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 CA030312012Transmitter · corroded(CAN) IN CLIMB, THE OIL PRESSURE GRADUALLY DESCENDED. THE PILOT PERFORMED A PRECAUTIONARY LANDING. THE OIL SYSTEM WAS INSPECTED TO ENSURE THAT THE OIL FILTER WAS NOT BLOCKED. WHEN ATTEMPTING TO RESTART THE ENGINE, CODE 50 ILLUMINATED ON THE (EIS) PANEL INDICASDR CA021115013Actuator · failed(CAN) DURING SCHEDULED MAINTENANCE OF THE AIRCRAFT. THE FLAPS WERE SELECTED DOWN TO THE 40 DEGREE POSITION. DURING MOVEMENT OF THE FLAPS A 'GRINDING' NOISE WAS HEARD COMING FROM THE L/H INBOARD FLAP ACTUATOR. THE ACTUATOR BECAME VERY HOT AND WOULD CAUSE THE FLSDR CA021108008Harness · shorted(CAN) PROPELLER DE-ICE FAILURE INDICATION REPORTED. DEFECT WAS FOUND AS AN INTERMITTENT OPEN CIRCUIT ON ONE OF THE DEICE HARNESS LEADS. PART REPLACED WITH NEW. THIS DEFECT OCCURRED 106.2 HRS PREVIOUS,TWO DIFFERENT HARNESS ASSY WERE REPLACED AT THAT TIME. THE 4SDR K5S2002F00000Wire · damagedPILOT REPORTED FIRE ON UPPER RT SIDE OF COPILOTS WINDOW. RT WINDSHIELD DEICING CIRCUIT BREAKER WAS PULLED. AFTER INVESTIGATION FOUND TWO WIRES (WIRE L AND K). WIRE L SPLICE AN AWG 10-12 SPLICE WAS SEVERELY BURNED. THE AIRCRAFT IS POST SERVICE BULLETIN FOR SDR CA021105011Pad · worn(CAN) AIRCRAFT WAS BEING TOWED FROM TERMINAL TO HANGER WHEN THE RT BRAKE SEIZED AND WHEEL WOULD NOT TURN.FURTHER INSPECTION REVEALED THAT THE RIVITS WERE SHEARED ON THE WEAR PADS ON THE OUTSIDE ROWS OF THE BRAKE ASSY. THE WEAR PIN INDICATOR WAS SHOWING AROUNDSDR CA021115014Disk · broken(CAN) ON LANDING LT WHEEL BRAKE LOCKED UP AND SKIDDED TIRE. ON INSPECTION FOUND ROTOR DISK AND BROKEN INTO 2 PIECES AND JAMMED BRAKE ASSEMBLY. BRAKE ASSEMBLY AND TIRE REPLACED. ON INSPECTION OF R/H BRAKE ASSEMBLY, FOUND ONE ROTOR DISK ALSO BROKEN. BUT THIS ASSSDR CA021127002Plate · dislodged(CAN) PROPELLER WAS NOT IN THE FULL FEATHER POSITION. INSPECTION SHOWED THAT THERE WAS A GAP BETWEEN THE FEATHER STOP NUT AND THE REVERSE ADJUST SLEEVE. PROPELLER WAS REMOVED AND SENT TO PROPELLER OVERHAUL SHOP FOR REPAIR. ON DISASSEMBLY, THE PRELOAD PLATE WASDR CA021115008Disk · broken(CAN) ON INSPECTION FOUND RT BRAKE ASSEMBLY TO HAVE A BROKEN ROTOR DISK. BRAKE ASSEMBLY REPLACED.SDR CA021030008Stator · worn(CAN) DURING ROUTINE WHEEL BEARING SERVICING, THE RT MAIN WHEEL WAS FOUND WITH EXCESSIVE BRAKE DRAG. THE STATOR WEAR PADS WERE OBSERVED TO BE WARPED AND EXCESSIVELY WORN. THE ROTOR HAS WORN INTO THE WEAR PADS TO THE POINT WHERE THE TOP OF THE STATOR PAD IS TOUSDR CA021101006Switch · failed(CAN) THE PILOT SELECTED THE GEAR DOWN DURING APPROACH. THE NOSE GEAR AND THE LT MAIN INDICATIONS SHOWED 'DOWN & LOCKED'. THE RT GEAR INDICATOR WAS SHOWING A 'GEAR UNSAFE' CONDITION. THE PILOT USED THE EMERGENCY GEAR PUMP TO INSURE THAT THE GEAR WAS INDEED DOSDR CA021101005Actuator · failed(CAN) THE PILOT SELECTED FLAPS IN PREPARATION FOR LANDING.THE AURAL WARNING AND FLAP CAUTION LIGHT ON THE CAWS PANEL WERE THEN OBSERVED BY THE PILOT. THE AIRCRAFT LANDED AND THE FLAPS WERE RESET ON THE GROUND.THIS SNAG OCCURRED AN ADDITIONAL TWO (2) TIMES THRSDR CA021008005Wire Harness · shorted(CAN) PROPELLER DE-ICE WAS REPORTED AS FAILED BY FLIGHT CREW. DEFECT WAS DISCOVERED AS AN INTERMITTENT OPEN CIRCUIT ON TWO OF THE DEICE HARNESS LEADS BETWEEN THE SPINNER BACKPLATE AND THE DEICE BOOT. ALTHOUGH THE SYSTEM TESTED OK WITH THE BLADES IN FEATHER, ITSDR CA020904006Actuator · seized(CAN) DURING HORIZONTAL STAB PITCH TRIM TEST/INSPECTION MAINTENANCE FOUND THAT PITCH TRIM ACTUATOR WOULD NOT MOVE IN ALTERNATE TRIM MODE. ACTUATOR WOULD LOAD UP BUT NOT MOVE. AIRCRAFT GROUNDED.SDR CA021003004Relay · failed(CAN) FLIGHT CREW EXPERIENCED UNCOMMANDED UP TRIM ON HORIZONTAL STAB TRIM. SYSTEM WAS DEACTIVATED USING TRIM INTERRUPT SWITCH, AND AIRCRAFT LANDED USING ACT. STAB TRIM. ON INVESTIGATION FAULTY RELAY FOUND (K22) RELAY REPLACED AND SYSTEM TESTED.SDR CA020924001Wire · chafed(CAN) AFTER TAKEOFF, THE PILOT LOST OIL PRESSURE INDICATION, HOWEVER, THERE WAS NO MASTER CAUTION INDICATION. THE PILOT RETURNED TO BASE WITHOUT INCIDENT. INVESTIGATION REVEALED THAT THE WIRE HARNESS, BETWEEN THE OIL PRESSURE TRANSMITTER AND THE FIREWALL CONNESDR CA021003003Tire · leaking(CAN) TIRE RUN FOR 46.0 HOURS TIRE WOULD LEAK 25 PERCENT PER DAY. TIRE LEAKS THROUGH SIDE WALL VENTS. THIS IS SECOND TIRE THIS WEEK TO DO THIS. SECOND TIRE HAD 413 HOURS.SDR CA021003002Liner · worn(CAN) DURING INSPECTION FOUND 10 PERCENT OF BRAKE LININGS WORN BEYOND LIMITS STATED IN CLEVELAND BRAKE MANUAL. EVEN THOUGH LININGS ARE WORN OUT WEAR INDICATORS SHOW BRAKE ASSEMBLY AT HALF LIFE.SDR CA020927003Light · intermittent(CAN) AFTER FLIGHT CREW TURNED ON INTERNAL BATTERY POWER THEY NOTICED THAT THE OVERHEAD ELECTRICAL MANAGEMENT POWER PANEL BACKGROUND LIGHTING WAS FLICKERING. SELECTED SWITCHES WERE ALSO FLICKERING. THE CREW CONTINUED WITH NORMAL OPERATIONS, THE OVERHEAD PASDR CA020923005Actuator · inoperative(CAN) FLIGHT CREW REPORTED AUTOPILOT DISCONNECTED IN FLIGHT AND TRIM INDICATOR WOULD MOVE FULL DEFLECTION WHEN PITCH TRIM OPERATED. SUSPECT INTERNAL FAULT WITH ACTUATOR. ACTUATOR REPLACED.SDR CA020923004Actuator · failed(CAN) FLIGHT CREW REPORTED AUTOPILOT FAILED IN FLIGHT, CREW SUSPECTED PITCH TRIM ACTUATOR DUE TO AN 'OUT OF TRIM' CONDITION WHEN AUTOPILOT FAILS. REMOVED ACTUATOR AND NOTICED THAT THE SHAFT SEAL WAS DIRTY AND WORN, SUSPECT THAT MOISTURE WAS ENTERING ACTUATOR ASDR CA020910006Link · corroded(CAN) THE WORN TRAILING LINK BUSHINGS WERE SCHEDULED TO BE REPLACED DURING THE ANNUAL INSPECTION. UPON REMOVING THE BUSHINGS FROM THE RT TRAILING LINK, SEVERAL SPOTS OF CORRORSION WERE DISCOVERED IN THE MAIN BUSHING BORE. TECH REP. DIRECTED A CHANGE OUT OF DEFSDR CA020904005Bearing · worn(CAN) PILATUS GIVES A 3000 HOUR LIFE TO NR 2 GEN DRIVE OUTER BEARING, BUT NOT TO INNER BEARING. DURING REPLACEMENT OF OUTER BEARING DUE TO T/X, FOUND INNER BEARING UNSERVICEABLE. IT IS NOW OUR POLICY TO REPLACE INNER BEARING AS WELL DURING OUTER BEARING REPLACSDR CA030312010Control Quadrant · failed(CAN) AFTER TAKEOFF THE PILOT SELECTED FLAPS UP. A FLAP WARNING LIGHT ILLUMINATED AND THE FLAPS DID NOT MOVE. (FLAPS REMAINED AT 15 DEGREES). THE PILOT RETURNED TO LAND AT THE AIRPORT WITHOUT INCIDENT. A FLAP RESET WAS CARRIED OUT ON THE GROUND SERVICEABLE.SDR CA020812001Arm · cracked(CAN) DURING TAXI, AIRCRAFT CREW RECEIVED A FLAP WARNING FAULT. THE COMPUTER AUTOMATICALLY DISABLES THE SYSTEM WHEN A WARNING OCCURS SO NO FLAP SELECTION WAS AVAILABLE. ON INSPECTION THE RT INBOARD FLAP DRIVE ARM WAS FOUND CRACKED AT THE WING ATTACHMENT.SDR CA020729013Window · broken(CAN) DURING REMOVAL OF THE MAIN RT WINDSCREEN, IT WAS NOTICED THAT ONE OF THE SCREW ATTACHMENT LUGS ON THE TOP SECTION OF THE RT SIDE WINDOW WAS CRACKED. THE SIDE WINDOW REQUIRED REPLACEMENT.SDR CA020702007Tube · contaminated(CAN) WHILE PERFORMING A REMOVAL / INSTALLATION OF THE FUEL NOZZLES,A SMALL PIECE OF METAL DEBRIS WAS FOUND WITHIN THE INTERNAL PASSAGE OF ONE OF THE FUEL MANIFOLD TRANSFER TUBES. THE DEBRIS WAS LODGED WITHIN THE TUBE AND HAD TO BE EXTRACTED BY PUSHING IT THRSDR CA020628001Tube · contaminated(CAN) WHILE PERFOMING A SCHEDULED REMOVAL / INSTALLATION OF THE FUEL NOZZLES, A SMALL PIECE OF METAL DEBRIS WAS FOUND WITHIN THE INTERNAL PASSAGE OF ONE OF THE FUEL MANIFOLD TRANSFER TUBES. THE DEBRIS WAS LODGED WITHIN THE TUBE AND HAD TO BE EXTRACTED BY PUSHISDR CA020704005Slip Ring · grooved(CAN) INSPECTED GEN NR 2 BRUSHES FOR WEAR DURING SCHEDULED 100 HR INSP. FOUND APPROX 50 PERCENT LIFE REMAINING ON MOD "C" BRUSHES, HOWEVER THE BRUSH SLIP RING CONTACT AREA WAS GROOVED. IAW AIRCRAFT MM IF THERE IS PITTING, GROOVES OR SCORING FOUND ON THE SLIP SDR CA020702008Warning System · failed(CAN) PILOT REPORTED NO MASTER WARNING OR CAUTION LIGHTS WORKING ON A/C.THE SYSTEM SENDS POWER TO LIGHTS FROM CENTRAL ADVISORY & WARNING CONTROL UNIT & PLACES GROUND TO TURN LIGHTS ON. 14.62 VOLTS MEASURED FROM UNIT. AFTER CONSULTING WITH TECHNICAL REPRESENTSDR CA020729014Window · broken(CAN) DURING REMOVAL OF THE MAIN RT WINDSCREEN, IT WAS NOTICED THAT ONE OF LOWER SECTION SCREW ATTACHMENT LUGS ON THE RT SIDE WINDOW WAS CRACKED. THE SIDE WINDOW REQUIRED REPLACMENT.SDR CA020517004Nozzle · contaminated(CAN) REPLACEMENT SET OF ENGINE FUEL NOZZLES WERE RECEIVED FROM P&W ACCESSORIES SERVICES TO REPLACE A PREVIOUSLY RECEIVED U/S SET OF EXCHANGE FUEL NOZZLES. PACKING AGAIN APPEARED NORMAL. ONE FUEL NOZZLE ASSY. WAS FOUND TO BE VISIBLY CONTAMINATED AND DISCOLORESDR CA020517003Fuel Nozzle · corroded(CAN) EXCHANGE FUEL NOZZLE SET WAS ORDERED TO PERFORM ROUTINE MAINTENANCE. SET RECEIVED FROM P&W CANADA ACCESSORIES SERVICES, LONGUEUIL. PACKING BOX APPEARED NORMAL. WHEN IDIVIDUAL NOZZLE PACKINGS WERE OPENED 10 OUT OF 14 HAD VISIBLE CORROSION. SOME WERE RUSTYSDR CA020517005Hub · leaking(CAN) PROPELLER LEAKS GREASE FROM BLADE CLAMP AREA. CAN OBSCURE PILOT'S VIEW THOUGH WINDSHEILD. TEFLON TAPE PROVIDES GREASE SEAL. WORN OUT BEFORE TBO.REPAIR TIME 2/3 DAYS.SDR CA020515008Swivel · leaking(CAN) DURING THE ANNUAL INSPECTION, IT WAS NOTICED THAT THE LOWER RT BRAKE SWIVEL FITTING WAS LEAKING BREAK FLUID. THE PART WAS REPLACED WITH NEW.SDR CA020426001Indicator · malfunctioned(CAN) IN CRUISE FLIGHT, PILOTS NOTICED QUICK RISE OF OIL TEMP, POWER WAS THEN REDUCED WHICH LOWERED THE OIL TEMP SHORTLY AFTER, NEW RISE IN OIL TEMP (LIMITS EXCEEDED), RISE AND FALL OF OIL PRESSURE (WITHIN LIMITS). PILOTS DECLARED EMERGENCY AND LANDED SAFELY.SDR CA020417002Shaft · sheared(CAN) CREW LOST NR 2 GENERATOR IN FLIGHT. AIRCRAFT RETURNED TO BASE AND THE SHAFT WAS FOUND SHEARED.SDR S4W2002F00001Rod Cap · separatedON 100 HOUR INSPECTION THE ROD END BEARING ON THE NOSE GEAR STEERING ORING WAS FOUND TO BE MIGRATING OUT OF THE ROD END ASSEMBLY. IF ROD END WAS NOT REPLACED AND THE BEARING MIGRATED ALL THE WAY OUT OF THE ROD END THEN STEERING CONTROL WOULD BE LOST. THIS COSDR CA020430013Handle · failed(CAN) DURING CLOSING OF DOOR THE HANDLE BROKE IN HALF.THIS IS THE 3RD ONE BROKEN.SDR CA020326010Bolt · worn(CAN) DUE TO PREVIOUS EXPERIENCE REMOVED LEFT AND RIGHT AXLE BOLTS EVEN THOUGH AIRCRAFT WAS POST S/B 32-006 AND DID NOT REQUIRE REMOVAL. BOLT WAS FOUND TO BE WORN AND STEPPED EVEN THOUGH AIRCRAFT WAS LOW TIME.AS BEFORE THERE IS NO REQUIREMENT TO REMOVE THIS BOSDR CA020325002Switch · failed(CAN) PILOT REURNED FROM FLIGHT,LANDED AND WAS TAXIING TO HANGER WHEN HE TRIED TO CENTER HIS HORIZONTAL STAB. TRIM.,USING PILOT'SSWITCH ON CONTROL COLUMN. SELECTING "UP" TRIM,THE INDICATOR SHOWED NO MOVEMENT.SO HE USED THE CO'PILOTS SWITCH AND STAB WAS ABLE TOSDR CA020327004Pressure Switch · failed(CAN) AFTER TAKEOFF, REPORTED THE HYDRAULIC PUMP SEEMED TO RUN LONGER THAN NORMAL, AND THAT THE UNDER FLOOR HEATER WAS NOT FUNCTIONING. INVESTIGATION REVEALED THAT THE HYDRALIC SYSTEM PRESSURE SWITCH WAS INTERMITTENT, CAUSING THE HYDRAULIC PUMP TO RUN UNTILL SDR CA020314002Bolt · corroded(CAN) AIRCRAFT WAS DELIVERED WITH S/B 32-006 COMPLIED WITH THEREBY NOT REQUIRING INSPECTION EVERY 100HRS OF THE MLG TRAILING LINK BOLTS THE SUBJECT AIRCRAFT HAD THE TRAILING LINK SAFETY BOLTS REMOVED FOR OTHER ACESS AND THEY WERE FOUND TO BE BADLY CORRODED ANDSDR CA020326003Drag Link · broken(CAN) ON APPROACH PILOT HEARD A LOAD BANG A FEW SECONDS LATER A SECOND LOUD BANG WAS HEARD. THE NOSE GEAR EXTENDED AND GEAR DOWN AND LOCKED LIGHT CAME ON AS WELL AS NOSE GEAR UNSAFE LIGHT. PILOT SLOWED AIRCRAFT DOWN TO GEAR EXTENDED SPEED SELECTED GEAR DOWN. LSDR 2002F00320Structure · crackedDURING 100 HOUR INSPECTION 2 IDENTICAL CRACKS WERE NOTICED ON THE UPPER VERTICAL STABILIZER, DIRECTLY ABOVE THE RUDDER AND MIGRATING FORWARD APPROXIMATELY 4.5 INCHES. AFTER CONTACTING MANUFACTURER, IT WAS SUGGESTED THAT THE BOTTOM FAIRING OF THE VERTICAL STABSDR CA020306004Window · cracked(CAN) A CRACK WAS FOUND IN THE LT SIDE WINDOW IN THE TOP CORNER EXTENDING FORWARD AND AFT FROM A SCREW HOLE. THE CRACK WAS NOT VISIBLE INSTALLED IN THE AIRCRAFT. IT WAS DISCOVERED WHILE REMOVING FOR A DIFFERENT REASON. SIDE WINDOW WAS REPLACED AND AIRCRAFT RSDR CA020227004Swivel · leaking(CAN) HYD BRAKE FLUID WAS NOTED LEAKING FROM THE SWIVEL FITTING ON THE BRAKE LINE ,LT MLG TRAILING LINK AREA. PART REPLACED WITH NEW, BRAKES BLED, RETURNED TO SERVICE.SDR CA020226016Attach Fitting · cracked(CAN) AIRCRAFT WAS IN ROUTE TO HOME BASE AND 20 MINUTES INTO ITS FLIGHT WNEN THE OIL TEMPERATURE DROPPED FROM 60 C TO 40 C AND THE OIL PRESSURE WENT UP THE BOTTOM OF THE RED LINE WHICH IS 130 PSI.THE PROBLEM WAS THE OIL COOLER DOOR HINGE HOLDER CRACKED AND ALLSDR CA020225002Fan Blade · bent(CAN) CREW REPORTS GROWLING NOISE WHEN TURNING ON CABIN HEATER. INSPECTED CABIN HEATER INLET DUCT AND FOUND I.D.TAG FROM BAGGAGE NET JAMMED IN FAN SHROUD. CABIN HEATER REQUIRED REPLACEMENT. INLET IS LOCATED BELOW REAR BAGGAGE AREA AND HAS FAIRLY LARGE GRILL OPSDR CA020218002Shaft · broken(CAN) WHILE ON APPROACH, PILOT REPORTED THAT WHEN HE SELECTED 30 DEGS OF FLAP HE GOT FLAP WARNING ON CAWS PANEL. NO EFFECT ON FLT CONTROLS AND HE LANDED WITH OUT INCIDENT. PILOT RESET FLAPS ON GROUND AND TRIED TO RETRACT FLAPS. FLAPS WOULD NOT RETRACT AND FLAPSDR CA020215016Relay · intermittent(CAN) LANDING GEAR WOULD NOT EXTEND. PILOT HAD TO USE EMERGENCY EXTENSION. MAINTENANCE FOUND THE POWER PACK RELAY WAS ACTUATING YET NO POWER WOULD GO THROUGH.RELAY WAS REPLACED AND AIRCRAFT RETURNED OT SERVICE.
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