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 HSYA2012072512Landing Gear · malfunctionedPILOT REPORTED THAT AFTER TAKEOFF AND UPON RETRACTION OF THE LANDING GEAR, THE RT NOSE GEAR INDICATED UP AND LOCKED AND THE LT MAIN GEAR INDICATED DOWN AND LOCKED. PILOT ELECTED TO RETURN TO DEPARTURE. GEAR WAS SELECTED DOWN AND 3 DOWN AND LOCKED LIGHTS ILLUMSDR CA120717003Fuel Control · fluctuates(CAN) DURING REPOSITIONING FLIGHT, WHILE IN CRUISE, CREW NOTICED NR 2 ENGINE TORQUE FLUCTUATION. JUST PRIOR TO DESCENT, NR 2 PARAMETER DROPPED TO IDLE. THE POWER SECTION FLAMED OUT AS THE PILOT CLOSED THROTTLE TO IDLE. ACFT DIVERTED AND LANDED WITHOUT INCIDESDR CA120619005Engine · flamed out(CAN) DURING A TRAINING FLIGHT WHILE SIMULATING AN ENGINE OUT & DURING FINAL APPROACH, THE OTHER ENGINE FLAMED OUT. AN UNEVENTFUL LANDING FOLLOWED. TROUBLESHOOTING IS ONGOING.SDR CA120612009Magnetic Brake · no test(CAN) AS PART OF A DAILY MAINTENANCE INSPECTION THE FORCE TRIM RELEASE OF THE YAW MAGNETIC BRAKE ASSY WAS TESTED. THE MECHANIC WAS ABLE TO DETECT THAT THE BRAKE ASSY WAS NOT RELEASING ON APPLICATION OF THE FORCE TRIM SWITCH. THE UNIT WAS REMOVED AND A SERVICESDR CA120608011Connector · disconnected(CAN) WHILE IN CONFINED SPACE, FORCE TRIM OFF, PILOT FELT PEDALS BIND AND COULD NOT INPUT MORE TAIL ROTOR CONTROL. IT THEN BROKE LOOSE AND NORMAL FEEL WAS ESTABLISHED. MAINTENANCE WAS ABLE TO DUPLICATE THE SNAG IN THE HANGER. MAGNETIC BRAKE FOR THE TAIL CONTSDR CA120530002Hook · failed(CAN) HELICOPTER WAS CARRYING A LOAD ON A 130 FOOT LONG LINE FROM ONE STAGING AREA TO ANOTHER STAGING AREA. THE LOAD 1800 LBS AND LONG LINE CAME ACCIDENTLY OUT OF THE BELLY HOOK ABOUT 1.5 MILES FROM STAGING. THERE WAS NO TURBULENCE ENCOUNTERED THE ENTIRE FLIGSDR CA120430012Seal · cracked(CAN) CARRYING OUT INSPECTION OF MAIN TRANSMISSION OIL LEVEL, IT WAS DISCOVERED THAT THE QTY WAS LOW. A GROUND RUN AND LEAK CHECK WAS PERFORMED AND FOUND THAT THE NR 1 HYDRAULIC PUMP QUILL SHAFT SEALS WERE THE SOURCE. UPON REMOVAL OF THE PUMP IT WAS DISCOVERSDR ALGA2012032100002Bearing · wornMAIN ROTOR DRIVE LINK BEARING WORN BEYOND LIMITS.SDR CA120213007Trim Switch · intermittent(CAN) PILOT REPORTED, ATT MODE-ERRATIC PITCH. DISCUSSION WITH THE PILOT REVEALED THAT THE PROBLEM OCCURED IN THE DECENT AND IN ATT MODE. THE PILOT STATED THAT HE ELECTED NOT TO USE THE VERTICAL MODE AND REPORTED THE FAULT UPON LANDING. THE CO-PILOT CYCLIC SSDR ALGA2012011600712Mast · corrodedMAST HAS PITTING CORROSION ON UPPER SPLINES BEYOND REPAIRABLE LIMITS.SDR ALGA2012011631712Plate · corrodedPLATE HAS PITTING CORROSION BEYOND REPAIRABLE LIMITS.SDR ALGA2012011301712Panel · corrodedFORWARD EDGE OF PANEL CORRODED BEYOND REPAIRABLE LIMITS.SDR CA111214006Servo · defective(CAN) SERVO RECEIVED ZERO TIME SINCE OVERHAUL. CUSTOMER REPORTED LOWER CYLINDER ASSEMBLY LOCKS HYD WILL NOT EXTEND. SUSPECT IMPROPER BYPASS SERVO TIMING. SERVO FUNCTIONALLY TESTED PRIOR TO DISASSEMBLY. THE SERVO LOWER PISTON MOVED TO THE EXTEND POSITION BUSDR CA111201003Engine · power loss(CAN) DURING A POST MAINTENANCE TEST FLIGHT THE HELICOPTER WAS ON APPROACH TO LAND WHEN THE ROTOR BEGAN TO DROOP. THE PILOT MADE AN EMERGENCY LANDING.SDR CA111123011Tube · cracked(CAN) P3 FILTER AIR TUBE CRACKED AT THE P3 FILTER.SDR CA111130009Transducer · failed(CAN) PILOT REPORTED PEDAL FEEDBACK DURING FLIGHT. FEEDBACK DISAPPEARED BELOW 40 KTS. MAINTENANCE REPORTED, TAIL ROTOR SCAS TUBE P/N 7018078 & NO. 1 YAW CMT P/N 412-074-101-103 REPLACED. DETAILS OF MAINTENANCE CARRIED OUT ONADDITIONAL TASK SHEETS (3). AIRCRAFSDR CA111026006Bearing · delaminated(CAN) BEARING FOUND DELAMINATED DURING DAILY INSPECTION.SDR CA111011007Turbine Blades · failed(CAN) DURING FLIGHT, THE CREW RECEIVED AN "ENGINE OUT" WARNING FOLLOWED BY A FIRE WARNING. THE FIRE BOTTLE WAS DISCHARGED AND AN EMERGENCY LANDING WAS MADE SAFELY ON A ROAD. POST FLIGHT INSP FOUND FRACTURED POWER TURBINE BLADES AND THE COMPRESSOR ROTOR HARD SDR CA110929007Engine · failed(CAN) DURING TEST FLIGHT, AFTER INSTALLATION OF THE FRESHLY O/H P/S, DURING AN AUTO-ROTATION MANEUVER, THE PILOT HEARD A LOUD NOISE AND RECEIVED A CHIP DETECTOR WARNING. HE WAS ABLE TO SAFELY LAND THE ACFT. POST FLIGHT INSPECTION FOUND THE P/S GAS GENERATORSDR CA110921007Line · broken(CAN) LINE SEPARATED FROM P3 FILTER HSG. UNDER HEAVY POWER CHANGE ENGINE TORQUE WOULD SPLIT FROM OTHER POWER SECTION. DEFECT FOUND DURING LEAK CHECK OF P3 AIR SYS.SDR CA111014001Bearing · delaminated(CAN) BEARING FOUND DELAMINATED AROUND FULL CIRCUMFERENCE OF BEARING ASSY.SDR CA110815017Control Tube · damaged(CAN) THIS CONTROL TUBE WAS REMOVED FROM THE AIRCRAFT AND AN INSPECTION WAS BEING CONDUCTED IN ACCORDANCE WITH B 212 MM CHAPTER 67 AND B 212 CR&O CHPATER 67. THE NYLATRON WEAR SLEEVES WERE REMOVED AND A RADIAL CRACK WAS REVEALED UNDER THE END SLEEVE. THE TUBE SDR CA110722005Bleed Valve · stuckON APPROACH, THE CREW NOTICED THAT THEY HAD ZERO TORQUE INDICATION AND HIGH ITT ON ENGINE NR1. THE CREW SHUTDOWN THE NR 1 ENGINE AND LANDED WITHOUT FURTHER INCIDENT. THE ENGINEER TROUBLESHOOTING THE FAULT, NOTED THAT THE BLEED VALVE WAS STUCK IN THE CLOSED POSDR CA110803012Bleed Valve · stuckDURING FINAL APPROACH, THE PILOT DECLARED EMERGENCY AFTER PERFORMING A PRECAUTIONARY SHUTDOWN OF THE ENGINE DUE TO OBSERVED HIGH TEMPERATURE. AN UNEVENTFUL SINGLE ENGINE LANDING FOLLOWED. POST FLIGHT INSP FOUND A STUCK COMPRESSOR BLEED VALVE (BOV) PISTON AS SDR 2011FA0000471Windshield · crackedHEATED WINDSHIELD WAS FOUND CRACKED WHEN ACFT LANDED.SDR CA110803004Engine · power loss(CAN) PILOT REPORTED THAT AFTER TAKEOFF, THE NR 2 ENGINE ROLLED BACK TO IDLE. PILOT SWITCHED TO MANUAL MODE AND LANDED AT AIRPORT SAFELY WITH NO DAMAGE TO HELICOPTER. POST FLIGHT INSPECTION REVEALED THE P3 LINE HAD FRACTURED. LOCAL AUTHORITIES HAVE ASKED ENGSDR CA110714005Ahrs · malfunctioned(CAN) DURING FLIGHT TEST, IN HOVER AT APPROXIMATELY 5FT ABOVE GROUND, PILOT ENCOUNTERED FLIGHT CONTROL ANOMALIES. AIRCRAFT LANDED SAFELY. INVESTIGATING ROOT CAUSE(S).SDR CA110623010Relay · failed(CAN) PILOT APPLIED POWER TO NR 2 DC BUSS AND THE NR 2 STARTER-GENERATOR ENGAGED. THIS RESULTED IN THE NR 2 ENGINE STARTING TO SPOOL UP WITH THE STARTER SWITCH STILL IN THE OFF POSITION. TROUBLESHOOTING FOUND THE NR 2 GENERATOR RELAY MAIN CONTACTS WELDED IN THSDR CA110602007Radar · intermittentPILOT REPORTED, "WX RADAR- DIM IMAGE AND GOING INTO "WAIT" MODE. THIS OCCURED DURING HEAVY RAIN. RADAR TURNED OFF RTB." AVIONCS PERSONNEL WERE ABLE TO REPRODUCE THE FAULT DURING A GROUND TEST. RADAR PEDESTAL AND SURROUNDING AREA IN THE AVIONICS BAY WAS FOUNSDR CA110527005Damper · delaminatedUPON RETURNING FROM THE FLIGHT, THE PILOT ADVISED MX OF "LATERAL VIBE IN HELICOPTER. VERY NOTICEABLE AT HIGH POWER SETTINGS." UPON INSP, MX HAD FOUND THAT THE DAMPER BEARING, LOCATED ON THE INBD SIDE OF THE SPINDLE, HAD DELAMINATED FROM THE SPINDLE. (THE SPINDSDR CA110516019Fuel Control · malfunctionedPOWER ROLLBACK DURING FLIGHT, THE ENGINE ROLLED BACK TO 80 PERCENT NG IN AUTO MODE. THE PILOT SWITCHED TO MANUAL MODE AND THE ENGINE RECOVERED. AFTER LANDING AT BASE AND TROUBLESHOOTING, SUBSEQUENT START ATTEMPTS IN AUTO MODE RESULTED IN A HUNG START AT 40 PERSDR CA110414009Sealant · damagedWHILE COMPLETING 100 HR INSP 5-22A A VOID WAS FOUND IN THE SEALANT OF THE DOUBLER AT THE ROOT END OF THE BLADE. DUE TO THE HOURS ON THE BLADE IT WAS DETERMINED THAT IT IS A MFG FLAW. VOID DEPTH .162" MAX ALLOWABLE DEPTH IS .060"SDR CA110330004Fitting · cracked(CAN) ONE INCH CRACK IN LOAD FLANGE OF FITTING.SDR CA110322003Crosstube · failed(CAN) REPORTED AN INCIDENT WHICH SUFFERED A FAILURE OF THE AFT CROSS TUBE WHILE TAKING ON PAXS AT AN OFFSHORE WELL HEAD TOWER. NO INJURIES WERE REPORTED.SDR CA080813010Line · bent(CAN) TRANSMISSION OIL COOLER SOLID LINES WERE BENT TO FIT AT DRAIN VALVE ENDS AND WERE INSTALLED OPPOSITE TO THEIR RESPECTIVE DRAIN VALVE TEES. BOTH LINES WERE REPLACED AND RE-ROUTED CORRECTLY.SDR CA110317004Blade · cracked(CAN) MAIN ROTOR BLADE, PN 212-015-501-115 WITH TTSN 2986 .4 HR WAS REMOVED FROM HELICOPTER ON OCTOBER 20 2010 & SENT INTO FACILITY IN FEBRUARY 2011. BLADE WAS SENT IN FOR INSPECTION & FULL CHORD SKIN & HONEYCOMB CORE REPAIR AT STATION 244.0 - 253.0 UPON INSPSDR CA110413002Fuel Control · malfunctioned(CAN) ABORTED T/O, AS POWER WAS APPLIED ABOVE 80 PERCENT TORQUE ON BOTH ENGINES, THE TORQUE NEEDLES BEGAN TO OSCILLATE RAPIDLY AND AN UNUSUAL VIBRATION WAS FELT THROUGHOUT THE AIRFRAME. THE T/O WAS ABORTED. POST EVENT TROUBLESHOOTING LED TO THE REPLACEMENT OSDR CA110210001Fuel Control · inoperativeUPON 1ST START OF THE DAY, NR 1 ENG WOULD NOT ACCELERATE PAST 40 PERCENT NI. PROBLEM WAS TROUBLESHOT & ALL INDICATION POINTED TO THE AFCU. A NEW UNIT WAS THEN INSTALLED & THE ACFT WAS SUCCESSFULLY STARTED. THAT PROVED THE ORIGINAL AFCU WAS THE FAULTY COMPONESDR CA110125011Engine · making metal(CAN) OIL CONTAMINATION/IFSD DURING FLIGHT, THE ENGINE CHIP LIGHT CAME ON. THE AFFECTED POWER SECTION WAS SHUT DOWN AND THE HELO LANDED SAFELY. POST FLIGHT INSPECTION FOUND METAL CONTAMINATION ON THE NO. 1 POWER SECTION SIDE. SUBSEQUENT PENALTY GROUND RUNS PESDR CA101213005Engine · power loss(CAN) POWER LOSS FIRE DEPARTMENT, PT6T-3D, S/N TH0360, TTSN 2102, TCSN 3040 DURING A CHECK FLIGHT FOLLOWING RGB 2500HRS INSPECTION, WHILE FLYING LEVEL AT 500` THE NR 2 ENGINE TORQUE DROPPED TO IDLE UNCOMMANDED. THE OTHER POWER SECTION TOOK THE FULL TORQUE WITHSDR CA110613013Indicator · misoverhauledITT INDICATOR REMOVED FOR REMARKING. UNIT DISSASEMBLED IN O/H FACILITY AND FOUND UN-APPROVED PARTS INSTALLED. UNIT REMOVED FROM SERVICE.SDR R29R2010003Damper · debonded(R29R) FOUND ONE DAMPER SET DEBONDED AND THE REMAINING 3 SETS SHOWING SIGNS OF DEBONDING. ACFT GROUNDED UNTIL REPLACEMENT DAMPERS ARE INSTALLED. SECOND DISCOVERY OF THIS PROBLEM IN THE CUSTOMERS FLEET.SDR R29R2010002Damper · debonded(R29R) FOUND 3 OUT OF 4 DAMPER HALF SETS HAD DEBONDED THE ELASTOMERS FROM THE METAL MOUNT PADS. IT APPEARS AS THOUGH THERE WAS A LACK OF ADHESIVE BETWEEN THE 2 SURFACES. THE VIBRATION LEVEL MEASURES 4.0 IPS AT THE BEGINNING OF THE TRACK AND BALANCE PROCESS. THSDR CA110214010Engine · power lossPOWER LOSS/IFSD ENGINE SHUT ITSELF DOWN WITHOUT ANY NOTICE. AN UNEVENTFUL SINGLE LANDING WAS MADE. POST EVENT INSP FOUND A LARGE TEAR IN THE GAS GENERATOR CASE. THE ENGINE WAS SENT TO MFG FOR INVESTIGATION WHERE THE CAUSE WAS IDENTIFIED A CRACKING FROM FATISDR CA100928002O-Ring · damagedFLAMEOUT DURING CRUISE, THE NR 2 ENGINE FLAMED OUT WITH NO PRIOR WARNING. AN EMERGENCY SINGLE ENGINE LANDING WAS MADE. TROUBLESHOOTING REVEALED A FUEL LEAK FROM A DAMAGED O-RING ON THE FUEL LINE BETWEEN THE AUTOMATIC FUEL CONTROL AND THE FLOW DIVIDER. THE PRSDR CA100824005Retainer · failed(CAN) DURING THE FIRST REVENUE FLT AFTER THE NR 2 ENGINE WAS CHANGED (APPROX 20 HRS PREVIOUS) THE PILOTS REPORTED THAT CHIP LIGHT FOR THE NR 2 ENG WAS FLICKERING VERY FAINTLY, ALTHOUGH NO LIGHTS WERE SEEN DURING THE POST ENG CHANGE, GROUND RUNS OR TEST FLIGHT.SDR 2010FA0000841Support · crackedDURING A 300 HOUR, PART B INSP, IT WAS DISCOVERED THAT THE SUPPORTS (PN - 205-030-889-015) WERE FOUND CRACKED. 2 OTHER ACFT IN THE FLEET WERE CHECKED AND FOUND TO HAVE WORKING RIVETS IN THE SAME LOCATION. THIS CAUSES PLAY IN THE ELEVATORS AND IF LEFT UNDETECTSDR CA100804009Engine · power lossPOWER LOSS/IFSD DURING A TEST FLIGHT, FOLLOWING A NR 1 POWER SECTION (PS) CHANGE, THE ACFT EXPERIENCED A NR 2 PS IFSD. THE ACFT LANDED WITHOUT INCIDENT. DURING THE SUBSEQUENT VISUAL INSP, METALLIC DEBRIS WAS FOUND IN THE EXHAUST DUCT. MFG WILL INVESTIGATE TOSDR CA100726012Packing · pinchedHYDRAULIC LEAK DISCOVERED BY FORESTRY GROUND CREW MEMBER WHILE HOOKING UP WATER BUCKET LONG LINE TO HELICOPTER BELLY CARGO HOOK. PILOT OBSERVED NR2 SYS HYD RESERVOIR FLUID LEVEL BELOW NORMAL LIMITS. AME TRACED LEAK TO NR 2 HYD ACCUMULATOR. PART WAS DISASSEMBSDR CA100602001Line · crackedWHILE ON A TRAINING MISSION, THE PILOT EXPERIENCED LOSS OF NR 1 HYD SYS PRESSURE. THE ACFT RETURNED TO BASE AND LANDED WITHOUT INCIDENT. MX DISCOVERED A CRACKED RIGID HYD LINE, BETWEEN THE CUTOFF BLOCK AND THE 3 WAY SHUTOFF VALVE. CRACK DEVELOPED UNDER A SW
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