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Commercial Airplanes 757 Requirements Bulletin ALERT Number: 757-53A0129 RB Original Issue:
December 08, 2025 ATA System: 5311 SUBJECT: FUSELAGE - Fuselage - Section 43 and Section 46 - Fuselage Frame Lower Lobe Areas 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: December 08, 2025 757-53A0129 RB 1 of 42
3.0
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 08, 2025 757-53A0129 RB 2 of 42 REQUIREMENTS BULLETIN 757-53A0129
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Table of Contents
1. EFFECTIVITY .
.5
A. Airplanes5
B. Spares Affected7
2. CONCURRENT REQUIREMENTS7
3. COMPLIANCE7
4. APPROVAL8
5. ACCOMPLISHMENT INSTRUCTIONS9
A. General Information9
B. Work Instructions11
FIGURE 1: LEFT SIDE - FUSELAGE FRAME LOWER LOBE AREAS BETWEEN STRINGERS S-20L AND S-25L FROM STA 440 TO STA 820 - GENERAL VISUAL INSPECTION (GVI) [Group 1-2] . 13 FIGURE 2: LEFT SIDE - FUSELAGE FRAME LOWER LOBE AREAS BETWEEN STRINGERS S-20L AND S-25L FROM STA 440 TO STA 820 - GENERAL VISUAL INSPECTION (GVI) [Group 3] . 18 FIGURE 3: RIGHT SIDE - FUSELAGE FRAME LOWER LOBE AREAS BETWEEN STRINGERS S-20R AND S-24R FROM STA 440 TO STA 820 - GENERAL VISUAL INSPECTION (GVI) [Group 1-2]
.23
FIGURE 4: RIGHT SIDE - FUSELAGE FRAME LOWER LOBE AREAS BETWEEN STRINGERS S-20R AND S-24R FROM STA 440 TO STA 820 - GENERAL VISUAL INSPECTION (GVI) [Group 3]
.27
FIGURE 5: LEFT SIDE - FUSELAGE FRAME LOWER LOBE AREAS BETWEEN STRINGERS S-25L AND
S-28L FROM STA 1300 TO STA 1661 - GENERAL VISUAL INSPECTION (GVI)31
FIGURE 6: RIGHT SIDE - FUSELAGE FRAME LOWER LOBE AREAS BETWEEN STRINGERS S-25R AND S-27R FROM STA 1300 TO STA 1661 - GENERAL VISUAL INSPECTION (GVI) [Group
1, 3]35
FIGURE 7: RIGHT SIDE - FUSELAGE FRAME LOWER LOBE AREAS BETWEEN STRINGERS S-25R AND S-27R FROM STA 1300 TO STA 1661 - GENERAL VISUAL INSPECTION (GVI) [Group
2]39
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 08, 2025 757-53A0129 RB 3 of 42 REQUIREMENTS BULLETIN 757-53A0129
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Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 08, 2025 757-53A0129 RB 4 of 42 REQUIREMENTS BULLETIN 757-53A0129
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Commercial Airplanes 757 Requirements Bulletin ALERT Number: 757-53A0129 RB Original Issue:
December 08, 2025 ATA System: 5311 SUBJECT: FUSELAGE - Fuselage - Section 43 and Section 46 - Fuselage Frame Lower Lobe Areas Inspection
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER.
THIS IS AN ENHANCED REQUIRED FOR COMPLIANCE DOCUMENT. THE BOEING PROCESSES USED
TO CREATE THE SERVICE BULLETIN (SB) AND THE REQUIREMENTS BULLETIN (RB) ENSURE THAT THE INFORMATION BETWEEN "RC START" AND "RC END" IN THE SB ARE IDENTICAL TO THE INFORMATION IN THE SAME SECTIONS (COMPLIANCE, WORK INSTRUCTIONS…) OF THE RB WHICH THE SB REFERS TO AS THE RELATED DOCUMENT.
1.
Effectivity A. Airplanes This bulletin is applicable to 757-200, 757-200CB, 757-200PF, 757-300 Airplane(s), line number(s) 1-1050 in 3 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, 757-200CB, and 757-200PF Airplanes with two lower cargo doors.
- 1 757-200 Airplanes with three lower cargo doors.- 2 All 757-300 Airplanes.- 3 Airplane Models:
757-200, 757-200CB, 757-200PF, 757-300 GroupVariable Number 1NA001 - NA028 GroupVariable Number 1NA191 - NA199 GroupVariable Number 2NA201 - NA236 Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 08, 2025 757-53A0129 RB 5 of 42
GroupVariable Number 1NA237 - NA239 1NA301 - NA305 2NA341 - NA352 2NA391 - NA399 1NA401 - NA408 1NA441 - NA447 1NA501 - NA586 1NB001 - NB004 1NB021 - NB023 1NB036 - NB041 1NB051 - NB053 1NB061 - NB073 1NB079 1NB131 - NB148 1NB161 - NB162 1NB166 - NB168 1NB201 - NB204 1NB221 - NB228 1NB230 1NB236 1NB239 1NB261 - NB267 1NB291 - NB299 1NB301 - NB302 1NB311 - NB312 1NB321 - NB331 1NB421 - NB438 1NB446 1NB451 - NB454 1NB501 - NB523 1NB561 1NB571 1NB581 - NB583 GroupVariable Number 1NC001 - NC033 1NC041 - NC042 1NC051 - NC052 1NC056 - NC062 1NC066 - NC084 1NC091 - NC094 1NC151 1NC161 1NC901 - NC951 1NC971 - NC974 1ND001 - ND007 1ND011 - ND059 1ND111 - ND113 1ND161 - ND199 1ND201 - ND203 1ND221 - ND225 1ND241 - ND248 1ND301 - ND322 1ND401 1ND891 1ND895 1NE001 - NE008 1NE011 - NE088 1NE091 - NE094 1NE141 - NE150 1NE161 - NE177 1NE201 - NE204 1NE301 - NE302 1NE311 - NE325 1NJ001 - NJ004 1NJ031 - NJ032 1NJ551 - NJ555 3NL001 - NL002 GroupVariable Number 3NL006 - NL017 3NL101 - NL109 3NL141 3NL601 - NL616 1NN001 - NN002 1NN051 - NN052 1NP901 - NP904 1NS601 - NS616 1NT001 - NT009 1NT201 - NT202 1NT231 - NT234 1NT237 - NT240 1NT242 1NT245 - NT248 1NT281 - NT289 1NT341 - NT347 1NT351 - NT360 1NT371 - NT373 1NT375 - NT379 1NT381 - NT386 1NT401 - NT409 1NT411 - NT412 1NT426 - NT427 1NT431 - NT432 1NT436 - NT438 1NT441 - NT442 1NT446 1NT701 - NT769 1NT791 - NT796 1NT861 - NT862 1NT881 - NT885 1NT901 - NT916 1NT971 - NT985 Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 08, 2025 757-53A0129 RB 6 of 42 REQUIREMENTS BULLETIN 757-53A0129
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GroupVariable Number 1NU031 - NU038 3NU701 - NU705 GroupVariable Number 3NU721 - NU728 3NU731 - NU732 GroupVariable Number -- -- 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 757-53A0129 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 757-53A0129 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: Section 43 - Fuselage Frame Lower Lobe Areas - Inspection Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time ActionCondition -Within 36 months after the Original Issue date of Requirements Bulletin 757-53A0129 RB.
Do a General Visual Inspection (GVI) of the fuselage frame lower lobe areas for any existing reinforcing repair.
All Airplanes.
-Before further flight.Contact The Boeing Company for further instructions and do as instructed by The Boeing Company.
CONDITION 1: ANY REIN-
FORCING REPAIR FOUND.
--No further action is required.
CONDITION 2: NO REIN-
FORCING REPAIR FOUND.
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 08, 2025 757-53A0129 RB 7 of 42 REQUIREMENTS BULLETIN 757-53A0129
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Table 2: Section 46 - Fuselage Frame Lower Lobe Areas - Inspection Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time ActionCondition -Within 36 months after the Original Issue date of Requirements Bulletin 757-53A0129 RB.
Do a General Visual Inspection (GVI) of the fuselage frame lower lobe areas for any existing reinforcing repair.
All Airplanes.
-Before further flight.Contact The Boeing Company for further instructions and do as instructed by The Boeing Company.
CONDITION 3: ANY REIN-
FORCING REPAIR FOUND.
--No further action is required.
CONDITION 4: NO REIN-
FORCING REPAIR FOUND.
4.
APPROVAL This Requirements Bulletin was examined by the Federal Aviation Administration (FAA). This Requirements Bulletin contains no information that changes the approved configuration of the airplane. The actions specified in this Requirements Bulletin 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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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).
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 08, 2025 757-53A0129 RB 9 of 42 REQUIREMENTS BULLETIN 757-53A0129
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— 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 General Visual Inspection (GVI) is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance, unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked.
Basic cleaning may be required to ensure appropriate visibility.
11. 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.
12. The instructions in Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools.
13. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. Refer to SOPM 20-50-01 for ADJUSTMENT OF GRIP LENGTH and USE OF WASHERS as an accepted procedure.
14. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200.
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 08, 2025 757-53A0129 RB 10 of 42 REQUIREMENTS BULLETIN 757-53A0129
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B. WORK INSTRUCTIONS Actions Required for Compliance
1. Requirements Group 1-2:
Table 1: Section 43 - Fuselage Frame Lower Lobe Areas - Inspection Refer to the listed procedures in SB 757-53A0129 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition Do PART 1: SECTION 43 OPEN ACCESS.
-Do a General Visual Inspection (GVI) of the fuselage frame lower lobe areas for any existing reinforcing repair.
All Airplanes.
-FIGURE 1 and FIGURE 3 --Contact The Boeing Company for further instructions and do as instructed by The Boeing Company.
CONDITION 1: ANY REIN-
FORCING REPAIR FOUND. Do PART 2: SECTION 43CLOSE ACCESS.- Do PART 2: SECTION 43 CLOSE ACCESS.
-No further action is required.
CONDITION 2: NO REIN-
FORCING REPAIR FOUND.
Group 3:
Table 2: Section 43 - Fuselage Frame Lower Lobe Areas - Inspection Refer to the listed procedures in SB 757-53A0129 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition Do PART 1: SECTION 43 OPEN ACCESS.
-Do a General Visual Inspection (GVI) of the fuselage frame lower lobe areas for any existing reinforcing repair.
All Airplanes.
-FIGURE 2 and FIGURE 4 --Contact The Boeing Company for further instructions and do as instructed by The Boeing Company.
CONDITION 1: ANY REIN-
FORCING REPAIR FOUND. Do PART 2: SECTION 43CLOSE ACCESS.- Do PART 2: SECTION 43 CLOSE ACCESS.
-No further action is required.
CONDITION 2: NO REIN-
FORCING REPAIR FOUND.
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 08, 2025 757-53A0129 RB 11 of 42 REQUIREMENTS BULLETIN 757-53A0129
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Group 1, 3:
Table 3: Section 46 - Fuselage Frame Lower Lobe Areas - Inspection Refer to the listed procedures in SB 757-53A0129 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition Do PART 3: SECTION 46 OPEN ACCESS.
-Do a General Visual Inspection (GVI) of the fuselage frame lower lobe areas for any existing reinforcing repair.
All Airplanes.
-FIGURE 5 and FIGURE 6 --Contact The Boeing Company for further instructions and do as instructed by The Boeing Company.
CONDITION 3: ANY REIN-
FORCING REPAIR FOUND. Do PART 4: SECTION 46CLOSE ACCESS.- Do PART 4: SECTION 46 CLOSE ACCESS.
-No further action is required.
CONDITION 4: NO REIN-
FORCING REPAIR FOUND.
Group 2:
Table 4: Section 46 - Fuselage Frame Lower Lobe Areas - Inspection Refer to the listed procedures in SB 757-53A0129 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition Do PART 3: SECTION 46 OPEN ACCESS.
-Do a General Visual Inspection (GVI) of the fuselage frame lower lobe areas for any existing reinforcing repair.
All Airplanes.
-FIGURE 5 and FIGURE 7 --Contact The Boeing Company for further instructions and do as instructed by The Boeing Company.
CONDITION 3: ANY REIN-
FORCING REPAIR FOUND. Do PART 4: SECTION 46CLOSE ACCESS.- Do PART 4: SECTION 46 CLOSE ACCESS.
-No further action is required.
CONDITION 4: NO REIN-
FORCING REPAIR FOUND.
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 08, 2025 757-53A0129 RB 12 of 42 REQUIREMENTS BULLETIN 757-53A0129