U/A Canada PT6A-50
Service difficulty reports · 225
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 = 'PT6A50' 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 = 'PT6A50' 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 CA050213007Engine · power loss(CAN) DURING CRUISE, THE ENGINE LOW OIL PRESSURE INDICATOR ANNUNCIATED ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED. SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE VANES AND BLADES AND A PUSDR CA050203004Planetary Gear · failed(CAN) SOURCE OF METAL CONTAMINATION WAS FAILURE OF 1ST STAGE GEARS. GEARS WERE SENT TO METALLURGICAL LABORATORY FOR FURTHER INVESTIGATION THAT REVEALED THE EXISTENCE OF AN OLDER FATIGUE CRACK SURFACE ON PARTS OF A FRACTURED TOOTH ON THE 1ST STAGE SUN GEAR, SUNSDR CA050527014Fuel Control · failedIN DESCENT, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT. THE ENGINE WAS SHUT DOWN IN FLIGHT. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.SDR CA050211003Engine · failed(CAN) DESTRUCTION OF COMPRESSOR OF ENGINE RESULT OF TIE ROD BOLT STRETCH. LACK OF TORQUE REMAINING ON HALF OF TIE RODS INDICATES THAT 3 LOOSE TIE RODS STRETCHED & CAUSED COMPRESSOR TO LOSE AXIS OF ROTATION & ALLOWED COMPRESSOR TO RUB HEAVILY & CAUSE MATERIAL TSDR CA050107006Engine · failed(CAN) APPOX 20 MINS INTO FLT, & AT FLT LEVEL 120 ENROUTE TO DIKO FROM DIBK WITH 19 PAX, MASTER CAUTION LIGHT ILLUMINATED ACCOMPANIED WITH NR 2 ENG LOW OIL PRESSURE LIGHT. NR 2 OIL PRESSURE GAUGE CONFIRMED ACTIVE WARNING LIGHT WITH PRESSURE INDICATION OF BELOSDR CA050110006Engine · inoperative(CAN) THE ENGINE EXPERIENCED AN OIL PRESSURE LOSS IN CRUISE. THE CREW SHUT THE ENGINE DOWN AND DIVERTED FLIGHT. SUBSEQUENT INSPECTION REVEALED METALLIC DEBRIS ON THE ENGINE CHIP DETECTOR AND IN THE ENGINE OIL FILTER. MFG WILL MONITOR THE INVESTIGATION OF THSDR CA041130003Bearing · failed(CAN) THE AIRCRAFT ON DEPARTURE RETRACT, THE GEAR WOULD NOT RETRACT. POSITION INDICATION LIGHTS REMAINED GREEN AND THE GEAR SELECTOR LEVER WAS ILLUMINATED AND REMAINED SO. NO CIRCUIT BREAKERS WERE TRIPPED ON THE FLIGHT DECK. THE AIRCRAFT LANDED WITHOUT INCIDENSDR CA041013008Pump · failed(CAN) WHILE THE AIRCRAFT WAS IN CRUISE AT 15,000 FEET, NR 4 HYDRAULIC PUMP CAUTION LIGHT ILLUMINATED, FOLLOWED 5 MINUTES LATER BY NR 3 HYDRAULIC PUMP CAUTION LIGHT COMING ON. ALL HYDRAULIC PRESSURE WAS LOST ON NR 2 HYDRAULIC SYSTEM AND ALTERNATE LANDING GEARSDR CA040903003Engine · failedENG REMOVED WHEN BETA CONTROL SYS JAMMED. SEIZED BETA CONTROL LINKAGE RESULT OF HEAVY CONTACT WEAR BETWEEN THE REAR SEALING LAND OF BETA TRANSFER SLEEVE AND PROP SHAFT. A PREVIOUS SIMILAR FAILURE INVESTIGATION HAD CONCLUDED THAT FAILURE RELATED TO LACK OF LUBSDR CA040819009Engine · lack of lubeENG REMOVED FROM WING WHEN OPERATOR FOUND BETA CONTROL SYSTEM JAMMED. ENG SHIPPED TO ENGINE AMO FOR INVESTIGATION & REPAIR. SEIZED BETA CONTROL LINKAGE RESULT OF HEAVY CONTACT WEAR BETWEEN REAR SEALING LAND OF BETA TRANSFER SLEEVE & PROP SHAFT. REASON FOR SESDR CA040713006Fcu · failed(CAN) AT CRUISE ALTITUDE AT FL110 ON A MEDEVAC FLIGHT DESCENT CHECKS WERE CARRIED OUT. AS TURBULENCE WAS EXPECTED A RATE OF 500 RPM AND SPEED OF 170 KIAS WAS BRIEFED AFTER DESCENT. CLEARANCE RECEIVED POWER LEVERS WERE PULLED BACK TO APPROX 3000 TORQUE. NR 3 ESDR CA040617007Fuel Control · failedSHORTLY AFTER TAKEOFF, ON CLIMBING THROUGH 6,000 FT, PILOT NOTICED OVER TORQUE LIGHT ON FOR ENGINE NR 4. A QUICK GLANCE AT OTHER ENGINE GAUGES TO CONFIRM ENGINE OVERSPEED, AND PULLED BACK THE POWER LEVER FOR NR 4 ENGINE TO SEE IF THERE WAS ANY RESPONSE. PILOSDR CA040614008Circuit Breaker · failed(CAN) IN ORDER TO INSTALL A LIGHT ASSEMBLY IN THE NOSE COMPARTMENT THE L4 (CB) WAS PULLED IN THE COCKPIT. AFTER INSTALLATION WAS COMPLETED, CB WAS PUSHED BACK IN TO TEST SYSTEM, BY THE TIME THE INDIVIDUAL WALKED FROM THE COCKPIT BACK TO THE NOSE COMPARTMENT THSDR CA040316007Coupler · burned(CAN) HF SYS FAILED, SMOKE AND BURN SMELL CAME FROM HF PWR AMP/COUPLER. UNIT WAS REMOVED AND SENT FOR INSP. FOUND THAT HARDWARE ATTACHING COVER ON CONNECTOR J9524 TO FACEPLATE OF UNIT HAD CONTACTED PRINTED CIRCUIT BD AND SHORTED +28 VDC SUPPLY TO GROUND. ELESDR CA040302002Blade · separated(CAN) ON 2ND FLIGHT OF THE DAY, A SUDDEN PARTIAL POWER LOSS OCCURRED ON NR 1 ENGINE, A STRONG SMELL ACCOMPANIED THE POWER LOSS. ENGINE NR 1 WAS SUBSEQUENTLY SHUT DOWN. THE AIRCRAFT COMPLETED AN UNEVENTFUL UNSCHEDULED LANDING. UPON SUBSEQUENT INSPECTION IT WASDR CA031223003Shaft · sheared(CAN) AFTER FLIGHT MAINTENANCE NOTICED AN OIL LEAK FROM THE NR 2 NACELLE, FURTHER INVESTIGATION FOUND THE NR 2 AC GENERATOR SHAFT SHEARED. THE FLIGHT CREW HAD NOT NOTICED ANY FAILURES SINCE IN THE NORMAL OPERATION MODE THIS AC GEN IS IN STANDBY AND ONLY WORKS SDR CA031210003Oil Runner · loose(CAN) DURING THE UNSCHEDULED REMOVAL OF NR 2 PROP DUE TO OIL LEAKING FROM THE PROP SHAFT, IT WAS NOTICED THAT THE PROP SHAFT OIL RUNNER (PART OF THE POWER SECTION) WOULD ROTATE WITHOUT THE PROP SHAFT MOVING. INFORMED US THAT THIS IS AN INDICATION THAT BEARING SDR CA031015015Brake Assy · leaking(CAN) BRAKE WAS SENT TO SHOP FOR WARRANTY REPAIR. SNAGGED AS LEAKING FROM PIN ON OCT 02, 2002. THE UNIT WAS REPAIRED AND RETURNED. BRAKE WAS INSTALLED ON 13 AUG 03, IT WORKED FOR 132.1 HOURS AND THEN STARTED TO LEAK FROM ONE OF THE PISTONS. THIS IS NOT THE FIRSDR CA031103005Engine · lightning strike(CAN) AC WAS HIT BY LIGHTNING STRIKE. REVIEWED ENG ON GROUND AND RESIDUAL MAGNETISM WAS FOUND ON PROP SHAFT. IT WAS CONFIRMED THAT ENG DID SUFFER FROM LIGHTNING STRIKE, PARTS FOUND WITH HIGH MAGNETISM ON THEM. PRESENCE OF ARCING ON FRONT RED GB MAIN BEARINGSSDR CA030923006Engine · failed(CAN) ENG SHUTDOWN IN FLT WHEN OIL PRESSURE DROPPED BELOW 75 PSI. REMOVED FOR INVEST. ENG FOUND TO HAVE 3 SOURCES OF OIL LOSS, PRINCIPAL ONE IS THOUGHT TO HAVE RESULTED IN RAPID OIL LOSS & MAIN PRESSURE PUMP OIL STARVATION, AN OIL GALLERY PORT ON RGB ACCESSORYSDR CA030908007Bearing · failed(CAN) TWO MIN AFTER TAKEOFF THE NR 3 DC STARTER-GEN FAILED, THE GENERATING SYSTEM WAS SHUTDOWN. MAINTENANCE FOUND THAT THE STARTER MODE FUNCTIONING OK. AFTER TROUBLESHOOTING THE STARTER-GENERATOR WAS REPLACED DUE TO HEAVY BRUSH WEAR AND THE BEARING WAS FAILINSDR CA030908008Shaft · sheared(CAN) SHORTLY AFTER TAKEOFF THE NR 3 DC GEN LIGHT CAME ON, THE SYSTEM WAS DEACTIVATED. AFTER ABOUT FIVE MINUTES THE NR 3 DC GEN HOT LIGHT CAME ON FOR ABOUT 20 SECONDS. FOR TROUBLESHOOTING WE ATTEMPTED TO START THE NR 3 ENG, WHICH KNOCKED THE GROUND POWER UNIT SDR CA030616004Solenoid · failed(CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN ALL THREE GEAR STAYED UP AND LOCKED. AN EMERGENCY GEAR EXTENSION WAS COMPLETED AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE JACKED THE AIRCRAFT AND ATTEMPTED TO COMPLETE GEAR SWINGS WHEN THESDR CA030609002Seal · swollen(CAN) WHILE REMOVING FUEL LIDS TO ACCESS FUEL TANKS FOR SNAG RECERTIFICATION FOLLOWING MAJOR INSPECTION, IT WAS NOTICED THAT THE NEW LIGHTNING SEAL P/N CVR 67 THAT WAS INSTALLED IN THE LAST WEEK OR TWO HAD SWOLLEN ALMOST 50 PERCENT LARGER THEN ITS NORMAL SIZE SDR CA030514008Wire · broken(CAN) DURING HEAVY MAINT INSPECT FOUND TWO WIRES CHAFED & BROKEN AT DETERIORATED CLAMPS IN LOWER AFT FIREWALL AREA. RUBBER CUSHION HAD TORN AWAY ALLOWING METAL CLAMP TO WEAR WIRES. THESE WIRES ARE FOR FIRE LOOP SYSTEM ON NR 3 ENGINE, WHICH WAS WORKING WHEN AIRSDR CA030320001Line · chafed(CAN) AFTER FINDING THIS LINE CHAFED ON AN OTHER AIRCRAFT WE COMPLETED A SPECIAL INSPECTION. WE FOUND THAT THE DE-ICE LINE HAD BEEN CHAFING ON A HYDRAULIC LINE. THIS LINE IS LOCATED UNDER PANEL 419AT (NR 1 ENG BATMAN PANEL). THE LINE IS HIDDEN UNDER NUMEROUS SDR CA030314005Line · chafed(CAN) DURING TROUBLESHOOTING A DE-ICE SNAG, ( NR 1 ENG DE-ICE BOOT WILL NOT INFLATE ) IT WAS FOUND THAT THE DE-ICE LINE P/N 73010033-147 HAD BEEN CHAFFING ON A HYDRAULIC LINE. THIS LINE IS LOCATED UNDER PANEL 419AT (NR 1 ENG BATMAN PANEL). THE LINE IS HIDDEN USDR CA021010010Engine · failed(CAN) ENGINE WAS SENT TO ATI FOR INVESTIGATION AFTER THE OPERATOR COMPLAINED OF COMPRESSOR WHINING AND COMPRESSOR STALLS AT HIGH POWER SETTINGS. A T-5 INDICATION PROBLEM AT START-UP AND THE FUEL PUMP IS LEAKING FROM THE DRAIN.ATI WILL RESTORE THE ENGINE TO SERSDR CA020104020Spar Cap · chafed(CAN) DURING "C" CHECK AND CORROSION INSPECTION THE LT REAR SPAR CAP AND SPAR AREA ABOVE THE SPAR CAP WAS FOUND CHAFED. THE CHAFING WAS CAUSED BY SPIRAL WRAP WOUND AROUND A WIRE BUNDLE THAT RUNS ACROSS THE FACE OF THE REAR SPAR.SDR CA011217015Boot · dislodged(CAN) THE AIRCRAFT WAS FERRYING BACK TO BASE. IN CRUISE THE FLT MECHANIC WHILE STANDING AT THE BACK BETWEEN THE GALLEY AND THE WASHROOM FELT A LOW FREQ VIBRATION ON THE FLOOR. THE VIBRATION WAS NOTICEABLE TO THE FLIGHT ATTENDANT ALSO. THE INFORMATION WAS RELAYSDR CA011121012Panel · separated(CAN) ON DESCENT, A LOUD BANG WAS HEARD, FOLLOWED SHORTLY THEREAFTER BY ANOTHER SMALLER ONE. THE FLIGHT CARRIED ON TO A NORMAL APPROACH AND LANDING WITHOUT FURTHER INCIDENT. UPON INSPECTION AFTER LANDING, THE CAPTAIN NOTED THE ARMPIT PANEL WAS MISSING FROM UNSDR 2001F00200Line · crackedFLT 1253 - HAV - AFTER TAKEOFF, AT 4,800 FEET, NR 4 ENGINE EXPERIENCED A POWER LOSS. PERFORMED ENGINE FAILURE IN FLIGHT CHECK LIST. REMOVED AND REPLACED NR 4 ENGINE P3 LINE. RAN ENGINE. OPERATIONAL CHECK NORMAL. (M)SDR CA010713003Nut · sheared(CAN) DURING SCHEDULED MAINTENANCE, FOUND THAT THE NR 4 STARTER/GENERATOR COULD ROTATE 1/4 TURN ON IT'S MOUNT. THE SELF LOCKING NUT ON THE CLAMP HAD NO FRICTION AND BACKED OFF. THE CLAMP WAS LOOSE. THE STARTER HAD SHEARED THE ALIGNMENT PIN. WE REPLACED THE NUTSDR CA011025002Hose · mismarked(CAN) A HYDRAULIC HOSE, P/N DSC152D8-0254-260 WAS ORDERED FROM THE COMPANIES STORES DEPARTMENT. THE INFORMATION ON THE PACKAGING INDICATED 3000 PSI WORKING PRESSURE.THE INFORMATION BAND CRIMPED AROUND THE HOSE INDICATED 1000 PSI WORKING PRESSURE. THE HOSE, ASDR CA010529015Plate · cracked(CAN) DURING LPI OF BARREL PLATE IT FOUND TO HAVE A CRACK THAT GOES ACROSS PACKING GROOVE FOR PACKING THAT SEALS BARREL PLATE TO BARREL. THIS PACKING SEALS BARREL LUBRICATING OIL INTO BARREL.THE BARREL PLATE IS ITEM #682.IPL FIGURE #1A, CMM 61-13-01,REVISION 1SDR CA010509002Spar Cap · chafed(CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THEE EARLIER MAINTENANCE PROJECTS, ON THE FOLLOWING AIRCRAFT: (1) SDR CA010509003Spar Cap · chafed(CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THREE EARLIER MAINTENANCE PROJECTS, ON THE FOLLOWING AIRCRAFT:(1) SDR CA010509004Spar Cap · chafed(CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THREE EARLIER MAINTENANCE PROJECTS, ON THE FOLLOWING AIRCRAFT:(1) SDR CA010509005Spar Cap · chafed(CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THREE EARLIER MAINTENANCE PROJECTS, ON THE FOLLOWING AIRCRAFT:(1) SDR 20010524SG008Engine · failedFLT 1253 - HAV-MIA - EN ROUTE FROM HAVANA TO MIAMI, NR 1 ENGINE FAILED IN FLIGHT. REMOVED AND REPLACED NR 1 ENGINE. (M)SDR CA010301030Tube · worn(CAN) DURING INSPECTION, SEVERE WEARING WAS NOTED ON OUTBOARD FLAP DRIVE SECONDARY DRIVE TUBE P/N 72740196-011 BY THE STEADY BEARINGS. UNABLE TO DETECT WEAR PROPERLY UNLESS STEADY BEARING REMOVED. WEAR WAS FOUND ON BOTH SIDES OF FLAP DRIVE SYSTEM. MAXIMUM WEARSDR CA010131015Sealant · peeling(CAN) THE SEALANT USED UNDER THE NR 4 FLAP TRACK AS PER AD CF-87-04, SB 7-57-30 WAS FOUND PEELING OFF. 10481.68 HOURS HAVE ACCUMULATED ON THIS AIRCRAFT AFTER INITIAL APPLICATION BACK IN OCTOBER OF 1987. THIS AIRCRAFT HAS BEEN OPERATING IN ASIA.SDR CA001228029Filter · plugged(CAN) PENUMATIC DE-ICE SYSTEM FAILED IN FLIGHT. DE-ICE PRESSURE WAS DOWN TO 12-15 PSI INFLIGHT AND 8-10 PSI ON GROUND. MANUAL PRESSURE 1518 +/-1 PSI. MAINTENANCE FOUND THE SYSTEM FROZEN, AND ALL THE WATER SEPARATOR FILTERS PLUGGED WITH SOOT. THE FILTERS WERE ASDR CA001109004Fitting · broken(CAN) DURING CLIMB NR 2 HYDRAULIC PUMP CAUTION LIGHT ILLUMINTED, SYSTEM PRESSURE AND QUANTITY DROPPED TO ZERO. NR 1 HYDRAULIC PUMP THEN FAILED SHORTLY AFTER. MAINTENANCE DISCOVERED AN ALUMINUM HYDRAULIC LINE BROKEN AT THE FLARED FITTING. THIS LINE IS LOCATED SDR CA001106011Fuel Control · failed(CAN) ON THURSDAY 19 OCT. 2000, 11.22 GMT THE AIRCRAFT AT LIFT OFF THE PILOT NOTICED ENGINE NR 1 TORQUE INDICATOR STARTED TO DELAY AND ENGINE AUTO FEATHERED. CORRECTIVE ACTION TAKEN 1) FULL POWER RUNS CARRIED OUT PROBLEM COULD NOT BE REPEATED ON GROUND. 2) FUESDR CA001026015Fitting · cracked(CAN) DURING INSPECTION THE LEFT HAND OUTBOARD GROUND SPOILER INBOARD FITTING WAS FOUND CRACKED. SPOILER REMOVED FROM AIRCRAFT AND WILL BE REPLACED. THE CRACK LENGTH IS 0.75. NOTE: THE P/N WAS TAKEN FROM THE DATA PLATE ON THE SPOILER.SDR CA001026016Fitting · cracked(CAN) DURING INSPECTION, THE LEFT HAND INBOARD GROUND SPOILER FITTING WAS FOUND TO BE CRACKED BETWEEN FASTENERS. (NOTE: P/N WAS TAKEN FROM DATA PLATE ON THE SPOILER. SPOILER WILL BE REPLACED PRIOR TO AIRCRAFT RETURNING TO SERVICE. THE CRACKED FITTING IS LOCATESDR CA000907005Blade · misrepaired(CAN) . BLADE SER #841280. BLADE RECD FROM OPERATOR WITH FIBREGLASS DAMAGE BEYONG MANUAL LIMITSL. BLADE RETURNED TO MFG FOR REPAIR. BLADE RETURNED FROM MFG AFTER REPAIR ANDFOUND NOT TO COMPLY WITH COMPONENT MAINT MANUAL IN 2 AREAS. CMM61-13-01.1ST: ALUMINUM POSDR CA000824008Fuel Control · failed(CAN) THE FLIGHT CREW WAS COMPLETING THEIR PRE TAKEOFF CHECKS. THE NR 2 ENGINE WAS IN FEATHER. THE CREW HEARD A LOUD ENGINE ROAR. THE NR 2 ENGINE TORQUE AND TEMPS WERE INDICATING HIGH. THE ENGINE WAS SHUT DOWN. THE ENGINE WAS REPLACED, THE PROPELLER WAS INSPESDR CA000713016Fuel Control · failed(CAN) FUEL CONTROL UNIT WAS REPLACED. ENGINE RUN CARRIED OUT, TEST OKAY.AIRCRAFT RELEASED TO SERVICE.
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