# Boeing Alert Requirements Bulletin 757-53A0109 RB: No revision named

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- Title as filed: Boeing Requirements Bulletin 757-53A0109 RB
- Pages: 101
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## Text

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### Page 1

Commercial 
Airplanes
757
Requirements Bulletin
ALERT
Number: 757-53A0109 RB
Original Issue:
September 25, 2025
ATA System: 5300
SUBJECT: FUSELAGE - Fuselage - Section 43 and Section 46 - Stringer S-14 Lower Panels
Removal and Replacement
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, 757-200CB 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, 779-803, 805-809,
811-812, 814, 816-817, 819-822, 824-838, 840-845, 847-848, 850-854, 856-878, 880-881, 883-905,
907-908, 910-911, 913-914, 916-917, 919-922, 924-925, 927-928, 930-959, 961-962, 964-971,
973-975, 977, 979, 981-984, 986-989, 991-994, 996, 998, 1000, 1002, 1005-1006, 1009-1013,
1015-1016, 1026, 1028-1029, 1041, 1044-1050 in 7 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 Passenger airplanes with 2 lower cargo doors with no aft
potable water service panel at stringer S-27L, STA 1650.
- 1
757-200 Passenger airplanes with 4 passenger doors and no
overwing exit doors, 2 lower cargo doors and aft potable water service
panel at stringer S-27L, STA 1650.
- 2
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
5 of 105

### Page 2

DESCRIPTIONCONFIGURATIONGROUP
757-200 Passenger airplanes with overwing exit doors, 2 lower cargo
doors and aft potable water service panel at stringer S-27L, STA
1650.
- 3
757-200 Passenger airplanes with overwing exit doors, 2 lower cargo
doors, aft potable water service panel at stringer S-27L, STA 1650
and Door 4 lavatory service panel, 166AR.
- 4
757-200 Passenger airplanes with 3 lower cargo doors that have not
been converted into Special Freighters (SF) in accordance with
Boeing Supplemental Type Certificate (STC) ST00916WI-D.
- 5
757-200CB Combi airplane.- 6
190-Passenger Configuration.1
Passenger-Cargo Configuration.2
191-Passenger Configuration.3
757-200 airplanes that have been converted into Special Freighters
(SF) in accordance with Boeing STC ST00916WI-D.
- 7
Airplane Models:
757-200, 757-200CB
GroupVariable Number
1NA001 - NA028
1NA191 - NA199
7NA201 - NA204
5NA205
7NA206 - NA213
5NA214
7NA215 - NA236
1NA237 - NA239
1NA301 - NA305
5NA341 - NA352
5NA391 - NA399
1NA401 - NA408
GroupVariable Number
1NA441 - NA447
4NA501 - NA586
4NB001 - NB004
1NB021 - NB023
1NB036 - NB041
1NB051 - NB053
1NB061 - NB073
1NB079
1NB131 - NB148
1NB161 - NB162
1NB166 - NB168
1NB201 - NB204
GroupVariable Number
1NB221 - NB228
1NB230
1NB236
1NB239
1NB261 - NB267
1NB291 - NB299
1NB301 - NB302
1NB311 - NB312
1NB321 - NB331
1NB421 - NB438
1NB446
1NB451 - NB454
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
6 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 3

GroupVariable Number
1NB501 - NB523
1NB561
1NB571
1NB581 - NB583
1NC001 - NC033
1NC041 - NC042
1NC051 - NC052
1NC056 - NC062
1NC066 - NC084
1NC091 - NC094
1NC151
1NC161
4ND001 - ND007
4ND011 - ND059
4ND111 - ND113
4ND161 - ND199
4ND201 - ND203
4ND221 - ND225
4ND241 - ND248
4ND301 - ND322
4ND401
GroupVariable Number
4ND891
6ND895
4NE001 - NE008
4NE011 - NE088
4NE091 - NE094
4NE141 - NE150
4NE161 - NE177
4NE201 - NE204
4NE301 - NE302
4NE311 - NE325
2NJ001 - NJ004
2NJ031 - NJ032
2NJ551 - NJ555
3NN001 - NN002
3NN051 - NN052
1NP901 - NP904
1NT201 - NT202
1NT231 - NT234
1NT237 - NT240
1NT242
1NT245 - NT248
GroupVariable Number
1NT281 - NT289
1NT341 - NT347
1NT351 - NT360
1NT371 - NT373
1NT375 - NT379
1NT381 - NT386
1NT401 - NT409
1NT411 - NT412
1NT426 - NT427
1NT431 - NT432
1NT436 - NT438
1NT441 - NT442
1NT446
4NT701 - NT769
4NT791 - NT796
4NT861 - NT862
4NT881 - NT885
4NT901 - NT916
4NT971 - NT985
4NU031 - NU038
--
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 757-53A0109 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 757-53A0109 RB mandatory.
Federal Aviation Administration (FAA) Airworthiness Directives AD 2016-15-04, AD 2018-18-07, AD
2019-07-04, and AD 2020-01-18 are related to Requirements Bulletin 757-53A0109 RB.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
7 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 4

Accomplish the required action(s), based on the applicable condition(s) in Table(s) 1 through 6, 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.
Group 1:
Table 1: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of
the fuselage skin panels between
stringers S-14 and S-19 on the
left and right sides, from STA 439
to STA 661; and between
stringers S-14L and S-20L, from
STA 1180 to STA 1621; and be-
tween stringers S-14R and S-
20R, from STA 1459 to STA
1621.
All Airplanes.
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Contact The Boeing Company for
alternative modification instruc-
tions to the Requirements Bulletin
757-53A0109 RB and do the
modification and applicable on-
condition action(s).
CONDITION 1:
ANY EXISTING
REPAIR
FOUND.
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Replace the fuselage skin panels
or bond assemblies between
stringers S-14 and S-19 on the
left and right sides, from STA 439
to STA 661; and between
stringers S-14L and S-20L, from
STA 1180 to STA 1621; and be-
tween stringers S-14R and S-
20R, from STA 1459 to STA 1621
with new fuselage skin panels or
bond assemblies.
CONDITION 2:
NO EXISTING
REPAIR
FOUND.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
8 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 5

Group 2:
Table 2: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of
the fuselage skin panels between
stringers S-14 and S-19 on the
left and right sides, from STA 439
to STA 661; and between
stringers S-14 and S-20 on the
left and right sides, from STA
1180 to STA 1621.
All Airplanes.
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Contact The Boeing Company for
alternative modification instruc-
tions to the Requirements Bulletin
757-53A0109 RB and do the
modification and applicable on-
condition action(s).
CONDITION 3:
ANY EXISTING
REPAIR
FOUND.
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Replace the fuselage skin panels
or bond assemblies between
stringers S-14 and S-19 on the
left and right sides, from STA 439
to STA 661; and between
stringers S-14 and S-20 on the
left and right sides, from STA
1180 to STA 1621 with new fuse-
lage skin panels or bond assem-
blies.
CONDITION 4:
NO EXISTING
REPAIR
FOUND.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
9 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 6

Group 3-4:
Table 3: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of
the fuselage skin panels between
stringers S-14 and S-19 on the
left and right sides, from STA 439
to STA 661; and between
stringers S-14 and S-20 on the
left and right sides, from STA
1180 to STA 1621.
All Airplanes.
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Contact The Boeing Company for
alternative modification instruc-
tions to the Requirements Bulletin
757-53A0109 RB and do the
modification and applicable on-
condition action(s).
CONDITION 5:
ANY EXISTING
REPAIR
FOUND.
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Replace the fuselage skin panels
or bond assemblies between
stringers S-14 and S-19 on the
left and right sides, from STA 439
to STA 661; and between
stringers S-14 and S-20 on the
left and right sides, from STA
1180 to STA 1621 with new fuse-
lage skin panels or bond assem-
blies.
CONDITION 6:
NO EXISTING
REPAIR
FOUND.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
10 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 7

Group 5:
Table 4: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of
the fuselage skin panels between
stringers S-14 and S-19 on the
left and right sides, from STA 439
to STA 661; and between
stringers S-14 and S-20 on the
left and right sides, from STA
1180 to STA 1621.
All Airplanes.
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Contact The Boeing Company for
alternative modification instruc-
tions to the Requirements Bulletin
757-53A0109 RB and do the
modification and applicable on-
condition action(s).
CONDITION 7:
ANY EXISTING
REPAIR
FOUND.
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Replace the fuselage skin panels
or bond assemblies between
stringers S-14 and S-19 on the
left and right sides, from STA 439
to STA 661; and between
stringers S-14 and S-20 on the
left and right sides, from STA
1180 to STA 1621 with new fuse-
lage skin panels or bond assem-
blies.
CONDITION 8:
NO EXISTING
REPAIR
FOUND.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
11 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 8

Group 6:
Table 5: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of
the fuselage skin panels between
stringers S-14R and S-19R, from
STA 439 to STA 661; and be-
tween stringers S-14 and S-20 on
the left and right sides, from STA
1180 to STA 1621.
All Airplanes.
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Contact The Boeing Company for
alternative modification instruc-
tions to the Requirements Bulletin
757-53A0109 RB and do the
modification and applicable on-
condition action(s).
CONDITION 9:
ANY EXISTING
REPAIR
FOUND.
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Replace the fuselage skin panels
or bond assemblies between
stringers S-14R and S-19R, from
STA 439 to STA 661; and be-
tween stringers S-14 and S-20 on
the left and right sides, from STA
1180 to STA 1621 with new fuse-
lage skin panels or bond assem-
blies.
CONDITION 10:
NO EXISTING
REPAIR
FOUND.
Group 7:
Table 6: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of
the fuselage skin panels between
stringers S-14R and S-19R, from
STA 439 to STA 661; and be-
tween stringers S-14 and S-20 on
the left and right sides, from STA
1180 to STA 1621.
All Airplanes.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
12 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 9

Group 7:
Table 6: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Contact The Boeing Company for
alternative modification instruc-
tions to the Requirements Bulletin
757-53A0109 RB and do the
modification and applicable on-
condition action(s).
CONDITION 11:
ANY EXISTING
REPAIR
FOUND.
-Within 2,000 flight
cycles after the
Original Issue date
of Requirements
Bulletin 757-
53A0109 RB but
not earlier than
51,000 total flight
cycles.
Before 60,000 total
flight cycles but not
earlier than 51,000
total flight cycles.
Replace the fuselage skin panels
or bond assemblies between
stringers S-14R and S-19R, from
STA 439 to STA 661; and be-
tween stringers S-14 and S-20 on
the left and right sides, from STA
1180 to STA 1621 with new fuse-
lage skin panels or bond assem-
blies.
CONDITION 12:
NO EXISTING
REPAIR
FOUND.
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 Branch approves accomplishment of
the modification defined in this requirements bulletin as an alternative method of compliance (AMOC) to
the requirements of paragraph (g) of AD 2019-07-04 for the inspections of the inner skin at the S-14L and
S-14R fuselage skin lap splices along the lower fastener row at areas common to a skin panel replacement
accomplished in accordance with this bulletin. All provisions of AD 2019-07-04 that are not specifically
referenced above remain fully applicable and must be complied with accordingly.
In addition, the Manager of the FAA Continued Operational Safety Branch approves accomplishment of
the modification defined in this requirements bulletin as an alternative method of compliance (AMOC) to
the requirements of paragraph (g) of AD 2016-15-04 for the inspections of the inner skin at the S-14R
fuselage skin lap splices along the lower fastener row at areas common to a skin panel replacement
accomplished in accordance with this bulletin. All provisions of AD 2016-15-04 that are not specifically
referenced above remain fully applicable and must be complied with accordingly.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
13 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 10

In addition, the Manager of the FAA Continued Operational Safety Branch approves accomplishment of
the modification defined in this requirements bulletin as an alternative method of compliance (AMOC) to
the requirements of paragraph (g) of AD 2018-18-07 for the inspections of the inner skin at the S-14L and
S-14R fuselage skin lap splices along the lower fastener row at areas common to a skin panel replacement
accomplished in accordance with this bulletin, and for the inspections of the outer skin at the S-19L, S-19R,
S-20L and S-20R fuselage skin lap splices along the upper fastener row at areas common to a skin panel
replacement accomplished in accordance with this bulletin. All provisions of AD 2018-18-07 that are not
specifically referenced above remain fully applicable and must be complied with accordingly.
In addition, the Manager of the FAA Continued Operational Safety Branch approves accomplishment of
the modification defined in this requirements bulletin as an alternative method of compliance (AMOC) to
the requirements of paragraphs (g) and (h)(1) of AD 2020-01-18 for the SSI 53-30-07 and SSI 53-60-07
inspections of the inner skin at the S-14L and S-14R fuselage skin lap splices along the lower fastener row
as listed in Section 9 of Maintenance Planning Document (MPD), D622N001-9, at areas common to a skin
panel replacement accomplished in accordance with this bulletin, and for the inspections of the outer skin
at the S-19L, S-19R, S-20L and S-20R fuselage skin lap splices along the upper fastener row as listed in
Section 9 of Maintenance Planning Document (MPD), D622N001-9, at areas common to a skin panel
replacement accomplished in accordance with this bulletin. All provisions of AD 2020-01-18 that are not
specifically referenced above remain fully applicable and must be complied with accordingly.
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
14 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### 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).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
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### Page 12

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. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
14. Refer to APPENDIX G through APPENDIX L for skin panel, bond assembly, panel
assembly, and panel installation part number applicability.
15. A maintenance records check for repairs on a skin panel to be replaced can be done
provided an existing repair can be conclusively determined from that check.
16. Some Boeing skin panel spare parts are supplied in a temporary configuration. Those
parts are identified with a 'U' or 'Y' in the place of the '-' (dash) in the part number. It
is permitted to install parts identified with a 'U' or 'Y' as an alternative to the '-' (dash)
part number. Boeing Drawing 005W0900 contains more data.
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### Page 13

17. For skin panels with a 'Y' configuration, trim the skin on the bottom end, aft end, and
forward end of the skin as necessary to fit. Make sure to maintain an edge margin
of two hole diameters. Remove all nicks, burrs, and sharp edges from trimmed panel
edges. Keep a surface finish of 125 Ra or better. Apply chemical conversion coating
to bare metal surfaces on any trimmed edges of skin panels. Refer to SOPM 20-43-03
as an accepted procedure. Apply two coats of BMS 10-11, TYPE I primer where
chemical conversion coating was applied. Refer to SOPM 20-41-02 as an accepted
procedure. Do not apply primer within fastener holes.
18.
Many SOPM equivalent process to the BAC specification processes specified in
Boeing drawings may be found in SOPM 20-00-00.
B. WORK INSTRUCTIONS
Actions Required for Compliance
1. Requirements
Group 1:
Table 1: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Refer to the listed proce-
dures in SB 757-53A0109
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of Com-
pliance
ActionCondition
-FIGURE 1Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of the
fuselage skin panels between
stringers S-14 and S-19 on the left
and right sides, from STA 439 to
STA 661; and between stringers
S-14L and S-20L, from STA 1180
to STA 1621; and between
stringers S-14R and S-20R, from
STA 1459 to STA 1621.
All Airplanes.
--Contact The Boeing Company for
alternative modification instructions
to the Requirements Bulletin 757-
53A0109 RB and do the modifica-
tion and applicable on-condition
action(s).
CONDITION 1: ANY
EXISTING REPAIR
FOUND.
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### Page 14

Group 1:
Table 1: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Refer to the listed proce-
dures in SB 757-53A0109
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of Com-
pliance
ActionCondition
Do PART 1: OPEN ACCESS
and PART 2: PREPARATION
AND DETAILED INSPECTION
(DET).
-Replace the fuselage skin panels
or bond assemblies between
stringers S-14 and S-19 on the left
and right sides, from STA 439 to
STA 661; and between stringers
S-14L and S-20L, from STA 1180
to STA 1621; and between
stringers S-14R and S-20R, from
STA 1459 to STA 1621 with new
fuselage skin panels or bond as-
semblies.
CONDITION 2: NO EX-
ISTING REPAIR
FOUND.
-Left Side:
FIGURE 7
FIGURE 8
FIGURE 12
FIGURE 14
FIGURE 22
FIGURE 23
Right Side:
FIGURE 9
FIGURE 10
FIGURE 25
FIGURE 27
Do PART 3: CLOSE ACCESS.-
Group 2:
Table 2: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Refer to the listed proce-
dures in SB 757-53A0109
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of Com-
pliance
ActionCondition
-FIGURE 2Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of the
fuselage skin panels between
stringers S-14 and S-19 on the left
and right sides, from STA 439 to
STA 661; and between stringers
S-14 and S-20 on the left and right
sides, from STA 1180 to STA
1621.
All Airplanes.
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### Page 15

Group 2:
Table 2: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Refer to the listed proce-
dures in SB 757-53A0109
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of Com-
pliance
ActionCondition
--Contact The Boeing Company for
alternative modification instructions
to the Requirements Bulletin 757-
53A0109 RB and do the modifica-
tion and applicable on-condition
action(s).
CONDITION 3: ANY
EXISTING REPAIR
FOUND.
Do PART 1: OPEN ACCESS
and PART 2: PREPARATION
AND DETAILED INSPECTION
(DET).
-Replace the fuselage skin panels
or bond assemblies between
stringers S-14 and S-19 on the left
and right sides, from STA 439 to
STA 661; and between stringers
S-14 and S-20 on the left and right
sides, from STA 1180 to STA 1621
with new fuselage skin panels or
bond assemblies.
CONDITION 4: NO EX-
ISTING REPAIR
FOUND.
-Left Side:
FIGURE 7
FIGURE 8
FIGURE 12
FIGURE 14
FIGURE 22
FIGURE 23
Right Side:
FIGURE 9
FIGURE 10
FIGURE 17
FIGURE 19
FIGURE 25
FIGURE 27
Do PART 3: CLOSE ACCESS.-
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### Page 16

Group 3-4:
Table 3: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Refer to the listed proce-
dures in SB 757-53A0109
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of Com-
pliance
ActionCondition
-FIGURE 3Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of the
fuselage skin panels between
stringers S-14 and S-19 on the left
and right sides, from STA 439 to
STA 661; and between stringers
S-14 and S-20 on the left and right
sides, from STA 1180 to STA
1621.
All Airplanes.
--Contact The Boeing Company for
alternative modification instructions
to the Requirements Bulletin 757-
53A0109 RB and do the modifica-
tion and applicable on-condition
action(s).
CONDITION 5: ANY
EXISTING REPAIR
FOUND.
Do PART 1: OPEN ACCESS
and PART 2: PREPARATION
AND DETAILED INSPECTION
(DET).
-Replace the fuselage skin panels
or bond assemblies between
stringers S-14 and S-19 on the left
and right sides, from STA 439 to
STA 661; and between stringers
S-14 and S-20 on the left and right
sides, from STA 1180 to STA 1621
with new fuselage skin panels or
bond assemblies.
CONDITION 6: NO EX-
ISTING REPAIR
FOUND.
-Left Side:
FIGURE 7
FIGURE 8
FIGURE 13
FIGURE 15
FIGURE 22
FIGURE 23
Right Side:
FIGURE 9
FIGURE 10
FIGURE 18
FIGURE 20
FIGURE 25
FIGURE 27
Do PART 3: CLOSE ACCESS.-
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### Page 17

Group 5:
Table 4: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Refer to the listed proce-
dures in SB 757-53A0109
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of Com-
pliance
ActionCondition
-FIGURE 4Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of the
fuselage skin panels between
stringers S-14 and S-19 on the left
and right sides, from STA 439 to
STA 661; and between stringers
S-14 and S-20 on the left and right
sides, from STA 1180 to STA
1621.
All Airplanes.
--Contact The Boeing Company for
alternative modification instructions
to the Requirements Bulletin 757-
53A0109 RB and do the modifica-
tion and applicable on-condition
action(s).
CONDITION 7: ANY
EXISTING REPAIR
FOUND.
Do PART 1: OPEN ACCESS
and PART 2: PREPARATION
AND DETAILED INSPECTION
(DET).
-Replace the fuselage skin panels
or bond assemblies between
stringers S-14 and S-19 on the left
and right sides, from STA 439 to
STA 661; and between stringers
S-14 and S-20 on the left and right
sides, from STA 1180 to STA 1621
with new fuselage skin panels or
bond assemblies.
CONDITION 8: NO EX-
ISTING REPAIR
FOUND.
-Left Side:
FIGURE 7
FIGURE 8
FIGURE 12
FIGURE 14
FIGURE 22
FIGURE 23
Right Side:
FIGURE 9
FIGURE 10
FIGURE 17
FIGURE 19
FIGURE 26
FIGURE 29
Do PART 3: CLOSE ACCESS.-
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REQUIREMENTS BULLETIN 757-53A0109
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### Page 18

Group 6:
Table 5: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Refer to the listed proce-
dures in SB 757-53A0109
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of Com-
pliance
ActionCondition
-FIGURE 5Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of the
fuselage skin panels between
stringers S-14R and S-19R, from
STA 439 to STA 661; and between
stringers S-14 and S-20 on the left
and right sides, from STA 1180 to
STA 1621.
All Airplanes.
--Contact The Boeing Company for
alternative modification instructions
to the Requirements Bulletin 757-
53A0109 RB and do the modifica-
tion and applicable on-condition
action(s).
CONDITION 9: ANY
EXISTING REPAIR
FOUND.
Do PART 1: OPEN ACCESS
and PART 2: PREPARATION
AND DETAILED INSPECTION
(DET).
-Replace the fuselage skin panels
or bond assemblies between
stringers S-14R and S-19R, from
STA 439 to STA 661; and between
stringers S-14 and S-20 on the left
and right sides, from STA 1180 to
STA 1621 with new fuselage skin
panels or bond assemblies.
CONDITION 10: NO
EXISTING REPAIR
FOUND.
-Left Side:
FIGURE 13
FIGURE 16
FIGURE 22
FIGURE 24
Right Side:
FIGURE 9
FIGURE 11
FIGURE 18
FIGURE 21
FIGURE 25
FIGURE 28
Do PART 3: CLOSE ACCESS.-
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### Page 19

Group 7:
Table 6: Section 43 and Section 46 - Fuselage Skin Panel/Bond Assembly Replacement
Refer to the listed proce-
dures in SB 757-53A0109
Original Issue or later ap-
proved revisions as an ac-
cepted procedure
Method of Com-
pliance
ActionCondition
-FIGURE 6Do a General Visual Inspection
(GVI) or a Maintenance Records
Check for any existing repair of the
fuselage skin panels between
stringers S-14R and S-19R, from
STA 439 to STA 661; and between
stringers S-14 and S-20 on the left
and right sides, from STA 1180 to
STA 1621.
All Airplanes.
--Contact The Boeing Company for
alternative modification instructions
to the Requirements Bulletin 757-
53A0109 RB and do the modifica-
tion and applicable on-condition
action(s).
CONDITION 11: ANY
EXISTING REPAIR
FOUND.
Do PART 1: OPEN ACCESS
and PART 2: PREPARATION
AND DETAILED INSPECTION
(DET).
-Replace the fuselage skin panels
or bond assemblies between
stringers S-14R and S-19R, from
STA 439 to STA 661; and between
stringers S-14 and S-20 on the left
and right sides, from STA 1180 to
STA 1621 with new fuselage skin
panels or bond assemblies.
CONDITION 12: NO
EXISTING REPAIR
FOUND.
-Left Side:
FIGURE 12
FIGURE 14
FIGURE 22
FIGURE 23
Right Side:
FIGURE 9
FIGURE 10
FIGURE 17
FIGURE 19
FIGURE 26
FIGURE 29
Do PART 3: CLOSE ACCESS.-
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ALERTALERT

### Page 20 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 1.
STA  STA  STA  STA
439  661  1180  1459  1621  STA  STA
1720
S-26R
S-20R  IS-26R
LS-19R
S-14R  00000000000  100000 0 09 5-109  00000c  000000 000000  S-20R  - S-14R
S-10R
S-4R  S-4R
S-1  - S-1
S-4L  S-4L
I S-10L
0000000001000  J00000 o 02 S:10L  0000 300000000  S-14L
S-14L
S-20L
S-20L  I S-19L  S-26L
S-26L
FWD
GENERAL VISUAL INSPECTION AREA  3072450
FIGURE 1: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 1 OF 2)
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See page 1 for details  24 of 105

### 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) 1STA 439 TO STA 661,
S-14L TO S-19L
SKIN PANELInspect1
(a) 1STA 439 TO STA 661,
S-14R TO S-19R
SKIN PANELInspect
(a) 1STA 1180 TO STA
1459, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14R TO S-20R
SKIN PANELInspect
(a)
Do a General Visual Inspection (GVI) of the fuselage skin panel for any existing repair.
FIGURE 1: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 2 OF 2)
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ALERTALERT

### Page 22 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 2.
STA  STA  STA  STA
439  661  1180  1459  1621  STA  STA
1720
S-26R
S-20R  1S-26R
LS-19R
S-14R  00000000000  100000 0 09 5-109  000000 000000  S-20R  - S-14R
S-10R
S-4R  I S-4R
S-1  - S-1
S-4L  S-4L
0000000001000  100000 0 02 5101  000r200090000  I S-10L  S-14L
S-14L
S-20L
S-20L  I S-19L  S-26L
S-26L
FWD
GENERAL VISUAL INSPECTION AREA  3072478
FIGURE 2: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 1 OF 2)
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See page 1 for details  26 of 105

### Page 23

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) 1STA 439 TO STA 661,
S-14L TO S-19L
SKIN PANELInspect1
(a) 1STA 439 TO STA 661,
S-14R TO S-19R
SKIN PANELInspect
(a) 1STA 1180 TO STA
1459, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1180 TO STA
1459, S-14R TO S-20R
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14R TO S-20R
SKIN PANELInspect
(a)
Do a General Visual Inspection (GVI) of the fuselage skin panel for any existing repair.
FIGURE 2: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 2 OF 2)
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REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 24 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 3-4.
STA  STA  STA  STA
439  661  1180  1459  1621  STA  STA
1720
S-26R
S-20R  1S-26R
S- 19R
S-14R  00000000000  100000 0 09 5-109  0a 000000000 000000  S-20R  - S-14R
S-10R
S-4R  I S-4R
S-1  - S-1
S-4L  S-4L
0000000001000  0000 0 08 5102  0p000r/99000000  I S-10L  S-14L
S-14L
S-20L
S-20L  I S-19L  S-26L
S-26L
FWD
GENERAL VISUAL INSPECTION AREA  3072455
FIGURE 3: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
757-53A0109 RB
Export Controlled ECCN: 9E991
See page 1 for details  28 of 105

### Page 25

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) 1STA 439 TO STA 661,
S-14L TO S-19L
SKIN PANELInspect1
(a) 1STA 439 TO STA 661,
S-14R TO S-19R
SKIN PANELInspect
(a) 1STA 1180 TO STA
1459, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1180 TO STA
1459, S-14R TO S-20R
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14R TO S-20R
SKIN PANELInspect
(a)
Do a General Visual Inspection (GVI) of the fuselage skin panel for any existing repair.
FIGURE 3: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 2 OF 2)
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REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 26 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 5.
STA  STA  STA  STA
439  661  1180  1459  1621  STA  I STA
1720
S-26R
S-20R  1S-26R
LS-19R
S-14R  00000000000  100000 0 09 5-109  5000001000000  S-20R  - S-14R
S-10R
S-4R  I S-4R
S-1  - S-1
S-4L  S-4L
I S-10L
0000000001000  J00000 o 02 S:10L  10000200000000  S-14L
S-14L
S-20L
S-20L  I S-19L  S-26L
S-26L
FWD
GENERAL VISUAL INSPECTION AREA  3072482
FIGURE 4: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
757-53A0109 RB
Export Controlled ECCN: 9E991
See page 1 for details  30 of 105

### 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 parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a) 1STA 439 TO STA 661,
S-14L TO S-19L
SKIN PANELInspect1
(a) 1STA 439 TO STA 661,
S-14R TO S-19R
SKIN PANELInspect
(a) 1STA 1180 TO STA
1459, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1180 TO STA
1459, S-14R TO S-20R
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14R TO S-20R
SKIN PANELInspect
(a)
Do a General Visual Inspection (GVI) of the fuselage skin panel for any existing repair.
FIGURE 4: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 2 OF 2)
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REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 28 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 6.
STA  STA  STA  STA
439  661  1180  1459  1621  STA  STA
1720
S-26R
S-20R  1S-26R
S- 19R
S-14R  J00000 O 05 S:10R  00000d 000000000 1000000  S-20R  - S-14R
S-10R
S-4R  I S-4R
S-1 -  - S-1
S-4L  S-4L
00000  0op00 o or S-10L  apoor/ 99000000  I S-10L  S-14L
S-14L
S-20L
S-20L  I S-19L  S-26L
S-26L
FWD
GENERAL VISUAL INSPECTION AREA  3072490
FIGURE 5: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
757-53A0109 RB
Export Controlled ECCN: 9E991
See page 1 for details  32 of 105

### Page 29

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) 1STA 439 TO STA 661,
S-14R TO S-19R
SKIN PANELInspect1
(a) 1STA 1180 TO STA
1459, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1180 TO STA
1459, S-14R TO S-20R
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14R TO S-20R
SKIN PANELInspect
(a)
Do a General Visual Inspection (GVI) of the fuselage skin panel for any existing repair.
FIGURE 5: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
33 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 30 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 7.
STA  STA  STA  STA
439  661  1180  1459  1621  STA  STA
1720
S-26R
S-20R  1S-26R
IS-19R
S-14R  J00000 O 05 S:10R  S-20R
5000001000000  - S-14R
S-10R
S-4R  I S-4R
S-1 -  - S-1
S-4L  S-4L
00000  0op00 o or S-10L  Topor 200090000  S-14L  I S-10L
S-14L
S-20L
S-20L  I S-19L  S-26L
S-26L
FWD
GENERAL VISUAL INSPECTION AREA  3072520
FIGURE 6: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
757-53A0109 RB
Export Controlled ECCN: 9E991
See page 1 for details  34 of 105

### Page 31

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) 1STA 439 TO STA 661,
S-14R TO S-19R
SKIN PANELInspect1
(a) 1STA 1180 TO STA
1459, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1180 TO STA
1459, S-14R TO S-20R
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14L TO S-20L
SKIN PANELInspect
(a) 1STA 1459 TO STA
1621, S-14R TO S-20R
SKIN PANELInspect
(a)
Do a General Visual Inspection (GVI) of the fuselage skin panel for any existing repair.
FIGURE 6: SECTION 43 AND SECTION 46 - FUSELAGE SKIN PANEL - INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
35 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 32

This Figure applies only to: Group 1-5.
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
DO NOT REMOVE MORE THAN ONE SKIN PANEL AT A TIME.
CAUTION
(a)(b)1STA 439 TO STA 661,
S-14L TO S-19L
SKIN PANELRemove1
FIGURE 7: LEFT SIDE, SECTION 43 - FUSELAGE SKIN PANEL - REMOVAL
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
36 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 33

More DataQtyIdentificationNameTaskStep
(a)
Remove fasteners from the skin panel. Refer to 757-200 SRM 51-40-02 as an accepted procedure.
(b) Removal of other interfacing structure, including but not limited to doublers, triplers, etc. may occur while
removing the skin panel part number listed in APPENDIX G. Leave stringers and stringer splices in place.
Remove and keep all serviceable parts except for the skin panel part number listed in APPENDIX G for
later re-installation.
FIGURE 7: LEFT SIDE, SECTION 43 - FUSELAGE SKIN PANEL - REMOVAL
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
37 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 34 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 1-5.
S-1 -
S-4L
S-10L
000000000000  00
S-14L
S-19L
S-20L
S-26L
STA  STA  STA
439  661  900
3073124
FIGURE 8: LEFT SIDE, SECTION 43 - FUSELAGE SKIN PANEL - INSTALLATION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
Export Controlled ECCN: 9E991  757-53A0109 RB
See page 1 for details  38 of 105

### Page 35

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)(b)1STA 439 TO STA 661,
S-14L TO S-19L
SKIN PANELInstall (New)1
(a)
Install the skin panel in accordance with the applicable panel assembly (if any) and installation drawing
listed in APPENDIX G.
1. Maximum permitted fastener hole size is 1/32 inch larger than panel assembly (if any) and instal-
lation drawing nominal diameter.
2. Maintain 2D edge margin with existing fastener hole locations.
3. Do not introduce scratches greater than 0.001 inch deep on the replacement skin panel and in-
terfacing surfaces, particularly during the process of deburring holes.
(b) Reinstall any kept, serviceable interfacing structure and interfacing parts, including but not limited to
doublers, triplers, etc. Unserviceable parts must be replaced with serviceable parts.
FIGURE 8: LEFT SIDE, SECTION 43 - FUSELAGE SKIN PANEL - INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
39 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 36 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
- -S-1
S-4R
S-10R
10000000
S-14R
S-19R
S-20R
S-26R
STA
439
FWD
3073663
FIGURE 9: RIGHT SIDE, SECTION 43 - FUSELAGE SKIN PANEL - REMOVAL
(SHEET 1 OF 2)
Original Issue: September 25, 2025
Export Controlled ECCN: 9E991  757-53A0109 RB
See page 1 for details  40 of 105

### Page 37

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
DO NOT REMOVE MORE THAN ONE SKIN PANEL AT A TIME.
CAUTION
(a)(b)1STA 439 TO STA 661,
S-14R TO S-19R
SKIN PANELRemove1
(a)
Remove fasteners from the skin panel. Refer to 757-200 SRM 51-40-02 or 757-200CB SRM 51-40-02
as an accepted procedure.
(b) Removal of other interfacing structure, including but not limited to doublers, triplers, etc. may occur while
removing the skin panel part number listed in APPENDIX J. The bear strap may be removed and kept,
or left in place. Leave stringers and stringer splices in place. Remove and keep all serviceable parts except
for the skin panel part number listed in APPENDIX J for later re-installation.
FIGURE 9: RIGHT SIDE, SECTION 43 - FUSELAGE SKIN PANEL - REMOVAL
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
41 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 38 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 1-5, 7.
-S-1
S-4R
S-10R
000000
S-14R
S-19R
S-20R
S-26R
STA  STA  STA
900  661  439
FWD  3073666
FIGURE 10: RIGHT SIDE, SECTION 43 - FUSELAGE SKIN PANEL - INSTALLATION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
757-53A0109 RB
Export Controlled ECCN: 9E991
See page 1 for details  42 of 105

### Page 39

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)(b)1STA 439 TO STA 661,
S-14R TO S-19R
SKIN PANELInstall (New)1
(a)
Install the skin panel in accordance with the applicable installation drawing listed in APPENDIX J.
1. Maximum permitted fastener hole size is 1/32 inch larger than installation drawing nominal diam-
eter.
2. Maintain 2D edge margin with existing fastener hole locations.
3. Do not introduce scratches greater than 0.001 inch deep on the replacement skin panel and in-
terfacing surfaces, particularly during the process of deburring holes.
(b) Reinstall any kept, serviceable interfacing structure and interfacing parts, including but not limited to bear
strap, doublers, triplers, etc. Unserviceable parts must be replaced with serviceable parts.
FIGURE 10: RIGHT SIDE, SECTION 43 - FUSELAGE SKIN PANEL - INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
43 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 40 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 6.
- S-1
S-4R
S-10R
0000000
S-14R
OC
S-19R
S-20R
S-26R
STA  STA  STA
900  661  439
3072491
FIGURE 11: RIGHT SIDE, SECTION 43 - FUSELAGE SKIN PANEL - INSTALLATION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
757-53A0109 RB
Export Controlled ECCN: 9E991
See page 1 for details  44 of 105

### Page 41

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)(b)1STA 439 TO STA 661,
S-14R TO S-19R
SKIN PANELInstall (New)1
(a)
Install the skin panel in accordance with the applicable installation drawing listed in APPENDIX J.
1. Maximum permitted fastener hole size is 1/32 inch larger than installation drawing nominal diam-
eter.
2. Maintain 2D edge margin with existing fastener hole locations.
3. Do not introduce scratches greater than 0.001 inch deep on the replacement skin panel and in-
terfacing surfaces, particularly during the process of deburring holes.
(b) Reinstall any kept, serviceable interfacing structure and interfacing parts, including but not limited to bear
strap, doublers, triplers, etc. Unserviceable parts must be replaced with serviceable parts.
FIGURE 11: RIGHT SIDE, SECTION 43 - FUSELAGE SKIN PANEL - INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
45 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 42 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 1-2, 5, 7.
STA  STA  STA STA
1180  1380  1459 1500
- S-1
→ S-4L
S-10L
0000000  > S-14L
S-20L
S S-26L
3073126
FIGURE 12: LEFT SIDE, SECTION 46 - FUSELAGE SKIN PANEL/BOND ASSEMBLY - REMOVAL
(SHEET 1 OF 2)
Original Issue: September 25, 2025
Export Controlled ECCN: 9E991  757-53A0109 RB
See page 1 for details  46 of 105

### Page 43

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
DO NOT REMOVE MORE THAN ONE SKIN PANEL AT A TIME.
CAUTION
(a)(b)(c)1STA 1180 TO STA
1459, S-14L TO S-20L
SKIN PANEL OR
BOND ASSEMBLY
Remove1
(a)
Remove fasteners attaching the highest level part (bond assembly or skin panel) within the panel instal-
lation listed in APPENDIX H. Refer to 757-200 SRM 51-40-02 as an accepted procedure.
(b) Removal of other interfacing structure, including but not limited to doublers, triplers, etc. may occur while
removing the skin panel or bond assembly part number listed in APPENDIX H. The bear strap may be
removed and kept, or left in place. Leave stringers and stringer splices in place. Remove and keep all
serviceable parts except for the skin panel or bond assembly part number listed in APPENDIX H for later
re-installation.
(c) It may be necessary to remove some fasteners from an adjacent skin panel in order to detach and remove
a bond assembly with a bear strap that extends beneath an adjacent skin panel.
FIGURE 12: LEFT SIDE, SECTION 46 - FUSELAGE SKIN PANEL/BOND ASSEMBLY - REMOVAL
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
47 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 44 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 3-4, 6.
STA  STA STA
1180  1459 1500
[]-s-1
> S-4L
S-10L
00000000000
> S-14L
S-20L
- S-26L
FWD
3073134
FIGURE 13: LEFT SIDE, SECTION 46 - FUSELAGE SKIN PANEL - REMOVAL
(SHEET 1 OF 2)
Original Issue: September 25, 2025
757-53A0109 RB
Export Controlled ECCN: 9E991
See page 1 for details  48 of 105

### Page 45

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
DO NOT REMOVE MORE THAN ONE SKIN PANEL AT A TIME.
CAUTION
(a)(b)1STA 1180 TO STA
1459, S-14L TO S-20L
SKIN PANELRemove1
(a)
Remove fasteners from the skin panel. Refer to 757-200 SRM 51-40-02 or 757-200CB SRM 51-40-02
as an accepted procedure.
(b) Removal of other interfacing structure, including but not limited to doublers, triplers, etc. may occur while
removing the skin panel part number listed in APPENDIX H. Leave stringers and stringer splices in place.
Remove and keep all serviceable parts except for the skin panel part number listed in APPENDIX H for
later re-installation.
FIGURE 13: LEFT SIDE, SECTION 46 - FUSELAGE SKIN PANEL - REMOVAL
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
49 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 46 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 1-2, 5, 7.
STA  STA STA
1180  1459 1500
• S-1
_ S-4L
S-10L
J00  0000
S-14L
S-20L
S-26L
3073135
FIGURE 14: LEFT SIDE, SECTION 46 - FUSELAGE SKIN PANEL/BOND ASSEMBLY - INSTALLATION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
757-53A0109 RB
Export Controlled ECCN: 9E991
See page 1 for details  50 of 105

### Page 47

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)(b)(c)1STA 1180 TO STA
1459, S-14L TO S-20L
SKIN PANEL OR
BOND ASSEMBLY
Install (New)1
(a) Install the highest level replacement part (bond assembly or skin panel) in accordance with the applicable
installation drawing listed in APPENDIX H.
1. Maximum permitted fastener hole size is 1/32 inch larger than installation drawing nominal diam-
eter.
2.
Maintain 2D edge margin with existing fastener hole locations.
3. Do not introduce scratches greater than 0.001 inch deep on the replacement skin panel and in-
terfacing surfaces, particularly during the process of deburring holes.
(b) Reinstall any kept, serviceable interfacing structure and interfacing parts, including but not limited to bear
strap, doublers, triplers, etc. Unserviceable parts must be replaced with serviceable parts.
(c) Install replacement fasteners at locations where fasteners were required to be removed from an adjacent
skin panel after installing a replacement bond assembly with a bear strap that extends beneath the adjacent
skin panel.
FIGURE 14: LEFT SIDE, SECTION 46 - FUSELAGE SKIN PANEL/BOND ASSEMBLY - INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
51 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 48 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 3-4.
STA  STA STA
1180  1459 1500
- S-1
S-10L
00000000000  > S-14L
S-20L
→ S-26L
FWD
3073137
FIGURE 15: LEFT SIDE, SECTION 46 - FUSELAGE SKIN PANEL - INSTALLATION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
Export Controlled ECCN: 9E991  757-53A0109 RB
See page 1 for details  52 of 105

### Page 49

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)(b)1STA 1180 TO STA
1459, S-14L TO S-20L
SKIN PANELInstall (New)1
(a)
Install the skin panel in accordance with the applicable panel assembly (if any) and installation drawing
listed in APPENDIX H.
1. Maximum permitted fastener hole size is 1/32 inch larger than panel assembly (if any) and instal-
lation drawing nominal diameter.
2. Maintain 2D edge margin with existing fastener hole locations.
3. Do not introduce scratches greater than 0.001 inch deep on the replacement skin panel and in-
terfacing surfaces, particularly during the process of deburring holes.
(b) Reinstall any kept, serviceable interfacing structure and interfacing parts, including but not limited to
doublers, triplers, etc. Unserviceable parts must be replaced with serviceable parts.
FIGURE 15: LEFT SIDE, SECTION 46 - FUSELAGE SKIN PANEL - INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
53 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 50 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 6.
STA  STA STA
1180  1459 1500
- S-1
S S-4L
00000000000S14L  • S-10L
L  S-20L
→ S-26L
-WD
3073154
FIGURE 16: LEFT SIDE, SECTION 46 - FUSELAGE SKIN PANEL - INSTALLATION
(SHEET 1 OF 2)
Original issue: September 25, 2025
Export Controlled ECCN: 9E991  757-53A0109 RB
See page 1 for details  54 of 105

### Page 51

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)(b)1STA 1180 TO STA
1459, S-14L TO S-20L
SKIN PANELInstall (New)1
(a)
Install the skin panel in accordance with the applicable panel assembly and installation drawing listed in
APPENDIX H.
1. Maximum permitted fastener hole size is 1/32 inch larger than panel assembly and installation
drawing nominal diameter.
2. Maintain 2D edge margin with existing fastener hole locations.
3. Do not introduce scratches greater than 0.001 inch deep on the replacement skin panel and in-
terfacing surfaces, particularly during the process of deburring holes.
(b) Reinstall any kept, serviceable interfacing structure and interfacing parts, including but not limited to
doublers, triplers, etc. Unserviceable parts must be replaced with serviceable parts.
FIGURE 16: LEFT SIDE, SECTION 46 - FUSELAGE SKIN PANEL - INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
55 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 52 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 2, 5, 7.
STA STA  STA
1500 1459  1180
S-1
S-4R
S-10R
1000C
S-14R-
S-20R
S-26R -
3073668
FIGURE 17: RIGHT SIDE, SECTION 46 - FUSELAGE SKIN PANEL/BOND ASSEMBLY - REMOVAL
(SHEET 1 OF 2)
Original Issue: September 25, 2025
Export Controlled ECCN: 9E991  757-53A0109 RB
See page 1 for details  56 of 105

### Page 53

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
DO NOT REMOVE MORE THAN ONE SKIN PANEL AT A TIME.
CAUTION
(a)(b)(c)1STA 1180 TO STA
1459, S-14R TO S-20R
SKIN PANEL OR
BOND ASSEMBLY
Remove1
(a) Remove fasteners attaching the highest level part (bond assembly or skin panel) within the panel assembly
(if any) or installation listed in APPENDIX K. Refer to 757-200 SRM 51-40-02 as an accepted procedure.
(b) Removal of other interfacing structure, including but not limited to doublers, triplers, etc. may occur while
removing the skin panel or bond assembly part number listed in APPENDIX K. The bear strap may be
removed and kept, or left in place. Leave stringers and stringer splices in place. Remove and keep all
serviceable parts except for the skin panel or bond assembly part number listed in APPENDIX K for later
re-installation.
(c) It may be necessary to remove some fasteners from an adjacent skin panel in order to detach and remove
a bond assembly with a bear strap that extends beneath an adjacent skin panel.
FIGURE 17: RIGHT SIDE, SECTION 46 - FUSELAGE SKIN PANEL/BOND ASSEMBLY - REMOVAL
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
57 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 54 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 3-4, 6.
STA STA  STA
1500 1459  1180
S-1
S-4R T
S-10R
0000000
S-14R.
S-20R
S-26R -
FWD
3073670
FIGURE 18: RIGHT SIDE, SECTION 46 - FUSELAGE BOND ASSEMBLY - REMOVAL
(SHEET 1 OF 2)
Original Issue: September 25, 2025
Export Controlled ECCN: 9E991  757-53A0109 RB
See page 1 for details  58 of 105

### Page 55

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
DO NOT REMOVE MORE THAN ONE SKIN PANEL AT A TIME.
CAUTION
(a)(b)(c)1STA 1180 TO STA
1459, S-14R TO S-20R
BOND ASSEMBLYRemove1
(a)
Remove fasteners attaching the bond assembly. Refer to 757-200 SRM 51-40-02 or 757-200CB SRM
51-40-02 as an accepted procedure.
(b) Removal of other interfacing structure, including but not limited to doublers, triplers, etc. may occur while
removing the bond assembly part number listed in APPENDIX K. The bear strap may be removed and
kept, or left in place. Leave stringers and stringer splices in place. Remove and keep all serviceable parts
except for the bond assembly part number listed in APPENDIX K for later re-installation.
(c) It may be necessary to remove some fasteners from an adjacent skin panel in order to detach and remove
a bond assembly with a bear strap that extends beneath an adjacent skin panel.
FIGURE 18: RIGHT SIDE, SECTION 46 - FUSELAGE BOND ASSEMBLY - REMOVAL
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
59 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 56 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 2, 5, 7.
STA STA  STA
1500 1459  1180
S-1-
S-4R^
S-10R
00000000  00000
S-14R-
S-20R
S-26R<
FWD
3073675
FIGURE 19: RIGHT SIDE, SECTION 46 - FUSELAGE SKIN PANEL/BOND ASSEMBLY - INSTALLATION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
757-53A0109 RB
Export Controlled ECCN: 9E991
See page 1 for details  60 of 105

### Page 57

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)(b)(c)1STA 1180 TO STA
1459, S-14R TO S-20R
SKIN PANEL OR
BOND ASSEMBLY
Install (New)1
(a) Install the highest level replacement part (bond assembly or skin panel) in accordance with the applicable
panel assembly (if any) and installation drawing listed in APPENDIX K.
1. Maximum permitted fastener hole size is 1/32 inch larger than panel assembly (if any) and instal-
lation drawing nominal diameter.
2.
Maintain 2D edge margin with existing fastener hole locations.
3. Do not introduce scratches greater than 0.001 inch deep on the replacement skin panel and in-
terfacing surfaces, particularly during the process of deburring holes.
(b) Reinstall any kept, serviceable interfacing structure and interfacing parts, including but not limited to bear
strap, doublers, triplers, etc. Unserviceable parts must be replaced with serviceable parts.
(c) Install replacement fasteners at locations where fasteners were required to be removed from an adjacent
skin panel after installing a replacement bond assembly with a bear strap that extends beneath the adjacent
skin panel.
FIGURE 19: RIGHT SIDE, SECTION 46 - FUSELAGE SKIN PANEL/BOND ASSEMBLY - INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
61 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 58 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 3-4.
STA STA  STA
1500 1459  1180
S-1-
S-4RT
S-10R
00000000000
S-14R
S-20R
S-26R<
FWD
3073676
FIGURE 20: RIGHT SIDE, SECTION 46 - FUSELAGE BOND ASSEMBLY - INSTALLATION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
Export Controlled ECCN: 9E991  757-53A0109 RB
See page 1 for details  62 of 105

### Page 59

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)(b)(c)1STA 1180 TO STA
1459, S-14R TO S-20R
BOND ASSEMBLYInstall (New)1
(a)
Install the bond assembly in accordance with the applicable panel assembly (if any) and installation
drawing listed in APPENDIX K.
1. Maximum permitted fastener hole size is 1/32 inch larger than panel assembly (if any) and instal-
lation drawing nominal diameter.
2. Maintain 2D edge margin with existing fastener hole locations.
3. Do not introduce scratches greater than 0.001 inch deep on the replacement skin panel and in-
terfacing surfaces, particularly during the process of deburring holes.
(b) Reinstall any kept, serviceable interfacing structure and interfacing parts, including but not limited to bear
strap, doublers, triplers, etc. Unserviceable parts must be replaced with serviceable parts.
(c) Install replacement fasteners at locations where fasteners were required to be removed from an adjacent
skin panel after installing a replacement bond assembly with a bear strap that extends beneath the adjacent
skin panel.
FIGURE 20: RIGHT SIDE, SECTION 46 - FUSELAGE BOND ASSEMBLY - INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991
See page 1 for details
Original Issue: September 25, 2025
757-53A0109 RB
63 of 105
REQUIREMENTS BULLETIN 757-53A0109
ALERTALERT

### Page 60 (OCR)

REQUIREMENTS BULLETIN 757-53A0109
ALERT  ALERT
This Figure applies only to: Group 6.
STA STA  STA
1500 1459  1180
S-1-
S-4R*
S-10R
00000000000c
S-14R<
S-20R
S-26R-
FWD
3073692
FIGURE 21: RIGHT SIDE, SECTION 46 - FUSELAGE BOND ASSEMBLY - INSTALLATION
(SHEET 1 OF 2)
Original Issue: September 25, 2025
757-53A0109 RB
Export Controlled ECCN: 9E991
See page 1 for details  64 of 105

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