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 = '152' 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 = '152' 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 CA031219001Rib · cracked(CAN) THE STABILIZER WAS REMOVED FROM THE AIRCRAFT TO PERFORM OTHER UNRELATED REPAIRS WHEN IT WAS DISCOVERED THAT BOTH OF THE IB LEADING EDGE NOSE RIBS WERE CRACKED. THE CRACKS APPEAR ON THE FLANGE ADJACENT TO THE MOST AFT ATTACHING TABS. CRACKS WERE FOUND TSDR CA031212005Bracket · cracked(CAN) AN INSPECTION WAS PERFORMED TO THE BRACKET AT THE REAR OF THE HORIZONTAL STABILIZER IN PREPARATION FOR COMPLIANCE WITH CESSNA SERVICE BULLETIN 03-6.ONCE THE STABILIZER AND BRACKET WERE REMOVED FROM THE AIRCRAFT, A CLOSE VISUAL EXAMINATION REVEALED A CRACSDR CA031211001Line · corroded(CAN) FUEL LINE HAD A ROUGH LOOK TO THE SURFACE. THE FUEL LINE WAS ACCESSED BY REMOVING CENTER CONSOLE COVER AND PEELING BACK CARPET. CLOSER EXAMINATION OF LINE REVEALED CORROSION PITS AND RESIDUE THAT WAS DETERMINED TO BE CAUSED BY THE FUEL LINE CONTACT WITHSDR AUS20031250Clamp · split(AUS) ENGINE MOUNT LOWER CLAMP SPLIT ON LT SIDE.SDR AUS20031202Spar · corroded(AUS) RT WING SPAR ANGLE CONTAINED INTERGRANNULAR CORROSION IN AREA WHERE IT PASSES THROUGH THE FUEL TANK CAVITY.SDR 2003FA0001207Pulley · looseRFD CONTROL TOWER NOTED SPARKS COMING FROM COWLING AREA. UPON COWL REMOVAL NOTED ALTERNATOR AND ALTERNATOR PULLEY HAD BEEN LOOSE AND WOBBLING. ALTERNATOR HOUSING GOUGED, PULLEY SEVERELY DAMAGED FROM EXCESSIVE WOBBLING AND VIBRATION. ROTOR SHAFT END AND THRESDR 2003FA0001197Support Bracket · crackedSUPPORT BRACKET WAS FOUND TO HAVE A CRACK IN THE WELD WHILE INSPECTING NUTPLATES IAW AD. CRACK WAS LOCATED JUST FORWARD OF NUTPLATE INSIDE BRACKET ABOUT .7500 INCH LONG. WITH DYE PENETRANT INSPECTION, DYE PENETRATED COMPLETELY THROUGH WELD TO OUTSIDE BRACKETSDR CA031031005Hinge · worn(CAN) RT ELEVATOR OB HINGE ASSY BOLT HOLE IS WORN AND OBLONGED IN SHAPE AS WELL AS THE HINGES INNER FACES ARE GROOVED FROM BUSHING. NOTE THAT BUSHING IS NOT SE IZED IN THE BEARING ASSY ON THE ADJOINING HORIZONTAL STAB HINGE.SDR 2003FA0001130Bracket · crackedFOUND LT REAR VERTICAL FIN BRACKET CRACKED AT BASE (FITTING).SDR CA031015009Bar · cracked(CAN) LOSS OF LT RUDDER CONTROL IN FLIGHT. LT RUDDER TORQUE TUBE BAR FOUND CRACKED AND DEFORMED WHERE THE 'TEE' IS WELDED TO THE BAR. LT RUDDER PEDAL ON THE RT. (AIRCRAFT BEING FLOWN FROM RT SEAT) CRACK 2 INCHES LONG, FROM END OF PIPE, AROUND HEAT AFFECTED ZOSDR CA031015012Spar · cracked(CAN) RT WING AFT SPAR FOUND CRACKED AT AFT WING ATTACH POINT. 1 INCH CRACK LOCATED FROM INBOARD END OF AFT SPAR P/N 0426400-32 JUST BELOW SPAR REINFORCEMENT CRACK EXTENDS ALONG THE LENGTH OF THE SPAR 1 INCH. WING REMOVED FOR REPAIR.SDR CA031015016Shaft · loose(CAN) CRANKSHAFT IDLER GEAR SHAFT P/N 61151 FOUND LOOSE AT ENGINE DISASSEMBLY. 2 BOLTS STD-705 UNLOOKED, BACK OFF 2C3 THREADS. LOCKPLATE 73817 NOT BENT FAR ENOUGH ONBOLT HEAD. THIS ENGINE WAS REBUILT.SDR CA031113002Drain Valve · failed(CAN) AFTER DRAINING ENGINE OIL DURING A 100 HOUR INSPECTION, THE VALVE WAS CLOSED. UPON CLOSING THE VALVE, IT CAME APART. NO ABNORMAL AMOUNT OF FORCE WAS APPLIED. THE VALVE IS SPRING LOADED CLOSED. IF THIS WERE TO HAPPEN IN FLIGHT ALL OIL COULDBE LOST AT A RSDR 2003FA0000853Attach Fitting · crackedON ANNUAL INSPECTION FOUND LEFT VERTICAL FIN ATTACH POINT OUTBOARD EAR BROKEN OFF. ALSO FOUND A STEEL TAPERED SHIM (.018 TO .065) UNDER THE RIGHT THREE OF THE FOUR AFT FIN ATTACH FITTING BOLTS. TECH SUPPORT FOUND NO REF TO ANY SUCH PART. REMOVED SHIM AND RESDR CA030731010Bracket · cracked(CAN) DURING ROUTINE 200 HOUR INSPECTION THE FORWARD LT VERTICAL FIN ATTACHMENT BRACKET APPEARED TO BE CRACKED ALONG THE BASE EXTERNAL SURFACE WHERE IT MATES WITH THE VERTICAL TABS OF THE PART. DISASSEMBLY REVEALED THE CRACK EXTENDED FORWARD AND AFT ALONG THISDR CA030731009Bolt · loose(CAN) ON OVERHAUL DISASSEMBLY OF THE ENGINE, WE NOTICED THAT THE TWO BOLTS HOLDING THE IDLER GEAR SHAFT UNSCREWED AND THE LOCK PLATES HALF WAY ON THE BOLTS. THIS PROVOKE THE WITHDRAWAL OF THE IDLER GEAR AND CAUSED AN ENGINE SHUTDOWN. THE MANUFACTURER PERFORMEDSDR 2003FA0000828Connecting Rod · brokenAIRCRAFT MADE EMERGENCY LANDING. NR 3 CONNECTING ROD BROKE, CAUSING A HOLE TO BE PUNCHED IN THE CRANKCASE AND DESTROYING THE CAM FOLLOWER AREA. CAUSE OF FAILURE HAS NOT BEEN DETERMINED.SDR 2004FA0000084Carburetor · leakingFUEL LEAKING AT PRODUCTION BREAK. LACK OF QUALITY CONTROL AT OVERHAUL.SDR CA030703007Piston · failed(CAN) NR 3 CYLINDER PISTON EXPERIENCED FAILURE OF ITS ALUMINUM SIDE DURING CRUISE FLIGHT, RESULTING IN ENGINE POWER LOSS AND ROUGH OPERATION. PISTON FAILURE CAUSED PRESSURE FROM COMBUSTION TO ENTER THE CRANKCASE. THIS RESULTED IN THE CRANKCASE BECOMING PRESSURSDR 2003FA0000870Tire · damagedPILOT NOTICED A LARGE BUMP ON SIDEWALL OF TIRE. UPON INVESTIGATION THE TUBE WAS FOUND TO BE IN GOOD CONDITION BUT TIRE SIDEWALL WAS VERY SOFT, ALLOWING THE TUBE TO PUSH OUTWARD. NO OTHER DEFECTS WERE EVIDENT AND TIRE NEVER LOST AIR PRESSURE. NO HARD LANDINGSDR CA030609012Engine · failed(CAN) DURING LANDING AFTER PASSING THE RUNWAY THRESHOLD ENGINE BROUGHT TO IDLE CAUSING IT TO STOP AND PROP TO WINDMILL. AFTER LANDING PILOT TAXIED WITH REMAINING SPEED OFF THE RUNWAY. (RESTARTING WAS UNSUCCESSFUL). PLANE WAS TOWED TO THE RAMP. NOTE: 164 HOUSDR 2003FA0000596Cylinder · wornPROBLEM WITH HIGH OIL TEMP ON TEST FLIGHT. AT 280.3 OIL CONSUMPTION INCREASED AND ENG STARTED RUNNING ROUGH, WHEN CHECKING SPARK PLUGS FOUND OIL ON NR 3 CYL PLUG. REMOVED NR 3 CYLINDER FOUND OIL CONTROL RING BROKEN, METAL IN OIL SYS. ON 12/27/02 REPLACED SDR 2003FA0000595Cylinder · wornENG WAS REMOVED AT 353.2 HRS SMOH AND WAS SENT BACK TO MFG FOR REPAIR DUE TO METAL IN THE OIL. AT 779.5 HRS METAL WAS FOUND IN OIL SYS. WE REPLACED ALL FOUR CYLINDERS AND CONNECTING ROD ASSY. GROUND RUN AND TEST FLIGHT CHECKED GOOD. AT 981.6 HRS TSO AND 2SDR 2003FA0000594Cylinder · wornWITH 137 HOURS ON THIS ENGINE THE OIL CONSUMPTION WENT UP. ON INSPECTION OF THE ENGINE, OIL WAS FOUND ON NR 1 AND NR 3 CYLINDER SPARK PLUGS. ALL FOUR CYLINDERS WERE REMOVED AND THE OIL CONTROL RINGS WERE FOUND BROKEN ON CYL NR 1 AND NR 3. THE CYLINDER WALLSSDR AUS20030591Flap Track · corroded(AUS) LT WING FLAP TRACK CORRODED ON INNER FACE. MATERIAL THICKNESS REDUCED BY APPROXIMATELY 25 PERCNET. TRACK IS LOCATED AT STN 312.75.SDR AUS20030610Rod End · seized(AUS) LT FLAP ASSEMBLY PUSH/PULL ROD END BEARING SEIZED CAUSING CONTROL ROD TO SNAP.SDR CA040407012Hub · cracked(CAN) PROPELLER FOUND CRACKED AT BOLT HOLES WHILE COMPLYING WITH AD 2003-12-05. PROPELLER WAS PREVIOUSLY NOT CRACKED WHILE COMPLYING WITH AD 97-06-16 (PREVIOUS VERSION OF 2003-12-05). TWO RADIAL 1/2 INCH CRACKS AROUND TWO BOLT HOLES WERE LOCATED WITH LPI ANDSDR AUS20030348Bracket · loose(AUS) LOWER LH ENGINE MOUNT BRACKET RIVETS SHEARED. SUSPECT CAUSED BY UNREPORTED HEAVY LANDING.SDR AUS20030314Spar · corroded(AUS) RT ELEVATOR CORRODED IN AREA OF TORQUE TUBE. CAUSED BY LACK OF PRIMER DURING ASSEMBLY. INSPECTION ALSO FOUND RACKS FOUND EMANATING FROM UPPER AND LOWER RIVET HOLES EXTENDING TOWARDS INBOARD END OF ELEVATOR SPAR AND OUTBOARD END. UPPER RIVET CRACK18.9MM (SDR AUS20030313Spar · cracked(AUS) ELEVATOR SPAR CRACKED AROUND UPPER RIVET HOLE FOR HINGE BRACKET ATTACHMENT. CRACK LENGTH 30.04MM (1.183IN). CRACK TRAVELS INBOARD AND OUTBOARD FROM RIVET HOLE.SDR CA030128003Carburetor · malfunctioned(CAN) ROUGH RUNNING ENGINE WAS NOTICED IN FLIGHT. PILOT THOUGHT IT WAS CARB ICE TRIED TO CLEAR IT OUT BY USING CARB HEAT. THIS DID NOT WORK, SO HE CAME BACK TO THE HANGER. AIRCRAFT WAS BROUGHT BACK INTO THE HANGER, ALL THE PLUGS WERE CLEANED. THEY WERE FULL OFSDR CA030107012Rib · cracked(CAN) RT HORIZONTAL STAB RIB WAS FOUND CRACKED.SDR CA021204008Carburetor · failed(CAN) LOSS OF CONTROL AT/ON TAKEOFF 200KM. CARBUETOR MALFUNCTION.SDR CA021122006Cylinder · cracked(CAN) CYLINDER BARREL CRACKED, 2 INCHES LONG AT BOTTOM OF CYLINDER HEAD.SDR CA021119010Rib · cracked(CAN) THE RT INBOARD LEADING EDGE RIB CRACKED AT TOP REAR CORNER.SDR CA021119009Rib · cracked(CAN) THE LT INBOARD LEADING EDGE RIB CRACKED AT TOP REAR CORNER.SDR 2002FA0001264Spar · crackedFOUND CRACK EXTENDING ABOUT.5 INCH FROM OUTBOARD HINGE POINT TO SPAR ATTACHMENT.SDR CA021031002Bracket · cracked(CAN) DURING ROUTINE INSPECTION OF STABILIZER BRACKET NUTPLATES AS PER AD 80-11-04, IT WAS NOTED THAT STEEL BRACKET ITSELF WAS CRACKED. AT REMOVAL, BOTH LEFT AND RIGHT TOP SIDES WERE CRACKED. THE FIN BOLTS TO THIS BRACKET, SO THE CRACKING COULD BE A RESULT OF SDR AUS20021235Gasket · damaged(AUS) ENGINE FUEL PUMP/BLANK PLATE GASKET CUT BY LOCKWIRE WRAPPED AROUND THE TWO MOUNTING BOLTS. GASKET LEAKING ENGINE OIL. ENGINEWAS FITTED WITH A BLANKING PLATE AND NOT A FUEL PUMP. ENGINE WASA RECENTLY OVERHAULED AND FITTED UNIT. PERSONNEL/MAINTENANCEERROR.SDR CA020724010Fork · cracked(CAN) WITH THE PAINT CLEANED AWAY FROM THE UPPER OUTSIDE RADIUS OF THE FORK, THE TECHNICIAN WAS ABLE TO DETECT THE CRACK WITH A GOOD LIGHT AND 10 X MAGNIFIER. THE CRACK RUNS HORIZONTALLY AND IS ABOUT 1-2 INCHES LONG. THE DEFECTIVE PART HAS BEEN REMOVED FROM SSDR CA030106018Strap · broken(CAN) FUEL LEAK. RT WING. UPON REMOVAL OF THE FUEL TANK WING PANEL, DISCOVERED THE AFT FUEL TANK STRAP TO BE BROKEN. DUE TO THE BROKEN STRAP THE SCREEN ASSEMBLY HAD CHAFED THROUGH THE TOP OF THE FUEL TANK CAUSING A FUEL LEAK. FUEL TANK REPAIRED AT AN APPROVESDR CA020725008Mount · cracked(CAN) ON INSPECTION (100 HOUR) ENGINE MOUNT WAS FOUND CRACKED AT LOWER RIGHT TUBE AT NOSE OLEO MOUNTING. THE ENGINE WAS REMOVED AND THE MOUNT REPLACED. THE ENGINE WAS RE-INSTALLED AND GROUND RUN SERVICEABLE. THE AIRCRAFT WAS RETURNED TO SERVICE.SDR CA020726019Butterfly Valve · separated(CAN) THE SEAL FOR THE BUTTERFLY VALVE IN THE CARBURETOR AIR BOX (FOR CARBURETOR HEAT) SEPARATED AND WAS SUCKED UP INTO THE CARBURETOR. THIS CAUSED THE ENGINE TO LOSE PERFORMANCE WHICH MADE THE PILOT RETURN FOR A LANDING. TOWER REPORTED SMOKE (LIKELY FROM A RISDR 2002FA0000837Control Cable · failedTHE PILOT COMPLAINED OF COPILOTS LEFT RUDDER PEDAL BEING LOOSE AND NOT VERY RESPONSIVE. INSPECTED PEDALS AND RUDDER CABLE SYSTEM. FOUND RIGHT RUDDER CABLE AT AFT FUSELAGE BULKHEAD HOLDING BY TWO STRANDS, FORWARD OF WHERE CABLE COMES OUT OF FUSELAGE TO ATTACHSDR CA020718009Fitting · broken(CAN) ON PRE-FLIGHT INSPECTION THE PILOT NOTICED A CRACK ON THE LEFT VERTICAL FIN ATTACH BRACKET. WHEN MAINTENANCE REMOVED THE BRACKET IT WAS FOUND BROKEN THROUGH. THE BRACKET WAS REPLACED WITH NEW AND NEW HARDWARE USED. THE RIGHT BRACKET WAS REMOVED CLEANED ASDR CA020619004Fork · cracked(CAN) DURING ROUTINE INSPECTION WE TOOK A CLOSE LOOK AT THE OLEO ASSEMBLY BASED ON PREVIOUS FINDINGS OF LIKE PARTS. THE PRIMARY REASON FOR THIS DETAILED INSPECTION IS BASED UPON THE KNOWN HIGH TIME AND OPERATING ENVIRONMENT OF THESE UNITS. WE DETECTED A CRACK SDR CA020619001Fork · cracked(CAN) AIRCRAFT WAS BROUGHT IN FOR ROUTINE INSPECTION. DECIDED TO DO A CLOSER INSPECTION ON THE OLEO COMPONENTS DUE TO THE HIGH TIME ON THESE UNITS. A CLOSE VISUAL INSPECTION AIDED BY A MAGNIFIER REVEALED A CRACK ON THE TOP OUTER SURFACE OF THE FORK ASSEMBLY. SDR CA020603002Fork · cracked(CAN) THE OLEO ASSEMBLY WAS REMOVED FROM THE AIRCRAFT TO BE INSPECTED AND REBUILT. UPON INSPECTION OF THE INDIVIDUAL COMPONENTS, IT WAS DETERMINED THAT THE FORK WAS CRACKED ON THE OUTER SIDE NEAR THE TOP COLLAR. VERIFICATION OF THE CRACK WAS MADE WITH A 10X MASDR CA020530016Magneto · contaminated(CAN) AIRCRAFT RAN ROUGH WHEN RT MAG SELECTED. OIL CONTAMINATION WAS FOUND IN BREAKER COMPARTMENT. MAGNETO WAS REPLACED AND A/C GROUND RUNS COMPLETED.SDR CA020904001Spar · cracked(CAN) UPON REMOVAL OF BRACKET TO GAIN ACCESS TO NUT PLATES DISCOVERED THE REINFORCEMENT AND RT SPAR CRACKED ALONG BEND RADIUS UNDER THE BRACKET. CRACKS COULD NOT BE SEEN UNTIL BRACKET WAS REMOVED.
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