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 97ZZZX5045Hinge · crackedWHILE AIRCRAFT WAS UNDERGOING A SCHEDULED INSPECTION, NOTED THE RIVETS IN THE THE AFT LOWER CABIN DOOR HINGE APPEARED TO BE LOOSE. FURTHER VISUAL AND EDDY CURRENT INSPECTION SHOWED THE HINGE WAS CRACKED AT ALL THREE RIVET LOCATIONS. THE RIVETS HAD BEEN INSTASDR CA971219002Valve · failed(CAN) INTERNAL WIRING OF SOLENOID ON FLOW LIMITING VALVE FAILED, CAUSING VALVE TO REMAIN IN MAX FLOW POSITION.SDR CA971222003Transducer · failed(CAN) TRANSDUCER GAVE INCORRECT SIGNAL TO ENGINE COMPUTER-CAUSING SRL TO BE INCORRECT. THE ERROR WAS GREATER AS THE AIRCRAFT CLIMBED. THUS; TORQUE, FUEL FLOW, AND EGT DID NOT MATCH THE OTHER ENGINE AS THE AIRCRAFT CLIMBED. THIS IS THE P/P TRANSDUCER.SDR CA971222002Fuel Pump · failed(CAN) ENGINE WOULD NOT LIGHT UP DURING START UNTIL 18 PERCENT-20 PERCENT. A NORMAL START LIGHT OFF IS 12 PERCENT-14 PERCENT. FOUND FUEL PUMP OUTPUT PRESSURE AT LOW RPM BELOW SPECS.SDR 97ZZZX4457Support · crackedFUEL CONTROL SUPPORT SPLIT BETWEEN TWO BOLT HOLES. PART NEEDS TO BE LONGER.SDR PNSA970804Switch · closedBETA LIGHT ILLUMINATED ON TAKEOFF ROLL. REPLACED BETA SWITCH, OP'S CHECK OK.SDR 97ZZZX3680Canted Rib · crackedDURING A PHASE INSPECTION, FOUND BOTH RT AND LT CANTED RIBS TOP CAPS TO BE CRACKED. CRACKS START AT AFT SIDE OF FORWARD WING SPAR AND RUN AFT, PARALLEL TO THE BEND RADIUS. STOP DRILLED BOTH ENDS OF EACH CRACK PER CESSNA ENGINEERING INSTRUCTIONS.SDR 97ZZZX3679Canted Rib · crackedDURING A PHASE INSPECTION, FOUND BOTH RT AND LT CANTED RIBS TOP CAPS TO BE CRACKED. CRACKS START AT AFT SIDE OF FORWARD WING SPAR AND RUN AFT, PARALLEL TO THE BEND RADIUS. STOP DRILLED BOTH ENDS OF EACH CRACK PER CESSNA ENGINEERING INSTRUCTIONS.SDR CA971223002Ignition Box · failed(CAN) IGNITION BOX FAILED.SDR 97ZZZX3091Acm · damagedACTT 4,328.25 HOURS. BLADES FOUND DAMAGED, SOURCE UNKNOWN. APPLIANCE TTSN UNKNOWN. REPLACED ACM.SDR AU970710Computer · failed(AUS) ENGINE FUEL COMPUTER ELECTRONIC FAILURESDR 97ZZZX2906Armature · damagedWHILE APPROACHING TO LAND AT 'LAS', PILOT LOST LT GENERATOR INDICATION. TWO MINUTES LATER PILOT GOT A FIRE WARNING INDICATION AND SECURED THE ENGINE AND FIRED THE LT FIRE BOTTLE. LANDED WITH NO FURTHER PROBLEMS. EXAMINATION FOUND THE GENERATOR SHAFT SHEAREDSDR AU970575Governor · cracked(AUS) LH ENGINE PROPELLER GOVERNOR HOUSING CRACKED AT RH SIDE UPPER LUGSDR AU970546Line · failed(AUS) HYDRAULIC LINE BURST DURING RIG TESTING AT APPROXIMATELY 220PSISDR 97ZZZX2951Resistor · faultDURING ROUTINE CLIMB THROUGH 12,000 FEET, LOST POWER IN LT ENG, OBSERVED TORQUE AT 300 POUNDS AND EGT OVER RED LINE. SHUT DOWN NR 1 ENG AND SECURED. DURING TROUBLESHOOTING, ISOLATED PROBLEM TO INTERMITTENT FAULT IN EGT COMPENSATING RESISTOR. A FAULT IN THISSDR 97ZZZX2589Transducer · malfunctionTRANSDUCER CAUSES ERRATIC OIL PSI GAUGE READINGS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR 97ZZZX2361Hinge · crackedWHILE AIRCRAFT WAS IN HANGAR FOR MAINTENANCE, LOWER CABIN DOOR, AFT HINGE BROKE IN TWO. BREAK WAS ALIGNED WITH THREE RIVETS THAT WERE ADDED TO C/W SB PJ 81-21. EVIDENCE OF PREVIOUS CRACKING WAS VISIBLE. NEW HINGE WAS INSTALLED.SDR AU970445Compensator · loose(AUS) LH ENGINE EGT COMPENSATOR CONNECTOR PLUG LOOSE AND CORRODEDSDR 97ZZZX2016Fuel Line · chafedMAIN FUEL LINE FROM BOOST PUMP TEE TO FUEL CROSSFEED SHUTOFF VALVE WAS CHAFED BEYOND LIMITS BY WING RIB ASSY, AT WS 88.0 INCH, RIB P/N 572225-33. SUBMITTER RECOMMEND ALL CONQUEST II SHOULD BE INSPECTED IN THIS AREA - SHOULD THIS LINE OPEN UP DUE TO CHAFING, CSDR PNSA970401Hyd Sys · reqd serviceHYDRAULIC LOW FLOW LIGHTS ILLUMINATED DURING TAXI. FOUND SYSTEM OVER SERVICED AND AIR LOCKED. RESERVICED SYSTEM. NO FURTHER SYSTEM PROBLEMS NOTED.SDR AU970379Fcu · malfunctioned(AUS) ENGINE FUEL CONTROL UNIT SUSPECT FAULTY - ENGINE SURGED AND EGT REACHED APPROXIMATELY 520 DEGREES C (OVERTEMP) - AN HOT END INSPECTION WAS CARRIED OUT WITH NO MAJOR DAMAGE FOUNDSDR AU970357Hook · broken(AUS) LARGE CABIN DOOR TOP LOCKING HOOK FAILEDSDR PNSA970311Wire · brokenLEFT FUEL JET PUMP FAIL LIGHT CAME ON DURING CLIMB. REPAIRED WIRE ON TRANSFER SELECT SWITCH.SDR AU970378Turnbuckle · fouled(AUS) LH REAR AILERON CABLE TURNBUCKLE BETWEEN LH REAR AILERON CABLE PNO 5815103-26 AND BELLCRANK PNO 5815114-1 INTERMITTENTLY CATCHING ON FLOOR SUPPORT BRACKETSDR AU970290Governor · faulty(AUS) RH ENGINE PROPELLER GOVERNOR FAULTYSDR AU970292Valve · sticking(AUS) NTS CHECK VALVE ON GEARCASE STICKING ALLOWING HIGH PRESSURE GOVERNOR OIL TO ACTIVATE BETA SWITCHSDR 97ZZZX1062Rib · crackedDURING A PHASE INSPECTION, FOUND A CRACK IN THE RT WING CANTED RIB TOP CAP. CRACK STARTS AT AFT SIDE OF FORWARD WING SPAR AND RUNS AFT PARALLEL TO THE BEND RADIUS, APPROXIMATELY 1 INCH IN LENGTH. STOP-DRILLED ENDS OF CRACK PER CESSNA INSTRUCTIONS.SDR AU970291Empennage · lightning strike(AUS) AIRCRAFT LIGHTENING STRIKE - ENTRY POINT APPEARS TO BE LH FLAP AND AILERON - BOTH ELEVATORS HAD EXIT HOLES ADJACENT TO OUTER STATIC WICKS - RUDDER TOP FAIRING HAD EXIT HOLE AND EVIDENCE OF BURNING - UPPER RUDDER SKIN HAD EVIDENCE OF ARCINGSDR AU970094Slip Ring · separated(AUS) PROPELLER SLIP RING SEPARATING FROM DE-ICE PLATTER - SUSPECT NONAPPROVED REPAIR CARRIED OUTSDR AU970092Latch · cracked(AUS) PROPELLER STARTING LATCH CRACKEDSDR 97ZZZX1100Skin · corrodedRIGHT WING DEICE BOOT WAS REMOVED FOR REPLACEMENT. WING SKIN WAS FOUND TO HAVE EXCESSIVE CORROSION PITS ON MUCH OF THE SKIN. DAMAGE ALLOWANCE IS ONLY 15 PERCENT OF .032 INCH SKIN THICKNESS. LEADING EDGE ASSEMBLY HAS TO BE REPAIRED. THIS COULD POSSIBLY BE FSDR 97ZZZX988Hinge · brokenDURING PREFLIGHT, FOUND THE AFT LOWER CABIN DOOR HINGE BROKEN IN TWO PIECES AT THE LOCATION OF THREE RIVETS INSTALLED THROUGH THE HINGE AND DOOR FRAME. NEW HINGE ASSY INSTALLED.SDR AU970065Nozzle · leaking(AUS) FUEL NOZZLE BODY LEAKING - INVESTIGATION FOUND TWO PIN HOLES IN THE BODY BASE - NOZZLES WERE A NEW ITEMSDR 97ZZZX678Selector Valve · miswiredTHE NOSE GEAR RETRACTED DURING ENGINE START WITH THE GEAR SELECTOR DOWN AND THREE GREEN GEAR IND LIGHTS. INVESTIGATION FOUND THE LEFT DOWNLOCK SWITCH FAILED IN THE CONTROL CIRCUIT APPLYING POWER TO THE LOADING VALVE AND HYD SLECTOR VALVE. PIN B AND D IN CONNSDR PNSA970102Beta Switch · intermittentLEFT BETA LIGHT CAME ON DURING TAKEOFF. COULD NOT DUPLICATE. REPLACED SWITCH.SDR 97ZZZX638Switch · sticksSWITCH STICKS IN OPEN POSITION. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR 96ZZZX5655Canted Rib · crackedDURING A PHASE INSPECTION FOUND BOTH RT AND LT WING CANTED RIB TOP CAP CRACKED. CRACK STARTS AT AFT SIDE OF FWD WING SPAR AND RUNS AFT PARALLEL TO THE BEND RADIUS. STOP-DRILLED ENDS OF CRACKS PER CESSNA INSTRUCTIONS.SDR 96ZZZX5654Canted Rib · crackedDURING A PHASE INSPECTION FOUND BOTH RT AND LT WING CANTED RIB TOP CAP CRACKED. CRACK STARTS AT AFT SIDE OF FWD WING SPAR AND RUNS AFT PARALLEL TO THE BEND RADIUS. STOP-DRILLED ENDS OF CRACKS PER CESSNA INSTRUCTIONS.SDR 96ZZZX5653Angle · crackedDURING A PHASE INSPECTION, FOUND A CRACK IN THE OUTBOARD END OF THE RT AND LT MAIN GEAR UPLOCK HOOK SUPPORT ANGLE THAT ATTACHES TO THE FORWARD WING SPAR WEB. CRACK ORIGINATES AT THE OUTBOARD HILOCK HOLE AND EXTENDS FOR A TOTAL LENGTH OF 1.25 INCHES. INSTALLESDR 96ZZZX5652Angle · crackedDURING A PHASE INSPECTION, FOUND A CRACK IN THE OUTBOARD END OF THE RT AND LT MAIN GEAR UPLOCK HOOK SUPPORT ANGLE THAT ATTACHES TO THE FORWARD WING SPAR WEB. CRACK ORIGINATES AT THE OUTBOARD HILOCK HOLE AND EXTENDS FOR A TOTAL LENGTH OF 1.25 INCHES. INSTALLESDR 96ZZZX5804Bellcrank · looseTHE LEFT AND RIGHT FLAP IDLER BELLCRANKS, BOTH P/N 5865105-3, ARE FOUND TO BE WORKING BETWEEN THE CAST ARM AND THE TUBULAR BEARING SUPPORT COLUMN. THE 4 SECURING RIVETS ALSO APPEAR TO BE LOOSE BUT NOT SHEARED. SUBMITTED STATED IT IS BELIEVED THAT RIVET FAILUSDR 96ZZZX5606Bellcrank · wornTHE LT AND RT FLAP IDLER BELLCRANKS, BOTH P/N 5865105-3, ARE FOUND TO BE WORKING BETWEEN THE CAST ARM AND THE TUBULAR BEARING SUPPORT COLUMN. THE 4 SECURING RIVETS ALSO APPEAR TO BE LOOSE, BUT NOT SHEARED. IT IS BELIEVED THAT RIVET FAILURE WOULD RESULT IN FLSDR 96ZZZX5587Rib · crackDURING A PHASE INSPECTION, FOUND A 1.5 INCH CRACK IN RT WING CANTED RIB TOP CAP. CRACK STARTS AT AFT SIDE OF FWD WING SPAR AND RUNS AFT PARALLEL TO THE BEND RADIUS. STOP DRILLED CRACK PER CESSNA INSTRUCTIONS.SDR 96ZZZX6101Tee Structure · crackedNOSE GEAR TUNNEL FORWARD SUPPORT 'TEE' WAS FOUND CRACKED IN THE RADIUS OF THE 'TEE' STRUCTURE. THIS IS THE THIRD CRACKED 'TEE' THAT HAS BEEN FOUND ON THIS TYPE OF AIRCRAFT. SUSPECT GROUND HANDLING MAY CONTRIBUTE TO CAUSE. INSPECT ANYTIME NOSE BAY FLOORS ARESDR 96ZZZX5113Rib · crackedDURING PHASE INSPECTION, FOUND 1.5 INCH CRACK IN RT WING CANTED RIB TOP CAP. CRACK STARTS AT AFT SIDE OF FORWARD SPAR AND RUNS AFT PARALLEL TO THE BEND RADIUS. STOP DRILL CRACK PER CESSNA INSTRUCTIONS.SDR PNSA960901Brake Cylinder · brokenLOSS OF RT BRAKE FLUID. CYLINDER BROKE AT TORQUE PLATE PIN.SDR 96ZZZX5050Flow Control · pluggedWING BOOTS INFLATED AND STAYED INFLATED UNTIL ENGINE SHUT DOWN. THEY WOULD NOT RESET. REMOVED FLOW CONTROL EJECTOR VALVE AND FOUND OVERBOARD PORT PLUGGED WITH MUD AND INSECT EGG SACKS.SDR 96ZZZX4884Line · pluggedPILOT REPORTED LOUD BANG IN-FLIGHT AND NOTED RT OUTBOARD WING WAS CAVED IN AND AILERONS WERE VERY HARD TO MOVE. SAFE LANDING WAS MADE. BOTH TOP AND BOTTOM OF RT OUTBOARD WING PANEL WERE COLLAPSED WITH RIBS COMPRESSED FROM OUTBOARD RIB OF FUEL BAY, INBOARD 8.SDR 96ZZZX4883Flow Control Vlv · pluggedWING BOOTS INFLATED AND REMAINED INFLATED UNTIL ENGINE SHUT-DOWN. THEY WOULD NOT RESET. REMOVED FLOW CONTROL EJECTOR VALVE AND FOUND OVERBOARD PORT PLUGGED WITH MUD AND INSECT EGG SACKS.SDR 96ZZZX4882Elbow · pluggedINSPECTING LEFT WING FUEL VENT SYSTEM FOR OBSTRUCTION, FOUND MUD NEST IN ELBOW OF LINE, P/N 5700113-28, ABOUT 2.50 FEET IN FROM INLET. ALSO, FOUND OUTBOARD RIB COLLAPSED.
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