Pilatus PC-12/45
Service difficulty reports · 982
Newest first. General aviation reporting is voluntary.
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 = 'PC1245' 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 = 'PC1245' 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 CA131118002Fuel Control · malfunctioned(CAN) DURING START, THE NG RAISED RAPIDLY UP TO 45 PERCENT TO 85-90 PERCENT IN 2-3 SEC. THE PILOT IN CHARGE SHUTDOWN AND SECURED THE ENGINE. DURING THE ON GROUND TROUBLESHOOTING THE SUBSEQUENT ENGINE STARTS WERE NORMAL. THE INSPECTION OF THE DRAIN LINE AT BOSDR 6CBA20131021127Skin · damagedLEFT FLAP SKIN DAMAGED. THE INNER SKIN PANEL WAS REPLACED WITH A FACTORY NEW PANEL IAW SRM 12-A-51-40-03-00A-041A-A.SDR AJAA2014F00029Adc · failedDURING TAKEOFF, PILOT REPORTED STICK-SHAKER AUDIO SOUNDED, STICK BRIEFLY SHOOK. ELECTED TO COME BACK AROUND AND LAND SAFELY. ACFT MAINTENANCE DIAGNOSED THE PROBLEM TO BE A FAULTY AIR DATA COMPUTER.SDR CA131020001Sensor · intermittent(CAN) NORMAL OIL TEMPERATURE READING UP TO 80 DEGREES. AFTER REACHING MORE THAN 80 DEGREES OIL TEMP GAUGE READING ERRATIC AND GOING TO MAX INTERMITTENTLY.SDR PCPR201309261Structure · corrodedSEVERE CORROSION DISCOVERED ON LT MLG PROXIMITY SWITCH WIRING STRAIN RELIEF, . CORROSION WAS INITIALLY DETECTED AT GAP BETWEEN SHRINK WRAP COVERING WIRING STRAIN RELIEF AND SHRINK WRAP COVERING CONNECTOR PLUG ASSY, PN 971.75.16.500. SHRINK WRAP CUT FROM STRASDR CA131104008Transmitter · unresponsive(CAN) THE STICK SHAKER AND PUSHER SYSTEM WAS TESTED PRIOR TO DEPARTURE AS REQUIRED TO CLEAR THE CAWS DISPLAY OF THE PUSHER INDICATION AND INDICATED A SERVICEABLE SYSTEM. DURING TAKE OFF THE SHAKER SYSTEM WAS ACTIVATED AND THE AIRCRAFT RETURNED TO BASE WITHOUT SDR CA131118004Gear · failed(CAN) THE ACFT TOOKOFF AND CLIMBED UP TO 10,000 FT WHEN THE PILOT HEARD A LOUD BANG AND THE CHIP DETECTOR LIGHT CAME ON SOON AFTER THAT AND THE ENGINE WAS MAKING A LOUD GROWLING NOISE. THE PILOT DIVERTED AND PROCEEDED TO LAND AT OTHER AIRPORT. AFTER LANDING, SDR S642013F00001Wheel · damagedDURING LANDING AND TAXI, CREW NOTICED AN INTERMITTENT NOISE COMING FROM THE RT MLG AREA AND THE TIRE APPEARED TO BE LOW. THE ACFT WAS LEFT ON THE RAMP FOR 2 DAYS BEFORE MX INSPECTED IT . THE ACFT WAS FOUND WITH A FLAT TIRE AND ONCE THE HUB CAP WAS REMOVED, SSDR S64201308230001Wheel · damagedDURING LANDING AND TAXI, CREW NOTICED AN INTERMITTENT NOISE COMING FROM RT MLG AREA AND TIRE APPEARED TO BE LOW. ACFT FOUND WITH A FLAT TIRE AND ONCE HUB CAP REMOVED, NUTS AND WASHERS FROM WHEEL ASSY WERE FOUND LOOSE AND SOME MISSING. WHEEL REMOVED AND SSDR CA130724007Helicoil · failed(CAN) AFTER LANDING AND GOING TO REVERSE PITCH, PILOT REPORTED SMOKE COMING FROM ENGINE. SHORTLY AFTER LANDING, THERE WAS SMOKE ALSO IN COCKPIT. PILOT DECLARED EMERGENCY. AFTER INVESTIGATION, FOUND MAJOR OIL LEAK COMING FROM A CAPPED TRANSFER TUBE PORT ON THE SDR 2VMA201307080001Fuel Control · malfunctionedON DESCENT AIRCRAFT HAD ENGINE FLAME-OUT. AIRCRAFT LANDED WITHOUT INCIDENT AND TAXIED OFF RUNWAY. AIRCRAFT WAS ABLE TO BE RESTARTED AFTER LANDING.SDR CA130705003Collar · missing(CAN) DURING A 16000 HR WING INSPECTION OF THE WING CRITICAL FASTENER, THE PRC WAS REMOVED TO EXPOSE THE STEM OF THE HY-LOK FASTENER. UPON INSPECTION IT WAS NOTED THAT NO COLLAR WAS ON THE HY-LOK. THIS IS THE FIRST INSPECTION OF THIS PART SINCE MFG AND THE FSDR 2013FA0000442Motor · failedDURING NORMAL OPERATION FLIGHT, THE FREON AIR CONDITIONER SYS SHUTDOWN. PILOT REPORTED WHEN, AFTER LANDING, THEY CHECKED CIRCUIT BREAKER IN AFT TAIL CONE AND NOTICED IT WAS TRIPPED. AFTER FURTHER INVESTIGATION, IT WAS NOTED THAT THE COMPRESSOR MOTOR SHOWS SISDR CA130619004Display · failed(CAN) WHILE ACFT WAS POWERED UP ON GROUND FOR MAINTENANCE, IT WAS NOTICED THAT THE LT LOWER EFIS DISPLAY WOULD MAGNIFY AND THEN RETURN TO NORMAL IN A PULSING ACTION. THE DISPLAY WAS REPLACED WITH A SERVICEABLE UNIT AND TESTED OK.SDR QMLA2013061613081Terminal Block · arcedLANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. LANDING GEAR INDICATOR LIGHTS SHOWED 3 RED/UNLOCKED GEAR. HYD LIGHT ILLUMINATED ON CAWS PANEL. BETWEEN 5 AND 10 MINUTES AFTER THE INITIAL FAILURE, THE GEAR CYCLED TO THE UP POSITION WITHOUT ANY PILOT ACTION.SDR CA130618001Fcu · contaminated(CAN) AIRCRAFT WOULD NOT START. WOULD ONLY GO TO MINIMUM FLOW. TROUBLESHOOTING FOUND EXCESSIVE METAL IN OUTLET FILTER, REPLACED PUMP AND FCU FOR METAL CONTAMINATION. THIS CLEARED THE DEFECT. UPON FURTHER INVESTIGATION, REMOVED INLET FILTER AND FOUND NO METASDR PCPR2013061301Pump · leakingDURING UNSCHEDULED MX, FOUND ENGINE DRIVEN FUEL PUMP LEAKING AT RELIEF VALVE GASKET. ENGINE COMPARTMENT COVERED WITH FUEL RESIDUE.SDR CA130610011Tire · cracked(CAN) IT WAS REPORTED TO MAINTENANCE THAT DURING GROUND HANDLING THE FLIGHT CREW NOTICED A CRACK IN THE SIDE WALL OF THE MAIN LT TIRE. MAINTENANCE REPLACED THE TIRE AND AFTER FURTHER INSPECTION FOUND THE RT TIRE ALSO HAD A CRACK IN THE SIDE WALL. CRACK APPEARSDR CA130607003Line · leaking(CAN) UPON TROUBLESHOOTING A HYD LIGHT SNAG, MAINTENANCE JACKED THE ACFT AND PREFORMED A GEAR SWING. GEAR WENT UP WITHOUT INCIDENT. UPON SELECTION OF GEAR DOWN A LOUD BANG WAS HEARD AND HYDRAULIC FLUID STARTED POURING FROM MULTIPLE PLACES ON LT SIDE OF FUSELSDR CA130709004Fuel Control · malfunctioned(CAN) PILOT REPORTED THAT POWER LEVER WAS VERY STIFF, MAINTENANCE DISCOVERED THAT INPUT SHAFT ON FCU WAS VERY STIFF TO MOVE. FCU R & R WITH SERVICEABLE UNIT.SDR QMLA2013052713072Relay · malfunctionedLANDING GEAR FAILED TO RETRACT AFTER TAKE OFF. THE LANDING GEAR INDICATOR LIGHTS SHOWED 3 RED/UNLOCKED GEAR. HYD LIGHT ILLUMINATED ON CAWS PANEL. PERFORMED EMERGENCY GEAR EXTENTION AND RETURNED TO POINT OF DEPARTURE.SDR AJAA2013F00117Generator · malfunctionedHAVING MULTIPLE ISSUES WITH THE NR 2 GENERATOR STAYING ON LINE. NR 2 GEN. CONTINUES TO FALL OFF-LINE, AND CONTINUE TO BECOME MULTIPLE DISCREPANCIES. CAN ADJUST THE GCU VOLTAGE, AND SYSTEM WILL REMAIN ON-LINE FOR ANYWHERE FROM 1 DAY, TO 1 MONTH.SDR 2013FA0000264Seat · crackedAIRCRAFT WAS IN FOR A ANNUAL INSPECTION. FOUND PASSENGER SEAT CRACKED AT THE BACKREST ACTUATOR FORWARD ATTACH POINT.SDR CA130429010Wire · broken(CAN) UPON DEPARTURE THE CREW NOTICED THE PLANE WAS NOT PRESSURIZING BASED ON THE CABIN ALTITUDE INDICATOR. THEY RESET THE ECS SWITCH WITH NO RESULTS. LEVELED OFF AND RESET THE SWITCH AGAIN AND CHECKED THE SELECTOR. THE ECS STILL DID NOT COME ON AND THERE WAS SDR CA130408008Pressure Switch · leaking(CAN) HYDRAULIC FLUID LEAKING THROUGH BODY OF PRESSURE SWITCH.SDR CA130408007Solenoid · leaking(CAN) DURING ROUTINE 100 HR INSPECTION, FLUID WAS SHOOTING OUT OF SMALL HOLE ON THE UPLOCK SOLONOID ON THE FIRST GEAR RETRACTION. DID NOT COME OUT SUBSEQUENT RETRACTIONS. QTY OF FLUID WAS APPROXIMATELY 3-4 TABLESPOONS.SDR 5APR20130314124Display · failedPILOT REPORTED: SIX MINUTES AFTER DEPARTURE, CAWS PANEL FAILED, FOLLOWED BY SMOKE EMANATING FROM THE CAWS PANEL. ACFT RETURNED TO DEPARTURE AND LANDED SAFELY. CAWS DISPLAY PANEL WAS FOUND TO BE FAULTY, IT WAS CONFIRMED BY A ELECTRICAL AND SMOKE ODOR FROM TSDR 2013FA0000136Seat Frame · crackedDURING ANNUAL INSPECTION, FOUND PASSENGER SEAT WITH THE MAIN FRAME CRACKEDSDR QMLA2013020813023Connector · burnedDURING OTHER MX TO CLEAN AN INTERNAL FUEL BAY IT WAS NOTED THAT THERE WAS A BLACK STREAK GOING BOTH UP FROM AND DOWN FROM THE FUEL QUANTITY WIRE HARNESS CONNECTOR INSIDE THE FUEL BAY OF THE LEFT WING. REMOVED THE CONNECTOR FROM THE BULKHEAD AND FOUND THAT THSDR CA121228003Fuel Control · malfunctioned(CAN) AFTER TAKEOFF DURING CLIMB, THE CREW ATTEMPTED TO REDUCE TAKEOFF POWER TO CLIMB POWER AND NOTED NO CHANGE IN POWER. THE PILOT COULD NOT REDUCE THE POWER AND THE ACFT CONTINUED TO ACCELERATE. WITHOUT POWER CONTROL AVAILABLE FROM FLIGHT CREW, PILOTS ELESDR CA121213001Engine · malfunctioned(CAN) DURING FLIGHT AT 1000 FT. PILOTS DID THE AFTER TAKEOFF CHECKS AND THE TORQUE WOULD NOT REDUCE WITH THE POWER CONTROL LEVER FROM AROUND 40 PSI. GEAR WAS LOWERED TO REDUCE AIR SPEED AND OPD RADIOED TO RETURN TO DEPARTURE AIRPORT IMMEDIATELY. A MAYDAY WASSDR QMLA2012102812173Relay · intermittentLANDING GEAR RETRACTED SLOWLY. NOSE GEAR DID NOT EXTEND UNTIL BELOW 110 KTS. JACKED ACFT AND HYD PUMP FAILED. TAPPING ON HYD PUMP RELAY MADE IT WORK HYD SYSTEM PUMP RELAY WAS NOT WORKING PROPERLY. REPLACED RELAY AND FUNCTION TEST OF LANDING GEAR, OK.SDR C41R201210300001Lead · splitINTERMITTENT PROP HEAT OPERATION AND HAD CAWS WARNING. COMPLETED TROUBLESHOOTING OF PROP HEAT SYS AND FOUND SEVERAL OF THE PROP DE-ICE LEADS WERE WORN THROUGH THE PROTECTIVE SLEEVES. INSTALLED ALL NEW PROP LEADS (X5). COMPLETED FUNCTIONAL AND OPS CHECKS.SDR CA121009017Hose · leaking(CAN) DURING A FUNCTIONAL TEST OF THE DE-ICE BOOT, WE HAVE CONNECTED AN AIR PRESSURE REGULATOR TO THE HOSE BLEED AIR FLEXIBLE LINE AND WE HAVE NOTICED THAT THE FLEXIBLE HOSE IS LEAKING. THIS HOSE IS DIRECTLY CONNECTED TO THE ENGINE P3 PICK UP, SO IF THE FLEXISDR CA121005001Hose · leaking(CAN) DURING PHASE CHECK, MAINTENANCE NEEDED TO PERFORM INFLATION TEST OF DE-ICING BOOT. THE MECHANIC CONNECTED A SHOP AIR SUPPLY REGULATOR TO THE BLEED HOSE, PN 946-37-74-101 AND NOTICED THAT THE HOSE WAS LEAKING. THERE WAS NO CHAFING OR ANY OTHER EVIDENCE SDR ESMR2012090401Unknown · unknownPOWER APPEARED TO BE NORMAL ON TAKEOFF AND THE INITIAL CLIMBOUT. CLIMBING THROUGH ABOUT 16,500 FT, OBSERVED THAT POWER CONTROL LEVER WAS UP AGAINST FORWARD STOP AND WERE BELOW BOTH MAXIMUM ITT AND TORQUE LIMITS. ALL OTHER PARAMETERS SEEMED NORMAL, ELECTED SDR CA120822013Csu · damaged(CAN) PILOT NOTICED AN ENGINE CHIP LIGHT INDICATION FLICKER ON DESCENT. ON LANDING AND TAXIING THE INDICATION RETURNED AND REMAINED ON. MAINTENANCE REMOVED AND CHECKED THE RGB CHIP DETECTOR FOR DEBRIS. IT WAS FOUND TO HAVE 3 SMALL BALL BEARING MEASURING 0.0SDR 6CBA20120622118Skin · damagedTHE LEFT FLAP WAS DAMAGED AT THE FLAP TRAILING EDGE, BEGINNING FROM THE REAR RIB 3 EXTENDING 317.5MM INBOARD TO THE INBOARD EDGE OF FLAP TRAILING EDGE SKIN AREA. THE LEFT FLAP WAS INSPECTED AND FOUND THE REPAIR NEEDED WAS LIMITED TO USING THE FOLLOWING PILATUSDR CA120702001Fuel Control · malfunctioned(CAN) DURING CRUISE AT FL190, THE ENGINE POWER INCREASED UNCOMMANDED FOR 3 SECONDS AND THEN RETURNED TO NORMAL. THE REMAINDER OF THE FLIGHT WAS UNEVENTFUL UNTIL SHORT FINAL WHEN THE POWER LEVER WAS REDUCED TO FLIGHT IDLE, THE TORQUE WAS STILL READING 12 PSI ISDR CA120612012Scoop · failed(CAN) DURING CLIMB THROUGHT FL 20 CABIN ALTITUDE COULD NOT BE MAINTAINED AT REQUESTED ALTITUDE, PRESSURE DIFFERENTIAL. DURING GROUND PRESSURIZATION TESTS IT WAS FOUND THAT THE AIR CONDITIONING EMERGENCY VENT SCOOP DOOR WAS OPENING UNDER PRESSURE, THE SHAFT INSDR 6CBA20120430116Relay · faultyCREW REPORTED A TRIM RUNAWAY IN FLIGHT (STAB TRIM DOWN) AFTER DEPARTING TEB. REMOVED AND REPLACED PITCH TRIM CONTROL RELAYS K021 AND K022 (P/N ON/OFF 974.20.01.212) IN ACCORDANCE WITH PILATUS WIRING DIAGRAM 27-40-00. PERFOMED HORIZONTAL STABILIZER OPERATIONSDR 6CBA20120429115Unknown · malfunctionedCREW REPORTED A/P TRIM ANNUNCIATOR CAWS. CREW ALSO REPORTED THIS WAS ACCOMPANIED BY A UNCOMMANDED PITCH TRIM DOWN. AS A PRECAUTION BOTH PITCH TRIM, UP AND DOWN RELAYS P/N 974.20.01.212 (K021 AND K022) WERE REMOVED AND REPLACED IAW PILATUS WIRING DIAGRAM MSDR CA120426009Motor · disconnected(CAN) DURING CLIMB, CREW EXPERIENCED AN UNCOMMANDED PITCH UP, AUTO PILOT DISCONNECTED AND FLIGHT CONTINUED. SUBSEQUENT MAINTENANCE TROUBLESHOOTING DETERMINED THE ELEVATOR SERVO, PN 065-0056-0059, SN M4907 WAS DEFECTIVE, UNIT REPLACED AND ACFT RETURNED TO SERVSDR AJAA2012F00076Actuator · intermittentON APPROACH, THE ACFT RUDDER TRIM WENT TO FULL DEFLECTION. PILOT DECLARED AN EMERGENCY, AND LANDED SAFELY. RUDDER TRIM ACTUATOR FOUND TO BE INTERMITTENT. REMOVED AND REPLACED ACTUATOR.SDR 5APR20120307110Efis · faultyPILOT REPORTS LEFT EHSI INTERMITTENT, HAS A BLURRY SCREEN. THE LEFT EHSI, WAS FOUND TO BE FAULTY. R & R WITH A SERVICEABLE UNIT IAW AMM 12-A-34-26-02-00A-920A-A AND TESTED GOOD IAW 2-A-34-26-00-00A-903A-A.SDR CA120214005Wire · broken(CAN) UNSAFE GEAR INDICATION SHORT DESC: WHILE ON SHORT FINAL LEFT MAIN GEAR INDICATION BEGAN TO FLICKER FROM GREEN TO RED AND THEN REMAINED ON RED. ALTHOUGH HAD PREVIOUS 3 GREEN INDICATION FOR THE APPROACH AFTER SELECTING GEAR DOWN DECIDED TO ABORT THE LANDISDR CA120130009Starter Gen · failed(CAN) ACFT WAS IN CRUISE WHEN A RUMBLING/VIBRATION WAS FELT AND HEARD. THEY ELECTED TO RETURN TO BASE AND AS THEY WERE RETURNING THE NR 1 GENERATOR FAILED. INVESTIGATION SHOWED THAT THE GENERATOR FAN HAD RUBBED AGAINST ITS HOUSING AND WAS IN THE PROCESS OF DESDR 5APR20120120107Display · faultyTHE EHSI WAS REPORTED AS INOPERATIVE. THE EHSI DISPLAY WAS FOUND TO BE FAULTY. THE EHSI DISPLAY WAS R & R USING A SERVICEABLE UNIT OF THE SAME PN IAW AMM12-A-34-26-02-00A-920A-A. THE SYS OPERATIONALLY CHECKED GOOD IAW AMM 12-A-34-26-00-00A-903A-A.SDR 5APR20120119106Eadi · failedTHE NR 2 EADI WAS FOUND TO BE BLOOMING DURING OTHER MX AND NEEDING REPLACEMENT. THE NR 2 EADI PN 066-03125-2500 WAS R & R USING A SERVICEABLE UNIT OF THE SAME PN 066-03125-2500 IAW AMM 12-A-34-26-03-00A-920A-A, OPS CHECKED GOOD IAW AMM 12-A-34-26-00-00A-903A-SDR 5APR20120117105Controller · faultyTHE FLIGHT CREW REPORTED THE AUTO PILOT SYSTEM AS BEING INOP. THE AUTO PILOT MODE CONTROLLER, PN 065-00086-0017 WAS FOUND TO BE FAULTY. IT WAS R & R USING A SERVICEABLE UNIT OF THE SAME PN IAW AMM 12-A-22-10-05-00A-920A-A. THE SYS OPERATIONALLY TESTED GOOD
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