# Boeing Service Bulletin A3515: U.S. DOT/FAA - Boeing Service Bulletin A3515, from page 37 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2011-1250; AD 2012-17-13 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Service Bulletin A3515](https://openairdocs.org/service-documents/boeing/a3515.md) - Title as filed: U.S. DOT/FAA - Boeing Service Bulletin A3515 - Pages: 41 - PDF: https://openairdocs.org/files/sha256/10/24/1024e89f4f72ffdcf6786513a656030160d50edaa87eac5651bfff1e7c5b6aad - Page: https://openairdocs.org/service-documents/boeing/a3515/file/1024e89f4f72 ## Text Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 37 FIGURE 3: HORIZONTAL STABILIZER - REAR SPAR - UPPER INBOARD CHORD - FORWARD SKIN FLANGE - STABILIZER STATION 92.55 TO STABILIZER STATION 182.55 - INSPECTION December 19, 2007 A3515 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 41 BOEING SERVICE BULLETIN A3515 ALERT ALERT FIGURE 3: HORIZONTAL STABILIZER - REAR SPAR - UPPER INBOARD CHORD - FORWARD SKIN FLANGE - STABILIZER STATION 92.55 TO STABILIZER STATION 182.55 - INSPECTION The step numbers shown below agree with the numbers shown in the circle symbols in the figure. STEP TASK NAME IDENTIFICATION QTY MORE DATA 1 Inspect Forward Skin Flange - 2 (a) (a) Do a Low Frequency Eddy Current (LFEC) inspection of the left and right side horizontal stabilizer rear spar upper inboard chord forward skin flange between stabilizer station 92.55 and 182.55 for any cracking. Refer to 707, 720 NDT, Part 6, 55-10-07, Figure 8 as an accepted procedure. A A BALANCE BAY PANEL NO.2FWD INBD UPPER CHORD REAR SPAR PANEL NO.3 BALANCE BAY RIGHT OPPOSITE LEFT HORIZONTAL STABILIZER UPPER SURFACE SHOWN, A-A 173.55 STAB STA 1 INSPAR SKIN 182.55 STAB STA UPPER 92.55 STAB STA 496279 (SHEET 1 OF 1) ### Page 38 FIGURE 4: HORIZONTAL STABILIZER - REAR SPAR - LOWER OUTBOARD CHORD - FORWARD SKIN FLANGE - STABILIZER STATION 182.55 TO STABILIZER STATION 272.55 - INSPECTION December 19, 2007 A3515 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 41 BOEING SERVICE BULLETIN A3515 ALERT ALERT FIGURE 4: HORIZONTAL STABILIZER - REAR SPAR - LOWER OUTBOARD CHORD - FORWARD SKIN FLANGE - STABILIZER STATION 182.55 TO STABILIZER STATION 272.55 - INSPECTION The step numbers shown below agree with the numbers shown in the circle symbols in the figure. STEP TASK NAME IDENTIFICATION QTY MORE DATA 1 Inspect Forward Skin Flange - 2 (a) (a) Do a Low Frequency Eddy Current (LFEC) inspection of the left and right side horizontal stabilizer rear spar lower outboard chord forward skin flange between stabilizer station 182.55 and 272.55 for any cracking. Refer to 707, 720 NDT, Part 6, 55-10-07, Figure 8 as an accepted procedure. A A FWD INBD LOWER CHORD REAR SPAR LEFT HORIZONTAL STABILIZER LOWER SURFACE SHOWN, RIGHT OPPOSITE A-A 1 LOWER INSPAR SKIN 182.55 STAB STA 263.55 STAB STA272.55STAB STA 496285 (SHEET 1 OF 1) ### Page 39 FIGURE 5: HORIZONTAL STABILIZER - REAR SPAR - LOWER INBOARD CHORD - FORWARD SKIN FLANGE - STABILIZER STATION 92.55 TO STABILIZER STATION 182.55 - INSPECTION December 19, 2007 A3515 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 41 BOEING SERVICE BULLETIN A3515 ALERT ALERT FIGURE 5: HORIZONTAL STABILIZER - REAR SPAR - LOWER INBOARD CHORD - FORWARD SKIN FLANGE - STABILIZER STATION 92.55 TO STABILIZER STATION 182.55 - INSPECTION The step numbers shown below agree with the numbers shown in the circle symbols in the figure. STEP TASK NAME IDENTIFICATION QTY MORE DATA 1 Inspect Forward Skin Flange - 2 (a) (b) (a) Do a Low Frequency Eddy Current (LFEC) inspection of the left and right side horizontal stabilizer rear spar lower inboard chord forward skin flange between stabilizer station 92.55 and 182.55 for any cracking. Refer to 707, 720 NDT, Part 6, 55-10-07, Figure 8 as an accepted procedure. (b) Exclude inspection of areas not accessible due to interference with any vortex generators mounted on the lower surface. However, if any cracks are found at any of the first six (6) inspectable fasteners on either side of the vortex generator, remove the vortex generator and inspect all fastener locations. A A LOWER CHORD REAR SPAR INBD FWD 1 LOWER INSPAR SKIN 92.55 STAB STA 173.55 STAB STA 182.55 STAB STA LEFT HORIZONTAL STABILIZER LOWER SURFACE SHOWN, A-A RIGHT OPPOSITE 496290 (SHEET 1 OF 1) ### Page 40 FIGURE 6: HORIZONTAL STABILIZER - REAR SPAR - LOWER INBOARD CHORD - FORWARD SKIN FLANGE - STABILIZER STATION -13.179 TO STABILIZER STATION 92.55 - INSPECTION December 19, 2007 A3515 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 41 BOEING SERVICE BULLETIN A3515 ALERT ALERT FIGURE 6: HORIZONTAL STABILIZER - REAR SPAR - LOWER INBOARD CHORD - FORWARD SKIN FLANGE - STABILIZER STATION -13.179 TO STABILIZER STATION 92.55 - INSPECTION The step numbers shown below agree with the numbers shown in the circle symbols in the figure. STEP TASK NAME IDENTIFICATION QTY MORE DATA 1 Inspect Forward Skin Flange - 2 (a) (b) (a) Do a Low Frequency Eddy Current (LFEC) inspection of the left and right side horizontal stabilizer rear spar lower inboard chord forward skin flange between stabilizer station -13.179 and 92.55 for any cracking. Refer to 707, 720 NDT, Part 6, 55-10-07, Figure 8 as an accepted procedure. (b) Exclude inspection of areas not accessible due to interference with any vortex generators mounted on the lower surface. However, if any cracks are found at any of the first six (6) inspectable fasteners on either side of the vortex generator, remove the vortex generator and inspect all fastener locations. A A LOWER CHORD REAR SPAR INBD FWD STAB STA -13.1791 STAB STA 92.55 LOWER INSPAR SKIN STAB STA 83.55 LEFT HORIZONTAL STABILIZER LOWER SURFACE SHOWN, A-A RIGHT OPPOSITE 496349 (SHEET 1 OF 1) ### Page 41 APPENDIX A: CONFIGURATION VERIFICATION - INSPECTION RESULTS FORM - MATERIAL DATA December 19, 2007 A3515 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 41 BOEING SERVICE BULLETIN A3515 ALERT ALERT APPENDIX A: CONFIGURATION VERIFICATION - INSPECTION RESULTS FORM - MATERIAL DATA AIRPLANE REGISTRY: FLIGHT HOURS: FLIGHT CYCLES: LEFT SIDE Horizontal Stabilizer Stabilizer Part Number (a): Stabilizer Serial Number (a): Spar Chord Segment Location Spar Chord Material (b): (from Part 2 - Configuration Check) Upper Inboard Side of Body to SSTA 182.55 Lower Inboard Side of Body to SSTA 182.55 Upper Outboard SSTA 182.55 to Stabilizer Tip Lower Outboard SSTA 182.55 to Stabilizer Tip RIGHT SIDE Horizontal Stabilizer Stabilizer Part Number (a): Stabilizer Serial Number (a): Spar Chord Segment Location Spar Chord Material (b) (from Part 2 - Configuration Check) Upper Inboard Side of Body to SSTA 182.55 Lower Inboard Side of Body to SSTA 182.55 Upper Outboard SSTA 182.55 to Stabilizer Tip Lower Outboard SSTA 182.55 to Stabilizer Tip (a) Record the horizontal stabilizer part number and serial number as recorded on the data plate. (b) Record spar chord material, 7079-T6 or 7075-T73511, as determined from maintenance record review, or electrical conductivity test. For the electrical conductivity test refer to 707 Non-Destructive Testing (NDT) Manual D6-48023 Part 6, 51-00-00, Figure 20, dated April 5, 2004, and Boeing Process Specification BAC5946, Table I, Page 12, Revision (AA) dated July 9, 2001. Comments: --- 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.