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 = '172R' 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 = '172R' 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 CA021010004Impulse Coupling · cracked(CAN) OUR MAINTENANCE SCHEDULE APPROVAL FOR 172R CALLS FOR MAG OVERHAUL AT 700 HOURS +/- 10 HOURS. AT 657.9 HR MAGS WERE CHANGED FOR ROUGH ENGINE (2-3 SEC) SNAG. AT OVERHAUL MAG IMPULSE COUPLINGS FOUND CRACKED AT HUB.SDR CA021022007Starter · shorted(CAN) PILOT REPORTED DURING PRE-TAKE-OFF RUN-UP: 'OVERCHARGING DURING RUN UP, COMPLETE ELECTRICAL MALFUNCTION 30 SEC. THEN COMPLETE ELECTRICAL FAILURE BURNING SMELL (PALASTIC RUBBER). CYCLED MASTER NO EFFECT, SHUTDOWN.' STARTER FOUND BURNED UP AND SHORTED, STSDR 2002FA0001084Manifold · malfunctionedTHE CREW REPORTED A MOMENTARY POWER ROUGHNESS. THE AIRCRAFT FUEL CONTROL SYSTEM AND IGNITION SYSTEM WERE INSPECTED. THE FUEL MANIFOLD WAS REPLACED ALONG WITH 2 INJECTOR NOZZLES. A GROUND OPERATIONAL CHECK WAS PERFORMED. FOLLOWING THAT A FUNCTIONAL CHECK FLIGHTSDR DF22002F00000Sensor · inoperativeNUMEROUS PILOT REPORTS OF LOW FUEL WARNING LIGHT FLICKERING IN FLIGHT, OFTEN TWO FAST TO DETERMINE IF LEFT OR RIGHT LIGHT. MAINTENANCE PERSONNEL UNABLE TO DUPLICATE ON GROUND. REMOVED LT FUEL QUANTITY SENDER FROM TANK AND MOVED FLOAT ARM BY HAND TO APPROX. SDR 2002FA0001065Pump · looseBOLTS LOOSE IN FUEL PUMP DIAPHRAGM.SDR 2002FA0001037Wire Harness · chafedWHEN THE PILOTS CONTROL COLUMN WAS PULLED AFT AND ROTATED, THE AILERON CABLE TURNBUCKLES AND ASSOCIATED HARDWARE CHAFED AGAINST A WIRE BUNDLE FORWARD OF THE INSTRUMENT PANEL. THIS CAUSED TWO WIRES FROM THAT BUNDLE TO SHORT OUT AND BREAK, THUS RESULTING IN SPASDR CA021022005Starter · stuck(CAN) STARTER NOT ENGAGING. STARTER REPLACED WITH SERVICEABLE UNIT. AFTER SENDING THE UNIT TO LAMAR FOR WARRANTY CONSIDERATION, AND TO DISCOVER WHAT WAS ACCTUALLY WRONG WITH THE UNIT, WE WERE INFORMED THE THE WARRANTY WILL NOT BE HONOURED. LAMAR DESCRIBED THASDR 2002FA0001088Engine · roughDURING FLIGHT, THE CREW REPORTED A ROUGH ENGINE. THE FLIGHT WAS TERMINATED AND MAINTENANCE WAS PERFORMED. THE SPARK PLUGS WERE CLEANED AND THE INJECTOR NOZZLES INSPECTED..SDR 2002FA0001018Alternator · failedTHE ALTERNATORS INSTALLED ARE FAILING CONSISTENTLY. THEY USUALLY LAST BETWEEN 100 AND 500 HOURS FOR WHATEVER REASON THE RESISTANCE IN THE FIELD CIRCUIT INCREASES TO THE (MEGA OHM) RANGE, RENDERING THE ALTERNATOR TOTALLY INOPERATIVE DUE TO THE NATURE OF THE WASDR MNZA0207008Reservoir · crackedUPON INSPECTION, IT WAS NOTED THAT A FUEL STAIN WAS EVIDENT ON THE UNDERBELLY OF THE AIRCRAFT IN THE VACINITY OF THE FUEL SELECTOR VALVE. CABIN FLOORING AND UPHOLSTERY WAS REMOVED AND THE FUEL SELECTOR AND FUEL RESERVOIR WAS REMOVED AND INSPECTED. THE RESEVOISDR 0207008Reservoir · rupturedUPON ROUTINE INSPECTION, IT WAS NOTED THAT A FUEL STAIN WAS EVIDENT ON THE UNDERBELLY OF THE AIRCRAFT IN THE FACINITY OF THE FUEL SELEVTOR VALVE. CABIN FLOORING AND UPHOLSTERY WAS REMOVED AND THE FUEL SELECTOR AND FUEL RESEVOIR PN 0516009-18 WAS REMOVED & INSPSDR 2002FA0000985Lock · weakTHE LOCK CYLINDER RECLINE MECHANSIM BECOMES WEAK OVER TIME. SEAT BACK WOULD RECLINE ABRUPTLY WHEN PRESSURE WAS APPLIED TO THE SEAT BACK, SUCH AS TAKEOFF. THIS COULD CAUSE THE PILOT TO LOOSE CONTROL OF THE AIRCRAFT.SDR 2002FA0000868Servo · inoperativeAFTER RECEIVING THE ENGINE BACK FROM MFG, YELLOW TAGGED, STICKERED IN THE LOG BOOK AIRWORTHY, REINSTALLED ENGINE. GROUND RUN FOR LEAKS BUT WOULD NOT IDLE SMOOTH UNTIL IDLE/MIXTURE WAS SET AT 625 RPM. OK`D TEST FLIGHT AND IT QUIT ON LANDING. THIS AIRCRAFT DSDR CA020619002Shaft · sheared(CAN) INVESTIGATION OF A SEVERE NOSEWHEEL SHIMMY REPORT REVEALED THAT THE SHIMMY DAMPENER SHAFT HAD SHEARED. BOTH HALVES OF THE ASSEMBLY REMAINED ATTACHED BUT THE UNIT COULD NO LONGER FUNCTION AS DESIGNED. THE FAULTY UNIT WAS REMOVED FROM SERVICE AND REPLACED SDR 2002FA0000784Seat · cracked1.5 INCH CRACKS ON COPILOTS SEAT CUSHION BASE. REPLACED WITH NEW PART WHICH IS TWICE AS THICK.SDR 0605023221Circuit Breaker · failedTHE OVERVOLTAGE SENSOR ACTIVATED, CLAMPING THE ACU POWER SUPPLY TO GROUND. THE ALTERNATOR CIRCUIT BREAKER FAILED TO TRIP. THIS RESULTED IN AN INFLIGHT ELECTRICAL FIRE WITH THE HARNESS BETWEEN THE J-BOX AND CIRCUIT BREAKER PANEL DAMAGED AS MULTIPLE CIRCUITS WSDR 2002FA0000674Switch · inoperativeHAD TO REPLACE THE PILOTS PUSH TO TALK SWITCH.SDR 2002FA0000673Switch · inoperativeREPLACED COPILOTS PUSH TO TALK SWITCH.SDR 2002FA0000672Switch · failedREPLACED PILOTS PUSH TO TALK SWITCH. 0510.2 TACH.SDR 2002FA0000507Skin · crackedCRACKS DEVELOPED IN TOP T/E LT WING SKIN AT EXTREME IB END OF WING AROUND 4 OF AN426AD4 RIVETS WHICH JOIN T/E STIFFENER TO UPPER AND LOWER WING SKINS JUST ABOVE FLAP. CRACKS RANGED FROM .500 INCH TO 1 INCH AND ONLY 1 PENETRATED A RIVET HOLE. ONE OF RIVETS, JSDR 2002FA0000399Manifold · detachedTHIS AIRCRAFT USES DUAL VACUUM PUMPS. THESE PUMPS ARE CONNECTED TO THE VACUUM SYSTEM VIA A MANIFOLD ASSEMBLY. THIS MANIFOLD PERFORMS TWO IMPORTANT FUNCTIONS, ONE TO ALLOW FOR A COMBINED SOURCE OF VACUUM FROM THESE TWO PUMPS, AS WELL AS PROVIDE AN ISOLATION FUNSDR 2002FA0000195Firewall · crackedDISCOVERED DURING AN ANNUAL INSPECTION THAT FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. ALMOST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF THE PROBLEM.SDR 2002FA0000194Firewall · crackedDISCOVERED DURING AN ANNUAL INSPECTION THAT THE FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. ALMOST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF THE PROBLEM.SDR 2002FA0000193Firewall · crackedDISCOVERED DURING AN ANNUAL INSPECTION THAT THE FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. ALMOST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF THE PROBLEM.SDR 2002FA0000191Firewall · crackedIT WAS DISCOVERED DURING AN ANNUAL INSPECTION THAT FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. ALMOST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF PROBLEM.SDR 2002FA0000223Roller · gougedDURING ACCOMPLISHMENT OF SB, THE LT FLAP INBOARD TRACK INBOARD AFT BEARING SUPPORT ARM WAS FOUND TO BE GOUGED .025 INCH DEEP MATCHING THE OUTER RADIUS OF THE ROLLER ASSEMBLY. THE ROLLER ASSEMBLY WAS FOUND TO HAVE THE INNER ROLLER CAGE OFFSET ENOUGH TO ALLOW TSDR 2002FA0000278Servo · malfunctionedREPORTED ENGINE LOST POWER TWICE (ENG RUNNING 1 HOUR).SDR 2002FA0000205Switch · intermittentREOCCURING INTERMITTENT PUSH TO TALK SWITCH OPERATION.SDR 2002FA0000152Pin · shearedWHILE REMOVING THE TRIM TAB ACTUATOR FOR SERVICE, BOTH GROOVE-PINS (P/N 3/32X.38TYPE3) WHICH ATTACH THE ROLL CHAIN SPROCKET, (P/N 0310332-0) TO THE SCREW-INTERNAL THREADS (P/N 1260049-1) OF THE TRIM TAB ACTUATOR WERE FOUND TO HAVE SHEARED. THIS ALLOWED THE SDR 2002FA0000186Firewall · crackedDISCOVERED DURING ROUTINE MAINTENANCE THAT THE LEFT LOWER FIREWALL HAD CRACK LOCATED BENEATH THE DOUBLER FOR THE LEFT LOWER COWL MOUNT. IN ONE INSTANCE, CRACK WAS ACTUALLY LOCATED BENEATH THE LEFT FLANGE OF THE BATTERY MOUNT.SDR 2002FA0000138Firewall · crackedIT WAS DISCOVERED DURING ROUTINE MAINTENANCE THAT THE LT LOWER FIREWALL HAD A NEARLY 3 INCH CRACK BENEATH THE CENTER, LOWER COWL MOUNT DOUBLER. THIS CONDITION WAS ALSO DISCOVERED ON THE NEXT FOUR LIKE AIRCRAFT AND THEY WERE ALL CORRECTED IN ACCORDANCE WITH SERSDR 2001FA0000686Cylinder · failedSEAT LOCK CYLINDER FAILED TO LOCK IN POSITION WITH NORMAL SEATBACK PRESSURE. CABLE ADJUSTMENT WITHIN LIMITS. FAILURE OCCURRED DURING NORMAL USE.SDR 2001FA0000571Nut Plate · brokenDURING 100 HOUR INSPECTION, TECHNICIAN FOUND LOWER ELEVATOR STOP NUTPLATE BROKEN AND FIBER LOCK PORTION OF PART SEPARATED FROM THE REST OF NUTPLATE DETAIL REPEATED ELEVATOR CONTACT WITH STOP BOLT WHEN AIRCRAFT IS PARKED AND CONTROL LOCK IS IN, SUCH AS IN WINDYSDR 2001FA0000494Connector · looseCOM 1 AND COM 2 INTERMITTENTLY INOPERATIVE. UPON INSPECTION FOUND SMALL COLLARS THAT COME WITH 90 DEGREE CONNECTOR LOOSE IN THE REAR OF BOTH COM 1 AND COM 2 COAX CONNECTORS.SDR 2001FA0000611Connector · inadequateCONNECTOR PB017, PN: S2800-275, WHICH ATTACHES SHIP WIRING TO J2 OF POWER JUCTION BOX MC01-2A, HAD INADEQUATE CRIMPS OF BOTH WIRE ENDS ATTACHING WIRES TO SOCKETS. SOCKET "A" HAD AN OPEN CIRCUIT WHICH CAUSED LOSS OF BUSS NR 2 H1014. WHEN PULLED ON, THE WIRESSDR 2001FA0000378Wire · burnedPILOT REPORTED LOSS OF HALF AVIONICS BUSS, SMOKE AND BAD ODOR IN COCKPIT. T/S, FOUND WIRE BURNT FROM NAV LIGHT C/B SWITCH TO PIN 11 OF THE JC001 CONNECTOR AND FROM PC001, PIN 11 TO JV001, PIN 1. RED LEAD FROM TAIL NAV LIGHT HOUSING SHORTED OUT TO NUT-PLATE SDR 2001FA0000352Buss · damagedPILOT REPORTED LOSS OF HALF OF AVIONICS BUSS, INCLUDING ONE NAV/COM AND GPS AND SMOKE AND A BAD ODOR IN THE COCKPIT. WIRE NR 2H1002 (22 GAUGE) BURNED FROM THE NAV. LIGHT C/B SWITCH TO PIN 11 OF THE JC001 CONNECTOR AND FROM PC001, PIN 11 TO JV001, PIN 1. TSDR 102401868Circuit Breaker · failedTHE TAIL LIGHT POSITIVE LEAD SHORTED TO GROUND BY CONTACT WITH A TINNERMAN NUT IN THE RUDDER. THERE WAS NO EVIDENCE OF TRAUMA TO THE WIRE. ONLY A PINPOINT OF CONTACT WAS EVIDENT THE NAV LIGHT BREAKER DID NOT TRIP AND THE WIRING BURNED FROM THE TAIL TO THE CSDR 2001FA0000309Injector · malfunctionedENGINE FAILED TO DEVELOP FULL POWER AFTER LONG POWER OFF DECENT AT HIGH DENSITY ALTITUDE CONDITIONS. CORRECTIVE ACTIONS TAKEN: FUEL INJECTOR SERVO REPAIRED BY CRS/NE2R WO R01-042240. FLOW DIVIDER MODIFIED IAW SI. C/W SI AND SB.SDR CA010831013Brushes · broken(CAN) - AIRCRAFT ALTERNATOR FAILED. - ALTERNATOR INTERIOR INSPECTION REVEALED A BROKEN BRUSH BLOCK ASSEMBLY CAUSED BY A INCORRECT INSTALLATIONSDR CA010831012Brushes · failed(CAN) - AIRCRAFT ALTERNATOR FAILED. - ALTERNATOR INTERIOR INSPECTION REVEALED A BROKEN BRUSH BLOCK ASSEMBLY CAUSED BY A INCORRECT INSTALLATION.SDR N3X2001F00000Bellcrank · looseBEARING HOUSING IS LOOSE IN BELLCRANK.SDR 2001FA0000171Check Valve · misinstalledWHEN FUEL TANKS WERE FILLED TO ABOVE 35 GALLONS, HIGH AMBIENT TEMPERATURE CAUSED FUEL TO LEAK FROM VENT TUBE. REMOVED LEFT FUEL BAY INSPECTION PLATE AND FOUND THAT THE FUEL VENT TUBE INVERTED CHECK VALVE S2359-1 ALSO INVERTED FROM FACTORY. ROTATED 180 DEGREESDR 2001FA0000172Hinge Pin · brokenDURING A PHASE II INSPECTION, FOUND LEFT AND RIGHT LOWER CABIN DOOR HINGE PINS, BROKEN. IT APPEARS THAT THE CABIN DOOR WAS NOT INSTALLED PROPERLY FROM THE FACTORY, CAUSING UNDUE STRAIN ON LOWER HINGES.SDR 2001FA0000102Gyro · failedGYRO TUMBLED IN FLIGHT AND WOULD NOT RE-ERECT. MAINTENANCE TROUBLESHOOTING REVEALED NO DEFECTS WITH INSTRUMENT AIR SYSTEM. GYRO WAS REPLACED WITH A SERVICEABLE OVERHAULED UNIT. SYSTEM RETESTED AND REPLACEMENT GYRO FUNCTIONS NORMALLY. AIRCRAFT AND SYSTEM HSDR 20010605CW016Tachometer · out of toleranceNEW TACHOMETERS OUT OF MFG 50 RPM TOLERANCES. DIGITAL CHECKS OF FINE ADDITIONAL 172R AND 172S AIRCRAFT SHOWED TACH TO READ WITHIN PLUS OR MINUS 50 RPM. DISCOVERED WHEN DOING AD.SDR 20010423CW005Universal Joint · corrodedPIVOTS RUSTY, WOULD NOT SWIVAL, U JOINT COVERED BY RUBBER BOOT. PILOT REPORTED AILERONS HARD TO MOVE.SDR 20010423CW006Camshaft · wornCAMSHAFT WORN ON NR 5 LOBE. CYLINDERS NR 3 AND NR 4 INTAKE VALVE NOT OPENING FULLY. PILOT REPORTED ENGINE RUNNING ROUGH.SDR 20010423CW004Mount · tornRUBBER TORN FROM MOUNTING PLATE.SDR 20010413CW013Actuator · distortedFOUND CRACKS ON BOTH SIDES OF SADDLE SHAPED HOLE OF ACTUATOR BODY .
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