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 = 'A185F' 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 = 'A185F' 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 CA030321010Rib · cracked(CAN) DURING 200 HR INSPECTION THE INBOARD FLAP TRACK BRACKETS FOR THE CLOSING SKIN WHERE FOUND CRACKED. DURING REPLACEMENT OF THESE BRACKETS IT WAS DISCOVERED THAT THE LOWER CORNER OF THE RIBS WHERE ALSO CRACKED. BOTH INBOARD AND OUTBOARD RIBS ON THE FELT INSDR CA040210007Blade · scored(CAN) AFTER SHUT-DOWN, PILOT NOTICED ONE PROPELLER BLADE ROOT SNAP RING HAD POPPED OUT OF ITS LOCATION DURING PREVIOUS FLIGHT. IN DOING SO, IT DAMAGED THE BLADE ROOT BY SCORING SURFACE. PROPELLER REMOVED AND SENT FOR REPAIR AT PROPELLER SHOP.SDR CA030228001Hinge · cracked(CAN) DURING ROUTINE SCHEDULED MAINTENANCE, IT WAS DISCOVERED THAT THE REINFORCEMENTS - STABILIZER HINGE WERE CRACKED. P/N 0732101-4 REPLACED WITH NEW PARTS.SDR CA030204012Wire · overheated(CAN) LUG IMPROPERLY CRIMPED TO WIRE PA-6 AT RADIO MASTER SWITCH CAUSING AN OVERHEAT SITUATION WITH EVENTUAL SEPARATION OF WIRE FROM LUG. WIRE WAS ORIGINAL FROM CESSNA FACTORY INSTALLATION.SDR CA021119011Cylinder · failed(CAN) WHILE CONDUCTING A CYLINDER COMPRESSION TEST, THE FOLLOWING RESULTS WERE DISCOVERED:CYLINDER 1-40PSI, 2-45PSI, 3-0PSI, 4-0PSI,5-40PSI, 6-58PSITHE MEASURE OF THE CYLINDER BARRELS INDICATES THAT THEY SHOULD MEASURE '10 THOU OVERSIZE'. THE EXHAUST VALVES ARSDR 2002FA0001118Blade · crackedRECEIVED PROPELLER FOR ROUTINE OVERHAUL. NO OVERHAUL OR INSPECTION SINCE 1982 (START OF LOG BOOK). PENETRANT INSPECTION OF PARTS REVEALED CRACK IN 1ST THREAD OF NR 1 BLADE. CONFIRMED WITH EDDY CURRENT. PROP WAS OIL FILLED IN 1982. NO INSPECTIONS PERFORMED ON BSDR CA021016026Connecting Rod · broken(CAN) PILOT EXPERIENCED STRANGE NOISE AND VIBRATION FROM ENGINE WHILE IN CRUISE. AIRCRAFT WAS LANDED AND TOWED TO SAFE STORAGE. ENGINE REPLACED.SDR CA020829005Bracket · cracked(CAN) AIRCRAFT LANDED IN ROUGH WATER, CAUSING THE BATTERY TO CRACK AT THE BATTERY POSTS. A COMPLETE INSPECTION OF THE AIRCRAFT WAS CARRIED OUT, AND THE CRACK IN THE REINFORCEMENT BRACKET WAS DISCOVERED. NO OTHER DEFECTS WERE FOUND.SDR 2002FA0001002Screw · missingTHIS OVERHAULED ALTERNATOR WAS INSTALLED 06/28/02 AT TACH:642.0. REMOVED 07/27/02 TACH:745.0. PILOT COMPLAINED OF LOW READING ON AMG GAUGE. UPON INSPECTION OF THE ALTERNATOR, FOUND 1 CASE SCREW MISSING AND THE OTHER 2 COMING OUT OF CASE HALF. THESE SCREWSSDR CA021122002Bracket · cracked(CAN) DURING SCHEDULED MAINTENANCE, IT WAS DISCOVERED THE REINFORCEMENT BRACKETS WERE CRACKED. NEW PARTS 0732101-4 WERE INSTALLED.SDR CA020729006Cover · departed(CAN) UPON LIFTING OFF THE WATER THE RT FLOAT HATCH - DEPARTED THE FLOAT - CREASING RT FUSELAGE SKIN AHEAD OF BULKHEAD AT STATION 108.0 AND HIT RT LEADING EDGE OF HORIZONTAL STABILIZER.SDR CA020626003Snap Ring · missing(CAN) PROPELLER RECEIVED FROM CUSTOMER AFTER LOSS OF SNAP RING. PROPELLER WAS DISMANTLED, BLADES DRESSED, PAINTED AND ASSEMBLED.SDR CA020619012Gear · broken(CAN) AT THE MOMENT OF ACCIDENT, THE MOTOR DID A "KICK BACK". TWO TEETH OF THE CRANKSHAFT GEAR THAT WERE IN CONTACT WITH THE STARTER CLUTCH SHAFT GEAR BECAME BROKEN AND FELL INTO THE OIL PAN. THIS MODEL OF THE STARTER CLUTCH CAN STICK IF IT IS TURNED COUNTER-CSDR CA020606008Angle · cracked(CAN) DURING SCHEDULED MAINTENANCE, IT WAS DISCOVERED THAT THE ANGLE - TAILCONE REINFORCEMENT RT IN THE TAILCONE BULKHEAD ASSEMBLY WERE CRACKED. NEW PARTS 0712048-7 (LT) AND 0712048-6 (RT) WERE INSTALLED USING THE EXISTING RIVET SIZE AND PATTERN.SDR CA020530008Pulley Bracket · broken(CAN) WHEN SELECTING FLAPS FOR LANDING, LEFT FLAP WOULD NOT COME DOWN. AIR PRESSURE KEPT IT UP. PILOT SELECTED FLAPS UP, AND LANDED.SDR CA020523017Fork · cracked(CAN) BOTH BOW WHEEL FORKS HAVE TWO CRACKS EACH UP TO 1.5 INCHES LONG LOCATED ON THE AFT UPPER EDGE OF FORK. THE CRACKS ARE RUNNING FROM EDGE OF THE FORK FORWARD THE TWO 5/16 INCH REAR MOUNTING BOLT HOLES. ONE OF THE CRACK HAD GONE BEYOND THE HOLE.SDR AWO2002F00000Light · inoperativeDURING ANNUAL INSPECTION FOUND LEFT HAND FORWARD DOOR POST LIGHT SWITCH IN CLOSE PROXIMITY TO MAIN FUEL LINES WHICH RUN DOWN FORWARD DOOR POST. THIS AD CALLS FOR AN INSULATOR TO BE INSTALLED ON THE BACK OF THE SWITCH.SDR CA020510016Cylinder · worn(CAN) ENGINE INDICATING SYS & PARAMETERS WERE OP NORMALLY.AT 164.1 HRS OF OP, A CYLINDER DIFFERENTIAL CHECK WAS CARRIED OUT. ALL CYLINDERS WERE FOUND TO BE IN 60/80 RANGE. A/C CONTINUED TO FLY & AT 260.6 HRS OF OP, A 2ND DIFFERENTIAL CHECK SHOWED READINGS OF SDR 2003FA0000755Control Column · crackedA CRACK WAS FOUND ON THE AFT SIDE, ASCENDING UP FROM THE BASE OF THE CONTROL COLUMN (CONTROL U ASSY). THE CRACK MEASURED APPROXIMATELY 6 INCHES AND HAD SPREAD APART APPROXIMATELY .5000 INCH JUST ABOVE THE ELEVATOR PUSH-PULL TUBE BEARING AND EXTENDED UP THROUGSDR CA011116014Pump · failed(CAN) DURING CLIMB AFTER TAKEOFF FROM RUNWAY 16 AT YYC WHEN THE PILOT ADJUSTED THROTTLE AND MIXTURE THE ENGINE STOPPED PRODUCING POWER. AN EMERGENCY LANDING WAS CARRIED OUT ON THE END OF RUNWAY 16.SDR CA011017007Valve Seat · cracked(CAN) - NR 6 CYLINDER ASSEMBLY CRACKED FROM EXHAUST VALVE SEAT TO INJECTOR PORT TO INTAKE VALVE SEAT. - INJECTOR AND FUEL FLOW AND PRESSURE NORMAL SO CAUSE UNKNOWN.- CYLINDER REPLACED.SDR 2001FA0000362Tube · disconnectedONE AFT COMPARTMENT PUMP OUT TUBE WAS DISCONNECTED NOT ALLOWING THE WATER TO BE PUMP FROM FLOAT. AIRCRAFT SWAMPED RIGHT FLOAT ON TURN AND STARTED TO SINK.SDR CA011003014Bracket · broken(CAN) FLAPS WOULD NOT EXTEND PROPERLY FOR TAKEOFF. PILOT LEFT FLAPS IN UP POSITION AND RETURNED TO BASE. BRACKET IS MOUNTED TO LOWER BULKHEAD USING 4 SCREWS AND LOCKNUTS ON THE 4 MOUNT TABS. BOTH INBOARD TABS ON BRACKET HAD FAILED AT THE BEND RADIUS, ALLOWING SDR CA011211004Control Cable · frayed(CAN) FWD (CARRY-THROUGH) CABLE REMOVED TO CARRY OUT AN INSPECTION ON IT'S CONDITION DUE TO THE FACT THAT IT IS IMPOSSIBLE TO FEEL OR SEE MOST OF THE CABLE AS IT'S INSTALLED IN THE A/C. INSPECTION REVEALED FRAYED SECTION WHERE CABLE GOES AROUND THE PULLEY SUGGSDR CA010626006Switch · failed(CAN) ON GEAR EXTENSIONFOR LANDING IN PRINCE ALBERT SASK. THE RH MAIN GEAR DOWN INDICATOR LIGHT DID NOT ILLUMINATE. AFTER TESTING THE SYSTEM AND HAVING THE SAME RESULTS, THE PILOT ELECTED TO LAND AND DID SOWITHOUT INCIDENT. ON THE GROUND, TESTING REVEALED THATSDR CA011221001Bracket · cracked(CAN) CRACK NOTED FROM RETAINER'S EDGE TO INBOARD ATTACHMENT SCREW HOLE AS VIEWED FROM THE LT SIDE OF A/C. ANOTHER CRACK NOTED IN BOTTOM BEND RADIUS OF BRACKET AND EXTENDING ALONG THE BEND FOR APPROX. 1 INCH. PROBABLE CAUSE IS FROM CARRYING EXTERNAL LOADS ON SDR CA011219006Bulkhead · cracked(CAN) CRACK NOTED ON LT BULKHEAD DURING INSPECTION WITH MIRROR. BULHEAD IS LOCATED DIRECTLY ADJACENT TO BAGGAGE DOOR.SDR CA011211005Channel · cracked(CAN) CHANNEL FOUND CRACKED DIRECTLY BEHIND LT STAB HINGE REINFORCEMENT, WHICH WAS ALSO CRACKED. FURTHER INVESTIGATION REVEALED CRACKED SPAR ALSO IN SAME AREA.SDR CA010628022Channel · cracked(CAN) PREVIOUS FILED SDR FOR CRACKED STABILIZER- HINGE REINFORCMENT P/N 0732101-4 AFTER REMOVAL OF THE REINFORCEMENT CH-RT WAS FOUND CRACK IN P/N 0732602-2/1232114-1 CRACK IN 07323603-1. LOWER RADIUS LT SIDE STA 6 INCH. LENGTH OF COACH I".SDR CA010628029Spar · cracked(CAN) DURING ANNUAL INSPECTION FOUND PLAY IN HORIZONTAL STABILIZER TO ELINMINATE PLAY REPLACE ALL HARDWARE AND BUSHING IN ASS. DURING LUBRICATING OF ELEVATOR HINGES DISCOVERED CRACK ON STABILIZER HINGE REINFORCEMENT. THIS REINFORCEMENT IS RIVETED ON MAIN SPARESDR CA011211019Rib · corroded(CAN) LEAD BALANCE WEIGHT ATTACHES TO AFFECTED RIB AND CORROSION FORMED DUE TO DISSIMILAR METAL. AREA IMPOSSIBLE TO INSPECT UNLESS ELEVATOR TIP SKIN IS REMOVED TO ACCESS RIB. UPON REPLACEMENT OF RIB,SDR 2001F00037Snap Ring · missing3-26-01 REMOVED NO. 1 AND 3 CYLINDERS TO COMPLY WITH CRANKSHAFT COUNTER WEIGHT AD. FACTORY TECH REP REMOVED AND INSPECTED COUNTER WEIGHT AMOUNTING FLANGES (4), REPLACED COUNTER WEIGHTS AND ASSOCIATED PARTS, AND CYLINDERS AND ASSOCIATED PARTS, 50 ENGINE HOURS SDR 20010507CW004Fuel Control · defectiveAIRCRAFT WAS INSPECTED FOR FUEL SYSTEM PROBLEMS. IT WAS DISCOVERED THAT THE CONTROL ARM ON THE THROTTLE BODY WAS SHIPPING ON THROUGH SHAFT. THIS CONDITION DID CAUSE THE AIRCRAFT TO ENCOUNTER A STOCK THROTTLE CONDITION, IN THE FULL THROTTLE POSITION.SDR AUS20010457Bracket · cracked(AUS) MAIN LANDING GEAR ATTACHMENT BRACKET CRACKED. MLG LEG LOOSE ATWEDGES.SDR AUS20010456Bracket · corroded(AUS) MAIN LANDING GEAR ATTACHMENT BRACKET SEVERELY CORRODED.SDR AU010066Spar · cracked(AUS) HORIZONTAL STABILISER REAR SPAR CRACKED IN AREA BEHIND THERE INFORCED HINGE BRACKET CRACK LENGTH 50MM (1.96IN). CAUSED BY SEVERE CORROSION ON THE DOUBLER BRACKET SECURING THE ATTACHMENT HINGE PNO 0732101-11.SDR CA010117015Bulkhead · cracked(CAN) ON FUSELAGE BULKHEAD P/N 0711112-22 WE HAVE FOUND CRACK ON L/H & R/H SIDE OF BULKHEAD JUST ABOVE THE FLOATS ATTACH FITTINGS ON THE FORWARD SIDE OF THE BULKHEAD. AN ANGLE DOUBLER HAS BEEN INSTALLED AS PER AC-43.13,1B.SDR 20001204SH019Handle · failedTHE HANDLE SPLINE BUSHING STRIPED CAUSING HANDLE FAILURE. (X)SDR CA001122012Exhaust Valve · burned(CAN) AFTER COMPLETING THE ENGINE CYLINDER DIFFERENTIAL COMPRESSION TEST ON A ROUTINE INSPECTION, DETERMINED NR 3 AND NR 4 CYLINDERS HAD EXCESSIVE LEAKAGE THROUGH THE EXHAUST VALVES. THE BAFFLES AT EACH END OF THE EXHAUST MUFFLER WERE FOUND BROKEN AWAY FROM TSDR CA001122025Bellcrank · worn(CAN) DURING INSPECTION OF TAIL WHEEL STEERING CABLES, WORN BELLCRANKS WERE DISCOVERED AT SPRING ATTACH POINT.SDR CA001122027Link · stripped(CAN) PILOT REPORTED RUDDER TRIM HARD TO ADJUST. PARTS REMOVED AND FOUND THREADS ON WHEEL SCREW AND LINK ROD STRIPPED. A PORTION OF SCREW FOUND BROKEN INSIDE LINK ROD.SDR CA001106020Fitting · cracked(CAN) THERE WAS A STRONG SMELL OF FUEL WHEN THE AIRCRAFT WAS PARKED AND DOOR OPENED.A CHECK OF THE COMPLETE FUEL SYSTEM, FOUND UNDER CABIN FLOOR. LEFT SIDE WHERE FRONT AND REARFUEL TANK LINES ARE CONNECTED, TEE FITTING WAS LEAKING. UPON REMOVAL ATHE TEE FITTINSDR CA001110043Spring · cracked(CAN) WHEN AIRCRAFT LANDED, THE WHEEL AND AXLE CAME OFF AND GEAR LEG DUG IN RUNWAY AND SEPARATED FROM AIRCRAFT. IN FUTURE, AIRCRAFT SPRING ASSEMBLIES WILL BE SENT FOR N.D.T. EVERY 12 MONTHS. (X)SDR CA000928021Roll Pin · displaced(CAN) ROLL PIN ON LEFT STABILIZER ACTUATOR SLID OUT AND GOT CAUGHT ON THE ACTUATOR HINGE ASSEMBLY. THIS PREVENTED THE STABILIZER TRIM FROM MOVING. THE TRIM ACTUATORS WERE REMOVED, THE PIN RE-INSTALLED, AND LOCKWIRED. SUGGEST LOCKWIRING PINS IN ALL ACTUATORS.SDR 20000913SH013Cap · missingCAP WAS FOUND MISSING UPON POST-INSPECTION. AIRCRAFT WAS JUST PURCHASED WITH A RECENT ANNUAL. (X)SDR 20000911SH045Altimeter · stuckALTIMETER STICKING EXCESSIVELY 500-600 FEET. THIS AIRCRAFT WAS PITOT STATIC TESTED THE DAY BEFORE THE FLIGHT FROM PLACERVILLE CA TO WHITEMAN AIRPARK. THIS ALTIMETER HAS AN INTERNAL ENCODER. THE PITOT STATIC CASE WAS ORDERED TO BE C/W PRIOR TO CLOSURE OF THSDR 20000908SH006Control Cable · separatedCABLE PARTED .25 INCH AFT OF MS20668-3 SWAGED TERMINAL EYE END FITTING, IN AN AREA VERY DIFFICULT TO INSPECT VISUALLY, CAUSING SUDDEN FLAP RETRACTION. SUBMITTER RECOMMENDED PERIODIC INSPECTION EVEN IF IT REQUIRES REMOVAL OF THE CABLE. SUBMITTER STATED DESIGNSDR CA000804021Cylinder · cracked(CAN) CYLINDER CRACKED SPARK PLUG HOLE TO INJECTOR HOLE.SDR CA000804020Cylinder · cracked(CAN) CYLINDER CRACKED INJECTOR PLACE TO VALVE. (X)SDR CA000801017Hub · cracked(CAN) PROPELLER HUB CRACKED/LEAKING RED DYED.
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