U/A Canada PT6A-61
Service difficulty reports · 36
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 = 'PT6A61' 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 = 'PT6A61' 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 FXTA20190627001Transducer · abnormalIN CRUISE FLIGHT THE NUMBER ONE ENGINE WAS OBSERVED LOOSING OIL PRESSURE SLOWLY. OIL PRESSURE DROPPED TO RED LINE THEN BEGAN TO CLIMB BACK TO INTO THE GREEN ARC. OIL TEMP AND ALL OTHER ENGINE PARAMETERS STAYED NORMAL SO IN WAS BELIEVE THIS WAS AN INDICATION ERSDR CA140630018Warning Message · activated(CAN) DURING REVENUE FLIGHT, THE PILOT NOTICED A HIGH OIL TEMPERATURE DURING CLIMB. THEY REDUCED THE ENGINE POWER TO MAINTAIN THE OIL TEMPERATURE WITHIN LIMITS. THE CREW ELECTED TO RETURN TO HOME BASE AND LANDED UNEVENTFULLY. TROUBLESHOOTING ONGOING.SDR CA131121014Fcu · failed(CAN) ENGINE WOULD NOT ACCELERATE OFF OF IDLE GROUND POWER.SDR CA130805012Engine · fluctuates(CAN) PRIOR LANDING THE PILOT OBSERVED ENGINE PARAMETERS FLUCTUATION THEN THE ENGINE SHUTDOWN ITSELF. THIS IS A RECURRENT ISSUE. ENG REP WILL INVESTIGATE THE IFSD. AT INITIAL OCCURRENCE AN FCU REPLACEMENT WAS CONDUCTED.SDR CA130612007Drive Shaft · worn(CAN) DURING ENGINE UPGRADE, COMPLETED AT ELLIOTT AVIATION CRS KX5R005N, IAW BLACKHAWK STC SA10737SE THE COMPRESSOR QUILL DRIVE SHAFT WAS NOT REPLACED BY SHAFT PN 117-910058-5 AS DETAILED IN BLACKHAWK DWG 06010001 REV B AND SB21-3303 R1. THE SHORTER -3 SHAFT ESDR CA130212017Engine · malfunctioned(CAN) DURING THE DESCENT AT 20K FT, THE PILOT REPORTED A HIGH FUEL FLOW AND TORQUE FLUCTUATIONS. THEY FLEW TO A LOWER ALTITUDE TO ELIMINATE A POSSIBLE ICING CONDITION WITHOUT CHANGE. THEY DIVERTED THE FLIGHT WHERE A UNEVENTFUL LANDING WAS PERFORMED. DURING SDR CA130128002Engine · making metal(CAN) PILOT GOT A CHIP DETECT ALARM ON ON THE NR 2 ENGINE. CREW APPLIED IMMEDIATELY AN ENGINE SHUT OFF PROCEDURE AND TERMINATED FLIGHT OEI AT CAEN WHICH IS LOCATED AT CHALAIR AVIATION MAINTENANCE SHOP WHERE THE PLANE IS MAINTAINED. AFTER LANDING ON GROUND INVESDR CA120903004Turbine Blades · fractured(CAN) SHORTLY AFTER T/O, A LOUD NOISE WAS HEARD AND ENGINE TORQUE DROPPED TO ZERO ACCOMPANIED WITH FLAMES COMING OUT OF THE EXHAUST. THE ENGINE WAS SECURED AND THE CREW RETURNED TO THE DEPARTURE POINT WHERE AN UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHEDSDR CA120918013Oil System · leaking(CAN) PILOT INITIATED IFSD OF RIGHT ENGINE AND DIVERSION TO NEWCASTLE DUE AN OIL PRESSURE LOSS COMBINED WITH SMOKE IN THE CABIN. AN UNEVENTFUL SINGLE ENGINE LANDING WAS MADE. POST FLIGHT INSPECTION FOUND AN OIL LEAK FROM THE INLET. TROUBLESHOOTING ON GOING.SDR CA110606004Drain · blockedDURING CRUISE AT FL210, CREW NOTICED OIL PRESSURE AND TORQUE FLUCTUATIONS WITH SMOKE COMING FROM THE EXHAUST STACK. THE ENGINE WAS SHUTDOWN AND AN UNEVENTFUL SINGLE ENGINE LANDING WAS ACCOMPLISHED AT THE POINT OF DEPARTURE. POST-FLIGHT INSPECTION REVEALED A SDR CA070605005Attach Bolt · bent(CAN) CONTINUOUS PROBLEM OF PREMATURE WEAR AND INDICATIONS OF STRESS ON MAIN LANDING GEAR ACTUATOR ATTACH HARDWARE. LOWER FORK BOLT PN 41789-02 AND UPPER ACTUATOR ATTACH BOLT 401-195 (AN5-17A) (BOTH LIFE LIMITED BY MFG INSPECTION PROGRAM) SHOW SIGNS OF BENDINSDR CA080128003Filter · cracked(CAN) DURING APPROACH TO LANDING, FLIGHT CREW EXPERIENCED DIFFICULTY EXTENDING THE LANDING GEAR VIA NORMAL MEANS AND SUBSEQUENTLY MANUALLY LOWERED THE GEAR. INVESTIGATION SHOWED SUBSTANTIAL HYD FLUID LOSS THROUGH CRACKED THREADS OF THE LT ENG HYDR FILTER BOWL.SDR RX8R2006003Structure · crackedFOUND CRACK IN LT NOSE LANDING GEAR DOOR ON RADIUS OF FRONT STIFFENER SECTION. ALSO FOUND CRACK IN RT NOSE LANDING GEAR DOOR AT FORWARD HINGE ATTACH POINT. HAVE PREVIOUSLY FOUND CRACKS IN THE NOSE LANDING GEAR DOORS ON 4 OTHER PA-42'S. THE CRACKS ARE USUALLY ISDR CA060427005Wire · corroded(CAN) DURING CLIMB FLIGHT CREW SMELLED AND VISUALLY CONFIRMED SMOKE IN COCKPIT. THEY SHUTOFF WINDSHIELD HEAT AND PITOT/STALL HEAT AND SMOKE DISSIPATED. FLIGHT RETURNED TO POINT OF DEPARTURE FOR INVESTIGATION. MAINTENANCE FOUND SURFACE CORROSION ON PITOT/STALL SDR RX8R2006001Hydraulic Line · damagedAFTER TAKEOFF THE LANDING GEAR HANDLE WAS MOVED TO THE UP POSITION THE LANDING GEAR CAME UP BUT THE GEAR DOORS DID NOT CLOSE. THE LANDING GEAR HANDLE WAS PUT IN THE DOWN POSITION BUT THE LANDING GEAR DID NOT LOCK DOWN. THE EMERGENCY HAND PUMP WAS USED TO MAKE SDR CA060411002Brake · failedLEFT SIDE BRAKE FAILED ON LANDING CAUSING RIGHT MAIN TIRE TO BLOW OUT. NO DAMAGE TO A/C.SDR CA051223010Csu · leakingDURING CRUISE, THE ENGINE LOST OIL PRESSURE AND WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A LEAK AT THE CSU PITCH LOCK SOLENOID.SDR CA051130005Engine · failed(CAN) NR1 ENGINE THE AUTO FEATHER SYSTEM WAS ARMED FOR TAKEOFF. SHORTLY AFTER TAKEOFF THE PILOT DISARMED THAT AUTO FEATHER SYSTEM. THE AIRCRAFT CONTINUED TO CLIMB OUT. THE PILOT NOTICED PROPELLER RPM SLOWLY DROPPING OFF (SUCH AS PROPELLERS OUT OF SYNC). THE PSDR CA060405007Outflow Valve · malfunctionedDURING AN EVENT, NR 2 INSPECTION OF THE EMERGENCY PRESSURIZATION SYSTEM, VALVE ASSY (BY-PASS) P/N 73318-00-1) WAS REMOVED FROM RT WING ROOT AREA, FURTHER INSPECTION FOUND EXTENSIVE CORROSION IN THIS VALVE AND REDUCER P/N: 584-124 (A55-16-12). SYSTEM CLEANED. SDR CA051108005Fitting · crackedPART NUMBER 43286-02 (2 OF) WERE REMOVED FROM STOCK FOR INSTALLATION ON PA42-720 AS REQUIRED BY A/C MX SCHEDULE REPLACEMENT INTERVAL. CLOSE INSPECTION PRIOR TO INSTALLATION REVEALED BOTH FITTINGS (PART NUMBER 40286-00) WERE CRACKED WHERE THEY MATE WITH THE PISDR RX8R2004002Strut · crackedRIGHT MAIN LANDING GEAR STRUT CRACKED AT ATTACH POINT TO ACTUATING BRACE. CRACK IS 2.5 INCHES LONG ALONG AFT SIDE OF AFT ATTACH POINT LUG. CRACK IS AT SAME LOCATION THAT GETS INSPECTED IAW PIPER SERVICE BULLETIN 969. AREA WAS INSPECTED PER SB 65.2 HRS. AGO,SDR GW12004F00003Line · fracturedPILOT REPORTED FUEL DRIPPING OUT OF COWLING ON SHUT DOWN. REMOVAL OF COWLING AND GROUND RUN OF ENGINE REVEALED FRACTURE OF HIGH PRESSURE FCU TO FUEL NOZZLE DELIVERY TUBE. TUBE WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE.SDR CA040621003Fire Detector · shortedDURING APPROACH FOR LANDING, THE RT ENGINE FIRE WARNING ANNUNCIATOR ACTIVATED. THE PILOT DEPLOYED THE ENGINE FIRE BOTTLE, SECURED THE ENGINE AND DECLARED AN EMERGENCY. THE LANDING CONTINUED UNEVENTFUL. MX INSPECTED THE ENGINE AND FOUND NO EVIDENCE OF FIRE. THESDR RX8R2004001Bolt · shearedWHILE TAXIING AFTER LANDING, THE PILOT DISCOVERED THE AIRCRAFT WOULD NOT TURN TIGHT. AFTER EXAMINATION, IT WAS FOUND THE (3) AN-3 BOLTS THAT SECURE THE NOSE STEERING LINKAGE TO THE TOP OF THE NOSE LANDING GEAR STRUT HAD SHEARED. FOUR OTHER AIRCRAFT WERE EXAMSDR CA040427016Master Switch · worn(CAN) NEARING FINAL APPROACH THE PILOT NOTICED HE HAD LOST PRIMARY AVIONICS POWER AND THE STANDBY POWER SUPPLY HAD ENGAGED TO PROVIDE BASIC POWER. AN UNEVENTFUL LANDING WAS CARRIED OUT. MAINTENANCE DETERMINED THE AVIONICS MASTER SWITCH (PUSH TO ENGAGE, PUSH AGSDR CA011121008Bolt · broken(CAN) FLT CREW WERE UNABLE TO EXTEND LT MLG THROUGH NORMAL (HYDRAULIC) OR EMERG (HYDRAULIC/PNEUMATIC) MEANS PRIOR TO LDG. LOSS OF HYDRAULIC FLUID EVIDENT AROUND TRAILING EDGE OF LT WING & FLAP AREAS. NOSE & RT MLG WERE RETRACTED & A/C MADE SUCCESSFUL GEAR UP LSDR CA011121009Wire Harness · disconnected(CAN) PILOT ACTIVATED LDG GEAR EMERG BLOWDOWN PNEUMATIC SYS SWITCH DURING LDG GEAR EXTENSION MFLFUNCTION. LATER GROUND INSP DETERMINED THAT PENUMATIC SYS (LT MLG) HAD NOT PROPERLY ACTIVATED. SYS SHOULD HAVE FIRED T HE NITROGEN BOTTLE EXPLOSIVE SQUIB (ON LDG GESDR RX8R2001001Skin · debondedAFTER LANDING IT WAS NOTICED THAT THE RIGHT INBOARD LANDING GEAR DOOR SKIN HAD PEELED OFF FROM THE REST OF THE DOOR AT THE LEADING EDGE. UPON FURTHER EXAMINATION THE DOOR SKIN AND SUPPORTING STRUCTURE WHICH ARE BONDED TOGETHER WITH STRUCTURAL ADHESIVE SHOWED CSDR CA001206003Wheel · cracked(CAN) SCHEDULED MAINTENANCE INSPECTION DISCOVERED CRACKED WHEEL HALF DURING TIRE REPLACEMENT. CRACK IS IN OUTER WHEEL HALF AND ORIGINATES FROM A LARGE LIGHTENING HOLE. CRACK APPROXIMATELY .250 INCH IN LENGTH. WHEEL HALF SCRAPPED. (X)SDR CA000906005Chip Detector · broken(CAN) DURING CLIMB, PILOT NOTICED SMOKE FROM LEFT ENGINE. SUSPECTING FIRE, ENGINE WAS SHUTDOWN AND SECURED AND FIRE BOTTTLE ACTIVATED. UNEVENTFUL LANDING C/O SASKATOON. MAINTENANCE DISCOVERED BROKEN CHIP DETECTOR ALLOWING ENGINE OIL TO LEAK ONTO ENGINE CASESDR CA000621020Switch · failed(CAN) PILOT EXPERIENCED RIGHT ENGINE FIRE WARNING AND MASTER CAUTION ANNUCIATORS. ENGINE WAS SHUTDOWN BY CHECKLIST AND RE FIRE BOTTLE DISCHARGE SWITCH ACTIVATED. LANDING C/O UNEVENTFUL. MAINTENANCE DETERMINED ENGINE FIRE WARNING WAS FALSE AND THAT THE FIRE BOTSDR AU000128027Rod End · seized(AU) ENGINE FAILED TO PRODUCE FULL POWER. INSPECTION FOUND PROP GOVERNOR RESET ARM POSITIONED AFT OF STOP ALLOWING PY AIR LEAK AND RESULTANT REDUCED NG AND WF. SEIZED BEARING.SDR CA000128027Rod End · seized(CAN) ENGINE FAILED TO PRODUCE FULL POWER. INSPECTION FOUND PROP GOVERNOR RESETA RM POSITIONED AFT OF STOP ALLOWING PY AIR LEAK AND RESULTANT REDUCED NG ANDWF. SEIZED BEARING.SDR CA990430023Engine · failed(CAN) NR 2 ENGINE WOULD NOT START. INVESTIGATION DETERMINED THE COMPRESSOR SECTION WOULD NOT ROTATE. ENGINE REMOVED FOR OVERHAUL, FURTHER REPORT TO FOLLOW.SDR CA981207007Circuit Breaker · overheated(CAN) DURING GROUND RUN, A HOT ODOR WAS DETECTED. INVESTIGATION FOUND THE SOURCE TO BE THE RIGHT GENERATOR BUS TIE CIRCUIT BREAKER IN THE LOWER CENTER PEDESTAL. THE BOLT CONNECTING THE BREAKER TO THE BUS WAS NOT TIGHT AND THE PHENOLIC BLOCK WAS GETTING HOT.SDR 97ZZZX592Chip Detector · brokenIN-FLIGHT, PILOT NOTICED TORQUE FLUCTUATION AND LOSS OF OIL PRESSURE. LANDED WITHOUT INCIDENT. RT ENGINE AND COWLING COVERED WITH OIL. INSPECTED ENGINE AND FOUND CHIP DETECTOR BROKEN CAUSING ALL ENG OIL TO DRAIN FROM POWER SECTION.
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