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 CA990915039Bolt · wrong part(CAN) WHILE DOING A MAIN ROTOR BLADE REPLACEMENT, THE BLADE BOLTS LOOKED DIFFERENT AND WERE LATER CONFIRMED BY MANUFACTURER TO BE BOGUS. ORIGINATOR CHECKING ON PREVIOUS HISTORY OF M/R HEAD ASSY.SDR CA991027051Cover · worn(CAN) P3 FILTER SPINNING IN THE COVER CAUSING INTERNAL WEAR OF THE UNIT.SDR CA990817020Hub · cracked(CAN) T/R HUB WAS REMOVED AND DISASSEMBLED IN ORDER TO COMPLY WITH SB. DURING OVERHAUL, AN NDT INSPECTION REVEALED A CRACK IN THE RADIUS OF THE MOUNTING FLANGE (INBD SIDE). IT IS THOUGHT THAT A FAULTY CASTING MAY HAVE CAUSED THE CRACK.SDR CA990927020Heater · failed(CAN) THE ENGINE DRIVEN PUMP WAS UNABLE TO MAINTAIN FUEL PRESSURE WITH THE LOSS OF BOOST PUMP PRESSURE. THE CAUSE WAS FOUND TO BE FUEL HEATER PARTIAL BLOCKAGE. (FUNGI CONTAMINATION) .SDR CA990430016Coupling · cracked(CAN) DURING LUBRICATION OF T/R DRIVE SHAFT COUPLINGS (ON SCHEDULED INSPECTION), CHIPPED TEETH WERE FOUND ON THE SPLINES.SDR HEEA061659Indicator · stickingNR 1 INDICATION AND CURSOR POINTERS STICKING.SDR CA990129025Servo · sticking(CAN) SERVO STICKING DURING CONTROL INPUTS UNDER HYDRAULIC SYSTEM PRESSURE.SDR CA990129026Seal · leaking(CAN) MAIN INPUT SEAL LEAKING. REPLACED.SDR CA990125004Transmission · making metal(CAN) SERVICEABLE TRANSMISSION INSTALLED AND ALTERNATE RUN-IN PROCEDURE CARRIED OUT IAW WITH BELL MM. FILTERS REMOVED AND FOUND CLEAN. TWO TEST FLIGHTS OF 0.3 AND 0.2 CARRIED OUT. DURING SECOND FLIGHT, THE TRANSMISSION CHIP WARNING LIGHT CAME ON AND AIRCRAFSDR CA990119002Engine · malfunctioned(CAN) NR 1 ENGINE EXHIBITED HIGH ITT, CAUSING A MARGINAL POWER ASSURANCE CHECK. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. PART TC: 7,225.SDR CA981123021Brake · malfunctioned(CAN) PILOT REPORTED MAGNETIC BRAKE INOPERATIVE IN THE FORE AND AFT AXIS.SDR HEEA0016414Compressor · failedNOISE COMING FROM COMPRESSOR.SDR HEEA0016416Control Unit · failedTORQUE CONTROL UNIT CAUSES TORQUE OSCILLATION ON NR 2 ENGINE.SDR CA980916041Servo · wrong part(CAN) SUBSEQUENT TO BELL ASB 212-98-103, TAIL SERVO INPUT LEVER FOUND TO BE UNAPPROVED PART AS DESCRIBED IN THE ASB.SDR CA980908001Case Gas Gen · cracked(CAN) AFTER POWER SECTION FAILED, ENGINE WAS BORESCOPED AND INTERNAL DAMAGE WARRANTED ENGINE REMOVAL. SUBSEQUENTLY, THE GAS GENERATOR CASE WAS FOUND CRACKED. PART TC: 3,086.SDR CA980827009Blade · cracked(CAN) ON DAILY INSPECTION, FOUND REPAIR PATCH MISSING FROM THE UNDERSIDE OF BLADE S/N A-833. DURING REMOVAL OF RESIDUAL ADHESIVE, A CRACK WAS FOUND IN THE SKIN AT 111.25 INCHES FROM TIP AND 6 INCHES FROM LEADING EDGE. THE 20 INCH LONG CRACK ORIGINATES AT A NSDR CA980827008Blade · delaminated(CAN) ON DAILY INSPECTION, VOID FOUND IN NR 2 DOUBLER EXCEEDING LIMITS. BLADE REPLACED.SDR HEEA0015424Gearbox · making metalGEARBOX HAS METAL ON NR 1 SIDE.SDR HEEA0015279Control Unit · leakingNR 2 SIDE HAS INTERNAL AIR LEAK THAT PREVENTS NR 2 ENGINE FROM TOPPING. (BOTH SERVO VALVES LEAK).SDR CA980804007Electrical Sys · failed(CAN) A LARGE AMOUNT OF STATIC ELECTRICITY WAS OCCURRING DURING SLINGING OPS ON LONG LINE. WHILE SLINGING A LOAD, THE STARTER/GENERATOR FOR ONE ENGINE WENT OFF-LINE. PILOT RESET THE GENERATOR AND IT CAME BACK ON-LINE. A SECOND BUILD-UP OF STATIC FOLLOWED BYSDR 98ZZZX2588Gearbox · making metalCHIP LIGHT ILLUMINATED, METAL FOUND ON MAGNETIC CHIP PLUG. EXCESSIVE TORQUE SPLIT.SDR CA980819001Bearing · failed(CAN) CHIP DETECTOR LIGHT ILLUMINATED FOLLOWED BY ENGINE VIBRATION, ON NR 1 ENGINE. ENGINE WAS SECURED. POST-FLIGHT INSPECTION FOUND THE NR 3 BEARING HAD FAILED CAUSING METAL CONTAMINATION TO THE C-BOX. THE BEARING WAS PREVIOUSLY A RE-MANUFACTURED BII BEARISDR HEEA0014838Actuator · failedMOTOR WILL NOT ACTUATE.SDR HEEA0014851Valve · faultyBLEED VALVE NOT READING CORRECTLY. TIME SINCE REPAIR 0:00.SDR HEEA0014912Gearbox · making metalCOMBINING GEARBOX HAS METAL CONTAMINATION ON NR 2 SIDE.SDR HAIGJQR0184Ring · corrodedRETAINING RING CORRODED REPLACED WITH NEW PARTS FROM BHTSDR CA980602053Transmission · leaking(CAN) FOLLOWING INSTALLATION, OIL WAS FOUND LEAKING FROM THE UPPER OIL JETS. O-RING WAS NOT INSTALLED ON THE JET.SDR CA980504003Blade · dented(CAN) PILOT LANDED TOO CLOSE TO A TREE. TREE STRIKE RESULTED IN DENTS TO BOTH BLADES NEAR THE TIPS.SDR CA980507001Friction Damper · cracked(CAN) BOTH EARS OF ATTACHMENT LUG BROKEN OFF DUE TO CRACKING THROUGH BOLT HOLES. DAMPER NO LONGER ATTACHED TO AIRFRAME.SDR CA980113002Turbine Wheel · damaged(CAN) AT 6,000 FEET IN CRUISE AT 80 PERCENT TORQUE, NR 2 ENGINE MADE A LOUD BANG WITH A GRINDING SOUND -'POOF SOUND'- THEN A CHIP DETECTOR LIGHT. THERE WAS NO PREVIOUS WARNING. PILOT REDUCED NR 2 ENGINE POWER TO IDLE AND LANDED ON A FROZEN LAKE. POST-FLIGHTSDR CA971110004Spiralbevel Gear · cracked(CAN) IN NORMAL SERVICE, THE ATTACHMENT BOLT TORQUE OF THE GEAR TO SHAFT (P/N 204-040-324-5) BECAME REDUCED RESULTING IN FRETTING CORROSION OF THE MATING SURFACES. A SURFACE CRACK WAS FOUND DURING OVERHAUL BETWEEN TWO OF THE ATTACH BOLT HOLES IN THE GEAR. SUSDR CA971222001Fittng · broken(CAN) AIRCRAFT ON LOGGING MISSION, AFTER LAST FLIGHT AME FOUND THAT THE LUG OF THE PYLON FITTING HAD BROKEN OFF.SDR CA971113060Couplings · no lube(CAN) INSUFFICIENT GREASE IN BOTH DRIVE SHAFT COUPLINGS. IN ADDITION, ONE BOOT WAS FOUND COMPLETELY TORN.SDR CA971113056Fuel Contrl Unit · leak(CAN) FUEL LEAKING FROM THE FUEL CONTROL UNIT THROTTLE SHAFT INTERCONNECT SIDE.SDR CA971028012Tip Cap · failed(CAN) TIE DOWN WAS INSTALLED ON FORWARD AND REAR BLADE OF AIRCRAFT DUE TO HIGH WINDS. TIP CAP FAILED DUE TO FLAPPING CAUSED BY HIGH WINDS THEN FORWARD MAIN ROTOR BLADE CONTACTED WIRE STRIKE KIT, CAUSING DAMAGE TO MAIN ROTOR BLADE.SDR CA971125006Retaining Ring · failed(CAN) POWER SECTION DEVELOPED COMPRESSOR STALLS. INSPECTION FOUND PIECES OF METAL INSIDE INTAKE PLENUM WITH BENT AND DAMAGED ROTOR AND STATOR VANES. THE SOURCE OF THE FOD WAS BELIEVED TO BE RETAINING RINGS AND PINS (P/N 30113032) WHICH LET GO AND WENT INTO TSDR CA971016019Servo · malfunctioning(CAN) FOLLOWING INSTALLATION OF THIS SERVO, THE PILOT REPORTED CONTROL FEEDBACK IN THE CYCLIC CONTROL.SDR CA971015065Cowling · departed(CAN) EVERYTHING NORMAL ON TEST FLIGHT. AFTER SHUTDOWN IT WAS NOTED THAT LEFT COWLING WAS MISSING. A FASTENER REQUIRED PER ASB 412-95-87 HAD NOT BEEN INSTALLED. THE LEFT STABILIZER WAS DAMAGED AT ITS JUNCTION WITH TAILBOOM BY COWL.SDR CA970922009Mount · worn(CAN) DURING FLIGHT NR1 GENERATOR WENT OFF LINE AND WAS RESET. SMOKE WAS OBSERVED COMING FROM NR1 ENGINE, SO HELICOPTER LANDED. FIRE WAS OBSERVED COMING FROM NR1 ENGINE WHICH WAS EXTINGUISHED BY AME. INITIAL INVESTIGATION INDICATES THE ALIGNMENT DOWEL WEAR ON SDR CA971015053Line · leaking(CAN) OIL LEAKING FROM OIL PRESSURE SWITCH SPLIT LINE.SDR CA970728017Flex Shaft · jammed(CAN) NR 2 ENGINE FAILED TO LIGHT ON START WITHIN 15 SECONDS, START ABORTED. THE THROTTLE JAMMED AND THE PILOT DID NOT NOTICE THAT LIGHT OFF HAD OCCURRED PRIOR TO COMPLETING FAILED START PROCEDURE CALLING FOR STARTER DISENGAGE AND FUEL SHUT OFF. LIMITS EXCEESDR CA970709013Hose · chafed(CAN) WHILE IN HOVER, AIRCRAFT EXPERIENCED LOSS OF NR 2 HYDRAULIC PRESSURE INDICATION WITH WARNING INDICATION AND THE SMELL OF HYDRAULIC FLUID WAS NOTICED IN CABIN. FLEX LINE FOUND CHAFED AND LEAKING.SDR CA970716005Key Washer · broken(CAN) DURING CLIMB OUT THE ENGINE CHIP LIGHT ILLUMINATED. PILOT INITIATED RETURN TO BASE, ON APPROACH A LOUD BANG WAS HEARD AND THE #1 POWER SECTION DECELERATED. AN EMERGENCY LANDING WAS CARRIED OUT. POST FLIGHT INVESTIGATION FOUND THE KEY BROKE OFF THE KEY WASDR CA970421046Line · chafed(CAN) FLIGHT CONTROL SERVO HYDRAULIC LINES P/N 7--012J220W234 AND 70-012V000G146 WERE CHAFED THROUGH AND LEAKING DUE TO IMPROPER CLAMPING.SDR 97ZZZX2775Diaphragm · rupturedDURING DISASSEMBLY OF AFCU, FOUND DIAPHRAGM RUPTURED, P/N 2525013.SDR CA970311040Tube Assembly · chafed(CAN) AFT SECTION OF TUBE CHAFED AGAINST AIRFRAME BULKHEAD, CAUSING HOLE IN TUBE AND LOSS OF TRANSMISSION OIL. CLAMPS NOT INSTALLED.SDR CA970206020Fuel Pump · leaking(CAN) AFTER TEST FLIGHT FOLLOWING 600 HOUR INSPECTION FUEL WAS SEEN COMING FROM THE DRAIN AT THE BOTTOM OF THE ENGINE. INSPECTION FOUND THE FUEL WAS COMING FROM THE PIPE THAT DRAINS THE AUTOMATIC FUEL CONTROL SEAL. CLOSER INVESTIGATION FOUND THE ENGINE DRIVEN SDR CA961230010Elbow · cracked(CAN) DURING DAILY INSPECTION AME FOUND HYDRAULIC OIL ON FLOOR UNDER AIRCRAFT HELL HOLE. AFTER INVESTIGATION, THE AME FOUND OIL DRIPPING FROM THE INLET ELBOW OF THE #1 HYDRAULIC PUMP. THE FLEX LINE WAS DISCONNECTED AND ELBOW FOUND CRACKED.SDR CA961230013Governor · faulty(CAN) UPON DEPARTURE THE LOW SIDE GOVERNOR FAILED ON THE #1 ENGINE. #1 THROTTLE WAS ROLLED BACK TO IDLE, GOVERNOR SELECTED TO MANUAL AND THROTTLE ROLLED UP TO 4 PERCENT BELOW #2 ENGINE. THE FLIGHT WAS CONCLUDED WITHOUT FURTHER INCIDENT.SDR CA970226004Spacer · damaged(CAN) DURING A START ATTEMPT OF #1 ENGINE THE PILOT WAS UNABLE TO OBTAIN ANY N1 ROTATION. WHEN A SECOND START WAS ATTEMPTED AN AUDIBLE "CLUNK" WAS HEARD. THE STARTER GENERATOR AND TACHOMETER WERE REMOVED TO ATTEMPT TO MANUALLY ROTATE N1 DRIVE. NO ROTATION WAS
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