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 = 'LA4200' 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 = 'LA4200' 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 CA151124009Oil Filter · damaged(CAN) DURING THE ANNUAL INSPECTION THE OIL FILTER WAS REMOVED AND CUT OPEN FOR INSPECTION AND THE FILTER INTERIOR WAS FOUND TO BE BENT. THERE WAS NO DAMAGE TO THE EXTERNAL CAN OF THE FILTER, AND IT DID NOT APPEAR TO AFFECT THE FILTRATION OF THE OIL.SDR CA150604015Contact · loose(CAN) ENGINE WAS A RECENTLY REBUILT, FACTORY ENG WITH ABOUT 100 HOURS IN SERVICE. WHILE RUNNING UP THE ENG AFTER REFUELING, PERFORMED A MAGNETO DROP CHECK & THE ENG RAN ROUGH ON THE RT MAG. IT HAD BEEN OPERATING FINE UP UNTIL THIS TIME. THEN CHECKED THE TIMSDR 2013FA0000589Tube · crackedDURING ANNUAL INSPECTION, DISCOVERED A CIRCUMFERENTIAL CRACK WHERE AIRBOX OUTLET TUBE IS WELDED TO AIRBOX. CRACK EXTENDED AROUND .33 OF THE CIRCUMFERENCE OF THIS WELD.SDR CA111028007Pushrod · corroded(CAN) ALUM ROD WAS BEING REMOVED TO REPLACE SOME CORRODED BLIND FASTENERS AT THE LOWER END FITTING (FIXED-END, STEEL FITTING). WHEN IT WAS DISCOVERED THE ALUMINUM TUBE WAS CORRODED APPROX 45 PERCENT AROUND THE CIRCUMFRENCE OF THE ROD, AT THE END OF THE STEEL SDR CA110627002Engine · power loss(CAN) POWER LOSS DURING REPOSITIONING FLIGHT WHILE ON CRUISE MODE, CREW REPORTED ALL ENGINE PARAMETERS REDUCED. N1 WENT FROM 88 PERCENT TO APPROX 72 PERCENT. CREW DECIDED RETURNING TO DEPARTURE. DURING DESCENT, ENGINE BECAME MORE RESPONSIVE AND RESUMED NORMASDR CA100121001Control Cable · worn(CAN) THE AILERON CABLES ON LAKE ACFT, MODELS, LA-4, -200, -250 HAVE BEEN FOUND WEARING AT FUS STA 117 0N LA-4, 200`S AND FUS STA 176 ON LA-250 WRE THE CABLE CONTACTS THE PHENOLIC FAIRLEAD. THE WEAR OF THESE CABLES IS DEPICTED IN AC43.13-1B, CHAP. 7, PG7-36, FSDR 2006FA0000299Hinge · wornDURING ANNUAL INSPECTION FOUND ALTERNATE AIR VALVE HINGE WORN THRU. REMOVED HEAT BOX ASSY AND FOUND BOX CRACKED 50 PERCENT AROUND MOUNTING FLANGE. CRACK COULD NOT BE SEEN WITH BOX ON AIRCRAFT.SDR CA050908002Line · obstructed(CAN) NOSE GEAR FAILED TO LOCK DOWN DUE TO A PLUGGED RETURN LINE ORIFACE, ACTUATOR REMOVED/DISASSEMBLED/CLEANED/REASSEMBLED, REINSTALLED, HYDRAULIC SYSTEM FLUSHED, GEAR SWINGS COMPLETED. NO FAULTS FOUND.SDR CA050518009Transducer · leaking(CAN) A NEW FP5-L FUEL FLOW WAS INSTALLED AND LEAK TESTED ON FIRST FLIGHT. APPROX 20 MINUTES AND AIRCRAFT WAS LANDED AND PILOT REALIZED HE HAD AN ENGINE FIRE. AIRCRAFT IS TURBO CHARGED. FUEL FLOW TRANSDUCER LOCATION APPROX. 10 INCHES FROM COMPRESSOR SIDE OF TSDR 2004FA0000855Line · crackedDURING FLT, HYD PUMP STARTED TO CYCLE ABNORMALLY. IDENTIFIED HYDRAULIC PRESSURE LOSS TO LANDING GEAR RETRACT CIRCUIT AND ISOLATED WITH LDG GEAR SELECTOR. GEAR EXTENDED FOR LANDING NORMALLY. DURING POST INSPECTION FOR LEAK, LOCATED HYD TUBE AT AFT BULKHEAD STASDR AUS20040298Rod End · failed(AUS) RUDDER CONTROL ROD BALL JOINT SEIZED AND ROD END FAILED. THE SEIZED BALL JOINT ALLOWED THE CONTROL ROD END TO BEND UP AND DOWN DURING RUDDER APPLICATIONS UNTIL FINAL FAILURE.SDR 2003FA0000693Blade · brokenDURING NORMAL OPERATION, A PORTION OF BLADE TIP (P-TIP) BROKE OFF.SDR AUS20030788Rivet · corroded(AUS) ELEVATOR PUSHROD AFT END FITTING RIVETS CORRODED. END FITTING SEPARATED FROM PUSHROD CAUSING LOSS OF CONTROL CAUSING DAMAGE TO AIRCRAFT DURING HEAVY LANDING.SDR CA020826008Doubler · cracked(CAN) LT WING LOWER SPAR CAP DOUBLER CRACKED AT OUTER BOLT HOLE.SDR CA020827009Hub · corroded(CAN) CORROSION ON HUB IN O-RING SEAL AREA. BALL WEAR ON BLADE BEARING. CHROME WORN THRU TO BASE METAL ON PITCH CHANGE ROD.SDR CA011031021Attach Fitting · mismanufactured(CAN) AD 98-10-12, HORIZONTAL STAB ATTACHMENT FITTING NO OF NEW CUSTOMERS A/C HAVE BEEN INSPECTED AT COMPANY & ARE NOT IN COMPLIANCE WITH AD, ALTHOUGH ITS BEEN PREVIOUSLY SIGNED OFF. MOST INSPECTIONS REVEAL THAT CLEARANCE I S LESS THAN THE REQUIRED 5/32 INCH. SDR 2001FA0000066Pushrod · corrodedREMOVED FORWARD LOWER ROD END FROM RUDDER PUSHROD ASSEMBLY, DUE TO VISIBLE CORROSION. FOUND EXTENSIVE CORROSION INTERNALLY ON ARM AND ROD ASSEMBLY.SDR 20010409AP001Adapter · crackedFUEL SMELL IN CABIN, FUEL STAIN LEFT SIDE OF INTERNAL FUSELAGE AT AND BELOW ADAPTER. VISUALLY INSPECTED PART AND FOUND CRACK AT SUMP DRAIN VALVE FITTING. FUEL LEAKED INTO AND WAS STANDING IN THE HULL. LEAK DETECTED DURING REPAIR OF STRUCTURE IN THAT AREA.SDR 20000523SH002Piston · failedENGINE PISTON ON NR 4 CYLINDER HEAD SEPARATED FROM BASE BELOW THE OIL RING LAND. TWISTED ROD AND CAUSED ENGINE TO FAIL. ENGINE FAILURE ON CLIMB-OUT AT ABOUT 700 FEET AGL AT CLIMB POWER. ENGINE TT SN, 1,445 HOURS. (X)SDR 99ZZZX2546Air Box · crackedPILOT REPORTED THAT WiTH FULL THROTTLE AND THE WASTEGATE CLOSED, ENGINE HAD EXCESSIVELY LOW BOOST. (TURBO CHARGER INSTALLATION WAS AN AFTERMARKET INSTALLATION. ALSO, RECORDS WERE UNAVAILABLE AS OF THIS DATE TO DETERMINE AIRCRAFT TIMES, TURBO CHARGER STC, ETCSDR 99ZZZX964Fuel Filter · dirtyIN-FLIGHT, ENGINE STOPPAGE. PILOT EXPERIENCED ENGINE STOPPAGE IN-FLIGHT, SAW FUEL PRESSURE GAUGE REGISTERING ZERO. WHEN HE TURNED ON FUEL PUMP BOOST SWITCH, ENG RE-STARTED AND MADE A SAFE LANDING. UPON INVESTIGATION OF FUEL SYSTEM, FOUND THE FUEL FILTER DIRSDR CA981006015Hub · corroded(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE HUB CORRODED. THE SUBMITTER STATES THAT THE LAST CORROSION INSPECTION, WHICH WAS IN 1988, REQUIRED REWORK TO THE MAXIMUM LIMITS DUE TO THE LACK OF INSPECTION AT THE SCHEDULED TIME.SDR 98ZZZX4269Support · failedPILOT REPORTED NOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF. INSPECTION OF NOSE LANDING GEAR WHEEL WELL REVEALED BROKEN UPPER NOSE L/G SUPPORT ASSEMBLY. THIS PART IS THE VERY TOP SUPPORT TUBE THAT IS MOUNTED ACROSS THE WHEEL WELL. INSPECTION OF THE BROSDR 99ZZZX587Magneto · failedMAGNETO FAILED IN-FLIGHT. TROUBLESHOOTING REVEALED DISTRIBUTOR GEAR NOT TURNING. PAPER SHIM NEXT TO COIL HAD MIGRATED TOWARD GEAR AND CAUSED CATASTROPHIC FAILURE OF GEAR TEETH. ENGINE AND MAGS 50 HOURS SINCE OVERHAUL.SDR 98ZZZX3185Fitting · crackedWHILE C/W AD 98-10-12, THE FITTING REQUIRED REPLACEMENT PER PARA (A)(2). INSPECTION OF THIS FITTING PER REVO SB B-78 DISCLOSED A CRACK IN ADDITION TO CORROSION AND FRETTING. IT SHOULD BE NOTED EVEN AFTER REPLACEMENT OF AFFECTED FITTINGS, THE ACFT IN MOST CASSDR CA980519011Hub · lack of lube(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE PROPELLER HUB REAR BORE TO BE OVERSIZE. THE CONTROL FORK TO BE OVERSIZE. THE PISTON TO BE UNDERSIZE. THESE CONDITIONS ARE A RESULT OF LACK OF LUBRICATION. THE HUB HAD NOT BEEN GREASED.SDR CA980504011Blade · damaged(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BOTH PROPELLER BLADES WERE FOUND BADLY NICKED FROM FOD. FIELD REPAIRS WERE NOT MADE IN ACCORDANCE WITH THE HARTZELL MANUAL.SDR CA980325028Hub · corroded(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PROPELLER HUB WAS FOUND TO BE BADLY CORRODED IN THE O-RING AREA.SDR 97ZZZX4505Actuator Rod · failedAFTER TAKEOFF, MLG RETRACTED NORMALLY AND NLG REMAINED EXTENDED. LANDING GEAR WAS RE-EXTENDED AND A SAFE LANDING WAS MADE. MAINTENANCE INSP FOUND THE THREADED END OF NLG ACTUATOR ROD HAD BROKEN OFF ALLOWING NLG ACTUATOR TO HANG FREELY IN THE WHEELWELL. THESDR 97ZZZX4258Hose · omittedTHE 2-6050-27 HOSE CONNECTS THE ALTERNATOR COOLING PORT TO THE FLEXIBLE DUCT (SCAT HOSE) THAT BRINGS AIR FROM ABOVE ENGINE TO THE ALTERNATOR. THIS NON-CONDUCTIVE HOSE HAD BEEN OMITTED (AFTER ENGINE CHANGE) WHICH ALLOWED THE WIRE IN THE FLEX DUCT TO CHAFE ON ASDR 97ZZZX2594Hose Assy · misassemblyHYDRAULIC HOSE KIT ORDERED FROM LAKE FACTORY INSTALLED ON AIRCRAFT. TWO OUT OF SIX LANDING GEAR RETRACT HOSES LEAKED AT THE FITTINGS. UPON DISASSEMBLY OF HOSES, FOUND THE ENDS WERE IMPROPERLY INSTALLED. THE FERRULES WERE SCREWED ONTO THE HOSE ONLY ONE THREASDR CA970506007Blade · damaged(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. #1 PROPELLER BLADE HAD DAMAGE TO THE FACE SIDE DUE TO BOLT OR SCREW DAMAGE WHICH WAS NOT DRESSED OUT, WHEN PROPELLER WAS RECEIVED FOR INSPECTION.SDR EY2R9600152Blade · crackedBLADE SN D66432, CRACKED NEAR SHANK IN LIPSDR EY2R9600938Hub · corrodedHUB CORRODED.SDR 96ZZZX2031Actuator · failedNOSE GEAR ACTUATOR PISTON ASSY (ROD AND PISTON) RECEIVES A SIDE LOAD AT THE THREADED END OF ACTUATOR ROD. NOSE GEAR ACTUATES AT A VERY FAST RATE WHICH MAY CAUSE A 'BOUNCE' AT THE TRAVEL LIMIT WHICH BENDS AND CRACKS, AND ULTIMATELY BREAKS THE END OF THE ACTUATSDR 95ZZZX5769Bolt · failedONE LOWER ENGINE MOUNT BOLT BROKE IN-FLIGHT, CONDITION WAS DISCOVERED BY OWNER WHILE CHECKING OIL. ENGINE MOUNT SPACER WENT OUT THROUGH PROPELLER CAUSING SIGNIFICANT DAMAGE TO PROPELLER. WHEN MFG WAS ASKED, THEY SAID NEW BOLTS ARE NOW INSTALLED AND SENT 4 NSDR 95ZZZX3487Trunnion · corrodedANNUAL INSPECTION REVEALED SEVERE CORROSION INSIDE OF THE MLG TRUNNION TUBES (THE LANDING GEAR PIVOT TUBES EXTENDING FROM THE GEAR LEG FORWARD INTO THE LEADING EDGE). THE TUBES WERE REMOVED AND REPLACED WITH NEW TUBES. THE OLD TUBES WERE CUT IN TWO AND THE DSDR 95ZZZX220Breather · ice blockedAIRCRAFT DEPARTED INL ON A MINUS 9 DEGREE FAHRENHEIT DAY. OIL BREATHER PLUGGED WITH ICE, FRONT OIL SEAL BLEW OUT ALONG WITH ALL THE ENGINE OIL. AIRCRAFT WAS SUBSTANTIALLY DAMAGED DURING 'OFF-FIELD' LANDING. AD 64-17-05 IS NOT APPLICABLE BECAUSE BREATHER HASSDR 95ZZZX1005Breather · ice blockedAIRCRAFT DEPARTED INL ON A MINUS 9 DEGREES FAHRENHEIT DAY. OIL BREATHER PLUGGED WITH ICE, FRONT OIL SEAL BLOW-OUT ALONG WITH ALL THE ENGINE OIL. AIRCRAFT WAS SUBSTANTIALLY DAMAGED DURING 'OFF FIELD' LANDING. AD 64-17-05 IS NOT APPLICABLE BECAUSE BREATHER HA
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