Boeing 747-2D7B
Service difficulty reports · 726
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Query with SQL
duckdb -csv -c "SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE aircraft_model_key = '7472D7B' ORDER BY difficulty_date DESC"
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 sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE aircraft_model_key = '7472D7B' ORDER BY difficulty_date DESC
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.
SDR UIEA201000062Frame · corrodedDURING C-CHECK, MAINTENANCE FOUND CORROSION IN THE 65B04331-165 AFT LOWER LOBE FRAME TEE CAP AT BS 1880, LBL 21-22. CORROSION WAS BLENDED AS PER FAA FORM 8100-9 DATED 04 FEB 2010 AND EO 4753B246.SDR UIEA201000061Skin · corrodedDURING C-CHECK, MAINTENANCE FOUND CORROSION IN THE SKIN LAP JOINTS BETWEEN BS 1700 AND 1960 AND S-40L. CORROSION WAS BLENDED AS PER FAA FORM 8100-9 DATED 05 FEB 2010 AND EO 4753B248.SDR UIEA201000060Frame · corrodedDURING C-CHECK, MAINTENANCE FOUND CORROSION ON THE FLANGE OF THE OUTER CHORD 65B10365-10 OF FRAME 1265 IS WHEEL WELL S-30 R-S-31R. CORROSION WAS BLENDED AS PER FAA FORM 8100-9 DATED 05 FEB 2010 AND EO 4753B245.SDR UIEA201000192Nozzle · crackedNR 4 ENG EXHAUST NOZZLE ASSY FOUND 3 LOCATIONS CRACKED AT FWD FLANGE AREA. NR 4 ENG EXHAUST ASSY 3 LOCATIONS CRACK REPAIR CARRIED OUT AS PER EM CF6-50 REPAIR O2 PROCEDURE B (1) AND EO 4778A148.SDR UIEA2010020400005Nozzle · crackedDURING AN ENGINE CHANGE AT AN A-CHECK, MX FOUND 3 EA CRACKS ON THE NR 4 ENG FIXED COWL EXHAUST NOZZLE FWD FLANGE COWL SUPPORT ASSY. THE CRACKS CAN BE REPAIRED IAW THE ESM TASK 78-33-05. REPAIR 002. THE REPAIR CALLS FOR A POST WELD HEAT TREATMENT AND THERMAL SPSDR UIEA201000154Skin · corrodedDURING C-CHECK, CORROSION WAS FOUND BETWEEN BS 2020 AND 2040 AT S-46L IN THE 65B04151-2 FUSELAGE SKIN. THE DENT WAS TRIMMED OUT AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-30-03, FIG 19. THE 65B04151-2 SKIN PANEL IS MADE FROM 0.063 INCH THICK 2024-T3 CLAD ASDR UIEA201000064Frame · crackedDURING C-CHECK, MAINTENANCE FOUND CRACKS IN THE 65B07415-5 FRAME WEB AT BS 720 BETWEEN S-42L AND S-44L. EFFECTED AREA WAS REMOVED AND REPAIRED AS PER EO 4753B243.SDR UIEA201000059Skin · corrodedDURING C-CHECK, MAINTENANCE FOUND LEVEL 2 CORROSION AT BS 1970 AT S46L IN THE 65B04151-2 FUSELAGE SKIN. AREA WAS TRIMMED OUT AND A REPAIR DOUBLER WAS INSTALLED AS PER EO 4753B244.SDR UIEA201000066Skin · corrodedDURING C-CHECK, MAINTENANCE FOUND CORROSION ON THE INTERSPAR SKIN AFT OF REAR SPAR. CORROSION WAS BLENDED OUT AS PER EO 4757A493 AND FAA 8100-9 DATED 1 FEB 2010.SDR UIEA201000058Structure · corrodedDURING C-CHECK, MAINTENANCE FOUND CORROSION BETWEEN BS 2020 AND 2040 AT S 46L. CORROSION WAS BLENDED OUT AS PER EO 4752B242.SDR UIEA201000001Escape Hatch · unsecurePASSING THROUGH 21,000' POPPING NOISE HEARD AND THEN LOUD NOISE OF RUSHING AIR FROM ESCAPE HATCH. RETURNED TO DEPARTURE. GROUND CHECKED REVEALED OVERHEAD ESCAPE HATCH NOT FULLY CLOSED. VISUALLY CHECKED AREA, ALL OK AND PERFORMED OPS CHECK AND DOOR CLOSED IASDR UIEA201000130Skin · delaminatedDURING LETTER "A" CHECK IN MIA, DELAMINATION WAS FOUND ON THE LEFT WING TRAILING EDGE AT WBL 208 UPPER EXTERNAL SKIN, RT LEADING EDGE ILES 760 UPPER EXTERNAL SKIN, AND RT LEADING EDGE ILES 672 GAP PANEL. ENGINEERING ORDER 4757A490 DATED 20 OCT 2009 WAS ISSUEDSDR UIEA200900054Actuator · failedAIR TURN BACK DUE TO RED GEAR LIGHT ILLUMINATED AFTER GEAR RETRACTION . F/E PANEL RIGHT WING GEAR DOOR OPEN ON BOTH PRIMARY AND ALTERNATE . AFTER FHB CHECK WITH GEAR EXTENDED LIGHTS EXTINGUISHED. RIGHT WING GEAR DOOR ACTUATOR REPLACED, GEAR SWING ACCOMPLISHEDSDR UIEA20090052Slide · unwanted deployDURING A-CHECK UPPER DECK RT DOOR SLIDE WAS ACCIDENTALLY DEPLOYED INSIDE THE ACFT BY MX PERSONNEL. SLIDE WAS NOT IN POSITION FOR NORMAL SUCCESSFUL DEPLOYMENT. SLIDE AND BOTTLE WAS REPLACED IAW AMM 25-68-02.SDR UIEA200900047Skin · crackedFUSELAGE SKIN RT SIDE ABOVE STABILIZER CUT-OUT AT STA 2589.5 TO 2598, SKIN MISSING CRACKED AND MISSING MATERIAL. PERMANENT REPAIR ACCOMPLISHED IAW SRM 53-30-03 FIG 1A. ALSO, REFERENCE EO 4753B229.SDR UIEA200900046Skin · puncturedRT WING INBD FLAP HAS 0.500 INCH DIAMETER PUNCTURED HOLE AT LWR SURFACE, WBL 188.30 AND 4.0 INCHES FROM L/E. PERMANENT REPAIR ACCOMPLISHED IAW SRM 51-40-09 FIG. 5, SHEETS 4 AND 8, 250* F CURE IAW SRM 51-40-12. REF: EO 4757A485.SDR UIEA200900045Pdu · unserviceableGROUND CREW REPORTED MAIN DECK PDU 15 R SMOKING DURING OFFLOAD. DEACTIVATED AND DEFERRED THE PDU. REPLACED DOWN LINE.SDR UIEA200900040Attach Fitting · crackedMAIN ENTRY DOOR NR 3 RT, FWD ATTACHMENT FOR SLIDE GIRT BAR, SUPPORT ATTACHMENT HAS A 0.625 INCH CRACK. INTERIM REPAIR WAS ACCOMPLISHED IAW SRM 51-10-01. REFERENCE EO4754A298 APPROVED VIA FAA 8110-3 FORM.SDR UIEA200900039Skin · delaminatedRT WING INBD MID FLAP UPPER SURFACE AT WBL 347.78 AND 22.0 INCHES FROM T/E HAS AN AREA OF 1.0 BY 1.0 INCH OF DELAMINATION. PERMANENT REPAIR ACCOMPLISHED IAW SRM 51-40-09, FIG. 5, SHEETS 3 AND 8. REF: EO 4757A484.SDR UIEA200900038Panel · crackedRT WING NR 3 PYLON UPPER SURFACE GAP PANEL HAS 2 EA COMPOSITE CRACKS. STA ILES 666.22 CRACK IS 24.0 INCHES LONG AND AT ILES 670.22 CRACK IS 12.0 INCHES LONG. PERMANENT REPAIR ACCOMPLISHED IAW SRM 51-40-09, FIG 18, SHEETS 2 AND 5, 250 DEGREE CURE IAW SRM 51-4SDR UIEA200900031Panel · delaminatedLT WING LEADING EDGE UPPER SURFACE FIXED PANEL A PREVIOUS REPAIR AT ILES 865.5 AND 18.0 INCHES FROM PANEL TRAILING EDGE, AN AREA OF 7.0 INCHES BY 11.0 INCHES IN DIAMETER IS DELAMINATED. PERMANENT REPAIR ACCOMPLISHED AS PER 747-200 SRM 51-40-09, FIG 18 SHEET 3SDR UIEA200900030Panel · delaminatedRT WING LEADING EDGE UPPER SURFACE FIXED PANEL A PREVIOUS REPAIR AT ILES 857.5 AND 13.0 INCHES FROM TRAILING EDGE, AN AREA OF 5.0 INCHES IN DIAMETER IS DELAMINATED. PERMANENT REPAIR ACCOMPLISHED AS PER 747-200 SRM 51-40-09, FIG 18 SHEET 3 AND 5. PREPREG 250 SDR UIEA200900029Panel · delaminatedRT WING LEADING EDGE UPPER SURFACE FIXED PANEL A PREVIOUS REPAIR AT ILES 897.5 AND 26.0 INCHES FROM PANEL TRAILING EDGE, AN AREA OF 6.0 INCHES IN DIAMETER IS DELAMINATED. PERMANENT REPAIR ACCOMPLISHED AS PER 747-200 SRM 51-40-09, FIG 18 SHEET 3 AND 5. PREPRESDR UIEA200900028Skin · dentedLT WING OUTBOARD AFT FLAP HAS A DENT ON TOP SURFACE SKIN. AT WBL 525.32 AND 14 INCHES FROM TRAILING EDGE. DENT IS 1.750 INCHES IN DIAMETER. PERMANENT REPAIR ACCOMPLISHED AS PER SRM 51-40-09, FIG 5, SHEETS 7 AND 8, 250 DEGREE CURE PER SRM 51-40-12. ALSO, RESDR UIEA201000182Nozzle · damagedPUNCTURE ON THE LONG FIXED CORE EXHAUST NOZZLE (LFCEN) ON THE NR 2 ENGINE. THE PUNCTURE IS APPROX 0.25" WIDE, APPROX 5.0 INCHES FROM THE T/E OF THE EXHAUST SLEEVE AT THE 3:00 POS. SMOOTH THE EDGES OUT USING STANDARD PRACTICES AND ELEMENTARY OPERATIONS. REPLACESDR UIEA201000183Skin · delaminatedRT INBD MID FLAP AT WBL 128.45 AND RT INBD AFT FLAP AT WBL 195.45 DAMAGED WITH DELAMINATION. INBD LOWER SURFACE DAMAGE MEASURES 4.0 IN X 4.0 IN. L/E LOWER SUFACE DAMAGE MEASURES 3.0 IN X 3.0 IN. "PERMANENT REPAIRS PERFORMED IAW THE SRM 51-41-09 FIG 6. TABLE I,SDR UIEA200900020Unknown · unknownDURING DESCENT ELECTRICAL ARCING WAS NOTICED IN THE CENTER CONSOLE NEAR TAWS AND GPS. INSPECTED ALL WIRING BEHIND CENTER CONSOLE. FOUND ALL SECURED. FOUND BLINKING LED LIGHT INSIDE TAWS INDICATOR. TAWS CHECKED OUT NORMAL THE BLINKING LIGHT WAS NORMAL. AIRSDR UIEA200900017Rod Bearing · brokenAIR TURN BACK - AFTER TAKEOFF AND GEAR RETRACTED THE RED GEAR DOOR LIGHT ON BOTH PRIMARY AND ALTERNATE ON ENGINEERS PANEL. BOTH TILT LIGHTS ON. GEAR EXTENDED DOWN AND LOCKED. DOOR OPEN LIGHT ON. FOUND RIGHT WING GEAR DOOR ACTUATOR ROD BROKEN, AND RIGHT WINSDR UIEA200900013Skin · damagedLT WING OUTBOARD FLAP, AFT FLAP INBOARD AFT CORNER FROM WBL 502.0 TO 515.0 HAS A GROUND DAMAGED AREA OF 5.5 BY 13.0 INCHES ON COMPOSITE SKIN. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09, FIG 5, SHEET 7 AND 8, 250 DEGREES F CURE PER SRM 51-40-12SDR UIEA200900012Panel · chafedLOWER CENTER WING PANEL SKIN HAS CHAFED MARKS FROM DELAMINATED NR 1 HEAT EXCHANGER HEADER DUCT DAMAGE AT BS 1078, LBL 42.0. TIME LIMITED REPAIR WAS ACCOMPLISHED AS PER SRM 57-30-1 FIG 2 AND EO O 4757A474. REQUIRES REPEAT INSPECTION AT EVERY 2 A-CHECKS UNTIL SDR UIEA200900011Panel · delaminatedRT WING UPPER SURFACE FIXED L/E PANEL AT ILES 332.0 AND 8.0 INCHES FROM AFT END OF PANEL HAS AN AREA OF 2.0 INCH DIAMETER OF DELAMINATION. PERMANENT REPAIR ACCOMPLISHED AS PER B747 SRM 51-40-09 FIG 18, SHEETS 3 AND 5, PREPREG 250 DEGREES F CURE PER SRM 51-40-SDR UIEA200900010Panel · delaminatedLT WING UPPER SURFACE FIXED L/E PANEL AT ILES 1048.0 AND 8.0 INCHES FROM AFT END OF PANEL HAS AN AREA OF 3.0 INCH DIAMETER OF DELAMINATION. PERMANENT REPAIR ACCOMPLISHED AS PER B747 SRM 51-40-09 FIG 18, SHEETS 3 AND 5, PREPREG 250 DEGREES F CURE PER SRM 51-40SDR UIEA200900009Skin · delaminatedLT WING UPPER SURFACE FIXED L/E PANEL AT ILES 921.5 AND 25.0 INCHES FROM AFT END OF PANEL HAS AN AREA OF 3.0 INCH DIAMETER OF DELAMINATION. PERMANENT REPAIR ACCOMPLISHED AS PER B747 SRM 51-40-09 FIG 18, SHEETS 3 AND 5, PREPREG 250 DEGREES F CURE PER SRM 51-40SDR UIEA200900008Panel · delaminatedRT WING UPPER SURFACE FIXED T/E PANEL AT WBL 445.0 JUST FWD OF INBD AILERON SMALL AREA OF DELAMINATION. AREA IS 3.5 BY 1.250 INCHES. PERMANENT REPAIR ACCOMPLISHED IAW SRM 51-40-09, FIG. 2 SHEET 2 AND 5, PREPREG LAYUP 250 DEGREES F CURE IAW SRM 51-40-12.
ALSO,SDR UIEA200800343Panel · crackedRT WING UPPER L/E PANEL HAS A 19 INCH COMPOSITE CRACK AT ILES 657.22, 5.0 INCHES FROM PANEL FRONT EDGE. PERMANENT REPAIR ACCOMPLISHED AS PER SRM 51-40-09 FIG 18, SHEETS 2 AND 5 AND SRM 51-40-12. REF ATLAS AIR EO 4757A467.SDR UIEA200800342Panel · delaminatedRT WING PREVIOUS REPAIR ON UPPER WING SURFACE L/E PANEL AN AREA OF 6.0 BY 38.0 INCHES IS DELAMINATED AT ILES 522.06 AND 7.5 INCHES FROM PANEL FRONT EDGE. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09 FIG 18, SHEETS 2, 5 AND SRM 51-40-12. REF. ATLSDR UIEA200800340Connector · defectiveAIR TURN BACK. NR 1 ENGINE OIL TEMP OFF SCALE HIGH FOR AT LEAST 10 MINUETS . ENGINE SHUT DOWN. WIRING CHECKS ACCOMPLISHED AND FOUND NR 1 OIL TEMP SENSOR CONNECTOR DEFECTIVE . CONNECTOR REPLACED AND ALL OPERATIONS NORMAL. ENGINE RUN UP NORMAL. NR 1 ENGINE OIL SDR UIEA200800336Computer · failedWHEN "A" AUTOPILOT ENGAGED AIRCRAFT STARTED UNCOMMANDED LEFT ROLL. DISENGAGED "A". "B" WOULD NOT ENGAGE. CYCLED YOKE SWITCHES AND YOKES NEITHER WOULD ENGAGE. FINALLY GOT "B" TO ENGAGE BUT IT WOULD NOT FOLOW ANY COMMANDS. REPLACED "A" CHANNEL CCA IAW 22-13-02. SDR UIEA200800332Autopilot Sys · malfunctionedAIR TURNBACK, WHEN A/P "A" IS ENGAGED THE AIRCRAFT STARTED UNCOMMANDED LEFT ROLL. DISENGAGED "A" A/P. "B" A/P WOULD NOT ENGAGE. CYCLED YOKE SWITCH NIETHER "A" OR "B" A/P WOULD ENGAGE. FINALLY GOT "B" TO ENGAGE BUT IT WOULD NOT FOLLOW ANY MODE CONTROL PANEL SDR UIEA200800323Skin · damagedFUSELAGE SCRIBE LINE OVERLAPPED SKIN BETWEEN BS 520-560 AT S34R DAMAGED. REPAIRED IN ACCORDANCE WITH SERVICE REQUEST 1-751139526 APPROVED BY FAA FORM 8100-9 DATED 02 OCT 2008, DETAILS OF WORK KEPT IN EO-4753B204 & EO-4753B114.SDR UIEA200800322Skin · damagedBS 740 TO 999.9 AT S6L/R LAP JOINT SCRIBE LINE DAMAGED. REPAIRED IN ACCORDANCE WITH SERVICE REQUEST 1-750626371 APPROVED BY FAA FORM 8100-9 DATED 2 OCT 2008, DETAILS OF WORK KEPT IN EO-473B205 & EO-4753B113.SDR UIEA200800320Skin · damagedFUSELAGE STA 520 TO STA 740 AT S-23L/R LAP JOINT SCRIBE LINE DAMAGED. REPAIRED IN ACCORDANCE WITH SERVICE REQUEST 1-750634474 APPROVED BY FAA FORM 8100-9 DATED 2 OCT 2008, DETAILS OF WORK KEPT AT EO-4753B203 & EO-4753B114.SDR UIEA200800321Skin · damagedBS 2181-2360 AT S12L/R LAP JOINT SCRIBE LINE DAMAGED. REPAIRED IN ACCORDANCE WITH SERVICE REQUEST 1-750626156 APPROVED BY FAA FORM 8100-9 DATED 30 SEP 2008, DETAILS OF WORK KEPT AT EO-4753B202 & EO-4753B114.SDR UIEA200800319Skin · damagedFUSELAGE STA 520 TO STA 740 AT S-23L/R LAP JOINT SCRIBE LINE DAMAGED. REPAIRED IN ACCORDANCE WITH SERVICE REQUEST 1-750634474 APPROVED BY FAA FORM 8100-9 DATED 2 OCT 2008, DETAILS OF WORK KEPT AT EO-4753B203 & EO-4753B114.SDR UIEA200800325Skin · damagedFUSELAGE SCRIBE LINE OVERLAPPED SKIN BETWEEN STA 670 TO 741 AT STR 34R DAMAGED. REPAIRED IAW BOEING SERVICE REQUEST 1-751139674 APPROVED BY FAA FORM 8100-9 DATED 26 SEP 2008. DETAILS OF WORK PERFORMED KEPT ON ATLAS ENGINEERING ORDER EO4753B207 AND EO4753B114SDR UIEA200800324Skin · damagedFUSELAGE STA 520 TO 740 AT STR 34L LAP JOINT SCRIBE LINE DAMAGE. REPAIRED IAW SERVICE REQUEST 1-963742727 APPROVED BY FAA FORM 8100-9 DATED 02 OCT 08 DETAILS OF WORK EO4753B206 & EO 4753B114.SDR UIEA200800318Autopilot Sys · malfunctionedATB BOTH AUTOPILOTS A AND B WILL NOT ENGAGE. BOTH TESTED OK ON GROUND. A/P A AND B PITCH AND ROLL COMPUTERS, FLIGHT CTL HYD PWR SHUT OFF SWITCHES ALL CHECKED IN ON POSITION. ACCESS BOXES INSTALLATION OCCURRED OK. MSP ELECT CONNECTORS INSPECTION NO FAULTS.SDR UIE2008F00042Skin · corrodedCENTER SECTION UPPER SKIN PANEL AT REAR SPAR LBL 100.0, LBL 108.65 CORROSION. REPAIRED IAW MFG SERVICE REQUEST 1-957658161 APPROVED BY FORM 8100-9 DATED 9 SEPT 2008, DETAILS OF WORK KEPT AT EO-4752A462. (K)SDR UIE2008F00041Frame · dentedBS 1740 FRAME BETWEEN S-12R AND S-13R DENT. REPAIRED IAW MFG SERVICE REQUEST 1-954640770 APPROVED BY FORM 8100-9 DATED 12 SEP 2008, DETAILS OF WORK KEPT AT EO -4753B201. (K)SDR UIE2008F00040Frame · dentedBS 1780 FRAME BETWEEN S-12R AND S-13R DENT. REPAIRED IAW MFG SERVICE REQUEST 1-954640956 APPROVED BY FORM 8100-9 DATED 12 SEPT 2008, DETAILS OF WORK KEPT AT EO 4753B201. (K)
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