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 = '441' 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 = '441' 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 CA021202002Gps · intermittent(CAN) GPS FUNCTION FAILS INTERMITTENTLY.SDR AUS20020792Valve · failed(AUS) RT ENGINE PRIMARY FUEL SOLENOID VALVE FAULTY. INVESTIGATION FOUND THE OPERATING COIL SHORT CIRCUITED TO EARTH.SDR CA020719002Dial · mismarked(CAN) THE ALTIMETER DIAL MARKED IN HG AND THE BARO SCALE SUB DIAL IS IN MB.SDR CA020611001Wire Harness · chafed(CAN) DURING INSPECTION AND COMPLYING WITH AD 2002-09-13 AND CESSNA SERVICE BULLITEN CQB02-1 REV. 1, FOUND THAT THE BLACK WIRE IN THE HARNESS WAS CHAFED THROUGH AND ARCING TO GROUND ON THE FUEL PUMP SHROUD. THE OTHER WIRES IN THE HARNESS WERE ALSO CHAFED, BUSDR AUS20020577Pump · failed(AUS) LT ENGINE TORQUE FLUCTUATIONS. METAL CONTAMINATION OF OIL FILTER AND CHIP DETECTOR. SUSPECT CAUSED BY FAILURE OF OIL SCAVENGE PUMP.SDR CA020612002Hose · chafed(CAN) HYDRAULIC FLUID LEAK, FROM BELLY THE MAIN LANDING GEAR RETRACTION LINE WAS RUBBING AGAINST A SCREW, THAT WAS HOLDING TWO CLAMPS AROUND TWO OTHER HYDRAULIC LINES UNDER THE RELAY BOX IN THE BELLY.SDR AUS20020530Wire Harness · chafed(AUS) FUEL BOOST PUMP WIRING HARNESSES CHAFED. FOUND DURING INSPECTION IAW AD/CESSNA400/111 (SB CQB02-1R1).SDR AUS20020464Harness · worn(AUS) LT FUEL BOOST PUMP WIRING HARNESS CHAFED. FOUND DURING INSPECTION IAW SB CQB02-1.SDR AUS20020453Fastener · misinstalled(AUS) CHERRY RIVETS IN FUSELAGE EMERGENCY EXIT DOOR CUTOUT FRAMEPREVENTING OPERATION OF EMERGENCY EXIT.SDR AUS20020408Harness · chafed(AUS) LT FUEL TANK HARNESS WIRE CHAFFED BUT WITHIN ACCEPTABLE LIMITS OF SB CQB02-1. HARNESS MODIFIED IAW SB AND REINSTALLED.SDR AUS20020409Harness · chafed(AUS) RT FUEL TANK HARNESS WIRE CHAFED BUT WITHIN ACCEPTABLE LIMITS OF SB CQB02-1. HARNESS MODIFIED IAW SB AND REINSTALLED.SDR PAZ2002F00001Wire · chafedFOUND WIRING TO RIGHT AUXILIARY BOOST PUMP CHAFING ON BOOST PUMP HOUSING AND DAMAGING THE INSULATION OF THE WIRING. FABRICATE A SHEATH FOR THE WIRE BUNDLE TO PROTECT IT FROM CHAFFING DAMAGE.SDR AUS20020288Trunnion · cracked(AUS) NLG TRUNNION CRACKED. FOUND DURING INSPECTION IAW SBCQB00-3.SDR AUS20020323Pump · cracked(AUS) LT ENGINE OIL PRESSURE PUMP CRACKED.SDR 441M032002Wire · chafedWIRING FOR FUEL BOOST PUMPS IN EACH WING WERE CHAFED THROUGH TO CONDUCTOR. WIRING HARNESS HAS TWO CONNECTOR PLUGS, ONE TO EACH BOOST PUMP. CONNECTOR PLUGS ARE WIRED TO A THIRD, LARGER PLUG THAT CONNECTS TO BULKHEAD PLUG THAT FEEDS THROUGH INBOARD MOST RIB IN SDR DEBA2624DWire Harness · chafedFUEL BOOST PUMP WIRING IN THE WET WING AREA OF EACH WING, WAS CHAFED THROUGH THE INSULATION TO THE CENTER CONDUCTOR. THE WIRING, WHERE IT EXITS THE FEED THROUGH CONNETOR PLUG, INTO THE WET WING, AT THE INBOARD MOST RIB, IS CHAFING ON THE BOX THAT SURROUNDS THESDR 441MWire Harness · chafedFOUND CHAFED WIRE THAT HAD BEEN ARCING ON THE BOX THAT SURROUNDS THE BOOST PUMPS TO KEEP THE FUEL IN THE FUEL HOPPER. ABOUT SIX INCHES FROM WHERE THE BOOST PUMP, CONNECTOR PLUG ENTERS THE INBOARD RIB OF THE WET WING AREA, A WIRE (THE RED WIRE) HAD BEEN CHAFINGSDR AUS20020263Pushrod · cracked(AUS) LT AILERON TRIM TAB PUSH ROD AFT ROD END CRACKED ACROSS BEARING RETAINER. RODEND BEARING CORRODED. CRACK FOUND WHEN PUSHROD WAS REMOVED FOR REPLACEMENT DUE TO WEAR.SDR 2002FA0000335Ammeter · blew outN442HA A CESSNA 441 WAS DECENDING THROUGH APPROX. 12000 FT WHEN THE PROPELLER DE-ICE AMP METER EXPLODED SENDING BROKEN GLASS INTO THE PILOT FACE JUST MISSING HIS EYES. PRIOR TO THE FAILURE THE PILOT HAD SELECTED THE PROPELLER DE-ICE SYSTEM TO THE ON POSITION. SDR AUS20020168Spar · delaminated(AUS) LT AND RT AFT SPAR WEBS DELAMINATED.SDR AUS20020195Spar · delaminated(AUS) LT WING REAR SPAR WEB DELAMINATED IN THREE AREAS.SDR AUS20020167Spar · delaminated(AUS) LT AND RT AFT SPAR WEBS DELAMINATED.SDR 2002FA0000398Wire · chafedFOUND RT WING AUXILLARY BOOST PUMP WIRING, CHAFING ON BOOST PUMP HOUSING CAUSING AN ELECTRICAL ARCING INSIDE OF FUEL BAY.SDR AUS20020138Hook · cracked(AUS) MAIN LANDING GEAR UPLOCK HOOK CRACKED.SDR AUS20020071Spar Cap · corroded(AUS) WING SPAR CAP CONTAINED EXFOLIATION CORROSION.SDR 2002FA0000211Pin · crackedDUE TO PIN FAILURE ON AIRCRAFT, PINS WERE REMOVED FOR INSPECTION AND THE LEFT TO THE POINT OF FAILURE . THE FORWARD PIN ON THE RIGHT SIDE WAS INTACT BUT SHOWING SIGNS OF SHEARING. ALL FOUR MAIN LANDING GEAR PIVOT SLOTTED PINS WERE REPLACED WITH NEW NAS561P62SDR AUS20020043Bearing · failed(AUS) LT OUTBOARD FLAP INBOARD BELLCRANK BEARING HAD EXCESSIVE PLAY. SUSPECT CAUSED BY WATER INGRESS.SDR 2002FA0000129Rib · crackedDURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE RIGHT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-2 (RCWS 26.85) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45) AND EXTENDING APPROXIMATELY 1.5 INCH AFT OF THE SPAR. AFTERSDR 2002FA0000128Rib · crackedDURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE LEFT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-1 (LCWS 26.85) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45) AND EXTENDING APPROXIMATELY 1.5 INCH AFT OF THE SPAR. AFTER SDR CA030312013Skin · delaminated(CAN) THE LT INBOARD FLAP WAS DISCOVERED PARTIALLY SEPARATED ON THE TOP SURFACE OF THE COMPOSITE STRUCTURE WHERE A NON CONFORMANT REPAIR (AS INDICATED IN THE APPLICABLE MANUAL) WAS CARRIED OUT. THIS REPAIR SEEMS TO HAVE BEEN DONE WITHOUT ANY DOCUMENTATION.THESDR AUS20020027Hose · restricted(AUS) RT ENGINE OIL COOLER SCAVENGE HOSE INTERNALLY RESTRICTED. SUSPECT HOSE COULD HAVE BEEN KINKED DURING ENGINE INSTALLATION.SDR AUS20020026Limiter · failed(AUS) DURING ENGINE EMERGENCY SHUTDOWN THE NR 2 ELECTRICAL SYSTEM BUS LIMITERS (225A) FAILED.SDR 2002FA0000127Rib · crackedDURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE RIGHT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-2 (RCWS 26.85) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45) AND EXTENDING APPROXIMATELY 1 INCH AFT OF THE SPAR. AFTER RSDR 2002FA0000126Rib · crackedDURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE LEFT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-1 (LCWS 26.85 INCHES) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45 ) AND EXTENDING APPROXIMATELY 1 INCH AFT OF THE SPAR. SDR VE72002F00002Pin · shearedPREFLIGHT INSPECTION FOUND LANDING GEAR PIVOT PIN BACKED OUT OF TRUNION DUE TO SLOTTED PIN BEING SHEARED. SAFETY WIRE USED TO RETAIN PIN WAS ALSO SHEARED BUT DUE TO ITS LENGTH AND DIAMETER. IT STAYED IN THE TRUNION GIVING THE IMPRESSION THAT IT WAS SECURE. SDR VE72002F00001Pin · shearedDUE TO SLOTTED PIN FAILURE OF THE OTHER GEAR THIS PIN WAS INSPECTED AND FOUND TO BE PARTIALLY SHEARED. PIN WAS REPLACED WITH NEW NAS561P628 PIN. THE AFT TRUNION SLOTTED PINS ON BOTH MAIN GEAR WERE INSPECTED WITH NO DEFECTS NOTED BUT WERE REPLACED WITH NEW. SDR VE72002F00000Pin · shearedDUE TO SLOTTED PIN FAILURE OF 4410175 THIS AIRCRAFT WAS INSPECTED AND FOUND TO HAVE BOTH FORWARD SLOTTED PINS ON THE MAIN LANDING GEAR TRUNION PIVOT PINS PARTIALLY SHEARED. PINS LOCATED ON FORWARD POSITION LEFT AND RIGHT MAIN LANDING GEAR TRUNNION.SDR LAT2002F00000Starter Gen · shortedCOWLING OF AIRCRAFT FOUND WITH EXCESSIVE CARBON CONTAMINATION. REMOVED STARTER GENERATOR. TEARDOWN REPORT REVEALED THE STARTER SHORTED. CAUSE UNKNOWN.SDR AUS20011439Housing · cracked(AUS) ENGINE OIL PUMP HOUSING CRACKED.SDR AUS20011361Hook · failed(AUS) LT MAIN LANDING GEAR UPLOCK HOOK FAILED AT PIVOT POINT.SDR AUS20011384Exhaust Stack · cracked(AUS) ENGINE EXHAUST DUCT CRACKED AT AFT FLANGE ATTACHMENT WELD.SDR AUS20011224Housing · cracked(AUS) ENGINE OIL PUMP HOUSING CRACKED.SDR 2001FA0000544Rib · crackedDURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE RIGHT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-2 (RCSW 26.85) HAD A VISUALLY SUSPECT AREA ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45). FURTHER INSPECTION USING FLUORESCENT PENETSDR 2001FA0000543Rib · crackedDURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE LEFT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-1 (LCWS 26.85) HAD A VISUALLY SUSPECT AREA ALONG THE BEND RADIUS BETWEEN THE CENTER WING MAIN SPAR (FS 177.45) AND FS 188.95. FURTHER INSPECTION USING FLUSDR AUS20011135Bearing · failed(AUS) STARTER-GENERATOR BEARINGS FAILED.SDR AUS20011113Door Frame · cracked(AUS) LOWER CABIN DOOR FRAME CRACKED IN AREA ADJACENT TO AFT HINGEPOINT.SDR AUS20011049Circuit Breaker · failed(AUS) NR 1 AVIONICS SWITCH / CIRCUIT BREAKER FAILED INTERNALLY. SUSPECT CAUSED BY RAIN WATER CORROSION DUE TO LOCATION OF CIRCUIT BREAKER BELOW THE LT OPENING WINDOW.SDR CA011003016Valve · failed(CAN) DURING AIRCRAFT CLIMB, THE EMERGENCY PRESSURIZATION VALVE OPENED ALLOWING UNCONDITIONAL BLEED AIR INTO THE CABIN. CABIN TEMPERATURE INCREASED AT AN UNCONTROLED RATE. AIRCRAFT RETURNED TO THE AIRPORT FROM WHICH IT DEPARTED. THE EMERGENCY PRESSURIZATION VASDR CA010830007Starter Gen · failed(CAN) PILOT WAS TAXING WHEN HE LOST TOTAL POWER TO NO. 2 BUS. INVESTIGATION FOUND THAT THE R/H GENERATOR COOLING FAN BLADES TOTALLY CRACKED OFF AND FLEW INTO THE GENERATOR WINDINGS, DESTROYING ALL WORKING CAPABLITY OF STARTER GENERATOR. THIS CAUSED A GCU FAILSDR 2001FA0000365Screw · looseEXCESS FRICTION IN PITCH, (ELEVATOR) CONTROL. DISASSEMBLY OF CONTROL, REVEALED RETAINING SCREW HAD BACKED OUT OF NYLON SLIDE. UNCONTAINED PARTS OCCASSIONALLY POSITIONED THEMSELVES THROUGH OUT NORMAL MOTION OF THE CONTROL SO AS TO CREATE EXCESS FRICTION. (M)
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