Text
From the PDF’s text layer: layout, tables and figures are lost. The PDF is the document.
Query with SQL
duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = '1024e89f4f72ffdcf6786513a656030160d50edaa87eac5651bfff1e7c5b6aad' ORDER BY p.page"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = '1024e89f4f72ffdcf6786513a656030160d50edaa87eac5651bfff1e7c5b6aad' ORDER BY p.page
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
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STATION 92.55 TO STABILIZER STATION 182.55 - INSPECTION December 19, 2007 A3515 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 41 BOEING SERVICE BULLETIN A3515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)
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STATION 182.55 TO STABILIZER STATION 272.55 - INSPECTION December 19, 2007 A3515 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 41 BOEING SERVICE BULLETIN A3515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)
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)
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)
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: