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 CA020226003Display · failed(CAN) - POWER FAILURE IN CAWS DISPLAY UPON START UP.- DISPLAY & CONTROL UNIT REMOVED DIRECTED FOR BENCH CHECK.- REPLACED DISPLAY & CONTROL UNIT, NORMAL OPERATION RESULTS.SDR CA020212001Attach Fitting · loose(CAN) ATTACHMENT BRACKET FOR CABIN DOOR COUNTER BALANCE SYSTEM FOUND WITH LOOSE RIVETS. RIVETS REMOVED AND REPLACED WITH CR3243-4 BLIND RIVETS.SDR CA020214002Relay · failed(CAN) WHILE IN CRUISE FLT "ESSENTIAL BUS" WARNING LIGHT ILLUMINATED ON CAWS PANEL. NR 2 BATTERY OBSERVED TO BE DISCHARGING AT APPROX 35 AMPS & SELECTED TO OFF POSITION. DISCHARGE RATE FROM BATTERY STOPPED & "ESSENTIAL BUS" LIGHT WENT OUT. WITHIN 3 MINS AOA CSDR S4W2002F00000Rod End · separatedPILOT CALLED THE ON-CALL MECHANIC AND REPORTED THAT UPON LANDING AT AIRPORT, THE NOSE WHEEL STEERING DID NOT FEEL NORMAL. AFTER ENGINE SHUT DOWN THE PILOT LOOKED IN NOSE GEAR WELL AND FOUND THE NOSE WHEEL STEERING ROD AND EYELET HAD SEPARATED FROM THE ROD ENDSDR CA020117012Exciter · failed(CAN) PILOT WENT TO START ENGINE AND HAD NO LIGHT OFF.TRIED TWICE TO START ENGINE AND HAD NO LIGHT OFF. IGNITION EXCITOR BOX WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.NOTE: THIS IS TYPICAL FOR PILATUS IGNITOR BOX. THE SAME BOX WILL LAST 2-3 TIMES LONGESDR CA020115001Symbol Generator · inoperative(CAN) WHEN A/C POWERED UP, LOWER PILOT'S EFIS DISPLAY REMAINED BLANK. LOWER CO-PILOTS EFIS DISPLAY SWITCHED FOR TROUBLE SHOOTING. DISPLAY ALSO REMAINED BLANK. WHEN DISPLAY RETURNED TO IT'S ORIG POSSITION, IT REMAINEDBLANK AS WELL. IT DETERMINED THROUGH FURTHERSDR CA020103018Panel · failed(CAN) EIS GIVING FALSE READING FOR ITT. EIS PANEL REPLACED.SDR CA011217013Starter Gen · wrong part(CAN) STARTER- GEN REMOVED PREMATURELY AT 950 HRS TSO DUE TO UNIT BEING VERY NOISY AT LOWER RPMS. UNIT TAKEN TO AMO FOR OVERHAUL. ON DISASSEMBLY, IT WAS NOTICED THAT UNIT DOES NOT PHYSICALLY CORRESPOND WITH MANUFACTURE`S STARTER-GEN.SDR CA011217004Drive Shaft · worn(CAN) DURING ROUTINE 3000 HOUR INSPECTION THE DRIVE SHAFT WAS FOUND TO BE WORN AT THE FWD END OF THE SHAFT. THIS CAUSED THE SHAFT TO WOBBLE EVEN WITH THE NEW BEARING IN PLACE.FWD BEARING WAS NOT SIEZED OR STIFF.NEW SHAFT AND BEARINGS INSTALLED.SDR CA020103003Powerpack · cracked(CAN) DURING A DAILY INSPECTION BY MAINTENANCE STAFF AT THE COMPLETION OF SCHEDULED FLIGHT. HYDRAULIC FLUID WAS FOUND AT LH WING ROOT, BOTTOM OF WING,WHERE ACCESS PANEL IS LOCATED FOR HYDRAULIC POWER PACK. THE AMOUNT OF FLUID LOST DID NOT EFFECT OPERATION OF SDR CA011210020Drive Shaft · worn(CAN) 3000 HR. REPLACEMENT OF OUTER DRIVE SHAFT BEARING WAS CARRIED OUT. ON DISASSEMBLY OF DRIVE HOUSING ASSEMBLY, THE INNER BEARING MOUNTING SURFACE OF DRIVE SHAFT WAS FOUND WORN DUE TO DRIVE SHAFT SPINNING IN THE INNER RACE OF THE BEARING.A NEW DRIVE SHAFTSDR CA020103017Display · malfunctioned(CAN) MISC. WARNINGS LITES ILLUMINATED ALONG WITH MASTER CAUTION EVEN THOUGH ALL SYSTEMS WERE FUNCTIONING NORMALLY. ALSO CAWS DISPLAY WOULD NOT PASS LITE TEST. CAWS DISPLAY REPLACED.SDR CA011127012Contactor · shorted(CAN) WHILE LOWERING THE FLAPS DURING ROUTINE MAINTENANCE, THE FLAP POWER DRIVE UNIT (PDU )WAS LABOURING. THE FLAP DRIVE SHAFTS WERE DISCONNECTED AT THE PDU, BUT THE PDU WAS STILL LABOURING. THE PDU WAS REPLACED, BUT THE CONDITION STILL PERSISTED. THE K670 CSDR CA011120002Fcu · malfunctioned(CAN) THE PILOT REPORTED AN AMBER FLAPS LIGHT ON THE CAWS PANEL WHEN THE AIRCRAFT POWER WAS TURNED ON. THE AIRCRAFT WAS ON THE GROUND OUTSIDE FOR APPROXIMATELY THREE HOURS, OUTSIDE TEMPERATURE WAS -20C. ONCE TEH AIRCRAFT HAD BEEN WARMED UP IT WAS POSSIBLE TOSDR 2001F00637Engine · making metalENGINE OIL ANALYSIS SHOWED A CLIMBING TREND IN MAGNESIUM AND IRON AMOUNTS. AFTER THREE SAMPLES, IN ACCORDANCE WITH MANUFACTURER, REMOVED AND SENT ENGINE TO THEM FOR INSPECTION AND REPAIR.SDR CA011113007Wire · broken(CAN) DURING PROP DEICE OPERATION THE SYSTEM INDICATED A FAILURE.UPON INVESTIGATION / TROUBLESHOOT IT WAS FOUND THE HARNESS P/N 3E23060-2 HAD AN INTERNAL BREAK WITH LITTLE OR NO CONTINUITY WHILE MOVING THE HARNESS AS INSTALLED.PART WAS REMOVED NEW ONE INSTALLSDR CA011120001Brush Holder · worn(CAN) DURING A 100 HOUR INSPECTION, THE BRUSH ASSEMBLY WAS REMOVED TO VERIFY THE CONDITION. THE BRUSH ASSEMBLY WAS WORN EXCESSIVELY, AND HAS BEEN REPLACED.SDR CA011108013Wire · broken(CAN) PILOT REPORTED PROP DE-ICE SYSTEM OPERATING INTERMITTENTLY. INVESTIGATION REVEALED THAT THE GROUND WIRE IN THE HARNESS BETWEEN THE BACKING PLATE TERMINAL BLOCK AND THE BLADE DE-ICER BOOT WAS BROKEN INTERNALLY. WITH FEATHERING AND UNFEATHERING OF THE PROPSDR CA011031001Wire · chafed(CAN) DURING CRUISE, THE STROBE LIGHT CIRCUIT BREAKER POPPED. THE CIRCUIT BREAKER WAS NOT RESET IN FLIGHT. INVESTIGATION REVEALED A CHAFED WIRE (P/N L08E20) IN THE LEFT HAND WING. THE WIRE WAS REPAIRED AND THE AIRCRAFT RETURNED TO SERVICE.SDR CA011127009Drive Shaft · worn(CAN) WHILE CARRYING OUT REPLACEMENT OF GEN 2 DRIVE ASSY OUTER BEARING FOR 3000 HR REQUIREMENTS, IT WAS NOTED THAT THE DRIVE SHAFT WAS WORN AT THE BEARING JOURNAL AND THE BEARING WAS LOOSE ON THE SHAFT. THE DRIVE SHAFT HAD TO BE REPLACED.SDR CA011023002Display · failed(CAN) LOWER HALF OF EIS PANEL WOULD GO BLANK INTERMITTENTLY. TORQUE ITT, NG AND FUEL INDICATION TAPES REMAINED NORMAL. ALL OTHER INSTRUMENTS WERE AFFECTED, EITHER FLASHING, DISAPPEARING TOTALLY AND/OR INDICATING ERRONEOUS INFORMATION.YELLOW AND RED CAUTION LISDR 2001F00580Actuator · leakingDURING 100 HR INSPECTION, FOUND RIGHT GEAR ACTUATOR SEEPING HYDRAULIC FLUID DURING RETRACTION TESTS. REMOVED AND REPLACED ACTUATOR WITH SERVICEABLE PART IAW AMM CHPT 32 AND OPS CHECK OK.SDR CA011023001Display(CAN) EIS DISPLAY LIGHTING IS VERY DIM, BARELY READABLE.IT WAS ALSO INTERMITTENTLY FLASHING FROM BRIGHT TO DIM. ACQ DISPLAY REPLACED WITH ASERVICEABLE UNIT. A/C TIME SINCE NEW 435.2 CYCLES SINCE NEW 493 THE ACQUISITION DISPLAY HAS 135.3 HOURS.SDR 2001F00581Sensor · faultyDURING FINAL APPROACH THE ECS CAWS LIGHT ILLUMINATED AND THE ECS SYSTEM SHUT DOWN. TROUBLESHOT SYSTEM AND FOUND THE DUCT TEMP SENSOR TO BE FAULTY. REMOVED AND REPLACED WITH SERVICEABLE IAW AMM CHPT 21 AND OPS CHECK OK.SDR CA011011015Stop · missing(CAN) WHILE CARRING OUT ANNUAL INSPECTION IT WAS NOTED THAT THIS AILERON BELLCRANK STOP ON THE LEFT HAND WING WAS MISSING. LOOKING AT THE STOP ON THE RIGHT HAND WING IT APPEARS TO BE JUST A PLASTIC STOP PUSHED INTO A HOLE IN THE WING STRUCTURE.SDR CA011011022Wire · pinched(CAN) ON REMOVAL OF THE BOOSTER PUMP, IT WAS FOUND THAT THE WIRE HARNESS, WHICH IS PART OF THE PUMP HAD APPEARED TO HAVE BEEN TRAPPED BETWEEN THE BOOSTER PUMP MOUNTING PLATE & THE AIRFRAME. THIS HAS CAUSED ONE WIRE OF THE HARNESS TO BE CRIMPED FLAT & THE INTERSDR CA010927001Drag Link · broken(CAN) FAILURE OF PN 532.20.12.072 NOSE GEAR DRAG LINK ON 25TH JUNE 2001. SENT IT OUT FOR INDEPENDENT FAILURE ANALYSIS & CAME BACK WITH CORROSION PITTING AS CAUSE FOR COMPROMISED STRUCTURAL STRENGTH.SDR CA010926001Indicator · failed(CAN) CREW REPORTED JUST PRIOR TO LEVELING AT FL250, THE NR 1 EADI (UPPER PILOT WAS FLAGGED WITH "ATITUDE FAIL" .SUBSEQUENTLY, THE FLIGHT DIRECTOR AND AUTOPILOT KICKED OFF LINE.CREW SELECTED NR 2 AHRS AND FLIGHT CONTINUED UNEVENTFULLY TO THE NEXT DESTINATION. SDR FE62001F00001Adapter · leakingFLIGHT CREW REPORTS FUEL SMELL IN COCKPIT ON THIS LOW TIME AC. MAINTENANCE FOUND RAW FUEL IN THE ENGINE COWLING. FUEL IS NOTED TO BE SEEPING FROM THE INLET FITTING (ADAPTER) ON THE LOW PRESSURE ENGINE DRIVEN FUEL PUMP. REPLACING THE ADAPTER RESOLVED THE DISSDR FE62001F00000Fitting · leakingFLIGHT CREW REPORTS FUEL SMELL IN COCKPIT. MAINTENANCE FOUND RAW FUEL IN THE ENGINE COWLING. FUEL IS NOTED TO BE SEEPING FROM THE INLET FITTING (ADAPTER) ON THE LOW PRESSURE ENGINE DRIVEN FUEL PUMP. REPLACING THE ADAPTER RESOLVED THE DISCREPANCY.(K)SDR 2001F00332Engine · making metalENGINE OIL ANALYSIS SHOWED A CLIMBING TREND IN THE MAGNESIUM AND IRON AMOUNTS. AFTER THREE SAMPLES, IN ACCORDANCE WITH THE MANUFACTURER, REMOVED AND ENGINE AND SENT TO MANUFACTURER FOR INSPECTION AND REPAIR.SDR 2001F00333Engine · making metalENGINE OIL ANALYSIS SHOWED A CLIMBING TREND IN THE MAGNESIUM AND IRON AMOUNTS. AFTER THREE SAMPLES, IN ACCORDANCE WITH THE MANUFACTURER, REMOVED ENGINE AND SENT TO MANUFACTURER FOR INSPECTION AND REPAIR.SDR 2001F00331Engine · making metalENGINE OIL ANALYSIS SHOWED A CLIMBING TREND IN THE MAGNESIUM AND IRON AMOUNTS. AFTER THREE SAMPLES, IN ACCORDANCE WITH THE MANUFACTURER, REMOVED ENGINE AND SENT TO MANUFACTURER FOR INSPECTION AND REPAIR.SDR CA010917006Brushes · worn(CAN) NR 2 GENERATOR FAILED IN CRUISE FLIGHT. NR 2 GENERATOR WAS TURNED OFF, AND AIRCRAFT RETURNED TO BASE. INVESTIGATION REVEALED NR 2 GENERATOR BRUSHES WORN. NR 2 GENERATOR BRUSH HOLDER ASSEMBLY P/N 978.96.01.090 REPLACED WITH NEW, AIRCRAFT GROUND RUN AND CSDR CA010917001Brushes · worn(CAN) THE NR 2 GENERATOR CAUTION LIGHT ILLUMINATED ON CAWS PANEL. EIS INDICATED THAT NR 2 GENERATOR HAD COME OFF LINE.THE PILOT THEN RE-SELECTED GENERATOR SWITCH TO ON POS,&HAD SAME SEQUENCE OF EVENTS OCCUR AGAIN. NR 2 GENERATOR WE AS LEFT OFF LINE FOR REMAINDSDR CA010912016Harness · chafed(CAN) WHILE MOVING THE ELEVATOR CONTROL, A SLIGHT "CATCH" COULD BE FELT.INVESTIGATION REVEALED THAT WHEN PULLED BACK, THE AILERON CROSSOVER TIE ROD P/N 941.93.43.415 ON THE CONTROL COLUMN, CAME INTO CONTACT WITH THE WIRING HARNESS ON THE BACK OF THE MULTI FUNCSDR 2001F00266A/C Pack · inoperativeECS SYSTEM WOULD NOT COOL BELOW AMBIENT TEMPERATURE NO MATTER WHAT POSITION THE CONTROL WAS IN, AUTO OR MANUAL. AFTER TROUBLESHOOTING SYSTEM AND TALKING TO TECH REPS, CHANGED COOLING TURBINE AND HEAT EXCHANGER. OPERATIONAL AND FUNCTIONAL CHECKED OK.SDR 2001F00373A/C Pack · inoperativeECS SYSTEM BLOWS WARM AIR IN EITHER MANUAL OR AUTO MODES. REMOVED AND REPLACED REFRIGERATION PACK AND OPS CHECK OK.SDR CA010906006Fuel Control · intermittent(CAN) A/C IN QUESTION IN RED LAKE & ON ITS BACKTRACK.EVERYTHING INDICATING NORMAL.FLT IDLE ASKED FOR & WHEN LEVER SET FOR FLT IDLE IT NOTICED GEN 1 LIGHT CAME ON. ENGINE IN PROCESS OF FLAME OUT & CONTINUED UNTIL STOPPED. MAINT CONTACTED & INSP ENGINE FROM FRONSDR CA010831018Cover · loose(CAN) COVER SCREWS WERE FOUND WITH INSUFICIENT TORQUE AS PER FOCA AD HB 2001-500. COVER SCREWS WERE TORQUED TO SPECIFICATIONS AND SAFTIED AS PERSB28-009NO SIGNS OF FUEL LEAKAGE OR EXTRUDED GASKET MATERIAL WAS FOUND.SDR CA010831016Tube · leaking(CAN) PART TIME NOT KNOWN. METAL CLAMP ON LINE CHAFED THROUGH OIL LINE.TUBE WAS FOR TORQUE TRANSDUCER. FIG 01, 77-10-00 ITEM 10 MOST OF THESE LINES HAVE CLAMPS WITHOUT RUBBER INSERTS. THEY ARE METAL ON METAL.SDR CA010831019Pump · leaking(CAN) INSPECTION OF THE ENGINE DRIVEN FUEL PUMP AS PER PILATUS AWD HB2001-500 AND SB 28-009 REVEALED THAT FUEL PUMP WAS LEAKING AND EXTRUDED GASKET MATERIAL WAS FOUND. THE TORQUE OF THE SCREWS WAS CHECKED. 1/8TH TO 1/4 TURNS WERE NEEDED TO TORQUE THE SCREWS TSDR CA010831014Windshield · failed(CAN) ON TAKE-OFF AT FT ST. JOHN, CO-PILOTS WINDSHIELD SHATTERED JUST AT ROTATION, PILOT ABORTED TAKEOFF AND TAXIED BACK TO RAMP. WINDSHIELD WAS REPLACED 132 HRS PRIOR.SDR CA010830009Control Valve · seized(CAN) AFTER STARTUP THE PILOT SELECTED COOL SETTING ON THE ENVIRONMENTAL CONTROL SYSTEM (ECS). THE SYSTEM BLEW COOL AIR FOR APPROX 25 SECONDS, THEN BLEW HOT AIR. AFTER APPROX 1 MINUTE THE SYSTEM SHUTDOWN AND AN AMBER LIGHT INDICATING ECS FAILURE APPEARED ON THSDR CA010821003Timer · malfunctioned(CAN) ON THE SCHEDULED AIRFOIL DEICER SYSTEM INSPECTION, IT WAS DISCOVERED THAT THE NORMAL INFLATION SEQUENCE WOULD WORK PROPERLY ONLY 1 TIME OUT OF THREE. IT WAS DETERMINED THAT THE TIMER WAS FUNCTIONING IN AN INTERMITTENT MANNER. DEICER CAUTION LIGHT WOULD CSDR CA010813018Brush Holder · worn(CAN) DURING A 100 HOUR INSPECTION, THE BRUSH ASSEMBLY WAS REMOVED TO VERIFY THE CONDITION. THE BRUSH ASSEMBLY WAS WORN EXCESSIVELY, AND HAS BEEN REPLACED.SDR CA010813017Indicator · failed(CAN) DURING STRAIGHT AND LEVEL FLIGHT THE CO-PILOTS AHRU DISPLAY WENT BLANK. THE PILOT CYCLED THE AVIONICS POWER, AND THE UNIT CAME BACK ON. THE UNIT HAS BEEN REPLACED.SDR CA010725010Pump · unserviceable(CAN) BOOST PUMP FAILED CAUSING FUEL IMBALANCE. AIRCRAFT LANDED AND PUMP REPLACED.SDR CA010725008Selector Valve · leaking(CAN) PILOTS REPORTED A INTERMITTENT PROBLEM WITH THE HYDRAULIC LIGHT COMING ON WHEN LANDING. THIS INDICATES THE HYDRAULIC PUMP CYCLED 6 TIMES IN 1 HOUR. AFTER SERVICING THE SYSTEM THE PROBLEM WOULD STILL OCCUR. IT WAS DECIDED TO CHANGE THE HYDRAULIC SERVICE SSDR CA010813016Indicator · failed(CAN) DURING STRAIGHT AND LEVEL FLIGHT THE PILOTS AHRU DISPLAY WENT BLANK. THE PILOT CYCLED THE CIRCUIT BREAKERS, AND THE UNIT CAME BACK ON. THE UNIT HAS BEEN REPLACED.
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