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 CA030708011Tube · chafed(CAN) CONTROL TUBE CHAFING IS 0.017 INCH DEEP. TUBE IS STEEL ALLOY. TUBE CHAFED FROM CONTACT WITH FIREWALL BOOT/ALUMINUM FLANGE. TUBE REPLACED.SDR CA030708008Hanger Assy · corroded(CAN) DEFECTS FOUND DURING ROUTINE INSPECTION/LUBRICATION. PROBLEM MAY HAVE EXISTED ATPRIOR INSPECTIONS BUT NOT DISCOVERED. 4 INNER, 4 OUTER COUPLINGS REPLACED. CORROSION PITS/SPALLING WERE ON SEVERAL TEETH OF EACH COUPLING.SDR CA030708009Control Arm · chafed(CAN) CONTROL TUBE AT PRIOR MAINTENANCE EVENT WAS INSTALLED BACKWARDS (180 DEGREES OUT). TUBE HAD NYLATRON SLEEVES BUT REVERSED POSITION CAUSED WEAR AT AFT FAIRLEAD. TUBE WORN 0.013. TUBE WALL THICKNESS IS 0.035. PART REPLACED.SDR CA030416003Bellcrank · failed(CAN) DURING APPROACH THE DROOP COMPENSATOR SYSTEM FAILED TO RESPOND AND ENGINE RPM INCREASED AS THE COLLECTIVE WAS LOWERED. PILOT ADJUSTED ENGINE RPM USING THE ELECTRICAL TRIM SYSTEM, (BEEP SWITCH). SUBSEQUENT INSPECTION FOUND THAT THE ENGINE GOVERNOR CONTROLSDR EHI0404Spring · failedHYDRAULIC SYSTEM FEEDBACK FELT AND AUDIBLY OBSERVED WHILE IN ALL OPERATIONAL GROUND AND FLIGHT PROFILES. DURING MAINTENANCE TROUBLESHOOTING THE SUBJECT SERVO SPRING WAS FOUND FATIGUED/BROKEN.SDR CA030425003Bearing · making metal(CAN) DURING 600 HR TRANSMISSION INSPECTION INPUT QUILL WAS REMOVED TO FACILITATE MAINTENANCE. BEARING DEFECTS WERE IDENTIFIED THAT REQUIRED REPLACEMENT PRIOR TO AIRCRAFT WAS RETURNED TO SERVICE.SDR CA030220001Window · missing(CAN) HELI SKIING: HELICOPTER WAS UP IN AN ALPINE LANDING PAD. THE PASSENGERS HAVE BEEN ON LOADED FROM THEHELICOPTER. THE HELICOPTER SKIING GUIDE ON THE RIGHT SIDE OF THE HELICOPTER GAVE THE SIGNAL TO TAKE OFF. THE HELICOPTER TOOK OFF AND DESCENDED DOWN THE HISDR CA030213003Case · punctured(CAN) PIN SIZE HOLE LOCATED ON NR 2 PT6T-3 POWER SECTION GAS GENERATOR CASE AT APPROXIMATELY 7 O'CLOCK POSITION 3 3/4 INCHES AFT OF FIRST CIRCUMFIRENTIAL SEAM WELD (BY P3 AIR BOSS SUPPLYING AIR TO TORQUEMETER CLUTCH SEAL) WHILE PERFORMING VISUAL INSPECTION OF SDR CA030603009Angle · cracked(CAN) CRACK IS IN ANGLE ONLY, NOT FITTING.SDR CA030603010Bulkhead · cracked(CAN) TAIL BOOM ATTACH BULKHEAD AT STA 243.937, P/N 212030156047. CRACK UNDER 1 INCH LENGTH. BULKHEAD REPLACED WITH NEW.SDR CA021231002Fuel Control · malfunctioned(CAN) WHILE STARTING, THE START WENT HOT & THE START WAS ABORTED. THE NEXT START WAS A VERY LONG START WITH THE N1 HANGING UP AT 71 PERCENT WITH NO ACCELERATION PAST 71 PERCENT. THE HELICOPTER WAS STARTED USING THE MANUAL FUEL CONTROL AND THE START WAS NORMAL.SDR CA021204001Line · broken(CAN) THE GOVERNOR WAS LAGGING BEHIND. THE ENGINEER CARRIED OUT SOME ADJUSTMENTS BUT THE ADJUSTMENTS DID NOT HELP. A P3 AIR LEAK CHECK WAS CARRIED OUT AND THE ENGINEER DISCOVERED AIR LEAKING NEAR THE P3 AIR FILTER. FURTHER INVESTIGATION REVEALED THE LINE WAS BSDR CA021001004Bracket · cracked(CAN) IN THE PROCESS OF DOING A 3000 HOUR INSPECTION ON THE TAILBOOM LEFT HAND ELEVATOR, THE ENGINEER FOUND THE ELEVATOR ATTACHMENT LUG BRACKET CRACKED. THE CRACK WAS ON THE AFT SIDE ATTACHMENT LUG BRACKET B ELOW THE ATTACHMENT LUG, BETWEEN THE 1ST AND 2ND RISDR HEEA080638Drain Valve · corrodedENGINE BURNER DRAIN VALVE WILL NOT CLOSE - CORROSION. REPAIRED.SDR HEEA080443Fuel Control · malfunctionedENGINE HAD TORQUE AND N1 OSCILLATIONS. REPLACED WITH SERVICEABLE FUEL CONTROL.SDR HEEA080444Fuel Control · malfunctionedNR 2 ENGINE HAS N1 AND TORQUE OSCILLATIONS. REPLACED WITH SERVICEABLE FUEL CONTROL.SDR EHA2002F00009Fuel Control · failedON APPROACH TO LANDING AT A REMOTE LOCATION, THE PILOT EXPERIENCED A LOW SIDE GOVERNING FAILURE ON THE NR 2 AUTOMATION FUEL CONTROL UNIT. THE AFCU WAS PUT ON IAW MEL AND A FERRY FLIGHT PERMIT WAS ISSUED. THE AIRCRAFT RETURNED AND THE AFCU WAS CHANGED.SDR CA020827006Bearing · spalled(CAN) THE PILOT WAS FLYING WHEN THE MASTER CAUTION LIGHT ACTIVED. THE ENGINE CHIP LIGHT ON THE NR 1 SIDE ALSO ACTIVED. THE PILOT LANDED AS SOON AS PRACTICAL. THE REDUCTION GEARBOX AND BOTH POWER SECTIONS WERE REMOVED. THE SOURCE OF METAL WAS LOCATED. IT WSDR CA020718011Engine · failed(CAN) AFTER TAKEOFF ON A SCHEDULED TRIP FROM THE FIRE CAMP, THE PILOT LEELLED THE AIRCRAFT AND REDUCED POWER TO NORMAL CRUISE POWER. AT THIS MOMENT HE HEARD A LOUD BANG AND FELT A PRONOUNCED YAW. THE NR 1 ENGINE OUT LIGHT ILLUMINATED AND ALL NR 1 ENGINE INSTRUSDR HEEA080114Diaphragm · damagedINCREASE OF 75 DEGREES ITT AND 4.5 PERCENT N1 IN CRUISE FLIGHT. FOUND HOLE IN DIAPHRAGM. REPLACED.SDR CA020718008Support · broken(CAN) AFTER LANDING THE AIRCRAFT, THE PILOT HEARD A LOUD BANG. THE AIRCRAFT DID NOT MOVE AND THERE WAS NO INDICATON OF ANY MALFUNCTION ON THE INSTRUMENTS. THE PILOT OPENED THE CREW DOOR AND SAW THE RT SKID TUBE SLIPPED OUT TO THE RIGHT. INSPECTION REEALED THATSDR AUS20020630Bearing · delaminated(AUS) MAIN ROTOR BLADE INBOARD ELASTOMERIC BEARING DELAMINATED.SDR CA020815002Case · cracked(CAN) POWER SECTION WAS REMOVED DUE LOW POWER.SDR AUS20020634Pressure Switch · leaking(AUS) FUEL PRESSURE SWITCH LEAKING FROM SOLDER JOINT. SUSPECT CAUSED BY INTERNAL FAILURE OF METAL DIAPHRAGM.SDR CA020621010Bearing · failed(CAN) SUMP CHIP INDICATION DURING GROUND RUN PRIOR TO FLIGHT. METAL CONTAMINATION OF INTERNAL FILTER AND SUMP CHIP PLUG.TRANSMISSION REMOVED FROM SERVICE, TEARDOWN CARRIED OUT. HYDRAULIC QUILL DUPLEX BEARING IDENTIFIED AS SOURCE OF METAL GENERATION.SDR AUS20020360Diode · failed(AUS) NR 2 GENERATOR OFF LINE, THE EMERGENCY BUS INTERCONNECT CIRCUIT BREAKER POPPED, PILOT LOST POWER TO THE NR 2 BUS. INVESTIGATION FOUND 2 DIODES ON THE EMERGENCY BUS FAILED RESISTANCE CHECK.SDR AUS20020361Sleeve · worn(AUS) THE FIRE SLEEVE OF FUEL HOSE (PN 10544E) WAS FOUND CHAFFED APPROX 0.005 IN (0.127MM) IN DEPTH THROUGH WALL OF FUEL HEATER.SDR CA020408002Seal · leaking(CAN) MANUAL FCU LEAKS AT CONTROL SHAFT SEAL, INTERCONNECT SIDE.SDR CA020408001Vent · clogged(CAN) FUEL PRESSURE FLUCTUATED, FUEL PRESSURE TRANSMITTER PORT AND VENT FOUND ALMOST CLOGGED BY MUDDY SUBSTANCE.SDR CA020408003Control Box · corroded(CAN) WHILE HOVERING OVER WATER ALL KINDS OF WARNING LIGHTS AND HORNS CAME ON. PARAMETERS LOOKED NORMAL, AIRCRAFT WAS FLOWN TO THE CLOSEST AIRPORT, RPM BOX WAS OPENED AND FOUND CORRODED, WAS SUBSEQUENTLY REPLACED.SDR CA020408004Pump · failed(CAN) IN FLIGHT, FUEL PRESSURE FLUCTUATED AND WENT TO ZERO ON LT FUEL PUMP, CIRCUIT BREAKER POPPED.SDR CA020228012Governor(CAN) COCKPIT INDICATION OF ENGINE TORQUE SPLIT DURING HOVER TAXI, AIRCRAFT RETURNED TO RAMP. TORQUE SPLIT CAUSED BY N2 GOVERNOR FAILURE CONFIRMED BY UNIT REPLACEMENT.SDR AUS20020101Pressure Switch · cracked(AUS) FUEL PRESSURE SWITCH FAULTY. FUEL LEAKING FROM SOLDERED JOINT ON PLUG FITTING LOCATED ON TOP OF SWITCH.SDR LSI2002F00000Filter · failedDURING MAINTENANCE OF THE ENGINE FUEL CONTROL AIR SUPPLY SYSTEM, THE P3 WAS REMOVED FOR INSPECTION AND FOUND TO BE IN TWO PIECES. THE METAL END CAPS ARE NORMALLY WELDED TO METAL SCREEN. THIS PMA FILTER WAS BONDED TOGETHER. THE BOND MATERIAL WAS SO BRITTLE FSDR CA020131004Chain · broken(CAN) THE HELICOPTER WAS IN CRUISE WHEN ALL OF A SUDDEN THE ROTOR TACH GENERATOR INDICATOR WENT TO ZERO.BACK AT THE BASE AN ENGINEER TROUBLE SHOOTED THE PROBLEM AND FOUND THE TACH. GEN DRIVE WAS DISCONNECTED. THE ROTOR TACH GENERATOR DRIVE IS LOCATED IN THE #1SDR CA020131003Line · broken(CAN) HE AIRCRAFT NR 1 HYDRAULIC SYSTEM LOST SYSTEM PRESSURE(FLUID LOSS). THE ENGINEER FOUND A HYDRAULIC TUBE BROKEN IN THE MID POINT.SDR CA020123003Gearbox · contaminated(CAN) IN CRUISE FLIGHT THE PILOT THE PILOT NOTED THE C-BOX CHIP LIGHT FLICKER FAINTLY FOLLOWED SHORTLY BY THE C-BOX OIL PRESSURE CAUTION LIGHT ILLUMINATING.C-BOX OIL PRESSURE WAS OBSERVED DROPPING AND AN UNSCHEDULED BUT NORMAL LANDING PROCEDURE WAS CARRIED OSDR CA020104023Oil Jet · mislocated(CAN) DURING INSTALLATION OF MAIN ROTOR MAST ASSEMBLY IT WAS VISUALLY IDENTIFIED THAT THE OIL JET WAS LOCATED IN THE WRONG POSITION FOR CONNECTION OF OIL SUPPLY LINE. PART WAS REPLACED WITH SERVICEABLE UNIT.SDR CA020402004Bearing · failed(CAN) TRANSMISSION REPLACED DUE METAL CONTAMINATION.SDR CA011211002Bolt · bent(CAN) THIS BOLT HOLDS THE TAIL ROTOR DRIVESHAFT COUPLING TO THE INPUT QUILL OF THE 90 DEGREE GEARBOX. WHEN THE BOLT WAS REMOVED FOR SCHEDULED MAINTENANCE (GREASE REPACKING). IT WAD NOTICED THAT IT WAS NOT THE NORMAL COLOR (BLACK) THAN IT WAS NOTICED THAT IT WASDR HEEA076255Engine · malfunctionedHIGH OIL CONSUMPTION. SENT TO PRATT AND WHITNEY FOR WARRANTY REPAIR.SDR HEEA076256Engine · corrodedCORROSION AT 12 OCLOCK. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.SDR HEEA076257Engine · stalledCOMPRESSOR STALLS AND HIGH ITT. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.SDR HEEA076259Engine · malfunctionedLOW POWER. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.SDR HEEA076261Engine · hot startHOT STARTS. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.SDR HEEA076269Blade · corrodedCOMPRESSOR BLADE CORRODED.SDR HEEA076464Diaphragm · damagedINCREASE OF 40 DEGREES ITT AND 4 PERCENT N1 AT POWER CHECK SETTINGS. FOUND HOLE IN DIAPHRAGM. REPLACED WITH SERVICEABLE DIAPHRAGM.SDR CA011012001Blade · delaminated(CAN) ON A DAILY INSPECTION THE ENGINEER WAS INSPECTING THE TAIL ROTOR BLADES, ON T/R BLADE S/N A-11101 HE FOUND A DELAMINATION AT THE TIP. A REPLACEMENT T/R HUB ASSEMBLY WAS ORDERED (TSN 729.9 OF S/N A-11101) AT TTSN 413.9 T/R BLADE WAS REMOVED DUE TO DELAMISDR CA011031026Bulkhead · cracked(CAN) DURING A SCHEDULED MAINTENANCE INSPECTION THE CRACK WAS DISCOVERED. HEADQUARTERS HAS RECEIVED THE PARTICULARS AND IS PREPARING A REPAIR SCHEME.SDR CA011005002Bevel Gear · broken(CAN) METAL PARTICLES FOUND IN SUMP FILTER AT 50 HOUR INSPECTION. TRANSMISSION REMOVED AND SENT FOR OVERHAUL. WHEN ROTOR BRAKE QUILL WAS REMOVED I NOTICED HEAVY WEAR ON THE TEETH OF THE PINION. INSPECTION OF THE SPIRAL BEVEL GEAR REVEALED TWO BROKEN TEETH AND
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