# Boeing Alert Requirements Bulletin 757-53A0112 RB: Revision 1

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- Title as filed: 757-53A0112 RB Rev 1
- Pages: 90
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### Page 1

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0112 RB
Original Issue: November 16, 2018
Revision 1: June 17, 2022
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Inspection of Station 1640 Fuselage Frame Web at S-14
EXPORT CONTROLLED - This technology or software is subject to the U.S. Export Administration Regulations
(EAR), (15 C.F.R. Parts 730-774). No authorization from the U.S. Department of Commerce is required for
export, re-export, in-country transfer, or access EXCEPT to country group E:1 or E:2 countries/persons per
Supp.1 to Part 740 of the EAR.
9E991ECCN:
Copyright © 2018 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Unpublished Work.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 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
1 of 90
4.0

### Page 2

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757-53A0112 RBRevision 1: June 17, 2022
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REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
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Table of Contents
Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
FIGURE 1: LEFT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME GENERAL VISUAL INSPECTION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73
FIGURE 2: RIGHT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME GENERAL VISUAL
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76
FIGURE 3: LEFT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME OPEN HOLE HFEC INSPECTION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79
FIGURE 4: RIGHT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME OPEN HOLE HFEC
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82
FIGURE 5: LEFT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME FASTENER RE-INSTALLATION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85
FIGURE 6: RIGHT SIDE - BODY STATION (STA) 1640 FUSELAGE FRAME FASTENER RE-INSTALLATION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88
Export Controlled ECCN: 9E991
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REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 4

Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
4 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
BLANK PAGE

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Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Revision Transmittal SheetNumber: 757-53A0112 RBOriginal Issue: November 16, 2018
Revision 1: June 17, 2022
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Inspection of Station 1640 Fuselage Frame Web at S-14
This revision includes all pages of the requirements bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2019-23-06 is related to this service bulletin.
The effective date of AD 2019-23-06 is January 13, 2020.
Effects of this Revision on airplanes on which Original Issue was previously done:
None.
REASON FOR REVISION
This revision is sent to change the compliance time for Group 1 airplanes that have accomplished Service
Bulletin 757-53A0108 with no crack found, but have not accomplished Service Bulletin 757-53A0112. The repeat
inspection interval for Group 2 airplanes has also been changed.
These sections were changed:
- In Compliance, added new Airworthiness Directive (AD) related to this service bulletin. Changed grace period,
and added and changed compliance table, initial conditions for Group 1 airplanes. Changed repeat inspection
period, and added and changed compliance table, initial conditions for Group 2 airplanes. Changed compliance
table, initial conditions for Group 3, Group 4 and Group 5 airplanes.
- In Work Instructions, added and changed work instruction table, initial conditions for Group 1 airplanes. Added
and changed work instruction table, initial conditions for Group 2 airplanes. Changed work instruction table,
initial conditions for Group 3, Group 4 and Group 5 airplanes.
- In Figure 5 and 6, updated illustrations.
Operators are suggested to review changes to the compliance times and adopt it into their maintenance program
as applicable.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
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REVISION HISTORY
Service BulletinService BulletinRequirement BulletinRequirement Bulletin
757-53A0112757-53A0112757-53A0112 RB757-53A0112 RB
Issue DateIssue Date
November 16, 2018Original Issue:November 16, 2018Original Issue:
June 17, 2022Revision 1:June 17, 2022Revision 1:
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
6 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 7

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0112 RB
Original Issue: November 16, 2018
Revision 1: June 17, 2022
ATA System: 5360
SUBJECT: FUSELAGE - Section 46 - Inspection of Station 1640 Fuselage Frame Web at S-14
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. THIS IS AN ENHANCED REQUIRED FOR COMPLIANCE DOCUMENT. THE BOEING
PROCESSES USED TO CREATE THE SERVICE BULLETIN (SB) AND THE REQUIREMENTS BULLETIN
(RB) ENSURE THAT THE INFORMATION BETWEEN "RC START" AND "RC END" IN THE SB ARE IDENTICAL
TO THE INFORMATION IN THE SAME SECTIONS (COMPLIANCE, WORK INSTRUCTIONS…) OF THE RB
WHICH THE SB REFERS TO AS THE RELATED DOCUMENT.
1. Effectivity
A. Airplanes
This bulletin is applicable to 757-200, 757-200CB, 757-300 Airplane(s), line number(s) 1-138, 140,
142, 144-146, 148, 150-175, 177-180, 182-183, 185, 187-188, 190, 192, 194, 196, 198, 200-236,
238-257, 259-299, 301-313, 315-317, 319-321, 323-325, 327-329, 331-333, 335-339, 341-394,
396-398, 400-402, 404-406, 408-410, 412-476, 478-480, 482-484, 486-488, 490-492, 494-568,
570-572, 574-576, 578, 580, 582-624, 626-627, 629-630, 632-633, 635, 637, 639, 641, 643, 645,
647-648, 650, 652-653, 655, 657-658, 660-674, 676-678, 680-682, 684-686, 688-690, 692-727,
731-732, 735-754, 756-758, 760-762, 764, 766, 768, 770, 772-773, 775, 777, 779-812, 814,
816-822, 824-878, 880-881, 883-1050 in 5 Group(s). Where the effectivity is presented with hyphens
between line numbers, the airplane applicability means "through" and "inclusive", e.g. line numbers
1-9 means line numbers 1 through 9 inclusive.
DESCRIPTIONCONFIGURATIONGROUP
757-200 and -200CB airplanes that have a long inner chord strap at
the Body Station (STA) 1640 fuselage frame. Line numbers 45 and
subsequent .
-1
757-200 airplanes changed to the Special Freighter (SF) configuration
by the Boeing Company in accordance with Supplemental Type
Certificate (STC) ST00916WI-D that have a long inner chord strap
at the Body Station (STA) 1640 fuselage frame. Line numbers 50,
52, 54, 58, 63, 77-78, 81, 89-90, 93, 98, 123, 145, 160, 166, 168,
175, 179, 210-211, and 214.
-2
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### Page 8

DESCRIPTIONCONFIGURATIONGROUP
757-300 airplanes that have a long inner chord strap at the Body
Station (STA) 1640 fuselage frame.
-3
757-200 airplanes that have a short inner chord strap at the Body
Station (STA) 1640 fuselage frame. Line Numbers 1-8, 12, 14-15,
17-22, 26-28, 31, and 34-44.
-4
757-200 airplanes changed to the Special Freighter (SF) configuration
by the Boeing Company in accordance with Supplemental Type
Certificate (STC) ST00916WI-D that have a short inner chord strap
at the Body Station (STA) 1640 fuselage frame. Line numbers 9-11,
13, 16, 23-25, 29-30, and 32-33.
-5
Airplane Models:
757-200, 757-200CB, 757-300
GroupVariable Number
4NA001 - NA021
1NA022 - NA028
4NA191
1NA192 - NA199
5NA201 - NA204
4NA205
5NA206 - NA213
4NA214
2NA215 - NA236
1NA237 - NA239
1NA301 - NA305
1NA341 - NA352
1NA391 - NA399
4NA401 - NA403
1NA404 - NA408
1NA441 - NA447
4NA501 - NA504
1NA505 - NA586
4NB001
GroupVariable Number
1NB002 - NB004
1NB021 - NB023
1NB036 - NB041
1NB051 - NB053
1NB061 - NB073
1NB079
1NB131 - NB148
1NB161 - NB162
1NB166 - NB168
1NB201 - NB204
1NB221 - NB228
1NB230
1NB236
1NB239
1NB261 - NB267
1NB291 - NB299
1NB301 - NB302
1NB311 - NB312
1NB321 - NB331
GroupVariable Number
1NB421 - NB438
1NB446
1NB451 - NB454
1NB501 - NB523
1NB561
1NB571
1NB581 - NB583
1NC001 - NC033
1NC041 - NC042
1NC051 - NC052
1NC056 - NC062
1NC066 - NC084
1NC091 - NC094
1NC151
1NC161
1ND001 - ND007
1ND011 - ND059
1ND111 - ND113
1ND161 - ND199
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REQUIREMENTS BULLETIN 757-53A0112
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### Page 9

GroupVariable Number
1ND201 - ND203
1ND221 - ND225
1ND241 - ND248
1ND301 - ND322
1ND401
1ND891
1ND895
1NE001 - NE008
1NE011 - NE088
1NE091 - NE094
1NE141 - NE150
1NE161 - NE177
1NE201 - NE204
1NE301 - NE302
1NE311 - NE325
1NJ001 - NJ004
1NJ031 - NJ032
1NJ551 - NJ555
GroupVariable Number
3NL001 - NL002
3NL006 - NL017
3NL101 - NL109
3NL141
3NL601 - NL616
1NN001 - NN002
1NN051 - NN052
1NP901 - NP904
1NT201 - NT202
1NT231 - NT234
1NT237 - NT240
1NT242
1NT245 - NT248
1NT281 - NT289
1NT341 - NT347
1NT351 - NT360
1NT371 - NT373
1NT375 - NT379
GroupVariable Number
1NT381 - NT386
1NT401 - NT409
1NT411 - NT412
1NT426 - NT427
1NT431 - NT432
1NT436 - NT438
1NT441 - NT442
1NT446
1NT701 - NT769
1NT791 - NT796
1NT861 - NT862
1NT881 - NT885
1NT901 - NT916
1NT971 - NT985
1NU031 - NU038
3NU701 - NU705
3NU721 - NU728
3NU731 - NU732
B. Spares Affected
None.
2. CONCURRENT REQUIREMENTS
None.
3. COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2019-23-06 is related to this service
bulletin. The effective date of AD 2019-23-06 is January 13, 2020.
Accomplish the required action(s), based on the applicable condition(s) in Tables 1 through 10 in accordance
with the Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION. When more than
one ACTION is given for a CONDITION or an OPTION, do all of the ACTION numbers for that CONDITION
or OPTION.
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### Page 10

Group 1:
Table 1: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 500 flight
cycles after the
Revision 1 date
of Requirements
Bulletin 757-
53A0112 RB.
Before 20,000
total flight cycles.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14L intercostal
area.
Airplanes with less than
32,000 total flight cycles at
the Revision 1 date of Re-
quirements Bulletin 757-
53A0112 RB that have not
accomplished the inspec-
tions in accordance with
the original issue of Ser-
vice Bulletin 757-53A0108,
the Revision 1 of Service
Bulletin 757-53A0108, or
the original issue of Re-
quirements Bulletin 757-
53A0112 RB.
-Within 30 days
of the Revision 1
date of Require-
ments Bulletin
757-53A0112
RB.
Before 32,500
total flight cycles.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14L intercostal
area.
Airplanes with 32,000 total
flight cycles or more at the
Revision 1 date of Require-
ments Bulletin 757-
53A0112 RB that have not
accomplished the inspec-
tions in accordance with
the original issue of Ser-
vice Bulletin 757-53A0108,
the Revision 1 of Service
Bulletin 757-53A0108, or
the original issue of Re-
quirements Bulletin 757-
53A0112 RB.
-Within 500 flight
cycles after the
Revision 1 date
of Requirements
Bulletin 757-
53A0112 RB not
to exceed 5,600
flight cycles after
the last inspec-
tion done in ac-
cordance with
the Original Is-
sue or the Revi-
sion 1 of Service
Bulletin 757-
53A0108.
Within 2,900
flight cycles after
the last inspec-
tion done in ac-
cordance with
the original issue
or the Revision 1
of Service Bul-
letin 757-
53A0108.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes with less than
39,500 total flight cycles at
the Revision 1 date of Re-
quirements Bulletin 757-
53A0112 RB that have ac-
complished the inspections
in accordance with the
original issue or the Revi-
sion 1 of Service Bulletin
757-53A0108 with no crack
found and have not accom-
plished the inspections in
the original issue of Re-
quirements Bulletin 757-
53A0112 RB.
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### Page 11

Group 1:
Table 1: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before 40,000
total flight cycles
or, within 30
days of the Revi-
sion 1 date of
Requirements
Bulletin 757-
53A0112 RB,
whichever oc-
curs later.
Within 2,900
flight cycles after
the last inspec-
tion done in ac-
cordance with
the original issue
or the Revision 1
of Service Bul-
letin 757-
53A0108.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes with 39,500 total
flight cycles or more at the
Revision 1 date of Require-
ments Bulletin 757-
53A0112 RB that have ac-
complished the inspections
in accordance with the
original issue or the Revi-
sion 1 of Service Bulletin
757-53A0108 with no crack
found and have not accom-
plished the inspections in
the original issue of Re-
quirements Bulletin 757-
53A0112 RB.
-Within 12,000
flight cycles after
the installation of
the local frame
replacement or
within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 16,000
flight cycles after
the installation of
the local frame
replacement or
before 50,000 to-
tal flight cycles.
Whichever oc-
curs first.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14L in-
tercostal area that is Boe-
ing Organization Designa-
tion Authorization (ODA)
approved via an FAA form
8100-9 and the frame web
common to the tee clip
fastener holes at stringer
S-14L has been replaced.
Whichever oc-
curs later.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14L in-
tercostal area that is not
Boeing ODA approved.
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### Page 12

Group 1:
Table 1: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a reinforcing repair
in the S-14L intercostal
area.
--Within 12,000
flight cycles after
the last Require-
ments Bulletin
757-53A0112
RB inspections.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue of Requirements
Bulletin 757-53A0112 RB
with no crack found.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 1:
ANY REINFORCING RE-
PAIR FOUND IN THE
STRINGER S-14L INSPEC-
TION AREA.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 2:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14L
INSPECTION AREA THAT
IS NOT BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9.
-Within 12,000
flight cycles after
the installation of
the local frame
replacement or
within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 16,000
flight cycles after
the installation of
the local frame
replacement or
before 50,000 to-
tal flight cycles.
Whichever oc-
curs first.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14L
INSPECTION AREA THAT
IS BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON
TO THE TEE CLIP FAS-
TENER HOLES AT
STRINGER S-14L HAS
BEEN REPLACED. Whichever oc-
curs later.
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### Page 13

Group 1:
Table 1: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
CONDITION 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND
IN THE STRINGER S-14L
INSPECTION AREA.
-Before further flight.CONDITION 5 (ACTION 1):CONDITION 5:
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
ANY CRACK FOUND.
12,000-CONDITION 5 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14L intercostal tee
clip for any crack. (a)
-Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Install fasteners common to
the frame web and S-14L
intercostal tee clip.
NO CRACK FOUND.
12,000-CONDITION 6 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14L intercostal tee
clip for any crack. (a)
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements Bulletin
757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance with Re-
quirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
13 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 14

Group 1:
Table 2: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 500 flight
cycles after the
Revision 1 date
of Requirements
Bulletin 757-
53A0112 RB.
Before 20,000
total flight cycles.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14R intercostal
area.
Airplanes with less than
32,000 total flight cycles at
the Revision 1 date of Re-
quirements Bulletin 757-
53A0112 RB that have not
accomplished the inspec-
tions in accordance with
the original issue of Ser-
vice Bulletin 757-53A0108,
the Revision 1 of Service
Bulletin 757-53A0108, or
the original issue of Re-
quirements Bulletin 757-
53A0112 RB.
-Within 30 days
of the Revision 1
date of Require-
ments Bulletin
757-53A0112
RB.
Before 32,500
total flight cycles.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14R intercostal
area.
Airplanes with 32,000 total
flight cycles or more at the
Revision 1 date of Require-
ments Bulletin 757-
53A0112 RB that have not
accomplished the inspec-
tions in accordance with
the original issue of Ser-
vice Bulletin 757-53A0108,
the Revision 1 of Service
Bulletin 757-53A0108, or
the original issue of Re-
quirements Bulletin 757-
53A0112 RB.
-Within 500 flight
cycles after the
Revision 1 date
of Requirements
Bulletin 757-
53A0112 RB not
to exceed 5,600
flight cycles after
the last inspec-
tion done in ac-
cordance with
the Original Is-
sue or the Revi-
sion 1 of Service
Bulletin 757-
53A0108.
Within 2,900
flight cycles after
the last inspec-
tion done in ac-
cordance with
the original issue
or the Revision 1
of Service Bul-
letin 757-
53A0108.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes with less than
39,500 total flight cycles at
the Revision 1 date of Re-
quirements Bulletin 757-
53A0112 RB that have ac-
complished the inspections
in accordance with the
original issue or the Revi-
sion 1 of Service Bulletin
757-53A0108 with no crack
found and have not accom-
plished the inspections in
the original issue of Re-
quirements Bulletin 757-
53A0112 RB.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
14 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 15

Group 1:
Table 2: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before 40,000
total flight cycles
or, within 30
days of the Revi-
sion 1 date of
Requirements
Bulletin 757-
53A0112 RB,
whichever oc-
curs later.
Within 2,900
flight cycles after
the last inspec-
tion done in ac-
cordance with
the original issue
or the Revision 1
of Service Bul-
letin 757-
53A0108.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes with 39,500 total
flight cycles or more at the
Revision 1 date of Require-
ments Bulletin 757-
53A0112 RB that have ac-
complished the inspections
in accordance with the
original issue or the Revi-
sion 1 of Service Bulletin
757-53A0108 with no crack
found and have not accom-
plished the inspections in
the original issue of Re-
quirements Bulletin 757-
53A0112 RB.
-Within 12,000
flight cycles after
the installation of
the local frame
replacement or
within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 16,000
flight cycles after
the installation of
the local frame
replacement or
before 50,000 to-
tal flight cycles.
Whichever oc-
curs first.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14R in-
tercostal area that is Boe-
ing Organization Designa-
tion Authorization (ODA)
approved via an FAA form
8100-9 and the frame web
common to the tee clip
fastener holes at stringer
S-14R has been replaced.
Whichever oc-
curs later.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14R in-
tercostal area that is not
Boeing ODA approved.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
15 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 16

Group 1:
Table 2: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a reinforcing repair
in the S-14R intercostal
area.
--Within 12,000
flight cycles after
the last Require-
ments Bulletin
757-53A0112
RB inspections.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue of Requirements
Bulletin 757-53A0112 RB
with no crack found.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 1:
ANY REINFORCING RE-
PAIR FOUND IN THE
STRINGER S-14R IN-
SPECTION AREA.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 2:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14R
INSPECTION AREA THAT
IS NOT BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9.
-Within 12,000
flight cycles after
the installation of
the local frame
replacement or
within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 16,000
flight cycles after
the installation of
the local frame
replacement or
before 50,000 to-
tal flight cycles.
Whichever oc-
curs first.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14R
INSPECTION AREA THAT
IS BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON
TO THE TEE CLIP FAS-
TENER HOLES AT
STRINGER S-14R HAS
BEEN REPLACED. Whichever oc-
curs later.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
16 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 17

Group 1:
Table 2: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
CONDITION 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND
IN THE STRINGER S-14R
INSPECTION AREA.
-Before further flight.CONDITION 5 (ACTION 1):CONDITION 5:
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
ANY CRACK FOUND.
12,000-CONDITION 5 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14R intercostal tee
clip for any crack. (a)
-Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Install fasteners common to
the frame web and S-14R
intercostal tee clip.
NO CRACK FOUND.
12,000-CONDITION 6 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14R intercostal tee
clip for any crack. (a)
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements Bulletin
757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance with Re-
quirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
17 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 18

Group 2:
Table 3: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14L intercostal
area.
Airplanes that have not ac-
complished the inspections
in accordance with the
original issue or the Revi-
sion 1 of Service Bulletin
757-53A0108 and have not
accomplished the inspec-
tions in accordance with
the original issue of Re-
quirements Bulletin 757-
53A0112 RB.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 2,600
flight cycles after
the last Service
Bulletin 757-
53A0108 inspec-
tion.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 with no crack
found and have not accom-
plished the inspections in
accordance with the origi-
nal issue of Requirements
Bulletin 757-53A0112 RB.
--Within 5,700
flight cycles after
the last Require-
ments Bulletin
757-53A0112
RB inspection.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue of Requirements
Bulletin 757-53A0112 RB
with no crack found.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 5,000
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14L in-
tercostal area that is Boe-
ing Organization Designa-
tion Authorization (ODA)
approved via an FAA form
8100-9 and the frame web
common to the tee clip
fastener holes at stringer
S-14L has been replaced.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
18 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 19

Group 2:
Table 3: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14L in-
tercostal area that is not
Boeing ODA approved.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a reinforcing repair
in the S-14L intercostal
area.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 1:
ANY REINFORCING RE-
PAIR FOUND IN THE
STRINGER S-14L INSPEC-
TION AREA.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 2:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14L
INSPECTION AREA THAT
IS NOT BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
19 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 20

Group 2:
Table 3: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 5,000
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14L
INSPECTION AREA THAT
IS BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON
TO THE TEE CLIP FAS-
TENER HOLES AT
STRINGER S-14L HAS
BEEN REPLACED.
-Before further flight.Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
CONDITION 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND
IN THE STRINGER S-14L
INSPECTION AREA.
-Before further flight.CONDITION 5 (ACTION 1):CONDITION 5:
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
ANY CRACK FOUND.
4,900-CONDITION 5 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14L intercostal tee
clip for any crack. (a)
-Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Install fasteners common to
the frame web and S-14L
intercostal tee clip.
NO CRACK FOUND.
4,900-CONDITION 6 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14L intercostal tee
clip for any crack. (a)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
20 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 21

Group 2:
Table 3: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements Bulletin
757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance with Re-
quirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Group 2:
Table 4: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14R intercostal
area.
Airplanes that have not ac-
complished the inspections
in accordance with the
original issue or the Revi-
sion 1 of Service Bulletin
757-53A0108 and have not
accomplished the inspec-
tions in accordance with
the original issue of Re-
quirements Bulletin 757-
53A0112 RB.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 2,600
flight cycles after
the last Service
Bulletin 757-
53A0108 inspec-
tion.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 with no crack
found and have not accom-
plished the inspections in
accordance with the origi-
nal issue of Requirements
Bulletin 757-53A0112 RB.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
21 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 22

Group 2:
Table 4: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 5,700
flight cycles after
the last Require-
ments Bulletin
757-53A0112
RB inspection.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue of Requirements
Bulletin 757-53A0112 RB
with no crack found.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 5,000
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14R in-
tercostal area that is Boe-
ing Organization Designa-
tion Authorization (ODA)
approved via an FAA form
8100-9 and the frame web
common to the tee clip
fastener holes at stringer
S-14R has been replaced.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14R in-
tercostal area that is not
Boeing ODA approved.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a reinforcing repair
in the S-14R intercostal
area.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
22 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 23

Group 2:
Table 4: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 1:
ANY REINFORCING RE-
PAIR FOUND IN THE
STRINGER S-14R IN-
SPECTION AREA.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 2:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14R
INSPECTION AREA THAT
IS NOT BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 5,000
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14R
INSPECTION AREA THAT
IS BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON
TO THE TEE CLIP FAS-
TENER HOLES AT
STRINGER S-14R HAS
BEEN REPLACED.
-Before further flight.Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
CONDITION 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND
IN THE STRINGER S-14R
INSPECTION AREA.
-Before further flight.CONDITION 5 (ACTION 1):CONDITION 5:
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
ANY CRACK FOUND.
4,900-CONDITION 5 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14R intercostal tee
clip for any crack. (a)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
23 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 24

Group 2:
Table 4: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Install fasteners common to
the frame web and S-14R
intercostal tee clip.
NO CRACK FOUND.
4,900-CONDITION 6 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14R intercostal tee
clip for any crack. (a)
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements Bulletin
757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance with Re-
quirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Group 3:
Table 5: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 1,300
flight cycles after
the original issue
date of Require-
ments Bulletin
757-53A0112
RB or before
16,500 total flight
cycles.
Before 10,000
total flight cycles.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14L intercostal
area.
Airplanes with less than
16,000 total flight cycles at
the original issue date of
Requirements Bulletin 757-
53A0112 RB that have not
accomplished the inspec-
tions in accordance with
the original issue or the
Revision 1 of Service Bul-
letin 757-53A0108. Whichever oc-
curs first.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
24 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 25

Group 3:
Table 5: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14L intercostal
area.
Airplanes with 16,000 total
flight cycles or more at the
original issue date of Re-
quirements Bulletin 757-
53A0112 RB that have not
accomplished the inspec-
tions in accordance with
the original issue or the
Revision 1 of Service Bul-
letin 757-53A0108.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 3,250
flight cycles after
the last Service
Bulletin 757-
53A0108 inspec-
tion.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 with no crack
found.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 6,300
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14L in-
tercostal area that is Boe-
ing Organization Designa-
tion Authorization (ODA)
approved via an FAA form
8100-9 and the frame web
common to the tee clip
fastener holes at stringer
S-14L has been replaced.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14L in-
tercostal area that is not
Boeing ODA approved.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
25 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 26

Group 3:
Table 5: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a reinforcing repair
in the S-14L intercostal
area.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 1:
ANY REINFORCING RE-
PAIR FOUND IN THE
STRINGER S-14L INSPEC-
TION AREA.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 2:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14L
INSPECTION AREA THAT
IS NOT BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 6,300
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14L
INSPECTION AREA THAT
IS BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON
TO THE TEE CLIP FAS-
TENER HOLES AT
STRINGER S-14L HAS
BEEN REPLACED.
-Before further flight.Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
CONDITION 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND
IN THE STRINGER S-14L
INSPECTION AREA.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
26 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 27

Group 3:
Table 5: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 5 (ACTION 1):CONDITION 5:
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
ANY CRACK FOUND.
6,300-CONDITION 5 (ACTION 2):
Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14L intercostal tee
clip for any crack. (a)
flight cycles.
-Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Install fasteners common to
the frame web and S-14L
intercostal tee clip.
NO CRACK FOUND.
6,300-CONDITION 6 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14L intercostal tee
clip for any crack. (a)
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements Bulletin
757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance with Re-
quirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
27 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 28

Group 3:
Table 6: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 1,300
flight cycles after
the original issue
date of Require-
ments Bulletin
757-53A0112
RB or before
16,500 total flight
cycles.
Before 10,000
total flight cycles.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14R intercostal
area.
Airplanes with less than
16,000 total flight cycles at
the original issue date of
Requirements Bulletin 757-
53A0112 RB that have not
accomplished the inspec-
tions in accordance with
the original issue or the
Revision 1 of Service Bul-
letin 757-53A0108. Whichever oc-
curs first.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14R intercostal
area.
Airplanes with 16,000 total
flight cycles or more at the
original issue date of Re-
quirements Bulletin 757-
53A0112 RB that have not
accomplished the inspec-
tions in accordance with
the original issue or the
Revision 1 of Service Bul-
letin 757-53A0108.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 3,250
flight cycles after
the last Service
Bulletin 757-
53A0108 inspec-
tion.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 with no crack
found.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 6,300
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14R in-
tercostal area that is Boe-
ing Organization Designa-
tion Authorization (ODA)
approved via an FAA form
8100-9 and the frame web
common to the tee clip
fastener holes at stringer
S-14R has been replaced.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
28 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 29

Group 3:
Table 6: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14R in-
tercostal area that is not
Boeing ODA approved.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a reinforcing repair
in the S-14R intercostal
area.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 1:
ANY REINFORCING RE-
PAIR FOUND IN THE
STRINGER S-14R IN-
SPECTION AREA.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 2:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14R
INSPECTION AREA THAT
IS NOT BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
29 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 30

Group 3:
Table 6: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 6,300
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14R
INSPECTION AREA THAT
IS BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON
TO THE TEE CLIP FAS-
TENER HOLES AT
STRINGER S-14R HAS
BEEN REPLACED.
-Before further flight.Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
CONDITION 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND
IN THE STRINGER S-14R
INSPECTION AREA.
-Before further flight.CONDITION 5 (ACTION 1):CONDITION 5:
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
ANY CRACK FOUND.
6,300-CONDITION 5 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14R intercostal tee
clip for any crack. (a)
-Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Install fasteners common to
the frame web and S-14R
intercostal tee clip.
NO CRACK FOUND.
6,300-CONDITION 6 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14R intercostal tee
clip for any crack. (a)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
30 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 31

Group 3:
Table 6: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements Bulletin
757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance with Re-
quirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Group 4:
Table 7: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14L intercostal
area.
Airplanes that have not ac-
complished the inspections
in accordance with the
original issue or the Revi-
sion 1 of Service Bulletin
757-53A0108.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 2,400
flight cycles after
the last Service
Bulletin 757-
53A0108 inspec-
tion.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 with no crack
found.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
31 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 32

Group 4:
Table 7: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 8,600
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14L in-
tercostal area that is Boe-
ing Organization Designa-
tion Authorization (ODA)
approved via an FAA form
8100-9 and the frame web
common to the tee clip
fastener holes at stringer
S-14L has been replaced.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14L in-
tercostal area that is not
Boeing ODA approved.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a reinforcing repair
in the S-14L intercostal
area.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 1:
ANY REINFORCING RE-
PAIR FOUND IN THE
STRINGER S-14L INSPEC-
TION AREA.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
32 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 33

Group 4:
Table 7: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 2:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14L
INSPECTION AREA THAT
IS NOT BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 8,600
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14L
INSPECTION AREA THAT
IS BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON
TO THE TEE CLIP FAS-
TENER HOLES AT
STRINGER S-14L HAS
BEEN REPLACED.
-Before further flight.Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
CONDITION 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND
IN THE STRINGER S-14L
INSPECTION AREA.
-Before further flight.CONDITION 5 (ACTION 1):CONDITION 5:
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
ANY CRACK FOUND.
8,600-CONDITION 5 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14L intercostal tee
clip for any crack. (a)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
33 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 34

Group 4:
Table 7: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Install fasteners common to
the frame web and S-14L
intercostal tee clip.
NO CRACK FOUND.
8,600-CONDITION 6 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14L intercostal tee
clip for any crack. (a)
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements Bulletin
757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance with Re-
quirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Group 4:
Table 8: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14R intercostal
area.
Airplanes that have not ac-
complished the inspections
in accordance with the
original issue or the Revi-
sion 1 of Service Bulletin
757-53A0108.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 2,400
flight cycles after
the last Service
Bulletin 757-
53A0108 inspec-
tion.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 with no crack
found.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
34 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 35

Group 4:
Table 8: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 8,600
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14R in-
tercostal area that is Boe-
ing Organization Designa-
tion Authorization (ODA)
approved via an FAA form
8100-9 and the frame web
common to the tee clip
fastener holes at stringer
S-14R has been replaced.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14R in-
tercostal area that is not
Boeing ODA approved.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a reinforcing repair
in the S-14R intercostal
area.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 1:
ANY REINFORCING RE-
PAIR FOUND IN THE
STRINGER S-14R IN-
SPECTION AREA.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
35 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 36

Group 4:
Table 8: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 2:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14R
INSPECTION AREA THAT
IS NOT BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 8,600
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14R
INSPECTION AREA THAT
IS BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON
TO THE TEE CLIP FAS-
TENER HOLES AT
STRINGER S-14R HAS
BEEN REPLACED.
-Before further flight.Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
CONDITION 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND
IN THE STRINGER S-14R
INSPECTION AREA.
-Before further flight.CONDITION 5 (ACTION 1):CONDITION 5:
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
ANY CRACK FOUND.
8,600-CONDITION 5 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14R intercostal tee
clip for any crack. (a)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
36 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 37

Group 4:
Table 8: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Install fasteners common to
the frame web and S-14R
intercostal tee clip.
NO CRACK FOUND.
8,600-CONDITION 6 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14R intercostal tee
clip for any crack. (a)
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements Bulletin
757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance with Re-
quirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Group 5:
Table 9: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14L intercostal
area.
Airplanes that have not ac-
complished the inspections
in accordance with the
original issue or the Revi-
sion 1 of Service Bulletin
757-53A0108.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 1,900
flight cycles after
the last Service
Bulletin 757-
53A0108 inspec-
tion.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 with no crack
found.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
37 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 38

Group 5:
Table 9: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 3,000
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14L in-
tercostal area that is Boe-
ing Organization Designa-
tion Authorization (ODA)
approved via an FAA form
8100-9 and the frame web
common to the tee clip
fastener holes at stringer
S-14L has been replaced.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14L in-
tercostal area that is not
Boeing ODA approved.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a reinforcing repair
in the S-14L intercostal
area.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 1:
ANY REINFORCING RE-
PAIR FOUND IN THE
STRINGER S-14L INSPEC-
TION AREA.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
38 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 39

Group 5:
Table 9: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 2:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14L
INSPECTION AREA THAT
IS NOT BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 3,000
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14L
INSPECTION AREA THAT
IS BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON
TO THE TEE CLIP FAS-
TENER HOLES AT
STRINGER S-14L HAS
BEEN REPLACED.
-Before further flight.Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14L intercostal tee clip for
any crack.
CONDITION 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND
IN THE STRINGER S-14L
INSPECTION AREA.
-Before further flight.CONDITION 5 (ACTION 1):CONDITION 5:
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
ANY CRACK FOUND.
3,300-CONDITION 5 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14L intercostal tee
clip for any crack. (a)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
39 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 40

Group 5:
Table 9: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Install fasteners common to
the frame web and S-14L
intercostal tee clip.
NO CRACK FOUND.
3,300-CONDITION 6 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14L intercostal tee
clip for any crack. (a)
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements Bulletin
757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance with Re-
quirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Group 5:
Table 10: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Do a general visual inspec-
tion for any reinforcing re-
pair or local frame replace-
ment on the STA 1640
fuselage frame at the
stringer S-14R intercostal
area.
Airplanes that have not ac-
complished the inspections
in accordance with the
original issue or the Revi-
sion 1 of Service Bulletin
757-53A0108.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 1,900
flight cycles after
the last Service
Bulletin 757-
53A0108 inspec-
tion.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 with no crack
found.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
40 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 41

Group 5:
Table 10: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 3,000
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14R in-
tercostal area that is Boe-
ing Organization Designa-
tion Authorization (ODA)
approved via an FAA form
8100-9 and the frame web
common to the tee clip
fastener holes at stringer
S-14R has been replaced.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a local frame re-
placement in the S-14R in-
tercostal area that is not
Boeing ODA approved.
--Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
Airplanes that have accom-
plished the inspections in
accordance with the origi-
nal issue or the Revision 1
of Service Bulletin 757-
53A0108 and have in-
stalled a reinforcing repair
in the S-14R intercostal
area.
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 1:
ANY REINFORCING RE-
PAIR FOUND IN THE
STRINGER S-14R IN-
SPECTION AREA.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
41 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 42

Group 5:
Table 10: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.Contact The Boeing Compa-
ny for alternative inspec-
tion(s) and do the inspec-
tion(s) and any corrective
actions as applicable.
CONDITION 2:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14R
INSPECTION AREA THAT
IS NOT BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9.
-Within 500 flight
cycles after the
original issue
date of Require-
ments Bulletin
757-53A0112
RB.
Within 3,000
flight cycles after
the installation of
the local frame
replacement.
Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
CONDITION 3:
ANY LOCAL FRAME RE-
PLACEMENT FOUND IN
THE STRINGER S-14R
INSPECTION AREA THAT
IS BOEING ODA AP-
PROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON
TO THE TEE CLIP FAS-
TENER HOLES AT
STRINGER S-14R HAS
BEEN REPLACED.
-Before further flight.Do an open hole HFEC in-
spection of the STA 1640
fuselage frame web fasten-
er holes common to the S-
14R intercostal tee clip for
any crack.
CONDITION 4:
NO REINFORCING RE-
PAIR OR LOCAL FRAME
REPLACEMENT FOUND
IN THE STRINGER S-14R
INSPECTION AREA.
-Before further flight.CONDITION 5 (ACTION 1):CONDITION 5:
Contact The Boeing Compa-
ny for repair instructions
and do the repair.
ANY CRACK FOUND.
3,300-CONDITION 5 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14R intercostal tee
clip for any crack. (a)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
42 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 43

Group 5:
Table 10: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 6 (ACTION 1):CONDITION 6:
Install fasteners common to
the frame web and S-14R
intercostal tee clip.
NO CRACK FOUND.
3,300-CONDITION 6 (ACTION 2):
flight cycles.Repeat the open hole
HFEC inspection of the STA
1640 fuselage frame web
fastener holes common to
the S-14R intercostal tee
clip for any crack. (a)
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements Bulletin
757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance with Re-
quirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
4. APPROVAL
This Requirements Bulletin was examined by the Federal Aviation Administration (FAA). The changes
specified in this document comply with the applicable regulations and are FAA approved, as well as European
Union Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in this Requirements Bulletin effectivity. This document and its approval were based on the
airplane in its original Boeing delivery configuration or as modified by other Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected by
this Requirements Bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this Requirements Bulletin.
In addition, the Manager of the FAA Los Angeles ACO Branch approves accomplishment of the inspection
and actions defined in this Requirements Bulletin revision as an alternative method of compliance to
accomplishing the requirements of paragraph (g)(1) of AD 2019-23-06. All provisions of AD 2019-23-06
that are not specifically referenced in the above statement remain fully applicable and must be complied
with accordingly.
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REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 44

Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
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REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT
BLANK PAGE

### Page 45

5.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF
METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED
MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE
BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES
CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE.
CAUTION
NOTE: 1. This is an Enhanced Required for Compliance document. There will be a separate
Service Bulletin (SB) and a separate Requirements Bulletin (RB). If an RB is mandated
by an Airworthiness Directive (AD), then all applicable requirements specified in the
RB must be done. For the related SB, some locations are marked RC Start and RC
End to identify the requirements that are restated from the RB. For the related SB,
the areas between RC Start and RC End, including sub-steps and any figures
identified between RC Start and RC End, must be done to comply with the AD.
Therefore, an Alternative Method of Compliance (AMOC) is required for any deviations
to steps between RC Start and RC End, including substeps and identified figures.
For the related SB, the steps not between RC Start and RC End 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
steps between RC Start and RC End, including sub-steps and identified figures, can
still be done as specified, and the airplane can be put back in an airworthy condition.
Figures not required for compliance are omitted from the RB.
2. This is an Enhanced Required for Compliance document. The Boeing processes
used to create the Service Bulletin (SB) and the Requirements Bulletin (RB) ensure
that the information between "RC Start" and "RC End" in the SB are identical to the
information in the same sections (Compliance, Work Instructions...) of the RB which
the SB refers to as the related document.
3. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
4. 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).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
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REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 46

— Values for engine maintenance tasks are included in Chapter 70 of 757
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
5. 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.
6. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
7. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure or irregularity.
This level of inspection is made from within touching distance, unless otherwise
specified. A mirror may be necessary to enhance visual access to all exposed surfaces
in the inspection area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may
require removal or opening of access panels or doors. Stands, ladders or platforms
may be required to gain proximity to the area being checked. Basic cleaning may be
required to ensure appropriate visibility.
8. 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 or an OPTION,
do all of the ACTION numbers for that CONDITION or OPTION.
9. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed to adjust
fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01
for alternate full threaded fasteners (screws) needed for installation in this service
bulletin.
10. 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.
B. WORK INSTRUCTIONS
Actions Required for Compliance:
1. Requirements
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REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 47

Group 1:
Table 1: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
DO PART 1: OPEN AC-
CESS.
-Do a general visual inspection
for any reinforcing repair or local
frame replacement on the STA
1640 fuselage frame at the
stringer S-14L intercostal area.
Airplanes with less than 32,000
total flight cycles at the Revision
1 date of Requirements Bulletin
757-53A0112 RB that have not
accomplished the inspections in
accordance with the original is-
sue of Service Bulletin 757-
53A0108, the Revision 1 of
Service Bulletin 757-53A0108,
or the original issue of Require-
ments Bulletin 757-53A0112
RB.
-FIGURE 1
DO PART 1: OPEN AC-
CESS.
-Do a general visual inspection
for any reinforcing repair or local
frame replacement on the STA
1640 fuselage frame at the
stringer S-14L intercostal area.
Airplanes with 32,000 total flight
cycles or more at the Revision
1 date of Requirements Bulletin
757-53A0112 RB that have not
accomplished the inspections in
accordance with the original is-
sue of Service Bulletin 757-
53A0108, the Revision 1 of
Service Bulletin 757-53A0108,
or the original issue of Require-
ments Bulletin 757-53A0112
RB.
-FIGURE 1
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14L intercostal tee
clip for any crack.
Airplanes with less than 39,500
total flight cycles at the Revision
1 date of Requirements Bulletin
757-53A0112 RB that have ac-
complished the inspections in
accordance with the original is-
sue or the Revision 1 of Service
Bulletin 757-53A0108 with no
crack found and have not ac-
complished the inspections in
the original issue of Require-
ments Bulletin 757-53A0112
RB.
-FIGURE 3
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
47 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 48

Group 1:
Table 1: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14L intercostal tee
clip for any crack.
Airplanes with 39,500 total flight
cycles or more at the Revision
1 date of Requirements Bulletin
757-53A0112 RB that have ac-
complished the inspections in
accordance with the original is-
sue or the Revision 1 of Service
Bulletin 757-53A0108 with no
crack found and have not ac-
complished the inspections in
the original issue of Require-
ments Bulletin 757-53A0112
RB.
-FIGURE 3
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14L intercostal tee
clip for any crack.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a local frame replace-
ment in the S-14L intercostal
area that is Boeing Organization
Designation Authorization
(ODA) approved via an FAA
form 8100-9 and the frame web
common to the tee clip fastener
holes at stringer S-14L has
been replaced.
-FIGURE 3
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a local frame replace-
ment in the S-14L intercostal
area that is not Boeing ODA
approved.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
48 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 49

Group 1:
Table 1: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a reinforcing repair in the
S-14L intercostal area.
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14L intercostal tee
clip for any crack.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue of
Requirements Bulletin 757-
53A0112 RB with no crack
found.
-FIGURE 3
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
CONDITION 1:
ANY REINFORCING REPAIR
FOUND IN THE STRINGER S-
14L INSPECTION AREA.
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
CONDITION 2:
ANY LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14L INSPEC-
TION AREA THAT IS NOT
BOEING ODA APPROVED VIA
AN FAA FORM 8100-9.
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14L intercostal tee
clip for any crack.
CONDITION 3:
ANY LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14L INSPEC-
TION AREA THAT IS BOEING
ODA APPROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON TO
THE TEE CLIP FASTENER
HOLES AT STRINGER S-14L
HAS BEEN REPLACED.
-FIGURE 3
Export Controlled ECCN: 9E991
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Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
49 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 50

Group 1:
Table 1: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14L intercostal tee
clip for any crack.
CONDITION 4:
NO REINFORCING REPAIR
OR LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14L INSPEC-
TION AREA.
-FIGURE 3
--CONDITION 5 (ACTION 1):CONDITION 5:
ANY CRACK FOUND. Contact The Boeing Company
for repair instructions and do the
repair.
DO PART 2: CLOSE AC-
CESS.
-
DO PART 1: OPEN AC-
CESS.
-CONDITION 5 (ACTION 2):
Repeat the open hole HFEC in-
spection of the STA 1640 fuse-
lage frame web fastener holes
common to the S-14L intercostal
tee clip for any crack. (a)
-FIGURE 3
-FIGURE 5CONDITION 6 (ACTION 1):CONDITION 6:
NO CRACK FOUND. Install fasteners common to the
frame web and S-14L intercostal
tee clip.
DO PART 2: CLOSE AC-
CESS.
-
DO PART 1: OPEN AC-
CESS.
-CONDITION 6 (ACTION 2):
Repeat the open hole HFEC in-
spection of the STA 1640 fuse-
lage frame web fastener holes
common to the S-14L intercostal
tee clip for any crack. (a)
-FIGURE 3
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements
Bulletin 757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance
with Requirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
50 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 51

Group 1:
Table 2: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
DO PART 1: OPEN AC-
CESS.
-Do a general visual inspection
for any reinforcing repair or local
frame replacement on the STA
1640 fuselage frame at the
stringer S-14R intercostal area.
Airplanes with less than 32,000
total flight cycles at the Revision
1 date of Requirements Bulletin
757-53A0112 RB that have not
accomplished the inspections in
accordance with the original is-
sue of Service Bulletin 757-
53A0108, the Revision 1 of
Service Bulletin 757-53A0108,
or the original issue of Require-
ments Bulletin 757-53A0112
RB.
-FIGURE 2
DO PART 1: OPEN AC-
CESS.
-Do a general visual inspection
for any reinforcing repair or local
frame replacement on the STA
1640 fuselage frame at the
stringer S-14R intercostal area.
Airplanes with 32,000 total flight
cycles or more at the Revision
1 date of Requirements Bulletin
757-53A0112 RB that have not
accomplished the inspections in
accordance with the original is-
sue of Service Bulletin 757-
53A0108, the Revision 1 of
Service Bulletin 757-53A0108,
or the original issue of Require-
ments Bulletin 757-53A0112
RB.
-FIGURE 2
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14R intercostal tee
clip for any crack.
Airplanes with less than 39,500
total flight cycles at the Revision
1 date of Requirements Bulletin
757-53A0112 RB that have ac-
complished the inspections in
accordance with the original is-
sue or the Revision 1 of Service
Bulletin 757-53A0108 with no
crack found and have not ac-
complished the inspections in
the original issue of Require-
ments Bulletin 757-53A0112
RB.
-FIGURE 4
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
51 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 52

Group 1:
Table 2: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14R intercostal tee
clip for any crack.
Airplanes with 39,500 total flight
cycles or more at the Revision
1 date of Requirements Bulletin
757-53A0112 RB that have ac-
complished the inspections in
accordance with the original is-
sue or the Revision 1 of Service
Bulletin 757-53A0108 with no
crack found and have not ac-
complished the inspections in
the original issue of Require-
ments Bulletin 757-53A0112
RB.
-FIGURE 4
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14R intercostal tee
clip for any crack.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a local frame replace-
ment in the S-14R intercostal
area that is Boeing Organization
Designation Authorization
(ODA) approved via an FAA
form 8100-9 and the frame web
common to the tee clip fastener
holes at stringer S-14R has
been replaced.
-FIGURE 4
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a local frame replace-
ment in the S-14R intercostal
area that is not Boeing ODA
approved.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
52 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 53

Group 1:
Table 2: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a reinforcing repair in the
S-14R intercostal area.
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14R intercostal tee
clip for any crack.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue of
Requirements Bulletin 757-
53A0112 RB with no crack
found.
-FIGURE 4
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
CONDITION 1:
ANY REINFORCING REPAIR
FOUND IN THE STRINGER S-
14R INSPECTION AREA.
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
CONDITION 2:
ANY LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14R INSPEC-
TION AREA THAT IS NOT
BOEING ODA APPROVED VIA
AN FAA FORM 8100-9.
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14R intercostal tee
clip for any crack.
CONDITION 3:
ANY LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14R INSPEC-
TION AREA THAT IS BOEING
ODA APPROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON TO
THE TEE CLIP FASTENER
HOLES AT STRINGER S-14R
HAS BEEN REPLACED.
-FIGURE 4
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
53 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 54

Group 1:
Table 2: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14R intercostal tee
clip for any crack.
CONDITION 4:
NO REINFORCING REPAIR
OR LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14R INSPEC-
TION AREA.
-FIGURE 4
--CONDITION 5 (ACTION 1):CONDITION 5:
ANY CRACK FOUND. Contact The Boeing Company
for repair instructions and do the
repair.
DO PART 2: CLOSE AC-
CESS.
-
DO PART 1: OPEN AC-
CESS.
-CONDITION 5 (ACTION 2):
Repeat the open hole HFEC in-
spection of the STA 1640 fuse-
lage frame web fastener holes
common to the S-14R inter-
costal tee clip for any crack. (a)
-FIGURE 4
-FIGURE 6CONDITION 6 (ACTION 1):CONDITION 6:
NO CRACK FOUND. Install fasteners common to the
frame web and S-14R inter-
costal tee clip.
DO PART 2: CLOSE AC-
CESS.
-
DO PART 1: OPEN AC-
CESS.
-CONDITION 6 (ACTION 2):
Repeat the open hole HFEC in-
spection of the STA 1640 fuse-
lage frame web fastener holes
common to the S-14R inter-
costal tee clip for any crack. (a)
-FIGURE 4
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements
Bulletin 757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance
with Requirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
54 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 55

Group 2:
Table 3: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
DO PART 1: OPEN AC-
CESS.
-Do a general visual inspection
for any reinforcing repair or local
frame replacement on the STA
1640 fuselage frame at the
stringer S-14L intercostal area.
Airplanes that have not accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have not
accomplished the inspections in
accordance with the original is-
sue of Requirements Bulletin
757-53A0112 RB.
-FIGURE 1
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14L intercostal tee
clip for any crack.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 with no crack
found and have not accom-
plished the inspections in accor-
dance with the original issue of
Requirements Bulletin 757-
53A0112 RB.
-FIGURE 3
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14L intercostal tee
clip for any crack.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue of
Requirements Bulletin 757-
53A0112 RB with no crack
found.
-FIGURE 3
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14L intercostal tee
clip for any crack.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a local frame replace-
ment in the S-14L intercostal
area that is Boeing Organization
Designation Authorization
(ODA) approved via an FAA
form 8100-9 and the frame web
common to the tee clip fastener
holes at stringer S-14L has
been replaced.
-FIGURE 3
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
55 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 56

Group 2:
Table 3: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a local frame replace-
ment in the S-14L intercostal
area that is not Boeing ODA
approved.
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a reinforcing repair in the
S-14L intercostal area.
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
CONDITION 1:
ANY REINFORCING REPAIR
FOUND IN THE STRINGER S-
14L INSPECTION AREA.
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
CONDITION 2:
ANY LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14L INSPEC-
TION AREA THAT IS NOT
BOEING ODA APPROVED VIA
AN FAA FORM 8100-9.
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14L intercostal tee
clip for any crack.
CONDITION 3:
ANY LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14L INSPEC-
TION AREA THAT IS BOEING
ODA APPROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON TO
THE TEE CLIP FASTENER
HOLES AT STRINGER S-14L
HAS BEEN REPLACED.
-FIGURE 3
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
56 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 57

Group 2:
Table 3: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14L
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14L intercostal tee
clip for any crack.
CONDITION 4:
NO REINFORCING REPAIR
OR LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14L INSPEC-
TION AREA.
-FIGURE 3
--CONDITION 5 (ACTION 1):CONDITION 5:
ANY CRACK FOUND. Contact The Boeing Company
for repair instructions and do the
repair.
DO PART 2: CLOSE AC-
CESS.
-
DO PART 1: OPEN AC-
CESS.
-CONDITION 5 (ACTION 2):
Repeat the open hole HFEC in-
spection of the STA 1640 fuse-
lage frame web fastener holes
common to the S-14L intercostal
tee clip for any crack. (a)
-FIGURE 3
-FIGURE 5CONDITION 6 (ACTION 1):CONDITION 6:
NO CRACK FOUND. Install fasteners common to the
frame web and S-14L intercostal
tee clip.
DO PART 2: CLOSE AC-
CESS.
-
DO PART 1: OPEN AC-
CESS.
-CONDITION 6 (ACTION 2):
Repeat the open hole HFEC in-
spection of the STA 1640 fuse-
lage frame web fastener holes
common to the S-14L intercostal
tee clip for any crack. (a)
-FIGURE 3
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements
Bulletin 757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance
with Requirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
57 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 58

Group 2:
Table 4: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
DO PART 1: OPEN AC-
CESS.
-Do a general visual inspection
for any reinforcing repair or local
frame replacement on the STA
1640 fuselage frame at the
stringer S-14R intercostal area.
Airplanes that have not accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have not
accomplished the inspections in
accordance with the original is-
sue of Requirements Bulletin
757-53A0112 RB.
-FIGURE 2
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14R intercostal tee
clip for any crack.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 with no crack
found and have not accom-
plished the inspections in accor-
dance with the original issue of
Requirements Bulletin 757-
53A0112 RB.
-FIGURE 4
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14R intercostal tee
clip for any crack.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue of
Requirements Bulletin 757-
53A0112 RB with no crack
found.
-FIGURE 4
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14R intercostal tee
clip for any crack.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a local frame replace-
ment in the S-14R intercostal
area that is Boeing Organization
Designation Authorization
(ODA) approved via an FAA
form 8100-9 and the frame web
common to the tee clip fastener
holes at stringer S-14R has
been replaced.
-FIGURE 4
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
58 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 59

Group 2:
Table 4: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a local frame replace-
ment in the S-14R intercostal
area that is not Boeing ODA
approved.
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
Airplanes that have accom-
plished the inspections in accor-
dance with the original issue or
the Revision 1 of Service Bul-
letin 757-53A0108 and have in-
stalled a reinforcing repair in the
S-14R intercostal area.
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
CONDITION 1:
ANY REINFORCING REPAIR
FOUND IN THE STRINGER S-
14R INSPECTION AREA.
--Contact The Boeing Company
for alternative inspection(s) and
do the inspection(s) and any
corrective actions as applicable.
CONDITION 2:
ANY LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14R INSPEC-
TION AREA THAT IS NOT
BOEING ODA APPROVED VIA
AN FAA FORM 8100-9.
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14R intercostal tee
clip for any crack.
CONDITION 3:
ANY LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14R INSPEC-
TION AREA THAT IS BOEING
ODA APPROVED VIA AN FAA
FORM 8100-9 AND THE
FRAME WEB COMMON TO
THE TEE CLIP FASTENER
HOLES AT STRINGER S-14R
HAS BEEN REPLACED.
-FIGURE 4
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
59 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

### Page 60

Group 2:
Table 4: General Visual and Open Hole High Frequency Eddy Current (HFEC) Inspections of the Body
Station (STA) 1640 Fuselage Frame at S-14R
Refer to the listed proce-
dures in SB 757-53A0112
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of
Compliance
ActionCondition
DO PART 1: OPEN AC-
CESS.
-Do an open hole HFEC inspec-
tion of the STA 1640 fuselage
frame web fastener holes com-
mon to the S-14R intercostal tee
clip for any crack.
CONDITION 4:
NO REINFORCING REPAIR
OR LOCAL FRAME REPLACE-
MENT FOUND IN THE
STRINGER S-14R INSPEC-
TION AREA.
-FIGURE 4
--CONDITION 5 (ACTION 1):CONDITION 5:
ANY CRACK FOUND. Contact The Boeing Company
for repair instructions and do the
repair.
DO PART 2: CLOSE AC-
CESS.
-
DO PART 1: OPEN AC-
CESS.
-CONDITION 5 (ACTION 2):
Repeat the open hole HFEC in-
spection of the STA 1640 fuse-
lage frame web fastener holes
common to the S-14R inter-
costal tee clip for any crack. (a)
-FIGURE 4
-FIGURE 6CONDITION 6 (ACTION 1):CONDITION 6:
NO CRACK FOUND. Install fasteners common to the
frame web and S-14R inter-
costal tee clip.
DO PART 2: CLOSE AC-
CESS.
-
DO PART 1: OPEN AC-
CESS.
-CONDITION 6 (ACTION 2):
Repeat the open hole HFEC in-
spection of the STA 1640 fuse-
lage frame web fastener holes
common to the S-14R inter-
costal tee clip for any crack. (a)
-FIGURE 4
(a) In areas with reinforcing repairs or local frame replacements installed common to the Requirements
Bulletin 757-53A0112 RB inspection area, it is not required to do the repeat inspections in accordance
with Requirements Bulletin 757-53A0112 RB provided the repair meets all the following criteria:
1. The repair is installed after the Original Issue date of Requirements Bulletin 757-53A0112 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9 which states that the repeat inspection program for the repair or local frame
replacement is an alternate means of compliance with the Requirements Bulletin 757-53A0112
RB inspections in the repair area.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: November 16, 2018
757-53A0112 RBRevision 1: June 17, 2022
60 of 90
REQUIREMENTS BULLETIN 757-53A0112
ALERTALERT

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