U/A Canada PT6A-65B
Service difficulty reports · 628
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 = 'PT6A65B' 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 = 'PT6A65B' 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 CA110322001Engine · failed(CAN) MARCH 16TH, 2011, 11:20 PM, DIVERTED DUE TO RISE IN ITT, FOLLOWED WITH AN ENG SURGE. THE CREW SHUT THE ENG DOWN & LANDED SAFELY AT THE AIRPORT. AS OF NOW ALL WE KNOW IS THAT THERE WAS AN INTERNAL ENG FAILURE. THE ENG WAS REMOVED & SENT FOR A TEAR DOWNSDR EPUA12152010404GVActuator · failedNLG FAILED TO EXTEND DUE TO FAILURE OF HYD ACTUATOR CAUSING LOSS OF HYD FLUID. UPON INSP, HYD ACTUATOR END CAP FOUND TO BE UNSERVICABLE.SDR HSYA2010110310Landing Gear · malfunctionedAFTER TAKEOFF, THE LANDING GEAR WOULD NOT RETRACT -COME UP-AFTER CYCLING THE GEAR STILL WOULD NOT COME UP AND WAS STILL INDICATING 3 GREEN IN THE DOWN POSITION. CREW ADVISED THE TOWER AND DECLARED AN EMERGENCY TO LAND. ACFT LANDED WITH NO FURTHER INCIDENT. MX SDR CA101020001Wire · chafedWHILE COMPLETEING PHASE 3 INSP IN THE CABIN WHICH INVOLVES REMOVING THE FLOOR PANELS, THERE WERE WIRES FOUND CHAFING ON THE EDGE OF THE WIRING TRAY AT FS 177.35. ALSO DISCOVERED WIRES CHAFED THROUGH THE INSULATION AND WAS ARCING ON THE METAL TRAY THAT THE WISDR CA100921005Engine · failedLOSS OF TORQUE/IFSD DURING FLIGHT, THE PILOT REPORTED ENGINE NOISES AND OBSERVED TORQUE INDICATION DECREASING. HE ELECTED TO SHUTDOWN THE ENGINE AND AN UNEVENTFUL SINGLE ENGINE LANDING WAS PERFORMED. POST FLIGHT INSP FOUND DAMAGES TO THE COMPRESSOR.SDR CA100723004Line · crackedON TAKEOFF, ENGINE WAS UNABLE TO ACHIEVE FULL POWER AND ACFT RETURNED TO BASE. A NORMAL LANDING WAS CARRIED OUT. UPON INSP, THE P3 LINE FROM THE COMPRESSOR CASE TO THE FCU WAS FOUND CRACKED, PREVENTING FULL P3 AIR FROM REACHING THE FCU. LINE WAS REPLACED, NOSDR CA100715004Wire · burnedWHEN REMOVING THE RT CIRCUIT BREAKER PANEL TO CHECK THE EDGELIGHT PANEL, THERE WAS ONE BRASS SCREW WITH THE TIP BURNED. MX IMMEDIATELY INVESTIGATED THE SOURCE. THERE WAS A NR 10 WIRE FROM THE AVIONICS BUSS BAR TO THE ARTIFICIAL HORIZON THAT WAS ALMOST BURNEDSDR FFSA201000001Channel · crackedDURING NR 3 PHASE INSP THE LOWER DOOR FRAME CHANNEL WAS FOUND TO BE CRACKED. THE CHANNEL, PN 114-420041-41, RUNS FROM FUSELAGE STA 150.60 TO STA 177.35 ACROSS THE BOTTOM OF THE DOOR OPENING. THE CRACK WAS LOCATED IN THE BEND RADIUS OF THE OTBD SUPPORT FLANGE SDR CA100622013Compressor · failedON SHORT FINAL, LT ENGINE STARTED TO SURGE, TORQUE FLUCTUATING BETWEEN 200-1200 LBS, ITT RISING RAPIDLY TO 900 DEGREE`S. THE POWER WAS REDUCED TO IDLE AND LANDED NORMALLY. TAXIED IN ON IDLE POWER AND SHUTDOWN ENGINE. MX FOUND 1 STAGE COMPRESSOR RUBBING ON HOSDR HSYA2010060210Cable · looseAFTER ROTATION, CAPTAIN REPORTED AN UNCOMMANDED RT ENGINE AUTO FEATHER. THE ACFT RETURNED TO THE AIRPORT WITHOUT FURTHER INCIDENT ARRIVING BACK IN THE BLOCKS FOR MX TROUBLESHOOTING AND EVALUATION AT 1355Z. MX TROUBLESHOT ACFT AND FOUND BETA VALVE OUT OF ADJUSTSDR CA100525018Resistor · overheatedAFT VENT BLOWER LOW SPEED RESISTOR OVERHEATED AND CAUSED SMOKE ODOR IN CABIN. NO FIRE OR SMOKE WAS CREATED.SDR GLBA201005122Switch · deterioratedPILOTS REPORTED THAT THE RIGHT AUTOFEATHER CYCLED DURING LANDING. MAINTENANCE REMOVED AND REPLACED THE LEFT PRESSURE SWITCH. THE OPERATIONAL CHECK WAS GOOD IAW BMM 61-21-01. P/N ON AND OFF 50-389121-47. S/N OFF 0112.SDR GLBA201005121Switch · malfunctionedPILOTS REPORTED THAT THE AUTOFEATHER SEQUENCE CYCLED MULTIPLE TIMES DURING LANDING FLARE. MAINTENANCE ADJUSTED THE RIGHT AUTOFEATHER ARMING SWITCH IN THE PEDESTAL IAW BMM 61-21-02. OPERATIONAL CHECK WAS GOOD.SDR CA100212003Skin · corroded(CAN) UPON FUSELAGE BELLY PROTECTIVE TAPE INSP, FOUND LOWER FUSELAGE SKIN CORRODED (THROUGH CABIN AFTER REMOVAL OF FLAKING MATERIAL) AT BS 290 LBL 19 TO 24. (TC 20100212003)SDR 2010FA0000135Line · chafedMAIN FUEL LINE WAS REMOVED TO FACILITATE REPLACEMENT OF THE LT WING INBD WHEEL WELL KEEL. THE LINE WAS CHAFED APPROX HALF WAY THRU WHERE IT PASSES THRU THE KEEL. THIS AREA IS VERY DIFFICULT TO INSPECT AS IT IS ABOVE AND BEHIND THE MLG. THE RT WING MAIN FUEL LSDR CA100203010Structure · debonded(CAN) AFTER THE DAYS FLIGHT, THE PILOTS NOTICED THE MAIN CABIN PASSENGER DOOR STRUCTURE WAS SEPARATED AT THE HINGE ATTACH AREA. SEVERE CORROSION FOUND BY MX. THE HONEYCOMB INNER DOOR STRUCTURE WAS SEVERELY CORRODED. SOME RIVETS ATTACHING THE BONDED ASSY TO THSDR CA100126003Skin · cracked(CAN) THERE WAS HAIRLINE CRACK ON THE UNDERSIDE OF THE SKIN OF THE LT AILERON. THE SKIN WAS ALSO SLIGHTLY WRINKLED, SO THERE WAS AN INSPECTION DONE ON THE AILERON SPAR AND A CRACK WAS FOUND IN THE ACTUAL SPAR.SDR CA100125008Line · chafed(CAN) THERE WAS A FUEL LINE ON BOTH SIDES OF THE AIRPLANE THAT WAS FOUND TO BE SEVERELY CHAFED. THIS FUEL LINE IS LOCATED AT THE BACK OF THE MLG WHEEL WELL. THE LINE ON BOTH SIDES (LT & RT) WERE REPLACED. THIS LINE WAS DISCOVERED DURING A REPLACEMENT OF THE ISDR CA100122009Shaft · worn(CAN) STARTER GENERATOR WAS FOUND TO HAVE FAILED. DISCOVERED DURING ENGINE START-UP, ENGINE FAILED TO ROTATE FOR START. UPON REMOVAL AND STARTER DISSASSEMBLY IT WAS DISCOVERED THAT THE ARMATURE SHAFT END, THAT RIDES IN THE BRG, WAS WORN TO THE POINT THAT IT HASDR CA091215004Drive Shaft · sheared(CAN) RT OB FLAP WOULD NOT MOVE WHEN SELECTED. MAINTENANCE DISCOVERED THE RT OB FLEXIBLE FLAP DRIVE SHAFT SEVERLY CORRODED AND SHEARED OF. THIS IS THE SECOND INSTANCE OF FLAP FLEXIBLE DRIVE SHAFTS SEVERLY CORRODED CAUSING FAILURE.SDR CA091217006Firewall · damaged(CAN) FIREWALL WEB P/N 114-980025-87 WORN THROUGH AT THREE LOCATIONS, PRESUMABLY FROM ENGINE HOSES WEARING ON IT. (TC NR 20091217006)SDR FFSA200900004Terminal · meltedSHORTLY AFTER TAKEOFF, SMOKE WAS OBSERVED COMING OUT OF F/OS GLARE SHIELD. ACFT RETURNED FOR LANDING. FOUND TERMINAL BLOCK AND RING TERMINAL INSULATION FOR CO-PILOT WINDSHIELD LOW HEAT PWR LEAD MELTED AND CRACKED. THE TERMINAL APPEARED TO BE LOOSE CAUSING A HSDR CA091118013Doubler · cracked(CAN) DURING A SCHEDULED 1200 HOUR INSPECTION, A CRACK WAS FOUND ON A DOUBLER WHERE THE HORIZONTAL STAB MEETS THE VERTICAL STAB ON THE TAIL. MAINTENANCE GROUNDED THE AIRPLANE IMMEDIATELY. UPON FURTHER INVESTIGATION, IT WAS FOUND THAT THE BOLTS THAT HOLDS THESDR CA091112004Lever · worn(CAN) THE ALUMINUM INPUT LEVER ARM THAT GOES ONTO THE SHAFT FOR THE ENGINE CONTROL CAMBOX, LOCATED ON THE ENGINE, SLIPPED ON THE SHAFT CAUSING A RE-INDEXING OF THE ENGINE RIGGING, PILOTS WERE UNABLE TO REDUCE THE POWER TO IDLE. THIS IS A VERY POOR DESIGN FROMSDR CA091103010Motor · unserviceable(CAN) ELECTRIC POWERPACK MOTOR SUFFERED AN INTERNAL SHORT CAUSING THE MOTOR TO FAIL, CAUSE SEEMED TO BE FAULTY INTERNAL GROUND CONNECTION.SDR CA091020005Spar · corroded(CAN) DURING INCORPORATION OF SB 27-3928 OF WEIGHT BALANCE CLIP INSP AND REPLACEMENT, THE TECH DISCOVERED SEVERE EXFOILATION CORROSION OF THE AILERON REAR SPAR IN A AREA OF THE AILERON TRIM TAB. REAR SPAR WAS REPLACED WITH NEW.SDR CA090924009Motor · failed(CAN) ON APPROACH GEAR WAS SELECTED DOWN, HYDRAULIC POWERPACK FAILED. GEAR HAD TO BE MANUALLY EXTENDED. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. UPON INSPECTION IT WAS FOUND THAT THE ELECTRIC MOTOR THAT DRIVES THE HYDRAULIC PUMP HAD FAILED DUE TO INTERNAL SHOSDR CA090921001Purge Can · failed(CAN) AIRCRAFT WAS SMOKING UPON SHUTDOWN. PURGE CAN END WALL WAS FOUND BLOWN OUT. (TC# 20090921001)SDR CA090807006Slip Ring · damagedNR 1 PROPELLER DEICE FAULT IN FLIGHT. MX INSPECTED AND FOUND NR 1 PROPELLER SLIP RING IN POOR CONDITION. SLIP RING REPLACED.SDR CA090708002Feeder Cable · burned(CAN) BATTERY FEEDER CABLES TO LT DC PWR CONTROLLER WAS FOUND BURNED OFF AT WING DISCONNECT TERMINAL WHICH IS FOUND AT FLIGHT STA 350-380. IT LOOKS LIKE THE TERMINAL BLOCK WHICH THESE WIRES WHERE CONNECTED TO WAS DESIGNED TO ACCOMMODATE A FUSIBLE LINK, NONE WSDR CA090625007Line · cracked(CAN) PY LINE CRACKED AT FLARE FITTING AT PROP GOVENOR ATTACH POINT, ENGINE DECREASED TO IDLE.SDR CA090619002Wire Rope · broken(CAN) WHEN THE CREW MOVED THE FLAPS THE LT OTBD FLAP DID NOT MOVE. MX INSPECTED THE FLAP SYS AND DISCOVERED THE LT OTBD FLAP SHAFT WIRE ROPE WAS BROKEN AT THE FLAP ACTUATOR END.SDR CA090605002Clamp · damaged(CAN) PROPELLER RECEIVED FOR OVERHAUL. UPON VISUAL INSP, DAMAGE TO ONE OF THE BLADE CLAMPS CONSISTENT WITH LIGHTENING STRIKE WAS OBSERVED. CLAMP IS UNSERVICABLE IAW MANUAL 118F AND 202A.SDR CA090511002Tube · chafed(CAN) FUEL LINE FOUND CHAFED AND LEAKING. LINE WAS CHAFED BY STARTER GENERATOR COOLING SCAT HOSE.SDR CA090507002Actuator · intermittent(CAN) INTERMITTENT OPERATION CONCERNING ELECTRIC NOSE WHEEL STEERING ACTUATOR.SDR CA090508001Selector · unknown(CAN) GEAR DID NOT RETRACT WHEN HANDLE SELECTED UP. 3 GREEN INDICATED, NO RED LIGHT AND NO HYDR FLUID LOW ANNUNCIATOR INDICATED.SDR CA090505005Bolt · missing(CAN) DURING WHEEL REPLACEMENT A BOLT WAS FOUND TO BE MISSING FROM THE WHEEL. DAMAGE TO THE WHEEL AND BRAKE HAS SHOWN THE BOLT WAS FITTED AT ASSY AND BECAME DETACHED DUE TO A BOLT FAILURE. THE BOLT PARTS WERE NOT RECOVERED AND THE TIME OF FAILURE WAS NOT ESTABSDR CA090505010Bearing · failed(CAN) REAR BEARING FAILURE ON STARTER GENERATOR. COOLING FAN BLADES BROKE OFF AS WELL.SDR CA090422003Governor · malfunctioned(CAN) DURING ENGINE START IT WAS NOTED THAT THE RT ENGINE TORQUE WAS SLOW TO INCREASE WHEN THE PROP WAS TAKEN OUT OF FEATHER. MX COFIRMED THE SNAG AND REPLACED THE RT PROPELLOR GOVERNOR. THIS FIXED THE PROBLEM.SDR CA090507004Compressor · leaking(CAN) THE PULLEY SHAFT WAS NOTED AS LEAKING. AIR CONDITIONING COMPRESSOR REPLACED.SDR FFSA200900003Terminal · meltedSHORTLY AFTER TAKE OFF, SMOKE WAS OBSERVED COMING OUT OF FIRST OFFICER’S GLARE SHIELD. AIRCRAFT RETURNED FOR LANDING. FOUND TERMINAL BLOCK AND RING TERMINAL INSULATION FOR CO-PILOT WINDSHIELD LOW HEAT POWER LEAD MELTED AND CRACKED. THE TERMINAL APPEARED TO BESDR CA090519011Structure · corroded(CAN) DURING A YEARLY INTERNAL WING CORROSION INSP AS REQUIRED BY CHAPTER 5 REQUIREMENTS, EXTENSIVE SPAR/STRINGER/SKIN CORROSION WAS DISCOVERED IN THE INBD SECTION OF THE MAIN TANKS AND THE COLLECTOR TANKS. X-RAY INSP REVEALED UNDISCOVERED SPOTS OF CORROSION BSDR CA090312003Selector · unserviceable(CAN) THE LANDING GEAR RELAY CIRCUIT BREAKER "POPPED" IN FLIGHT, GEAR MANUALLY EXTENDED. GEAR HANDLE ASSY REPLACED WITH SERVICEABLE UNIT. NUMEROUS GEAR SWINGS CARRIED OUT. NO FAULTS FOUND. THE GEAR HANDLE SWITCH WAS TESTED BY MX. THE SWITCH WHEN SELECTED DOWSDR CA090302007Stringer · corroded(CAN) SEVERE CORROSION FOUND IN LT WING STRINGER J STN 124.588. MFG RDO CONTACTED REGARDING REPAIR PROCEDURE.SDR FFSA200900001Door Frame · crackedDURING THE THIRD 200 HOUR DETAILED INSP, A CRACK WAS DISCOVERED IN THE AIRSTAIR DOOR FRAME RUNNING HORIZONTALLY ALONG THE RIVET HOLES OF THE UPPER LINE OF RIVETS THAT HOLD THE AIRSTAIR DOOR HINGE HALF TO THE FUSELAGE. THE DOOR FRAME, P/N 114-420034-1, WAS CRASDR CA090219005Spar Cap · corroded(CAN) SEVERE CORROSION FOUND ON RT HORIZONTAL STABALIZER LOWER SPAR CAP AT STN. 90.00. MFG RDO OFFICE CONTACTED FOR REPAIR.SDR CA090210001Turbine · failedEIR PT6A 2009-014 INTERNAL ENGINE FAILURE. (TC NR 20090210001)SDR CA090112001Blades · damaged(CAN) EIR PT6A 2009-002 CT BLADE DAMAGE.SDR CA090220004Turbine Blades · erodedTHE TREND MONITORING PROGRAM STARTED TO SHOW SIGNS OF HOT SECTION DISTRESS ON THE GRAPHS. BOROSCOPE INSPECTION REVEALED SOME EROSION AND IMPACT DAMAGE ON THE CT BLADES. AN HOT SECTION INSPECTION WAS CARRIED OUT AND THE COMPONENTS REPLACED. WHEN THE CT BLADESDR CA081210011Engine · shutdown(CAN) NR 1 ENGINE SHUTDOWN CARRIED OUT AFTER TAKEOFF. HERE IS THE DEFECT ENTERED BY THE FLIGHT CREW "LT PROP RPM ONLY GOES TO 1500 RPM ON TAKEOFF AS POWER REDUCED RPM DROPS". THE INCIDENT IS UNDER INVESTIGATION.
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