# Boeing Alert Requirements Bulletin 757-53A0122 RB: No revision named

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- Title as filed: RB-757-53A0122
- Pages: 30
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### Page 1

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0122 RB
Original Issue:
September 26, 2025
ATA System: 5365
SUBJECT: FUSELAGE - Section 46 - Between Stringers S-13 and S-14, from STA 1380 to STA
1620, Fuselage Frame Splice 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 26, 2025
757-53A0122 RB
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2.0

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Export Controlled ECCN: 9E991
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REQUIREMENTS BULLETIN 757-53A0122
ALERTALERT
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Table of Contents
1. EFFECTIVITY .
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
FIGURE 1: LEFT SIDE - FUSELAGE FRAME SPLICES BETWEEN STRINGERS S-13L AND S-14L FROM
STA 1380 TO STA 1620 - GENERAL VISUAL INSPECTION . . . . . . . . . . . . . . . . 19
FIGURE 2: RIGHT SIDE - FUSELAGE FRAME SPLICES BETWEEN STRINGERS S-13R AND S-14R
FROM STA 1380 TO STA 1620 - GENERAL VISUAL INSPECTION . . . . . . . . . . . . 22
FIGURE 3: LEFT SIDE - UPPER FRAMES AT THE FUSELAGE FRAME SPLICES BETWEEN STRINGERS
S-13L AND S-14L FROM STA 1380 TO STA 1620 - DETAILED INSPECTION . . . . . . 25
FIGURE 4: RIGHT SIDE - UPPER FRAMES AT THE FUSELAGE FRAME SPLICES BETWEEN STRINGERS
S-13R AND S-14R FROM STA 1380 TO STA 1620 - DETAILED INSPECTION . . . . . . 28
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REQUIREMENTS BULLETIN 757-53A0122
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Export Controlled ECCN: 9E991
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REQUIREMENTS BULLETIN 757-53A0122
ALERTALERT
BLANK PAGE

### Page 5

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0122 RB
Original Issue:
September 26, 2025
ATA System: 5365
SUBJECT: FUSELAGE - Section 46 - Between Stringers S-13 and S-14, from STA 1380 to STA
1620, Fuselage Frame Splice 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 757-300 Airplane(s), line number(s) 804, 810, 818, 839, 846, 849,
855, 906, 909, 912, 915, 918, 923, 926, 929, 960, 963, 972, 976, 978, 980, 985, 990, 995, 997,
999, 1001, 1003-1004, 1007-1008, 1014, 1017-1025, 1027, 1030-1040, 1042-1043 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
All 757-300 Airplanes.- 1
Airplane Models:
757-300
GroupVariable Number
1NL001 - NL002
1NL006 - NL017
1NL101 - NL109
GroupVariable Number
1NL141
1NL601 - NL616
1NU701 - NU705
GroupVariable Number
1NU721 - NU728
1NU731 - NU732
--
B.
Spares Affected
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### Page 6

None.
2.
CONCURRENT REQUIREMENTS
None.
3. COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
Requirements Bulletin 757-53A0122 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 757-53A0122 RB mandatory.
Accomplish the required action(s), based on the applicable condition(s) in Table 1 and 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: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Left Side
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-
53A0122 RB.
Before
40,000 total
flight cycles.
Do a General Visual Inspection
(GVI) or a maintenance records
check of the forward and aft
sides of the upper frames at the
frame splices between S-13L
and S-14L, from STA 1380 to
STA 1620, for any repair.
All Airplanes.
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0122 RB.
Before
40,000 total
flight cycles.
CONDITION 1 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspection
and applicable corrective ac-
tions in the repaired areas.
CONDITION 1:
ANY REPAIR FOUND.
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0122 RB.
Before
40,000 total
flight cycles.
CONDITION 1 (ACTION 2):
Do a Detailed Inspection (DET)
of the upper frames around the
uppermost fastener common to
the fail-safe chord at the frame
splices between S-13L and S-
14L, from STA 1380 to STA
1620, for any crack in the unre-
paired areas.
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### Page 7

Table 1: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Left Side
Repeat Interval (Not
to Exceed)
Boeing Recommended
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 1.1 (ACTION 1):CONDITION 1.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK FOUND.
12,000 flight cycles.-CONDITION 1.1 (ACTION 2):
Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13L and S-14L, from
STA 1380 to STA 1620, for any
crack. (a)
12,000 flight cycles.-Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13L and S-14L, from
STA 1380 to STA 1620, for any
crack. (a)
CONDITION 1.2:
NO CRACK FOUND.
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0122 RB.
Before
40,000 total
flight cycles.
Do a DET of the upper frames
around the uppermost fastener
common to the fail-safe chord
at the frame splices between S-
13L and S-14L, from STA 1380
to STA 1620, for any crack.
CONDITION 2:
NO REPAIR FOUND.
-Before further flight.CONDITION 2.1 (ACTION 1):CONDITION 2.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK FOUND.
12,000 flight cycles.-CONDITION 2.1 (ACTION 2):
Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13L and S-14L, from
STA 1380 to STA 1620, for any
crack. (a)
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Table 1: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Left Side
Repeat Interval (Not
to Exceed)
Boeing Recommended
Compliance Time
(Whichever Occurs Later)
ActionCondition
12,000 flight cycles.-Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13L and S-14L, from
STA 1380 to STA 1620, for any
crack. (a)
CONDITION 2.2:
NO CRACK FOUND.
(a)
It is not required to do the DET inspections in accordance with Requirements Bulletin 757-53A0122 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
757-53A0122 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 inspec-
tion plan for the repair affected area(s), and approves the inspection plan as an alternative in-
spection method to the inspection(s) in Requirements Bulletin 757-53A0122 RB.
Table 2: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Right Side
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-
53A0122 RB.
Before
40,000 total
flight cycles.
Do a General Visual Inspection
(GVI) or a maintenance records
check of the forward and aft
sides of the upper frames at the
frame splices between S-13L
and S-14L, from STA 1380 to
STA 1620, for any repair.
All Airplanes.
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### Page 9

Table 2: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Right Side
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-
53A0122 RB.
Before
40,000 total
flight cycles.
CONDITION 3 (ACTION 1):
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspection
and applicable corrective ac-
tions in the repaired areas.
CONDITION 3:
ANY REPAIR FOUND.
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0122 RB.
Before
40,000 total
flight cycles.
CONDITION 3 (ACTION 2):
Do a Detailed Inspection (DET)
of the upper frames around the
uppermost fastener common to
the fail-safe chord at the frame
splices between S-13R and S-
14R, from STA 1380 to STA
1620, for any crack in the unre-
paired areas.
-Before further flight.CONDITION 3.1 (ACTION 1):CONDITION 3.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK FOUND.
12,000 flight cycles.-CONDITION 3.1 (ACTION 2):
Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13R and S-14R, from
STA 1380 to STA 1620, for any
crack. (a)
12,000 flight cycles.-Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13R and S-14R, from
STA 1380 to STA 1620, for any
crack. (a)
CONDITION 3.2:
NO CRACK FOUND.
-Within 3,000
flight cycles af-
ter the Original
Issue date of
Requirements
Bulletin 757-
53A0122 RB.
Before
40,000 total
flight cycles.
Do a DET of the upper frames
around the uppermost fastener
common to the fail-safe chord
at the frame splices between S-
13R and S-14R, from STA 1380
to STA 1620, for any crack.
CONDITION 4:
NO REPAIR FOUND.
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### Page 10

Table 2: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Right Side
Repeat Interval (Not
to Exceed)
Boeing Recommended
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 4.1 (ACTION 1):CONDITION 4.1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK FOUND.
12,000 flight cycles.-CONDITION 4.1 (ACTION 2):
Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13R and S-14R, from
STA 1380 to STA 1620, for any
crack. (a)
12,000 flight cycles.-Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13R and S-14R, from
STA 1380 to STA 1620, for any
crack. (a)
CONDITION 4.2:
NO CRACK FOUND.
(a)
It is not required to do the DET inspections in accordance with Requirements Bulletin 757-53A0122 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
757-53A0122 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 inspec-
tion plan for the repair affected area(s), and approves the inspection plan as an alternative in-
spection method to the inspection(s) in Requirements Bulletin 757-53A0122 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.
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### Page 11

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).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
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### Page 12

— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
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 Detailed Inspection (DET) is defined as: An intensive examination of a specific
item, installation or assembly to detect damage, failure or irregularity. This could
include tactile assessment in which a component or assembly can be checked for
tightness/security. Available lighting is normally supplemented with a direct source
of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors
and magnifying lenses may be necessary. Surface cleaning and elaborate access
procedures may be required.
11. 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.
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. A maintenance records check for any existing repair at the frame splices can be
done provided an existing repair at the frame splices can be conclusively determined
from that check. If the maintenance records check cannot conclusively determine
an existing repair at the frame splices, the General Visual Inspection (GVI) must be
done.
14. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
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### Page 13

B. WORK INSTRUCTIONS
Actions Required for Compliance
1. Requirements.
Table 1: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Left Side
Refer to the listed
procedures in SB
757-53A0122 Origi-
nal Issue or later
approved revisions
as an accepted pro-
cedure
Method of ComplianceActionCondition
Do PART 1: LEFT
SIDE OPEN AC-
CESS.
-Do a General Visual Inspection
(GVI) or a maintenance records
check of the forward and aft
sides of the upper frames at the
frame splices between S-13L
and S-14L, from STA 1380 to
STA 1620, for any repair.
All Airplanes.
-FIGURE 1
--CONDITION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspection
and applicable corrective ac-
tions in the repaired areas.
ANY REPAIR FOUND.
-FIGURE 3CONDITION 1 (ACTION 2):
Do a Detailed Inspection (DET)
of the upper frames around the
uppermost fastener common to
the fail-safe chord at the frame
splices between S-13L and S-
14L, from STA 1380 to STA
1620, for any crack in the unre-
paired areas.
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### Page 14

Table 1: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Left Side
Refer to the listed
procedures in SB
757-53A0122 Origi-
nal Issue or later
approved revisions
as an accepted pro-
cedure
Method of ComplianceActionCondition
--CONDITION 1.1 (ACTION 1):CONDITION 1.1:
ANY CRACK FOUND.
Contact The Boeing Company
for repair instructions and do the
repair.
Do PART 3: LEFT
SIDE CLOSE AC-
CESS.
-
Do PART 1: LEFT
SIDE OPEN AC-
CESS.
-CONDITION 1.1 (ACTION 2):
Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13L and S-14L, from
STA 1380 to STA 1620, for any
crack.(a)
-FIGURE 3
Do PART 3: LEFT
SIDE CLOSE AC-
CESS.
--CONDITION 1.2:
NO CRACK FOUND.
Do PART 1: LEFT
SIDE OPEN AC-
CESS.
-Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13L and S-14L, from
STA 1380 to STA 1620, for any
crack. (a)
-FIGURE 3
-FIGURE 3Do a DET of the upper frames
around the uppermost fastener
common to the fail-safe chord
at the frame splices between S-
13L and S-14L, from STA 1380
to STA 1620, for any crack.
CONDITION 2:
NO REPAIR FOUND.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 26, 2025
757-53A0122 RB
14 of 30
REQUIREMENTS BULLETIN 757-53A0122
ALERTALERT

### Page 15

Table 1: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Left Side
Refer to the listed
procedures in SB
757-53A0122 Origi-
nal Issue or later
approved revisions
as an accepted pro-
cedure
Method of ComplianceActionCondition
--CONDITION 2.1 (ACTION 1):CONDITION 2.1:
ANY CRACK FOUND.
Contact The Boeing Company
for repair instructions and do the
repair.
Do PART 3: LEFT
SIDE CLOSE AC-
CESS.
-
Do PART 1: LEFT
SIDE OPEN AC-
CESS.
-CONDITION 2.1 (ACTION 2):
Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13L and S-14L, from
STA 1380 to STA 1620, for any
crack.(a)
-FIGURE 3
Do PART 3: LEFT
SIDE CLOSE AC-
CESS.
--CONDITION 2.2:
NO CRACK FOUND.
Do PART 1: LEFT
SIDE OPEN AC-
CESS.
-Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13L and S-14L, from
STA 1380 to STA 1620, for any
crack.(a)
-FIGURE 3
(a) It is not required to do the DET inspections in accordance with Requirements Bulletin 757-53A0122 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
757-53A0122 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 inspec-
tion plan for the repair affected area(s), and approves the inspection plan as an alternative in-
spection method to the inspection(s) in Requirements Bulletin 757-53A0122 RB.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 26, 2025
757-53A0122 RB
15 of 30
REQUIREMENTS BULLETIN 757-53A0122
ALERTALERT

### Page 16

Table 2: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Right Side
Refer to the listed
procedures in SB
757-53A0122 Origi-
nal Issue or later
approved revisions
as an accepted pro-
cedure
Method of ComplianceActionCondition
Do PART 2: RIGHT
SIDE OPEN AC-
CESS.
-Do a General Visual Inspection
(GVI) or a maintenance records
check of the forward and aft
sides of the upper frames at the
frame splices between S-13L
and S-14L, from STA 1380 to
STA 1620, for any repair.
All Airplanes.
-FIGURE 2
--CONDITION 3 (ACTION 1):CONDITION 3:
Contact The Boeing Company
for alternative inspection and
corrective action instructions
and do the alternative inspection
and applicable corrective ac-
tions in the repaired areas.
ANY REPAIR FOUND.
-FIGURE 4CONDITION 3 (ACTION 2):
Do a Detailed Inspection (DET)
of the upper frames around the
uppermost fastener common to
the fail-safe chord at the frame
splices between S-13R and S-
14R, from STA 1380 to STA
1620, for any crack in the unre-
paired areas.
--CONDITION 3.1 (ACTION 1):CONDITION 3.1:
ANY CRACK FOUND.
Contact The Boeing Company
for repair instructions and do the
repair.
Do PART 4: RIGHT
SIDE CLOSE AC-
CESS.
-
Do PART 2: RIGHT
SIDE OPEN AC-
CESS.
-CONDITION 3.1 (ACTION 2):
Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13R and S-14R, from
STA 1380 to STA 1620, for any
crack.(a)
-FIGURE 4
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 26, 2025
757-53A0122 RB
16 of 30
REQUIREMENTS BULLETIN 757-53A0122
ALERTALERT

### Page 17

Table 2: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Right Side
Refer to the listed
procedures in SB
757-53A0122 Origi-
nal Issue or later
approved revisions
as an accepted pro-
cedure
Method of ComplianceActionCondition
Do PART 4: RIGHT
SIDE CLOSE AC-
CESS.
--CONDITION 3.2:
NO CRACK FOUND.
Do PART 2: RIGHT
SIDE OPEN AC-
CESS.
-Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13R and S-14R, from
STA 1380 to STA 1620, for any
crack.(a)
-FIGURE 4
-FIGURE 4Do a DET of the upper frames
around the uppermost fastener
common to the fail-safe chord
at the frame splices between S-
13R and S-14R, from STA 1380
to STA 1620, for any crack.
CONDITION 4:
NO REPAIR FOUND.
--CONDITION 4.1 (ACTION 1):CONDITION 4.1:
ANY CRACK FOUND.
Contact The Boeing Company
for repair instructions and do the
repair.
Do PART 4: RIGHT
SIDE CLOSE AC-
CESS.
-
Do PART 2: RIGHT
SIDE OPEN AC-
CESS.
-CONDITION 4.1 (ACTION 2):
Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13R and S-14R, from
STA 1380 to STA 1620, for any
crack.(a)
-FIGURE 4
Do PART 4: RIGHT
SIDE CLOSE AC-
CESS.
--CONDITION 4.2:
NO CRACK FOUND.
Do PART 2: RIGHT
SIDE OPEN AC-
CESS.
-Repeat the DET of the upper
frames around the uppermost
fastener common to the fail-safe
chord at the frame splices be-
tween S-13R and S-14R, from
STA 1380 to STA 1620, for any
crack.(a)
-FIGURE 4
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 26, 2025
757-53A0122 RB
17 of 30
REQUIREMENTS BULLETIN 757-53A0122
ALERTALERT

### Page 18

Table 2: Inspections of the Upper Frames at Fuselage Frame Splices between Stringers S-13 and S-14
from STA 1380 to STA 1620, Right Side
Refer to the listed
procedures in SB
757-53A0122 Origi-
nal Issue or later
approved revisions
as an accepted pro-
cedure
Method of ComplianceActionCondition
(a)
It is not required to do the DET inspections in accordance with Requirements Bulletin 757-53A0122 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
757-53A0122 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 inspec-
tion plan for the repair affected area(s), and approves the inspection plan as an alternative in-
spection method to the inspection(s) in Requirements Bulletin 757-53A0122 RB.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 26, 2025
757-53A0122 RB
18 of 30
REQUIREMENTS BULLETIN 757-53A0122
ALERTALERT

### Page 19 (OCR)

REQUIREMENTS BULLETIN 757-53A0122
ALERT  ALERT
STA
1620
STA
1380
STA  STA  STA  STA  STA  STA
1620  1600  1580  1560  1540  1520
S-10L -
S-11L
S-12L
S-13L
S-14L
STA  STA  STA  STA  STA  STA
1500  1480  1460  1440  1400  1380
- S-10L
• S-1.1L
- S-12L
- S-13L
- S-14L
VIEW IN THE OUTBOARD DIRECTION
(TYPICAL)
3084512
FIGURE 1: LEFT SIDE - FUSELAGE FRAME SPLICES BETWEEN STRINGERS S-13L AND S-14L FROM
STA 1380 TO STA 1620 - GENERAL VISUAL INSPECTION
(SHEET 1 OF 3)
Original Issue: September 26, 2025
Export Controlled ECCN: 9E991  757-53A0122 RB
See page 1 for details  19 of 30

### Page 20 (OCR)

REQUIREMENTS BULLETIN 757-53A0122
ALERT  ALERT
UPPER FRAME-  - S-13L
FUSELAGE
SKIN
INBD
SHEAR TIE  - S-14L
SIDE FRAME
SPLICE
DOUBLER
FAIL-SAFE
CHORD
VIEW IN THE AFT DIRECTION
(TYPICAL FRAME SPLICE SHOWN,
SOME STRUCTURES MAY VARY
SLIGHTLY AND THE DIFFERENCES DO
NOT AFFECT THE INSPECTABILITY)
A-A  3084513
GENERAL VISUAL
INSPECTION AREA
FIGURE 1: LEFT SIDE - FUSELAGE FRAME SPLICES BETWEEN STRINGERS S-13L AND S-14L FROM
STA 1380 TO STA 1620 - GENERAL VISUAL INSPECTION
(SHEET 2 OF 3)
Original Issue: September 26, 2025
Export Controlled ECCN: 9E991  757-53A0122 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 parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a) 13-UPPER FRAMEInspect1
(a)
Do a General Visual Inspection (GVI) of the forward and aft sides of the upper frame at the frame splice
for any repair.
FIGURE 1: LEFT SIDE - FUSELAGE FRAME SPLICES BETWEEN STRINGERS S-13L AND S-14L FROM
STA 1380 TO STA 1620 - GENERAL VISUAL INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 26, 2025
757-53A0122 RB
21 of 30
REQUIREMENTS BULLETIN 757-53A0122
ALERTALERT

### Page 22 (OCR)

REQUIREMENTS BULLETIN 757-53A0122
ALERT  ALERT
STA
1620
STA
1380
STA  STA  STA  STA  STA
1520  1540  1560  1600  1620
- S-10R
S-11R
S-12R
• S-13R
- S-14R
STA  STA  STA  STA  STA  STA  STA
1380  1400  1420  1440  1460  1480  1500
S-10R
S-11R-
S-12R-
S-13R
S-14R
→ A
VIEW IN THE OUTBOARD DIRECTION
(TYPICAL)  3084704
FIGURE 2: RIGHT SIDE - FUSELAGE FRAME SPLICES BETWEEN STRINGERS S-13R AND S-14R FROM
STA 1380 TO STA 1620 - GENERAL VISUAL INSPECTION
(SHEET 1 OF 3)
Original Issue: September 26, 2025
757-53A0122 RB
Export Controlled ECCN: 9E991
See page 1 for details  22 of 30

### Page 23 (OCR)

REQUIREMENTS BULLETIN 757-53A0122
ALERT  ALERT
S-13R -  - UPPER FRAME
FUSELAGE
SKIN
INBD
S-14R  • SHEAR TIE
- SIDE FRAME
• SPLICE
DOUBLER
FAIL-SAFE
CHORD
VIEW IN THE AFT DIRECTION
(TYPICAL FRAME SPLICE SHOWN,
SOME STRUCTURES MAY VARY
SLIGHTLY AND THE DIFFERENCES DO
NOT AFFECT THE INSPECTABILITY)
4 INSPECTION AREA  GENERAL VISUAL  A-A  3084705
FIGURE 2: RIGHT SIDE - FUSELAGE FRAME SPLICES BETWEEN STRINGERS S-13R AND S-14R FROM
STA 1380 TO STA 1620 - GENERAL VISUAL INSPECTION
(SHEET 2 OF 3)
Original Issue: September 26, 2025
Export Controlled ECCN: 9E991  757-53A0122 RB
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 parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a) 13-UPPER FRAMEInspect1
(a)
Do a General Visual Inspection (GVI) of the forward and aft sides of the upper frame at the frame splice
for any repair.
FIGURE 2: RIGHT SIDE - FUSELAGE FRAME SPLICES BETWEEN STRINGERS S-13R AND S-14R FROM
STA 1380 TO STA 1620 - GENERAL VISUAL INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 26, 2025
757-53A0122 RB
24 of 30
REQUIREMENTS BULLETIN 757-53A0122
ALERTALERT

### Page 25 (OCR)

REQUIREMENTS BULLETIN 757-53A0122
ALERT  ALERT
STA
1620
STA
1380
STA  STA  STA  STA  STA  STA
1620  1600  1580  1560  1540  1520
S-10L -
S-11L
S-12L
S-13L
S-14L
STA  STA  STA  STA  STA  STA
1500  1480  1460  1440  1400  1380
- S-10L
• S-1.1L
- S-12L
- S-13L
• S-14L
VIEW IN THE OUTBOARD DIRECTION
(TYPICAL)
3084567
FIGURE 3: LEFT SIDE - UPPER FRAMES AT THE FUSELAGE FRAME SPLICES BETWEEN STRINGERS
S-13L AND S-14L FROM STA 1380 TO STA 1620 - DETAILED INSPECTION
(SHEET 1 OF 3)
Original Issue: September 26, 2025
Export Controlled ECCN: 9E991  757-53A0122 RB
See page 1 for details  25 of 30

### Page 26 (OCR)

REQUIREMENTS BULLETIN 757-53A0122
ALERT  ALERT
UPPER FRAME  - S-13L
B
FUSELAGE
- SKIN
NBD
SHEAR TIE  - S-14L
SIDE FRAME
SPLICE
DOUBLER
FAIL-SAFE
CHORD
VIEW IN THE AFT DIRECTION
(TYPICAL FRAME SPLICE SHOWN,
SOME STRUCTURES MAY VARY
SLIGHTLY AND THE DIFFERENCES DO
NOT AFFECT THE INSPECTABILITY)
A-A  3084568
DETAILED
INSPECTION AREA
FIGURE 3: LEFT SIDE - UPPER FRAMES AT THE FUSELAGE FRAME SPLICES BETWEEN STRINGERS
S-13L AND S-14L FROM STA 1380 TO STA 1620 - DETAILED INSPECTION
(SHEET 2 OF 3)
Original Issue: September 26, 2025
Export Controlled ECCN: 9E991  757-53A0122 RB
See page 1 for details  26 of 30

### Page 27 (OCR)

REQUIREMENTS BULLETIN 757-53A0122
ALERT  ALERT
FAIL-SAFE
UPPER  CHORD
FRAME.
SHEAR
SPLICE  TIE
DOUBLER
SIDE
FRAME
FUSELAGE
SKIN
INBD  SHEAR
TIE
VIEW IN THE DOWN DIRECTION
(TYPICAL FRAME SPLICE SHOWN,
SOME STRUCTURES MAY VARY
SLIGHTLY AND THE DIFFERENCES DO
NOT AFFECT THE INSPECTABILITY)
INSPECTION AREA  DETAILED  B-B
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 parts necessary for this figure.
Step  Task  Name  Identification  Qty  More Data
Inspect  UPPER FRAME  13  (a)
(a) Do a Detailed Inspection (DET) of the upper frame around the uppermost fastener common to the fail-
safe chord at the frame splice for any crack.
FIGURE 3: LEFT SIDE - UPPER FRAMES AT THE FUSELAGE FRAME SPLICES BETWEEN STRINGERS
S-13L AND S-14L FROM STA 1380 TO STA 1620 - DETAILED INSPECTION
(SHEET 3 OF 3)
Original Issue: September 26, 2025
Export Controlled ECCN: 9E991  757-53A0122 RB
See page 1 for details  27 of 30

### Page 28 (OCR)

REQUIREMENTS BULLETIN 757-53A0122
ALERT  ALERT
STA
1620
STA
1380
STA  STA  STA  STA  STA
1520  1540  1560  1600  1620
- S-10R
S-11R
S-12R
• S-13R
- S-14R
STA  STA  STA  STA  STA  STA  STA
1380  1400  1420  1440  1460  1480  1500
S-10R
S-11R-
S-12R-
S-13R
S-14R
→ A
VIEW IN THE OUTBOARD DIRECTION
(TYPICAL)
3084711
FIGURE 4: RIGHT SIDE - UPPER FRAMES AT THE FUSELAGE FRAME SPLICES BETWEEN STRINGERS
S-13R AND S-14R FROM STA 1380 TO STA 1620 - DETAILED INSPECTION
(SHEET 1 OF 3)
Original Issue: September 26, 2025
Export Controlled ECCN: 9E991  757-53A0122 RB
See page 1 for details  28 of 30

### Page 29 (OCR)

REQUIREMENTS BULLETIN 757-53A0122
ALERT  ALERT
S-13R-  - UPPER FRAME
B
FUSELAGE
SKIN
INBD
S-14R  SHEAR TIE
• SIDE FRAME
•SPLICE
DOUBLER
• FAIL-SAFE
CHORD
VIEW IN THE AFT DIRECTION
(TYPICAL FRAME SPLICE SHOWN,
SOME STRUCTURES MAY VARY
SLIGHTLY AND THE DIFFERENCES DO
NOT AFFECT THE INSPECTABILITY)
A INSPECTION AREA  DETAILED  A-A  3084713
FIGURE 4: RIGHT SIDE - UPPER FRAMES AT THE FUSELAGE FRAME SPLICES BETWEEN STRINGERS
S-13R AND S-14R FROM STA 1380 TO STA 1620 - DETAILED INSPECTION
(SHEET 2 OF 3)
Original Issue: September 26, 2025
Export Controlled ECCN: 9E991  757-53A0122 RB
See page 1 for details  29 of 30

### Page 30 (OCR)

REQUIREMENTS BULLETIN 757-53A0122
ALERT  ALERT
FAIL-SAFE
CHORD  UPPER
FRAME
SHEAR
TIE  SPLICE
DOUBLER
SIDE
FRAME
FUSELAGE
SKIN
INBD
SHEAR
TIE
VIEW IN THE DOWN DIRECTION
(TYPICAL FRAME SPLICE SHOWN,
SOME STRUCTURES MAY VARY
SLIGHTLY AND THE DIFFERENCES DO
NOT AFFECT THE INSPECTABILITY)
DETAILED  B-B  3084714
INSPECTION AREA
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 parts necessary for this figure.
Step  Task  Name  Identification  Qty  More Data
Inspect  UPPER FRAME  13  (a)
(a) Do a Detailed Inspection (DET) of the upper frame around the uppermost fastener common to the fail-
safe chord at the frame splice for any crack.
FIGURE 4: RIGHT SIDE - UPPER FRAMES AT THE FUSELAGE FRAME SPLICES BETWEEN STRINGERS
S-13R AND S-14R FROM STA 1380 TO STA 1620 - DETAILED INSPECTION
(SHEET 3 OF 3)
Original Issue: September 26, 2025
757-53A0122 RB
Export Controlled ECCN: 9E991
See page 1 for details  30 of 30

---
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