Pratt & Whitney PT6T-3

Service difficulty reports · 421

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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.

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.May 15, 2003 · Bell 212 · Main Rotor Drive SystemSDR 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.May 1, 2003 · Bell 212 · Tail Rotor Drive ShaftSDR 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.May 1, 2003 · Bell 212 · Tail Rotor SystemSDR 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 CONTROLApr 6, 2003 · Bell 212 · Fuel Controlling SystemSDR 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.Apr 4, 2003 · N59633 · Bell 212 · Hydraulic System, MainSDR 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.Mar 31, 2003 · Bell 212 · Main Rotor GearboxSDR 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 HIFeb 14, 2003 · Bell 212 · Passenger Compartment WindowsSDR 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 Feb 10, 2003 · Bell 212 · Turbine Engine Compressor SectionSDR CA030603009Angle · cracked(CAN) CRACK IS IN ANGLE ONLY, NOT FITTING.Jan 31, 2003 · Bell 212 · Fuselage Main, StructureSDR CA030603010Bulkhead · cracked(CAN) TAIL BOOM ATTACH BULKHEAD AT STA 243.937, P/N 212030156047. CRACK UNDER 1 INCH LENGTH. BULKHEAD REPLACED WITH NEW.Jan 31, 2003 · Bell 212 · Rotorcraft Tail BoomSDR 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.Dec 11, 2002 · Bell 212 · Fuel Control/Turbine EnginesSDR 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 BNov 23, 2002 · Bell 212 · Fuel Control/Turbine EnginesSDR 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 RISep 24, 2002 · Bell 212 · Empennage StructureSDR HEEA080638Drain Valve · corrodedENGINE BURNER DRAIN VALVE WILL NOT CLOSE - CORROSION. REPAIRED.Jul 29, 2002 · N107X · Bell 412 · Turbine Engine Combustion SectionSDR HEEA080443Fuel Control · malfunctionedENGINE HAD TORQUE AND N1 OSCILLATIONS. REPLACED WITH SERVICEABLE FUEL CONTROL.Jul 9, 2002 · N102PH · Bell 212 · Fuel Controlling SystemSDR HEEA080444Fuel Control · malfunctionedNR 2 ENGINE HAS N1 AND TORQUE OSCILLATIONS. REPLACED WITH SERVICEABLE FUEL CONTROL.Jul 9, 2002 · N102PH · Bell 212 · Fuel Controlling SystemSDR 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.Jul 1, 2002 · N16974 · Bell 212 · Fuel Control/Turbine EnginesSDR 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 WJun 28, 2002 · Bell 212 · Engine/Transmission CouplingSDR 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 INSTRUJun 27, 2002 · Bell 212 · Engine (Turbine/Turboprop)SDR HEEA080114Diaphragm · damagedINCREASE OF 75 DEGREES ITT AND 4.5 PERCENT N1 IN CRUISE FLIGHT. FOUND HOLE IN DIAPHRAGM. REPLACED.Jun 25, 2002 · N5736J · Bell 212 · Compressor Bleed ValveSDR 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 THATJun 23, 2002 · Bell 212 · Main Landing Gear Strut/Axle/TruckSDR AUS20020630Bearing · delaminated(AUS) MAIN ROTOR BLADE INBOARD ELASTOMERIC BEARING DELAMINATED.Jun 21, 2002 · Bell 412 · Main Rotor HeadSDR CA020815002Case · cracked(CAN) POWER SECTION WAS REMOVED DUE LOW POWER.Jun 1, 2002 · Bell 212 · Turbine SectionSDR AUS20020634Pressure Switch · leaking(AUS) FUEL PRESSURE SWITCH LEAKING FROM SOLDER JOINT. SUSPECT CAUSED BY INTERNAL FAILURE OF METAL DIAPHRAGM.May 28, 2002 · Bell 412 · Fuel Pressure SensorSDR 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.May 19, 2002 · Bell 212 · Main Rotor GearboxSDR 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.Mar 20, 2002 · Bell 412 · DC Generator-AlternatorSDR 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.Mar 20, 2002 · Bell 412 · Engine Fuel DistributionSDR CA020408002Seal · leaking(CAN) MANUAL FCU LEAKS AT CONTROL SHAFT SEAL, INTERCONNECT SIDE.Mar 19, 2002 · Bell 212 · Fuel Control/Turbine EnginesSDR CA020408001Vent · clogged(CAN) FUEL PRESSURE FLUCTUATED, FUEL PRESSURE TRANSMITTER PORT AND VENT FOUND ALMOST CLOGGED BY MUDDY SUBSTANCE.Mar 8, 2002 · Bell 212 · Fuel Pressure IndicatingSDR 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.Mar 8, 2002 · Bell 212 · Engine RPM Indicating SystemSDR CA020408004Pump · failed(CAN) IN FLIGHT, FUEL PRESSURE FLUCTUATED AND WENT TO ZERO ON LT FUEL PUMP, CIRCUIT BREAKER POPPED.Mar 7, 2002 · Bell 212 · Fuel Boost PumpSDR 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.Feb 16, 2002 · Bell 212 · Turbine GovernorSDR AUS20020101Pressure Switch · cracked(AUS) FUEL PRESSURE SWITCH FAULTY. FUEL LEAKING FROM SOLDERED JOINT ON PLUG FITTING LOCATED ON TOP OF SWITCH.Feb 12, 2002 · Bell 412 · Fuel Pressure SensorSDR 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 FFeb 4, 2002 · N8530B · Bell 212 · Aircraft Fuel Filter/StrainerSDR 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 #1Jan 29, 2002 · Bell 212 · Rotor Drive Indicating SystemSDR 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.Jan 29, 2002 · Bell 212 · Hydraulic System, MainSDR 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 OJan 16, 2002 · Bell 212 · Turbine Engine Reduction GearSDR 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.Dec 27, 2001 · Bell 212 · Main Rotor Mast/SwashplateSDR CA020402004Bearing · failed(CAN) TRANSMISSION REPLACED DUE METAL CONTAMINATION.Dec 22, 2001 · Bell 212 · Main Rotor GearboxSDR 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 WANov 22, 2001 · Bell 212 · Tail Rotor Drive ShaftSDR HEEA076255Engine · malfunctionedHIGH OIL CONSUMPTION. SENT TO PRATT AND WHITNEY FOR WARRANTY REPAIR.Oct 9, 2001 · N102PH · Bell 212 · Engine (Turbine/Turboprop)SDR HEEA076256Engine · corrodedCORROSION AT 12 OCLOCK. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.Oct 9, 2001 · N1079U · Bell 212 · Engine (Turbine/Turboprop)SDR HEEA076257Engine · stalledCOMPRESSOR STALLS AND HIGH ITT. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.Oct 9, 2001 · N5736D · Bell 212 · Engine (Turbine/Turboprop)SDR HEEA076259Engine · malfunctionedLOW POWER. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.Oct 9, 2001 · N5009N · Bell 212 · Engine (Turbine/Turboprop)SDR HEEA076261Engine · hot startHOT STARTS. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.Oct 9, 2001 · N5736D · Bell 212 · Engine (Turbine/Turboprop)SDR HEEA076269Blade · corrodedCOMPRESSOR BLADE CORRODED.Oct 9, 2001 · N1082G · Bell 212 · Engine (Turbine/Turboprop)SDR HEEA076464Diaphragm · damagedINCREASE OF 40 DEGREES ITT AND 4 PERCENT N1 AT POWER CHECK SETTINGS. FOUND HOLE IN DIAPHRAGM. REPLACED WITH SERVICEABLE DIAPHRAGM.Oct 4, 2001 · N102PH · Bell 212 · Compressor Bleed ValveSDR 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 DELAMIOct 2, 2001 · Bell 212 · Tail Rotor BladesSDR CA011031026Bulkhead · cracked(CAN) DURING A SCHEDULED MAINTENANCE INSPECTION THE CRACK WAS DISCOVERED. HEADQUARTERS HAS RECEIVED THE PARTICULARS AND IS PREPARING A REPAIR SCHEME.Sep 28, 2001 · Bell 212 · Rotorcraft Tail BoomSDR 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 Sep 26, 2001 · Bell 212 · Main Rotor Gearbox
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