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 = 'TU206G' 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 = 'TU206G' 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 2025FA0000673Wire · damagedDURING FLIGHT, PILOT REPORTED FUEL FLOW DISCREPANCY AND ENGINE ROUGHNESS AND RETUNRED TO BASE FOR A PRECAUTIONARY, ALBEIT IF VERY STRESSFUL, LANDING. UPON INSPECTION OF THE FUEL FLOW SENSOR ( PART OF THE JPI 930 ENGINE INSTRUMENTAION - STC SA01435SA ) IT WAS SDR 2023FA0000000Contactor · failed0.0 TSMO OVH MAG INSTALLED ON 0.0 TSMO IO550F AT ENG CHANGE. TEST FLIGHTS AND GROUND RUNS ALL OK. 28.7 HOURS LATER MAG WAS REMOVED FOR MAJOR ROUGHNESS, INABILITY TO IDLE, AND MULTIPLE CYLINDERS WITH ERRANT TEMPERATURES. POINT CONTACTOR PAD IN STAMPED ARM WAS SDR CA190402009Bearing Race · corroded(CAN) ENGINE COULD NOT ATTAIN TAKE OFF RPM. PROPELLER WAS REMOVED AND BENCH TESTED. IT WAS FOUND THAT IT WOULD NOT CYCLE INTO FINE PITCH. UPON DISASSEMBLY IT WAS FOUND THAT THE BEARING RACES, RETAINERS AND BALLS WERE SEVERELY CORRODED. PROPELLER WAS REASSEMBLESDR 2019FA0000168Nut · defectiveATTACHMENT NUTS SUPPLIED WITH ATTACHMENT KIT (P/N KPL2001) FAILED BEFORE REACHING RECOMMENDED TORQUE (180-220 IN LBS). THE NUTS SEEM VERY SOFT.SDR 4DSR2018081000002Fitting · crackedDURING AN ANNUAL INSPECTION, AFTER REMOVAL OF THE RT MAIN GEAR TO FUSELAGE FAIRING FOR INSPECTION, FOUND THE GEAR ATTACHMENT OUTBOARD FITTING CRACKED. THE CRACK WAS IN THE WEB OR BODY OF THE PART AND NOT EMANATING FROM AN EDGE. REQUIRED MAGNIFICATION TO CONFIRSDR 4DSR2018081000001Line · chafedDURING ANNUAL INSPECTION, AFTER REMOVAL OF THE RIGHT MAIN GEAR TO FUSELAGE FAIRING, FOUND THE ALUMINUM BRAKE LINE SEVERELY GOUGED AND CHAFED. CHAFING ON THE FUSELAGE SKIN CUTOUT WHERE THE LEAF SPRING-TYPE GEAR PASSED THROUGH. THE BRAKE LINE WALL WAS OVER 90%SDR M2LA201806221001Cylinder · crackedACFT STARTED AND RUNNING FOR A TRAINING FLIGHT, PILOTS NOTICED A VIBRATION OF THE ENGINE AND NO CYLINDER HEAD TEMP OR EXHAUST TEMP ON NR 6 CYLINDER IAW THE ENGINE MONITOR. PILOTS SHUT ENGINE DOWN AND NOTIFIED MAINTENANCE. AFTER INSPECTION OF CYLINDER NR 6, BSDR 2017FA0000401Post · crackedDURING LOWER FWD DOOR POST AND STRUT FITTING INSPECTION REQUIRED BY SERVICE BULLETIN SEB935R1, FOUND A CRACK IN RADIUS OF CORNER ADJACENT TO AND DISAPPEARING UNDER THE STRUT FITTING.SDR 2016FA0000539Belt · shearedSQUEALING SOUND AT ENGINE START VOLTMETER SHOWING DISCHARGE. ALTERNATOR BELT WAS SHEARED.SDR 2015FA0000364Master Cylinder · crackedUPON LANDING, PILOT LOST RT BRAKE PEDAL ACTUATION AS WELL AS RT BRAKE CAPABILITIES. INITIAL GVI-VISUAL INVESTIGATION REVEALED RT BRAKE MASTER CYLINDER PISTON ROD PN 0541143, BROKEN AT BASE BELOW CLEVIS CHECK NUT PN 0541140. UPON DVI-VISUAL INSPECTION THE CLSDR CA140714002Oil System · malfunctioned(CAN) ENGINE REMOVED FOR TEARDOWN AND INSPECTION DUE PERSISTENT LOW OIL PRESSURE, HIGH OIL TEMPERATURE. AIRCRAFT REMOVED FROM SERVICE.SDR CA130930006Cylinder · cracked(CAN) JUST AFTER TAKEOFF, PILOT HEARD A LOUD BANG. PARTIAL POWER LOSS WAS NOTED AND THE ACFT RETURNED TO DEPARTURE. VISUAL INSPECTION HAS SHOWN SUBSTANTIAL OIL LOSS. THE NR 5 CYLINDER WAS FOUND TO HAVE CRACKED AND SEPARATED.SDR WU52013F00000Drag Link · brokenLINK-DRAG BROKEN AT WELDED JOINT.SDR CA130809002Spar · cracked(CAN) WHILE COMPLYING WITH SB SEB85-7, REV 3, TO REPLACE RT ELEVATOR TRIM TAB AND LT & RT T/E WEDGES DUE TO THE FOAM CORES WERE SATURATED, IT WAS DISCOVERED THAT THE AFT SPAR OF THE ELEVATOR, ITSELF, WAS CRACKED.SDR YN8R201301240001Cover · crackedDURING INSPECTION OF FLOATS, FOUND NUMEROUS CRACKS IN COVER REINFORCEMENTS ON FLOAT. CRACKS WERE AT THE OUTER ATTACHMENT THROUGH THE RIVET HOLES. UNKNOWN TIME ON FLOATS, AT LEAST 1200 HRS. THIS FLOAT HAD FOUR TOTAL CRACKED REINFORCEMENTS, BOTH LARGE AND SMASDR YN8R01242013RHBHReinforcement · crackedDURING INSPECTION OF FLOATS, FOUND NUMEROUS CRACKS IN COVER REINFORCEMENTS ON FLOAT. CRACKS WERE AT THE OUTER ATTACHMENT THROUGH THE RIVET HOLES. UNKNOWN TIME ON FLOATS, AT LEAST 1200 HRS. THIS FLOAT HAD 6 TOTAL CRACKED REINFORCEMENTS, BOTH LARGE AND SMALLSDR 2012FA0000522Attach Fitting · crackedDURING AN ANNNUAL INSPECTION, FOUND A .7500" CRACK IN THE LT MAIN LANDING GEAR OUTBOARD ATTACH FITTING AS VIEWED THROUGH A FLOOR ACCESS PANEL. THE CRACK IS IN THE RADIUS OF THE FITTING AFT AND BELOW THE MLG SPRING. FOUND NO HISTORY OF A HARD LANDING.SDR 2012FA0000375Wire · burnedPILOT REPORTED SMOKE IN COCKPIT AND TERMINATED FLIGHT. FOUND WIRE PB7 FROM FIELD CIRCUT BREAKER TO ALTERNATOR SWITCH BURNED AND MELTED INTO WIRE BUNDLE. MELTING AND HEAT DAMAGED APPROX 10-12 WIRES IN THE BUNDLE. VOLTAGE REGULATOR FAILURE CAUSED THE 24 GA WSDR 2012FA0000157Bolt · looseDURING TROUBLESHOOTING FOR ALTERNATOR NOISE, INSPECTED ALTERNATOR AND FOUND BOLT LOOSE INSIDE ALTERNATOR CASE. REMOVED ALTERNATOR AND DISASSEMBLED, FOUND DIODE RECTIFIER BRIDGE BOLT HAD BACKED OUT AND HAD CONTACTED THE ROTOR, BENDING THE BOLT AND ELONGATING TSDR 2012FA0000068Governor · disintegratedPROP GOVERNOR BEARING IN THE IDLER PART OF THE OIL PUMP DISINTEGRATED.SDR 2011FA0000270Nut · looseSHORTLY AFTER INSTALLATION, THE ENG BEGAN AN OIL LEAK, UP FRONT ON THE RT SIDE NEAR THE OIL COOLER. OIL COOLER WAS REMOVED, FOUND THAT THE NUTS THAT HOLD THE OIL COOLER ADAPTER WERE LOOSE AND COULD BE REMOVED BY HAND. THIS ENGINE HAD 39.1 HOURS TSN ON IT WHESDR 2010FA0001222Magneto · failedTHIS O/H MAGNETO WAS INSTALLED ON THE ACFT IAW MM AND STANDARD PRACTICES, TIMED TO ENG IAW MM. THE ENGINE WAS RUNUP IAW POH AND THE MAG CHECK WAS SATISFACTORY. THE ENGINE WAS SHUTDOWN AND COWLING INSTALLED. AT THE NEXT ENGINE STARE, THE LT MAGNETO FAILED TOSDR 2011FA0000153Throttle Control · looseTHROTTLE CONTROL ASSEMBLY - ON AFT END OF THE CONTROL, THE PILOT END OF THE PUSH/PULL CONTROL - THE THREADED ALUMINUM ATTACH FITTING IS LOOSE ON THE STEEL SLEEVE, NORMALLY A TIGHT FIT. ON THE FWD END OF THE CONTROL - THE ENGINE ATTACHMENT END , THE SLEEVE ISSDR CA100114004Alternator · failed(CAN) ALTERNATOR FAILED DURING FLIGHT. ELECTRICAL POWER LOSS INDICATED TO CREW. CREW RETURNED FOR LANDING AT CYTZ. (TC NR 20100114004)SDR 2009FA0000761Ignition Switch · failedIGNITION SWITCH FAILED TO SHUT-OFF MAGENTO DURING A PRE-FLIGHT MAGNETO CHECK AND FAILED AT 1201.1 HOURS SINCE NEW . THE REQUIRED DIODE ON THE STARTER SOLENOID WAS INSTALLED PER THE AD/SERVICE BULLETIN SO THIS SWITCH SHOULD NOT HAVE FAILED AT 1201.1 HOURS.SDR 2009FA0000712Cylinder · peelingCYLINDER BARREL PEELING FOUND AFTER A LOW COMPRESSION TEST. THE BARREL PEELED IN AN AREA APPROX 2 INCHES WIDE. THE METAL CONTAMINATED THE ENG LUBRICATION SYS REQUIRING A COMPLETE TEARDOWN OF THE ENG. THIS CYL WAS INSTALLED AT ENG O/H ON 5/30/2009. (K)SDR CA090707002Aneroid · failed(CAN) FUEL PUMP ANEROID FAILED CAUSING ERRATIC FUEL FLOWS.SDR M2L2009F00000Hinge Bracket · brokenTHIS PART HAS 2 SMALL 90 DEGREE ANGLES AT EITHER SIDE BOTTOM. THEY HAVE LITTLE OR NO ACTUAL STRENGTH OTHER THAN TO PREVENT THE LOWER WING SKIN FROM NOT BEING SECURED. RT AILERON OTBD HINGE BRACKET. (K)SDR M2L2009F00001Hinge Bracket · brokenTHIS PART HAD 1 OR 2, 90 DEGREE ANGLES ON THE BOTTOM SIDE, CRACKED. THIS WAS CAUSED MOST LIKELY FROM YEARS OF FATIGUE. DON`T THINK THIS WOULD HAVE CAUSED AN AIRWORTHINESS CONCERN AS IT DOES NOT APPEAR TO HAVE WEAKENED THE ATTACHMENT OF THE HINGE BRACKET. THSDR 2009FA0000198Cylinder · crackedNR 4 CYLINDER BARREL CRACKED APPROX. 1INCH FROM THE TOP OF THE BARREL AND ALMOST .7500 INCH OF THE WAY AROUND THE INSIDE CIRCUMFERENCE. THIS WAS A NEW ECI FREEDOM STEEL BARREL CYLINDER. THE CYLINDER HAS TEST CELL AND GROUND RUN TIME ONLY, WHEN THE MECHANIC NSDR 2008FA0000565Intake Duct · crackedMFG SUPPLIED ENGINE INTAKE DUCT BEFORE THE AIR FILTER IS SUBJECT TO CRACKING IN MULTIPLE LOCATIONS. THIS PARTICULAR AC AND ANOTHER IDENTICAL MODEL AC THIS FACILITY MAINTAINS, HAVE BEEN CONVERTED TO ANOTHER ENGINE AFTER THE STC CONVERSION. CRACKING PROBLEM HASDR 2008FA0000554Intake Duct · crackedMANUFACTURER SUPPLIED ENG INTAKE DUCT BEFORE THE AIR FILTER IS SUBJECT TO CRACKING IN MULTIPLE LOCATIONS. THIS PARTICULAR ACFT AND ANOTHER IDENTICAL MODEL ACFT THIS FACILITY MAINTAINS HAVE BEEN CONVERTED TO AN IO-550-F ENG. AFTER THE STC CONVERSION, THE CRACSDR 243DR1Servo · misinstalledWHILE UNDERGOING A SCHEDULED INSPECTION, MECHANIC FOUND ELEVATOR TRIM SYS WAS MISRIGGED. TRAVEL LIMITS WERE NOT CORRECT AND WERE ACTUALLY RIGGED OPPOSITE WITH REGARDS TO MAX TRAVEL UP/DOWN. TRAVEL LIMITS IN MM NR D2070-3-13 FIGURE 1-1 WERE MISINTERPRETED, MFG SDR CA070119010Spar · failed(CAN) DURING REPLACEMENT OF LOWER OB SKIN, EDGE DISTANCE OF RIVETS THROUGH LOWER FLANGE LESS THAN MINIMUM ALLOWED IN 32 PLACES FROM STAT. 100.0 TO STAT. 154.00 REPLACEMENT OF PARTS REQUIRED TO REPAIR PROBLEM. (TC NR 20070119010)SDR CA070119009Spar · failed(CAN) EDGE DISTANCE OF RIVETS ON LOWER FLANGE LESS THAN MINIMUM ALLOWED. REPLACEMENT OF PART REQUIRED TO REPAIR PROBLEM. (TC NR 20070119009)SDR CA061218014Seal · leaking(CAN) BLADE GREASE SEAL FAILED. GREASE LEAVING HUB. PROP REMOVED AND SENT TO REPAIR FACILITY WHERE NEW SEALS WERE INSTALLED. PROP REINSTALLED AND A/C SERVICEABLE (TC NR 20061218014).SDR 2006ADP09001Wire Harness · crackedDURING INSPECTION ON A NEW, LOW TIME ENGINE, THE MT NOTICED A RATHER LARGE CRACK IN THE RT IGNITION HARNESS COVER, WHERE THE HARNESS ATTACHES TO THE MAGNETO. AFTER LOOKING A LITTLE CLOSER, IT IS CLEAR THAT THE CRACK WAS THERE PRIOR TO OVERHAUL AND PAINTING. SDR MPVMANIFOLDFuel Divider · leakingFUEL MANIFOLD VALVE IS LEAKING FROM THE VENT PORT.SDR 2006ADP001Cylinder · crackedALL SIX CYLINDERS HAVE CRACKS IN THE SAME AREA JUST ABOVE THE TOP SPARK PLUG HOLE.SDR MAFALT4Rotor · failedELECTROSYSTEM WOES CONTINUE, WITH ANOTHER ROTOR GOING BAD. DETAILS: M/N DOFF10300BR S/N B110413 WITH A TS0 :1095.1 ON THE ALTERNATOR. THE ROTOR WAS CHANGED 3 DIFFERENT TIMES ON THIS ALTERNATOR AND IT RAN ON FOUR DIFFERENT A/C IN IT'S LIFE HERE. THIS LAST ROSDR GAJ2005F00001Control Cable · frozen3/25/04, HOBBS 3218.1, TTAF 9745.1, REMOVED AND REINSTALLED ENGINE, THROTTLE, MISTURE AND PROP CONTROLS. 7/22/04, HOBBS 3417.7, TTAF 9944.0, VERNIER CONTROL RELEASE BUTTON FROZE IN PUSHED POSITION, REMOVED MIXTURE CONTROL CABLE AND REPLACED WITH NEW. 8/12/05SDR DUKESPUMPMPGPump · leakingPUMP IS LEAKING AT THE SEAL AT THE BASE OF THE PUMP, NEAR DRAIN PIPE.SDR DUKESPUMPPKMPPump · leakingPUMP IS LEAKING AT THE SEAL AT THE BASE OF THE PUMP-NEAR/AT DRAIN PIPE.SDR MAFALT3Wire · openOPEN FIELD WINDING AT SLIP RING (WIRE BROKEN AT SOLDER JOINT).SDR MAFALT2Alternator · openOPEN FIELD WINDING AT SLIP RING (WIRE BROKEN AT SOLDER JOINT).SDR MAFALT1Alternator · openOPEN FIELD WINDING.SDR CA050324006Counterweight · failed(CAN) ROLLER RETAINER AND SNAP RING CAME OUT OF CLUT, RELEASING ROLLER IN 5TH ORDER CWT. (NO DAMAGE TO PARTS, POSSIBILITY WAS NOT INSTALLED CORRECTLY.) ROLLER MIGRATED TO REAR OF ENGINE AND JAMMED BETWEEN 6TH ORDER CWT AND ENGINE CASE STOPPING ENGINE. CRANKSHSDR TCMMAQ2Magneto · deformedCOIL WEDGES OVERDRIVEN TO THE POINT OF CONTACT WITH COIL, CRACKING THE INSULATION.SDR TCMMAQ1Magneto · deformedCOIL WEDGES OVERDRIVEN TO THE POINT OF CONTACT WITH COIL, CRACKING THE INSULATION.SDR M2L2005F00000Fitting · crackedTHIS IS A RESULT OF HARD USE FOR MANY YEAR IN BACK COUNTRY. THE CRACKS WERE FOUND AT A PHASE II INSPECTION. THESE PARTS HAVE SERVED THEIR USEFUL LIFE AND SHOULD BE CHANGED WITH THIS MUCH TIME AND HARD USE. LANDING GEAR FITTINGS, LT AND RT, OB. (NM1120040361
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