# Boeing Alert Requirements Bulletin 757-53A0123 RB: No revision named, part 4 of 4 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2025-0012; AD 2025-11-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Requirements Bulletin 757-53A0123 RB](https://openairdocs.org/service-documents/boeing/757-53a0123-rb.md) - Title as filed: RB 757-53A0123 R0_Part4 - Pages: 6 - PDF: https://openairdocs.org/files/sha256/db/93/db93edf7f69c041a4de197ee006534da2e0853ce176c2e7b56fa3e8f27133e87 - Page: https://openairdocs.org/service-documents/boeing/757-53a0123-rb/file/db93edf7f69c ## 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 (OCR) REQUIREMENTS BULLETIN 757-53A0123 ALERT ALERT — S-13R INTERCOSTAL STRAP • SUPPORT FITTING • SKIN COVER PLATE FRAME INNER CHORD BEAR STRAP FRAME WEB FRAME OUTER CHORD INTERCOSTAL STRAP LOWER HINGE _LOWER HINGE FITTING CENTERLINE LOWER HINGE FLAP INTERCOSTAL STRAP • S-14R INBD (VIEW IN THE FORWARD DIRECTION) A-A OPEN-HOLE HFEC INSPECTION 3045726 FIGURE 23: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 LOWER HINGE FITTING - OPEN-HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION - LOCATION 9 (SHEET 2 OF 3) Original Issue: March 13, 2024 Export Controlled ECCN: 9E991 757-53A0123 RB See page 1 for details 173 of 178 ### Page 2 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 this figure. More DataQtyIdentificationNameTaskStep (a)1-FASTENERRemove / Keep1 (b)(c)(d)--FRAME WEBInspect2 (a) Refer to 757-200 SRM 51-40-02, 757-200CB SRM 51-40-02 or 757-300 SRM 51-40-02 as an accepted procedure. (b) Do an open-hole HFEC inspection of the frame web for any crack in accordance with 757 NDT Manual PART 6, 51-00-04, 757 NDT Manual PART 6, 51-00-11 or 757 NDT Manual Part 6, 51-00-16. (c) Insert the probe to a minimum depth of 0.30 inches to reach the entire thickness of the frame web, and to a maximum depth of 0.40 inches to avoid interfering with the nutplate. (d) Do the open-hole inspection from the aft side of the frame through the external access door or the hinge opening. FIGURE 23: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 LOWER HINGE FITTING - OPEN-HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION - LOCATION 9 (SHEET 3 OF 3) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: March 13, 2024 757-53A0123 RB 174 of 178 REQUIREMENTS BULLETIN 757-53A0123 ALERTALERT ### Page 3 (OCR) REQUIREMENTS BULLETIN 757-53A0123 ALERT ALERT STA STA 1640 1640 STA 1620 S-8R - S-9R S-10R S-11R LOWER S-13R HINGE INTERCOSTAL S-14R- • CO S-16R FLOOR S-17R - - A or B S-18R FWD S-19R - (VIEW IN THE OUTBOARD DIRECTION) A Or B 3045727 FIGURE 24: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 ABOVE S-19R - SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION - LOCATION 10 (SHEET 1 OF 4) Original Issue: March 13, 2024 Export Controlled ECCN: 9E991 757-53A0123 RB See page 1 for details 175 of 178 ### Page 4 (OCR) REQUIREMENTS BULLETIN 757-53A0123 ALERT ALERT FLOOR BEAM S-18R NUT SPACER PLATES MAY BE DIFFERENT FOR EACH AIRPLANE CONFIGURATION FRAME OUTER CHORD • FAILSAFE CHORD 1 S-19R FRAME INNER CHORD • BEAR STRAP • SKIN FRAME WEB S-20R INBD (VIEW IN THE FORWARD DIRECTION AT FRAME WITHOUT FRAME SEGMENT REPLACEMENT REPAIR) A-A / SURFACE HFEC INSPECTION 3045728 FIGURE 24: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 ABOVE S-19R - SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION - LOCATION 10 (SHEET 2 OF 4) Original Issue: March 13, 2024 Export Controlled ECCN: 9E991 757-53A0123 RB See page 1 for details 176 of 178 ### Page 5 (OCR) REQUIREMENTS BULLETIN 757-53A0123 ALERT ALERT FLOOR BEAM FRAME REPAIR ANGLE (NESTED S-18R INSIDE INNER CHORD) FRAME REPAIR DOUBLER FRAME OUTER CHORD NUT SPACER PLATES MAY BE DIFFERENT FOR FAILSAFE EACH AIRPLANE CHORD CONFIGURATION FRAME TRIM LINE S-19R FRAME INNER CHORD BEAR STRAP SKIN FRAME WEB FRAME REPAIR FILLER S-20R INBD (VIEW IN THE FORWARD DIRECTION AT FRAME WITH FRAME SEGMENT REPLACEMENT REPAIR) B-B SURFACE HFEC INSPECTION 3051222 FIGURE 24: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 ABOVE S-19R - SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION - LOCATION 10 (SHEET 3 OF 4) Original Issue: March 13, 2024 Export Controlled ECCN: 9E991 757-53A0123 RB See page 1 for details 177 of 178 ### Page 6 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 this figure. More DataQtyIdentificationNameTaskStep (a)--FRAME WEBInspect1 (a) Do a surface HFEC inspection of the frame web around the fastener for any crack in accordance with 757 NDT Manual Part 6, 51-00-19. FIGURE 24: RIGHT SIDE - FUSELAGE FRAME WEB AT STA 1640 ABOVE S-19R - SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION - LOCATION 10 (SHEET 4 OF 4) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: March 13, 2024 757-53A0123 RB 178 of 178 REQUIREMENTS BULLETIN 757-53A0123 ALERTALERT --- 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.