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 CA040811005Tire · leaking(CAN) TIRE WAS LOOSING AIR PRESSURE, ON INVESTIGATION IT WAS NOTED THAT THE AIR WAS LEAKING FROM HOLES THAT ARE LOCATED JUST UP FROM THE BEAD/SEAT AREA, APPARENTLY TO VENT AIR FROM BETWEEN THE LAYERS OF THE RUBBER. THIS IS THE THIRD TIME THAT WE HAVE CHANGED SDR CA040805004Generator · damaged(CAN) GENERATOR WAS OVERHAULED AND INSTALLED ON THE AIRPLANE ON JULY 13TH 2004. ON JULY 30TH, (85.2) FLIGHT HOURS LATER THE STARTER DID NOT TURN DURING A ATTEMPTED ENGINE START AND AFTER TROUBLESHOOTING IT WAS DISCOVERED THAT THE STARTER HAD FAILED. THIS IS THSDR CA040730009Skin · worn(CAN) THE UPPER ATTACHMENT HOLE WAS FOUND WORN. THE HOLE WAS SO LARGE THAT IT COULD NOT BE REPAIRED IAW MFG TECH MEMO ECE-12-TM-02-327. IN ORDER TO SEE THE BOLT AND DAMAGE AREA, PANEL 32AT HAD TO BE REMOVED TO SEE THE DEFECT. THIS PANEL IS NOT NORMALLY CALLESDR 2004FA0000707Fcu · failedLOSS OF ENGINE POWER AND LOW TORQUE INDICATION. ENGINE SHUT DOWN, PROP FEATHERED, EMERGENCY LANDING EXECUTED. (M)SDR CA040730002Control Valve · inoperativeDURING CRUISE, THE AIR TEMP SELECTOR WHILE IN AUTO MODE WAS MOVED TO A MORE COOL POSITION, WITH NO EFFECT. ECS SWITCH WAS MOVED TO MANUAL MODE AND MORE COOL WAS TOGGLE WITH THE MANUAL SWITCH. AIR TEMP STILL NOT GETTING COOLER. MINUTES LATER THE ECS CAUTION SDR CA040726007Bearing · failed(CAN) GENERATOR HAD BEEN REPAIRED, WO NR 12585, MAR 18,2004. INSTALLED ON VKC WITH 442.9 TSO AND 0 HOURS SINCE REPAIR. APPARENT BEARING FAILURE. WOULD NOT ENGAGE/TURN ON, AN ATTEMPTED START.SDR CA040713010Switch · intermittent(CAN) WHILE PERFORMING DAILY INSPECTION AND REPORTED INTERMITTENTLY BY PILOT THAT TWO LIGHT SWITCHES ON CONTROL PANEL. OCCASIONALLY WILL NOT SWITCH (OFF) OR SOMETIMES WILL NOT REMAIN IN (ON) POSITION THIS WOULD OCCUR INTERMITTENTLY AND IT WAS DISCOVERED. PROBSDR CA040713009Exhaust Stack · cracked(CAN) LT EXHAUST STACK CRACKED FROM ONE MOUNTING HOLE OUTWARDS. STACK REPLACED WITH SERVICEABLE UNIT. CRACK DISCOVERED DURING ENGINE INSPECTION.SDR CA040712006Valve · failed(CAN) TEMP CONTROL VALVE FOUND TO BE AT FAULT AFTER CREW COMPLAINED OF ECS HEAT NOT RESPONSIVE. VALVE REPLACED WITH REPAIRED UNIT, RETURNED TO SERVICE.SDR CA040709008Warning Flag · malfunctioned(CAN) (OFF) WARNING FLAG DOES NOT COMPLETELY GO OUT OF VIEW. GYRO WAS FUNCTIONING NORMALLY AND FLAG SEEMS TO BE DISLOCATED TOO FAR TO THE RIGHT AS COMPARED TO A SERVICEABLE UNIT.SDR CA040630003Controller · malfunctioned(CAN) DURING DESCENT CABIN PRESSURE WAS LEADING PRESSURE DIFFERENTIAL MORE RAPIDLY AND GREATER THAN NORMAL. DETERMINED THAT THE OUTFLOW VALVE CONTROLLER WAS NOT CONTROLLING OUTFLOW VALVE MOVEMENT PROPERLY. NO OVERPRESSURES (DIFFERENTIAL) WERE NOTED. PART WASDR CA040709009Pdu · failed(CAN) FLAPS WERE SELECTED UP, RETRACTED NORMALLY. FLAPS WERE SELECTED DOWN, EXTENDED NORMALLY. FLAPS WERE RETRACTED ONCE MORE, OPS WERE NORMAL. FLAPS WERE SELECTED DOWN, WHEN THEY REACHED 15 DEGREE POINT, STARTED TO BIND AND FLAP RESET WAS PERFORMED. FLAPS WERSDR CA040630006Brake Assy · failed(CAN) WHILE ON TAXI FROM THE HANGER RAMP TO TAXI WAY, THE AIRCRAFT MADE A SUDDEN MOVE TO THE RT AND A LOUD GRINDING METALLIC SOUND WAS HEARD IN THE AIRCRAFT. THE AIRCRAFT ENGINE WAS SHUT DOWN ON THE TAXIWAY AND AN INVESTIGATION WAS CONDUCTED IN THE AREA OF THESDR CA040630004Tube · cracked(CAN) CRACK WAS DISCOVERED AT INSPECTION NEXT TO EXHAUST TUBE USED TO SUPPLY ENGINE EXHAUST TO COWLING LIP DEICE. ABOUT ONE INCH FROM ENGINE MOUNTING FLANGE , CRACK WAS ABOUT ONE AND A QUARTER INCH LONG. REPAIR PERFORMED IAW MM CHAPTER 78 10-01.SDR CA040621005Pressure Switch · leakingLOW PRESSURE HYDRAULIC SWITCH (P/N 973.81.14.304) LEAKING FROM VENT HOLE. SIMILAR PROBLEMS FOUND WITH HIGH PRESSURE SWITCH (P/N 973.81.14.306).SDR CA040616007Bushing · wornEXCESSIVE UP AND DOWN MOVEMENT FOUND IN STEERING SECTION OF NOSE LANDING GEAR. BRONZE BUSHINGS FOUND TO BE WORN (P/N 532.20.12.078) IT IS BELIEVED THAT WHEN GREASING THE NOSE GEAR ASSEMBLY, THE CONTACT SURFACES OF THE BUSHINGS ARE NOT GETTING PROPER LUBRICATISDR CA040616003Relay · frozenLANDING GEAR MOTOR CONTINUED TO RUN AFTER LANDING GEAR WAS DOWN AND LOCKED. AIRCRAFT LANDED AND TAXIED TO APRON. FLIGHT CREW TURNED OFF MASTER TO STOP MOTOR FROM RUNNING. MAINTENANCE WAS CALLED TO PULL UNDER FLOOR POWER PACK CIRCUIT BREAKER. MAINTENANCE CHSDR CA040608001Drive Shaft · shearedON RETURN, PILOT NOTED GEN 2 FAILURE IN CRUISE AND CONT`D ON TO COMPLETE FLT. NR 1 GEN AUTO COVERS FOR NR 2 GEN WHEN A FAILURE OCCURS. INVESTIGATION BY MX REVEALED SHEARED DRIVE SHAFT FOR NR 2 GEN. SHAFT BROKE AT PROPER SHEAR POSITION WITH NO DAMAGE TO ANY SDR CA040621007Proximity Switch · failedNOSE GEAR DOWN PROXIMITY SWITCH NOT GIVING DOWN AND LOCKED INDICATIONS ON NOSE GEAR. REOCCURRING PROBLEM AROUND THE 9000-10000 CYCLE RANGE ON PC-12'S. PC-12'S INCORPORATE THESE SWITCHES IN THE NOSE GEAR UP AND DOWN LOCK INDICATION POSITIONS THE MAIN GEAR UPLSDR CA040621004Switch · stickingFLAP UP SWITCH STICKING IN ALL ENVIRONMENTAL CONDITIONS CAUSING FLAP FAILURES IN FLIGHT AND ON GROUND. FLIGHT CREWS SHOULD BE AWARE THAT IF FAILURE OCCURS AND FLAPS ARE SET AT 15, 30 OR 40. THE ONBOARD COMPUTER WILL NOT GIVE THE AIRSPEED WARNING AT 165 KTS. SDR CA040616004Switch · stickingFLAP DOWN SWITCH IS STICKING IN ALL ENVIRONMENTAL CONDITIONS CAUSING FLAP FAILURES BOTH IN FLIGHT AND ON THE GROUND. BETTER SEALS OR DUST CAPS MAY SOLVE THE PROBLEM.SDR CA040621002Drive Assy · crackedRT INBOARD FLAP DRIVE ARM FOUND CRACKED DURING SCHEDULED MAINTENANCE AT THE ATTACHMENT POINT OF THE FLAP INTERCONNECT CABLE. FREQUENT FREEZING OF THE FLAP INTERCONNECT CABLE BELIEVED TO BE THE CAUSE OF PROBLEM. PILATUS SB 27-010 STATES THAT THE DISCONNECTIONSDR CA040616010Bracket · crackedCOUNTERBALANCE BRACKET ON PASSENGER DOOR FOUND CRACKED ON SCHEDULED INSPECTION. THE BRACKET IS OFTEN FOUND LOOSE DUE TO THE RIVETS USED ON INSTALLATION ARE NOT OF SUFFICIENT STRENGTH. RECOMMEND USING STRUCTURAL SCREWS OR BOLTS TO SECURE BRACKET TO PREVENT FUSDR CA040616008Handle · brokenINNER PASSENGER DOOR HANDLE BROKE OFF WHEN TRYING TO OPEN DOOR. THIS IS A REOCCURRING PROBLEM BELIEVED TO BE CAUSED BY A COMBINATION OF FACTORS INCLUDING:1) CONDENSATION IN THE DOOR CAUSES TO UNLOCKING MECHANISM CABLE TO FREEZE.2) THE SPRING USED ON THE SECONSDR CA040616005Fairing · crackedCRACKS FOUND AROUND SCREW HOLES ON MAIN WHEEL FAIRING. REOCCURRING PROBLEM ON MANY OF OUR AIRCRAFT. AVERAGING 600 TO 700 HOURS PER FAIRING.SDR CA040604003Seal · damaged(CAN) AIRCRAFT HAD JUST LANDED AND SHUT DOWN AT IT'S DESTINATION AIRPORT. THE PILOT DISEMBARKED THE AIRCRAFT AND NOTICED A LARGE STREAK OF OIL DOWN THE LT SIDE OF THE FUSELAGE. MAINTENANCE INVESTIGATED THE INCIDENT AND FOUND ANOTHER LARGE OIL STREAK DOWN THE BSDR CA040601012Heater · inoperativeP-S 2 FAIL INDICATION. NR 2 PITOT HEAT FOUND INOP. PITOT TUBE ASSY REPLACED WITH NEW. AIRCRAFT TTAF 3710.72576 CYC.SDR CA040601011Annunciator · inoperative'FD' ANNUNCIATOR LIGHT INOP. FLIGHT DIRECTOR COMMAND BARS FUNCTION OK. UNIT REPAIRED AT LOCAL AVIONICS FACILITY, REINSTALLED.SDR CA040601010Pressure Switch · leakingHYD PRESSURE SWITCH WAS FOUND TO HAVE A SLIGHT SEEPAGE OF HYDRAULIC FLUID AT THE SWITCH BODY SEAM. SWITCH REPLACED WITH NEW, GROUND CHECKS SATISFACTORY.SDR CA040526009Relay · failedAFTER LANDING PILOTS TRIED TO RETRACT THE FLAPS BUT COULD NOT GET THEM TO MOVE. AIRCRAFT WAS INSPECTED AND FLAP UP RELAY WAS FOUND TO HAVE FAILED, P/N 974.20.01.902. RELAY WAS REPLACED AND FLAP SYSTEM TESTED. AIRCRAFT RETURNED TO FLIGHT LINE.SDR CA040521004Control Valve · malfunctioned(CAN) THE PILOT REPORTED THAT THE 'OVERTEMP' LIGHT ON THE CAWS PANEL CAME ON DURING FLIGHT. WHEN THE TEMPERATURE CONTROL WAS TURNED DOWN, THERE WAS NO CHANGE IN THE CABIN TEMP OR THE INDICATION ON THE CAWS PANEL. THE PILOT SELECTED THE ECS SWITCH TO MANUAL, WHSDR CA040421002Terminal · burned(CAN) THE AIRCRAFT WAS HAVING PROBLEMS WITH THE WINDSCREEN DE-ICE SYSTEM. THE MAIN POWER INPUT LEAD TO THE GENERATOR 2 BUSS WAS FOUND BURNED AND CORRODED. A NEW TERMINAL WAS INSTALLED AND THE SYSTEM FUNCTIONED NORMALLY.SDR 2004FA0000350Line · separatedPILOT EXPERIENCED AN ALTITUDE PORPOISE WITH AUTOPILOT ENGAGED. AIRSPEED IND INDICATED THAT AIRSPEED WAS DECREASING, ALTHOUGH AIRSPEED REMAINED SAME. BOTH PITOT SYS WERE CHECKED, OK. RT STATIC SYS WAS CHECKED, FOUND TO BE OK. THE LT STATIC SYS WOULD NOT PRESSDR CA040401006Actuator · failed(CAN) AUTO-PILOT TEST FAILED. ALTERNATE TRIM WAS SELECTED AND TESTED AND FOUND TO BE INTERMITTENT. PITCH TRIM ACTUATOR WAS REPLACED. NO FURTHER ACTION REQUIRED. PITCHTRIM FAILED TO MAKE OVERHAUL LIFE.SDR S642004F00000Powerpack · inoperativeSMOKING AT LT WING FAIRING EDGES. FAIRING PULLED, FOUND HYD PKG SOFT START RESISTOR SMOKED AS WELL AS LARGE BLACK AREA ON FUSELAGE BLACK. INSIDE OF WING FAIRING BURNED AND BUBBLED ON OUTSIDE. INSTALLED NEW RESISTOR AND NEW HYD UNIT SELECT RELAY. PULLED NR SDR CA040323002Pump · cracked(CAN) AIRCRAFT WAS ON DECENT. WHEN GEAR DOWN WAS SELECTED DOWN GRINDING NOISES WERE HEARD IN THE CABIN AND THE NOSE DOWN AND LOCKED LIGHT WAS NOT ILLUMINATED. EMERGENCY PROCEDURES WERE USED TO GET THE NOSE DOWN LOCKED LIGHT AND THE A/C WAS LANDED WITHOUT FURTHSDR CA040331006Isolator · misrepaired(CAN) DURING A SCHEDULED ENGINE CHANGE NEW ENGINE MOUNT ASSEMBLIES WERE BEING INSTALLED. THREE OUT OF FIVE NEW ENGINE MOUNT FORWARD VIBRATION ISLOATORS HAD A BUSHING DIAMETER TOO SMALL TO ALLOW INSERTING THE NEW ENGINE MOUNT BOLTS. EVEN THE OLD ENGINE MOUNT BOSDR CA040311007Light · failed(CAN) NAVIGATION LIGHT ASSEMBLY (TAIL) APPEARS TO HAVE PROBLEMS WITH THE TOP BULB BURNING OUT. THERE HAS BEEN 8 BULBS P/N 972.87.87.184 REPLACED WITHIN 7 DAYS. THE COMPLETE ASSEMBLY HAS BEEN REPLACED ALONG WITH A ELECTRONIC SWITCH UNIT. THE SAME RESULTS. THE BSDR CA040311005Pump · inoperative(CAN) WHILE IN CRUISE FLIGHT THE PILOT NOTED A 2 LED DIFFERENCE BETWEEN LT AND RT FUEL INDICATORS. A FEW MINUTES LATER THE RT BOOST PUMP LT INDICATOR CAME ON. THE LT REMAIN ON FOR THE DURATION OF THE FLIGHT AND THE FUEL IMBALANCE REMAINED. ON THE GROUND THE FSDR CA040301003Drive Shaft · sheared(CAN) ON RETURN FLIGHT, THE FLIGHT CREW HAD A GEN 2 FAILURE SO DECREASED ELECTRICAL LOAD AND CONTINUED TO MAINTENANCE BASE. MAINTENANCE REMOVED THE GEN 2 AND INSPECTED IT FOR ANY FAULTS. A REPLACEMENT GENERATOR WAS BEING INSTALLED WHEN IT WAS NOTICED THAT THSDR CA040224006Warning Light · illuminated(CAN) 3 GREEN ANNUNICATOR LIGHTS CAME AS WELL AS RED WARNING LIGHT ON LT MLG. AC DID FLY OVER TO CONFIRM LT MLG WAS DOWN. PILOT SELECTED 30 DEGREES OF FLAP TO SLOW AC DOWN. WHEN 30 DEGREES OF FLAP WAS REACHED, 3 RED WARNING LIGHTS FOR LT MLG CAME ON. AC LANSDR CA040316004Bearing · worn(CAN) OPERATOR HEARD GRINDING NOISE DURING ENGINE START. NOISE WAS LOUDEST AT 10 PERCENT NG. ABORTED START AND INVESTIGATED. FOUND RADIAL PLAY AT FAN END OF ARMATURE. REPLACED STARTER GEN. SENT FAILED UNIT FOR REPAIRS. FOUND THE ADE BEARING HAD RADIAL PLSDR CA040217012Starter Gen · inoperative(CAN) DURING AN ENGINE START THE PILOT NOTED THERE WAS AN ABNORMAL NOISE GENERATING FROM THE ENGINE. THE NOISE WAS NOTICEABLE AROUND 10 PERCENT GG SPEED AND DISAPPEARED AFTER STABLE RPM WAS REACHED AT 17 PERCENT GG SPEED. THE STARTER GENERATOR WAS REPLACED ANDSDR CA040209011Wire · broken(CAN) LT MLG GREEN INDICATION WAS INTERMITENTLY LOST. FAULT COULD BE DUPLICATED BY WIGGLING THE WIRES AT THE ACTUATOR PLUG. WIRE G21A24 FOUND BROKEN AT P055 CONNECTOR, REPAIRED, GROUND TESTS SATISFACTORY.SDR CA040206004Display · failed(CAN) DURING CRUISE THE CREW NOTICED SOME OF THE CAWS LIGHTS OUT. THE TEST BUTTON WAS USED TO DETERMINE IF THE BULBS WERE AT FAULT. ONCE PRESSED THE CAWS PANEL AND MASTER CAUTION/WARNING ILLUMINATED FOLLOWED A SERIES OF FLICKERING LIGHTS AND A ODOR OF BURNED SDR CA040205006Display · failed(CAN) DURING CRUISE FLIGHT, THE UPPER PORTION OF THE ENGINE INDICATION SCREEN FAILED TQ, NG, & ITT. THE ALTERNATE SCREEN WAS SELECTED AND PERFORMED PROPERLY. THE EIS COMPUTER WAS REPLACED WITH A SERVICEABLE UNIT AND FUNCTION TREATED SERVICEABLE. IT WAS NOTED SDR CA040206005Wire · burned(CAN) ONE POWER WIRE FOR THE FOOT HEATER HEAT CONTROL HAD FALLEN ON TO THE BRAKE LINE THAT RUNS ALONG THE FIREWALL JUST AHEAD OF THE RUDDER PEDALS. AS A RESULT ARCING OCCURED AND BURNED A HOLE IN THE LINE. THE .2500 INCH ALUMINUM BRAKE LINE WAS REPLACED, SYSTSDR CA040204010Bearing · failed(CAN) GEN NR 1 FAILED IN FLIGHT. UPON ARRIVAL, MAINTENANCE FOUND THE REAR BEARING OF THE STATER GENERATOR FAILED CAUSING THE COOLING FAN TO RUB ON THE CASE.CREATING VIBRATION. STARTER GENERATOR REPLACED.SDR CA040204009Pin · missing(CAN) PAX/CREW DOOR HANDLE LOCKING MECHANISM HARD TO OPERATE EXCEPT UPON ARRIVAL AT MAIN BASE. INSPECTING DOOR, FOUND PIN LOCK AND ITS SPRING FROM SAFETY LOCKING MECH TO BE MISSING. LOCKING MECH STOPS ACCIDENTAL OPERATION OF DOOR HANDLE INSIDE AC. RELEASE LESDR CA040122001Cylinder · defective(CAN) PROPELLER CYLINDER FOUND DEFECTIVE. MANUFACTURE DEFECT IN THE C AREA MISSING MATERIAL. THIS HAS BEEN SEEN IN SEVERAL OTHER CYLINDERS, MFG WAS CONTACTED ON ALL OF THE DEFECTIVE ASSEMBLIES. MFG INSPECTED AND ANALYZED THEM ALL AND HAS NOT PROVIDED ANY LIM
Back to Pilatus PC-12/45