 INSPECTIONS 5,000 flight cy-cles.-(ACTION 2) OPTION 1: RepeatPART 4: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair and no existing floor
beam repair. (c)
12,000 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 7: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair and no ex-
isting floor beam repair. (c)
5,000 flight cy-
cles.
-OPTION 1: Repeat PART 4: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND LOW FRE-
QUENCY EDDY CURRENT (LFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair
and no existing floor beam repair.
(c)
CONDITION 10:
NO CRACK
FOUND DURING
PART 4 OR PART
7 INSPECTION
12,000 flight cy-
cles.
-OPTION 2: Repeat PART 7: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair and no existing floor beam re-
pair. (c)
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### Page 43

Group 2, Configuration 1:
Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 11:
ANY CRACK
FOUND DURING
PART 5 OR PART
7 INSPECTION 3,700 flight cy-cles.-(ACTION 2) OPTION 1: RepeatPART 5: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair. (d)
12,000 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 7: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair. (d)
3,700 flight cy-
cles.
-OPTION 1: Repeat PART 5: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND LOW FRE-
QUENCY EDDY CURRENT (LFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
(d)
CONDITION 12:
NO CRACK
FOUND DURING
PART 5 OR PART
7 INSPECTION
12,000 flight cy-
cles.
-OPTION 2: Repeat PART 7: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair. (d)
(a) More than one CONDITION can be applicable in areas with no existing frame repair.
(b) It is acceptable to change the repeat inspection method between PART 2, PART 3 and PART 6, provided
the repeat interval for the previously accomplished inspection method is complied with.
(c) It is acceptable to change the repeat inspection method between PART 4 and PART 7, provided the repeat
interval for the previously accomplished inspection method is complied with.
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### Page 44

Group 2, Configuration 1:
Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC), Low Frequency
Eddy Current (LFEC) and Open Hole HFEC inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
(d) It is acceptable to change the repeat inspection method between PART 5 and PART 7, provided the repeat
interval for the previously accomplished inspection method is complied with.
Group 2, Configuration 2:
Table 5: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency
Eddy Current (LFEC) inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 500 flight cycles after the
original issue date of this service
bulletin.
Inspect for any existing frame repair
and for any existing floor beam re-
pair common to the STA 1681 frame
inspection area.
757-200, -200CB
and -300 airplanes
with 31,000 total
flight cycles or
more at the origi-
nal issue date of
this service bul-
letin.
-Before further flight.Contact The Boeing Company for
repair evaluation and inspection in-
structions and do the instructions.
CONDITION 1:
ANY EXISTING
FRAME REPAIR
COMMON TO
THE STA 1681
FUSELAGE
FRAME INSPEC-
TION AREA
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### Page 45

Group 2, Configuration 2:
Table 5: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency
Eddy Current (LFEC) inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 1: Do PART 2: FORWARD
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair.
CONDITION 2:
NO EXISTING
FRAME REPAIR
COMMON TO
THE STA 1681
FUSELAGE
FRAME INSPEC-
TION AREA (a)
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 2: Do PART 3: AFT SIDE
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 3: Do PART 6: AFT SIDE
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair.
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 1: Do PART 4: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair and no ex-
isting floor beam repair.
CONDITION 3:
NO EXISTING
FLOOR BEAM
REPAIR COM-
MON TO THE
STA 1681 FUSE-
LAGE FRAME IN-
SPECTION AREA
(a)
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 2: Do PART 7: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND OPEN HOLE HFEC
INSPECTIONS for any crack in ar-
eas with no existing frame repair
and no existing floor beam repair.
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### Page 46

Group 2, Configuration 2:
Table 5: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency
Eddy Current (LFEC) inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 1: Do PART 5: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair.
CONDITION 4:
ANY EXISTING
FLOOR BEAM
REPAIR COM-
MON TO THE
STA 1681 FUSE-
LAGE FRAME IN-
SPECTION AREA
(a) -Within 500 flight cycles after the
original issue date of this service
bulletin.
OPTION 2: Do PART 7: BELOW
THE FLOOR BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND OPEN HOLE HFEC
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 5:
ANY CRACK
FOUND DURING
PART 2, PART 3
OR PART 6 IN-
SPECTIONS
2,200 flight cy-
cles.
-(ACTION 2) OPTION 1: Repeat
PART 2: FORWARD SIDE BODY
STATION (STA) 1681 FUSELAGE
FRAME HIGH FREQUENCY EDDY
CURRENT (HFEC) AND LOW
FREQUENCY EDDY CURRENT
(LFEC) INSPECTIONS for any crack
in areas with no existing frame re-
pair. (b)
6,700 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 3: AFT SIDE BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) INSPECTIONS for
any crack in areas with no existing
frame repair. (b)
12,000 flight cy-
cles.
-(ACTION 2) OPTION 3: Repeat
PART 6: AFT SIDE BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair. (b)
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### Page 47

Group 2, Configuration 2:
Table 5: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency
Eddy Current (LFEC) inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
2,200 flight cy-
cles.
-OPTION 1: Repeat PART 2: FOR-
WARD SIDE BODY STATION (STA)
1681 FUSELAGE FRAME HIGH
FREQUENCY EDDY CURRENT
(HFEC) AND LOW FREQUENCY
EDDY CURRENT (LFEC) INSPEC-
TIONS for any crack in areas with
no existing frame repair. (b)
CONDITION 6:
NO CRACK
FOUND DURING
PART 2, PART 3
OR PART 6 IN-
SPECTION
6,700 flight cy-
cles.
-OPTION 2: Repeat PART 3: AFT
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
(b)
12,000 flight cy-
cles.
-OPTION 3: Repeat PART 6: AFT
SIDE BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair. (b)
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### Page 48

Group 2, Configuration 2:
Table 5: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency
Eddy Current (LFEC) inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 9:
ANY CRACK
FOUND DURING
PART 4 OR PART
7 INSPECTIONS 5,000 flight cy-cles.-(ACTION 2) OPTION 1: RepeatPART 4: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair and no existing floor
beam repair. (c)
12,000 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 7: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair and no ex-
isting floor beam repair. (c)
5,000 flight cy-
cles.
-OPTION 1: Repeat PART 4: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND LOW FRE-
QUENCY EDDY CURRENT (LFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair
and no existing floor beam repair.
(c)
CONDITION 10:
NO CRACK
FOUND DURING
PART 4 OR PART
7 INSPECTION
12,000 flight cy-
cles.
-OPTION 2: Repeat PART 7: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair and no existing floor beam re-
pair. (c)
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### Page 49

Group 2, Configuration 2:
Table 5: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency
Eddy Current (LFEC) inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.(ACTION 1): Contact The Boeing
Company for repair instructions and
do the repair.
CONDITION 11:
ANY CRACK
FOUND DURING
PART 5 OR PART
7 INSPECTIONS 3,700 flight cy-cles.-(ACTION 2) OPTION 1: RepeatPART 5: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND LOW FREQUENCY EDDY
CURRENT (LFEC) INSPECTIONS
for any crack in areas with no exist-
ing frame repair. (d)
12,000 flight cy-
cles.
-(ACTION 2) OPTION 2: Repeat
PART 7: BELOW THE FLOOR
BODY STATION (STA) 1681
FUSELAGE FRAME HIGH FRE-
QUENCY EDDY CURRENT (HFEC)
AND OPEN HOLE HFEC INSPEC-
TIONS for any crack in areas with
no existing frame repair. (d)
3,700 flight cy-
cles.
-OPTION 1: Repeat PART 5: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND LOW FRE-
QUENCY EDDY CURRENT (LFEC)
INSPECTIONS for any crack in ar-
eas with no existing frame repair.
(d)
CONDITION 12:
NO CRACK
FOUND DURING
PART 5 OR PART
7 INSPECTION
12,000 flight cy-
cles.
-OPTION 2: Repeat PART 7: BE-
LOW THE FLOOR BODY STATION
(STA) 1681 FUSELAGE FRAME
HIGH FREQUENCY EDDY CUR-
RENT (HFEC) AND OPEN HOLE
HFEC INSPECTIONS for any crack
in areas with no existing frame re-
pair. (d)
(a) More than one CONDITION can be applicable in areas with no existing frame repair.
(b) It is acceptable to change the repeat inspection method between PART 2, PART 3 and PART 6, provided
the repeat interval for the previously accomplished inspection method is complied with.
(c) It is acceptable to change the repeat inspection method between PART 4 and PART 7, provided the repeat
interval for the previously accomplished inspection method is complied with.
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### Page 50

Group 2, Configuration 2:
Table 5: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency
Eddy Current (LFEC) inspection for any crack
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
(d) It is acceptable to change the repeat inspection method between PART 5 and PART 7, provided the repeat
interval for the previously accomplished inspection method is complied with.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The tables below show an estimate of the task hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools
Group 1, Configuration 1:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low
Frequency Eddy Current (LFEC) inspection for airplanes with no existing floor beam repair
in the STA 1681 frame inspection area - OPTION 1
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Open Access
(a)(a)(a)Aft Galley and Aft
Lavatory Removal
3.303.301FIGURE 3
3.303.301FIGURE 4
5.605.601FIGURE 7
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### Page 51

Group 1, Configuration 1:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low
Frequency Eddy Current (LFEC) inspection for airplanes with no existing floor beam repair
in the STA 1681 frame inspection area - OPTION 1
Elapsed HoursTask HoursNumber of PersonsTask
5.605.601FIGURE 8
(a)(a)(a)Aft Galley and Aft
Lavatory Installation
3.507.002Close Access
24.8031.80TOTAL FOR EACH AIRPLANE
(a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re-
moved from that step or sub-step.
Group 1, Configuration 1:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Open
Hole HFEC inspection for airplanes with no existing floor beam repair in the STA 1681 frame
inspection area - OPTION 2
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Open Access
(a)(a)(a)Aft Galley and Aft
Lavatory Removal
2.202.201FIGURE 15
2.202.201FIGURE 16
2.602.601FIGURE 19
2.602.601FIGURE 20
(a)(a)(a)Aft Galley and Aft
Lavatory Installation
3.507.002Close Access
16.6023.60TOTAL FOR EACH AIRPLANE
(a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re-
moved from that step or sub-step.
Group 1, Configuration 1:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low
Frequency Eddy Current (LFEC) inspection for airplanes with any existing floor beam repair
in the STA 1681 frame inspection area - OPTION 1
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Open Access
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### Page 52

Group 1, Configuration 1:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low
Frequency Eddy Current (LFEC) inspection for airplanes with any existing floor beam repair
in the STA 1681 frame inspection area - OPTION 1
Elapsed HoursTask HoursNumber of PersonsTask
(a)(a)(a)Aft Galley and Aft
Lavatory Removal
3.303.301FIGURE 3
3.303.301FIGURE 4
5.605.601FIGURE 11
5.605.601FIGURE 12
(a)(a)(a)Aft Galley and Aft
Lavatory Installation
3.507.002Close Access
24.8031.80TOTAL FOR EACH AIRPLANE
(a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re-
moved from that step or sub-step.
Group 1, Configuration 1:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Open
Hole HFEC inspection for airplanes with any existing floor beam repair in the STA 1681
frame inspection area - OPTION 2
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Open Access
(a)(a)(a)Aft Galley and Aft
Lavatory Removal
2.202.201FIGURE 15
2.202.201FIGURE 16
2.102.101FIGURE 19
2.102.101FIGURE 20
(a)(a)(a)Aft Galley and Aft
Lavatory Installation
3.507.002Close Access
15.6022.60TOTAL FOR EACH AIRPLANE
(a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re-
moved from that step or sub-step.
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### Page 53

Group 1, Configuration 2-3; Group 2:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low
Frequency Eddy Current (LFEC) inspection for airplanes with no existing floor beam repair
in the STA 1681 frame inspection area - OPTION 1
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Open Access
3.703.701FIGURE 1
3.703.701FIGURE 2
3.403.401FIGURE 9
3.403.401FIGURE 10
3.507.002Close Access
21.2028.20TOTAL FOR EACH AIRPLANE
Group 1, Configuration 2-3; Group 2:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low
Frequency Eddy Current (LFEC) inspection for airplanes with no existing floor beam repair
in the STA 1681 frame inspection area - OPTION 2
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Open Access
(a)(a)(a)Aft Galley and Aft
Lavatory Removal
2.502.501FIGURE 5
2.502.501FIGURE 6
3.403.401FIGURE 9
3.403.401FIGURE 10
(a)(a)(a)Aft Galley and Aft
Lavatory Installation
3.507.002Close Access
18.8025.80TOTAL FOR EACH AIRPLANE
(a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re-
moved from that step or sub-step.
Group 1, Configuration 2-3; Group 2:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Open
Hole HFEC inspection for airplanes with no existing floor beam repair in the STA 1681 frame
inspection area - OPTION 3
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Open Access
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 54

Group 1, Configuration 2-3; Group 2:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Open
Hole HFEC inspection for airplanes with no existing floor beam repair in the STA 1681 frame
inspection area - OPTION 3
Elapsed HoursTask HoursNumber of PersonsTask
(a)(a)(a)Aft Galley and Aft
Lavatory Removal
2.002.001FIGURE 17
2.002.001FIGURE 18
2.202.201FIGURE 21
2.202.201FIGURE 22
(a)(a)(a)Aft Galley and Aft
Lavatory Installation
3.507.002Close Access
15.4022.40TOTAL FOR EACH AIRPLANE
(a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re-
moved from that step or sub-step.
Group 1, Configuration 2-3; Group 2:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low
Frequency Eddy Current (LFEC) inspection for airplanes with any existing floor beam repair
in the STA 1681 frame inspection area - OPTION 1
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Open Access
3.703.701FIGURE 1
3.703.701FIGURE 2
3.403.401FIGURE 13
3.403.401FIGURE 14
3.507.002Close Access
21.2028.20TOTAL FOR EACH AIRPLANE
Group 1, Configuration 2-3; Group 2:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low
Frequency Eddy Current (LFEC) inspection for airplanes with any existing floor beam repair
in the STA 1681 frame inspection area - OPTION 2
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Open Access
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: November 14, 2016
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54 of 188
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ALERTALERT

### Page 55

Group 1, Configuration 2-3; Group 2:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low
Frequency Eddy Current (LFEC) inspection for airplanes with any existing floor beam repair
in the STA 1681 frame inspection area - OPTION 2
Elapsed HoursTask HoursNumber of PersonsTask
(a)(a)(a)Aft Galley and Aft
Lavatory Removal
2.502.501FIGURE 5
2.502.501FIGURE 6
3.403.401FIGURE 13
3.403.401FIGURE 14
(a)(a)(a)Aft Galley and Aft
Lavatory Installation
3.507.002Close Access
18.8025.80TOTAL FOR EACH AIRPLANE
(a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re-
moved from that step or sub-step.
Group 1, Configuration 2-3; Group 2:
Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Open
Hole HFEC inspection for airplanes with any existing floor beam repair in the STA 1681
frame inspection area - OPTION 3
Elapsed HoursTask HoursNumber of PersonsTask
3.507.002Open Access
(a)(a)(a)Aft Galley and Aft
Lavatory Removal
2.002.001FIGURE 17
2.002.001FIGURE 18
2.002.001FIGURE 21
2.002.001FIGURE 22
(a)(a)(a)Aft Galley and Aft
Lavatory Installation
3.507.002Close Access
15.0022.00TOTAL FOR EACH AIRPLANE
(a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re-
moved from that step or sub-step.
Export Controlled ECCN: 9E991 - BOEING
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### Page 56

H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin 757-53-0024
b. Boeing Service Letter 757-SL-51-022
c. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)
2017-NM-001-AD.
d. Boeing Service Related Problem (SRP) 757-SRP-53-0489
e. Service Bulletin Index D624N001
f. Standard Overhaul Practices Manual (SOPM) 20-50-12
g. 757 Aircraft Maintenance Manual (AMM) 25-21-02, 25-21-05, 25-21-06, 25-31-04, 25-41-04,
25-50-07, 25-55-00, 25-55-07, 53-01-01, 53-13-01
h. 757 Fleet Team Digest (FTD) 53-14002
i. 757 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-11, Part 6, 51-00-16,
Part 6, 51-00-19, Part 6, 51-00-23
j. 757-200 Structural Repair Manual (SRM) 51-40-02, 51-40-03
k. 757-200CB Structural Repair Manual (SRM) 51-40-02, 51-40-03
l. 757-300 Structural Repair Manual (SRM) 51-40-02, 51-40-03
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
AFT FRAME INSTL, STA1681.80 - NO.4 PASSENGER DOOR146N8712
LWR MAIN SILL INSTL NO.4 PASSENGER DOOR146N8722
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### Page 57

The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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### Page 58

Export Controlled ECCN: 9E991 - BOEING
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BLANK PAGE

### Page 59

2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each
Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin
does not show the Boeing price and supply data.
B. Industry Support Information
Boeing warranty remedies are not available for the inspections given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
NotesNameQTYPart Number / Specification
(a)(b)(c)Liner Retainer Stud12045081-1 (OP1913-1 optional)
(d)(g)Sealant1 OzBMS5-95, Class B
(e)(g)Sealant1 OzBMS 5-44, Class B (BMS 5-45,
Class B optional)
(f)Adhesive1 OzPR 2701, Class A
(h)Bolt-BACB30UB8K( )
(h)Collar-BACC30BF8
(h)Rivet-BACR15FT6KE( )C
(a) This part is only necessary to replace a damaged part. Quantity given is for one location.
(b) 2045081-1 can be purchased from: Southco, Inc., 210 North Brinton Lake Road, Con-
cordville, Pennsylvania 19331, USA. CAGE code: 94222.
(c) OP1913-1 can be purchased from: NMC Group, Inc. 2755 Thompson Creek Road,
Pomona, California 91767-1861, USA. CAGE code: 03296.
(d) This material is only necessary if a liner retainer stud is replaced and the bonding procedure
used is SOPM 20-50-12, Type 93. Quantity given is for one location.
(e) This material is only necessary if a liner retainer stud is replaced and the bonding procedure
used is SOPM 20-50-12, Type 44. Quantity given is for one location.
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### Page 60

NotesNameQTYPart Number / Specification
(f) This material is only necessary if a liner retainer stud is replaced and the bonding procedure
used is SOPM 20-50-12, Type 121. Quantity given is for one location. This material can
be purchased from: PRC - Desoto International, Inc., PPG Aerospace ASC - Los Angeles,
24811 Avenue Rockefeller, Valencia, California 91355-3468, USA. CAGE code: 83574.
(g) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
(h) Refer to 757 Structural Repair Manual Chapter 51 for alternative fasteners.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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