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Commercial A BOEING Airplanes 747 Requirements Bulletin : ALERT Number: 747-53A2907 RB Original Issue: March 03, 2022 Revision 1: March 14, 2025 ATA System: 5312 SUBJECT: FUSELAGE STRUCTURE - Center Section - Stringers at Stringer Splice at STA 1000, STA 1140, STA 1660, STA 1740, STA 1960, and STA 2180 - 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.
ECCN: 9E991 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: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB 1 of 260
2.0
REQUIREMENTS BULLETIN 747-53A2907
ALERT ALERT
BLANK PAGE Revision 1 Mach 03, 2022 , 2020 747-53A2907 RB port Controlled ECCN: 9E9 e page 1 for deta 2 of 260
REQUIREMENTS BULLETIN 747-53A2907
ALERT ALERT Table of Contents Revision Transmittal Sheet 5 EFFECTIVITY 7 A. Airplanes 7 B. Spares Affected
2. CONCURRENT REQUIREMENTS.
COMPLIANCE 8
4. APPROVAL 23
5. ACCOMPLISHMENT INSTRUCTIONS. 25 A. General Information 25 B. Work Instructions 26 FIGURE 1: LEFT SIDE - S-8L TO S-16L AT STA 1740, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - GENERAL VISUAL INSPECTION [Group 1] . 42 FIGURE 3: LEFT SIDE - S-8L TO S-16L AT STA 1740, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 1 OPTION 1 [Group 1] 55 FIGURE 4: LEFT SIDE - S-8L TO S-16L AT STA 1740, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 1 OPTION 2 [Group 1] FIGURE 5: LEFT SIDE - S-8L TO S-16L AT STA 1740, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - RADIUS FILLER INSTALLATION [Group 1 71 FIGURE 6: LEFT SIDE - S-8L TO S-16L AT STA 1740, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 2 [Group 1] FIGURE 7: RIGHT SIDE - S-8R TO S-16R AT STA 1740, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - GENERAL VISUAL INSPECTION [Group 1] FIGURE 9: RIGHT SIDE - S-8R TO S-16R AT STA 1740, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 3 OPTION 3 [Group FIGURE 10: RIGHT SIDE - S-8R TO S-16R AT STA 1740, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 3 OPTION 4 [Group FIGURE 11: RIGHT SIDE - S-8R TO S-16R AT STA 1740, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - RADIUS FILLER INSTALLATION [Group 1] FIGURE 12: RIGHT SIDE - S-8R TO S-16R AT STA 1740, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 4 [Group 1] . 136 FIGURE 13: LEFT SIDE - S-7L TO S-12L AT STA 1000, S-13L TO S-16L AT STA 1140, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - GENERAL VISUAL INSPECTION [Group 2-3] FIGURE 15: LEFT SIDE - S-7L TO S-12L AT STA 1000, S-13L TO S-16L AT STA 1140, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 5 OPTION 5 [Group 2-3] .
FIGURE 16: LEFT SIDE - S-7L TO S-12L AT STA 1000, S-13L TO S-16L AT STA 1140, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 5 OPTION 6 [Group 2-3] FIGURE 17: LEFT SIDE - S-7L TO S-12L AT STA 1000, S-13L TO S-16L AT STA 1140, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - RADIUS FILLER INSTALLATION [Group 2-3] Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 3 of 260
REQUIREMENTS BULLETIN 747-53A2907
ALERT ALERT FIGURE 18: LEFT SIDE - S-7L TO S-12L AT STA 1000, S-13L TO S-16L AT STA 1140, S-1L TO S-12L AT STA 1960 AND S-1L TO S-12L AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 6 [Group 2-3] . . . . .
FIGURE 19: RIGHT SIDE - S-7R TO S-12R AT STA 1000, S-13R TO S-16R AT STA 1140, S-7R TO S-11R AT STA 1660, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - GENERAL VISUAL INSPECTION [Group 2-3] . 200 FIGURE 21: RIGHT SIDE - S-7R TO S-12R AT STA 1000, S-13R TO S-16R AT STA 1140, S-7R TO S-11R AT STA 1660, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 7 OPTION 7 [Group 2-3] .
FIGURE 22: RIGHT SIDE - S-7R TO S-12R AT STA 1000, S-13R TO S-16R AT STA 1140, S-7R TO S-11R AT STA 1660, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER DETAILED INSPECTION - CONDITION 7 OPTION 8 [Group 2-3] .
FIGURE 23: RIGHT SIDE - S-7R TO S-12R AT STA 1000, S-13R TO S-16R AT STA 1140, S-7R TO S-11R AT STA 1660, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - RADIUS FILLER INSTALLATION [Group 2-3] .
FIGURE 24: RIGHT SIDE - S-7R TO S-12R AT STA 1000, S-13R TO S-16R AT STA 1140, S-7R TO S-11R AT STA 1660, S-1R TO S-12R AT STA 1960 AND S-1R TO S-12R AT STA 2180 - STRINGER
DETAILED INSPECTION - CONDITION 8 [Group 2-3]251
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Commercial A BOEING Airplanes 747 Requirements Bulletin
• ALERT Number: 747-53A2907 RB Revision Transmittal Sheet Original Issue: March 03, 2022 Revision 1: March 14, 2025 ATA System: 5312 SUBJECT: FUSELAGE STRUCTURE - Center Section - Stringers at Stringer Splice at STA 1000, STA 1140, STA 1660, STA 1740, STA 1960, and STA 2180 - Inspection This revision includes all pages of the requirements bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2023-12-18 is related to Requirements Bulletin 747-53A2907 RB.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to Requirements Bulletin 747-53A2907 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 747-53A2907 RB mandatory.
Effects of this Revision on airplanes on which the Original Issue was previously done:
None.
Airplanes RC690-RC696, RC701-RC704 were added to the new Group 3 of this bulletin effectivity.
REASON FOR REVISION This revision is sent to add new airplanes to the new Group 3 of this bulletin effectivity and add compliance instructions for the new Group 3. This revision is also sent to change existing compliance requirements and add FAA Airworthiness Directive AD 2023-12-18 information for Group 1 and Group 2 airplanes.
These sections were changed:
- In Effectivity, added new Group 3 airplanes.
- In Compliance, changed existing compliance tables, changed AD statement, added new compliance tables, and added new AD information
- In Work Instructions, Requirements, changed existing work instructions and added new work instructions.
- In FIGURES 13, 16, 17, 18, 19, 22, 23, and 24, changed group applicability.
- In FIGURES 15 and 21, changed illustrations and group applicability.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes.
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REQUIREMENTS BULLETIN 747-53A2907
ALERT ALERT Pages with no vertical lines have no changes.
REVISION HISTORY Requirement Bulletin Requirement Bulletin Service Bulletin Service Bulletin 747-53A2907 RB 747-53A2907 RB 747-53A2907 747-53A2907 Issue Date Issue Date Original Issue: March 03, 2022 Original Issue: March 03, 2022 Revision 1: March 14, 2025 Revision 1: March 14, 2025 Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 6 of 260
Commercial A BOEING Airplanes 747 Requirements Bulletin : ALERT Number: 747-53A2907 RB Original Issue: March 03, 2022 Revision 1: March 14, 2025 ATA System: 5312 SUBJECT: FUSELAGE STRUCTURE - Center Section - Stringers at Stringer Splice at STA 1000, STA 1140, STA 1660, STA 1740, STA 1960, and STA 2180 - Inspection
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., 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, 747-8F Airplane(s), line number(s) 1420-1574 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.
GROUP CONFIGURATION DESCRIPTION 747-8 Airplanes.
2 747-8F Airplanes.
747-8F Airplanes with manufacturing improvements.
Airplane Models:
747-8, 747-8F Variable Number Group Variable Number Group Variable Number Group RC001 - RC009 1 RC066 - RC072 1 RC521 - RC528 2 RC021 - RC040 1 RC076 - RC077 1 RC531 - RC541 2 RC051 - RC060 1 RC501 - RC514 2 RC546 - RC566 2 Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 7 of 260
REQUIREMENTS BULLETIN 747-53A2907
ALERT ALERT Variable Number Group Variable Number Group Variable Number Group RC571 - RC582 2 RC651 - RC652 RC681 - RC689 2 RC601 - RC610 2 RC661 RC690 - RC696 3 RC641 - RC644 2 RC671 - RC674 RC701 - RC704 3 B. Spares Affected None.
2. CONCURRENT REQUIREMENTS None.
3. COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2023-12-18 is related to Requirements Bulletin 747-53A2907 RB. The effective date of AD 2023-12-18 is August 11, 2023.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to Requirements Bulletin 747-53A2907 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 747-53A2907 RB mandatory.
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:
Accomplish the required action(s), based on the applicable condition(s) in Table 1 and Table 2 in accordance with Accomplishment Instructions.
Group 2:
Accomplish the required action(s), based on the applicable condition(s) in Table 3 and Table 4 in accordance with Accomplishment Instructions.
Group 3:
Accomplish the required action(s), based on the applicable condition(s) in Table 5 and Table 6 in accordance with Accomplishment Instructions.
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REQUIREMENTS BULLETIN 747-53A2907
ALERT ALERT Group 1:
Table 1: Stringer Splice Inspection of Stringers S-8L to S-16L at STA 1740, S-1L to S-12L at STA 1960 and S-1L to S-12L at STA 2180.
Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) All Airplanes. Do a General Visual Inspection Before 12,000 Within 38 (GVI) of each free flange of the total flights cy- months after the stringers at the stringer splice cles or 8 years Original Issue for radius fillers at the fastener after the date of date of Requirelocations. issuance of the ments Bulletin original stan- 747-53A2907 dard certificate RB.
of airworthiness or the original export certificate of airworthiness, whichever occurs first.
CONDITION 1: OPTION 1 (ACTION 1): Re- Before further flight.
FOUND TWO OR move radius fillers at each free MORE RADIUS flange of the stringer with two FILLERS AT ANY or more fastener locations.
FREE FLANGE OF OPTION 1 (ACTION 2): Do a Before further flight.
THE STRINGER.
detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
OPTION 2: Do a detailed in- Before further flight.
spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
CONDITION 1.1: ANY CONDITION 1.1 (ACTION 1): Before further flight.
CRACK FOUND AS Contact the Boeing Company A RESULT OF OP- for repair instructions and do TION 1 INSPECTION. the repair.
CONDITION 1.1 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed inof the stringers at the stringer spection, whichever occurs first.
splice for radius fillers at the fastener locations.
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REQUIREMENTS BULLETIN 747-53A2907
ALERT ALERT Group 1:
Table 1: Stringer Splice Inspection of Stringers S-8L to S-16L at STA 1740, S-1L to S-12L at STA 1960 and S-1L to S-12L at STA 2180.
Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) CONDITION 1.2: NO CONDITION 1.2 (ACTION 1): Before further flight.
CRACK FOUND AS Install radius fillers.
A RESULT OF OP- TION 1 INSPECTION. CONDITION 1.2 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed inof the stringers at the stringer spection, whichever occurs first.
splice for radius fillers at the fastener locations.
CONDITION 1.3: ANY CONDITION 1.3 (ACTION 1): Before further flight.
CRACK FOUND AS Contact the Boeing Company A RESULT OF OP- for repair instructions and do TION 2 INSPECTION. the repair.
CONDITION 1.3 (ACTION 2): Within 4,600 flight cycles or within - Do a GVI of each free flange 8 years after the last detailed inof the stringers at the stringer spection, whichever occurs first.
splice for radius fillers at the fastener locations.
CONDITION 1.4: NO Do a GVI of each free flange Within 4,600 flight cycles or within CRACK FOUND AS of the stringers at the stringer 8 years after the last detailed in- A RESULT OF OP- splice for radius fillers at the spection, whichever occurs first.
TION 2 INSPECTION. fastener locations.
CONDITION 2: Do a detailed inspection of the Before further flight.
FOUND NO MORE stringers and the stringer THAN ONE RADIUS splice fitting within the profile FILLER AT ANY of the stringer splice installa- FREE FLANGE OF tion for any crack.
THE STRINGER.
CONDITION 2.1: ANY CONDITION 2.1 (ACTION 1): Before further flight.
CRACK FOUND. Contact the Boeing Company for repair instructions and do the repair.
CONDITION 2.1 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed inof the stringers at the stringer spection, whichever occurs first.
splice for radius fillers at the fastener locations.
CONDITION 2.2: NO Do a GVI of each free flange Within 9,600 flight cycles or within CRACK FOUND. of the stringers at the stringer 8 years after the last detailed insplice for radius fillers at the spection, whichever occurs first.
fastener locations.
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REQUIREMENTS BULLETIN 747-53A2907
ALERT ALERT Group 1:
Table 2: Stringer Splice Inspection of Stringers S-8R to S-16R at STA 1740, S-1R to S-12R at STA 1960 and S-1R to S-12R at STA 2180.
Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) All Airplanes. Do a General Visual Inspection Before 12,000 Within 38 (GVI) of each free flange of the total flights cy- months after the stringers at the stringer splice cles or 8 years Original Issue for radius fillers at the fastener after the date of date of Requirelocations. issuance of the ments Bulletin original stan- 747-53A2907 dard certificate RB.
of airworthiness or the original export certificate of airworthiness, whichever occurs first.
CONDITION 3: OPTION 3 (ACTION 1): Re- Before further flight.
FOUND TWO OR move radius fillers at each free MORE RADIUS flange of the stringer with two FILLERS AT ANY or more fastener locations.
FREE FLANGE OF OPTION 3 (ACTION 2): Do a Before further flight.
THE STRINGER.
detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
OPTION 4: Do a detailed in- Before further flight.
spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack.
CONDITION 3.1: ANY CONDITION 3.1 (ACTION 1): Before further flight.
CRACK FOUND AS Contact the Boeing Company A RESULT OF OP- for repair instructions and do TION 3 INSPECTION. the repair.
CONDITION 3.1 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed inof the stringers at the stringer spection, whichever occurs first.
splice for radius fillers at the fastener locations.
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REQUIREMENTS BULLETIN 747-53A2907
ALERT ALERT Group 1:
Table 2: Stringer Splice Inspection of Stringers S-8R to S-16R at STA 1740, S-1R to S-12R at STA 1960 and S-1R to S-12R at STA 2180.
Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) CONDITION 3.2: NO CONDITION 3.2 (ACTION 1): Before further flight.
CRACK FOUND AS Install radius fillers.
A RESULT OF OP- TION 3 INSPECTION. CONDITION 3.2 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed inof the stringers at the stringer spection, whichever occurs first.
splice for radius fillers at the fastener locations.
CONDITION 3.3: ANY CONDITION 3.3 (ACTION 1): Before further flight.
CRACK FOUND AS Contact the Boeing Company A RESULT OF OP- for repair instructions and do TION 4 INSPECTION. the repair.
CONDITION 3.3 (ACTION 2): Within 4,600 flight cycles or within - Do a GVI of each free flange 8 years after the last detailed inof the stringers at the stringer spection, whichever occurs first.
splice for radius fillers at the fastener locations.
CONDITION 3.4: NO Do a GVI of each free flange Within 4,600 flight cycles or within CRACK FOUND AS of the stringers at the stringer 8 years after the last detailed in- A RESULT OF OP- splice for radius fillers at the spection, whichever occurs first.
TION 4 INSPECTION. fastener locations.
CONDITION 4: Do a detailed inspection of the Before further flight.
FOUND NO MORE stringers and the stringer THAN ONE RADIUS splice fitting within the profile FILLER AT ANY of the stringer splice installa- FREE FLANGE OF tion for any crack.
THE STRINGER.
CONDITION 4.1: ANY CONDITION 4.1 (ACTION 1): Before further flight.
CRACK FOUND. Contact the Boeing Company for repair instructions and do the repair.
CONDITION 4.1 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed inof the stringers at the stringer spection, whichever occurs first.
splice for radius fillers at the fastener locations.
CONDITION 4.2: NO Do a GVI of each free flange Within 9,600 flight cycles or within CRACK FOUND. of the stringers at the stringer 8 years after the last detailed insplice for radius fillers at the spection, whichever occurs first.
fastener locations.
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