# Boeing Alert Service Bulletin 757-53A0105: No revision named

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- Document: [Boeing Alert Service Bulletin 757-53A0105](https://openairdocs.org/service-documents/boeing/757-53a0105.md)
- Title as filed: SB-757-53A0105 rev 00
- Pages: 27
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## Text

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### Page 1

Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-53A0105
Original Issue: June 10, 2016
ATA System: 5340
SUBJECT: FUSELAGE - Section 44 - Circumferential Splice Plate Inspection at STA 900 and STA
1180, from S-6L to S-6R
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Unpublished Work.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.
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2.0

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### Page 3

Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 16
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 19
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 19
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
FIGURE 1: INSPECTION OF THE CIRCUMFERENTIAL SPLICE PLATES . . . . . . . . . . . . . . . 23
APPENDIX A: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
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Commercial 
Airplanes
757
Service Bulletin
ALERT
SummaryNumber: 757-53A0105Original Issue: June 10, 2016
ATA System: 5340
SUBJECT: FUSELAGE - Section 44 - Circumferential Splice Plate Inspection at STA 900 and STA
1180, from S-6L to S-6R
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
The fuselage circumferential splice plates along the center fastener rows, forward and aft of STA 900 and STA
1180 splice centerlines, have been determined to be susceptible to widespread fatigue cracking, from Stringer
S-6L to S-6R. Cracking was found on the fatigue test article, and Widespread Fatigue Damage (WFD) analysis
has identified the need for inspections. Currently, there have been no reports of cracking on airplanes in service.
Inspections will mitigate a safety issue, allowing continued operation to the Limit of Validity (LOV). Accomplishment
of the inspections in this service bulletin will make sure that any crack in the circumferential splice plates, at the
locations specified in this service bulletin, is found. Continued operation with any undetected splice plate crack
could adversely affect the structural integrity of the airplane.
The circumferential splice plates have been determined to be structure that is susceptible to Widespread Fatigue
Damage (WFD).
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
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ReferenceAffectedPlanning Data
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
NoOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Do external Low Frequency Eddy Current (LFEC) inspection of the circumferential splice plates at STA 900 and
STA 1180, from S-6L to S-6R, for any crack.
If any crack is found, contact The Boeing Company for repair instructions and do the repair.
If no crack is found, repeat the inspections at the time specified in Paragraph 1.E., Compliance.
EFFECTIVITY
All 757-200/-200CB/-200PF Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
None.
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BOEING SERVICE BULLETIN 757-53A0105
ALERT  ALERT
STA  STA
900  1180
• ОГ
S-6R  DO LOW FREQUENCY EDDY CURRENT
INSPECTION OF THE CIRCUMFERENTIAL
S-6L  CEI  - THE  SPLICE PLATES AT STA 900 AND STA 1180,
BODY SE  I JOINT  FROM S-6L TO S-6R, FOR ANY CRACK
AT STA 900 A  ) STA 1180
- S-3
•00
•00  - S-4
10 0 0
olo  •
YPICAL
2480761
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Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-53A0105
Original Issue: June 10, 2016
ATA System: 5340
SUBJECT: FUSELAGE - Section 44 - Circumferential Splice Plate Inspection at STA 900 and STA
1180, from S-6L to S-6R
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
All 757-200/-200CB/-200PF airplanes-1
Airplane Models:
757-200, 757-200CB, 757-200PF
GroupVariable Number
1NA001 - NA002
1NA005
1NA008
1NA021 - NA028
1NA195
1NA197 - NA199
1NA201 - NA213
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GroupVariable Number
1NA216 - NA218
1NA220 - NA239
1NA301 - NA305
1NA342 - NA344
1NA346 - NA352
1NA392 - NA399
1NA401 - NA407
1NA441 - NA447
1NA502 - NA505
1NA509 - NA510
1NA512
1NA516 - NA535
1NA537 - NA538
1NA546
1NA548 - NA586
1NB001 - NB004
1NB021 - NB023
1NB036 - NB041
1NB052 - NB053
1NB061 - NB068
1NB070 - NB073
1NB079
1NB131 - NB148
1NB161 - NB162
1NB167 - NB168
1NB201 - NB202
1NB221 - NB228
1NB230
1NB236
1NB239
1NB261 - NB267
1NB291 - NB299
1NB301 - NB302
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GroupVariable Number
1NB311 - NB312
1NB321 - NB331
1NB421 - NB424
1NB426 - NB438
1NB446
1NB451 - NB454
1NB501 - NB523
1NB561
1NB571
1NB581 - NB583
1NC001 - NC003
1NC005
1NC008
1NC012 - NC013
1NC017
1NC020 - NC021
1NC024
1NC026
1NC030
1NC042
1NC051 - NC052
1NC056 - NC062
1NC066 - NC084
1NC091 - NC094
1NC151
1NC161
1NC901 - NC951
1NC971
1NC973 - NC974
1ND002
1ND004
1ND011 - ND027
1ND029 - ND044
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GroupVariable Number
1ND046 - ND059
1ND111 - ND113
1ND161 - ND166
1ND168 - ND199
1ND201 - ND203
1ND221 - ND225
1ND241 - ND248
1ND301 - ND322
1ND401
1ND891
1ND895
1NE001 - NE004
1NE006 - NE008
1NE011 - NE030
1NE032 - NE081
1NE083 - NE088
1NE092 - NE094
1NE141 - NE150
1NE161 - NE177
1NE201 - NE204
1NE301
1NE311 - NE325
1NJ001 - NJ004
1NJ031 - NJ032
1NJ551 - NJ555
1NN001 - NN002
1NN051 - NN052
1NP901 - NP904
1NS601 - NS616
1NT001 - NT009
1NT201 - NT202
1NT231 - NT234
1NT237 - NT240
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GroupVariable Number
1NT242
1NT245 - NT248
1NT281 - NT289
1NT341 - NT347
1NT351 - NT360
1NT371 - NT373
1NT375 - NT379
1NT381 - NT386
1NT401 - NT409
1NT411 - NT412
1NT426 - NT427
1NT431 - NT432
1NT436 - NT438
1NT441 - NT442
1NT446
1NT701 - NT769
1NT791 - NT796
1NT861 - NT862
1NT881 - NT885
1NT901 - NT903
1NT905 - NT916
1NT971 - NT985
1NU031 - NU038
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
The fuselage circumferential splice plates along the center fastener rows, forward and aft of STA 900
and STA 1180 splice centerlines, have been determined to be susceptible to widespread fatigue
cracking, from Stringer S-6L to S-6R. Cracking was found on the fatigue test article, and Widespread
Fatigue Damage (WFD) analysis has identified the need for inspections. Currently, there have been
no reports of cracking on airplanes in service. Inspections will mitigate a safety issue, allowing continued
operation to the Limit of Validity (LOV). Accomplishment of the inspections in this service bulletin will
make sure that any crack in the circumferential splice plates, at the locations specified in this service
bulletin, is found. Continued operation with any undetected splice plate crack could adversely affect
the structural integrity of the airplane.
The circumferential splice plates have been determined to be structure that is susceptible to Widespread
Fatigue Damage (WFD).
D. Description
Do external Low Frequency Eddy Current (LFEC) inspection of the circumferential splice plates at STA
900 and STA 1180, from S-6L to S-6R, for any crack.
If any crack is found, contact The Boeing Company for repair instructions and do the repair.
If no crack is found, repeat the inspections at the time specified in Paragraph 1.E., Compliance.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
233, 234, 243, 244, 253, 254757-200, 757-200CB, 757-
200PF
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Do the required actions in accordance with Paragraph 3.B., Work Instructions.
A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX
A.
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Table 1: INSPECTION OF THE CIRCUMFERENTIAL SPLICE PLATES AT STA 900 AND STA 1180, FROM
S-6L TO S-6R, FOR ANY CRACK
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 3,000 flight cy-
cles after the original
issue date of this ser-
vice bulletin.
Before 50,000
total flight cycles.
Do PART 1: LOW FRE-
QUENCY EDDY CUR-
RENT (LFEC) INSPEC-
TION OF THE CIRCUM-
FERENTIAL SPLICE
PLATES AT STA 900 AND
STA 1180, FROM S-6L TO
S-6R for any crack.
All airplanes
12,000 flight cy-
cles.
--Repeat PART 1: LFEC IN-
SPECTION OF THE CIR-
CUMFERENTIAL SPLICE
PLATES AT STA 900 AND
STA 1180, FROM S-6L TO
S-6R for any crack.
CONDITION 1: NO
CRACK FOUND
--Before further
flight.
(ACTION 1)
Contact The Boeing Com-
pany for repair instructions
and do the repair.
CONDITION 2: ANY
CRACK FOUND
12,000 flight cy-
cles.
--(ACTION 2)
Repeat PART 1: LFEC IN-
SPECTION OF THE CIR-
CUMFERENTIAL SPLICE
PLATES AT STA 900 AND
STA 1180, FROM S-6L TO
S-6R for any crack.
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.
The Manager of the FAA Los Angeles Aircraft Certification Office approves the action (i.e. inspection)
defined in this service bulletin as an Alternative Method of Compliance (AMOC) to the requirements
of paragraph (h) of AD 2006-11-11, for the inspections of SSI 53-40-05 [Circumferential Skin Splice,
BS900 S-6L to S-6R and Circumferential Skin Splice, BS1180, S-6L to S-6R (applicable to 757-200)]
listed in Section 9 of the maintenance Planning Data (MPD) Document, D622N001-9. This AMOC only
applies to the common areas inspected per this Service Bulletin. All provisions of AD 2006-11-11 that
are not specifically referenced in the above statement remain fully applicable and must be complied
with. Therefore, operators may revise their FAA-approved maintenance or inspection program with
these alternate inspections for common areas.
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If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools
Elapsed HoursTask HoursNumber of PersonsTask
2.905.802FIGURE 1
2.905.80TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2006-11-11
b. Service Bulletin Index D624N001
c. 757 Non-Destructive Testing (NDT) Manual Part 6, 53-40-07
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
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K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
None.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 757 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 757
Aircraft Maintenance Manual (AMM).
4. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
5. Boeing Service Letter 757-SL-51-022, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
6. Refer to APPENDIX A for logic diagram. The logic diagram is provided as an aid
only. Information contained in Paragraph 1.E., Compliance is the primary source for
compliance times. Information in Paragraph 3.B., Work Instructions is the primary
source for tasks required for compliance.
7. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
8. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
9. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
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10. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
11. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. An Alternative Method of
Compliance (AMOC) is required for any deviations to RC steps, including sub-steps
and identified figures. Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection program without
obtaining approval of an AMOC. This is provided that the RC steps, including
sub-steps and identified figures, can still be done as specified, and the airplane can
be put back in an airworthy condition.
B. WORK INSTRUCTIONS
1. RC - Do PART 1: LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE
CIRCUMFERENTIAL SPLICE PLATES AT STA 900 AND STA 1180, FROM S-6L TO S-6R, for
any crack.
a. CONDITION 1: NO CRACK FOUND
(1) Repeat PART 1: LFEC INSPECTION OF THE CIRCUMFERENTIAL SPLICE PLATES
AT STA 900 AND STA 1180, FROM S-6L TO S-6R, for any crack, at the time specified
in Paragraph 1.E., Compliance.
b. CONDITION 2: ANY CRACK FOUND
(1) (ACTION 1) Contact The Boeing Company for repair instructions and do the repair.
(2) (ACTION 2) Repeat PART 1: LFEC INSPECTION OF THE CIRCUMFERENTIAL SPLICE
PLATES AT STA 900 AND STA 1180, FROM S-6L TO S-6R, for any crack, at the time
specified in Paragraph 1.E., Compliance.
2. Put the airplane back to a serviceable condition.
PART 1: LFEC INSPECTION OF THE CIRCUMFERENTIAL SPLICE PLATES AT STA 900 AND
STA 1180, FROM S-6L TO S-6R
1. Do external LFEC inspection through the skin at STA 900 and STA 1180, from S-6L to S-6R, for
any crack in the circumferential splice plates, in accordance with FIGURE 1.
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BOEING SERVICE BULLETIN 757-53A0105
ALERT  ALERT
STA
900
nD
S-6R  200
S-6L
2480836
FIGURE 1: INSPECTION OF THE CIRCUMFERENTIAL SPLICE PLATES
(SHEET 1 OF 3)
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### Page 24 (OCR)

BOEING SERVICE BULLETIN 757-53A0105
ALERT  ALERT
• S-6R  80306У.  - S-6R
S-5R  13EE2  - S-5R
• S-4R  - S-4R
S-3R  - S-3R
- S-2R  - S-2R
S-1  - S-1
£103  - S-2L  - S-2L
S-3L  - S-3L
- S-4L  - S-4L
BLEED  - S-5L  -S-5L
1330033  • S-6L  79-S -
STA 900  STA 1180
2480838
FIGURE 1: INSPECTION OF THE CIRCUMFERENTIAL SPLICE PLATES
(SHEET 2 OF 3)
Original Issue: June 10, 2016
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### Page 25

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataLocationNameTaskStep
(a)STA 900, S-6L to S-6RCircumferential Splice
Plates
Inspect1
(a)STA 1180, S-6L to S-6RCircumferential Splice
Plates
Inspect2
(a) Do Low Frequency Eddy Current (LFEC) inspection around each fastener common to the circumferential
splice plates, for any crack in accordance with 757 NDT Manual Part 6, 53-40-07.
FIGURE 1: INSPECTION OF THE CIRCUMFERENTIAL SPLICE PLATES
(SHEET 3 OF 3)
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Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
1. The table below gives the description for the parts and conditions called out in the logic diagram.
DescriptionTitle
LFEC INSPECTION OF THE CIRCUMFERENTIAL SPLICE PLATES AT STA
900 AND STA 1180, FROM S-6L TO S-6R
PART 1
NO CRACK FOUNDCONDITION 1
ANY CRACK FOUNDCONDITION 2
APPENDIX A:
(SHEET 1 OF 2)
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 757-53A0105
ALERT  ALERT
WHICHEVER OCCURS LATER
WITHIN 3,000 FLIGHT
BEFORE 50,000 TOTAL  FLIGHT CYCLES  ORIGINAL ISSUE DATE  CYCLES AFTER THE  OF THIS SERVICE
BULLETIN
DO PART 1
CONDITION 1  CONDITION 2
NOT TO EXCEED  BEFORE FURTHER
12,000 FLIGHT CYCLES  FLIGHT
ACTION 1: CONTACT THE
REPEAT PART 1  BOEING COMPANY FOR
REPAIR INSTRUCTIONS
AND DO THE REPAIR
NOT TO EXCEED
12,000 FLIGHT CYCLES
ACTION 2: REPEAT PART 1
APPENDIX A:
(SHEET 2 OF 2)
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