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.

SDR CA011105003Line · leaking(CAN) DURING RUN UP THE SUBJECT LINE STARTED LEAKING, THIS WAS REPORTED BY PASSENGERS IN AIRCRAFT WHO NOTICED HYDRULIC FLUID LEAKING INTO CABIN FROM OVERHEAD.AIRCRAFT WAS SHUT DOWN AND THE AME LOCATED THE LEAKING LINE ON NR 2 HYDRAULIC SYSTEM. THIS LINE WAS LASep 21, 2001 · Bell 212 · Hydraulic System, MainSDR CA011003010Bearing · failed(CAN) AME WAS COMPLETING A DAILY INSPECTION WHEN HE PULLED THE LT SERVO BRUSH TUBE AND FELT PLAY. UPON INVESTIGATION A BEARING IN THE UNIVERSAL HAD FAILED.Sep 13, 2001 · Bell 212 · Rotorcraft Servo SystemSDR AUS20010939Window · failed(AUS) LT SLIDING DOOR REAR WINDOW FAILED. MINOR DAMAGE TO HF RADIO ANTENNA CONNECTOR AND HORIZONTAL STABILISER.Aug 27, 2001 · Bell 412 · Passenger Compartment WindowsSDR CA010831005Gearbox · damaged(CAN) ON RAMP AFTER M/R HEAD CHANGE MASTER CAUTION LIGHT ACTIVATED&ENGINE CHIP LIGHT ACTIVATED. ENGINEER FOUND ON REAR CHIP DETECTOR FOR ENGINE MINOR FUZZ. ENGINER CLEANED CHIP DETECTOR & REINSTALLED ENGINEER INSPECTED FILTERS & FOUND NO DISCREPANCY. A/C GROUNAug 15, 2001 · Bell 212 · Turbine Engine Reduction GearSDR AUS20010864Blade · cracked(AUS) TAIL ROTOR BLADE CRACKED ON INNER FACE. THE CRACK LENGTH RUNS FOR ALMOST THE FULL CHORD OF THE BLADE. FOUND DURING INSPECTION IAW AD/119/1 PT1.Aug 13, 2001 · Agusta A119 · Tail Rotor BladesSDR AUS20010836Pipe · cracked(AUS) HYDRAULIC PIPE CRACKED IN RADIUS.Aug 1, 2001 · Bell 412 · Hydraulic System, MainSDR EHA2001F00003Engine · failedON APPROACH TO REMOTE LANDING ZONE, WAITING FOR PREVIOUS A/C TO DEPART, PILOT WAS HOLDING IN PATTERN FOR LANDING AT APPROXIMATELY 50 KNOTS AND 400 FEET AGL. WHILE HOLDING, PILOT HEARD ENGINE OUT WARNING AUDIO AND VERIFIED NR 2 ENGINE POWER LOSS. HE THEN EXECJun 26, 2001 · N5017H · Bell 212 · Engine (Turbine/Turboprop)SDR ERAA074628Compressor · failedAFTER 451.2 HRS T.S.O. C-BOX REMOVED FROM AIRCRAFT DUE TO HIGH OIL PRESSURE.Jun 21, 2001 · N421EH · Bell 412 · Turbine Engine Compressor SectionSDR CA010530009Bearing · seized(CAN) DURING AN OPS CHECK IT WAS DISCOVERED THAT THE UPPER HOUSING NR 76 TO LOWER HOUSING NR 100, LOCK NR 79 WAS DISLODGED. FURTHER INVESTIGATION FOUND THAT THE BEARING NR 98 (WHICH ALLOWS THE CARGO HOOK TO ROTATE UNDER LOAD) WAS SEIZED DUE TO CORROSION. THEREMay 10, 2001 · Bell 212 · Cargo CompartmentsSDR CA010522025Crosstube · broken(CAN) HELICOPTER WAS ON A HELI SKIING JOB. THE JOB DESCRIPTION IS LOW HOURS BUT LOTS OF LANDINGS IN SNOW. THE PILOT HAD A RATHER ABRUPT LANDING ON ONE OF THE LANDING SITES (NOT HARD BUT NOT SMOOTH). AT THE NEXT LANDING THE PILOT HEARD A LOUD BANG AND IT WAS NOMay 1, 2001 · Bell 212 · Main Landing GearSDR CA010423005Bearing · failed(CAN) BAD BRINNELLING, TEFLON WORN AWAY.(FLAPPING BEARINGS)Mar 28, 2001 · Bell 212 · Tail Rotor HeadSDR CA010424002Shaft · failed(CAN) THE NR 2 ENGINE FLAMED OUT. AFTER THE PILOT LANDED THE AIRCRAFT SUCCESSFULLY, REMOVE THE AFCU, MFCU AND ENGINE DRIVEN FUEL PUMP. I FOUND THE FUEL PUMP SPLINES WITH NO LUBRICATION AND WORN WELL BEYOND LIMITS. (NOTE: THE SPLINED ADAPTER WAS SPINNING FREELYMar 16, 2001 · Bell 212 · Engine Fuel PumpSDR AU010155Switch · leaking(AUS) FUEL FILTER BYPASS SWITCH LEAKING FROM SWITCH BODY IN THE AREA WHERE THE ELECTRICAL CONNECTOR IS SOLDERED TO THE SWITCH. FUEL WAS SEEN RUNNING INTO THE ENGINE INTAKE PLENUM. A REPLACEMENT SWITCH HAD POOR SOLDERING OF THE CONNECTOR IN THE SAME AREA ASTHEFeb 19, 2001 · Bell 412 · Engine Fuel DistributionSDR CA010301036Turbine Blades · wrong part(CAN) POWER TURBINE SECTION DISASSEMBLED FOR EVALUATION. POWER TURBINE BLADES SHOWED A DIFFERENT CONFIG THAN P/N 3027102 POWER TURBINE BLA DES NORMALLY FOUND ON THIS MODEL ENGINE. ALSO PART NO (P/N 3013102) STAMPED ON BLADES WAS CROSSED OUT & P/N 3027102 WAS Feb 12, 2001 · Turbine SectionSDR CA010209015Window · failed(CAN) WHILE IN STRAIGHT AND LEVEL FLIGHT A LOUD BANG WAS HEARD. IT WAS DISCOVERED THAT THE RT REAR SLIDING DOOR WINDOW HAD SHATTERED. AN UNEVENTFUL LANDING WAS CARRIED OUT. ALLL PIECES WERE RECOVERED.Jan 21, 2001 · Bell 212 · Flight Compartment WindowsSDR 20010130CW007Fuel Line · chafedNR1 INLET COWLING CHAFING FUEL INLET LINE, PN3017392, DUE TO INSTALLATION OF SHADIN FUEL FLOW, STC SE1123GL.Dec 7, 2000 · N63177 · Bell 412EP · Aircraft Fuel Distribution SystemSDR CA001205024Bearing · seized(CAN) TOP BEARING SEIZED ON CARGO HOOK CAUSING SUPPORT TO CRACK AT BOLT HOLES, SEVERE STRESS ON MOUNTING BOLTS AND BUSHING CAUSING ABNORMAL WEAR OF MOUNTING BUSHING. (X)Nov 23, 2000 · Bell 212 · Cargo CompartmentsSDR CA001130003Transmission · making metal(CAN) APPROXIMATELY 1.3 HR INTO FLT MAIN TRANSMISSION WARNING LIGHT ILLUMINATED. A/C WAS APPROXIMATELY. 3 MINS AWAY FROM AN ON ROUTE AIRPORT; THE PILOT ELECTED TO LAND AT AIRPORT & HAVE MAINTENANCE ENGINEER INVESTIGATE PROBLEM. AME PULLED MAGNETIC CHIP DETECTONov 3, 2000 · Bell 212 · Main Rotor GearboxSDR CA001103021Solenoid Valve · leaking(CAN) WHILE THE FUEL SUMPS WERE BEING DRAINED IN PREPARATION FOR FLIGHT, IT WAS NOTED THAT THE LEFT FUEL SUMP WAS LEAKING. THE SUMP SOLENOID WAS RECYCLED AND FUEL LEAK STOPPED. WITH SIMPLEX SPRAY SYS INST FUEL DRAIN SOLENOID IS INACCESSIBLE. TH E SOLENOID DRSep 9, 2000 · Bell 212 · Aircraft Fuel Filter/StrainerSDR CA000925029Mount · cracked(CAN) IN THE PROCESS OF CHANGING WEAK TRANSMISSION LORD MOUNTS, FOUND A CRACKED LIFT LINK (FITTING) MOUNT. THE RIGHT FORWARD EAR WAS CRACKED. THE FITTING IS ON THE TRANSMISSION. THE DAMPERS WERE WEAK ALSO. (X)Aug 30, 2000 · Bell 212 · Main Rotor Transmission MountSDR CA000824009Main Rotor · cracked(CAN) WHILE WASHING THE M/R BLADES THE WASHER ON THE UNDERSIDE OF M/R BLADE A-1567 THAT THE SOAP BUBBLED AS PUSHED UP ON THE BLADE. FURTHER INVESTIGATION FOUND A CRACK RUNNING CHORDWISE FROM THE AFT EDGE OF THE SPAR TO ABOUT 4 INCHES FORWARD OF THE TRAILING EJul 30, 2000 · Bell 212 · Main Rotor BladesSDR CA000801007Line · leaking(CAN) UPON LANDING THE ENGINEER NOTICED OIL ON THE BELLY OF THE AIRCRAFT. UPON INVESTIGATION HE FOUND A PIN HOLE IN THE OIL LINE.Jul 17, 2000 · Bell 212 · Main Rotor GearboxSDR CA001205004Blade · delaminated(CAN) TAIL ROTOR BLADE DELAMINATION FOUND BETWEEN THE SKIN AND THE TIP BLOCK THAT WAS BEYOND LIMITS. TAILROTOR ASSEMBLY REPLACED.Jul 5, 2000 · Bell 212 · Tail Rotor BladesSDR CA000427004Beam · cracked(CAN) DURING PRE-FLIGHT, THE LEFT HAND BEAM CAP ON THE TAILBOOM PYLON WAS FOUND CRACKED (.080 INCH). NOTE: THIS CRACK WAS FOUND IN THE SAME PLACE AS DESCRIBED IN FAA AD 99-18-02 APPLICABLE TO BELL 205 SERIES.Apr 11, 2000 · Bell 212 · Rotorcraft Tail BoomSDR CA000719003Fastener · corroded(CAN) EXCESSIVE DISSIMILAR METAL CORROSION CAUSED BY SHEET METAL CLECOS BEING LEFT IN SINCE MANUFACTURE. THEY WERE LOCATED IN THE LEFT-HAND DOOR POST ON BULKHEAD STATION 63.27. NOTE: THIS AREA IS NOT ACCESSIBLE UNLESS THE SKIN IS REMOVED. IT WAS FOUND DURINApr 6, 2000 · Bell 212 · Fuselage Main, Plate/SkinSDR CA000427003Tube · loose(CAN) DURING INSPECTION, THE RIGHT CYCLIC SERVO INPUT LEVER WAS FOUND IN AN AFT OF CENTER ORIENTATION. SUBSEQUENT OBSERVATION REVEALED BOTH CYCLIC BOOST TUBES HAD LOOSE CLEVIS ASSEMBLIES AT LOWER END. THIS CAUSED THE SERVO TO ROTATE IN ANY POSITION AND INTERMar 29, 2000 · Bell 212 · Main Rotor ControlSDR CA000404002Pump · failed(CAN) FUEL PUMP SHAFT WAS ROUGH TO TURN. SENT FOR EVALUATION.Mar 24, 2000 · Bell 212 · Engine Fuel PumpSDR CA000316001Nut · fractured(CAN) AFTER M/R BLADE STRIKE, A CONDITIONAL INSPECTION WAS CARRIED OUT. BOTH ACORN NUTS WERE CONFIRMED FRACTURED BY NDT. ACORN NUTS SENT OUT FOR ANALYSIS.Mar 16, 2000 · Bell 212 · Main Rotor HeadSDR CA001013003Elt · failed(CAN) ELT WAS TESTED AS PER THE 100 HOUR INSPECTION SCHEDULED AND UNIT WOULD NOT ACTIVATE AFTER BEING SHAKEN OR WHEN THE MASTER SWITCH WAS TURNED TO THE ON POSITION. UNIT REPLACED.Mar 4, 2000 · Bell 212 · Emergency Locator BeaconSDR CA000518007Planetary Gear · chipped(CAN) METAL FOUND ON THE PLANETARY CHIP DETECTOR (.040 INCH - .060 INCH). TRANSMISSION WAS REMOVED SHORT OFF AND SENT FOR REPAIR.Feb 16, 2000 · Bell 212 · Main Rotor GearboxSDR CA000215026Floorboard · corroded(CAN) FLOOR HONEYCOMB CORRODED IN PANELS DIRECTLY UNDER THE DOWN RING ASSY AND TIE DOWN STUD. CORROSION IS ONLY APPARENT VISUALLY ON BOTTOM SIDE OF PANELS WHEN FILLER ASSY P/N 205-031-257-074 IS REMOVED.Feb 11, 2000 · Bell 212 · Fuselage Floor PanelSDR CA000215028Bearing Cover · chafed(CAN) DURING INSPECTION, THE SWASHPLATE BEARING COVER (P/N 204-011-428-003) WAS FOUND CHAFED THROUGH APPROX 330 DEGREES OF ITS CIRCUMFERENCE. THE CHAFING WAS CAUSED BY THE SEAL JUST BELOW THE BEARING COVER AS IT WAS RIDING HIGHER IN ONE SPOT WHICH CAUSED IT TOFeb 2, 2000 · Bell 212 · Main Rotor Mast/SwashplateSDR CA000530010Fuel Line · delaminated(CAN) WHEN REPLACING FLEXIBLE LINES INSIDE THE FUEL CELL, IT WAS NOTED THAT THE BOTTOM OF THE FUEL CELL WAS SPONGY. IT WAS THEN DESCOVERED THAT LAYERS OF RUBBER WERE BREAKING DOWN AND SEPARATING.Jan 16, 2000 · Bell 212 · Fuel StorageSDR AGQA065567Control Unit · failedCONTROL UNIT WOULD NOT MATCH TORQUES TORQUE SPLITJan 7, 2000 · N8530F · Bell 212 · Fuel Control/Turbine EnginesSDR AU000128011Hinge · cracked(AU) SMALL CRACK FOUND ON UPPER LT PYLON HINGE ATTACHMENT. NO OBVIOUS CAUSE.Jan 7, 2000 · Skrsky S58ET · Rotorcraft Tail BoomSDR CA000128011Hinge · cracked(CAN) SMALL CRACK FOUND ON UPPER LT PYLON HINGE ATTACHMENT. NO OBVIOUS CAUSE.Jan 7, 2000 · Skrsky S58ET · Rotorcraft Tail BoomSDR AGQA065543Exciter · failedEXCITER BOX IS INOPERABLE. WILL NOT EXCITE.Jan 6, 2000 · N8530F · Bell 212 · ExciterSDR CA991229018Starter Gen · malfunctioned(CAN) STARTER OVERHEAT DURING COMPRESSOR WASH CYCLES CAUSING SMOKE AND FLAMES IN STARTER.Nov 25, 1999 · Bell 212 · Starter-GeneratorSDR HEEA065210Indicator · intermittentFUEL PRESSURE INDICATOR INTERMITTENTLY STICKS AT ZERO.Nov 17, 1999 · N5010F · Bell 212 · Fuel Control/Reciprocating EnginesSDR HEEA065211Indicator · erraticFUEL PRESSURE INDICATOR HAD UNRELIABLE ERRATIC READINGS.Nov 17, 1999 · N5010F · Bell 212 · Fuel Control/Reciprocating EnginesSDR HEEA065166Gearbox · making metalCOMBINING GEARBOX MAKING METAL - GEAR TOOTH FOUND NR 2 AFT CHIP PLUG.Nov 15, 1999 · N3208H · Bell 212 · Turbine Engine Reduction GearSDR CA991210091Hose · ruptured(CAN) BRAIDED HYDRAULIC HOSE (PRESSURE) LOCATED FORWARD BULKHEAD OF TRANSMISSION COMPARTMENT FOUND TO BE RUBBING ON THE AIRFRAME AND RUPTURED ON START-UP.Nov 12, 1999 · Bell 212 · Hydraulic System, MainSDR CA000404012Bearing · failed(CAN) DURING FIRST START OF THE DAY, THE STARTER/GENERATOR WAS MAKING A RUMBLING/GROWLING NOISE. STARTER/GENERATOR REPLACED AND ON FURTHER INSPECTION, SOME BEARING PLAY WAS NOTED AT THE FAN END. SUSPECT DAMAGED BEARINGS.Nov 3, 1999 · Bell 212 · Starter-GeneratorSDR CA991028065Cargo Hook · failed(CAN) WHILE IN THE HOVER, IT WAS NOTED THAT THE CARGO HOOK WOULD NOT ELECTRICALLY CLOSE. THIS WAS CAUSED BY THE LOAD RING ENDING UP BETWEEN THE CARGO HOOK AND THE HOOK SECURITY LATCH. SUBMITTER STATED THE CREW WAS THEN UNABLE TO OPEN OR CLOSE THE CARGO HOOK Oct 18, 1999 · Bell 212 · Cargo CompartmentsSDR CA991028073Universal · seized(CAN) DURING REPLACEMENT OF THE RIGHT CYCLIC SERVO (FOR TIME), THE UNIVERSAL JOINT ON THE OUTPUT RAM WAS FOUND TO HAVE SEIZED (LOWER BEARING), AND THE INNER RACE WAS TURNING ON THE ATTACHMENT BOLT (P/N 20-057-5-24D). THE BOLT WAS ALSO CORRODED AND HAD WEAR STOct 18, 1999 · Bell 212 · Rotorcraft Servo SystemSDR CA991103017Piston Flange · failed(CAN) ENGINE SURGING EXPERIENCED. BLEED VAVE HAS HISTORY OF CAUSING SIMILAR PROBLEMS ON OTHER AIRCRAFT. REF: PT6 SB 5274R3 FOR IMPROVED BLEED VALVE CLOSING OPS.Oct 14, 1999 · Bell 212 · Compressor Bleed ValveSDR CA991208060Bleed Valve · surging(CAN) BLEED VALVE SPECIFIED TO HAVE HISTORY OF CAUSING SIMILAR ENGINE SURGING ON OTHER OPERATORS' A/C. SB 5274 R3 FOR POSSIBLE IMPROVED BLEED VALVE CLOSING OPS.Oct 14, 1999 · Bell 212 · Compressor Bleed ValveSDR CA991027038Rotor · damaged(CAN) POSSIBLE STATOR AND ROTOR DAMAGE. FOD - ENGINE TEAR DOWN RQUIRED TO CONFIRM.Oct 8, 1999 · Bell 212 · Turbine Engine Compressor SectionSDR CA991027033Servo · leaking(CAN) NR 1 HYDRAULIC SYSTEM GRADUALLY LOST PRESSURE, WARNING LIGHT CAME ON AND NR 1 SYSTEM WAS SHUT DOWN. POST-LANDING CHECK REVEALED HYDRAULIC FLUID LEAKING FROM T/R SERVO ACTUATOR.Sep 29, 1999 · Bell 212 · Rotorcraft Servo SystemSDR CA991103067Fitting · cracked(CAN) LOWER LEFT FITTING WAS FOUND CRACKED. TT 15,524 HOURS AND WAS POSSIBLY THE ORIGINAL FITTING. CRACK EXTENDED FROM FORWARD MOST RIVET HOLE .6250 INCH TO THE UPPER EDGE AND .75 INCH TO THE RADIUS OF THE 90 DEGREE ANGLE.Sep 6, 1999 · Bell 212 · Fuselage Miscellaneous Structure
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