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 Z4MR601462AGasket · leakingA RANDOM INSPECTION OF THE FUEL PUMP REVEALED FUEL LEAKING FROM THE ENGINE DRIVEN LOW PRESSURE FUEL PUMP RELIEF VALVE GASKET. THIS PUMP INCORPORATES THE SAME (OR VERY SIMILAR) RELIEF VALVE AND GASKET ASSEMBLY USED ON ROTARY FUEL PUMP WHICH WAS THE SUBJECT OF SDR CA010725014Seat Back · cracked(CAN) THE SEAT WAS REMOVED TO REPAIR BROKEN UP/DOWN ADJUSTMENT AND THE SEAT BACK WAS FOUND CRACKED. THE CRACKS WERE FOUND TO BE ONLY IN THE PLASTIC PART OF THE ALUMINUM STRAPS WERE NOT CRACKED, THE PART WAS REPLACED WITH A NEW UNIT.SDR CA010725013Drive Gear · failed(CAN) PILOTS REPORTED FLAP SYSTEM 1 AMP CIRCUIT BREAKER ON BATTERY BUS TRIPPED WHEN FLAP SELECTED DOWN. THE SYSTEM WOULD FUNCTION NORMAL IF THEY KEPT THE AIR SPEED BELOW 140 KNOTS. THE FAILURE COULD NOT BE DUPLICATED ON THE GROUND. THE FLAP POWER DRIVE UNIT WASDR CA010703015Buckle · broken(CAN) CO-PILOTS SEAT BELT BUCKLE WOULD NOT UNLATCH WHEN OPERATED.SDR CA010703011Actuator · noisy(CAN) PITCH TRIM ACTUATOR FAILED ROUTINE FUNCTION CHECK. PRIMARY MOTOR SOUNDS ROUGH WHEN ACTUATED.SDR CA010625029Hinge · cracked(CAN) DURING AN INSPECTION OF THE FLAP ASSY FOR THE OIL COOLER DOR A 1" CRACK WASFOUND DBETWEEN THE MOUNTING HOLES AND THE HINGE. NEW PART WAS INSTALLED.SDR FE62002F00001Actuator · restrictedTHE AILERON TRIM TAB LINEAR ACTUATOR ELECTRICAL HARNESS WAS TIED WITHOUT ENOUGH SERVICE LOOP WHICH CAUSED RESTRICTED AILERON MOVEMENT. THE LINEAR ACTUATOR ELECTRICAL WIRE HARNESS WAS THUS PULLED FROM THE ACTUATOR. THE ACTUATOR WAS STILL FUNCTIONAL BUT WAS RSDR CA010629035Actuator · failed(CAN) IN CRUISE THE CREW NOTICED THAT THE STAB TRIM WAS INOPERATIVE IN NOSE DOWN MODE. FURTHER TROUBLE SHOOTING AFTER LANDING CONFIRMED THE ACTUATOR FAILED INTERNALLY. LOUD GRATING NOISE WHEN TRIMED IN THE NOSE DOWN DIRECTION. ACTUATOR REPLACED AND AIRCRAFT RESDR QML2001F00000Actuator · failedFLAP SYSTEM MALFUNCTION. FLAPS FROZE AT APPROXIMATELY 15 DEGREES, WHILE BEING RETRACTED IMMEDIATELY FOLLOWING TAKEOFF. DEFECTIVE FLAP ACTUATOR. FAULTY FLAP ACTUATOR REMOVED AND REPLACED.SDR CA010629026Brushes · 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 CA010625030Control Valve · failed(CAN) WHEN IN CRUISE THE TEMPERATURE IN THE A/C STARTED TO GET VERY WARM THE ECS SWITCH WAS TURNED TO MANUAL AND TURNED DOWN. IT GOT VERY HOT SO ECS SWITCH WAS TURNED OFF AND BACK ON. THE HEAT THAN WENT TO THE COLD POSITION AND COULD NOT BE ADJUSTED. TRIP CONTSDR CA010629025Fuel Control · failed(CAN) WHEN TRYING TO START ENGINE, THE ENGINE WOULD NOT ACCELERATE ABOVE APPROXIMATELY 35-39 PERCENT THE FUEL CONTROL UNIT WAS REPLACED, AND THE AIRCRAFT WAS RETURNED TO SERVICESDR CA010629029Brushes · worn(CAN) #2 GENERATOR FAIL LIGHT CAME ON DURING FLIGHT. AN INSPECTION OF THE BRUSHES SHOWED ONE TO HAVE SUFFERED SIGNS OF ARCING.SDR CA010629027Arm · broken(CAN) ON CLOSING THE CARGO DOOR THE UNLOCKED WARNING LIGHT IN THE COCKPIT FAILED TO EXTINGUISH. ON INVESTIGATION THE ROLLER SPRING ON THE MICRO SWITCH WAS BROKEN.SDR CA010629024Brushes · worn(CAN) THE NR 2 GEN CAUTION LIGHT ILLUMINATED ON CAWS PANEL. PILOT ALSO NOTED THAT A VERY LOUD SQUEALING SOUND COULD BE HEARD IN HEADSET. CAUTION LIGHT THEN ILLUMINATED & PILOT THEN SELECTED NR 2 GEN SWITCH TO OFF POS. GEN WAS THEN RE-SELECTED TO ON POS, WITH SSDR CA010626004Brushes · shorted(CAN) DURING OVERHAUL OF REF. STARTER-GEN, DAMAGE TO ACCESS COVER & ONE BRUSH'S SHUNT WIRES FOUND. THIS DAMAGE CONSISTED OF BURNING MARKS ON COVER & BURNT &MELTED STRANDS OF BRAIDED SHUNT WIRES ON BRUSH. APPROX. 1/4 OF TOTAL BRUSH SHYNT WIRES WERE BURNT THROUGSDR CA010529013Skin · cracked(CAN) SMOKING WAS NOTICED AT THE ETOP R/H VERTICAL STAB SKIN. FURTHER INSPECTION REVEALED THAT THE REPAIR PATCH PREVIOUSLY INSTALLED IAW PILATUS TECH MEMO EC-12-TM-540 WAS CRACKED AT APPROXIMATELY THE SAME LOCATION AS THE ORIGINAL SKIN CRACKED. THE FIRST REPAISDR CA010629033Control Panel · malfunctioned(CAN) HDG CONTROL KNOB FEELS SCRATCHY, CAUSING INTERMITTENT RED FLAG ON HDG SYMBOL ON EFIS.PANEL REPLACED.SDR CA010629032Control Cable · defective(CAN) WHEN INSPECTING CONTROL CABLES AS PER 2000HR/5YR. INSPECTION REQUIREMENT, SOME ABNORMALITIES WERE NOTED ON THE 2 FORWARD AILERON CONTROL CABLES. ON ONE OF THE BUNDLES OF STRANDS IT APPEARED AS IF 2 OR 3 OF THE INDIVIDAL STRANDS WERE SEPARATED FROM EACHOTSDR CA010629030Connector · dirty(CAN) CRUISE ON HOMEWARD LEG OF FLT PILOT NOTICED ON OV ERHEAD ELECTICAL PANEL THAT BATTERY NR 2 DISPLAY WAS INDICATING A DECREASING VOLTAGE WITH AN INCREASING NEGATIVE AMPS. GEN. NR 2 IND WAS INDICATING A VIRTUAL ZERO AMPS WITH A 29.3 VOLTS. WITH NO OTHER WARSDR CA010629023Brushes · worn(CAN) THE NR 2 GENERATOR CAUTION LIGHT ILLUMINATED ON THE CAWS PANEL. THE PILOT NOTED THAT THE NR 2 GENERATOR OUTPUT WAS FLUCTUATING BETWEEN A 60AMP DISCHARGE AND A 20 AMP POSITIVE CHARGE. HE TURNED THE GENERATOR OFF, THEN RE-SELECTED IT TO THE ON POSITION.THESDR CA010530003Relay · damaged(CAN) FLAP WERE SET TO 30 DEGREES FOR APPROACH. UPON LANDING AND ROLL OUT TO THE TAXIWAY, THE FLAPS WERE SELECTED TO ZERO DEGREES. THE PILOT NOTED THAT THE "FLAP" CAUTION LIGHT ON THE CAWS PANEL ILLUMINATED. FURTHER SELECTIONS OF THE FLAPS WERE UNSUCCESSFUL. ISDR CA010530002Controller · failed(CAN) FLAPS WOULD NOT EXTEND. FOUND FLAP CONTROL CIRCUIT BREAKER POPPED. AIRCRAFT LANDED WITH ZERO FLAPS. FLAP CIRCUIT BREAKER RESET ON GROUND. FLAP CONTROL WARNING UNIT (FCWU) RESET. FLAP OPERATIONAL TEST, SATISFACTORY. FCWU MAINTENANCE CODES READ FOR TROUBLESDR CA010529002Combustion Liner · failed(CAN) SPARKS OBSERVED COMING FROM ENGINE EXHAUST STACKS DURING APPROACH. ENGINE BORESCOPE INSPECTION CARRIED OUT WITH ASSISTANCE OF PRATT & WHITNEY FIELD REP. EVIDENCE OF CERAMIC COATING IMPACT ON TURBINE BLADES. SUSPECT SPARKS WERE CAUSED BY CERAMIC COATING BSDR CA010530008Bracket · worn(CAN) GENERATOR 2 WAS REMOVED TO PERFORM A GENERATOR 2 DRIVE INSPECTION, AS THE UNIT WAS ON THE BENCH, IT WAS QUITE CONVENIENT TO INSPECT THE BRUSHES. THE BRUSHES WERE FOUND WITH EXCESSIVE WEAR GIVEN THE AMOUNT OF TIME SINCE INSTALLATION (71.0 HOURS). . .SDR CA010530006Indicator · malfunctioned(CAN) CREW REPORTED THAT THE ENGINE OIL PRESSURE INDICATION FLICKERED AND DROPPED TO ZERO, THEN CAME BACK TO NORMAL. A SECOND FLICKER OF THE SAME NATURE REOCCURRED. THE INDICATION REMAINED NORMAL THEREAFTER. MAINTENACNE REMOVED THE EIS (ENGINE INSTRUMENTATION SDR CA010507022Brush Holder · worn(CAN) DURING A 100 HOUR INSPECTION, THE BRUSH ASSEMBLY WASREMOVED TO VERIFY THE CONDITION. THE BRUSH ASSEMBLY WAS WORN EXCESSIVELY, AND HAS BEEN REPLACED.SDR CA010508002Accumulator · leaking(CAN) PILOT REPORTED LANDING GEAR FAILED TO LOCK UP IN RETRACTED POSITION. GEAR WAS SELECTED DOWN AND EMERGENCY HAND PUMP WAS USED TO LOCK GEAR IN PLACE. THE AIRCRAFT WAS THEN FLOWN TO MAINTENANCE BASE WITH GEAR DOWN. THIS SYSTEM HAS THE HYDRAULIC PUMP PRESSURSDR CA010508005Brushes · worn(CAN) 1) NR 2 GENERATOR, S/N 100222, INSTALLED, 00-07-02 AT 3200.6 A/F HRS. 2) NR 2 GENERATOR, S/N 100222, FAILED, 00-12-20 AT 3468.1 A/F HRS. TTSO: 267.5 HRS., FAILURE DUE TO WORN BRUSHES. 3) NR 2 GENERATOR, S/N 100262, INSTALLED 00-12-20 AT 3468.1 A/F HRS. PSDR CA010508003Switch · bent(CAN) AFTER START UP PILOT NOTICED THE CARGO DOOR LIGHT WAS ON. HE SHUT DOWN AND CONFIRMED THE DOOR WAS CLOSED, THEN ADVISED MAINTENANCE OF THE PROBLEM. THE DOOR HANDLE SWITCH LEVER ROLLER SPRING WAS FOUND BENT. THE SPRING WAS STRAIGHTENED AND ADJUSTED. AFTER SDR CA010507021A/C Pack · leaking(CAN) DURING CRUISE FLIGHT A BURNED OIL SMELL WAS NOTICED IN THE COCKPIT AND CABIN. AFTER RETURNING TO BASE THE SAME SMELL COULD BE DUPLICATED ON THE GROUND. THE SMELL WOULD DISSIPATE WHEN THE E.C.S. WAS TURNED OFF. INVESTIGATION REVEALED A VERY BLACK AND DIRTSDR CA010629031Brushes · worn(CAN) DUE TO PREMATURE WEAR OF NR 2 GEN BRUSHED PILATUS ISSD A S/B (S/B 24-016) TO ADDR ISSUE BY INTRODUCING A NEW LONGER WEARING BRUSH BLOCK ASSY WHICH IS FIELD REPLABLE. PRIOR TO THE S/B WE FOUND BRUSHES ON ORIGLY INST GEN S/N 100092 WITH .686.2 TAT HRS WAS SDR CA010508004Brushes · worn(CAN) DUE TO PREMATURE WEAR OF NR 2 GEN BRUSHES PILATUS ISSD A SB (SB 24-016) TO ADDR ISSUE BY INTRODUCING A NEW, LONGER WEARING BRUSH BLOCK ASSY WHICH IS FIELD REPLABLE.PRIOR TO THE SB, WE FOUND BRUSHES ON ORIGLY INST GEN S/N 100092 WITH 686.2 TAT HRS WAS VERSDR 2001F00634Seal · cokedTHE ENGINE OIL USAGE HAD INCREASED SIGNIFICANTLY. UP TO 1 QUART IN ONE HOUR OF FLIGHT TIME. WE SPLIT THE ENGINE AND INSPECT THE NR 2 MAIN BEARING LABYRINTH SEAL AREA. THERE IS A KNOWN PROBLEM OF THIS AREA RUNNING HOTTER THAN NORMAL AND A COKING PROBLEM HAS OSDR CA010406015Pump · failed(CAN) PILOT REPORTED FUEL BALANCING SYSTEM WAS NOT OPERATIONAL. BOOST PUMP REPLACED AND AIRCRAFT RETURNED TO SERVICE.SDR CA010426003Strap · broken(CAN) NOSE GEAR BONDING STRAP P/N 532.20.12.262 WAS WRAPPED AROUND SHOCK STRUT P/N 571.10.12.353 AND HAD BENT THE STRUT SOME 70 DEGREES UP FROM ITS NORMAL POSITION. THE STRUT COULD NO LONGER OPEN AND CLOSE THE OIL COOLER DOOR UPON GEAR RETRACTION. BONDING STRASDR CA010426002Shaft · sheared(CAN) ON SELECTION OF FLAPS DOWN, FLAPS CAUTION ON C.A.W.S. PANEL CAME ON. FLAPS WERE RESET & TRIED AGAIN. FLAPS CAUTION CAME ON AGAIN. A/C LANDED W/O FLAP. MULTIPLE RESETS WERE THEN TRIED ON GROUND WHICH WOULD CAUSE F LAP CCT BREAKER ON BATTERY BUS TO POP. TSDR CA010409006Adc · failed(CAN) GPWS INOP WARNING LIGHT WOULD COME ON RANDOMLY IN FLIGHT. THE AIR DATA COMPUTER WAS REPLACED AND SOLVED THE PROBLEM.SDR CA010322011Bracket · loose(CAN) WHEN PASSENGER DOOR WAS INSPECTED, SEVERAL OF THE CHERRY MAX RIVETS THAT HOLD THE BRACKET WERE FOUND TO BE SHEARED. BRACKET WAS REMOVED INSPECTED FOR DAMAGE AND RE-ATTACHED USING NEW HARDWARE. THIS IS THE SECOND BRACKET THAT WE HAVE FOUND LOOSE.SDR CA010409004Brush Holder · worn(CAN) DURING CRUISE FLIGHT THE SECOND GENERATOR WENT OFF LINE, THE PILOT DID A RESET, THE GENERATOR CAME BACK ONLINE. APPROXIMATELY FIVE MINUTES LATER IT WENT OFF LINE AGAIN. THIS TIME THE PILOT DID NOT TRY TO RESET. ONCE THE AIRCRAFT WAS BACK ON THE GROUND THSDR CA010404014Outflow Valve · failed(CAN) AIRCRAFT WAS REPORTED TO HAVE JUST REACHED CRUISING ALTITUDE AT FL 290. THE CABIN ALTITUDE WARNING LIGHT ON THE CAWS PANEL ILLUMINATED. THE CREW VERIFIED THAT THE CABIN ALTITUDE HAD CLIMBED TO ABOVE 10,700 FEET AND INITIATED AN EMERGENCY DESCENT. THE AIRSDR CA010409005Servo · failed(CAN) AUTO PILOT WOULD FAIL TO CAPTURE THE HEADING BUG IN BOTH HEADING AND NAV MODE.SDR CA010323020Rotor · frozen(CAN) RT BRAKE FROZE ON LANDING. ICE REMOVED AND AIRCRAFT CONTINUED ON.SDR 20010404CW006Pump · failedPILOT NOTICED EXCESSIVE CONSUMPTION OF FUEL COMPARED TO FLIGHT TIME AND LANDED. FOUND FUEL DRAINING FROM ENGINE COWLING AREA. PILOT PRESSURIZED FUEL SYSTEM, FOUND FUEL LEAKING FROM LOW PRESSURE FUEL PUMP GASKET BETWEEN PUMP REGULATOR AND PUMP BODY. THE INTESDR CA010409009Strut · broken(CAN) THE SHOCK STRUT IS ACTUALLY AN ALUMINUM TUBE. THE SHOCK STRUT IS ATTACHEED TO THE FLAP STRUT WITH A STRAIGHT PIN. TWO SPRINGS KEEP THE FLAP DOOR CLOSED ALL THE TIME EXCEPT WHEN THE NLG IS DOWN. THE CONSTANT TENSION ON THE ALUMINUM SHOCK STRUT RESULTS IN SDR CA010409008Meter · faulty(CAN) PILOT REPORTED LOW VOLTAGE ON NR 2 BATTERY SYSTEM CHECKED AND IT WAS FOUND THE VOLT METER IN OVERHEAD ELECTRICAL PANEL WAS AT FAULT. WE COULD NOT REPLACE JUST THE METER SO A PANEL WAS ORDERED AND REPLACED. THE OLD PANEL WHEN REMOVED WAS FOUND TO HAVE SOMSDR CA010409007Transmitter · failed(CAN) WHILE PERFORMING A DAILY INSPECTION, THE VANE WAS FOUND CATCHING AT ONE SPOT, ROUGHNESS COULD BE HEARD INTERNALLY AND IT BECAME LOADED IN THE UP POSITION. ALHOUGH THE VANE WOULD STILL MOVE FREELY, A MANUFACTURER TECH. REP. ADVISED TO REPLACE THE TRANSMITSDR CA010313020Strut · jammed(CAN) WHEN DOOR WAS OPENED TO DEPLANE PASSENGERS, SHOCK STRUT JAMMED AND POPPED RIVETS ON BRACKET (P/N 552.10.12.176) WHEN BRACKET FAILED DOOR FREE FELL UNTIL CHECK CABLES ATTEMPTED TO STOP TRAVEL, BUT THE MOMENTUM SNAPPED THE CABLE ATTACH BRACKETS (P/N 552.10SDR CA010314026Regulator · contaminated(CAN) SAFETY VALVE FAILED TON OPEN WHEN CARRYING OUT 1500 HOUR PRESSURIZATION CHECK. FAILED SAFETY VALVE WAS REMOVED AND VALVE AND SENSE LINE WERE FOUND CONTAMINATED WITH JET FUEL. FUEL APPEARED TO HAVE COME FROM A PREVIOUSLY SEEPING FUEL FILTER BOWL SEAL AND SDR CA010314014Gyro · failed(CAN) WHEN TRYING TO SWITCH THE NUMBER ONE ATTITUDE HEADING REFERENCE UNIT (AHRU) FROM MAGNETIC TO FREE GYRO THE UNIT WOULD NOT SWITCH. THE NR 1 AHRU WAS REPLACED.
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