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 CA070112002Bearing · worn(CAN) DURING INSPECTION OF TAIL TOP ATTACH BOLT FOUND TO HAVE EXCESSIVE WEAR. RUDDER REMOVED AND NEW BOLT P/N 932.35.71.166 AND BEARING REPLACED. MFG AIRCRAFT NOTIFIED OF DEFECT. (TC NR 20070112002)SDR CA070113001Hinge · corroded(CAN) AFTER A HEADS UP CONDITION FROM ANOTHER RCMP AIR SECTION. AN INSPECTION OF CONDITION WAS CARRIED OUT ON MPI. THE PART INSPECTED WAS FOUND SEVERELY CORRODED AND IF LT UNCHECKED COULD AFFECT THE INTEGRITY OF THE CABIN DOOR FRAME. THE HINGE PLATE MOUNTED SDR CA061218012Oil System · contaminated(CAN) NON ALLOWABLE DEBRIS FOUND IN OIL SYSTEM, CONFIRMED BY OIL ANALYSIS REPORT. ENGINE SENT BACK TO MANUFACTURER FOR INVESTIGATION. ENGINE EXCHANGED, WILL NOT BE SENT BACK TO THE OPERATOR. ENGINE TSO 214.7 TSN 8330.9 (TC NR 20061218012)SDR CA070112001Bearing · worn(CAN) DURING INSPECTION OF TAIL TOP ATTACH BOLT FOUND TO HAVE EXCESSIVE WEAR. RUDDER REMOVED FOR REPAIR. DURING REPAIR ANCHOR NUT WAS DAMAGED. NEW OVERSIZED BUSHING INSTALLED, WITH NEW BOLT, BEARING AND ANCHOR NUT. MFG WAS NOTIFIED OF THIS DEFECT. (TC NR 20070SDR CA061214003Boot · split(CAN) AIRCRAFT RETURNED FROM FLIGHT TO ARCTIC. ALL DE-ICE BOOTS ON AIRCRAFT WERE FOUND SPLIT ALONG CHORD AND HAD TO BE REPLACED. THE PRESSURE REGULATOR WAS TESTED AND FOUND TO BE FUNCTIONING NORMAL. WE WERE UNABLE TO DETERMINE THE CAUSE OF THE FAILURE. THESDR CA061204004Control Valve · malfunctioned(CAN) AIRCRAFT WAS ON CLIMBOUT GOING THROUGH 6000 FEET WHEN ECS LIGHT CAME ON AND CABIN STARTED TO DE-PRESSURIZE. AIRCRAFT RETURNED TO RANKIN INLET WHERE MAINTENANCE DISCOVERED THAT TCA VALVE WAS STUCK IN THE FULL OPEN POSITION AND EXCESS HEAT TRIPPED THE SYSTSDR CA061020001Flap · obstructed(CAN) ICE BUILD UP INTO THE IB FLAP COVER CAUSED THE FLAPS TO NOT GO FULL UP. IT TRIPPED THE FLAP CIRCUIT BREAKER. THE ICE CAUSED THE ROD TO BEND FROM THE STRESS OF TRYING TO MOVE THE FLAP UP. IT WAS NOTICE BY SEEING A 50 AMP DRAW FROM THE FLAP MOTOR. ROD SDR CA061017004Relay · burned(CAN) FOLLOWING LANDING OF AIRCRAFT AMBER (HYD). ANNUNCIATOR ILLUMINATED. INSPECTION OF HYDRAULIC MOTOR POWER RELAY MAIN CONTACTS INDICATED THE CONTACTS WERE SEVERLY BURNED. NEW RELAY INSTALLED ,FUNCTION TEST OF LANDING GEAR SYSTEM PERFORMED SATISFACTORY. (TCSDR CA061012001Clutch · cracked(CAN) DURING A ROUTINE PHASE INSPECTION, THE AREA AROUND THE PITCH SERVO IS INSPECTED. DURING THIS, THE FRICTION PLATE WAS DISCOVERED TO BE CRACKED IN HALF. THE PITCH SERVO CLUTCH WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061012001)SDR CA061010002Bearing · twisted(CAN) AFTER LANDING, CREW REPORTED TO MAINTENANCE THAT THEY HAD A HARD SHIMMY IN THE RUDDER PEDALS. UPON INSPECTION WE FOUND THE NOSE STEERING BRACKETS BENT AND THE SPRING STRUT UNABLE TO MOVE. THE STEERING STRUT CONNECTED TO THE STEERING HAD FAILED CAUSING SDR CA060913006Wheel · damaged(CAN) DURING AN INSPECTION WHEEL ASSY WAS REMOVED, GREASE COVER FOR THE BEARING AND BEARINGS REMOVED FOR INSPECTION/ REPACKING. THE WHEEL WAS THEN CLEANED AND INSPECTED FOR WEAR. AT THAT POINT IT WAS NOTICED THAT THE WHEEL HOUSING HAD SEVERAL DEEP GROOVES WHESDR CA060909002Screw · loose(CAN) DURING A SCHEDULEDED PRESSURIZATION CHECK LEAKS WHERE NOTED FROM THE WINDSCREEN ATTACHMENT SCREWS. ATTACHMENT SCREWS RE-TORQUED WHICH REVEALED THAT SEVERAL WERE LOOSE. ALTHOUGH THIS IS NOT AN UNHEARD OF SITUATION IT SEEMS TO BE HAPPENING MORE AND MORE.SDR CA060909001Screw · loose(CAN) DURING A SCHEDULEDED PRESSURIZATION CHECK LEAKS WHERE NOTED FROM THE WINDSCREEN ATTACHMENT SCREWS. ATTACHMENT SCREWS RE-TORQUED WHICH REVEALED THAT SEVERAL WERE LOOSE. ALTHOUGH THIS IS NOT AN UNHEARD OF SITUATION IT SEEMS TO BE HAPPENING MORE AND MORE.SDR CA060905005Bracket · cracked(CAN) WHILE DOING A WALKAROUND ON THE AIRCRAFT THERE WAS A CRACK FOUND ON THE UPPER ATTACHMENT BRACKET IN THE NOSE GEAR BAY THAT THE NOSE GEAR HYDRAULIC ACTUATOR ATTACHES TO. BRACKET REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060905005)SDR CA060905004Rib · broken(CAN) WHILE DOING A WALK AROUND ON THE AIRCRAFT, THERE WAS LOTS OF PLAY FOUND AT THE UPPER ATTACHMENT BOLT ON THE RUDDER. THE BOLT HAD ELONGATED THE HOLE AND DAMAGED THE NOSE RIB. WHEN TRYING TO TAKE THE BOLT OUT, THE NUT PLATE BROKE AWAY AND A PIECE OF THE SDR CA061006005Coupling · fractured(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION IN FLIGHT. THE ENGINE WAS SHUTDOWN AND SUCCESSFULLY RE-LIT AND THE UNCOMMANDED ACCELERATION REPEATED. THE ENGINE WAS AGAIN SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL /SDR CA060830001Warning System · malfunctioned(CAN) 1 HR INTO CRUISE AT FL 220 PILOT EXPERIENCED INSTANTANEOUS AURAL AND VISUAL WARNINGS OF MULTIPLE SYSTEMS FAILURE. CAUTION ADVISORY PANEL DISPLAYED PUSHER INOP, FLAPS INOP, AUTO PILOT FAIL; FLAP POSITION INDICATOR JUMPED FROM 0 DEG TO 40 DEG.ALSO INDICATISDR CA060909003Screw · backed out(CAN) ON A WALKAROUND SEVERAL WINDSCREEN ATTACHMENT SCREWS WERE NOTED AS BEING PARTIALLY BACKED OUT. ALL ATTACHMENT SCREWS RE-TORQUED AND SEVERAL MORE WERE FOUND TO BE LOOSE. SCREWS RETORQUED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060909003)SDR CA060808001Relay · malfunctioned(CAN) LANDING GEAR SELECTED DOWN ON FINAL. NO GEEN DOWN LOCK INDICATION FOR THE NOSE GEAR. PILOT DID AN EMERGENCY GEAR EXTENSION AND GOT THE LANDING GEAR DOWN AND LOCKED INDICATION FOR ALL THREE GEAR. THE SYSTEM WAS TROUBLESHOT AND FOUND TO HAVE A MALFUNCTIONISDR CA060724004Limiter · failed(CAN) PILOT SNAG: ENGINE POWER LOST IN FLIGHT HAD TO USE MANUAL OVERRIDE. RECTIFICATION: REPLACED TORQUE LIMITER P/N 3244882-1, S/N C50254 WITH REMOVED SERVICEABLE UNIT FROM ENGINE S/N PR0116 P/N 3244882-1 S/N C50621. ALL APPLICABLE ENGINE RUNS COMPLETED AND SDR CA060719002Actuator · leaking(CAN) ORIGINAL MAIN LANDING GEAR ACTUATOR REPLACED WITH AN OVERHAULED UNIT. (ORIGINAL ACTUATOR HAD AN INTERNAL LEAK) HYDRAULIC SYSTEM FLUSHED BEFORE OVERHAULED ACTUATOR WAS INSTALLED. INTERNAL LEAK DEVELOPED IN TSO 153.3. HYDRAULIC SYSTEM FLUSHED AGAIN AND A SDR CA060731015Limiter · malfunctioned(CAN) IN DESCENT THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT. THE MANUAL FUEL CONTROL OVER-RIDE WAS ENGAGED, AN EMERGENCY DECLARED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. THE ENGINE TORQUE LIMITER WAS SUBSEQUENTLY DETERMINED TO BE FAULTY AND WAS REPLACEDSDR CA060724003Burner Can · failed(CAN) BRIGHT FLASHES COMING FROM EXHAUST STACKS, NO CHANGE TO INDICATIONS. 15 FLASHES IN 2 HOUR PERIOD. ENGINE OUTER BURNER CAN FOUND INOPERATIVE, CERAMIC COATING FLAKING OFF AND IGNITING. REPLACED WITH OVERHAULED UNIT. GROUND RUN AND RELEASED SERVICEABLE. P/SDR CA060706006Relay · failed(CAN) LANDING GEAR WOULD NOT RETRACT FULLY AND HYDRAULIC LIGHT CAME ON AFTER LANDING GEAR WAS SELECTED UP IN CLIMB. CREW CHECK HYDRAULIC CONTROL CB AND IT WAS IN. CREW FOLLOWED CHECK LIST AND SELECTED GEAR DOWN AND HAND PUMPED LANDING GEAR DOWN AND LOCKED. SDR CA060706005A/C Pack · failed(CAN) PILOT REPORTED THAT ECS WAS SELECTED ON AT PREFLIGHT CHECK. NO PROBLEM NOTICED. SOON AFTER ROUTINE TAKEOFF AN ODOUR WAS PREVALENT IN COCKPIT. ECS SYSTEM WAS DEACTIVATED AND ODOUR DISSIPATED ALMOST IMMEDIATELY. AIRCRAFT RETURNED TO PLACE OF DEPARTURE WITHSDR CA060620002Solenoid Valve · sticking(CAN) OVERSPEED GOVERNOR REPLACED WITH AN OVERHAULED UNIT (DUE TO FEATHERING VALVE STICKING INTERMITTANTLY SEE SDR 20060620001) AND DURING FEATHER CHECK THE PROP WOULD NOT COME OUT OF FEATHER. ELECTRICAL SYSTEM CHECKED. NO FAULTS FOUND. ANOTHER SERVICEABLE SDR CA060620001Solenoid Valve · stickingFEATHERING SOLENIOD VALVE STICKING INTERMITTENTLY IN FEATHER POSITION AND THEREFORE PROP STAYS FEATHERED AFTER ENGINE START. FAULT ONLY OCCURS DURING QUICK TURN AROUNDS ON HOT DAYS. AFTER ENGINE COOLS VALVE OPERATES NORMALY.SDR CA060508004Pressure Switch · malfunctionedAFTER TAKEOFF AND GEAR UP SELECTION WAS COMPLETED, THE CREW HAD A HYD. LIGHT ON THERE CAWS. RETURNED AND UPON GEAR DOWN SELECTION THE GEAR MOTOR FAILED TO RUN. GEAR DID A FREE FALL AND LOCKED DOWN. ONCE IN HANGAR IT WAS NOTED THAT HYDRAULIC CONTROL CB WAS OSDR CA060405006Lamp · failedTHE A/C WAS MODIFIED PER LSTC 0-LSA06-001/D, INSTALLATION OF LED NAV LAMPS. LAMPS WERE INTSTALLED PER DRAWINGS ECA-12-TM-05-197. SINCE THIS INSTALLATION THREE NAV LAMP FAILURES HAVE OCCURRED, ONE TIME ON THE RIGHT LED AND TWICE ON THE TAIL NAV LED. THE CAUSSDR CA060322004Deice System · crackedDURING MAINTENANCE OPERATION NOTICED EXHAUST SOOT TRAIL FROM INNER EDGE OF DEICE LIP ASSY. REMOVAL OF DEICER LIP ASSY FROM COWL REVEALED A CRACK ON INNER PART OF LIP DEICE ON INLET SIDE. DEICE LIP ASSY REPLACED WITH NEW. P/N; OF CRACKED DEICE LIP ASSY IS 53SDR CA060317012Wire · failed(CAN) FLAPS FAILED TO EXTEND ON LANDING. FLAPS WORKED INTERMITTENTLY IN THE HANGER. VARIOUS FAULTS CODES WERE NOTED BUT THEY WERE NOT CONSISTENT AFTER RESETTING THE SYSTEM. UPON FURTHER INVESTIGATION IT WAS NOTED THAT THE WIRES TO THE P029 PLUG TO THE FCWU HADSDR CA060307002Proximity Switch · faulty(CAN) DURING CRUISE, THE (AIR/GROUND) LIGHT ON THE CAWS PANEL ILLUMINATED. UPON TOUCHDOWN, THE LIGHT WENT OUT. INVESTIGATION REVEALED A FAULTY LT GROUND PROXIMITY SWITCH. THE SWITCH WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060307002)SDR CA060228006Vane · inoperativeDURING A ROUTINE PHASE 5 INSPECTION , THE LT AOA VANE HEATER WAS FOUND TO BE INOPERATIVE. ASSY REPLACED WITH SERVICEABLE UNIT.SDR CA060131002Controller · failedPILOT SELECTED ENVIRONMENTAL SYSTEMS TO AUTO PRIOR TO FLIGHT AND RECEIVED A CAUTION LIGHT ON PANEL THAT THE SYSTEM WAS NOT FUNCTIONING. THE SYSTEM WAS CYCLED ON AND OFF THEN AN INCREASE IN POWER WAS APPLIED AND THE CAUTION LIGHT EXTINGUISHED INDICATING NORMALSDR CA060228007Control Valve · intermittentTEMPERATURE CONTROL VALVE FOUND TO INTERMITTENTLY STICK AT HOT POSITION CAUSING A DUCT TEMPERATURE WARNING. VALVE REPLACED WITH SERVICEABLE ASSY.SDR CA061107006Gearbox · damaged(CAN) THE ENGINE LOST OIL PRESSURE IN FLIGHT RESULTING IN LOSS OF THE AIRCRAFT. SUBSEQUENT INVESTIGATION REVEALED THAT A PROTECTIVE COATING HAD BEEN IMPROPERLY APPLIED TO THE AGB HOUSING AT THE PRIOR ENGINE OVERHAUL. THE COATING DEBONDED AND BLOCKED THE OIL SDR CA051129006Computer · malfunctionedPILOT RETURNED TO RAMP FOLLOWING NORMAL DEPARTURE AND REPORTED THAT SHORTLY AFTER TAKEOFF THE "STICK SHAKER" WAS OPERATING AND OPERATED MOST OF THE WAY THROUGH THE CIRCUIT TO RETURN TO RUNWAY AND THE RAMP. AIRCRAFT WAS BROUGHT INTO HANGAR AND A "CHECK" OF THESDR CA051116010Pdu · defective(CAN) FLAP PDU FOUND U/S NEW PDU INSTALLED.SDR CA051114006Adapter · failed(CAN) RED (PITCH TRIM) ANNUNCIATOR WOULD ILLUMINATE INTERMITTENTLY WHEN DESCENT COMMANDED. THIS WOULD SOMETIMES OCCUR AS THE AUTO PILOT WOULD ATTEMPT TO TRIM. AUTO PILOT WOULD NOT DISENGAGE. PITCH TRIM ADAPTER REPLACED 31.4 HRS PREVIOUS DUE TO A DIFFERENT DEFESDR CA051103007Governor · contaminated(CAN) DURING A ROUTINE PHASE 4 INSPECTION, METALLIC POWDER WAS DISCOVERED TRAPPED IN THE ENGINE MAIN OIL FILTER. SOURCE OF CONTAMINATION WAS CONFIRMED TO BE THE PROPELLER GOVERNOR AS SOME NON-METALLIC DEBRIS WAS FOUND IN THE OVERSPEED GOVERNOR GASKET SCREEN. SDR CA051103006Adi · faulty(CAN) EADI ON COPILOTS SIDE WOULD GO (FUZZY) INTERMITTENTLY. PART REPLACED WITH SERVICEABLE UNIT. THIS SEEMS TO BE A RECURRING DEFECT.SDR CA051103005Adapter · faulty(CAN) AUTO PILOT TRIPPED OFF LINE. RED TRIM ANNUNCIATOR ILLUMINATED ON MODE CONTROLLER. FLIGHT DIRECTOR WAS FUNCTIONING NORMAL. ALL ELECTRIC TRIMS FUNCTIONING NORMAL. AUTO PILOT WOULD NOT TEST, THEREFORE NOT ENGAGE. PITCH TRIM ADAPTER FOUND AT FAULT.SDR CA051028005Actuator · binding(CAN) ON FLAP RETRACTION AFTER TAKEOFF, FLAP WARNING LIGHT CAME ON. AIRCRAFT RETURNED TO AIRPORT AND CARRIED OUT A SUCCESSFUL FLAP RESET. AIRCRAFT DEPARTED, AND ON FLAP RETRACTION, FLAP WARNING CAME ON WITH FLAPS STOPPING BETWEEN 0 AND 15 DEGREES. AIRCRAFT SDR CA051027002Stop · missing(CAN) THIS IS THE SECOND PC-12 IN WHICH THE COMPANY HAS DISCOVERED THIS ELEVATOR STOP TO BE MISSING. THE MISSING STOP WAS DISCOVERED WHEN REMOVING FLIGHT CONTROLS TO PAINT THE AIRCRAFT.SDR CA051011004Wire Harness · chafedTHE MODE C FUNCTION OF ENCODING ALTIMETER FAILED, AS WELL THERE WERE INTERMITTENT FAULTS OF THE RADAR ALTIMETER AND OTHER AVIONICS SYSTEMS. DURING TROUBLESHOOTING, THE MAIN WIRE BUNDLE ATTACHED TO THE FORWARD FIREWALL/PRESSURE BULKHEAD BEHIND THE INSTRUMENT PSDR CA050922001Exciter · failed(CAN) ENGINE FAILED TO LIGHT AT REMOTE COMMUNITY AIRPORT. IGNITION EXCITER BOX FOUND TO BE AT FAULT. FAILED UNIT HAD BEEN REPLACED AT ENGINE CHANGE, 17.4 HRS PREVIOUS.SDR CA050930001Terminal Block · melted(CAN) THE WINDSHIELDS DE-ICE SYSTEM WAS SNAGGED AS DEFECTIVE BY THE PILOTS. AFTER INSPECTION OF THE SYSTEM 3 TERMINAL BLOCKS LOCATED IN THE COCKPIT ROOF PORTION WERE FOUND TO HAVE OVERHEATED. ALL (3) TERMINAL BLOCKS AND BOTH WINDSHIELDS HAVE BEEN REPLACED. SYSSDR CA050919004Radio · odor(CAN) 15 MINUTES INTO CLIMB TO ALTITUDE, PILOTS SAW AND SMELLED SMOKE EMANATING FROM LOWER PORTION OF COPILOT'S WINDSHIELD. AIRCRAFT RETURNED TO BASE OF DEPARTURE, MEANWHILE CIRCUIT BREAKERS FOR WHAT APPEARED TO BE CAUSE OF SMOKE WERE PULLED. WINDSHIELD HEAT SDR CA050922003Actuator · inoperative(CAN) PARTICLE SEPARATOR ACTUATOR FAILED TO OPERATE. UNIT REPLACED WITH SERVICEABLE UNIT, TESTS SATISFACTORY.SDR CA050922002Structure · cracked(CAN) TRACES OF EXHAUST EMISSIONS WERE NOTICED COMING OUT OF EDGE OF INTAKE LIP. PART WAS REMOVED FROM COWL AND WITH THE TAPE AND INSULATION REMOVED, AN 8 INCH CRACK WAS REVEALED ON THE AFT SIDE OF THE EXHAUST CHAMBER PASSAGE. NEW INTAKE LIP KIT WAS FITTED,
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