# Boeing Alert Requirements Bulletin 747-53A2907 RB: 747-53A2907 RB - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2022-0816; AD 2023-12-18 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Requirements Bulletin 747-53A2907 RB](https://openairdocs.org/service-documents/boeing/747-53a2907-rb.md) - Title as filed: 747-53A2907 RB - Pages: 243 - PDF: https://openairdocs.org/files/sha256/7f/3f/7f3f5b0471ecac69c2e6f03585084b64a654ccca6d839c90719cc695f5c05c8e - Page: https://openairdocs.org/service-documents/boeing/747-53a2907-rb/file/7f3f5b0471ec ## Text Some pages are 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 Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2907 RB Original Issue: March 03, 2022 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. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2022 Boeing. Unpublished Work. All Rights Reserved. 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March 03, 2022 747-53A2907 RB 1 of 243 4.0 ### Page 2 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 2 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT BLANK PAGE ### Page 3 Table of Contents 1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 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] . . . . . . . . . . . . . . . . 25 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] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 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] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 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] . . . . . . . . . . . . . . . . . 54 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] . . . . . 68 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] . . . . . . . . . . . . . 76 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 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 89 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 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 97 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] . . . . . . . . . . . . 105 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] . 119 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] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 127 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] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 141 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] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 150 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] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 159 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] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 174 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 3 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 4 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] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 183 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] . . . . . . . . . . . . . . 198 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] . . . . . . . . . . . . . . 208 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] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 218 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] . . . . . . . . . . . . . . . . . . . . 234 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 4 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 5 Commercial Airplanes 747 Requirements Bulletin ALERT Number: 747-53A2907 RB Original Issue: March 03, 2022 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) 1420-1563 in 2 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. DESCRIPTIONCONFIGURATIONGROUP 747-8 Airplanes.- 1 747-8F Airplanes.- 2 Airplane Models: 747-8, 747-8F GroupVariable Number 1RC001 - RC009 1RC021 - RC040 1RC051 - RC060 1RC066 - RC072 1RC076 - RC077 GroupVariable Number 2RC501 - RC514 2RC521 - RC528 2RC531 - RC541 2RC546 - RC566 2RC571 - RC582 GroupVariable Number 2RC601 - RC610 2RC641 - RC644 2RC651 - RC652 2RC661 2RC671 - RC674 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 5 of 243 ### Page 6 GroupVariable Number 2RC681 - RC689 GroupVariable Number -- GroupVariable Number -- B. Spares Affected None. 2. CONCURRENT REQUIREMENTS None. 3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Requirements Bulletin 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 Paragraph 3. Accomplishment Instructions. Group 2: Accomplish the required action(s), based on the applicable condition(s) in Table 3 and Table 4 in accordance with Paragraph 3. Accomplishment Instructions. 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 38 months after the original issue date of Require- ments Bulletin 747-53A2907 RB. Before 12,000 total flights cy- cles. Do a General Visual Inspection (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. All Airplanes. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 6 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 7 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.OPTION 1 (ACTION 1): Re- move radius fillers at each free flange of the stringer with two or more fastener locations. CONDITION 1: FOUND TWO OR MORE RADIUS FILLERS AT ANY FREE FLANGE OF THE STRINGER. Before further flight.OPTION 1 (ACTION 2): Do adetailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. Before further flight.OPTION 2: Do a detailed in- spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. -Before further flight.CONDITION 1.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 1.1: ANY CRACK FOUND AS A RESULT OF OP- TION 1 INSPECTION. -Within 9,600 flight cycles after the last detailed inspection. CONDITION 1.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Before further flight.CONDITION 1.2 (ACTION 1): Install radius fillers. CONDITION 1.2: NO CRACK FOUND AS A RESULT OF OP- TION 1 INSPECTION. -.Within 9,600 flight cycles after thelast detailed inspection.CONDITION 1.2 (ACTION 2):Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Before further flight.CONDITION 1.3 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 1.3: ANY CRACK FOUND AS A RESULT OF OP- TION 2 INSPECTION. -Within 4,600 flight cycles after the last detailed inspection. CONDITION 1.3 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 7 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 8 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,600 flight cycles after the last detailed inspection. 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 CRACK FOUND AS A RESULT OF OP- TION 2 INSPECTION. -Before further flight.Do a detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. CONDITION 2: FOUND NO MORE THAN ONE RADIUS FILLER AT ANY FREE FLANGE OF THE STRINGER. -Before further flight.CONDITION 2.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 2.1: ANY CRACK FOUND. -Within 9,600 flight cycles after the last detailed inspection. CONDITION 2.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Within 9,600 flight cycles after the last detailed inspection. 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 CRACK FOUND. 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 38 months after the original issue date of Require- ments Bulletin 747-53A2907 RB. Before 12,000 total flights cy- cles. Do a General Visual Inspection (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. All Airplanes. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 8 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 9 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.OPTION 3 (ACTION 1): Re- move radius fillers at each free flange of the stringer with two or more fastener locations. CONDITION 3: FOUND TWO OR MORE RADIUS FILLERS AT ANY FREE FLANGE OF THE STRINGER. Before further flight.OPTION 3 (ACTION 2): Do adetailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. Before further flight.OPTION 4: Do a detailed in- spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. -Before further flight.CONDITION 3.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 3.1: ANY CRACK FOUND AS A RESULT OF OP- TION 3 INSPECTION. -Within 9,600 flight cycles after the last detailed inspection. CONDITION 3.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Before further flight.CONDITION 3.2 (ACTION 1): Install radius fillers. CONDITION 3.2: NO CRACK FOUND AS A RESULT OF OP- TION 3 INSPECTION. -Within 9,600 flight cycles after thelast detailed inspection.CONDITION 3.2 (ACTION 2):Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Before further flight.CONDITION 3.3 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 3.3: ANY CRACK FOUND AS A RESULT OF OP- TION 4 INSPECTION. -Within 4,600 flight cycles after the last detailed inspection. CONDITION 3.3 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 9 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 10 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,600 flight cycles after the last detailed inspection. 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 CRACK FOUND AS A RESULT OF OP- TION 4 INSPECTION. -Before further flight.Do a detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. CONDITION 4: FOUND NO MORE THAN ONE RADIUS FILLER AT ANY FREE FLANGE OF THE STRINGER. -Before further flight.CONDITION 4.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 4.1: ANY CRACK FOUND. -Within 9,600 flight cycles after the last detailed inspection. CONDITION 4.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Within 9,600 flight cycles after the last detailed inspection. 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 CRACK FOUND. 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 38 months after the original issue date of Require- ments Bulletin 747-53A2907 RB. Before 12,000 total flights cy- cles. Do a General Visual Inspection (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. All Airplanes. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 10 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 11 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.OPTION 5 (ACTION 1): Re- move radius fillers at each free flange of the stringer with two or more fastener locations. CONDITION 5: FOUND TWO OR MORE RADIUS FILLERS AT ANY FREE FLANGE OF THE STRINGER. Before further flight.OPTION 5 (ACTION 2): Do adetailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. Before further flight.OPTION 6: Do a detailed in- spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. -Before further flight.CONDITION 5.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 5.1: ANY CRACK FOUND AS A RESULT OF OP- TION 5 INSPECTION. -Within 9,600 flight cycles after the last detailed inspection. CONDITION 5.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Before further flight.CONDITION 5.2 (ACTION 1): Install radius fillers. CONDITION 5.2: NO CRACK FOUND AS A RESULT OF OP- TION 5 INSPECTION. -Within 9,600 flight cycles after thelast detailed inspection.CONDITION 5.2 (ACTION 2):Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Before further flight.CONDITION 5.3 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 5.3: ANY CRACK FOUND AS A RESULT OF OP- TION 6 INSPECTION. -.Within 4,600 flight cycles after the last detailed inspection. CONDITION 5.3 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 11 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 12 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,600 flight cycles after the last detailed inspection. Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 5.4: NO CRACK FOUND AS A RESULT OF OP- TION 6 INSPECTION. -Before further flight.Do a detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. CONDITION 6: FOUND NO MORE THAN ONE RADIUS FILLER AT ANY FREE FLANGE OF THE STRINGER. -Before further flight.CONDITION 6.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 6.1: ANY CRACK FOUND. -.Within 9,600 flight cycles after the last detailed inspection. CONDITION 6.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Within 9,600 flight cycles after the last detailed inspection. 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 CRACK FOUND. 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 38 months after the original issue date of Require- ments Bulletin 747-53A2907 RB. Before 12,000 total flights cy- cles. Do a General Visual Inspection (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. All Airplanes. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 12 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 13 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.OPTION 7 (ACTION 1): Re- move radius fillers at each free flange of the stringer with two or more fastener locations. CONDITION 7: FOUND TWO OR MORE RADIUS FILLERS AT ANY FREE FLANGE OF THE STRINGER. Before further flight.OPTION 7 (ACTION 2): Do adetailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. Before further flight.OPTION 8: Do a detailed in- spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. -Before further flight.CONDITION 7.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 7.1: ANY CRACK FOUND AS A RESULT OF OP- TION 7 INSPECTION. -Within 9,600 flight cycles after the last detailed inspection. CONDITION 7.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Before further flight.CONDITION 7.2 (ACTION 1): Install radius fillers. CONDITION 7.2: NO CRACK FOUND AS A RESULT OF OP- TION 7 INSPECTION. -Within 9,600 flight cycles after thelast detailed inspection.CONDITION 7.2 (ACTION 2):Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Before further flight.CONDITION 7.3 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 7.3: ANY CRACK FOUND AS A RESULT OF OP- TION 8 INSPECTION. -Within 4,600 flight cycles after the last detailed inspection. CONDITION 7.3 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 13 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 14 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. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,600 flight cycles after the last detailed inspection. 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 CRACK FOUND AS A RESULT OF OP- TION 8 INSPECTION. -Before further flight.Do a detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. CONDITION 8: FOUND NO MORE THAN ONE RADIUS FILLER AT ANY FREE FLANGE OF THE STRINGER. -Before further flight.CONDITION 8.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 8.1: ANY CRACK FOUND. -Within 9,600 flight cycles after the last detailed inspection. CONDITION 8.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -Within 9,600 flight cycles after the last detailed inspection. 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 CRACK FOUND. 4. APPROVAL This Requirements Bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this document comply with the applicable regulations and are FAA approved, as well as European Union Aviation Safety Agency (EASA)/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. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 14 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 15 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 RC End to identify the requirements that are restated from the RB. For the related SB, the areas between RC Start and RC End, including sub-steps and any figures identified between RC Start and RC End, must be done to comply with the AD. Therefore, an Alternative Method of Compliance (AMOC) is required for any deviations to steps between RC Start and RC End, including substeps and identified figures. For the related SB, the steps not between RC Start and RC End may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC; this is provided that the steps between RC Start and RC End, including sub-steps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. Figures not required for compliance are omitted from the RB. 2. This is an Enhanced Required for Compliance document. The Boeing processes used to create the Service Bulletin (SB) and the Requirements Bulletin (RB) ensure that the information between "RC Start" and "RC End" in the SB are identical to the information in the same sections (Compliance, Work Instructions...) of the RB which the SB refers to as the related document. 3. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance. 4. Boeing Service Letter 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. 5. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque Values: — Values for structural fasteners are given in 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. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 15 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 16 6. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 7. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 8. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 9. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51. 10. A General Visual Inspection 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 for tightness/security. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors and magnifying lenses may be necessary. Surface cleaning and elaborate access procedures may be required. 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. B. WORK INSTRUCTIONS Actions Required for Compliance 1. Requirements Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 16 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 17 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. Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved revi- sions as an accepted proce- dure. Method of Compli- ance ActionCondition Do PART 1: OPEN ACCESS.-Do a General Visual Inspec- tion (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. All Airplanes. -FIGURE 1 DO PART 2: LEFT SIDE RA- DIUS FILLER REMOVAL. -OPTION 1 (ACTION 1): Re- move radius fillers at each free flange of the stringer with two or more fastener loca- tions. CONDITION 1: FOUND TWO OR MORE RADIUS FILLERS AT ANY FREE FLANGE OF THE STRINGER. -FIGURE 3OPTION 1 (ACTION 2): Do a detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. -FIGURE 4OPTION 2: Do a detailed in- spection of the stringers and the stringer splice fitting with- in the profile of the stringer splice installation for any crack. Do PART 4: CLOSE ACCESS.-CONDITION 1.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 1.1: ANY CRACK FOUND AS A RESULT OF OP- TION 1 INSPECTION. -FIGURE 1CONDITION 1.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 5CONDITION 1.2 (ACTION 1): Install radius fillers. CONDITION 1.2: NO CRACK FOUND AS A RESULT OF OP- TION 1 INSPECTION. -FIGURE 1CONDITION 1.2 (ACTION 2):Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 17 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 18 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. Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved revi- sions as an accepted proce- dure. Method of Compli- ance ActionCondition Do PART 4: CLOSE ACCESS.-CONDITION 1.3 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 1.3: ANY CRACK FOUND AS A RESULT OF OP- TION 2 INSPECTION. -FIGURE 1CONDITION 1.3 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 1Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 1.4: NO CRACK FOUND AS A RESULT OF OP- TION 2 INSPECTION. -FIGURE 6Do the detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. CONDITION 2: FOUND NO MORE THAN ONE RADIUS FILLER AT ANY FREE FLANGE OF THE STRINGER. Do PART 4: CLOSE ACCESS.-CONDITION 2.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 2.1: ANY CRACK FOUND. -FIGURE 1CONDITION 2.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 1Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 2.2: NO CRACK FOUND. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 18 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 19 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. Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. Method of ComplianceActionCondition Do PART 1: OPEN ACCESS. -Do a General Visual Inspection (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. All Airplanes. -FIGURE 7 DO PART 3: RIGHT SIDE RA- DIUS FILLER RE- MOVAL. -OPTION 3 (ACTION 1): Re- move radius fillers at each free flange of the stringer with two or more fastener locations. CONDITION 3: FOUND TWO OR MORE RADIUS FILLERS AT ANY FREE FLANGE OF THE STRINGER. -FIGURE 9OPTION 3 (ACTION 2): Do adetailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. -FIGURE 10OPTION 4: Do a detailed in- spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. Do PART 4: CLOSE ACCESS. -CONDITION 3.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 3.1: ANY CRACK FOUND AS A RESULT OF OP- TION 3 INSPECTION. -FIGURE 7CONDITION 3.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 11CONDITION 3.2 (ACTION 1): Install radius fillers. CONDITION 3.2: NO CRACK FOUND AS A RESULT OF OP- TION 3 INSPECTION. -FIGURE 7CONDITION 3.2 (ACTION 2):Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 19 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 20 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. Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. Method of ComplianceActionCondition Do PART 4: CLOSE ACCESS. -CONDITION 3.3 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 3.3: ANY CRACK FOUND AS A RESULT OF OP- TION 4 INSPECTION. -FIGURE 7CONDITION 3.3 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 7Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 3.4: NO CRACK FOUND AS A RESULT OF OP- TION 4 INSPECTION. -FIGURE 12Do the detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. CONDITION 4: FOUND NO MORE THAN ONE RADIUS FILLER AT ANY FREE FLANGE OF THE STRINGER. Do PART 4: CLOSE ACCESS. -CONDITION 4.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 4.1: ANY CRACK FOUND. -FIGURE 7CONDITION 4.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 7Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 4.2: NO CRACK FOUND. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 20 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 21 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. Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. Method of ComplianceActionCondition Do PART 1: OPEN ACCESS. -Do a General Visual Inspection (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. All Airplanes. -FIGURE 13 DO PART 2: LEFT SIDE RADIUS FILLER RE- MOVAL. -OPTION 5 (ACTION 1): Re- move radius fillers at each free flange of the stringer with two or more fastener locations. CONDITION 5: FOUND TWO OR MORE RADIUS FILLERS AT ANY FREE FLANGE OF THE STRINGER. -FIGURE 15OPTION 5 (ACTION 2): Do adetailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. -FIGURE 16OPTION 6: Do a detailed in- spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. Do PART 4: CLOSE ACCESS. -CONDITION 5.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 5.1: ANY CRACK FOUND AS A RESULT OF OP- TION 5 INSPECTION. -FIGURE 13CONDITION 5.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 17CONDITION 5.2 (ACTION 1): Install radius fillers. CONDITION 5.2: NO CRACK FOUND AS A RESULT OF OP- TION 5 INSPECTION. -FIGURE 13CONDITION 5.2 (ACTION 2):Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 21 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 22 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. Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. Method of ComplianceActionCondition Do PART 4: CLOSE ACCESS. -CONDITION 5.3 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 5.3: ANY CRACK FOUND AS A RESULT OF OP- TION 6 INSPECTION. -FIGURE 13CONDITION 5.3 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 13Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 5.4: NO CRACK FOUND AS A RESULT OF OP- TION 6 INSPECTION. -FIGURE 18Do the detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. CONDITION 6: FOUND NO MORE THAN ONE RADIUS FILLER AT ANY FREE FLANGE OF THE STRINGER. Do PART 4: CLOSE ACCESS. -CONDITION 6.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 6.1: ANY CRACK FOUND. -FIGURE 13CONDITION 6.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 13Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 6.2: NO CRACK FOUND. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 22 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 23 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. Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. Method of ComplianceActionCondition Do PART 1: OPEN ACCESS. -Do a General Visual Inspection (GVI) of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. All Airplanes. -FIGURE 19 DO PART 3: RIGHT SIDE RA- DIUS FILLER RE- MOVAL. -OPTION 7 (ACTION 1): Re- move radius fillers at each free flange of the stringer with two or more fastener locations. CONDITION 7: FOUND TWO OR MORE RADIUS FILLERS AT ANY FREE FLANGE OF THE STRINGER. -FIGURE 21OPTION 7 (ACTION 2): Do adetailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. -FIGURE 22OPTION 8: Do a detailed in- spection of the stringers and the stringer splice fitting within the profile of the stringer splice installation for any crack. Do PART 4: CLOSE ACCESS. -CONDITION 7.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 7.1: ANY CRACK FOUND AS A RESULT OF OP- TION 7 INSPECTION. -FIGURE 19CONDITION 7.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 23CONDITION 7.2 (ACTION 1): Install radius fillers. CONDITION 7.2: NO CRACK FOUND AS A RESULT OF OP- TION 7 INSPECTION. -FIGURE 19CONDITION 7.2 (ACTION 2):Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 23 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 24 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. Refer to the listed procedures in SB 747-53A2907 Original Issue or later approved re- visions as an ac- cepted proce- dure. Method of ComplianceActionCondition Do PART 4: CLOSE ACCESS. -CONDITION 7.3 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 7.3: ANY CRACK FOUND AS A RESULT OF OP- TION 8 INSPECTION. -FIGURE 19CONDITION 7.3 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 19Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 7.4: NO CRACK FOUND AS A RESULT OF OP- TION 8 INSPECTION. -FIGURE 24Do the detailed inspection of the stringers and the stringer splice fitting within the profile of the stringer splice installa- tion for any crack. CONDITION 8: FOUND NO MORE THAN ONE RADIUS FILLER AT ANY FREE FLANGE OF THE STRINGER. Do PART 4: CLOSE ACCESS. -CONDITION 8.1 (ACTION 1): Contact the Boeing Company for repair instructions and do the repair. CONDITION 8.1: ANY CRACK FOUND. -FIGURE 19CONDITION 8.1 (ACTION 2): Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. -FIGURE 19Do a GVI of each free flange of the stringers at the stringer splice for radius fillers at the fastener locations. CONDITION 8.2: NO CRACK FOUND. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 24 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 25 This Figure applies only to: Group 1. 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) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 25 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 26 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA STA 1960 1740 BL-0 - - 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-17L- S-16L 0000000000005510 - S-16L - S-17L S-18L - S-18L S-19L- -S-19L S-23L- - S-23L LEFT SIDE FWD MAIN ENTRY DOOR NO. 4 VIEW LOOKING UP AND OUTBOARD 2986725 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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 26 of 243 ### Page 27 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA 2180 STA 1960 BL-Ó 00000000 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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 27 of 243 ### Page 28 (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 00000000000000 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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 28 of 243 ### Page 29 (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 TYPICAI STRINGER SPLICE FITTING FWD STA STRINGER (3) (8 LOCATIONS) SKIN 1741.10 S-11L TYPICAL STRINGER 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 Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. ### Page 30 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT 8 LOCATIONS 4 1741 STA S-12L TYPICAL STRINGER A - FWD STRINGER SPLICE FITTING 5) 8 LOCATIONS STA STRINGER 1741.10 S-13L TYPICAL STRINGER FWD SPLICE FITTING STA 1741.10 ) 16 LOCATIONS STRINGER S-14l S-15L STRINGER YPICAL SPLICE FITTING -WD 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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 30 of 243 ### Page 31 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA 7) 12 LOCATIONS 1741.10 STRINGER A — S-16L STRINGER TYPICAL SPLICE FITTING K FWD STA 1960 STRINGER 8) 16 LOCATIONS S-1L S-2L S-3L TYPICAL STRINGER FWD SPLICE FITTING STA 1960 (9) 16 LOCATIONS STRINGER S-4L - TYPICAL STRINGER 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 7 OF 13) Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 31 of 243 ### Page 32 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA 16 LOCATIONS (10 1961.10 S-5L STRINGER FITTING STRINGER SPLICE TYPICAL FWD N STA 16 LOCATIONS (11 1960 S-6L S-7L •STRINGER STRINGER SPLICE FITTING TYPICAL STA 1960 STRINGER 12) 12 LOCATIONS A S-8L S-9L STRINGER SPLICE FITTING TYPICAI VD 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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 32 of 243 ### Page 33 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA 1960 (13) 12 LOCATIONS STRINGER A S-10L S-11L * *1 TYPICAL STRINGER SPLICE FITTING FWD 8 LOCATIONS 1 STA STRINGER 1960 S-12L STRINGER SPLICE FITTING TYPICAL R FWD STA 15) 16 LOCATIONS 2181.10 SKIN STRINGER TYPICAL S FWD FITTING STRINGER SPLICE 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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 33 of 243 ### Page 34 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT (16) 16 LOCATIONS STA SKIN STRINGER 2181.10 S-4L A → STRINGER SPLICE FITTING TYPICAL FWD 17) (12 LOCATIONS) STA 2181.10 SKIN Lit -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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 34 of 243 ### Page 35 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT 12 LOCATIONS (18 A — 2181.10 STA FITTING STRINGER SPLICE + S-TOL S-11L TYPICAL FWD STRINGER (19) 8 LOCATIONS STA FITTING STRINGER SPLICE 2181.10 S-12L • TYPICAL FWD STRINGER 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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 35 of 243 ### Page 36 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. More DataQtyIdentificationNameTaskStep (a)(b)(c)--STRINGERInspect1 (a)(b)(c)--STRINGERInspect2 (a)(b)(c)--STRINGERInspect3 (a)(b)(c)--STRINGERInspect4 (a)(b)(c)--STRINGERInspect5 (a)(b)(c)--STRINGERInspect6 (a)(b)(c)--STRINGERInspect7 (a)(b)(c)--STRINGERInspect8 (a)(b)(c)--STRINGERInspect9 (a)(b)(c)--STRINGERInspect10 (a)(b)(c)--STRINGERInspect11 (a)(b)(c)--STRINGERInspect12 (a)(b)(c)--STRINGERInspect13 (a)(b)(c)--STRINGERInspect14 (a)(b)(c)--STRINGERInspect15 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) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 36 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 37 More DataQtyIdentificationNameTaskStep (a)(b)(c)--STRINGERInspect16 (a)(b)(c)--STRINGERInspect17 (a)(b)(c)--STRINGERInspect18 (a)(b)(c)--STRINGERInspect19 (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) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 37 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 38 This Figure applies only to: Group 1. 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) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 38 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 39 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA STA 1960 1740 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 -122 -S-12L S-13L -S-13L S-14L - S-14L S-15L - S-15L S-17L S-16L - S-18L S-17L - S-16L S-18L S-19L - S-19L 00000000 10000 S-23L - S-23L LEFT SIDE FWD MAIN ENTRY DOOR NO. 4 VIEW LOOKING UP AND OUTBOARD INSPECTION AREA B 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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 39 of 243 ### Page 40 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) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 40 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 41 (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 -22 -S-4L S-5L -S-5L S-6L - S-6L S-7L -Z - 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 00000000 0000000 S-23L - S-23L VIEW LOOKING UP AND OUTBOARD INSPECTION 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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 41 of 243 ### Page 42 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT FRAME STA (TYPICAL) STRINGER (TYPICAL) END OF STRINGER SKIN MIRROR 023 END OF STRINGER SPLICE STRINGER SPLICE 12З END OF STRINGER SPLICE LEND STRINGER SPLICE INSPECTION AREA (TYPICAL) 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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 42 of 243 ### Page 43 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT MIRROR STRINGER SPLICE TYPICAL CRACK STRINGER STRINGER SPLICE STRINGER INSPECTION (TYPICAL) A-A STRINGER SKIN STRINGER SPLICE 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 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 43 of 243 ### Page 44 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. More DataQtyIdentificationNameTaskStep (a)(d)(e)--S-8L, STA 1740Inspect1 (a)(d)(e)--S-9L, STA 1740Inspect (a)(d)(e)--S-10L, STA 1740Inspect (a)(d)(e)--S-11L, STA 1740Inspect (a)(d)(e)--S-12L, STA 1740Inspect (a)(d)(e)--S-13L, STA 1740Inspect (a)(d)(e)--S-14L, STA 1740Inspect (a)(d)(e)--S-15L, STA 1740Inspect (a)(d)(e)--S-16L, STA 1740Inspect (b)(d)(e)--S-1L, STA 1960Inspect2 (b)(d)(e)--S-2L, STA 1960Inspect (b)(d)(e)--S-3L, STA 1960Inspect (b)(d)(e)--S-4L, STA 1960Inspect (b)(d)(e)--S-5L, STA 1960Inspect (b)(d)(e)--S-6L, STA 1960Inspect (b)(d)(e)--S-7L, STA 1960Inspect (b)(d)(e)--S-8L, STA 1960Inspect (b)(d)(e)--S-9L, STA 1960Inspect (b)(d)(e)--S-10L, STA 1960Inspect (b)(d)(e)--S-11L, STA 1960Inspect (b)(d)(e)--S-12L, STA 1960Inspect 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 7 OF 8) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 44 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 45 More DataQtyIdentificationNameTaskStep (c)(d)(e)--S-1L, STA 2180Inspect3 (c)(d)(e)--S-2L, STA 2180Inspect (c)(d)(e)--S-3L, STA 2180Inspect (c)(d)(e)--S-4L, STA 2180Inspect (c)(d)(e)--S-5L, STA 2180Inspect (c)(d)(e)--S-6L, STA 2180Inspect (c)(d)(e)--S-7L, STA 2180Inspect (c)(d)(e)--S-8L, STA 2180Inspect (c)(d)(e)--S-9L, STA 2180Inspect (c)(d)(e)--S-10L, STA 2180Inspect (c)(d)(e)--S-11L, STA 2180Inspect (c)(d)(e)--S-12L, STA 2180Inspect (a) Do a detailed inspection of the visible areas of affected stringers and the stringer splice fitting, forward and aft of STA 1740, for any crack. (b) Do a detailed inspection of the visible areas of affected stringers and the stringer splice fitting, forward and aft of STA 1960, for any crack. (c) Do a detailed inspection of the visible areas of affected stringers and the stringer splice fitting, forward and aft of STA 2180, for any crack. (d) Can be a production or repaired stringer splice. The stringer splices could have been repaired with or without radius fillers. (e) 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 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 8 OF 8) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 45 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 46 This Figure applies only to: Group 1. 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 (SHEET 1 OF 8) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 46 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 47 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA STA 1960 1740 BL-O S-IL — BL-O -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 -122 -S-12L S-13L -S-13L S-14L - S-14L S-15L - S-15L S-17L S-16L - S-18L S-17L - S-16L S-18L S-19L -S-19L 00000000 00000 S-23L - S-23L LEFT SIDE FWD MAIN ENTRY DOOR NO. 4 VIEW LOOKING UP AND OUTBOARD INSPECTION AREA B 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 (SHEET 2 OF 8) Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 47 of 243 ### Page 48 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 (SHEET 3 OF 8) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 48 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 49 (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 00000000 0000000 S-23L • S-23L VIEW LOOKING UP AND OUTBOARD INSPECTION 2984493 AREA 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 (SHEET 4 OF 8) Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 49 of 243 ### Page 50 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT FRAME STA (TYPICAL) STRINGER (TYPICAL) END OF STRINGER SKIN MIRROR B END OF STRINGER SPLICE STRINGER SPLICE (₴ 3) END OF STRINGER SPLICE [EWD STRINGER SPLICE INSPECTION AREA (TYPICAL) E DETAILED 2984494 INSPECTION 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 (SHEET 5 OF 8) Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 50 of 243 ### Page 51 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT MIRROR STRINGER SPLICE TYPICAL CRACK STRINGER STRINGER SPLICE RADIUS FILLERS STRINGER INSPECTION (TYPICAL) A-A STRINGER - SKIN • RADIUS FILLER STRINGER SPLICE NBD TYPICAL PRODUCTION OR REPAIR STRINGER SPLICE B-B 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 (SHEET 6 OF 8) Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 51 of 243 ### Page 52 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. More DataQtyIdentificationNameTaskStep (a)(d)(e)--S-8L, STA 1740Inspect1 (a)(d)(e)--S-9L, STA 1740Inspect (a)(d)(e)--S-10L, STA 1740Inspect (a)(d)(e)--S-11L, STA 1740Inspect (a)(d)(e)--S-12L, STA 1740Inspect (a)(d)(e)--S-13L, STA 1740Inspect (a)(d)(e)--S-14L, STA 1740Inspect (a)(d)(e)--S-15L, STA 1740Inspect (a)(d)(e)--S-16L, STA 1740Inspect (b)(d)(e)--S-1L, STA 1960Inspect2 (b)(d)(e)--S-2L, STA 1960Inspect (b)(d)(e)--S-3L, STA 1960Inspect (b)(d)(e)--S-4L, STA 1960Inspect (b)(d)(e)--S-5L, STA 1960Inspect (b)(d)(e)--S-6L, STA 1960Inspect (b)(d)(e)--S-7L, STA 1960Inspect (b)(d)(e)--S-8L, STA 1960Inspect (b)(d)(e)--S-9L, STA 1960Inspect (b)(d)(e)--S-10L, STA 1960Inspect (b)(d)(e)--S-11L, STA 1960Inspect (b)(d)(e)--S-12L, STA 1960Inspect 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 (SHEET 7 OF 8) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 52 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 53 More DataQtyIdentificationNameTaskStep (c)(d)(e)--S-1L, STA 2180Inspect3 (c)(d)(e)--S-2L, STA 2180Inspect (c)(d)(e)--S-3L, STA 2180Inspect (c)(d)(e)--S-4L, STA 2180Inspect (c)(d)(e)--S-5L, STA 2180Inspect (c)(d)(e)--S-6L, STA 2180Inspect (c)(d)(e)--S-7L, STA 2180Inspect (c)(d)(e)--S-8L, STA 2180Inspect (c)(d)(e)--S-9L, STA 2180Inspect (c)(d)(e)--S-10L, STA 2180Inspect (c)(d)(e)--S-11L, STA 2180Inspect (c)(d)(e)--S-12L, STA 2180Inspect (a) Do a detailed inspection of the visible areas of affected stringers and the stringer splice fitting, forward and aft of STA 1740, for any crack. (b) Do a detailed inspection of the visible areas of affected stringers and the stringer splice fitting, forward and aft of STA 1960, for any crack. (c) Do a detailed inspection of the visible areas of affected stringers and the stringer splice fitting, forward and aft of STA 2180, for any crack. (d) Can be a production or repaired stringer splice. The stringer splices could have been repaired with or without radius fillers. (e) 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 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 (SHEET 8 OF 8) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 53 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 54 This Figure applies only to: 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 (SHEET 1 OF 14) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: March 03, 2022 747-53A2907 RB 54 of 243 REQUIREMENTS BULLETIN 747-53A2907 ALERTALERT ### Page 55 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA STA 1960 1740 BL-0 - - 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 Q - S-10L S-11L - S-11L S-12L- H - S-12L S-13L S-14L R - S-14L - S-13L S-15L - - S-15L S-16L S-16L S-17L - - S-17L S-18L - S-18L S-19L K - S-19L 000000000 000000 S-23L - - S-23L LEFT SIDE FWD MAIN ENTRY DOOR NO. 4 VIEW LOOKING UP AND OUTBOARD 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 (SHEET 2 OF 14) Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 55 of 243 ### Page 56 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA 2180 STA 1960 BL-O D S-23L 2987426 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 (SHEET 3 OF 14) Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 56 of 243 ### Page 57 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA STA 2180 1960 BL-0 - --- 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 -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 00000000000000000 S-23L -S-23L FWD VIEW LOOKING UP AND OUTBOARD 2987428 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 (SHEET 4 OF 14) Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 57 of 243 ### Page 58 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA STRINGER 1) 8 LOCATIONS 1741.10 SKIN A - S-8L S-9L TYPICAL STRINGER SPLICE FITTING FWD STA STRINGER 2) 8 LOCATIONS 1741.10 SKIN S-10L TYPICAL STRINGER SPLICE FITTING FWD STA STRINGER 3) 8 LOCATIONS 1741.10 SKIN S-11l TYPICAL STRINGER SPLICE FITTING FWD 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 (SHEET 5 OF 14) Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 58 of 243 ### Page 59 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STRINGER 4) 8 LOCATIONS 1741 STA S-12L A - TYPICAL FWD STRINGER SPLICE FITTING STRINGER 5) 8 LOCATIONS 1741.10 STA A — S-13L TYPICAL STRINGER FWD SPLICE FITTING STA 1741.10 6) 16 LOCATIONS STRINGER S-14L S-15L STRINGER TYPICAL SPLICE FITTING 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 (SHEET 6 OF 14) Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 59 of 243 ### Page 60 (OCR) REQUIREMENTS BULLETIN 747-53A2907 ALERT ALERT STA 1741.10 STRINGER ) 12 LOCATIONS S-16L- STRINGER TYPICAL SPLICE FITTING K FWD STA 1960 STRINGER ) 16 LOCATIONS A - S-1L S-2L S-3L STRINGER TYPICAL SPLICE FITTING FWD STA 1960 STRINGER (9) 16 LOCATIONS S-4L - TYPICAL STRINGER SPLICE FITTING FWD 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 (SHEET 7 OF 14) Original Issue: March 03, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 747-53A2907 RB Copyright © Unpublished Work - See page 1 for details. 60 of 243 The text continues at https://openairdocs.org/service-documents/boeing/747-53a2907-rb/file/7f3f5b0471ec.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.