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 CA120327003Angle · cracked(CAN) WHILE CONDUCTING A CORROSION INSPECTION, CRACKS WERE FOUND ON THE NR 1 NACELLE, OTBD LONGERON CHANNEL, PN 75410103-105, AND LONGERON ANGLE, PN 75410104-103, AND NR 4 NACELLE, INBD LONGERON CHANNEL, P/N 75410119-106, LONGERON ANGLE P/N 75410104-104, NR 4 SDR CA120219001Boot · failed(CAN) A LIGHT PULSING SENSATION WAS FELT IN THE LT CONTROL WHEEL SHORTLY AFTER ROTATION. FLAP RETRACTION AT 400. NO CHANGE FELT. ACCELERATED TO NORMAL CLIMB SPEED OF 150 KTS. PULSING SENSATION IN LT CONTROL WHEEL REDUCED SLIGHTLY. DURING THE CLIMB THE AIRSDR CA120216001Wire · chafed(CAN) WHILE CONDUCT EWIS TASK E-430 ON THE NR 3 NACELLE, NUMEROUS WIRES WERE FOUND TO HAVE BEEN CHAFED BY THE PHENOLIC BLOCK THAT SECURES THESE WIRES AS THEY PASS FROM THE RT MLG WHEEL WELL THROUGH THE FIRE WALL. THE WIRING AFFECTED IS AS FOLLOWS: 7160-30006DSDR CA120214006Longeron · cracked(CAN) WHILE CONDUCTING A CORROSION INSPECTION, CRACKS WERE FOUND ON THE NR 1 NACELLE OTBD LONGERON CHANNEL, PN 75410103-105 AND LONGERON ANGLE, PN 75410104-103 AND NR 4 NACELLE INBD LONGERON CHANNEL, PN 75410119-106 AND LONGERON ANGLE, PN 75410120-104. THE CSDR CA120213003Cable · broken(CAN) DURING PRE-FLIGHT INSPECTION OF THE ACFT, AFTER PULLING THE AILERON DISCONNECT HANDLES, IT WAS NOTICED THAT THE AILERON CONTROL WAS NOT ROTATING FULLY TO THE LT. MAINTENANCE INSPECTED AND COULD NOT REPRODUCE THE EFFECT UNTIL AFTER THEY OPERATED THE AUTO-SDR CA120110005Nose Cone · cut(CAN) DURING A WALK AROUND, NOTICED SOME IMPACT DAMAGE ON THE COMPOSITE NOSE, ON THE LT SIDE AT STA X140 AND Z105.5. A "KNIFE LIKE" CUT THROUGH THE FIBERGLASS SHELL, APPROXIMATELY 1.5" LONG, AND GOING APPROXIMATELY 1 MILLIMETER DEEP INTO THE UNDERLYING HONEYCSDR CA120116010Tube · leaking(CAN) HYDRAULIC LEAK FROM NR 1 NACELLE NOTICED AFTER LANDING. THE LEAK LOCATED AT NR 1 PRESSURE MANIFOLD SUPPLY LINE. MAINTENANCE REPLACED THE TUBE AND REPLENISHED HYD SYS NR 1, ACFT WAS RETURNED TO SERVICE.SDR CA111219010Receiver · failed(CAN) INBOUND FOR LANDING, THE NR 2 GPS SCREEN WAS SEEN TEMPORARILY GOING BLANK THAN COMING BACK ON. WITHIN A FEW SECONDS BOTH CREW MEMBERS NOTED AN ODD ODOR IN THE COCKPIT. THE NR 2 GPS WAS TURNED OFF AND THE CIRCUIT BREAKERS WERE PULLED. THE ODOR DISSIPATEDSDR CA111110001Tire · separated(CAN) DURING A WALK AROUND A DEFECT WAS NOTICED ON THE INBD RT MAIN WHEEL TIRE. INVESTIGATION REVEALED THAT THE TIRE WAS SEPARATING/SPLITTING IN THE GAP BETWEEN THE TREAD, THIS WAS WELL INTO THE CORD. THE DEFECT WAS PRESENT 360 DEGREES AROUND THE TIRE IN VARYSDR CA110930011Data Plate · misinstalled(CAN) AFTER REPLACEMENT OF NR 3 CONSTANT SPEED UNIT, A FUNCTION CHECK WAS CARRIED OUT OF THE CONTROL SYS. IT WAS OBSERVED THAT ONCE YOU SELECTED MAX RPM YOU COULD NOT GO BACK TO MIN RPM OR FUEL SHUTOFF BECAUSE THE DATA PLATE ON THE AFT FACE OF THE CSU HAD BEESDR CA110811005Line · failedDURING CRUISE , ENROUTE , NR 1 HYD SYS FAILED. CREW COMPLETED THEIR CHECKLIST AND LANDED NORMALLY WITHOUT INCIDENT AT AN ALTERNATE DESTINATION. ON GROUND LOCATED LEAK IN NR 1 NACELLE AT THE HYD MANIFOLD SUPPLY LINE. THE TUBE IN QUESTION HAD FRACTURED FOR APSDR CA110621009Pump · leakingUPON STARTING THE NR 3 ENGINE, THE T5 WAS OBSERVED TO BE RISING WHILE THE NG WAS SLOW TO RISE. THE START WAS ABORTED WHEN THE T5 HIT 900 DEGREES. MX INVESTIGATED AND FOUND THAT THE FUEL PUMP WAS LEAKING AND THE FUEL WAS GOING THROUGH THE GARLOCK SEAL AND INTSDR CA100804014Reservoir · leakingWHILE IN CRUISE FLIGHT, A ROUTINE CHECK OF THE ENGINES/SYS REVEALED THE NR 2 HYD FLUID QTY WAS INDICATING A SLIGHTLY LOWER LEVEL THAN EARLIER NOTED. AFTER A FEW MORE MINUTES OF MONITORING A SLIGHTLY FURTHER DROP WAS NOTED. THE DECISION WAS MADE TO RETURN TO BSDR CA100706014Roll Pin · brokenWHEN THE DASH 7-103 A/C REACHED ITS INITIAL DESTINATION AND THE GEAR WAS LOWERED, THE MLG DOWN AND LOCKED GREEN LIGHTS WERE LIT BUT NOT THE NLG DOWN AND LOCKED GREEN LIGHT. THE GEAR WAS CYCLED BUT AGAIN THE NLG GREEN LIGHT DID NOT COME ON. THE CAPTAIN DECIDESDR CA100805011Garlock Seal · leakingON THE 29TH OF JUNE 2010, THE ACFT WAS FLYING IN CRUISE, THE PILOT NOTICED THE NR 4 ENGINE OIL PRESSURE DROP TO BELOW 75PSI. THE PILOT SHUTDOWN THE ENGINE IAW QRH. THE ACFT RETURNED TO BASE SAFELY. INVESTIGATING THE SEAL, FOUND OIL LEAK FROM HYD PUMP, GARLOCSDR CA091126002Tube · misinstalled(CAN) DURING FLIGHT, NR 4 ENGINE LOST OIL PSI INDICATION ALONG WITH MASTER CAUTION & OIL PSI LIGHT ILLUMINATED ON ANNUNCIATOR PANEL. ENGINE SHUTDOWN & ACFT LANDED WITHOUT FURTHER INCIDENT. ENGINE INSPECTED & FOUND TO HAVE NO OIL IN OIL TANK. AFTER SERVICING OISDR CA090821007Stud · shearedAFTER LANDING ROLL AT LXR, SPEED APPROX 20 KTS ON GROUND, A SEVERE VIBRATION, SHIMMY AND ABNORMAL SOUNDS WERE NOTICED IN NLG AREA OF THE ACFT WITH NO STEERING RESPONSE FROM THE NOSE WHEEL STEERING TILLER. STEERING SWITCHED OFF AND GENTLY TAXIED INTO THE ACFT SSDR CA090204007Control Cable · separatedON APPLICATION OF BRAKES AFTER LANDING, THE LEFT PEDAL WENT TO THE MAX POSITION WITH NO EFFECT. LT BRAKE CABLE WAS FOUND SEPARATED APPROX 8 INCHES FROM THE VALVE IN THE UPPER FUSELAGE CLOSE TO A SMALL DIAMETER PULLEY. THIS CABLE WAS THE ORIGINAL INSTALLED INSDR CA081222004Control Cable · corroded(CAN) DURING A PREFLIGHT, THE LEFT ELEVATOR DID NOT MOVE WITH THE CONTROL COLUMN INPUT. MAINTENANCE INVESTIGATED AND FOUND ONE OF THE CABLES SNAPPED UNDER THE LAVATORY. SUSPECT THAT A PREVIOUSLY REPAIRED LEAK FROM THE LAVATORY HAD LEAKED ON THE CABLES, AND TSDR CA080418001Rheostat · melted(CAN) CONCERNED WITH THE USE OF RHEOSTAT (PN REE75R) FOR REPLACEMENT OF RHEOSTAT SWITCH 20465-1. THE SB 7-33-21 CALLS THE NEW RHEOSTAT, A RHEOSTAT SWITCH BUT IT DOES NOT HAVE AN "OFF" POSITION LIKE THE ORIGINAL RHEOSTAT SWITCH HAD. AS SUCH, WHEN IT IS TURNED TSDR CA080116017Housing · cracked(CAN) DURING A 6 YEAR CORROSION INSPECTION, A CRACK WAS FOUND ON THE LT MLG OUTER HOUSING. THE CRACK IS LOCATED ON THE FWD SIDE AT ABOUT THE ONE O’CLOCK POSITION JUST WERE THE HOUSING TAPERS DOWN. EDDY CURRENT WAS USED ON THE CRACK, IT WAS DEEPER THAN THE 0.04SDR CA071217004Control Cable · disconnected(CAN) AFTER FLIGHT, THE NR 2 CONDITION LEVER WOULD NOT MOVE TO FEATHER OR CUTOFF, THE ENGINE HAD TO BE SHUTDOWN USING THE T-HANDLE. FURTHER INVESTIGATION REVEALED THAT THE NR 2 TELEFLEX CABLE HAD BECOME UNSCREWED NEAR THE BEARING. WE WERE UNAWARE THAT THE CASDR CA071115002Bearing · failed(CAN) AFTER LANDING THE LT OB MAIN WHEEL HUBCAP WAS DISCOVERED MISSING. FURTHER INVESTIGATION FOUND THE INNER BEARING WAS BLOWN APART, THE WHEEL AND BRAKE ASSY HAD EXTENSIVE DAMAGE FROM THE WHEEL RUBBING ON THE BRAKE ASSY. THE AXLE WAS INSPECTED, NO DAMAGE WASSDR CA070829004Intake Duct · corroded(CAN) LEVEL 3 CORROSION WAS FOUND BETWEEN THE LOWER INTAKE FORWARD LIP AND THE NACELLE STRUCTURE. (TC NR 20070829004)SDR CA070830006Rod · broken(CAN) DURING TROUBLESHOOTING, A PFCS INDICATOR PROBLEM, IT WAS NOTICED THAT THE ROD FOR THE RT IB ROLL SPOILER TRANSMITTER HAD SHEARED INSIDE OF THE ROD END AT THE SPOILER END. THERE WAS NO INDICATIONS OF THE ROD CONTACTING ANY OTHER SURFACE TO CAUSE IT TO BRESDR CA070710004Guide Vane · failed(CAN) DURING FLIGHT, THE TURBINE TEMPERATURE ROSE SUDDENLY FROM 738 TO 785 DEGREES CELSIUS. A BORESCOPE INSPECTION REVEALED DAMAGE TO THE CT GUIDE VANE. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE HOT SECTION WAS REMOVED FROM THE ENGINE ASDR CA070214005Line · broken(CAN) AFTER LANDING THE NR 1 PROP RPM WAS LOWER THAN NORMAL. MAINTENANCE FOUND THAT THE P3 LINE FROM THE P3 FILTER BOWL TO THE ENGINE WAS BROKEN PN 3035279. THE LINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070214005)SDR CA061123003Impeller · cracked(CAN) "IMPACT DAMAGE AND A CRACKED IMPELLER". A CRACK IN THE OUTER IMPELLER WAS FOUND. (TC# 20061123003)SDR CA061205006Shim · broken(CAN) AFTER LANDING, A POST-FLIGHT INSPECTION REVEALED AN OIL LEAK IN THE NR1 PROP. FURTHER INVESTIGATION SHOWED THAT THE BLADE SHIMS HAD BEEN INSTALLED ON THE WRONG SIDE OF THE BLADE RETAINING RING. THE SHIMS HAD BROKEN AND DAMAGED THE OIL SEALS. THE OTHER 3 SDR CA061106018Line · broken(CAN) WHILE IN CRUISE THE NR 3 ENGINE ROLLED BACK TO 60% NG.. A PRECAUTIONARY SHUT DOWN OF THE ENGINE WAS COMPLETED AND THE AIRCRAFT RETURNED TO BASE. ON INSPECTION OF THE ENGINE IT WAS FOUND THAT THE P3 SENSE LINE, FROM THE GAS GENERATOR CASE TO THE P3 FILTERSDR CA061219013Tube · fractured(CAN) ENGINE POWER ROLLED BACK UNCOMMANDED DURING CLIMB. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED A FRACTURED P3 PRESSURE LINE TO THE FUEL CONTROL UNIT. (TC NR 20061219013)SDR CA061106015Diffuser · loose(CAN) SHORTLY AFTER LEVELLING OFF AT 17000 FEET, THE NR 2 ENGINE BEGAN TO SURGE AFFECTING ALL ENGINE PARAMETERS. THE POWER WAS REDUCED TO ALLEVIATE THE RESULTING OVER TEMPERATURE CONDITION. AT POWER SETTING ABOVE 70% NG THE ITT WOULD FLUCTUATE WILDLY TO OVER SDR CA060821004Fcu · failed(CAN) AFTER INSTALLING THE FRESHLY OVERHAULED ENGINE IN THE NR 1 POSITION, THE ENGINE WAS STARTED TO PERFORM THE BETA RIGGING; THE PROPELLER WAS UNFEATHERED, THE POWER LEVEL MOVED UP TO THE FWD BETA STOP TO RECORD NUMBERS, ALL THE PARAMETERS STABILIZED. THE NSDR CA060712005Engine · failed(CAN) ABORTED TAKEOFF DUE TO NR 3 ENGINE FAILURE. DURING TAKEOFF ROLL AIRCRAFT REACHED APPROXIMATELY 45 KNOTS WHEN A JOLT WAS FELT. THE PILOT NOTICED ABNORMAL READINGS ON THE NR 3 ENGINE GAUGES & LARGE AMOUNTS OF SMOKE COMING OUT OF THE NR 3 ENGINE. EMERGENCY SDR CA060731011Engine · malfunctioned(CAN) ON TAKEOFF ROLL THE ENGINE EMITTED A LOUD NOISE AND SMOKE WAS SEEN EMERGING FROM THE EXHAUST. TAKEOFF WAS ABORTED AND THE ENGINE SECURED. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731011)SDR CA060717007Ballast · overheated(CAN) VP-FBQ (DASH 7, S/NO 111) FLUORESCENT TUBE LAMP HOLDER OVERHEATING PROBLEM SHORTLY AFTER RE-INSTATING POWER DURING A C CHECK, A STRONG SMELL OF BURNING WAS NOTED IN THE FWD SECTION OF THE AIRCRAFT. THE FAULT WAS TRACED TO A LAMP HOLDER AT THE FRONT OF TSDR CA060405002Engine · making metalENGINE OIL METAL CONTAMINATION WAS REPORTED AND ENGINE SENT TO APPROVED ENGINE FACULITY.SDR CA060504002Drive Assy · failedCLIMB TO FL 120, AT FL 085 COMMUNICATION ESTABLISHED WITH APPROACH, AND INSTRUCTED TO MAINTAIN FL 080. CAPT TOLD GO TO DESCENT AND MAINTAIN 080, AUTOPILOT WAS ENGAGED, CAPT REALIZED A/C WAS STILL CLIMBING AND THE WHEEL TRIM WAS TRIMMING FULL NOSE-UP, FO PUSHISDR CA051130012Light · burnedDURING PRESTART CHECKS BOTH THE PAX AND CREW NOTICED A BURNING ODOR AND THE FLIGHT WAS ABORTED. MAINTENANCE INSPECTION REVEALED A CHARRED RECEPTACLE FOR THE FLUORESCENT TUBE IN THE WINDOW LIGHT. FURTHER INVESTIGATION HAS SHOWN THAT BOTH THE RECEPTACLE AND THSDR CA051124005Bolt · corroded(CAN) DURING C CHECK, BOLT ON FWD CARGO DOOR FITTING WAS CORRODED TO THE EXTENT THAT BOLT HEAD SEPARATED AT LIGHT FINGER TOUCH. 6 FITTINGS ARE BOLTED TO THE SILL STRUCTURE BY 2 BOLTS EACH. THEY SECURE THE DOOR IN THE CLOSED POSITION. THE MOST FWD BOLT OF THE 1SDR CA051116008Engine · failed(CAN) ON OCTOBER 31, 05, THE PILOTS WHEN APPROACHING, WERE TOLD TO RETURN TO DEPARTURE, BECAUSE THE AIRPORT WAS CLOSED. UPON LANDING AFTER SLOWING THE AIRCRAFT, THE PILOT TRIED TO BRING THE POWER LEVERS TO FLT IDLE, BUT THE NR 3 ENGINE WOULD NOT MOVE. MAINTENSDR 2005FA0001475Engine · seizedENGINE INSTALLED ON AIRCRAFT AFTER RETURN FROM REPAIR FACILITY. DURING INITIAL GROUND RUN OF ENGINE THE POWER LEVER SEIZED AND VERY HARD TO MOVE. ENGINE TEMPERATURE AND PRESSURE WERE NORMAL. FEATHERED THE PROPELLER AND SHUTDOWN ENGINE. POST INSPECTION SHOWSDR CA051027006Windshield · cracked(CAN) AC, WHILE IN LIGHT ICING CONDITIONS, ENCOUNTERED A MALFUNCTION OF CAPTAIN'S (LT SIDE) WINDSHIELD. ENTERING ICING CONDITIONS, NORMAL MODE WAS SELECTED. CAPTAIN NOTICED DISCOLORATION IN LWR PORTION OF WINDSHIELD, VERBALIZED IT TO F/O. CAPTAIN OBSERVED DISCSDR CA050928003Bearing Race · cracked(CAN) DURING A ROUTINE VISUAL INSPECTION THE INNER BEARING RACE OF THE NR 4 MAIN WHEEL ASSY WAS FOUND CRACKED.SDR CA051006006Compressor · damaged(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER ROLL-BACK TO IDLE IN CRUISE, AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE 1ST STAGE COMPRESSOR BLADES. WILL MONITOR INVESTIGATION OF THE INCIDENT AND ADVISE OF ROOT CAUSE, ONCE ESTSDR CA050726002Engine · failed(CAN) DAMAGE OCCURRED TO PLATING OF FWD SEALING DIAMETER OF BETA CNTRL OIL TRANSFER SLEEVE. DIAMETER INDICATED BOND OF PLATING TO PARENT MATERIAL OF SLEEVE WAS STILL GOOD, WAS SCORING FROM FOD. EXTRUSION OF PLATE FWD FROM DIAMETER, INDICATION PIECES HAD SEPARSDR CA050725019Seal · leakingDURING CRUISE, OIL PRESSURE FLUCTUATED AND DECREASED. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED. GROUND INSPECTION REVEALED A LEAKING HYDRAULIC PUMP PAD ACCESSORY GEARBOX SEAL.SDR CA050707002Adc · malfunctionedDURING ROUTINE MAINTENANCE AND RECERTIFICATION OF THE AIRCRAFT AIR DATA COMPUTERS AND FLIGHT MANAGEMENT SYSTEM THE TECHNICIANS NOTED THAT THE ADC S SYSTEM HAD BEEN MODIFIED TO USE P/N 7000700-637 ADC S IN PLACE OF THE DEHAVILLAND INSTALLED P/N 7000700-920 UNITSDR CA050527010Engine · failedTHE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED GRINDING NOISES FROM THE POWER SECTION. THE ENGINE WAS REMOVED FOR REPAIR.SDR CA050323003Engine · failed(CAN) FOUND BETA CNTRL SYS WAS JAMMED. BETA CNTRL SLEEVE HAD WORN AGAINST PROPSHAFT DIA. RGB WAS REBUILT, IDENTICAL FAILURE IN TEST CELL. RGB WAS REBUILT, TESTED, RETURNED. NOT INSTALLED BUT RETURNED BECAUSE OF LOOSE MOUNT RING ON RGB. CORRECTED, ENG TESTED
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