U/A Canada PT6A-34
Service difficulty reports · 465
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 engine_model_key = 'PT6A34' 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 engine_model_key = 'PT6A34' 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 CA130610015Line · leaking(CAN) THE PILOTS NOTICED A FUEL ODOR IN THE CABIN THAN NOTIFIED MAINTENANCE. THE CABIN ODOR WAS THE RESULT OF A LEAKING FUEL LINE LOCATED IN THE FUEL GALLEY AREA. THE PROBLEM WAS LOCATED IN FUEL BAY 5 FWD PUMP, WHICH WAS A RESULT FROM ARCING AT BOTH THE FUELSDR CA130613009Rod · damaged(CAN) IT HAS BEEN FOUND THAT THE C6CW1083-1 FLAP ROD WAS FOUND SCUFFED AND FOULING ON ROOT RIB C6W1035-15/16. MFG IS CONTINUING TO INVESTIGATE.SDR CA130531007Pump · failed(CAN) PLASTIC DRIVE COUPLING FAILED. VACUUM PUMP SCHEDULED FOR REPLACEMENT.SDR ERHA20130604001Yaw Damper · activatedAUTOPILOT WAS RECENTLY INSTALLED THAT HAD A YAW DAMPENER AS AN OPTION. UPON THE TAKEOFF ROLL, THE PILOT CLAIMS THAT THE YAW DAMPENER CAME ONLINE, UNCOMMANDED, CAUSING A LOSS OF DIRECTIONAL CONTROL.SDR CA130527004Oil System · low pressure(CAN) ON CLIMB AT 1200 FT, THE OIL PRESSURE DROPPED FROM 90 TO 40 PSIG. THEN IT DROPPED BELOW 40 PSIG AND TORQUE FLUCTUATED. ENGINE WAS SHUTDOWN AND A SINGLE-ENGINE LANDING WAS MADE AT POINT OF ORIGIN.SDR CA130513021Door · damaged(CAN) DURING A SCHEDULED INSPECTION, SMOKING RIVETS WERE FOUND IN THE LAP JOINT OF THE INTAKE DIVERSION DOOR AND DEFLECTOR. THE INTAKE PLENUM WAS REMOVED, ALL ATTACHMENT RIVETS REPLACED AND DIVERSION DOOR AND INTAKE PLENUM RE-INSTALLED.SDR CA130513022Bulkhead · cracked(CAN) DURING A SCHEDULED INSPECTION, THE VERTICAL BULKHEAD FLANGES IN THE RT AND LT FLOATS, COMPARTMENT 13 WERE FOUND BUCKLED/CRACKED. THE DAMAGE WAS LIMITED TO THE CENTER FLANGE, WITH THE BULKHEAD SKIN DISTORTED IN A 1.5" DIAMETER. BOTH FLANGES WERE REPAIRESDR CA130510001Arm · cracked(CAN) DURING A SCHEDULED INSPECTION, THE CENTER FORWARD FLAP BRACKET ON THE RT FLAP ASSY WAS FOUND CRACKED IN THE ARM RADIUS ON THE INBD SIDE. THE FLAP ROLLER ARM ASSY PN 100-330-5003-02 WAS REPLACED WITH A NEW FLAP ROLLER ARM ASSY SUPPLIED BY QUEST ACFT COMPSDR CA130510002Filter · shorted(CAN) DURING A TRAINING FLIGHT, THE NR 1 FORWARD BOOST PUMP FAILED, AND THE PILOT NOTIFIED MAINTENANCE, ABOUT THIS FAULT. IT WAS FOUND THE NR 1 FWD BOOST PUMP NOISE FILTER PN A.3210 HAD SHORTED OUT AND NR 2 PUMP NOISE FILTER CONNECTION WAS ABOUT TO FAIL. THSDR CA130430020Roller · worn(CAN) IT WAS DETERMINED THIS WEAR WAS THE RESULT OF THE FLAP ROLLERS P/N C6CWM1072-29, ALLOWING TOO MUCH FORE AND AFT MOVEMENT WHEN FLAPS WERE FULLY EXTENDED. NEW FLAP RODS P/N C6CW1083-1 INSTALLED AND ROLLERS ADJUSTED ACCORDINGLY. THERE WAS AN MRO FINDING RESDR CA130429013Bolt · corroded(CAN) 3 REPLACEMENT WING STRUT ATTACHED BOLTS RECEIVED FROM MFG WITH SIGNIFICANT SURFACE PITTING. PN C3W114-3, 1 AND C3W129-3, 2.SDR 2013FA0000251Duct · crackedDISCOVERED EXHAUST CASE FLANGE CRACKED (APPROX 2" LONG) AT THE RADIUS OF THE FLANGE TO THE EXHAUST CASE PROPER. THIS CRACK WAS NOTED DURING MX FOLLOWING AN EXHAUST STACK/DUCT PIPE FRACTURE.SDR CA130418007Bracket · buckled(CAN) DURING INSPECTION OF TAIL SECTION, ELEVATOR QUADRANT SUPPORT BRACKET WAS FOUND TO BE BUCKLED IN 2 PLACES. PART WAS REMOVED FOR REPLACEMENT AND APPEARED TO BE NOT IN A HEAT TREATED CONDITION.SDR CA130422013Shaft · failed(CAN) DURING THE CHECK FLIGHT TURNING FINALS FOR LANDING, SET 10 FLAPS THEN PILOT FLYING CALLED FOR 20 FLAPS. WHEN 20 WAS SELECTED AND RUNNING HEARD A BANG/SNAP SOUND FROM THE OVERHEAD CABIN ROOF. CONTINUED THE APPROACH AND LANDING WITHOUT FURTHER INCIDENT. SDR CA130412017Switch · failed(CAN) PILOT ENCOUNTERED LT AUTOFEATHER ACTIVATION WHEN REDUCING TO CLIMB POWER SETTING. PILOT RESUMED TO POWER LEVER SETTING AND PROP UNFEATHERED. PILOT SHUTOFF AUTOFEATHER SYS. UN COMMANDED AUTOFEATHER ACTIVATION WAS TROUBLESHOT TO UNSERVICEABLE LT AUTO-FESDR CA130325019Torque Link · cracked(CAN) DURING A SPECIAL NDT INSPECTION OF THE MLG TORQUE LINKS, A VERY SMALL CRACK WAS FOUND JUST STARTING TO FORM IN THE RADIUS OF THE UPPER LINK. THIS NDT IS A SELF IMPOSED ADDITIONAL INSPECTION, STARTED AFTER WE FOUND SIMILAR SMALL CRACKS IN THE SAME RADIUSSDR CA130822004Engine · power loss(CAN) AFTER CUSTOMER VISIT, IT WAS JUST REPORTED TO ENGINE MFG THAT THE ACFT SUSTAINED A POWER ROLLBACK IN CRUISE. AFTER COMPLETING EMERGENCY CHECKLIST, PILOT ATTEMPTED TO RESTORE POWER USING THE EMERGENCY POWER LEVER. THE POWER WAS RESTORED AND ACFT CONTINUSDR CA130201008Fairing · damaged(CAN) DAMAGE WAS CAUSED BY THE OIL TUBE BONDING LEAD ATTACHMENT BOLT WHICH WAS POSITIONED IN A MANNER THAT RESULTED IN CONTACT WITH THE FAIRING RESULTING IN A SMALL HOLE BEING CHAFED IN THE FAIRING. MFG ENGINEERING IS INVESTIGATING.SDR CA130110011Relay · misinstalled(CAN) AFTER WIRING THE AVIONICS MASTER RELAY, PN MS24192-D1, IAW WITH A LSTC, THE CIRCUIT WAS TESTED AND THE CIRCUIT BREAKER IMMEDIATELY POPPED. UPON INVESTIGATION, IT WAS FOUND THAT THE RELAY WAS WIRED INCORRECTLY DUE TO THE LABELING ON THE RELAY. THE X1 ANSDR CA121221005Landing Gear · slow(CAN) PILOT REPORTS ON NUMEROUS OCCASIONS THAT THE NLG WILL NOT FULLY RETRACT WITH THE LANDING GEAR PUMP ASSY. ON CLIMB OUT ONCE THE GEAR UP IS SELECTED, THE MAINS RETRACT NORMALLY, BUT THE SYS PUMP WILL CUT OUT BEFORE THE NOSE GEAR IS FULLY RETRACTED. STANDSDR CA121219014Spring · corroded(CAN) DURING ROUTINE INSPECTION, THE WATER RUDDER TENSION STEERING SPRINGS WERE FOUND BADLY CORRODED, WITH CABLE ATTACHMENT POINT EXCESSIVELY WORN. NEW SPRINGS ON ORDER, AND WILL BE REPLACED BEFORE ACFT LEAVES MAINTENANCE BASE.SDR CA121213010Valve · misinstalled(CAN) THERE IS A POSSIBILITY THAT THE STATIC SWITCH VALVE AND STATIC VALVE HANDLE HAVE BEEN INSTALLED INCORRECTLY ON SOME ACFT. IF INSTALLED INCORRECTLY, THE VALVE WOULD OPERATE AS FOLLOWS: THE VALVE HANDLE WOULD INDICATE NORMAL SOURCE WHEN THE VALVE IS IN THESDR CA121206009Spar · cracked(CAN) UPON 100 HR INSPECTION, SEVERAL CRACKS WERE FOUND ON THE WING SPAR FLANGE ANGLE AT THE WING STRUT PICKUP AREA. FURTHER DISASSEMBLY OF THE WING CRACKS WERE FOUND ON A SECOND FLANGE ON THE OTHER SIDE OF THE PICKUP LUG AREA.SDR CA121211005Engine · failed(CAN) THE PILOT REPORTED THAT HE EXPERIENCED AN ENGINE FAILURE AFTER TAKEOFF WITH THE INTENTION TO LAND AT DESTINATION AIRPORT.SDR CA121122009Module · malfunctioned(CAN) WEATHER RADAR SYSTEM DISPLAYS: WX FAIL MESSAGE ON PILOTS PFD. REPLACED AGM MODULE NR 1 IN MODULAR AVIONICS UNIT.SDR CA121114013Power Lever · fouled(CAN) PRODUCTION NOTED THAT DURING RIGGING OF THE LT POWER LEVER THE STOP BOLT WAS CONTACTING THE ADJACENT STRUCTURE WHEN THE BOUNCE GAP OF 0.80, 0.120. REQUIRED BY DWG C6EC1007 WAS ACHIEVED. MFG ENGINEERING IS INVESTIGATING FURTHER.SDR CA121011010Circuit Card · shorted(CAN) WHEN CARRYING OUT GROUND TESTS, THE LT PROP WOULD NOT COME OUT OF FEATHER AND WHEN THE NR 2 FWD LOW FUEL PRESSURE INDICATOR LIGHT CAME ON THERE WAS AN UNCOMMANDED FREQUENCY SWAP OF NR 2 COMM. THE PROBLEM FOUND TO BE A SHORT IN THE GENERATOR INPUT/OUTPUTSDR CA121012019Module · malfunctioned(CAN) WHILE THE ACFT WAS IN A CRUISE CONFIGURATION, THE FLIGHT CREW EXPERIENCED A MOMENTARY LOSS OF THE PILOTS AND CO-PILOTS PRIMARY FLIGHT DISPLAYS, PFD IN ADDITION TO THE LOSS OF THE LOWER MULTI-FUNCTION FLIGHT DISPLAY, MFD. AFTER A MOMENTARY LOSS OF APPROXSDR 2012FA0000628Stud · shearedNOSE GEAR ASSEMBLY REMOVED FOR A SCHEDULED INSPECTION. A STUD THAT IS PART OF THE STEERING COLUMN WAS FOUND SHEARED.SDR CA120829006Bleed Valve · ruptured(CAN) POOR ENGINE PERFORMANCE DUE TO FAILED BLEED AIR VALVE, RUPTURED DIAPHRAM: HIGH NG LOW FUEL FLOW SLIGHTLY HIGH ITT LOW TORQUE.SDR CA120827015Fitting · cracked(CAN) L/T AFT REAR BAR FITTING, PN 12716 FOUND CRACKED DURING 400 HR. SCHEDULED INSPECTION. CRACKS THROUGH A HORIZONTAL PLANE/MAIN ATTACH BOLT HOLE, PROBABLY AS A RESULT OF CORROSION STRESS.SDR CA120918011Blade · damaged(CAN) THE ENGINE HAD AN IFSD UNDER UNKNOWN CIRCUMSTANCES. POST FLIGHT INSPECTION FOUND A FRACTURED FUEL LINE AND COMPRESSOR TURBINE BLADE DAMAGE.SDR ERHA2012F00160G Switch · inoperativeELT G SWITCH WILL NOT ACIVATE DURING TESTING. REMOTE PILOT ACTIVATED SWITCH WORKS INTERMITTENTLY.SDR CA120618007Exhaust Duct · cracked(CAN) DURING A ROUTINE INSPECTION, A CRACK WAS NOTICED ON THE EXHAUST DUCT, BETWEEN THE B FLANGE & C FLANGE OF THE POWER SECTION. THIS IS A PRELIMINARY REPORT, MORE TO COME ONCE THE POWER SECTION IS RECEIVED. TIMES & CYCLES SINCE NEW ARE APPROX.SDR CA120410007O-Ring · leaking(CAN) FOUND FUEL LEAKING FROM THE ENGINE FUEL PUMP DISCHARGE FILTER COVER, IT WAS A RESULT OF THE PACKING, PN: M25988-1-928, "BLOWN " OUT OF ITS SEALING AREA. THE FUEL PUMP, DISCHARGE FILTER COVER WAS INSTALLED AND TORQUED IAW MM, PN 3021242, DATED APRIL 03,SDR CA120208004Bumper · disintegrated(CAN) DISASSEMBLED ACTUATOR TO REPLACE O-RINGS AND FOUND BUMPER TO BE TOTALLY DISINTEGRATED. BUMPER LOOSENED ITSELF OFF AND PISTON KEPT POUNDING ON BUMPER AS THE SKIS WENT UP AND DOWN. THIS CAUSE THE CONTAMINATION IN THE HYDRAULIC SYS.SDR CA120115001Engine · power loss(CAN) WHILE ENROUTE, THE ENGINE LOST POWER AND THE PILOT OF THE FLOATPLANE MADE A FORCED LANDING ON WATER. THERE WERE NO INJURIES AND THE AC WAS NOT DAMAGED. IT WAS TOWED TO SHORE WHERE THE ENGINE WILL BE REPLACED. THE OPERATOR HAS YET TO DECIDE WHERE THE ENSDR CA120125015Blade · failed(CAN) ENROUTE AT 2500` THERE WAS A LARGE BANG FOLLOWED BY AN ENGINE FAILURE AND PROP FEATHERING. ENGINE HAD A TSN OF 4318.8 AND A CSN OF 9768 CYCLES AT THE TIME OF FAILURE. A TEARDOWN INSPECTION IS CURRENTLY ON-GOING TO DETERMINE THE CAUSE OF THE FAILURE.SDR CA111103012Actuator · contaminated(CAN) FLOAT PLANE OPERATOR, TAILPLANE ACTUATOR ASSY GETS WET, WATER HAS TO BE DRAINED AND BEARINGS REPLACED OCCASIONALLY (ANNUAL).SDR CA111003011Block · loose(CAN) DURING A REPETITIVE STAB TRIM JACK INSPECTION, NOTED THAT THE BOTTOM JACKSCREW MOUNT WAS LOOSE AND WORKING IN ITS FUSELAGE MOUNTING BRACKET. MOUNTING POINT AND BRACKET WAS REMOVED AND DISASSEMBLED AND THE 3 MOUNTING RIVETS AND THE ASSOCIATED HOLES WERSDR CA111007002Ring Gear · failed(CAN) IN CRUISE FLIGHT, CHIP DETECTOR LIGHT ILLUMINATED. 2-3 MINUTES LATER OIL PRESSURE BEGAN TO DROP AND BECAME ERATTIC. ENGINE WAS SHUTDOWN AND ACFT LANDED. A PRELIMINARY INSPECTION REVEALED THAT THE POWER SECTION SUN GEAR HAD FAILED. THE GEAR WAS NOT PASDR CA110909003Manifold · cracked(CAN) THE OPERATOR REPORTED THAT AN INFLIGHT SHUTDOWN OCCURRED ON ONE OF THEIR ACFT. CIRCUMSTANCES ARE UNKNOWN, POST FLIGHT INSPECTION REVEALED A CRACK AROUND A FUEL MANIFOLD BOSS ON THE GAS GENERATOR CASE. THE ENGINE WILL BE REMOVED AND FORWARDED FOR INVESTSDR CA110821001Transmitter · failed(CAN) DURING ROUTINE FLIGHT, THE PILOT NOTICED A DROP IN FUEL PRESSURE/FLOW AND IMMEDIATELY, THE ENGINE LOST POWER AND FLAMED OUT. PILOT TRIED TO RE-START THE ENGINE AND USE THE EMERGENCY POWER LEVER WITHOUT SUCCESS. AFTER A SAFE EMERGENCY LANDING ON A LAKESDR CA110802008Structure · damagedPILOT REPORTED A RUMBLING NOISE DURING CLIMB WITH FLAPS DEPLOYED TO THE CLIMB POSITION. UPON LANDING, THE TRAILING FLAP WAS FOUND DAMAGED ON INBD SECTION. TRAILING FLAP WAS REPAIRED AND REINSTALLED AND TEST FLIGHT WAS COMMENCED. THE SOUND WAS STILL EVIDENT ASDR CA110720005Engine · power loss(CAN) ACCIDENT AFTER T/O FOR AERIAL APPLICATION, THE ENGINE LOST POWER AND A FORCED LANDING WAS MADE IN A FIELD DURING WHICH THE A/C FLIPPED OVER. THE PILOT WAS NOT INJURED BUT THE A/C WAS SUBSTANTIALLY DAMAGED.SDR CA110711015Circuit Breaker · inoperativeCIRCUIT BREAKER WON`T RESET.SDR CA110516031Control Rod · damagedDURING A ANNUAL INSPECTION, IT WAS FOUND THAT THIS FLAP CONTROL ROD, HAD SUFFERED DAMAGE RESULTING FROM LONG SCREWS PN: AN 509-10-15. AFTER INVESTIGATING, IT WAS DETERMINED THAT THE 2 SCREWS WERE CORRECT IAW THE IPC, DUE TO ITS SHANK LENGTH, BUT WERE REQUIREDSDR CA110516014Bleed Valve · failedPOWER LOSS DURING CLIMB, PILOT HEARD A LOUD NOISE FOLLOWED BY A SIGNIFICANT POWER LOSS. POWER LEVER WAS PUSHED TO MAX POSITION BUT THE ENGINE DID NOT RESPOND. THE MANUAL OVERRIDE WAS USED AND A SIGNIFICANT AMOUNT OF POWER WAS RECOVERED, WHICH ENABLED A RETURN SDR CA110509010Engine · failed(CAN) PILOT WAS ABOUT TO TURN FINAL WESTBOUND AT 1500` WHEN A LOUD BANG OCCURRED AND LOTS OF ENGINE VIBRATION, WITH A CONTINUOUS LOUD HUMMING NOISE. PILOT WENT TO GLIDE SPEED OF 85 MPH AND LOOKED AT ENGINE GAUGES AND THE ENGINE SEEMED TO HAVE ROLLED BACK TO MSDR CA110428010Rod · loose(CAN) RUDDER CONTROL ROD WAS REMOVED TO REPLACE FORWARD ROD END AND UPON CLOSER INSPECTION LOOSE RIVETS WERE FOUND ATTACHING FORWARD ATTACH FITTING. REPLACED LOOSE RIVETS.
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