# Boeing Alert Requirements Bulletin 757-53A0128 RB: No revision named

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- Title as filed: RB-757-53A0128-00--
- Pages: 30
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### Page 1

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0128 RB
Original Issue:
September 17, 2025
ATA System: 5310
SUBJECT: FUSELAGE - Frames - STA 640 to STA 840 Frame Inner Chord Between Stringer
S-21 and S-23 Inspection
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 © 2025 The Boeing Company
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: September 17, 2025
757-53A0128 RB
1 of 30
4.0

### Page 2

Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
2 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT
BLANK PAGE

### Page 3

Table of Contents
1. EFFECTIVITY .
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
FIGURE 1: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21L TO S-23L - GENERAL VISUAL
INSPECTION (GVI) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
FIGURE 2: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21L TO S-23L - FRAME
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
FIGURE 3: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21R TO S-23R - GENERAL
VISUAL INSPECTION (GVI) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
FIGURE 4: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21R TO S-23R - FRAME
INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
3 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 4

Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
4 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT
BLANK PAGE

### Page 5

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0128 RB
Original Issue:
September 17, 2025
ATA System: 5310
SUBJECT: FUSELAGE - Frames - STA 640 to STA 840 Frame Inner Chord Between Stringer
S-21 and S-23 Inspection
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
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 Airplane(s), line number(s) 2-14, 16-17, 20-43, 46, 49-52,
54, 57-58, 61, 63-66, 71, 73-81, 84-85, 87, 89-102, 111-118, 120, 123, 126, 128-129, 133-135,
138, 144-146, 148, 150-151, 153-155, 157-161, 163-164, 166-168, 171, 173-175, 177, 179, 183,
187, 198, 200-203, 205-207, 210-211, 214, 216-218, 221-225, 227-230, 232-233, 238-239, 241,
244, 246-247, 251-252, 254, 256, 261-266, 270-272, 277-279, 282, 284, 286-288, 290-294,
298-299, 305-307, 310-313, 319-320, 323, 329, 331, 335, 338-339, 341-343, 346-347, 349,
352-355, 358-359, 361-364, 366-367, 372-374, 376-377, 380-381, 385-386, 389, 392-394, 396,
401, 405-406, 413-416, 420-421, 426-427, 429-431, 434-435, 439, 441-442, 445, 447-449, 453-456,
461-462, 465-467, 469, 475-476, 479-480, 487-488, 490, 492, 494, 497-502, 506, 508, 512-513,
515-516, 518, 524-525, 527, 531, 533-535, 539-540, 542-544, 546, 550-552, 554, 556, 559,
563-564, 567, 570-571, 584, 586, 589, 595, 601, 605, 607, 609-610, 613, 615, 622, 624, 630, 665,
669, 674, 685, 698, 718-719, 724, 727, 747, 751, 762, 773, 784-785, 789, 793-794, 798, 841, 844,
864, 867, 871-873, 877 in 1 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.
The Variable Numbers and Group Information for the applicable airplanes is given below.
DESCRIPTIONCONFIGURATIONGROUP
757-200 airplanes equipped with Air Cargo Equipment (ACE) Cargo
Loader provisions in the Forward Cargo Bay.
- 1
Airplane Models:
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
5 of 30

### Page 6

757-200
GroupVariable Number
1NA002 - NA028
1NA191 - NA199
1NA201 - NA239
1NA301 - NA305
1NA341 - NA352
1NA391 - NA399
1NA501 - NA584
1NB021 - NB023
GroupVariable Number
1NB036 - NB041
1NB051 - NB053
1NB061 - NB070
1NB261 - NB264
1NB291 - NB299
1NB301 - NB302
1NB501 - NB514
1NB581 - NB583
GroupVariable Number
1ND221
1ND224 - ND225
1NE011 - NE088
1NE091 - NE094
1NE141 - NE150
1NT401 - NT409
1NT791 - NT796
--
B.
Spares Affected
None.
2. CONCURRENT REQUIREMENTS
None.
3. COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
Requirements Bulletin 757-53A0128 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 757-53A0128 RB mandatory.
Accomplish the required action(s), based on the applicable condition(s) in Table 1 through Table 2, in
accordance with Accomplishment Instructions.
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.
Table 1: Fuselage - Frames STA 640 to STA 840, Stringer S-21L to S-23L - Frame Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0128 RB.
Before 37,000
total flight cy-
cles.
Do a General Visual Inspection
(GVI) or maintenance records
check for any repair of the
frames from STA 640 to STA
840, between stringer S-21L
and S-23L.
All airplanes with less
than 42,000 total flight
cycles as of the Original
Issue date of Require-
ments Bulletin 757-
53A0128 RB.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
6 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 7

Table 1: Fuselage - Frames STA 640 to STA 840, Stringer S-21L to S-23L - Frame Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 1,500 flight cycles after
the Original Issue date of Re-
quirements Bulletin 757-
53A0128 RB.
Do a GVI or maintenance
records check for any repair of
the frames from STA 640 to
STA 840, between stringer S-
21L and S-23L.
All airplanes with more
than or equal to 42,000
total flight cycles as of
the Original Issue date
of Requirements Bul-
letin 757-53A0128 RB.
-For airplanes with less than
42,000 total flight cycles as of
the Original Issue date of Re-
quirements Bulletin 757-
53A0128 RB: Before 37,000 to-
tal flight cycles, or within 3,000
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB,
whichever occurs later.
CONDITION 1 (ACTION 1):
Contact The Boeing Company
for alternative inspections to
Requirements Bulletin 757-
53A0128 RB and do the inspec-
tions and applicable on-condi-
tion actions at each repair loca-
tion.
CONDITION 1: ANY
REPAIR FOUND.
For airplanes with more than or
equal to 42,000 total flight cy-
cles as of the Original Issue
date of Requirements Bulletin
757-53A0128 RB: Within 1,500
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB.
-For airplanes with less than
42,000 total flight cycles as of
the Original Issue date of Re-
quirements Bulletin 757-
53A0128 RB: Before 37,000 to-
tal flight cycles, or within 3,000
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB,
whichever occurs later.
CONDITION 1 (ACTION 2): Do
a High Frequency Eddy Current
(HFEC) surface inspection of
the frames from STA 640 to
STA 840, between stringer S-
21L and S-23L for any crack at
any location without a repair. (a)
For airplanes with more than or
equal to 42,000 total flight cy-
cles as of the Original Issue
date of Requirements Bulletin
757-53A0128 RB: Within 1,500
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
7 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 8

Table 1: Fuselage - Frames STA 640 to STA 840, Stringer S-21L to S-23L - Frame Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 1.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do the
repair.
CONDITION 1.1: ANY
CRACK FOUND.
6,000 flight cycles.-CONDITION 1.1 (ACTION 2):
Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21L and S-23L for
any crack. (a)
6,000 flight cycles.-Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21L and S-23L for
any crack. (a)
CONDITION 1.2: NO
CRACK FOUND.
-For airplanes with less than
42,000 total flight cycles as of
the Original Issue date of Re-
quirements Bulletin 757-
53A0128 RB: Before 37,000 to-
tal flight cycles, or within 3,000
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB,
whichever occurs later.
Do a HFEC surface inspection
of the frames from STA 640 to
STA 840, between stringer S-
21L and S-23L for any crack.
CONDITION 2: NO
REPAIR FOUND.
For airplanes with more than or
equal to 42,000 total flight cy-
cles as of the Original Issue
date of Requirements Bulletin
757-53A0128 RB: Within 1,500
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB.
-Before further flight.CONDITION 2.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do the
repair.
CONDITION 2.1: ANY
CRACK FOUND.
6,000 flight cycles.-CONDITION 2.1 (ACTION 2):
Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21L and S-23L for
any crack. (a)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
8 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 9

Table 1: Fuselage - Frames STA 640 to STA 840, Stringer S-21L to S-23L - Frame Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time
(Whichever Occurs Later)
ActionCondition
6,000 flight cycles.-Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21L and S-23L for
any crack. (a)
CONDITION 2.2: NO
CRACK FOUND.
(a) It is not required to do the HFEC inspections in accordance with Requirements Bulletin 757-53A0128 RB
in the repair affected area(s) if the repair(s) meet all of the conditions that follow:
1.
The repair inspection plan was approved after the Original Issue date of Requirements Bulletin
757-53A0128 RB.
2. The repair plan is approved by the Boeing Organization Designation Authorization (ODA) via a
FAA Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area(s), states the post repair inspection
plan for the repair affected area(s), and approves the inspection plan as an alternative inspection
method to the inspection(s) in Requirements Bulletin 757-53A0128 RB.
Table 2: Fuselage - Frames STA 640 to STA 840, Stringer S-21R to S-23R - Frame Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0128 RB.
Before 37,000
total flight cy-
cles.
Do a General Visual Inspection
(GVI) or maintenance records
check for any repair of the
frames from STA 640 to STA
840, between stringer S-21R
and S-23R.
All airplanes with less
than 42,000 total flight
cycles as of the Original
Issue date of Require-
ments Bulletin 757-
53A0128 RB.
-Within 1,500 flight cycles after
the Original Issue date of Re-
quirements Bulletin 757-
53A0128 RB.
Do a GVI or maintenance
records check for any repair of
the frames from STA 640 to
STA 840, between stringer S-
21R and S-23R.
All airplanes with more
than or equal to 42,000
total flight cycles as of
the Original Issue date
of Requirements Bul-
letin 757-53A0128 RB.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
9 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 10

Table 2: Fuselage - Frames STA 640 to STA 840, Stringer S-21R to S-23R - Frame Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-For airplanes with less than
42,000 total flight cycles as of
the Original Issue date of Re-
quirements Bulletin 757-
53A0128 RB: Before 37,000 to-
tal flight cycles, or within 3,000
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB,
whichever occurs later.
CONDITION 3 (ACTION 1):
Contact The Boeing Company
for alternative inspections to
Requirements Bulletin 757-
53A0128 RB and do the inspec-
tions and applicable on-condi-
tion actions at each repair loca-
tion.
CONDITION 3: ANY
REPAIR FOUND.
For airplanes with more than or
equal to 42,000 total flight cy-
cles as of the Original Issue
date of Requirements Bulletin
757-53A0128 RB: Within 1,500
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB.
-For airplanes with less than
42,000 total flight cycles as of
the Original Issue date of Re-
quirements Bulletin 757-
53A0128 RB: Before 37,000 to-
tal flight cycles, or within 3,000
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB,
whichever occurs later.
CONDITION 3 (ACTION 2): Do
a High Frequency Eddy Current
(HFEC) surface inspection of
the frames from STA 640 to
STA 840, between stringer S-
21R and S-23R for any crack at
any location without a repair. (a)
For airplanes with more than or
equal to 42,000 total flight cy-
cles as of the Original Issue
date of Requirements Bulletin
757-53A0128 RB: Within 1,500
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
10 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 11

Table 2: Fuselage - Frames STA 640 to STA 840, Stringer S-21R to S-23R - Frame Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.CONDITION 3.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do the
repair.
CONDITION 3.1: ANY
CRACK FOUND.
6,000 flight cycles.-CONDITION 3.1 (ACTION 2):
Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21R and S-23R for
any crack. (a)
6,000 flight cycles.-Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21R and S-23R for
any crack. (a)
CONDITION 3.2: NO
CRACK FOUND.
-For airplanes with less than
42,000 total flight cycles as of
the Original Issue date of Re-
quirements Bulletin 757-
53A0128 RB: Before 37,000 to-
tal flight cycles, or within 3,000
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB,
whichever occurs later.
Do a HFEC surface inspection
of the frames from STA 640 to
STA 840, between stringer S-
21R and S-23R for any crack.
CONDITION 4: NO
REPAIR FOUND.
For airplanes with more than or
equal to 42,000 total flight cy-
cles as of the Original Issue
date of Requirements Bulletin
757-53A0128 RB: Within 1,500
flight cycles after the Original
Issue date of Requirements
Bulletin 757-53A0128 RB.
-Before further flight.CONDITION 4.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do the
repair.
CONDITION 4.1: ANY
CRACK FOUND.
6,000 flight cycles.-CONDITION 4.1 (ACTION 2):
Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21R and S-23R for
any crack. (a)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
11 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 12

Table 2: Fuselage - Frames STA 640 to STA 840, Stringer S-21R to S-23R - Frame Inspection
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs Later)
ActionCondition
6,000 flight cycles.-Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21R and S-23R for
any crack. (a)
CONDITION 4.2: NO
CRACK FOUND.
(a) It is not required to do the HFEC inspections in accordance with Requirements Bulletin 757-53A0128 RB
in the repair affected area(s) if the repair(s) meet all of the conditions that follow:
1.
The repair inspection plan was approved after the Original Issue date of Requirements Bulletin
757-53A0128 RB.
2. The repair plan is approved by the Boeing Organization Designation Authorization (ODA) via a
FAA Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area(s), states the post repair inspection
plan for the repair affected area(s), and approves the inspection plan as an alternative inspection
method to the inspection(s) in Requirements Bulletin 757-53A0128 RB.
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) approved for all EASA 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 Continued Operational Safety (COS) Branch approves the inspections
defined in this requirements bulletin as an Alternative Method Of Compliance (AMOC) to the requirements
of paragraph (g) and (h) of AD 2020-01-18 for the inspection of SSI 53-30-24 of the 757 Maintenance
Planning Data (MPD) Document Section 9 Airworthiness Limitations (AWLs) and Certification Maintenance
Requirements (CMRs), D622N001-9, affected by the inspection. This AMOC only applies to the areas
inspected in accordance with this requirements bulletin and to the airplanes identified in this requirements
bulletin. Operators of 757-200 airplanes must revise their FAA-approved maintenance or inspection program
to comply with paragraph (g) and (h) of AD 2020-01-18 when incorporating the inspections specified in this
requirements bulletin. All provisions of AD 2020-01-18 that are not specifically referenced in the above
statement remain fully applicable and must be complied with accordingly.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
12 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 13

5.    ACCOMPLISHMENT INSTRUCTIONS
A.
GENERAL INFORMATION
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. In the RB, the "Refer to the listed procedures..." column of the
table(s) in the Work Instructions is for reference only. The procedures in that column
are not required by the AD and are for guidance only. 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. Boeing Service Letter 757-SL-51-022, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
5. 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).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
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Original Issue: September 17, 2025
757-53A0128 RB
13 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 14

6. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
7. 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.
8.
If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
9. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
10. A General Visual Inspection (GVI) 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.
11. A maintenance records check of the repair at the frames can be done provided an
existing repair can be conclusively determined from that check. If the maintenance
records check cannot conclusively determine the part number, the General Visual
Inspection (GVI) must be done.
12. 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.
13. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
B. WORK INSTRUCTIONS
Actions Required for Compliance
1. Requirements
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757-53A0128 RB
14 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 15

Table 1: Fuselage - Frames STA 640 to STA 840, Stringer S-21L to S-23L - Frame Inspection
Refer to the listed procedures
in SB 757-53A0128 Original
Issue or later approved revi-
sions as an accepted proce-
dure
Method of Compli-
ance
ActionCondition
Do PART 1: LEFT SIDE OPEN
ACCESS.
-Do a General Visual Inspection
(GVI) or maintenance records
check for any repair of the
frames from STA 640 to STA
840, between stringer S-21L
and S-23L.
All airplanes with less
than 42,000 total flight
cycles as of the Original
Issue date of Require-
ments Bulletin 757-
53A0128 RB.
-FIGURE 1
Do PART 1: LEFT SIDE OPEN
ACCESS.
-Do a GVI or maintenance
records check for any repair of
the frames from STA 640 to
STA 840, between stringer S-
21L and S-23L.
All airplanes with more
than or equal to 42,000
total flight cycles as of
the Original Issue date
of Requirements Bul-
letin 757-53A0128 RB.
-FIGURE 1
--CONDITION 1 (ACTION 1):
Contact The Boeing Company
for alternative inspections to
Requirements Bulletin 757-
53A0128 RB and do the inspec-
tions and applicable on-condi-
tion actions at each repair loca-
tion.
CONDITION 1: ANY
REPAIR FOUND.
-FIGURE 2CONDITION 1 (ACTION 2): Do
a High Frequency Eddy Current
(HFEC) surface inspection of
the frames from STA 640 to
STA 840, between stringer S-
21L and S-23L for any crack at
any location without a repair. (a)
Do PART 2: LEFT SIDE CLOSE
ACCESS.
-CONDITION 1.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do the
repair.
CONDITION 1.1: ANY
CRACK FOUND.
Do PART 1: LEFT SIDE OPEN
ACCESS.
-CONDITION 1.1 (ACTION 2):
Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21L and S-23L for
any crack. (a)
-FIGURE 2
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757-53A0128 RB
15 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 16

Table 1: Fuselage - Frames STA 640 to STA 840, Stringer S-21L to S-23L - Frame Inspection
Refer to the listed procedures
in SB 757-53A0128 Original
Issue or later approved revi-
sions as an accepted proce-
dure
Method of Compli-
ance
ActionCondition
Do PART 2: LEFT SIDE CLOSE
ACCESS.
-Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21L and S-23L for
any crack. (a)
CONDITION 1.2: NO
CRACK FOUND.
Do PART 1: LEFT SIDE OPEN
ACCESS.
-
-FIGURE 2
-FIGURE 2Do a HFEC surface inspection
of the frames from STA 640 to
STA 840, between stringer S-
21L and S-23L for any crack.
CONDITION 2: NO
REPAIR FOUND.
Do PART 2: LEFT SIDE CLOSE
ACCESS.
-CONDITION 2.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do the
repair.
CONDITION 2.1: ANY
CRACK FOUND.
Do PART 1: LEFT SIDE OPEN
ACCESS.
-CONDITION 2.1 (ACTION 2):
Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21L and S-23L for
any crack. (a)
-FIGURE 2
Do PART 2: LEFT SIDE CLOSE
ACCESS.
-Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21L and S-23L for
any crack. (a)
CONDITION 2.2: NO
CRACK FOUND.
Do PART 1: LEFT SIDE OPEN
ACCESS.
-
-FIGURE 2
(a) It is not required to do the HFEC inspections in accordance with Requirements Bulletin 757-53A0128 RB
in the repair affected area(s) if the repair(s) meet all of the conditions that follow:
1.
The repair inspection plan was approved after the Original Issue date of Requirements Bulletin
757-53A0128 RB.
2. The repair plan is approved by the Boeing Organization Designation Authorization (ODA) via a
FAA Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area(s), states the post repair inspection
plan for the repair affected area(s), and approves the inspection plan as an alternative inspection
method to the inspection(s) in Requirements Bulletin 757-53A0128 RB.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
16 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 17

Table 2: Fuselage - Frames STA 640 to STA 840, Stringer S-21R to S-23R - Frame Inspection
Refer to the listed procedures
in SB 757-53A0128 Original
Issue or later approved revi-
sions as an accepted proce-
dure
Method of Compli-
ance
ActionCondition
Do PART 3: RIGHT SIDE
OPEN ACCESS.
-Do a General Visual Inspection
(GVI) or maintenance records
check for any repair of the
frames from STA 640 to STA
840, between stringer S-21R
and S-23R.
All airplanes with less
than 42,000 total flight
cycles as of the Original
Issue date of Require-
ments Bulletin 757-
53A0128 RB.
-FIGURE 3
Do PART 3: RIGHT SIDE
OPEN ACCESS.
-Do a GVI or maintenance
records check for any repair of
the frames from STA 640 to
STA 840, between stringer S-
21R and S-23R.
All airplanes with more
than or equal to 42,000
total flight cycles as of
the Original Issue date
of Requirements Bul-
letin 757-53A0128 RB.
-FIGURE 3
--CONDITION 3 (ACTION 1):
Contact The Boeing Company
for alternative inspections to
Requirements Bulletin 757-
53A0128 RB and do the inspec-
tions and applicable on-condi-
tion actions at each repair loca-
tion.
CONDITION 3: ANY
REPAIR FOUND.
-FIGURE 4CONDITION 3 (ACTION 2): Do
a High Frequency Eddy Current
(HFEC) surface inspection of
the frames from STA 640 to
STA 840, between stringer S-
21R and S-23R for any crack at
any location without a repair. (a)
Do PART 4: RIGHT SIDE
CLOSE ACCESS.
-CONDITION 3.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do the
repair.
CONDITION 3.1: ANY
CRACK FOUND.
Do PART 3: RIGHT SIDE
OPEN ACCESS.
-CONDITION 3.1 (ACTION 2):
Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21R and S-23R for
any crack. (a)
-FIGURE 4
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Original Issue: September 17, 2025
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REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 18

Table 2: Fuselage - Frames STA 640 to STA 840, Stringer S-21R to S-23R - Frame Inspection
Refer to the listed procedures
in SB 757-53A0128 Original
Issue or later approved revi-
sions as an accepted proce-
dure
Method of Compli-
ance
ActionCondition
Do PART 4: RIGHT SIDE
CLOSE ACCESS.
-Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21R and S-23R for
any crack. (a)
CONDITION 3.2: NO
CRACK FOUND.
Do PART 3: RIGHT SIDE
OPEN ACCESS.
-
-FIGURE 4
-FIGURE 4Do a HFEC surface inspection
of the frames from STA 640 to
STA 840, between stringer S-
21R and S-23R for any crack.
CONDITION 4: NO
REPAIR FOUND.
Do PART 4: RIGHT SIDE
CLOSE ACCESS.
-CONDITION 4.1 (ACTION 1):
Contact The Boeing Company
for repair instructions and do the
repair.
CONDITION 4.1: ANY
CRACK FOUND.
Do PART 3: RIGHT SIDE
OPEN ACCESS.
-CONDITION 4.1 (ACTION 2):
Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21R and S-23R for
any crack. (a)
-FIGURE 4
Do PART 4: RIGHT SIDE
CLOSE ACCESS.
-Repeat the HFEC surface in-
spection of the frames from STA
640 to STA 840, between
stringer S-21R and S-23R for
any crack. (a)
CONDITION 4.2: NO
CRACK FOUND.
Do PART 3: RIGHT SIDE
OPEN ACCESS.
-
-FIGURE 4
(a) It is not required to do the HFEC inspections in accordance with Requirements Bulletin 757-53A0128 RB
in the repair affected area(s) if the repair(s) meet all of the conditions that follow:
1.
The repair inspection plan was approved after the Original Issue date of Requirements Bulletin
757-53A0128 RB.
2. The repair plan is approved by the Boeing Organization Designation Authorization (ODA) via a
FAA Form 8100-9.
3. The FAA Form 8100-9 approval defines the repair affected area(s), states the post repair inspection
plan for the repair affected area(s), and approves the inspection plan as an alternative inspection
method to the inspection(s) in Requirements Bulletin 757-53A0128 RB.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
18 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 19 (OCR)

REQUIREMENTS BULLETIN 757-53A0128
ALERT  ALERT
STA
840
STA
640
STA
640
STA
660
S-17L
→S-18L
- S-19L
STA  740  =-S-20L
.S-21L
1-S-22L
/S-23L
S-24L
A  S-25L
• A  STA  680
TYPICAL
3087273
FIGURE 1: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21L TO S-23L - GENERAL VISUAL
INSPECTION (GVI)
(SHEET 1 OF 3)
Original Issue: September 17, 2025
Export Controlled ECCN: 9E991  757-53A0128 RB
See page 1 for details  19 of 30

### Page 20 (OCR)

REQUIREMENTS BULLETIN 757-53A0128
ALERT  ALERT
S-21L
FUSELAGE
SKIN
S-22L
+ i+
INBD  S-23L
FRAME
VIEW IN THE FORWARD DIRECTION
(TYPICAL)
A-A
• GENERAL VISUAL INSPECTION (GVI) AREA  3087275
FIGURE 1: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21L TO S-23L - GENERAL VISUAL
INSPECTION (GVI)
(SHEET 2 OF 3)
Original Issue: September 17, 2025
Export Controlled ECCN: 9E991  757-53A0128 RB
See page 1 for details  20 of 30

### Page 21

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of frame inspection areas necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a) 11-FRAMEInspect1
(a)
At each of the frame locations shown, do a General Visual Inspection (GVI) of the frame for any repair
between S-21L and S-23L, from STA 640 to STA 840.
FIGURE 1: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21L TO S-23L - GENERAL VISUAL
INSPECTION (GVI)
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
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Original Issue: September 17, 2025
757-53A0128 RB
21 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 22 (OCR)

REQUIREMENTS BULLETIN 757-53A0128
ALERT  ALERT
STA
840
STA
640
STA
640
STA
660
S-17L
.S-18L
•S-19L
--S-20L
.S-21L
1-S-22L
TA BOA  /S-23L
- →S-24L
→S-25L
STA
680
TYPICAL
3087330
FIGURE 2: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21L TO S-23L - FRAME INSPECTION
(SHEET 1 OF 3)
Original Issue: September 17, 2025
Export Controlled ECCN: 9E991  757-53A0128 RB
See page 1 for details  22 of 30

### Page 23 (OCR)

REQUIREMENTS BULLETIN 757-53A0128
ALERT  ALERT
FRAME  STANCHION CLIP  FRAME  INNER
INNER  CHORD
CHORD
STANCHION
CLIP
SUPPORT
CHANNEL
S-22L
FUSELAGE
SKIN
SUPPORT
INBD  CHANNEL  FAILSAFE
CHORD  FWD
FRAME
VIEW IN THE FORWARD DIRECTION  TYPICAL
(TYPICAL)  B-B
A-A
STANCHION
CLIP
SUPPORT  FRAME INNER CHORD
CHANNEL
VIEW IN THE OUTBOARD DIRECTION
(TYPICAL)
C-C
• (HFEC) SURFACE INSPECTION AREA  I HIGH FREQUENCY EDDY CURRENT
FIGURE 2: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21L TO S-23L - FRAME INSPECTION
(SHEET 2 OF 3)
Original Issue: September 17, 2025
757-53A0128 RB
Export Controlled ECCN: 9E991
See page 1 for details  23 of 30

### Page 24

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of frame inspection areas necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a) 11-FRAME INNER
CHORD
Inspect1
(b) 11-FRAME INNER
CHORD
Inspect2
(a)
At each of the frame locations shown, do a High Frequency Eddy Current (HFEC) surface inspection
around the end fasteners of the frame inner chord common to the support channel for any crack in accor-
dance with 757 NDT Manual Part 6, 51-00-01 or 757 NDT Manual Part 6, 51-00-19 between S-21L and
S-23L, from STA 640 to STA 840.
(b) At each of the frame locations shown, do a HFEC surface inspection along the edge of the return flange
of the frame inner chord from the upper end through the lower end of the support channel for any crack
in accordance with 757 NDT Manual Part 6, 51-00-01 or 757 NDT Manual Part 6, 51-00-19 between S-
21L and S-23L, from STA 640 to STA 840.
FIGURE 2: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21L TO S-23L - FRAME INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
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Original Issue: September 17, 2025
757-53A0128 RB
24 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 25 (OCR)

REQUIREMENTS BULLETIN 757-53A0128
ALERT  ALERT
STA
840
STA
640
STA
640
STA
660
S-17R~>
S-18R
S-19R
S-20R~=
S-21R_
S-22R_
S-23R~
S-24R_
S-25R_
SIA
680
TYPICAL
3087337
FIGURE 3: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21R TO S-23R - GENERAL VISUAL
INSPECTION (GVI)
(SHEET 1 OF 3)
Original Issue: September 17, 2025
Export Controlled ECCN: 9E991  757-53A0128 RB
See page 1 for details  25 of 30

### Page 26 (OCR)

REQUIREMENTS BULLETIN 757-53A0128
ALERT  ALERT
S-21R
+
FUSELAGE
SKIN
S-22R
*S-23R  INBD
FRAME
VIEW IN THE FORWARD DIRECTION
(TYPICAL)
A-A
• GENERAL VISUAL INSPECTION (GVI) AREA  3087338
FIGURE 3: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21R TO S-23R - GENERAL VISUAL
INSPECTION (GVI)
(SHEET 2 OF 3)
Original Issue: September 17, 2025
Export Controlled ECCN: 9E991  757-53A0128 RB
See page 1 for details  26 of 30

### Page 27

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of frame inspection areas necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a) 11-FRAMEInspect1
(a)
At each of the frame locations shown, do a General Visual Inspection (GVI) of the frame for any repair
between S-21R and S-23R, from STA 640 to STA 840.
FIGURE 3: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21R TO S-23R - GENERAL VISUAL
INSPECTION (GVI)
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
27 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

### Page 28 (OCR)

REQUIREMENTS BULLETIN 757-53A0128
ALERT  ALERT
STA
840
STA
640
STA
640
STA
660
S-17R
S-18R ~
S-19R ~-
S-20R
S-21R_
S-22R
S-23R.
S-24R.
S-25R.
TYPICA
3087340
FIGURE 4: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21R TO S-23R - FRAME INSPECTION
(SHEET 1 OF 3)
Original Issue: September 17, 2025
Export Controlled ECCN: 9E991  757-53A0128 RB
See page 1 for details  28 of 30

### Page 29 (OCR)

REQUIREMENTS BULLETIN 757-53A0128
ALERT  ALERT
STANCHION CLIP  FRAME  FRAME
-INNER  INNER  STANCHION
CHORD  CHORD  CLIP
SUPPORT
CHANNEL
S-22R
FUSELAGE
SKIN
SUPPORT
CHANNEL  FAILSAFE
CHORD
INBD
FWD
FRAME
VIEW IN THE FORWARD DIRECTION  TYPICAL
(TYPICAL)  B-B
A-A
/ CLIP  STANCHION
SUPPORT  FRAME INNER CHORD
CHANNEL
VIEW IN THE OUTBOARD DIRECTION
(TYPICAL)
• HIGH FREQUENCY EDDY CURRENT  C-C
THFEC) SURFACE INSPECTION AREA
FIGURE 4: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21R TO S-23R - FRAME INSPECTION
(SHEET 2 OF 3)
Original Issue: September 17, 2025
757-53A0128 RB
Export Controlled ECCN: 9E991
See page 1 for details  29 of 30

### Page 30

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of frame inspection areas necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a) 11-FRAME INNER
CHORD
Inspect1
(b) 11-FRAME INNER
CHORD
Inspect2
(a)
At each of the frame locations shown, do a High Frequency Eddy Current (HFEC) surface inspection
around the end fasteners of the frame inner chord common to the support channel for any crack in accor-
dance with 757 NDT Manual Part 6, 51-00-01 or 757 NDT Manual Part 6, 51-00-19 between S-21R and
S-23R, from STA 640 to STA 840.
(b) At each of the frame locations shown, do a HFEC surface inspection along the edge of the return flange
of the frame inner chord from the upper end through the lower end of the support channel for any crack
in accordance with 757 NDT Manual Part 6, 51-00-01 or 757 NDT Manual Part 6, 51-00-19 between S-
21R and S-23R, from STA 640 to STA 840.
FIGURE 4: FUSELAGE - FRAMES STA 640 TO STA 840, STRINGER S-21R TO S-23R - FRAME INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 17, 2025
757-53A0128 RB
30 of 30
REQUIREMENTS BULLETIN 757-53A0128
ALERTALERT

---
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