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Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2913 RB Original Issue: December 19, 2025 ATA System: 5300 5305 5312 SUBJECT: FUSELAGE - Fuselage Skin Between STA 1350 and STA 1480 at S-23L and S-23R
- Lap 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: December 19, 2025 747-53A2913 RB 1 of 22
3.0
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 19, 2025 747-53A2913 RB 2 of 22 REQUIREMENTS BULLETIN 747-53A2913
ALERTALERT
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Table of Contents
1. EFFECTIVITY5
A. Airplanes5
B. Spares Affected5
2. CONCURRENT REQUIREMENTS6
3. COMPLIANCE6
4. APPROVAL8
5. ACCOMPLISHMENT INSTRUCTIONS9
A. General Information9
B. Work Instructions10
FIGURE 1: LEFT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23L - LAP SPLICE
INSPECTION13
FIGURE 2: RIGHT SIDE - FUSELAGE SKIN BETWEEN STA 1350 AND STA 1480 AT S-23R - LAP SPLICE
INSPECTION18
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 19, 2025 747-53A2913 RB 3 of 22 REQUIREMENTS BULLETIN 747-53A2913
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Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 19, 2025 747-53A2913 RB 4 of 22 REQUIREMENTS BULLETIN 747-53A2913
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Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2913 RB Original Issue: December 19, 2025 ATA System: 5300 5305 5312 SUBJECT: FUSELAGE - Fuselage Skin Between STA 1350 and STA 1480 at S-23L and S-23R
- Lap 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 747-8 Airplane(s), line number(s) 1434-1435, 1439-1440, 1443, 1446, 1449, 1451, 1453, 1456, 1459, 1466, 1468, 1470, 1472, 1475, 1477, 1480, 1492, 1494-1495, 1497-1500, 1503, 1506-1515, 1517-1518, 1524-1525, 1527, 1529, 1531, 1537-1539 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 747-8 Passenger Airplanes-1 Airplane Models:
747-8 GroupVariable Number 1RC001 - RC009 1RC021 - RC040 GroupVariable Number 1RC051 - RC060 1RC066 - RC072 GroupVariable Number -- -- B. Spares Affected Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 19, 2025 747-53A2913 RB 5 of 22
None.
2. CONCURRENT REQUIREMENTS None.
3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Requirements Bulletin 747-53A2913 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 747-53A2913 RB mandatory.
Accomplish the required action(s), based on the applicable condition(s) in Tables 1 and 2, in accordance with Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION or an OPTION, do all of the ACTION numbers for that CONDITION or OPTION.
Table 1: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspections Between STA 1350 and STA 1480 at S-23L for any crack.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time ActionCondition -Before 20,000 total flight cycles.Do an external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack.
All Airplanes.
3,600 flight cycles.-Repeat the external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack.
(a) CONDITION 1: NO
CRACK FOUND -Before further flight.CONDITION 2 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 2: ANY
CRACK FOUND 3,600 flight cycles.-CONDITION 2 (ACTION 2):
Repeat the external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack.
(a) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 19, 2025 747-53A2913 RB 6 of 22 REQUIREMENTS BULLETIN 747-53A2913
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Table 1: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspections Between STA 1350 and STA 1480 at S-23L for any crack.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time ActionCondition
(a) It is not required to do the external surface HFEC inspection in accordance with Requirements Bulletin 747-53A2913 RB in the area covered by a repair if the repair meets all of the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 747- 53A2913 RB and installed after the Original Issue date of Requirements Bulletin 747-53A2913 RB.
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA) via a FAA Form 8100-9.
Table 2: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspections Between STA 1350 and STA 1480 at S-23R for any crack.
Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time ActionCondition -Before 20,000 total flight cycles.Do an external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack.
All Airplanes.
3,600 flight cycles.-Repeat the external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack.
(a) CONDITION 3: NO
CRACK FOUND -Before further flight.CONDITION 4 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 4: ANY
CRACK FOUND 3,600 flight cycles.-CONDITION 4 (ACTION 2):
Repeat the external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack.
(a)
(a) It is not required to do the external surface HFEC inspection in accordance with Requirements Bulletin 747-53A2913 RB in the area covered by a repair if the repair meets all of the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 747- 53A2913 RB and installed after the Original Issue date of Requirements Bulletin 747-53A2913 RB.
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA) via a FAA Form 8100-9.
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 19, 2025 747-53A2913 RB 7 of 22 REQUIREMENTS BULLETIN 747-53A2913
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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.
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 19, 2025 747-53A2913 RB 8 of 22 REQUIREMENTS BULLETIN 747-53A2913
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5. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION
KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED
MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE.
CAUTION NOTE: 1. This is an Enhanced Required for Compliance document. There will be a separate Service Bulletin (SB) and a separate Requirements Bulletin (RB). If an RB is mandated by an Airworthiness Directive (AD), then all applicable requirements specified in the RB must be done. 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. 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 747 Structural Repair Manual, Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747 Aircraft Maintenance Manual (AMM).
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 19, 2025 747-53A2913 RB 9 of 22 REQUIREMENTS BULLETIN 747-53A2913
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— Non-standard torque values for maintenance tasks are included in the applicable installation step.
5. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used.
6. 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.
7. 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.
8. Boeing Service Letter 747-SL-51-048, 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.
12. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200.
B. WORK INSTRUCTIONS Actions Required for Compliance
1. Requirements Table 1: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspections Between STA 1350 and STA 1480 at S-23L for any crack.
Refer to the listed procedures in SB 747-53A2913 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition Do PART 1: OPEN AC- CESS - LEFT SIDE.
-Do an external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack.
All Airplanes.
-FIGURE 1 Do PART 2: CLOSE AC- CESS - LEFT SIDE.
-Repeat the external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack. (a) CONDITION 1: NO
CRACK FOUND -FIGURE 1 Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 19, 2025 747-53A2913 RB 10 of 22 REQUIREMENTS BULLETIN 747-53A2913
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Table 1: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspections Between STA 1350 and STA 1480 at S-23L for any crack.
Refer to the listed procedures in SB 747-53A2913 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition --CONDITION 2 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 2: ANY CRACK FOUND Do PART 2: CLOSE AC- CESS - LEFT SIDE.
- Do PART 1: OPEN AC- CESS - LEFT SIDE.
-CONDITION 2 (ACTION 2):
Repeat the external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack. (a) -FIGURE 1
(a) It is not required to do the external surface HFEC inspection in accordance with Requirements Bulletin 747-53A2913 RB in the area covered by a repair if the repair meets all of the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 747- 53A2913 RB and installed after the Original Issue date of Requirements Bulletin 747-53A2913 RB.
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA) via a FAA Form 8100-9.
Table 2: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspections Between STA 1350 and STA 1480 at S-23R for any crack.
Refer to the listed procedures in SB 747-53A2913 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition Do PART 3: OPEN AC- CESS - RIGHT SIDE.
-Do an external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack.
All Airplanes.
-FIGURE 2 Do PART 4: CLOSE AC- CESS - RIGHT SIDE.
-Repeat the external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack. (a) CONDITION 3: NO
CRACK FOUND -FIGURE 2 Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 19, 2025 747-53A2913 RB 11 of 22 REQUIREMENTS BULLETIN 747-53A2913
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Table 2: Fuselage Skin - Lap Splice Upper Fastener Row - High Frequency Eddy Current (HFEC) Inspections Between STA 1350 and STA 1480 at S-23R for any crack.
Refer to the listed procedures in SB 747-53A2913 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition --CONDITION 4 (ACTION 1):
Contact The Boeing Company for repair instructions and do the repair.
CONDITION 4: ANY CRACK FOUND Do PART 4: CLOSE AC- CESS - RIGHT SIDE.
- Do PART 3: OPEN AC- CESS - RIGHT SIDE.
-CONDITION 4 (ACTION 2):
Repeat the external surface HFEC inspection of the upper fastener row of the fuselage skin lap splice for any crack. (a) -FIGURE 2
(a) It is not required to do the external surface HFEC inspection in accordance with Requirements Bulletin 747-53A2913 RB in the area covered by a repair if the repair meets all of the conditions that follow:
1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 747- 53A2913 RB and installed after the Original Issue date of Requirements Bulletin 747-53A2913 RB.
2. The installed repair was approved by the Boeing Organization Designation Authorization (ODA) via a FAA Form 8100-9.
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: December 19, 2025 747-53A2913 RB 12 of 22 REQUIREMENTS BULLETIN 747-53A2913