U/A Canada PT6A-20
Service difficulty reports · 197
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 = 'PT6A20' 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 = 'PT6A20' 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 CA980916048Battery · failed(CAN) DURING RAMP TAXI FLIGHT, CREW AND PASSENGER NOTED SMOKE IN AFT CABIN. GENERATOR AND ELECTRICAL SYSTEMS SHUT DOWN. PASSENGER DEPLANED. BAGGAGE COMPARTMENT OPENED AND AUXILIARY BATTERY FOUND SMOKING. IT HAD HAD A THERMAL RUNAWAY AND WAS MELTED. NO OTHSDR 98ZZZX3585Bearing · failedIN-FLIGHT, ENGINE POWER LOSS. LT ENGINE SLOWED AND LOST POWER. PILOT FEATHERED PROPELLER. FLIGHT LANDED WITHOUT INCIDENT. ENGINE REMOVED. ENGINE, SN PCE21765, PT6A-20, DISASSEMBLED. BEARING NR 2 FOUND FAILED. BEARING EXAMINED FOR LUBRICATION STARVATION.SDR CA980827006Bolt · cracked(CAN) SHORTLY AFTER TAKEOFF, PILOT NOTICED THE ENGINE WOULD NOT PRODUCE PROPER POWER (30 POUND TORQUE AT 700 T5). THE AIRCRAFT CONTINUED TO DESTINATION. POST-FLIGHT INSPECTION RUN-UP INDICATED RUBBING SOUND FROM COMPRESSOR TURBINE AREA. THE ENGINE WAS SPLIT SDR CA980629014Skin · cracked(CAN) DURING INSPECTION BEECH SI-0423-133, A 1 INCH CRACK DISCOVERED ON LT ELEVATOR LOWER SKIN AT EDGE OF OVERLAP WITH OUTBOARD SKIN. DURING REPAIR WHEN THE SKIN WAS REMOVED THE CRACK RAN 6 INCHES LONG UNDER THE OVERLAP. REPAIRED. PART TC: 14,763.SDR CA980623007Cylinder · worn(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE CYLINDER WAS FOUND WORN. THE CYLINDER WAS REPLACED.SDR 98ZZZX2707Engine · failedLEFT ENGINE LOST POWER IN-FLIGHT. AIRCRAFT LANDED WITH NO INCIDENT. NO DETERMINATION MADE, UNIT MUST BE TORN DOWN TO INSPECT. SOUNDS LIKE BAD BEARINGS WHEN MOTORED BY STARTER. ACFT LOST POWER IN-FLIGHT. LANDED SAFELY AT SHEBOYGAN, WINCONSIN. PILOT REPORTSDR AU980979Switch · lack of lube(AUS) RIGHT MAIN LANDING GEAR DOWNLOCK MICROSWITCH STIFF DUE TO LACK OF LUBRICATION.SDR CA980421027Window · cracked(CAN) CRACK FOUND ON INSPECTION PER SAFETY COMMUNIQUE NR 142 ISSUED BY RAYTHEON AIRCRAFT COMPANY DATED NOVEMBER, 1997.SDR CA980330013Spline · stripped(CAN) AFTER TAKEOFF, LANDING GEAR SELECTED UP RED LIGHT REMAINED ON IN HANDLE. GEAR SELECTED TO DOWN POSITION AND RED LIGHT STILL REMAINED ON, NO GREEN LIGHTS. GEAR LOWERED MANUALLY. THIS A/C IS NOT MODIFIED TO HYDRAULIC GEAR AND STILL USES ORIGINAL BEECH ESDR 98ZZZX317Governor · failedPOWER TURBINE GOVERNOR FLYWEIGHTS AND BUSHING FAILED CAUSING GOVERNOR TO DUMP PY AIR TO FUEL CONTROL UNIT ALLOWING POWER TO DROP TO 50 PERCENT. ENGINE WAS FEATHERED AND RETURNED TO HOME BASE WHERE GOVERNOR WAS REPLACED WITH OVERHAULED UNIT AND CHECKED OPERATISDR CA971231030Circuit Breaker · fused(CAN) WHEN GROUND POWER APPLIED, AND CABIN LIGHTS SELECTED ON, SMOKE WAS OBSERVED COMING FROM THE OVERHEAD CIRCUIT BREAKER PANEL. WIRING FOR THE LEFT HAND CABIN LIGHTS DIM WAS FOUND COMPLETELY BURNT. THE 5 AMP CIRCUIT BREAKER WAS FUSED IN THE CLOSED POSITION. SDR CA971216067Blade · corroded(CAN) DURING FLIGHT, THE PILOT NOTICED A DROP IN TORQUE, APPROXIMATELY 15 POUNDS, WITH A CORRESPONDING RISE IN T5 OF 20 DEGREES AND A REDUCTION IN FUEL FLOW OF 220 POUNDS. UPON LANDING, THE ENGINE WAS REMOVED AND INSPECTION FOUND SEVERE COMPRESSOR DAMAGE.SDR CA971117004Connectors · burnt(CAN) IN COMPLYING WITH AIRCRAFT SERVICES MEMO EWS 97-04, FOUND ONE OVERHEATED KNIFE CONNECTOR. AFFECTED AREA REPLACED WITH RELEASABLE WIRE SPLICE.SDR CA971028011Splice · burned(CAN) ELECTRICAL WIRING REAR OF LT AND RT WING LANDING LIGHTS FOUND BURNT DUE TO OVERHEATED SPLICE. KNIFE CONNECTORS WERE FOUND INSTALLED. THESE WERE REPLACED BY RAYCHEM ENVIROMENTAL PERMANENT SPLICE. FLEET WIDE INSPECTION TO BE CARRIED OUT.SDR AU971374Bolt · broken(AUS) COMPRESSOR TURBINE VANE BOLTS (3OFF) HAD THE BOLT HEADS SEPARATE AND BECOME TRAPPED BETWEEN THE VANE AND TURBINE DISC CAUSING DAMAGE TO THE DISC IN THE AREA OF THE FIR TREE AND THE VANE.SUSPECT BOLTS WERE NOT REPLACED DURING THE LAST REPAIR WHICH WAS FORSDR CA970930005Supercharger · oil leak(CAN) TIME EXPIRED SUPERCHARGER WAS REPLACED WITH AN OVERHAULED UNIT AND THERE WAS NO INDICATION OF OIL LEAKS ON THE ENGINE GROUND TEST RUN UP. AFTER 3.3 HOURS OF FLIGHT TIME, THE FLIGHT CREW FOUND OIL INDICATOR FLOAT LEVEL LOW ON THE NEXT PRE-FLIGHT INSPECTIOSDR CA970922020Bolt · wrong part(CAN) DURING INSPECTION BOLTS ON THE COMPRESSOR TURBINE SHROUD ASSEMBLY HOUSING WERE FOUND DEFORMED WITH MATERIAL LOSS. INVESTIGATION FOUND THE BOLTS USED IN THIS INSTALLATION WERE THE WRONG PART.SDR CA970909004Latch · failed(CAN) DOOR RIGGING FOUND TO BE A PROBLEM. INSPECTION FOUND ONE DOOR HOOK TO BE PHYSICALLY DIFFERENT CAUSING THE RIGGING DIFFICULTY.SDR CA970728003Transfer Sleeve · scored(CAN) DURING INSEPECTION OF THE REDUCTION GEAR NOSE CASE CHIP DETECTOR AND OIL SCREENS, SUBSTANTIAL AMOUNTS OF METAL PARTICLES WERE FOUND. THE ENGINE WAS REMOVED AND SENT FOR INSPECTION AND REPAIR. DISASSEMBLY REVEALED THE PROPELLER SHAFT TRANSFER SLEEVE HAD SSDR AU970736Circuit Breaker · intermittent(AUS) LANDING GEAR MOTOR 50AMP CIRCUIT BREAKER INTERMITTENTSDR CA970513010Skin · cracked(CAN) DURING 150 HR INSPECTION OF ELEVATOR AND STAB SKIN PER BEECH SI 0086-131, A 10 INCH CRACK WAS FOUND IN THE ELEVATOR UPPER SKIN BARREL TO DIRECTION OF FLIGHT ON THE EDGE OF OVERLAP OF TWO SKINS. SKIN REPLACED. AIRCRAFT TT: 11,077 HOURS.SDR CA970402005Nut · stripped(CAN) NUT STRIPPED ON MAIN GEAR ACTUATOR.SDR CA970326008Bolt · missing(CAN) IN CRUISE AT 11,500 FEET, A/C DEVELOPED NOTICEABLE VIBRATION, AUTOPILOT DISCONNECTED AND A/C STARTED A ROLL TO THE RIGHT. CONTROL REGAINED AND AT 8,000 FEET, VIBRATION WAS VERY CRITICAL. COPILOT HAD BOTH FEET ON RUDDER PEDALS TO DAMPEN VIBRATION. RUDDSDR CA970121006Deice Valve · failed(CAN) ON APPROACH AIRCRAFT ENCOUNTERED HEAVY ICING CONDITIONS. AFTER LANDING THE INBOARD HALF OF WING FOUND COVERED WITH ICE. WING DEICE DISTRIBUTOR VALVE WAS CYCLED BUT DID NOT WORK. VALVE REPLACED. A MOD WILL BE INTRODUCED TO INSTALL HEATER AROUND THE VALVESSDR CA961218006Spar · failed(CAN) ON LANDING, THERE WAS A MAJOR FAILURE OF THE RIGHT WING STRUCTURE BETWEEN THE NACELLE AND THE FUSELAGE. TSB INVESTIGATING. PART TC: 22,672.SDR CA961115012Flap Spars · cracked(CAN) BOTH LEFT AND RIGHT HAND INBOARD FLAPS WERE FOUND TO HAVE CRACKS IN THEIR SPARS. THE CRACKS, APPROXIMATELY 1 INCH IN LENGTH ARE LOCATED AT THE SLOT IN THE SPAR THAT ALLOWS THE INBOARD FLAP TRACK TO PASS THROUGH. THE CRACKS RADIATE IN BOTH DIRECTIONS AWAYSDR CA961118002Torque Tube · cracked(CAN) DURING EMMA #27 INSPECTION LIGHT RUB ON TOP STARBOARD SIDE OF CABLE BELLCRANK QUADRANT WHERE THE QUADRANT GOES THROUGH THE BULKHEAD. FURTHER CHECK NOTED THAT THE TORQUE TUBE THAT JOINS THE ELEVATOR CONTROL ROD LEVER TO THE CABLE QUADRANT HAD A DARK LINE SDR CA961113006Spar · cracked(CAN) LEFT INBOARD FLAP SPAR FOUND WITH A CRACK AT THE INBOARD AREA WHERE THE BRACKET ROLLERS ATTACH. PART TC: 11,398. AIRCRAFT TT: 11,883 HOURS.SDR CA961030001Spar · cracked(CAN) AT INBOARD FLAP TRACK CUTOUT IN THE SPAR THERE ARE TWO CRACKS EXTENDING FROM THE TOP CORNERS OF THE CUTOUT INTO THE BEND RADIUS. EACH CRACK ABOUT 2 INCHES LONG. PART TC: 16,223. AIRCRAFT TT: 12,807 HOURS.SDR CA961104007Spars · cracked(CAN) BOTH INBOARD FLAP SPARS WERE FOUND WITH CRACKS ON THE SPAR. THESE CRACKS WERE LOCATED AT THE AREA WHERE THE BRACKET FOR THE ROLLERS ATTACH. RIGHT HAND SPAR IS A 50-160003-55. PART TC: 10,688. AIRCRAFT TT: 10,893 HOURS.SDR CA961029007Spar · cracked(CAN) SMALL CRACK, APPROXIMATELY 0.750 INCH IN LENGTH WAS DETECTED ON THE LEFT INBOARD FLAP SPAR AT THE INBOARD FLAP TRACK ATTACHMENT POINT ON THE UPPER SKIN FROM THE RIVET. A LARGER CRACK WAS THEN FOUND, APPROXIMATELY 4 TO 6 INCHES IN LENGTH, FURTHER OUTBOARSDR CA961029001Wire · broken(CAN) ON PREFLIGHT PILOT NOTICED FLOAT BRACE WIRE END FORWARD LEFT HAND BROKEN AT BRACE WIRE CLEVIS ATTACH. PART SENT TO MANUFACTURER FOR INVESTIGATION.SDR CA960924020Back Plate · worn out(CAN) DURING OVERHAUL A PIECE OF BRASS WAS NOTED PROTRUDING BETWEEN THE BACK PLATE AND THE ARMATURE SHAFT. BRASS TURNED OUT TO BE A BRASS SHIM. INSERTED BETWEEN THE ARMATURE AND THE BACK PLATE SEAT. BACK PLATE FOUND WORN WELL BEYOND TOLERANCES AND THE BRASS HASDR CA960827018Coupling Drive · sheared(CAN) THE PILOT WAS FORCED TO SHUT THE ENGINE DOWN BECAUSE HE WAS UNABLE TO CONTROL IT. THE DEFECT WAS CAUSED BY THE BREAKING OF THE FUEL CONTROL AND FUEL PUMP COUPLING.SDR CA961007008Chip Detector · broken(CAN) ON TAKEOFF OIL PRESSURE ON LEFT ENGINE STARTED DROPPING AND VISUAL INSPECTION NOTED OIL POURING FROM ENGINE COWLING. ENGINE SHUTDOWN AND AIRCRAFT RETURNED. CANNON PLUG ON CHIP DETECTOR WAS INSTALLED 180 DEGREES OUT AND WAS HITTING ON LOWER COWLING RIB.SDR CA960827004Shaft Input · decoupled(CAN) DURING CLIMBOUT AFTER TAKEOFF THE #2 ENGINE STOPPED WITHOUT WARNING. ENGINE FAILURE DRILLS WERE CARRIED OUT & AIRCRAFT RETURNED TO POINT OF DEPARTURE. POST FLIGHT INSPECTION REVEALED METAL FLAKES IN THE OIL FILTER & A GRATINGSOUND FROM THE ACCESSORY GEARSDR CA960527003Gear Door · jammed(CAN) GEAR IN TRANSIT LIGHT STAYED ON AFTER GEAR RETRACTION. EMERGENCY GEAR EXTENSION RESULTED IN L.H. GEAR PARTIALLY EXTENDED. L.H. MAIN INBOARD GEAR DOOR JAMMED, PREVENTING GEAR EXTENSION.SDR CA960521005Blades · fractured(CAN)IN CRUISE, #2 ENGINE PARAMETERS DROPPING. ENGINE SECURED AND RETURN TO POINT OF DEPARTURE. INVESTIGATION REVEALED THE COMPRESSOR TURBINE BLADES FRACTURED NEAR THE ROOT PLATFORM.SDR 96ZZZX2700Bearing · failedRIGHT ENGINE FLUCTUATIONS 2-3 SECONDS, 3 TIMES. AIRCRAFT YAW. FIFTEEN MINUTES LATER, FLUCTUATINS OCCURRED THEN FUEL FLOW WENT TO ZERO. ENGINE QUIT. RESTARTED ON GROUND, NO RESPONSE TO THROTTLE. DISASSEMBLED FUEL CONTROL, FOUND BUSHING ASSY BEARING FAILED.SDR CA960507001Blower Motor · seized(CAN) ON TAKEOFF ROLL, TOWER ADVISED THAT FLAME VISIBLE ON BOTTOM OF AIRCRAFT, TAKEOFF ABORTED. COMBUSTION BLOWER MOTOR FOUND INOPERATIVE, OTHER HEATER SYSTEM FUNCTIONS CHECKED OK AT THIS TIME.SDR CA960419003Combustion Tube · cracked(CAN)DURING A SCHEDULED 500 HOUR HEATER PRESSURE DECAY TEST, LEAKAGE RATE WAS FOUND TO BE EXCESSIVE. UNABLE TO PINPOINT THE EXACT LOCATION DUE TO ACCESS PROBLEMS. HEATER WAS REPLACED AND SENT FOR OVERHAUL.SDR 96ZZZX780Bearing · failedFIRST STAGE REDUCTION GEAR BEARING FAILED CAUSING GEAR TO BIND OR SEIZE CAUSING POWER TURBINE SHAFT TO SHEAR CAUSING ENGINE TO STOP. CAUSE OF BEARING FAILURE UNKNOWN.SDR CA960131008Arm Assembly · missing parts(CAN)AFTER START THE LEFT HAND SECONDARY LOW PITCH ANNUNCIATOR WAS NOT ILLUMINATING AS REQUIRED. MAINTENANCE INVESTIGATION REVEALED THE CARBON BRUSH BLOCK OF THE PROPELLER PITCH REVERSING ARM ASSEMBLY WAS MISSING & THE ATTACHING LEVER ARM WAS BENT. THERE WAS SDR CA960102005Snow Deflector · not locked(CAN) PILOT REPORTED THAT IN CRUISE FLIGHT, IN MODERATE SNOW AND PRECIPITATION, THE NR 2 ENGINE BEGAN TO LOSE POWER. A PRECAUTIONARY ENGINE SHUTDOWN WAS CARRIED OUT. POST-FLIGHT INSPECTION REVEALED THAT THE NR 2 ENGINE SNOW DEFLECTOR WAS IN THE RETRACTED POSSDR CA951102004Quill Shaft · overheated(CAN)GEAR BOX REMOVED FOR SCHEDULED INSPECTION WITH 96.0 HOURS REMAINING. CURSORY INSPECTION OF THE GEAR BOX INDICATED NO DEFECTS UNTIL THE QUILL SHAFT WAS TURNED BY HAND. DURING THIS INSPECTION THE QUILL SHAFT AND BEARINGS SHOWED SIGNS OF OVER-HEATING. THE BSDR 95ZZZX1683Compressor · fod damageMGY - EN ROUTE, RT ENGINE FUEL FLOW FLUCTUATED AND FLAMES WERE OBSERVED OUT OF EXHAUST. FLIGHT DIVERTED TO DAY WHERE INSPECTION SHOWED FOD TO FIRST STAGE COMPRESSOR. ENGINE REMOVED FOR INSPECTION AND REPAIR FOLLOW-UP.SDR 95ZZZX751Pump · failedDURING APROACH TO LANDING, RIGHT ENGINE LOST POWER. INSPECTION AND REMOVAL OF THE FUEL PUMP REVEALED A FAILURE OCCURRED INTERNALLY IN THE FUEL PUMP ASSY. THIS ALSO CAUSED THE ENGINE-TO-PUMP DRIVE COUPLING TO FAIL. FAILURE OF THE ENGINE DRIVEN PUMP AND DRIVE
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