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 = '182A' 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 = '182A' 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 2021FA0000225Gascolator · broken7/31/2021: WINDS WERE OUT OF THE NORTH WEST. PLANNING TO CROSS SOUTH END OF THE RUNWAY TO ENTER LEFT DOWNWIND FOR RUNWAY 36. HAD DIPPED BELOW PATTERN ALTITUDE IN ORDER TO PULL UP AND LOSE AIRSPEED. THE ENGINE COMPLETELY DIED ABOUT 3/4 MILE EAST OF THE RUNWAY. SDR 2017FA0000424Hub · crackedPROPELLER WAS BROUGHT IN FOR REPAIR, DUE TO RED DYE LEAKAGE. DURING THE COURSE OF INSPECTION, A CRACK WAS FOUND. THE HUB IS CRACKED ON THE REAR SIDE OF BLADE SOCKET NR 1. ACFT ENG IS A O470-50 WITH A P PONK CONVERSION, STC SA02092SE, WHICH RAISES THE HORSEPSDR CA130903009Ring · damaged(CAN) WHILE TROUBLESHOOTING HIGH OIL CONSUMPTION AND LOW OIL PRESSURE, A SIGNIFICANT AMOUNT OF METAL WAS FOUND IN ENGINE OIL PRESSURE RELIEF VALVE. FURTHER INVESTIGATION REVEALED THAT 1 OF THE OIL RING SETS HAD A CENTER RETAINING SPRING THAT HAD FAILED AND WASDR CA120910012Piston · failed(CAN) ON APPROACH INTO FIRE LAKE, THE PILOT NOTICED CONSIDERABLE VIBRATION AND MECHANICAL KNOCKING NOISE. AFTER LANDING THE ENGINE WAS STILL RUNNING BUT WOULD VIBRATE QUITE BADLY OCCASIONALLY WITH THE ASSOCIATED KNOCKING NOISE. THE PILOT ELECTED TO SHUTDOWN SDR CA090424004Cable · frayed(CAN) FWD FLAP RETURN CABLE INSPECTED IN AREA UNDER PHENOLIC 1 INCH PULLEY AFT OF STN 44. FOUND ONE SHINY WEAR SPOT. ON REMOVAL DISCOVERED APPROX 7 WIRES BROKEN AT SHINY SPOT UNDER PULLEY AND APPROX 10 WIRES BROKEN AT FRAYED SPOT APPROX 2 INCHES FWD WHERE THE SDR 2007FA0000851Rod End · brokenROD END AT STEERING COLLAR SHEARED CAUSING LOSS OF DIRECTIONAL CONTROL.SDR 2007FA0000356Cylinder Head · separatedPERFORMED CYLINDER COMPRESSION TEST AND FOUND NR 1 CYLINDER READING 0 PSI AND FOUND LEAKING AROUND CYLINDER HEAD AND BARREL FINS. UPON REMOVAL THE HEAD IS COCKED SIDEWAYS ON THE BARREL. THE HEAD WAS SEPARATING FROM BARREL. THE CYLINDER PN FRCN68. OACA/01 CSDR 2007FA0000325Exhaust Pipe · brokenRT EXHAUST BROKE AT ELBOW, PART HAD BEEN REPAIRED 544 HRS AGO. DID NOT SHOW ANY CRACK 50 HRS EARLIER. DO NOT REPAIR EXHAUST PARTS THAT HAVE 1000 HRS ON THEM. (K)SDR 2006FA0001073Bracket · failedDURING LANDING ROLL OUT THE NOSE GEAR BEGAN TO SHIMMY UNTIL NOSE GEAR FAILURE. AN INSPECTION SHOWN, A FAILURE OF THE NOSE GEAR SHIMMY DAMPER BRACKET ON HOUSING. PART ORIGINAL TO 1958 INSTALLATION. (K)SDR 2006FA0000353Bulkhead · crackedBULKHEAD, PN 071220510, CRACKED AT TIE DOWN HOLE. BULKHEAD, PN 0712206, CRACKED AT BOLTHOLES ATTACHMENT TO ELEVATOR BELLCRANK SUPPORT MOUNT. (K)SDR 2006FA0000352Bulkhead · crackedBULKHEAD, PN 071220510, CRACKED AT TIE DOWN HOLE. BULKHEAD, PN 0712206 CRACKED AT BOLT HOLES ATTACHMENT TO ELEVATOR BELLCRANK SUPPORT MOUNT. (K)SDR 2004FA0000677Cylinder · crackedNR 3 CYLINDER CRACKED CIRCUMFERENTIALLY APPROXIMATELY 4 INCHES BELOW THE HEAD. THE RESULTANT VIBRATION MADE A PRECAUTIONARY LANDING PRUDENT. UPON REMOVAL AND INSPECTION, THE CRACK APPEARED TO VARY BETWEEN 0.060 INCH AND 0.030 INCH (APPROXIMATE) AS IT PROPAGASDR CA040708004Dowel Pin · missingPROPELLER INSTALLED AFTER OVERHAUL USING CESSNA MAINTENANCE MANUAL AS REFERENCE. AIR TEST AFTER INSTALLATION REFLECTS PROPELLER VIBRATION SHORTLY AFTER TAKEOFF. AIRCRAFT LANDED IMMEDIATELY. PROPELLER REMOVED. INSPECTED BY A-1 PROPELLER SERVICES. DETERMINESDR 2004FA0000641Cylinder · failedDURING ANNUAL INSP, CYLINDERS NR 1 AND NR 2 WERE FOUND TO HAVE A LOW COMPRESSION AND LEAKAGE PAST THE EXHAUST VALVE. ENGINE WAS STILL UNDER WARRANTY AND MFG WAS CONTACTED. MFG REP SUGGESTED TO READ SB03-3 WHICH SUPERSEDES SB84-15. SB03-3 SAYS ANY CYLINDER TSDR AUS20031308Brush Block · worn(AUS) ALTERNATOR BRUSHES WORN UNEVENLY. GROUND BRUSH WORN COMPLETELY AWAY WHILE THE POSITIVE BRUSH APPEARED IN NEAR NEW CONDITION.SDR AUS20020944Pump · worn(AUS) CARBURETTOR ACCELERATOR PUMP WORN AND BROKEN.SDR CA020731002Lead · intermittent(CAN) DURING RUN-UP AFTER ANNUAL INSPECTION LT MAGNETO GROUNDED OUT. INSPECTION FOUND "P" LEAD INTERMITTENT. ON FLEXING RT "P" LEAD IT WAS ALSO FOUND TO BE INTERMITTENT. FURTHER EXAMINATION DISCLOSED DETERIORATED INSULATION CLOSE TO ENTRY TO MAGNETOS ALLOWISDR CA010914002Casting · cracked(CAN) SUPPORT CASTING HAD CRACK FROM RADIUS OF CUTOUT FOR GEAR REARWARD. 0541153 U-BOLT WAS ALSO BROKEN AND REPLACED.SDR 20000619SH028Attach Fitting · crackedDURING ANNUAL INSP, LT SIDE HORIZONTAL STABILIZER ATTACH BRACKET WAS FOUND CRACKED NEXT TO A MOUNT BOLT. APPROX ONE YEAR PRIOR, THE HORIZ STAB HAD BEEN REBUILT. THE SPAR, STRINGERS, AND SKIN HAD BEEN REPLACED. VERY FEW OF THE ORIGINAL PARTS WERE RETURNED TOSDR 99ZZZX2511Housing · hole elongatedBOLT HOLE ELONGATED ON DRIVE-END OF FRAME, CESSNA KIT, AK210-54D. BOLT WAS NOT TIGHTENED ENOUGH AND ALLOWED MOVEMENT OF DRIVE-END FRAME. ENGINE VIBRATION CAUSED FRAME TO MOVE AND ELONGATE HOLE BY .1250 INCH PLUS. DRIVE-END FRAME WAS WORN AWAY WEAKENING FRASDR 98ZZZX2688Oil Filter · defectiveOUTLET TUBE HAS BURRS ON INSIDE SURFACE FROM MACHINING OPERATION. BURRS ARE HAIR-LIKE AND EASILY DETACHED. FILTER INSPECTED PRIOR TO INSTALLATION AND NOT USED. BURR APPEARS TO HAVE BEEN CAUSED WHEN CUTTING TOOL WAS RETRACTED. TOOKMARK CONTAINING BURRS IS ONSDR AU980642Bracket · broken(AUS) ENGINE INDUCTION SYSTEM BALANCE TUBE SUPPORT BRACKET BROKEN. ENGINE BACKFIRE CAUSED BALANCE TUBE TO COME OUT OF RUBBERS.SDR AU971397Support · cracked(AUS) LANDING GEAR SUPPORT CRACKED.SDR AU970139Cowling · damaged(AUS) UNSECURED AND UNATTACHED UPPER AND LOWER ENGINE COWLINGS PICKED UP BY A GUST OF WIND AND BLOWN INTO PROPELLER ARC DURING ENGINE GROUND RUN - DAMAGE TO PROPELLER BLADES AND DESTRUCTION OF COWLS- ENGINE BULK STRIP TO BE CARRIED OUTSDR CA961011003Oil Sump · cracked(CAN) OIL LEAK AT OIL SUMP. RETORQUE OF SUMP BOLTS MADE LEAK WORSE. REMOVAL OF OIL SUMP REVEALED CRACK AT MOUNTING FLANGE. THE AIRCRAFT IS USED TO TOW GLIDERS OFF GRASS STRIP AND THIS NO DOUBT CONTRIBUTED TO THIS FAILURE.SDR CA960826018Hose Fitting · cracked(CAN) DURING INSPECTION OF THE VACUUM HOSE FITTING. THE "B" NUT WAS FOUND CRACKED. SUBMITTER SUSPECTS THAT AN OVERTORQUING OF THE NUT TOOK PLACE.SDR 96ZZZX4874Battery · splitREMOVED BATTERY FOR REPLACEMENT DURING SCHEDULED MAINTENANCE AND FOUND BATTERY PACK HAD SPLIT AND EMITTING ACID. SPLIT WAS ALONG NARROW SIDE, RUNNING APPROXIMATELY 1.50 INCH. SUSPECT CAUSE APPEARED TO BE POOR EPOXY SURROUNDING BATTERY PACK.SDR 96ZZZX4813Float Assy · detachedCARBURETOR WAS REMOVED AT ANNUAL INSPECTION FOR EXCESSIVE WEAR ON THROTTLE SHAFT. UPON DISASSEMBLY, ONE OF THE FLOATS WAS FOUND BROKEN FROM THE ACTUATING ARM. IT WAS NOT RUPTURED OR WORN THROUGH. FLOAT WAS DATE CODED 4-84. SUSPECT A ROUGH RUNNING ENGINE ANSDR 96ZZZX2788U-Bolt · shearedDURING ROUTINE INSPECTION, RT MAIN LANDING GEAR U-BOLT WAS FOUND SHEARED AT AFT END. THIS MAY BE DUE TO PARACHUTISTS STANDING ON RT MAIN GEAR PRIOR TO DEPARTURE FROM AIRCRAFT.SDR 96ZZZX1282Support · elongated holesDURING ANNUAL INSPECTION, FOUND RT AILERON BELLCRANK BOLT HOLES ON THE SUPPORT CHANNELS TO BE ELONGATED. ONLY THE PIVOT HOLES WERE BAD, NOT THE STOP-PIN HOLES. SUSPECT CAUSED BY NOT INSTALLING CONTROL LOCK WHEN ACFT ON GROUND.SDR 96ZZZX1281Support · elongated holesDURING ANNUAL INSPECTION, FOUND RT AILERON BELLCRANK BOLT HOLES ON THE SUPPORT CHANNELS TO BE ELONGATED. ONLY THE PIVOT HOLES WERE BAD, NOT THE STOP-PIN HOLES. SUSPECT CAUSED BY NOT INSTALLING CONTROL LOCK WHEN ACFT ON GROUND.SDR 96ZZZX180Valve Guide · wornFOUND CYLINDER COMPRESSION AT 40/80. REMOVED CYLINDER AND FOUND EXHAUST VALVE GUIDE WORN OVER LIMITS. EXHAUST VALVE IN GUIDE CLEARANCE AS MEASURED IS 0.016 INCH. SERVICEABLE LIMITS ARE 0.006 INCH.SDR 95ZZZX634Fuel Cap · failedFUEL CAP FAILURE, RETAINING TAB, BROKE AFTER LESS THAN ONE HOUR IN SERVICE. PART RETURNED TO CESSNA FOR INSPECTION. THIS FAILURE LED TO THE LOSS OF FUEL IN THE TANK DURING FLIGHT.
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