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 = '182T' 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 = '182T' 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 2011FA0000219Points · corrodedAT THE LAST ANNUAL INSP, FOUND THE RT MAG POINTS PITTED AND REPLACED WITH A NEW SET OF M-3081 POINTS. CUSTOMER CALLED AS WAS HAVEING PROBLEMS WITH THE RT MAG, DEAD, NO SPARK. UPON INVESTIGATION, THE PROBLEM WAS THE POINTS TAB WAS BROKEN AND LAYING IN THE CASSDR 2011FA0000140Distributor Blk · burnedREMOVED LEFT MAGNETO FOR 500 HOUR INSPECTION AND FOUND DISTRIBUTOR BLOCK ASSEMBLY BURNED THROUGH AND PIECES FLOATING AROUND INSIDE MAGNETO. LARGE AMOUNT OF DUST COATED SURFACES AND BURNING EVIDENT ON COIL AND ROTOR HOUSING. CARBON BRUSH AND CAM ARE EXTREMELYSDR JRUR2011030119HPGasket · leakingRED DYE LEAKING FROM TWO SCREWS THAT ATTACH THE PROPELLER BALANCE RING TO THE HUB. THE PROPELLER HAS 640.1 HOURS SINCE OVERHAUL. THE PROPELLER HAS THE (OLD) STYLE HUB GASKET THAT REQUIRES A BLACK PERMATEX SEALANT TO BE USED.SDR JRUR2010122019HPDoubler · cracked(JRUR) A 1.5 INCH LONG CRACK WAS DISCOVERED IN THE FIREWALL FWD DOUBLER (PN 0753600-24). THE CRACK WAS LOCATED ON THE LOWER LT QUADRANT OF THE FWD FIREWALL DOUBLER. THE CRACKED LOCATION CAN BE FOUND BY LOCATING THE "BRACKET-PARKING BRAKE CONTROL" AFT OF THE SDR JRUR2010121518HPDoubler · crackedA CRACK WAS DISCOVERED IN THE FIREWALL FORWARD DOUBLER. THE CRACK IS LOCATED BEHIND THE "COWL EXIT RAMP- RIGHT HAND" (P/N 0752732-2 SEE MANUFACTURE IPC REV 19 53-10-00 ITEM 241). THE LONGEST SECTION OF CRACK IS 6 INCHES LONG. THERE IS ALSO A SECONDARY CRACK (3SDR 2010FA0001081Display · failedTHE MFD (RT SEAT) WOULD NOT ALLOW FOR FREQUENCY CHANGES ON BOTH THE NAV AND COM. THE PFD (LT SEAT) CONTINUED TO WORK FINE. ONCE THE NEW FREQUENCIES WERE TUNED IN ON THE LT, THE RT WOULD THEN WORK AND ALLOW FOR FREQUENCY CHANGES. THE G1000 WAS 4 YEARS OLD, WSDR JRUR20101215910HPDoubler · cracked(JRUR) A CRACK WAS DISCOVERED IN THE FIREWALL FWD DOUBLER (PN 0753600-24). THE CRACK WAS LOCATED BEHIND THE COWL EXIT RAMP- RT (PN 0752732-2). THE CRACK WAS 2-3 INCHES LONG. THIS AREA IS VERY DIFFICULT TO INSPECT ON A P1 (50 HR) WITH THE LOWER COWLING INSTALLSDR 2010FA0000513Brushes · wornUPON DISASSEMBLY OF THE RT MAGNETO FOR RECOMMENDED 500 HR. MAGNETO INSPECTION, FOUND THE DISTRIBUTOR BRUSH BADLY WORN. WEAR IS EXACTLY AS DESCRIBED IN SB3-08A FIG 1, ALTHOUGH MORE EXTREME. THIS MAGNETO SN AND MFG DATE ARE WELL OUTSIDE OF THE AFFECTED APPLICABISDR 2010FA0000512Brushes · wornUPON DISASSEMBLY OF THE LT MAGNETO FOR RECOMMENDED SLICK 500 HR. MAGNETO INSP, FOUND THE DISTRIBUTOR BRUSH BADLY WORN AND ABOUT TO BREAK OFF. WEAR IS EXACTLY AS DESCRIBED IN SB3-08A FIG 1, ALTHOUGH MUCH MORE EXTREME. THIS MAGNETO SN AND MFG DATE ARE WELL OUTSSDR 2010FA0000211Oil Filter · inoperativeWHILETRYING TO TIGHTEN A NEW OIL FILTER ONTO ENGINE, THE FILTER WOULD GET PARTIALLY TIGHT THEN POP LOOSE. REMOVED OIL FILTER TO FIND CENTER MOUNTING STUD HAD BROKEN LOOSE. REMOVED OIL FILTER TO FIND CENTER MOUNTING STUD HAD BROKEN LOOSE AND STRIPPED THREADS SDR DYCR020099Pitot Line · meltedPILOT REPORTED LOW AIRSPEED INDICATION DURING TAKEOFF, CONTINUED FLIGHT TO ALTITUDE AND NOTICED THAT A/S INDICATION WAS SLOWLY DROPPING. KNOWING THAT THE PROBLEM WAS INDICATION ONLY, THE PILOT LANDED WITHOUT INCIDENT. MX INVESTIGATED THE CAUSE OF THE PROBLEM SDR 2009FA0000992Line · chafedCOPILOT’S RUDDER PEDDLE COVER IS CHAFING INTO THE FUEL LINE. THIS CHAFING IS CAUSED BY INSUFFICIENT CLEARANCE OF THE RUDDER PEDDLE COVER AND THE FUEL LINE. THE SAME CONDITION HAS BEEN FOUND ON TWO OTHER AIRCRAFT. CORRECTED THE PROBLEM BY TRIMMING THE RUDDERSDR 2009FA0000991Line · chafedCOPILOT’S RUDDER PEDDLE COVER IS CHAFING INTO THE FUEL LINE. THIS CHAFING IS CAUSED BY INSUFFICIENT CLEARANCE OF THE RUDDER PEDDLE COVER AND THE FUEL LINE. THE SAME CONDITION HAS BEEN FOUND ON 2 OTHER ACFT, SN 1821675 AND SN 1821622. WE CORRECTED THE PROBLESDR 2009FA0000514Exhaust Valve · stuckDURING COMPLIANCE OF SB 388C, 3 EXHAUST VALVE GUIDES FAILED TO HAVE SERVICEABLE MEASUREMENTS. NR 4 CYL EXHAUST VALVE STUCK FULLY CLOSED. VALVE MOVEABLE WITH MINIMAL PRESSURE, NO DAMAGE TO OTHER COMPONENTS. NR 6 CYL EXHAUST VALVE GUIDE CLEARANCE MEASURED .03SDR 2009FA0000513Exhaust Valve · stuckNR 6 CYLINDER EXHAUST VALVE STUCK DURING TAKEOFF CLIMB. PILOT NOTED A SEVERE VIBRATION WHEN POWER WAS REDUCED AS HE LEVELED OFF. PILOT IMMEDIATELY RETURNED TO THE AIRPORT AND LANDED. VISUAL INSP REVEALED THAT THE NR 6 CYL EXHAUST VALVE HAD STUCK. PUSH ROD AND SDR 2008FA0000735Gear · damagedWHILE PERFORMING SB03-08, FOUND THE DISTRIBUTOR GEAR DRIVE GEAR WEARING PREMATURELY AND CAUSING GEAR DUST INSIDE MAGNETO. GEAR MATERIAL WAS COMING OFF CAUSING IT TO COLLECT INSIDE DISTRIBUTOR CAP. ALSO, FOUND EXCESSIVE AMOUNT OF OIL INSIDE MAGNETO. REPLACED MASDR 2008FA0000612Bearing · burnedREMOVED MAGNETO TO S/B3-08 AND MFG 500 HOUR INSPECTION. REMOVED HARNESS CAP FOUND A LIGHT SMOKE COLORED FILM COVERING CAP AND DISTRIBUTOR BLOCK. REMOVED MAGNETO FROM ENGINE FOUND BEARING BAR BURNED THROUGH ON LEFT SIDE WHEN VIEWED FROM DRIVE END. (K)SDR 2008FA0000414Injector · cloggedPLANE LOST ENGINE POWER, BECAME VERY LEAN, COULD NOT GET FUEL FLOW> 9 GPH. TURNED OUT TO BE ALUMINUM SHAVING FROM ORIGINAL MFG OF FUEL SERVO. CLOGGED MIXTURE HOLE INSIDE FUEL SERVO. THIS WAS A DEFECT FROM TIME OF MANUFACTURE OF FUEL SERVO. EMERGENCY LANDINGSDR 2008FA0000404Distributor Blk · misrepairedDURING INTERNAL MAGNETO INSPECTION, FOUND DISTRIBUTOR BLOCK SPOT FACED AREA FOR POLES. APPEARS TO BE INCORRECTLY SPOT FACED. MATERIAL THAT WAS LEFT BEHIND HAS THE SAME LOFT AS BEARING BOSS AREA ON DISTRIBUTOR BLOCK. THIS CAUSES THE FINGER ON THE DISTRIBUTORSDR 2008FA0000270Attach Fitting · crackedDISCOVERED CRACK DURING ANNUAL INSPECTION. (2) LONG CRACKS APPROXIMATELY (1) INCH ON (1) SIDE OF THE FITTING ONLY, (1) AT THE LT LOWER ATTACHMENT AND THE OTHER JUST AFT AND LT OF THE AREA WHERE THE STRUT BARREL IS SECURED. SUSPECT HARD LANDING BUT NO OTHER SDR CA080320007Gasket · looseAD2008-06-51 FUEL INJECTION SERVO PLUGS, SERVO PLUGS FOUND LOOSE UPON INSPECTION. SERVO PLUG SEALS REPLACED WITH NEW AS PER THE CONVERSATION WITH PRECISION AIRMOTIVE REPRESENTATIVE. ENGINE REMANUFACTURE DATE OF SEPT 8, 2004 DOES NOT FALL WITHIN THE DATES SPESDR PAI52008S4877Support Fitting · brokenPILOT COMPLAINED OF NOSE WHEEL SHIMMY. INSPECTION FOUND RIGHT-HAND SIDE OF NOSE GEAR LOWER SUPPORT FITTING BROKEN.SDR 2007FA0000963Fitting · chafedLOWER STRUT SUPPORT FITTING CLAMPING RING CENTER BORE IS NOT CENTERED. THIS CAUSES THE STEERING COLLAR AND LOWER STRUT SUPPORT TO CHAFE AND FOR METAL TO METAL CONTACT TO OCCUR. HAVE TRIED TWO OTHER NEW LOWER STRUT SUPPORT FITTING RESULTING WITH METAL TO METASDR 2007FA0000810Strut · leakingFOUND NOSE STRUT ASSEMBLY LEAKING. REMOVED STRUT ASSEMBLY FROM AIRCRAFT. ASSEMBLED WITH PN TCNS-1 SEAL KIT IWA SRM AND MM. RELEASED TO AC OWNER. OWNER FOUND FLUID NR 4 ON WHEEL FAIRING AFTER TAXI TO HANGAR. INSPECTION FOUND FLUID COMING FROM BEHIND NOSE GSDR 2007FA0000642Line · leakingFOUND HEAVY FUEL STAIN FROM OIL COOLER NR 5 INTAKE PIPE AND ON FIREWALL APPROVED TO BE NR 5 INTAKE PIPE. FURTHER INSPECTION FOUND NR 5 FUEL INJECTION LINE LOOSE AT INJECTOR. FOUND AND SNUGGED SEVERAL OTHER INJECTOR LINES AT INJECTOR AND FLOW DIVIDER AD-02-01SDR 2007FA0000691Alternator · failedAC ARRIVED AT 1R4 WITH A FAILED ALTERNATOR. SYSTEM WAS TESTED TO CONFIRM THAT THE ALTERNATOR WAS THE PROBLEM. ON 6/25/07 THE ALTERNATOR IN QUESTION WAS REMOVED FROM THE AC. UPON REMOVING THE ALTERNATOR THE TECHNICAN FOUND THE SAFETY LOCK WIRE FOR THE ALTERNSDR BUW2007F00002Fitting · looseDURING THE INSPECTION FOR SB 07-71-01 THE FUEL RETURN LINE AT THE FIREWALL BULKHEAD FITTING WAS FOUND LOOSE. (K)SDR BUW2007F00001Return Line · looseDURING THE INSPECTION FOR SB 07-71-01 THE FUEL RETURN LINE AT THE FIREWALL BULKHEAD FITTING WAS FOUND LOOSE. (K)SDR 2007FA0000219B-Nut · looseIN THIS CASE, FOUND THAT THE B-NUT CONNECTING TO THE FUEL CONTROL FROM THE SPIDER WAS LOOSE. IT WAS NOT LEAKING, BUT REQUIRED A THIRD OF A TURN TO TORQUE DOWN TO PROPER TORQUE. NO OTHER WORK HAS BEEN DONE TO THE SPIDER OR FUEL CONTROL BECAUSE I HAVE DONE THESDR 2007FA0000200Support · crackedFOUND BATTERY SUPPORT CRACKED. TOTAL AIRFRAME TIME 1716. THIS IS THE THIRD ONE THAT WE FOUND SUPPORTS NEED TO BE BEEFED UP, THEY ARE TOO LIGHT FOR THE APPLICATION. (K)SDR 2007FA0000199Support · crackedFOUND BATTERY SUPPORT CRACKED. TOTAL AIRFRAME TIME 1075. THIS IS THE 3RD ONE THAT WE FOUND. SUPPORTS NEED TO BE BEEFED UP, THEY ARE TOO LIGHT FOR THE APPLICATION. (K)SDR 2006FA0001235Valve Guide · stuckPERFORMED COMPRESSION CHECK ON ENGINE AND HAD 5/80 PSI ON NR 6 CYL, STAKED EXHAUST VALVE AND GOT 78/80. PERFORMED SB 388C AND HAD TO REAM VALVE GUIDES TO GET WITH-IN LIMITS OF SB. IT WAS ONLY 200 HRS SINCE LAST SB COMPLIANCE.SDR 2006FA0001222Starter · malfunctionedSTARTER STUCK IN ENGAGED MODE.SDR 2006FA0001013Valve Guide · leakingOPERATOR COMPLAINED OF AN OIL LEAK. WHEN COWL WAS REMOVED IT WAS OBVIOUS THAT THE NR3 AND NR4 EXHAUST PUSH RODS AND PUSH ROD HOUSING WERE BENT. SUSPECTED STICKING EXHAUST VALVES. EXHAUST VALVE TO GUIDE CLEARANCE WAS CHECKED ON ALL CYLINDERS IAW SB AND THE PSDR 2006FA0000993Exhaust Valve · stuckDURING A PHASE 2 INSPECTION, CYLINDER NR 5 WAS FOUND TO HAVE LOW COMPRESSION (10/80) WITH A STRONG LEAK PASSED THE EXHAUST VALVE. SUBSEQUENT INSPECTION FOLLOWING THE INSTRUCTIONS FOUND IN LYCOMING SB 388C REVEALED THAT THE EXHAUST VALVE WAS PARTIALLY STUCK ANSDR 2006FA0000257Autopilot Sys · intermittentINTERMITTENT PITCH TRIM AND ACCELEROMETER FAILURES. POSSIBLY CAUSED BY INADEQUATE CONNECTOR ENGAGEMENT WITH THE MOUNTING RACK CONNECTORS, CAUSED BY IMPROPER POSITIONING OF THE TOP COVER.SDR 2006FA0000108Control Cable · chafedAT AC STA 22 LWS 3 INCHES, 3.75 INCHES BELOW CABIN FLOOR, ELEVATOR TRIM CONTROL CABLES CHAFING HARD ON BOTTOM SURFACE OF .2500 DIA FUEL TUBE AT LEFT AND AFT OF AIRCRAFT FUEL SELECTOR. IF LEFT CONTROL CABLE WILL CUT THRU FUEL TUBE (CAUSE) NOT SEEN AT FACTORY.SDR 2005FA0001587Actuator · misdrilledMFG MANDATES THE REMOVAL DISASSEMBLY, AND INSPECTION OF THE ELEVATOR TRIM ACTUATOR AT 1000 HRS TT OR 6 YEARS. UPON REMOVAL OF THIS ACTUATOR, FOUND THAT THE GROOVED PIN HOLES IN HOUSING WERE MISDRILLED. THIS CAUSED THE PIN TO WEAR INTO THE ACTUATOR HOUSING. SDR 2005FA0001429Wire · chafedTRANSPONDER CIRCUIT BREAKER POPPED AND PILOTS NOTED SMOKE IN CABIN. FLIGHT WAS DISCONTINUED AND DISCREPENCY WAS NOTED. AFTER INSPECTION, CHAFFED WIRE WAS FOUND NEAR THE AVIONICS RACK THAT HAD SHORTED ON THE AIRFRAME. THE WIRES WERE REPAIRED IAW MFG RECOMMENSDR 2005FA0000898Housing · leakingAFTER ENGINE INSTALLATION, 2 HOURS INTO BREAK IN PERIOD, OIL LEAK DISCOVERED IN BOSS OF CAMSHAFT IDLER GEAR. LT MAY ADAPTER BASE, CUT TOO WIDE; HOLE THROUGH TO SHAFT SUPPORT OF IDLER GEAR. (K)SDR 2005FA0000768Probe · loose"OMEGA" BRAND NAME OF CONNECTORS USED ON THE ALCOR CHT/EGT PROBES. THE SCREWS THAT HOLD THE CONNECTOR AND CONNECTION OF THE WIRE FOR THE PROBES WILL WORK LOOSE CAUSING A FALSE OR NO INDICATION ON THE G-1000 SYSTEM. NEEDS TO HAVE SOMEWAY TO LOCK THE SCREWS INTOSDR 2005FA0000613Servo · chafedDURING MFG 200 HOUR INSPECTION FOUND THE AUTOPILOT SERVO CABLE IN THE RT WING RUBBING ON SERVO CABLE GUARD ALMOST RUBBING THRU ONE LEG OF GUARD. INSPECTED CABLE FOUND OK. INSTALLED A NEW GUARD AND CLOCKED TO CORRECT POSITION ON SERVO. (CE07200512741) (K)SDR 2005FA0000625Bushing · splitINNER RUBBER/ PLASTIC MATERIAL NOTED PROTRUDING FROM BOTH SIDES OF BUSHING. MATERIAL INSIDE BUSHING SPLITTING IN SEVERAL AREAS. LT MLG BUSHING ONLY, RT MLG BUSHING APPEARS NORMAL. (K)SDR 2005FA0000617Probe · failedDURING FLIGHT, FUEL INDICATIONS WOULD RED-X OUT AND INDICATIONS SHOWING QUANITY JUMPED AROUND LT AND RT SIDE. TROUBLESHOT, AND REPLACED PROBES/ SENDERS IAW MFG. CALIBRATED IAW MFG MM. OPS CHECK OK. NOTE: NEED IMPROVEMENT IN TROUBLESHOOTING PROCEDURES IN MMSDR 2005FA0000615Probe · inoperativeDURING LEAN FIND FOR G-1000 WOULD NOT INDICATE NR1 AND NR2 ENGINE CYLINDERS. TROUBLESHOT, USED EGT/CHT TESTER AND FOUND PROBES BAD ALSO SHIP SIDE CONNECTOR WAS ALSO BAD, FOUND SCREWS LOOSE INSIDE CONNECTOR. REPLACED NR1 AND NR2 ENGINE CYLINDER PROBES AND COSDR 2005FA0000614Connector · looseTACHOMETER INDICATION JUMPS AROUND IN FLIGHT. INSTALLED A NEW TACHOMETER CONNECTOR, IAW MFG SL. OPS CHECK OK. (CE07200512734) (K)SDR 2005FA0000610Wire · brokenFOUND ORANGE WIRE FOR THE LOW VOLT ANNUNCATOR FOR THE G-1000 BROKEN INSIDE THE J-BOX WOULD NOT CAUSE THE ANNUNCATOR TO LIGHT UP ON THE PFD (PILOTS FLIGHT DISPLAY). APPEARS WIRE HAVE CHAFED ON J-BOX TO BREAK WIRE. ADDRESSED AND CORRECTED AS REQUIRED. (CE0720SDR 2005FA0000518Pump · failedRECEIVED BOOST PUMP FOR WARRANTY CREDIT WITH A CUSTOMER COMPLAINT OF (FUEL BOOST PUMP POPS CIRCUIT BREAKER). PRELIMINARY INSPECTION OF THE PUMP REVEALED FOREIGN MATERIAL IN THE INLET PORT. FURTHER INSPECTION REVEALED THE FOREIGN MATERIAL TRIED TO PASS THROUGSDR 18HPControl Unit · defectiveWHILE RUNNING UP AIRCRAFT AFTER MAINTENANCE, IT WAS NOTICED THAT THE FUEL QTY GAGES WERE JUMPING FROM FULL TO EMPTY AND THE LOW FUEL LIGHT WAS FLASHING. BOTH TANKS WERE FULL AT THE TIME. INSTALLED NEW SENDING UNITS IN BOTH WINGS AND IT SEEMED TO REMEDY THE PSDR 2005FA0000612Pin · looseG-1000-3 PIN CONNECTOR FOR OIL PRESSURE TRANSDUCER, THE PINS WILL GET LOOSE AND CAUSE THE OIL PRESSURE INDICATION TO JUMP FROM 45 TO 110 PSI. TROUBLESHOT, RESET PIN TO SHRINK (SHIP SIDE). SUSPECT WILL HAVE PROBLEMS WITH THIS IN THE FUTURE DUE TO VIBRATION OF
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