# Boeing Alert Service Bulletin 747-53A2907: Revision 1, part 1 of 5 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2025-4000, the docket of AD 2026-13-03. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 747-53A2907](https://openairdocs.org/service-documents/boeing/747-53a2907.md) - Title as filed: B747-53A2907 RB_Rev1_Part1--BOEING - Pages: 62 - PDF: https://openairdocs.org/files/sha256/41/26/41265b269b501c2ce3c40d0b0ae1ecbc1d43272e6649376b4827c54ffb6ae52e - Page: https://openairdocs.org/service-documents/boeing/747-53a2907/file/41265b269b50 ## Text This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OCR) 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 ### Page 2 (OCR) 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 ### Page 3 (OCR) 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 ### Page 4 (OCR) 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 Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 4 of 260 ### Page 5 (OCR) 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. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 5 of 260 ### Page 6 (OCR) 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 ### Page 7 (OCR) 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 ### Page 8 (OCR) 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. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 8 of 260 ### Page 9 (OCR) 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 Require- locations. issuance of the ments Bulletin original stan- 747-53A2907 dard certificate RB. of airworthiness or the original export certificate of airworthiness, whichever oc- curs 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 installa- tion 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 in- of the stringers at the stringer spection, whichever occurs first. splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 9 of 260 ### Page 10 (OCR) 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 in- of 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 in- of 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 in- of 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 in- splice for radius fillers at the spection, whichever occurs first. fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 10 of 260 ### Page 11 (OCR) 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 Require- locations. issuance of the ments Bulletin original stan- 747-53A2907 dard certificate RB. of airworthiness or the original export certificate of airworthiness, whichever oc- curs 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 installa- tion 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 in- of the stringers at the stringer spection, whichever occurs first. splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 11 of 260 ### Page 12 (OCR) 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 in- of 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 in- of 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 in- of 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 in- splice for radius fillers at the spection, whichever occurs first. fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 12 of 260 ### Page 13 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 2: Table 3: Stringer Splice Inspection of Stringers 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. 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 Require- locations. issuance of the ments Bulletin original stan- 747-53A2907 dard certificate RB. of airworthiness or the original export certificate of airworthiness, whichever oc- curs first. CONDITION 5: OPTION 5 (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 5 (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 installa- tion for any crack. OPTION 6: 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 5.1: ANY CONDITION 5.1 (ACTION 1): Before further flight. CRACK FOUND AS Contact the Boeing Company A RESULT OF OP- for repair instructions and do TION 5 INSPECTION. the repair. CONDITION 5.1 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed in- of the stringers at the stringer spection, whichever occurs first. splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 13 of 260 ### Page 14 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 2: Table 3: Stringer Splice Inspection of Stringers 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. Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) CONDITION 5.2: NO CONDITION 5.2 (ACTION 1): Before further flight. CRACK FOUND AS Install radius fillers. A RESULT OF OP- TION 5 INSPECTION. CONDITION 5.2 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed in- of the stringers at the stringer spection, whichever occurs first. splice for radius fillers at the fastener locations. CONDITION 5.3: ANY CONDITION 5.3 (ACTION 1): Before further flight. CRACK FOUND AS Contact the Boeing Company A RESULT OF OP- for repair instructions and do TION 6 INSPECTION. the repair. CONDITION 5.3 (ACTION 2): Within 4,600 flight cycles or within - Do a GVI of each free flange 8 years after the last detailed in- of the stringers at the stringer spection, whichever occurs first. splice for radius fillers at the fastener locations. CONDITION 5.4: 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 6 INSPECTION. fastener locations. CONDITION 6: 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 6.1: ANY CONDITION 6.1 (ACTION 1): Before further flight. CRACK FOUND. Contact the Boeing Company for repair instructions and do the repair. CONDITION 6.1 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed in- of the stringers at the stringer spection, whichever occurs first. splice for radius fillers at the fastener locations. CONDITION 6.2: 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 in- splice for radius fillers at the spection, whichever occurs first. fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 14 of 260 ### Page 15 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 2: Table 4: Stringer Splice Inspection of Stringers 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. 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 Require- locations. issuance of the ments Bulletin original stan- 747-53A2907 dard certificate RB. of airworthiness or the original export certificate of airworthiness, whichever oc- curs first. CONDITION 7: OPTION 7 (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 7 (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 installa- tion for any crack. OPTION 8: 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 7.1: ANY CONDITION 7.1 (ACTION 1): Before further flight. CRACK FOUND AS Contact the Boeing Company A RESULT OF OP- for repair instructions and do TION 7 INSPECTION. the repair. CONDITION 7.1 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed in- of the stringers at the stringer spection, whichever occurs first. splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 15 of 260 ### Page 16 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 2: Table 4: Stringer Splice Inspection of Stringers 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. Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) CONDITION 7.2: NO CONDITION 7.2 (ACTION 1): Before further flight. CRACK FOUND AS Install radius fillers. A RESULT OF OP- TION 7 INSPECTION. CONDITION 7.2 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed in- of the stringers at the stringer spection, whichever occurs first. splice for radius fillers at the fastener locations. CONDITION 7.3: ANY CONDITION 7.3 (ACTION 1): Before further flight. CRACK FOUND AS Contact the Boeing Company A RESULT OF OP- for repair instructions and do TION 8 INSPECTION. the repair. CONDITION 7.3 (ACTION 2): Within 4,600 flight cycles or within - Do a GVI of each free flange 8 years after the last detailed in- of the stringers at the stringer spection, whichever occurs first. splice for radius fillers at the fastener locations. CONDITION 7.4: 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 8 INSPECTION. fastener locations. CONDITION 8: 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 8.1: ANY CONDITION 8.1 (ACTION 1): Before further flight. CRACK FOUND. Contact the Boeing Company for repair instructions and do the repair. CONDITION 8.1 (ACTION 2): Within 9,600 flight cycles or within Do a GVI of each free flange 8 years after the last detailed in- of the stringers at the stringer spection, whichever occurs first. splice for radius fillers at the fastener locations. CONDITION 8.2: 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 in- splice for radius fillers at the spection, whichever occurs first. fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 16 of 260 ### Page 17 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 5: Stringer Splice Inspection of Stringers 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. Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) All Airplanes. Do a General Visual In- Before 12,000 Within 38 spection (GVI) of each total flights cy- months after the free flange of the cles or 8 years Revision 1 date stringers at the stringer after the date of of Requirements splice for radius fillers at issuance of the Bulletin 747- the fastener locations. original stan- 53A2907 RB. dard certificate of airworthiness or the original export certificate of airworthiness, whichever oc- curs first. CONDITION 9: FOUND OPTION 9 (ACTION 1): Before further flight. TWO OR MORE RADIUS Remove radius fillers at FILLERS AT ANY FREE each free flange of the FLANGE OF THE stringer with two or more STRINGER. fastener locations. OPTION 9 (ACTION 2): Before further flight. Do a detailed inspection of the stringers and the stringer splice fitting with- in the profile of the stringer splice installation for any crack. OPTION 10: Do a de- Before further flight. tailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 17 of 260 ### Page 18 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 5: Stringer Splice Inspection of Stringers 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. Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) CONDITION 9.1: ANY CONDITION 9.1 (AC- Before further flight. CRACK FOUND AS A RE- TION 1): Contact the SULT OF OPTION 9 IN- Boeing Company for re- SPECTION. pair instructions and do the repair. CONDITION 9.1 (AC- Within 9,600 flight cycles or within TION 2): Do a GVI of 8 years after the last detailed in- each free flange of the spection, whichever occurs first. stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 9.2: NO CONDITION 9.2 (AC- Before further flight. CRACK FOUND AS A RE- TION 1): Install radius SULT OF OPTION 9 IN- fillers. SPECTION. CONDITION 9.2 (AC- Within 9,600 flight cycles or within TION 2): Do a GVI of 8 years after the last detailed in- each free flange of the spection, whichever occurs first. stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 9.3: ANY CONDITION 9.3 (AC- Before further flight. CRACK FOUND AS A RE- TION 1): Contact the SULT OF OPTION 10 IN- Boeing Company for re- SPECTION. pair instructions and do the repair. CONDITION 9.3 (AC- Within 4,600 flight cycles or within TION 2): Do a GVI of 8 years after the last detailed in- each free flange of the spection, whichever occurs first. stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 9.4: NO Do a GVI of each free Within 4,600 flight cycles or within - CRACK FOUND AS A RE- flange of the stringers at 8 years after the last detailed in- SULT OF OPTION 10 IN- the stringer splice for ra- spection, whichever occurs first. SPECTION. dius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 18 of 260 ### Page 19 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 5: Stringer Splice Inspection of Stringers 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. Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) CONDITION 10: FOUND Do a detailed inspection Before further flight. NO MORE THAN ONE of the stringers and the RADIUS FILLER AT ANY stringer splice fitting with- FREE FLANGE OF THE in the profile of the STRINGER. stringer splice installation for any crack. CONDITION 10.1: ANY CONDITION 10.1 (AC- Before further flight. CRACK FOUND. TION 1): Contact the Boeing Company for re- pair instructions and do the repair. CONDITION 10.1 (AC- Within 9,600 flight cycles or within - TION 2): Do a GVI of 8 years after the last detailed in- each free flange of the spection, whichever occurs first. stringers at the stringer splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 19 of 260 ### Page 20 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 5: Stringer Splice Inspection of Stringers 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. Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) CONDITION 10.2: NO Do a GVI of each free Within 9,600 flight cycles or within CRACK FOUND. flange of the stringers at 8 years after the last detailed in- the stringer splice for ra- spection, whichever occurs first. dius fillers at the fastener locations. Group 3: Table 6: Stringer Splice Inspection of Stringers 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. Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) All Airplanes. Do a General Visual In- Before 12,000 Within 38 spection (GVI) of each total flights cy- months after the free flange of the cles or 8 years Revision 1 date stringers at the stringer after the date of of Requirements splice for radius fillers at issuance of the Bulletin 747- the fastener locations. original stan- 53A2907 RB. dard certificate of airworthiness or the original export certificate of airworthiness, whichever oc- curs first. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 20 of 260 ### Page 21 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 6: Stringer Splice Inspection of Stringers 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. Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) CONDITION 11: FOUND OPTION 11 (ACTION 1): Before further flight. TWO OR MORE RADIUS Remove radius fillers at FILLERS AT ANY FREE each free flange of the FLANGE OF THE stringer with two or more STRINGER. fastener locations. OPTION 11 (ACTION 2): Before further flight. Do a detailed inspection of the stringers and the stringer splice fitting with- in the profile of the stringer splice installation tor any crack. OPTION 12: Do a de- Before further flight. tailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. CONDITION 11.1: ANY CONDITION 11.1 (AC- Before further flight. CRACK FOUND AS A RE- TION 1): Contact the SULT OF OPTION 11 IN- Boeing Company for re- SPECTION. pair instructions and do the repair. CONDITION 11.1 (AC- Within 9,600 flight cycles or within TION 2): Do a GVI of 8 years after the last detailed in- each free flange of the spection, whichever occurs first. stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 11.2: NO CONDITION 11.2 (AC- Before further flight. CRACK FOUND AS A RE- TION 1): Install radius SULT OF OPTION 11 IN- fillers. SPECTION. CONDITION 11.2 (AC- Within 9,600 flight cycles or within TION 2): Do a GVI of 8 years after the last detailed in- each free flange of the spection, whichever occurs first. stringers at the stringer splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 21 of 260 ### Page 22 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 6: Stringer Splice Inspection of Stringers 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. Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) CONDITION 11.3: ANY CONDITION 11.3 (AC- Before further flight. CRACK FOUND AS A RE- TION 1): Contact the SULT OF OPTION 12 IN- Boeing Company for re- SPECTION. pair instructions and do the repair. CONDITION 11.3 (AC- Within 4,600 flight cycles or within TION 2): Do a GVI of 8 years after the last detailed in- each free flange of the spection, whichever occurs first. stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 11.4: NO Do a GVI of each free Within 4,600 flight cycles or within CRACK FOUND AS A RE- flange of the stringers at 8 years after the last detailed in- SULT OF OPTION 12 IN- the stringer splice for ra- spection, whichever occurs first. SPECTION. dius fillers at the fastener locations. CONDITION 12: FOUND Do a detailed inspection Before further flight. NO MORE THAN ONE of the stringers and the RADIUS FILLER AT ANY stringer splice fitting with- FREE FLANGE OF THE in the profile of the STRINGER. stringer splice installation for any crack. CONDITION 12.1: ANY CONDITION 12.1 (AC- Before further flight. CRACK FOUND. TION 1): Contact the Boeing Company for re- pair instructions and do the repair. CONDITION 12.1 (AC- Within 9,600 flight cycles or within - TION 2): Do a GVI of 8 years after the last detailed in- each free flange of the spection, whichever occurs first. stringers at the stringer splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 22 of 260 ### Page 23 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 6: Stringer Splice Inspection of Stringers 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. Condition Action Boeing Recommended Repeat Interval Compliance Time (Whichever (Not to Exceed) Occurs Later) CONDITION 12.2: NO Do a GVI of each free Within 9,600 flight cycles or within CRACK FOUND. flange of the stringers at 8 years after the last detailed in- the stringer splice for ra- spection, whichever occurs first. dius fillers at the fastener locations. 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)/Joint Aviation Authorities (JAA) approved for all EASA/JAA 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 inspection defined in this bulletin revision as an alternative method of compliance to accomplishing the requirements of paragraph (g) of AD 2023-12-18. All provisions of AD 2023-12-18 that are not specifically referenced in the above statement remain fully applicable and must be complied with accordingly. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 23 of 260 ### Page 24 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT BLANK PAGE Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB port Controlled ECCN: 9E9 e page 1 for deta 24 of 260 ### Page 25 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT 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. For the related SB, some locations are marked RC Start and RO 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 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. 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). Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM). Non-standard torque values for maintenance tasks are included in the applicable installation step. Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 25 of 260 ### Page 26 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT 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. 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. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51. 10. A General Visual Inspection 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. 11. A Detailed Inspection 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 tor 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. 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. B. WORK INSTRUCTIONS Actions Required for Compliance 1. Requirements Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 26 of 260 ### Page 27 (OCR) 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 Method of Compli- Refer to the listed procedures ance in SB 747-53A2907 Original ssue or later approved revi- sions as an accepted proce- dure. All Airplanes. Do a General Visual Inspec- Do PART 1: OPEN ACCESS. tion (GVI) of each free flange FIGURE 1 of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 1: OPTION 1 (ACTION 1): Re- DO PART 2: LEFT SIDE RA- FOUND TWO OR move radius fillers at each DIUS FILLER REMOVAL. MORE RADIUS free flange of the stringer with FILLERS AT ANY two or more fastener loca- FREE FLANGE OF tions. THE STRINGER. OPTION 1 (ACTION 2): Do a FIGURE 3 detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. OPTION 2: Do a detailed in- FIGURE 4 spection of the stringers and the stringer splice fitting with- in the profile of the stringer splice installation for any crack. CONDITION 1.1: ANY CONDITION 1.1 (ACTION 1): CRACK FOUND AS Contact the Boeing Company A RESULT OF OP- for repair instructions and do Do PART 4: CLOSE ACCESS. TION 1 INSPECTION. the repair. CONDITION 1.1 (ACTION 2): FIGURE 1 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 1.2: NO CONDITION 1.2 (ACTION 1): FIGURE 5 A RESULT OF OP- CRACK FOUND AS Install radius fillers. DO PART 4: CLOSE ACCESS. TION 1 INSPECTION. CONDITION 1.2 (ACTION 2): FIGURE 1 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 See page 1 for details 747-53A2907 RB 27 of 260 ### Page 28 (OCR) 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 Method of Compli- Refer to the listed procedures ance in SB 747-53A2907 Original ssue or later approved revi- sions as an accepted proce- dure. CONDITION 1.3: ANY CONDITION 1.3 (ACTION 1): - CRACK FOUND AS A RESULT OF OP- for repair instructions and do Contact the Boeing Company Do PART 4: CLOSE ACCESS. TION 2 INSPECTION. the repair. CONDITION 1.3 (ACTION 2): FIGURE 1 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. • CONDITION 1.4: NO Do a GVI of each free flange Do PART 4: CLOSE ACCESS. CRACK FOUND AS ot the stringers at the stringer A RESULT OF OP- splice for radius fillers at the FIGURE 1 TION 2 INSPECTION. fastener locations. CONDITION 2: Do a detailed inspection of FIGURE 6 FOUND NO MORE the 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): CRACK FOUND. Contact the Boeing Company for repair instructions and do Do PART 4: CLOSE ACCESS. the repair. CONDITION 2.1 (ACTION 2): FIGURE 1 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. • CONDITION 2.2: NO Do a GVI of each free flange Do PART 4: CLOSE ACCESS. CRACK FOUND. of the stringers at the stringer FIGURE 1 splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 28 of 260 ### Page 29 (OCR) 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 Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. All Airplanes. Do a General Visual Inspection Do PART 1: OPEN (GVI) of each free flange of the ACCESS. stringers at the stringer splice FIGURE 7 for radius fillers at the fastener locations. CONDITION 3: OPTION 3 (ACTION 1): Re- DO PART 3: FOUND TWO OR move radius fillers at each free RIGHT SIDE RA- MORE RADIUS flange of the stringer with two DIUS FILLER RE- FILLERS AT ANY or more fastener locations. MOVAL. FREE FLANGE OF OPTION 3 (ACTION 2): Do a FIGURE 9 THE STRINGER. detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. OPTION 4: Do a detailed in- FIGURE 10 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): - CRACK FOUND AS Contact the Boeing Company A RESULT OF OP- TION 3 INSPECTION. for repair instructions and do the repair. Do PART 4: CLOSE ACCESS. CONDITION 3.1 (ACTION 2): FIGURE 7 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 See page 1 for details 747-53A2907 RB 29 of 260 ### Page 30 (OCR) 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 Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. CONDITION 3.2: NO CONDITION 3.2 (ACTION 1): FIGURE 11 CRACK FOUND AS Install radius fillers. A RESULT OF OP- Do PART 4: TION 3 INSPECTION. CLOSE ACCESS. CONDITION 3.2 (ACTION 2): FIGURE 7 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 3.3: ANY CONDITION 3.3 (ACTION 1): CRACK FOUND AS A RESULT OF OP- TION 4 INSPECTION. the repair. Contact the Boeing Company for repair instructions and do CLOSE ACCESS. Do PART 4: CONDITION 3.3 (ACTION 2): FIGURE 7 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 3.4: NO Do a GVI of each free flange Do PART 4: CRACK FOUND AS of the stringers at the stringer CLOSE ACCESS A RESULT OF OP- splice for radius fillers at the TION 4 INSPECTION. fastener locations. FIGURE 7 CONDITION 4: Do a detailed inspection of the FIGURE 12 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. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 30 of 260 ### Page 31 (OCR) 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 Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. CONDITION 4.1: ANY CONDITION 4.1 (ACTION 1): - CRACK FOUND. the repair. Contact the Boeing Company for repair instructions and do Do PART 4: CLOSE ACCESS. CONDITION 4.1 (ACTION 2): FIGURE 7 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 4.2: NO Do a GVI of each free flange Do PART 4: CRACK FOUND. of the stringers at the stringer CLOSE ACCESS. splice for radius fillers at the fastener locations. FIGURE 7 Group 2: Table 3: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. All Airplanes. Do a General Visual Inspection Do PART 1: OPEN (GVI) of each free flange of the ACCESS. stringers at the stringer splice FIGURE 13 for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 See page 1 for details 747-53A2907 RB 31 of 260 ### Page 32 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 2: Table 3: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. CONDITION 5: OPTION 5 (ACTION 1): Re- DO PART 2: LEFT FOUND TWO OR move radius fillers at each free SIDE RADIUS MORE RADIUS flange of the stringer with two FILLER RE- FILLERS AT ANY or more fastener locations. MOVAL. FREE FLANGE OF OPTION 5 (ACTION 2): Do a FIGURE 15 THE STRINGER. detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. OPTION 6: Do a detailed in- FIGURE 16 spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. CONDITION 5.1: ANY CONDITION 5.1 (ACTION 1): CRACK FOUND AS A RESULT OF OP- Contact the Boeing Company for repair instructions and do Do PART 4: CLOSE ACCESS. TION 5 INSPECTION. the repair. CONDITION 5.1 (ACTION 2): FIGURE 13 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 5.2: NO CONDITION 5.2 (ACTION 1): FIGURE 17 CRACK FOUND AS Install radius fillers. Do PART 4: A RESULT OF OP- TION 5 INSPECTION. CLOSE ACCESS. CONDITION 5.2 (ACTION 2): FIGURE 13 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 See page 1 for details 747-53A2907 RB 32 of 260 ### Page 33 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 2: Table 3: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. CONDITION 5.3: ANY CONDITION 5.3 (ACTION 1): - CRACK FOUND AS Contact the Boeing Company Do PART 4: A RESULT OF OP- for repair instructions and do TION 6 INSPECTION. the repair. CLOSE ACCESS. CONDITION 5.3 (ACTION 2): FIGURE 13 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the tastener locations. CONDITION 5.4: NO Do a GVI of each free flange Do PART 4: CRACK FOUND AS of the stringers at the stringer CLOSE ACCESS. A RESULT OF OP- splice for radius fillers at the TION 6 INSPECTION. fastener locations. FIGURE 13 CONDITION 6: Do a detailed inspection of the FIGURE 18 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 6.1: ANY CONDITION 6.1 (ACTION 1): CRACK FOUND. for repair instructions and do Contact the Boeing Company Do PART 4: the repair. CLOSE ACCESS. CONDITION 6.1 (ACTION 2): FIGURE 13 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 6.2: NO Do a GVI of each free flange Do PART 4: CRACK FOUND. of the stringers at the stringer CLOSE ACCESS. splice for radius fillers at the FIGURE 13 fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 See page 1 for details 747-53A2907 RB 33 of 260 ### Page 34 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 2: Table 4: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. All Airplanes. Do a General Visual Inspection Do PART 1: OPEN (GVI) of each free flange of the ACCESS. stringers at the stringer splice FIGURE 19 for radius fillers at the fastener locations. CONDITION 7: OPTION 7 (ACTION 1): Re- DO PART 3: FOUND TWO OR move radius fillers at each tree RIGHT SIDE RA- MORE RADIUS flange of the stringer with two DIUS FILLER RE- FILLERS AT ANY or more fastener locations. MOVAL. FREE FLANGE OF THE STRINGER. OPTION 7 (ACTION 2): Do a FIGURE 21 detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. OPTION 8: Do a detailed in- FIGURE 22 spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. CONDITION 7.1: ANY CONDITION 7.1 (ACTION 1): CRACK FOUND AS Contact the Boeing Company Do PART 4: A RESULT OF OP- TION 7 INSPECTION. the repair. for repair instructions and do CLOSE ACCESS. CONDITION 7.1 (ACTION 2): FIGURE 19 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 34 of 260 ### Page 35 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 2: Table 4: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. CONDITION 7.2: NO CONDITION 7.2 (ACTION 1): FIGURE 23 CRACK FOUND AS Install radius fillers. A RESULT OF OP- Do PART 4: TION 7 INSPECTION. CLOSE ACCESS. CONDITION 7.2 (ACTION 2): FIGURE 19 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 7.3: ANY CONDITION 7.3 (ACTION 1): CRACK FOUND AS Contact the Boeing Company Do PART 4: A RESULT OF OP- for repair instructions and do TION 8 INSPECTION. the repair. CLOSE ACCESS. CONDITION 7.3 (ACTION 2): FIGURE 19 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 7.4: NO Do a GVI of each free flange Do PART 4: CRACK FOUND AS of the stringers at the stringer CLOSE ACCESS. A RESULT OF OP- splice for radius fillers at the TION 8 INSPECTION. fastener locations. FIGURE 19 CONDITION 8: Do a detailed inspection of the FIGURE 24 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. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 See page 1 for details 747-53A2907 RB 35 of 260/ ### Page 36 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 2: Table 4: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. CONDITION 8.1: ANY CONDITION 8.1 (ACTION 1): CRACK FOUND. Contact the Boeing Company Do PART 4: for repair instructions and do CLOSE ACCESS. the repair. CONDITION 8.1 (ACTION 2): FIGURE 19 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 8.2: NO Do a GVI of each free flange Do PART 4: CRACK FOUND. of the stringers at the stringer CLOSE ACCESS splice for radius fillers at the FIGURE 19 fastener locations. Group 3: Table 5: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. All Airplanes. Do a General Visual Inspection Do PART 1: OPEN (GVI) of each free flange of the ACCESS. stringers at the stringer splice for radius fillers at the fastener FIGURE 13 locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 36 of 260 ### Page 37 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 5: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. CONDITION 9: OPTION 9 (ACTION 1): Re- DO PART 2: LEFT FOUND TWO OR move radius fillers at each free SIDE RADIUS MORE RADIUS flange of the stringer with two FILLER RE- FILLERS AT ANY or more fastener locations. MOVAL. FREE FLANGE OF OPTION 9 (ACTION 2): Do a FIGURE 15 THE STRINGER. detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. OPTION 10: Do a detailed in- FIGURE 16 spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. CONDITION 9.1: ANY CONDITION 9.1 (ACTION 1): A RESULT OF OP- TION 9 INSPECTION. CRACK FOUND AS the repair. for repair instructions and do Contact the Boeing Company Do PART 4: CLOSE ACCESS. CONDITION 9.1 (ACTION 2): FIGURE 13 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 9.2: NO CONDITION 9.2 (ACTION 1): FIGURE 17 CRACK FOUND AS Install radius fillers. Do PART 4: A RESULT OF OP- TION 9 INSPECTION. CLOSE ACCESS. CONDITION 9.2 (ACTION 2): FIGURE 13 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 See page 1 for details 747-53A2907 RB 37 of 260 ### Page 38 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 5: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. CONDITION 9.3: ANY CONDITION 9.3 (ACTION 1): A RESULT OF OP- CRACK FOUND AS Contact the Boeing Company for repair instructions and do Do PART 4: TION 10 INSPEC- the repair. CLOSE ACCESS. TION. CONDITION 9.3 (ACTION 2): FIGURE 13 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 9.4: NO Do a GVI of each free flange Do PART 4: CRACK FOUND AS of the stringers at the stringer CLOSE ACCESS A RESULT OF OP- TION 10 INSPEC- splice for radius fillers at the fastener locations. FIGURE 13 TION. CONDITION 10: Do a detailed inspection of the FIGURE 18 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 10.1: CONDITION 10.1 (ACTION 1): ANY CRACK Contact the Boeing Company FOUND. for repair instructions and do Do PART 4: CLOSE ACCESS. the repair. CONDITION 10.1 (ACTION 2): FIGURE 13 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 10.2: NO Do a GVI of each free flange Do PART 4: CRACK FOUND. of the stringers at the stringer CLOSE ACCESS. splice for radius fillers at the FIGURE 13 fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 38 of 260 ### Page 39 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 6: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. All Airplanes. Do a General Visual Inspection Do PART 1: OPEN (GVI) of each free flange of the ACCESS. stringers at the stringer splice FIGURE 19 for radius fillers at the fastener locations. CONDITION 11: OPTION 11 (ACTION 1): Re- DO PART 3: FOUND TWO OR move radius fillers at each free RIGHT SIDE RA- MORE RADIUS flange of the stringer with two DIUS FILLER RE- FILLERS AT ANY or more fastener locations. MOVAL. FREE FLANGE OF THE STRINGER. OPTION 11 (ACTION 2): Do a FIGURE 21 detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. OPTION 12: Do a detailed in- FIGURE 22 spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. CONDITION 11.1: CONDITION 11.1 (ACTION 1): - AS A RESULT OF ANY CRACK FOUND OPTION 11 INSPEC- the repair. for repair instructions and do Contact the Boeing Company Do PART 4: CLOSE ACCESS. TION. CONDITION 11.1 (ACTION 2): FIGURE 19 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 39 of 260 ### Page 40 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 6: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. CONDITION 11.2: NO CONDITION 11.2 (ACTION 1): FIGURE 23 CRACK FOUND AS Install radius fillers. Do PART 4: A RESULT OF OP- TION 11 INSPEC- CLOSE ACCESS. TION. CONDITION 11.2 (ACTION 2): FIGURE 19 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 11.3: CONDITION 11.3 (ACTION 1): ANY CRACK FOUND AS A RESULT OF Contact the Boeing Company for repair instructions and do CLOSE ACCESS. Do PART 4: OPTION 12 INSPEC- the repair. TION. CONDITION 11.3 (ACTION 2): FIGURE 19 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 11.4: NO Do a GVI of each free flange Do PART 4: CRACK FOUND AS of the stringers at the stringer CLOSE ACCESS A RESULT OF OP- splice for radius fillers at the TION 12 INSPEC- fastener locations. FIGURE 19 TION. CONDITION 12: Do a detailed inspection of the FIGURE 24 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. Original Issue: March 03, 2022 Revision 1: March 14, 2025 Export Controlled ECCN: 9E991 See page 1 for details 747-53A2907 RB 40 of 260 ### Page 41 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Group 3: Table 6: Stringer Splice Inspection of Stringers 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. Condition Action Method of Compliance Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. CONDITION 12.1: CONDITION 12.1 (ACTION 1): - ANY CRACK Contact the Boeing Company Do PART 4: FOUND. for repair instructions and do the repair. CLOSE ACCESS. CONDITION 12.1 (ACTION 2): FIGURE 19 Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 12.2: NO Do a GVI of each free flange Do PART 4: CRACK FOUND. of the stringers at the stringer CLOSE ACCESS. fastener locations. splice for radius fillers at the FIGURE 19 Original Issue: March 03, 2022 Revision 1: March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 41 of 260 ### Page 42 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT This Figure applies only to: Group 1. STA 2180 STA 1960 STA 1740 1960 STA →BL-O STA 1740 BL-0 00000000000 000000000000000000 S-23L 2986723 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 (SHEET 1 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 42 of 260 ### Page 43 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA STA 1960 1740 BL-0 - - BL-0 S-1L S-2L N S-2L ￾ S-1L S-3L -S-3L S-4L • S-4L S-5L -S-5L S-6L - S-6L S-7L - S-7L S-8L • S-8L S-9L • S-9L S-10L - Q S-10L S-11L • S-11L S-13L S-12L H - S-12L S-13L S-14L • S-14L S-15L • S-15L S-16L • S-16L S-17L- - S-17L S-18L • S-18L S-19L - K - S-19L 00000000 00000 S-23L - S-23L LEFT SIDE FWD MAIN ENTRY DOOR NO. 4 VIEW LOOKING UP AND OUTBOARD 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 (SHEET 2 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 43 of 260 ### Page 44 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA 2180 STA 1960 BL-O D S-23L 2986727 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 (SHEET 3 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 44 of 260 ### Page 45 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA STA 2180 1960 BL-O - - BL-0 S-1L -S-1L S-2L - S-2L S-3L -S-3L S-4L - S-4L S-5L -S-5L S-6L -S-6L S-7L -S-7L S-8L -S-8L S-9L - S-9L S-10L - VI -S-10L S-11L - S-11L S-12L - S-12L S-13L - S-13L S-14L -S-14L S-15L- - S-15L S-16L -S-16L S-17L -S-17L S-18L- -S-18L S-19L -S-19L 000000000000000 S-23L -S-23L FWD VIEW LOOKING UP AND OUTBOARD 2986728 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 (SHEET 4 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 45 of 260 ### Page 46 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA STRINGER 1) (8 LOCATIONS) SKIN 1741.10 S-8L S-9L TYPICAL STRINGER SPLICE FITTING FWD > STA STRINGER 2) (8 LOCATIONS) SKIN 1741.10 S-10L PICA STRINGER SPLICE FITTING FWD STA STRINGER 3) (8 LOCATIONS) SKIN 1741.10 S-11L TYPICAL STRINGER 2986721 SPLICE FITTING FWD 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 (SHEET 5 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 46 of 260 ### Page 47 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT 8 LOCATIONS 4 STA 1741 S-12L TYPICAL STRINGER H FWD SPLICE FITTING STRINGER 5) 8 LOCATIONS STA 1741.10 STRINGER S-13L TYPICAL STRINGER FWD SPLICE FITTING STA 1741.10 ) 16 LOCATIONS STRINGER S-14l S-15L STRINGER YPICAL SPLICE FITTING FWD 2986729 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 (SHEET 6 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 47 of 260 ### Page 48 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA 7) 12 LOCATIONS 1741.10 STRINGER S-16L- A TYPICAL STRINGER SPLICE FITTING K FWD STA 1960 STRINGER 8) 16 LOCATIONS S-1L S-2L S-3L A TYPICAL STRINGER FWD SPLICE FITTING STA 1960 9) 16 LOCATIONS STRINGER S-4L - TYPICAL STRINGER SPLICE FITTING FWD 2986731 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 (SHEET 7 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 48 of 260 ### Page 49 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA 16 LOCATIONS (10 1961.10 S-5L STRINGER STRINGER SPLICE FITTING TYPICAL FWD N SIA 1960 16 LOCATIONS S-6L S-7L STRINGER STRINGER SPLICE FITTING TYPICAL FWD STA 1960 STRINGER 12) 12 LOCATIONS S-8L S-9L STRINGER SPLICE FITTING TYPICA -WD 2986717 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 (SHEET 8 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 49 of 260 ### Page 50 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA 13) 12 LOCATIONS 1960 STRINGER + * S-10L S-11L TYPICAL STRINGER SPLICE WD FITTING 8 LOCATIONS (14 STA STRINGER 1960 S-12L A STRINGER SPLICE FITTING TYPICAL R FWD STA STRINGER 15) 16 LOCATIONS 2181.10 SKIN S-1L S-2L S-3L ti TYPICAL -WD STRINGER SPLICE 2986752 FITTING 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 (SHEET 9 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 50 of 260 ### Page 51 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT 16) 16 LOCATIONS SKIN STRINGER 2181.10 - 7₺-S STRINGER SPLICE FITTING TYPICAL FWD 17) (12 LOCATIONS) STA 2181.10 SKIN S-5L S-6L S-7L S-8L S-9L STRINGER STRINGER SPLICE FITTING TYPICAL FWD 2986739 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 (SHEET 10 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 51 of 260 ### Page 52 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STRINGER SPLICE 12 LOCATIONS STA FITTING 2181.10 S-10L S-11L A - TYPICAL FWD STRINGER (19) 8 LOCATIONS STA STRINGER SPLICE FITTING 2181.10 S-12L TYPICAL STRINGER W FWD 2986742 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 (SHEET 11 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 52 of 260 ### Page 53 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STRINGER SPLICE —STRINGER RADIUS FILLER SKIN TYPICAL PRODUCTION OR REPAIR STRINGER SPLICE A-A 2988876 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 each airplane. Step Task Name Identification Qty More Data 1 Inspect STRINGER (a)(b)(c) 2 Inspect STRINGER (a) (b)(c) Inspect STRINGER (a) (b)(c) 4 Inspect STRINGER (a) (b)(c) 5 Inspect STRINGER (a) (b)(c) Inspect STRINGER (a) (b)(c) 7 Inspect STRINGER (a) (b)(c) Inspect STRINGER (a) (b)(c) 9 Inspect STRINGER (a)(b)(c) 10 Inspect STRINGER (a) (b)(c) 11 Inspect STRINGER (a)(b)(c) 12 Inspect STRINGER (a)(b)(c) 13 Inspect STRINGER (a) (b)(c) 14 Inspect STRINGER (a) (b)(c) 15 Inspect STRINGER - (a) (b)(c) 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 (SHEET 12 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 53 of 260 ### Page 54 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT Step Task Name Identification Qty More Data 16 Inspect STRINGER (a) (b)(c) 17 Inspect STRINGER (a) (b)(c) 18 Inspect STRINGER (a) (b)(c) 19 Inspect STRINGER (a)(b)(c) (a) Do a General Visual Inspection (GVI) of each free flange of the stringer at the stringer splice for radius fillers at the fastener locations. (b) Can be a production or repaired stringer splice. The stringer splices could have been repaired with or without radius fillers. (C) A repaired stringer splice is defined as Structural Repair Manual (SRM) repairs, Boeing approved unpub- lished repair, or rework accomplished during production identified in the Significant Rework Log (SRL). 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 (SHEET 13 OF 13) Original Issue: March 03, 2022 Revision 1 March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 54 of 260 ### Page 55 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT This Figure applies only to: Group 1. STA 1960 STA 1740 STA - -BL-O 1960 0000000000000000000 BL-0 00000000000 S-23L 2970024 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 (SHEET 1 OF 8) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 55 of 260 ### Page 56 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA STA 1960 1740 BL-0 -- - BL-0 S-1L • S-1L S-2L • S-2L S-3L E - S-3L S-4L - S-4L S-5L -S-5L S-6L - S-6L S-7L - S-7L S-8L - S-8L S-9L - - S-9L S-10L -S-10L S-11L - S-11L S-12L - S-12L S-13L 1202 • S-13L S-14L - S-14L S-15L- - S-15L S-16L - S-16L S-17L -S-17L S-18L - S-18L S-19L - S-19L 000 000000000000 S-23L - S-23L LEFT SIDE FWD MAIN ENTRY DOOR NO. 4 VIEW LOOKING UP AND OUTBOARD INSPECTION AREA B 2984479 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 (SHEET 2 OF 8) Original Issue: March 03, 2022 Revision 1 March 14, 2025 747-53A2907 RB Export Controlled ECCN: 9E991 See page 1 for details 56 of 260 ### Page 57 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA 2180 -BL-O BL-O 600000000000 8-231-- 2984484 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 (SHEET 3 OF 8) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 57 of 260 ### Page 58 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA STA 2180 1960 BL-O -- BL-O S-1L -S- 1L S-2L -S-2L S-3L - S-3L S-4L -S-4L S-5L -S-5L S-6L - S-6L S-7L - S-7L S-8L -S-8L S-9L - S-9L S-10L -S-10L S-11L S-11L S-12L -S-12L S-13L - S-13L S-14L -S-14L S-15L - S-15L S-16L -S-16L S-17L - S-17L S-18L • S-18L S-19L - S-19L 000000000 00000 S-23L - S-23L FWD VIEW LOOKING UP AND OUTBOARD INSPECTION 2984485 AREA 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 (SHEET 4 OF 8) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 58 of 260 ### Page 59 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT FRAME STA (TYPICAL) STRINGER (TYPICAL) END OF STRINGER SKIN MIRROR 123 B END OF STRINGER SPLICE STRINGER SPLICE END OF STRINGER SPLICE FWD STRINGER SPLICE INSPECTION AREA (TYPICAL) E DETAILED 2984487 INSPECTION 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 (SHEET 5 OF 8) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 59 of 260 ### Page 60 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT MIRROR STRINGER SPLICE TYPICAL CRACK STRINGER STRINGER SPLICE STRINGER INSPECTION (TYPICAL) A-A - STRINGER — SKIN STRINGER SPLICE J NBD TYPICAL PRODUCTION OR REPAIR STRINGER SPLICE B-B 2984480 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 (SHEET 6 OF 8) Original Issue: March 03, 2022 Revision 1 March 14, 2025 Export Controlled ECCN: 9E991 747-53A2907 RB See page 1 for details 60 of 260 The text continues at https://openairdocs.org/service-documents/boeing/747-53a2907/file/41265b269b50.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). 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