Pratt & Whitney PT6T-3
Service difficulty reports · 421
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 = 'PT6T3' 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 = 'PT6T3' 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 CA100810003Crosstube · crackedREPORTED AN INCIDENT OF A CRACK/BROKEN D412-664-203 CROSSTUBE AT THE CTR SUPPORT. THE INCIDENT TOOK PLACE IMMEDIATELY FOLLOWING LANDING ON AN OIL RIG PLATFORM.SDR 2010FA0000508Packing · failedHELICOPTER EXPERIENCED AN UNCOMMANDED ACCELERATION OF THE LEFT ENGINE DURING HOVER ON MAY 5, 2010. THE ENGINE N1 SPEED IMMEDIATELY WENT TO 112% AND THE HOT SECTION TEMPERATURES REACHED 989 DEGREES. THE ACFT ROTOR SYSTEM AND LT ENGINE POWER TURBINE WHEEL WERE TSDR CA100525001Fcu · failedUNCOMMANDED POWER CHANGE FOLLOWING A MAJOR HELO INSP, WHILE PERFORMING A COMPASS HEADING CHECK IN HOVER, THE NR 1 ENGINE WENT TO 111 PERCENT N1 UNCOMMANDED. THE ACFT CLIMBED 10 FT AND WAS IMMEDIATELY BROUGHT BACK TO THE GROUND AS THE MAIN ROTOR SPEED KEPT CLSDR CA100430007Quill · cracked(CAN) TRANSMISSION TAIL ROTOR DRIVE QUILL CORK FOUND LEAKING OIL DURING 600 HOUR INSPECTION AND REPACK OF OUTPUT FLEX COUPLING. DRIVE QUILL REMOVED AND BEARING RETAINER FOUND CRACKED COMPLETELY ACROSS.SDR ALGA3810AL122398Impeller · crackedBLOWER ASSY. REMOVED FROM ACFT DUE TO A CRACKED IMPELLER. IMPELLER WAS CRACKED COMPLETELY THROUGH ON 3 SIDES OF THE MOUNTING BOSS.SDR 2010FA0000164Blade · detachedDURING GROUND RUN FOLLOWING COMPLETION OF ANNUAL INSP AND CHECK OF GENERATOR BEING INOPERATIVE. A VIB. WAS NOTED WITH THE ENGINE SHUTDOWN. INSP OF THE ACFT SHOWED A HOLE IN THE AFT COWLING TO THE RT SIDE OF THE OIL COOLER. THE DAMAGE CONTINUED THROUGH 2 BULSDR CA091211006Support · cracked(CAN) DURING A 300 HRS SCHEDULE INSP, 4 CRACKS WERE FOUND AROUND SCREW HOLES OF SUPPORT 205-032-817-019 IN THE TOOLBOOM LOWER AREA.SDR CA091211007Support · cracked(CAN) DURING 300 HRS SCHEDULE INSP, A CRACK WAS FOUND IN THE LOWER SECTION OF THE TAILBOOM. AFTER REMOVAL OF THE DEFECTIVE PART THE FORMER LOWER 212-030-124-017 AND THE SUPPORT 212-030-124-037 WERE CRACKED.SDR CA091222003Line · detached(CAN) WHILE PERFORMING A MAX NG CHECK, THE NR 1 POWER SECTION FLAMED OUT. THE FLAMEOUT WAS CAUSED BY FUEL STARVATION RESULTING FROM A FUEL LINE COMING LOOSE FROM THE AUTOMATIC FUEL CONTROL UNIT. MANUFACTURER WILL INVESTIGATE TO ESTABLISH ROOT CAUSE AND SUPPLSDR CA100114007Retainer · misinstalled(CAN) PART INSTALLED BACKWARDS, ALLOWING THE FUEL LINE BETWEEN THE AFCU AND MFCU TO BECOME DISCONNECTED. RESULTING IN ENGINE FLAME OUT. ALTHOUGH NOT A CONTRIBTING FACTOR AT THIS TIME, THE RETAINER IS ILLUSTRATED BACKWARDS IN THE IPC AND MM.SDR CA091109006Barrel · cracked(CAN) 2 CRACKS IN BARREL GRIP AREA, COURSE THREAD END, RUNNING LONGITUDLINALY, ONE 1/4 INCH, ONE 1/2 INCH LONG.SDR CA090917002Blade · cracked(CAN) ONE EA. BLADE ON OIL COOLER BLOWERS S/N`S 5100-662 AND 5100-655 FOUND CRACK AT WELD AREA. CONDITION FOUND DURING PREFLIGHT INSPECTION. SEE ATTACHED PICTURES FOR CLARITY. (TC# 20090917002)SDR CA090914002Washer · cracked(CAN) DURING A 600HRS INSPECTION, ONE OF THE WASHER P/N 204-030-913-005 WAS FOUND CRACKED. THE CRACK IS COMING INWARD FROM THE OUTTER CIRCONFERENCE OF THE WASHER. THIS IS THE THIRD TIME THAT THIS WASHER IS BEING REPLACED OVER A PERIOD OF JUST OVER A YEAR, THE SDR CA090730008Line · crackedFOREST FIRE FIGHTING CREW NOTICED HYD FLUID LEAKING AS HELICOPTER LANDED TO HOOK UP WATER BUCKET CABLE TO CARGO HOOK. HELICOPTER WAS SHUTDOWN AND PILOT FOUND CRACKED LINE IN NR 1 HYD SYS. SUSPECT OVERTIGHTENING OF NUT AND VIBRATION AS PROBABLE CAUSE OF CRACKSDR U0GA2009072582699Engine · failedDURING TRAINING FLIGHT, NR 1 ENGINE QUIT. DEPARTED A CONFINED AREA WITH A SIMULATED ENGINE FAILURE OF THE NR 2 ENGINE. THE SIMULATED NR 2 ENGINE FAILURE WAS INDUCED BY THE INSTRUCTOR WITH PLENTY OF OBSTACLE CLEARANCE PAST VTOCS, ACCELERATING TO VY . ALSO THE NSDR U0GA125467Engine · stoppedDURING A NEW HIRE INITIAL TRAINING FLIGHT, NR 1 ENGINE QUIT. DEPARTED A CONFINED AREA WITH A SIMULATED ENGINE FAILURE OF THE NR 2 ENGINE. THE SIMULATED NR 2 ENGINE FAILURE WAS INDUCED BY THE INSTRUCTOR WITH PLENTY OF OBSTACLE CLEARANCE PAS VTOCS, ACCELERATINSDR CA090727009Plate · improper part(CAN) RETAINER PLATE IS NOT AUTHORIZED FOR INSTALLATION IN A 212 HANGER ASSY, -005 IS REQUIRED. COUPLING INNER SPLINES WORN DUE TO LOSS OF CLAMP UP FORCE.SDR CA090909003Skin · crackedSKIN PN 212-030-099-066 CRACKED AT FWD FAIRING ATTACH ANCHOR NUT.SDR CA090702010Bearing · spalledFOUND FLECKS OF METAL ON CTR CHIP PLUG.SDR CA090408010Turbine · failed(CAN) SHORTLY AFTER T/O, THE NR 1 ENGINE CHIP LIGHT ILLUMINATED, ACCOMPANIED BY RISING TEMPERATURE IN EXCESS OF 810°C. THE PILOT SHUT THE POWER SECTION DOWN AND LANDED WITHOUT FURTHER INCIDENT. MX DETERMINED THAT THE DISTRESS ORIGINATED IN THE POWER SECTION OFSDR CA090324006Blade · debonded(CAN) DURING A DAILY INSP, THE ENGINEER NOTICED CRACKS IN THE BONDING SUROUNDING THE EFFECTED TAIL ROTOR TIP CAP. FURTHER INVESTIGATION REVEALED DELAMINTAION OF THE SKIN TO THE TIP CAP ON BOTH SIDES OF THE BLADE. NO ABNORMAL VIBRATIONS WERE REPORTED FOLLOWING SDR CA090304011Gearbox · cracked(CAN) PILOT REPORTED OIL PRESSURE FLUCTUATIONS ON THE NR 1 ENGINE DURING FLIGHT. PILOT SHUTDOWN ENGINE AND CARRIED OUT A SINGLE ENGINE PRECAUTIONARY LANDING. POST FLIGHT INSP REVEALED A CRACK ON THE AGB HSG AND OIL LOSS ON THE NR1 ENGINE. ENGINE IS BEING REPLASDR ULXR2009021080903Tube · wornTHIS TUBE WAS WORN AROUND THE CIRCUMFERENCE AT THE POINT WHERE IT PASSES THROUGH THE FIREWALL BOOT. DISCOVERED DURING A 300 HOUR INSP AND REPLACED.SDR ULXR2009021080901Tube · wornTHIS TUBE WAS WORN AROUND THE CIRCUMFERENCE AT THE POINT WHERE IT PASSES THROUGH THE FIREWALL BOOT. DISCOVERED DURING A 300 HOUR INSP AND REPLACED.SDR ULXR2009021080900Tube · wornTHIS TUBE WAS WORN AROUND THE CIRCUMFERENCE AT THE POINT WHERE IT PASSES THROUGH THE FIREWALL BOOT. DISCOVERED DURING A 300 HOUR INSP AND REPLACED.SDR ULXR2009021080902Throttle Control · wornTHIS TUBE WAS WORN AROUND THE CIRCUMFERENCE AT THE POINT WHERE IT PASSES THROUGH THE FIREWALL BOOT. DISCOVERED DURING A 300 HOUR INSPECTION AND REPLACED.SDR CA081217015Housing · cracked(CAN) DURING CRUISE, OIL PRESSURE WAS LOST ON THE COMBINING GEARBOX AND THE PILOT PERFORMED AN UNSCHEDULED LANDING OFF BASE. THE HELO HAD TO BE TRANSPORTED BACK ON A TRUCK. INSPECTION OF THE ENGINE REVEALED A CRACK IN THE GEARBOX HOUSING FROM WHICH THE OIL ESDR CA080924002Support · cracked(CAN) CRACKS FOUND IN SUPPORT CASTING NEAR UPPER ATTACHMENT TO AIRFRAME.SDR CA080924003Support · cracked(CAN) CRACKS FOUND IN SUPPORT CASTING NEAR UPPER ATTACHMENT TO AIRFRAME.SDR CA080924004Support · cracked(CAN) TAIL ROTOR SERVO SUPPORT FOUND CRACKED NEAR UPPER ATTACHMENT FLANGES.SDR CA080710001Window · missing(CAN) WHILE THE ACFT WAS IN A DIVE, IN ORDER TO REACH VNE FOR RADS READING, AFT RT PASSENGER DOOR WINDOW WAS LOST IN FLIGHT AT 138 KNOTS.SDR CA080728010Pilot Valve · chattering(CAN) ACFT ENCOUNTERED VIBRATION, FELT THROUGH FLIGHT CONTROLS. VIBRATION WORSENED RAPIDLY DURING RETURN TO BASE. UPON ARRIVAL TO BASE, ENGINEER INSPECTED ACFT AND FOUND LT CYCLIC SERVO PILOT VALVE TO BE CHATTERING EXCESSIVELY, CAUSING UNCOMMANDED CYCLIC INPUTSDR CA080618002Seat Frame · interference(CAN) DURING THE INSTALLATION OF VERTICAL REFERENCE SEAT KIT, IAW STC SH06-31, IT WAS DISCOVERED THAT THE CYCLIC FLIGHT CONTROL STICK IS INTERFERED WITH DUE TO THE SEAT NOW BEING POSITIONED FURTHER FWD AND ELEVATED BECAUSE OF THE KIT INSTALLATION. AN ELEVATIONSDR CA080515002Cyclic Control · obstructed(CAN) AFTER INSTALLATION OF THE VERTICAL REFERENCE SEAT KIT LISTED ABOVE, IT WAS DISCOVERED DURING FLIGHT CONTROL CLEARANCE CHECKS THAT THE SEAT IN VARIOUS PLACEMENTS OF IT`S RANGE OF TRAVEL INTERFERED WITH THE FULL MOVEMENT OF THE CYCLIC FLIGHT CONTROL. INCLUSDR CA080516003Gearbox · leaking(CAN) 90 DEGREES, GEARBOX STARTED LEAKING AFTER 7.8 HOURS OF FLIGHT. UPON LANDING (TOTAL FLIGHT TIME OF 24.1 HOURS ON THE HOURMETER),THE OIL LEVEL WAS CHECKED IN THE 90 DEGREE AND FOUND TO BE EMPTY, WITH OIL SPLASHED ALL OVER THE GEARBOX. THE GEARBOX WAS FILLESDR CA080409006Blades · failedON APPROACH, THE CREW NOTED ENGINE TEMP AT APPROX 900 DEGREES FOLLOWED BY SOME NOISES. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED. INITIAL INVESTIGATION REVEALED LOSS OF COMPRESSOR TURBINE BLADE MATERIAL AND SHROUD SEGMENT MATERIAL, THE ENGINE WAS SENT SDR CA080116015Turbine Blades · fractured(CAN) DURING HOVER THE CREW NOTED VIBRATION FOLLOWED BY CHIP DETECTOR LIGHT ILLUMINATION AND LOSS OF POWER. POST FLIGHT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND ASSOCIATED DAMAGE. IT WAS REPORTED THAT THE PILOT HAD DIFFICULTY STARTING THE ENGINE SDR CA071204007Balance Weight · incorrect(CAN) INCORRECT WEIGHT FOR PN CAUSED IMBALANCE IN TAIL ROTOR WHICH COULD NOT BE CORRECTED WITHIN BALANCE LIMITS. (TC NR 20071204007)SDR CA071026003Cyclic Stick · corroded(CAN) PILOTS CYCLIC STICK DISASSEMBLED FOR PAINT AND REFURBISH. STEEL RING PN 204-001-369-001 IS RIVETED ON THE CYCLIC STICK. THE STEEL RING IS USED FOR APPLICATION OF FRICTION. THE STEEL RING WAS REMOVED AND EXTREME CORROSION PITTING WAS FOUND IN THE CYCLIC SSDR CA071016005Gearbox · making metal(CAN) THE POWER SECTION CHIP DETECTOR ACTIVATED AND THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ACCESSORY GEARBOX. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071016005)SDR CA071003027Engine · making metal(CAN) AN ENGINE CHIP DETECTOR WARNING ACTIVED AND THE POWER SECTION WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL SYSTEM. MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20071003027)SDR HEEA116677Starter Gen · burnedSMELLED BURNED ELECTRICAL ODOR IN THE COCKPIT. MAINTENANCE REPLACED NR 2 STARTER GENERATOR.SDR EGI2007F00000Transmission · making metalDURING LOCAL TRAINING TRANSMISSION CHIP LIGHT CAME ON. AC WAS LANDED WITHOUT FURTHER INCIDENT. INVESTIGATION REVEALED NONFERROUS METAL FLAKES ON THE DEBRIS MONITOR. THE OIL WAS DRAINED THROUGH A STRAINER AND NO METAL WAS FOUND IN STRAINER. THE EXTERNAL FILSDR CA070717003Bracket · broken(CAN) ON APPROACH TO THE LANDING AREA, THE (DOOR LOCK) LIGHT ON CAUTION PANEL ILLUMINATED. AIRCRAFT LANDED SAFELY WITHOUT ANY FURTHER INCIDENT. UPON LANDING THE ENGINEER EXITED THE AIRCRAFT AND PHYSICALY CHECKED ALL DOORS AND PANELS TO ENSURE THAT THEY WERE COSDR CA070914007Turbine Blades · fractured(CAN) THE ENGINE COULD NOT BE RELIGHT IN FLIGHT FOLLOWING A SIMULATED ENGINE-OUT TRAINING EXERCISE. SUBSEQUENT INSPECTION REVEALED FRACTURED TURBINE BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.SDR CA070514014Spline · worn(CAN) THE ENGINE SUFFERED AN IN-FLIGHT SHUTDOWN DUE TO FUEL STARVATION AS A RESULT OF WORN FUEL PUMP DRIVE SHAFT SPLINES. (TC NR 20070514014)SDR CA070223005Spring · broken(CAN) ENGINEER CARRYING OUT REQUIREMENTS OF CAMP CODE NR 650121 (INSPECT/LUBE T/R DRIVESHAFT FLEX COUPLING). WHEN DISASSEMBLING THE T/R QUILL OUTPUT COUPLING IN SITU ON THE M/R TRANSMISSION. UPON REMOVAL OF RETAINER AND PLATE, A SMALL SECTION OF SPRING PN 20SDR CA070314020Turbine Blades · fractured(CAN) ON LANDING FOLLOWING A TRAINING FLIGHT, THE ENGINE EMITTED A LOUD NOISE. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314020)SDR CA070228004Splice · corroded(CAN) SPLICE CORRODED,TAIL BOOM REPLACED, A/C RETURNED TO SERVICE. (TC NR 20070228004)SDR CA061106005Engine · malfunctioned(CAN) DURING GROUND RUNS FOLLOWING EXTENSIVE MAINTENANCE THE POWER SECTION ACCELERATED UNCOMMANDED. POWER WAS REDUCED TO IDE AND THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED. ON SHUT DOWN SMOKE WAS SEEN EMINATING FROM THE EXHAUST. SUBSEQUENT INSPECTION REV
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