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 CA041123008Line · broken(CAN) LINE BROKE. A/C RETURNED TO BASE. LINE WAS REPLACED. A/C WAS RETURNED TO SERVICE. NO FURTHER DEFECTS.SDR CA040928016Line · broken(CAN) UNCOMANDED DECEL TO IDLE. PART CHANGED, ENGINE RETURNED TO NORMAL OPS.SDR CA040812003Bulkhead · cracked(CAN) BULKHEAD FRAME CRACKED ADJACENT TO RT UPPER TAILBOOM ATTACH BOLT. FRAME REPLACED.SDR CA040812006Angle · corroded(CAN) DURING IMPORT INSPECTION, RT FUEL CELL CAVITY AFT CAP ANGLE FOUND BADLY CORRODED (EXFOLIATION). PART REPLACED.SDR EHA2004F00003Line · chafedHYDRAULIC LEAK FROM AREA OF CARGO HOOK. TRACED TO TAIL ROTOR SAS LINK HYDRAULIC LINE CHAFED BY FUEL VENT LINE. REPLACED LINE, REROUTED AND SECURED FUEL VENT LINE. LEAK CHECKED AND MOC FLIGHT GOOD. (AL03200404250)SDR CA041123011Case · broken(CAN) PILOT REPORTED HEARING A LOUD BANG AND THOUGHT PIECES OF THE HELICOPTER FELL FROM THE BELLY. PILOT WAS FLYING VERTICAL REFERENCE WITH A BAMBI BUCKET. UPON IMMEDIATE RETURN TO THE PAD, THE HELL HOLE SIDE INSPECTION PANELS WERE REMOVED AND THE SUPPORT CASDR CA041123012Fuel Cell · split(CAN) LOW FUEL LIGHT COMING ON WITH 250-300 LBS INDICATED IN LT LOWER FUEL CELL. INVESTIGATION FOUND SPLIT IN FUEL CELL INTERNALLY ACROSS BAFFLE, WHICH ACTED LIKE A ONE WAY VALVE. THIS WOULD PUMP FUEL AWAY FROM BOOST PUMP WHEN A/C IS IN UNUSUAL ATTITUDES (HOVSDR CA040716004Control Unit · malfunctionedGENERATOR WOULDN'T COME ONLINE, NR 1 AND NR 1 SWAPPED FOR TROUBLESHOOTING, CONTROL CONFIRMED TO BE AT FAULT. CONTROL UNIT REPLACED, GENERATOR BALANCING C/O AND A/C RETURNED TO SERVICE. THIS UNIT CONTAINED WATER WHEN REMOVED.SDR CA040726009Support · cracked(CAN) PILOT REPORTED THAT THE AIRCRAFT WOULD ENTER INTO PYLON ROCK VERY EASILY. TRANSMISSION MOUNTS AND FRICTION DAMPERS WERE BEING REPLACED WHEN IT WAS FOUND THAT THE FRICTION DAMPER MOUNT SUPPORTS WERE CRACKED AND AS A RESULT NOT ATTACHED TO THE AIRFRAME. SUSDR HEEA096019Fuel Control · malfunctionedIN CRUISE FLIGHT, THE NR 1 ENGINE OUT LIGHT CAME ON, TORQUES SPLIT WITH NR 1 ENGINE LOW, RPM LIGHT CAME ON, LOW AUDIO CAME ON, CYCLIC CENTERING LIGHT CAME ON, AND NR 1 ENGINE N1 WENT TO 40 PERCENT. FOLLOWED CHECK LIST FOR LOW SIDE FUEL CONTROL FAILURE AND LASDR CA050616007Washer · unserviceable(CAN) CONICAL WASHER FOR TRANSMISSION MOUNT BOLT - LT AFT POSITION - FOUND CRACKED. CRACK HAD NOT TRAVELLED COMPETELY THROUGH WASHER, IT HAD STARTED AT OUTBOARD EDGE. WASHER REPLACED.SDR CA040428001Access Door · cracked(CAN) DURING THE DAILY INSPECTION THE COWL INSPECTION DOOR HINGE WAS FOUND LOOSE ALLOWING THE DOOR TO HANG DOWN. UPON REMOVAL OF THE COWLING IT WAS FOUND THAT THE ATTACH FLANGE FOR THE COWL ACCESS DOOR HINGE WAS CRACKED ACROSS 75 PERCENT OF THE FLANGE LENGTH. SDR CA040422004Grip · broken(CAN) DURING ROUTINE GREASING AND SERVICING OF MAIN ROTOR COMPONENTS AME ATTEMPTED TO MOVE THE PILOT'S CYCLIC STICK. AS THE MOVEMENT WAS ATTEMPTED, THE GRIP BROKE INTO TWO PIECES. THE FRACTURE OCCURRED BETWEEN THE FORCE TRIM RELEASE SWITCH AND CARGO RELEASE SDR CA040407010Pivot Assy · damaged(CAN) ADJUSTABLE PIVOT HAD MOST OF THE ADJUSTMENT SLOT BROKEN AWAY. PREVIOUS REPAIRER HAD 'FIXED' THE PROBLEM BY FLOODING THE AREA WITH EPOXY TO STOP THE PIVOT FROM ROTATING. THE RETAINING SCREW HAD INSUFFICIENT MATERIAL TO HOLD THE PIVOT AS DESIGNED.SDR CA040407011Tape · improper part(CAN) ADHESIVE BACKED LEAD TAPE HAD BEEN USED TO BALANCE THE PITCH ERECTION VANES. IAW MANUFACTURER'S SERVICE ADVISORY NR 75, DATED JANUARY 25, 1985, LEAD TAPE SHOULD NOT BE USED TO BALANCE AIM GYROS AS IT CAN FALL OFF AND CAUSE THE GYRO TO BECOME INOPERATIVESDR CA040318001Ring · burned(CAN) DURING ROUTINE HOT END BORESCOPE INSPECTION, HOT END DISTRESS WAS NOTED. POWER SECTION REMOVED FROM AIRCRAFT, HOT END REMOVED. COMBUSTION CHAMBER CRACKED (MANY) ON NR 2 LOUVERED COOLING RING. SMALL DUCT BURNED/WARPED IN TWO AREAS (VANES). VANE RING ASSDR CA040318003Coupling · corroded(CAN) DRIVESHAFT UNDERGOING SCHEDULED 600 HR/12 MONTH INSPECTION/LUBRICATION. COUPLING HAS EXCESSIVE CORROSION. PART REPLACED. COUPLING P/N 212-040-688-3.SDR CA040301007Bearing · disintegrated(CAN) VISUAL INSPECTION REVEALED BEARING RETAINING FAILURE. APRROXIMATELY ONE QUARTER OF RETAINER MISSING. WILL SEND TO PWC FOR EXAMINATION.SDR HEEA093677Pressure Switch · fluctuatesDURING CRUISE FLIGHT THE COMBINING GEARBOX OIL PRESSURE FLUCTUATED, LANDED. MAINTENANCE REPLACED THE OIL PRESSURE TRANSDUCER.SDR CA040203005Tube · cracked(CAN) DURING THE SCHEDULED INSPECTION CARRIED OUT THE BASE, THE AME NOTICED THAT THE TUBE P/N 3023724 WAS CRACKED BEHIND THE B-NUT AREA. THE CRACKED TUBE WAS REMOVED AND REPLACED.SDR ERAA092668Sun Gear · corrodedUPPER SUN GEAR WITH ONLY 143.1 HRS HAS NITRITING BREAKING DOWN, TEETH FRETTING AND PITTING. RETURNING ON ERA MMIR NR ERAA0001972 REQUESTING CREDIT.SDR CA040113006Bolt · sheared(CAN) HELISKI OPERATION. PILOT REPORTED BAD VIBRATION IN TURNS AND CONTROLLABILITY CONCERNS, ALSO IN TURNS. RETURNED TO BASE IMMEDIATELY. SHEARED BOLT FOUND WHERE MAIN ROTOR HYDRAULIC DAMPER CONTROL ARM ATTACHES TO STABILIZER BAR CONTROL TUBE ROD END. BOLT WASSDR CA031210008Connector · cracked(CAN) DIAPHRAGM BROKEN AND LEAKING AROUND PINS ON ELECTRICAL HARNESS.SDR AUS20031221Engine · noisy(AUS) ENGINE POWER SECTION REMOVED DUE TO UNKNOWN NOISE.SDR CA031128006Plenum · contaminated(CAN) WATER ENTERED IN PLENUM CHAMBER OF CABIN AIR INTAKE OVERFLOWED ONTO CEILING INSULATION CAUSING ELECTRICAL ARCING.SDR CA031110002Bushing · incorrect(CAN) TWO PITCH HORNS WERE IN FOR REPAIR, ONE HAD BUSHINGS IN HOLES AND BOTH HAD ODD SERIAL NUMBERS. WE CONTACTED OEM AND THEY SAID THAT THE BUSHED HOLES WOULD NOT BE APPROVED BY THEM. AS FOR THE SERIAL NUMBERS, ONE COULD NOT BE CONFIRNED AS BEING MADE BY MSDR EHA2004F00000Quill Assy · worn27 MINUTES INTO THE FLIGHT, STRAIGHT AND LEVEL, TQ 85 PERCENT, ALT 5700 FT, THE TRANSMISSION CHIP LIGHT ILLUMINATED. MIDDLE CAT EYE WAS WHITE. TURNED AROUND, REDUCED POWER TO 65 PERCENT AND RETURNED WITHOUT FURTHER NOTICE.SDR HEEA090147Servo · bindingFIVE MILES SOUTH OF MORGAN CITY STARTED HAVING TROUBLE WITH THE TRIM. LANDED AT MORGAN CITY. MAINTENANCE FOUND THE TAIL ROTOR SERVO BINDING. REPLACED SERVO.SDR CA030915013Panel · delaminated(CAN) THIS WAS FOUND ON A DAILY INSPECTION. THE TAILBOOM HELICOMB PANEL WAS DELAMINATED JUST AFT OF THE BAGGAGE COMPARTMENT. THIS AIRCRAFT WAS ON FIRES, DOING LOTS OF HOVERING WHICH MAY HAVE CONTRIBUTED TO THE DELAMINATION DUE TO HOT EXHAUST HITTING IT.SDR CA040413005Turbine Wheel · damaged(CAN) WHEN THROTTLES WERE ROLLED TO IDLE FOR COOL DOWN A LOW GROWL WAS HEARD AT IDLE. ENGINES WERE SPUN UP TO 100 PERCENT AND GROWL WENT AWAY. BOTH ENGINES WERE BROUGHT BACK TO IDLE AND NOISE WAS HEARD AGAIN. ENGINES WERE SPOOLED UP SEPARATELY AND PROBLEM WASDR CA031110007Blade · broken(CAN) THE AIRCRAFT WAS ENGAGED IN FIRE FIGHTING DUTIES WHEN ENGINE VIBRATION WAS FELT. ALL AIRCRAFT SYSTEMS WERE IN NORMAL, OPERATIONAL AND PERFORMANCE LIMITS. SUBSEQUENT TROUBLESHOOTING OF THE POWER SECTION WAS COMPLETED AND THE POWER SECTION WAS REMOVED FRSDR CA030828001Hose · ruptured(CAN) DURING FLIGHT THE PILOT NOTICED A LOSS OF HYD PRESSURE ON NR 1 HYDRAULIC SYSTEM. THE SYSTEM WAS DEACTIVATED AND THE PILOT RETURNED TO BASE. AFTER LANDING, SYSTEM NR 1 WAS INSPECTED AND A HYD PRESSURE HOSE WAS FOUND RUPTURED. THE HOSE ASSEMBLY WAS REPLACSDR AUS20030816Ring · loose(AUS) SWASHPLATE INNER RING LOOSE. INVESTIGATION FOUND GIMBAL BOLTS PNO 212-011-463-001 STEPPED AND BUSHING PNO 204-010-496-003 MOVING IN INNER RING HOLE. HOLE HAD BEEN ENLARGED BY APPROXIMATELY 0.762MM(0.030IN). SUSPECT CAUSED BY EXCESSIVE USE OF SEALANT ON BSDR CA031110006Piston Rod · severed(CAN) ON AIRCRAFT APPROACH FOR LANDING, AIRFRAME VIBRATION WAS FELT. UPON LANDING AIRCRAFT WAS GROUND ROCKING. REDUCTION OF ENGINE THROTTLES INCREASED GROUND ROCK AND AIRFRAME VIBRATION. THROTTLES SHUT-OFF AND ROTOR BRAKE APPLIED, UPON BRAKING M/R BLADE SWEPSDR AUS20030759Pinion Gear · cracked(AUS) MAIN ROTOR BRAKE QUILL PINION GEAR CRACKED FOR APPROXIMATELY 75 PERCENT ACROSS GEAR FACE. TRANSMISSION CHIP DETECTOR ACTIVATED. INSPECTION OF CHIP DETECTOR AND FILTER FOUND NO SIGNIFICANT CONTAMINATION.SDR AUS20030817Gearbox · making metal(AUS) REDUCTION GEARBOX OIL FILTER CONTAMINATED WITH FINE METAL PARTICLES.SDR CA030731020Hose · ruptured(CAN) TRANSMISSION OIL HOSE SWOLLEN AND BLOWN APPROX.6 INCHES FROM FITTING.PILOT HAD LOW OIL PRESSURE WARNING LIGHTCOME ON AND CARRIED OUT PRECAUTIONARY LANDING TO INVESTIGATE. HOSE IS SUBJECT TO TENSION AND TORSION AS TRANSMISSION IS MOUNTED WITH LORD RUBBER SDR CA030825008Attach Fitting · broken(CAN) DURING CRUISE FLIGHT THE CREW FELT A (POP) ON THE AIRCRAFT WITH NO OTHER INDICATIONS. NO WARNING LIGHTS, NO CONTROL OR HANDLING PROBLEMS. AFTER LANDING, THE ENGINEER CARRIED OUT HIS ROUTINE (BEFORE FLIGHT) INSPECTION. LOOKING AT THE TAILBOOM TO FUSELAGESDR CA030731019Blade · fractured(CAN) COMPRESSOR TURBINE BLADE FRACTURED CAUSING COMPLETE ENGINE FAILURE AT APPROX. 40KNOTS FORWARD AIRSPEED, PILOT CARRIED OUT EMERGENCY LANDING.ENGINE REMOVED FOR EXAMINATION BY PWC.SDR CA031028009Compressor · failed(CAN) ENGINE FAILURE, ENGINE FIRE, FIRE EXTINGUISHED. - AIRCRAFT LANDED SINGLE ENGINE.SDR CA030708013Line · ruptured(CAN) THE PILOT REPORTED A NOISE (FROM AN UNLOADED HYDRAULIC PUMP) FOLLOWED BY THE ODOR OF HYD FLUID. HYDRAULIC PRESSURE ON SYSTEM NUMBER 2 DROPPED TO ZERO. THE PILOT INITIATED AN UNSCHEDULED LANDINGTO INVESTIGATE THE PROBLEM. AFTER LANDING A CHAFED HYD LINESDR CA030625001Elbow · cracked(CAN) A HYD LEAK WAS FOUND DURING A GROUND RUN TO CHECK FOR LEAKS AFTER MINOR MAINTENANCE. THE ENGINEER NOTICED HYD FLUID DRIPPING FROM AN ELBOW FITTING ON THE NR 1 HYD PUMP. THE FITTING AND LINE B-NUT WERE CHECKED AND FOUND SECURE. THE FITTING WAS REMOVED ANDSDR HEEA087814Interphone · inoperativeCOPILOT ICS BOX IS NOT RECEIVING. SHOP REPAIR.SDR HEEA087813Interphone · inoperativeINTERPHONE BOX, NO SIDE TONE. SHOP REPAIR.SDR CA030710002Blade · failed(CAN) VOID IN S.S. LEADING EDGE STRIP OUTBOARD BLADE TIP JUNCTION OF BLADE SKIN. VOID AREA APPROXIMATELY 0.175 INCH CHORDWISE X 0.375 INCH SPANWISE. BLADE REMOVED AND SENT FOR REPAIR. SN A-7719.SDR AGQA088682Contactor · brokenINTERMITTENT, SLOW STARTS, CONTACTOR.SDR CA030530001Link · broken(CAN) AFTER THE FLIGHT AN INSPECTION OF THE AIRCRAFT IT WAS DETERMINED THAT PART OF THE LIFT LINK HAD BROKEN OFF NEAR THE UPPER STAKED BEARING BOSS. THE CAUSE OF THE BROKEN PIECE UNDETERMINED AT THIS TIME, INVESTIGATION IS ON GOING.SDR CA030613009Case · broken(CAN) WHILE CARRYING OUT A DAILY CHECK ON THE AIRCRAFT THE ENGINEER NOTICED THAT THE ONE EAR OF THE LIFT LINK SUPPORT ON THE TRANSMISSION SUPPORT CASE WAS BROKEN OFF. THE TRANSMISSION SUPPORT CASE WAS REPLACEDSDR ERAA087082Servo · vibrationTAIL ROTOR SERVO HAS HIGH FREQ BUZZ IN TAIL ROTOR PEDALS WITH HYD SYSTEM TURNED ON. HAS CYLINDER WEAR, INTERNAL LEAKAGE ON PILOT VALVES REPLACED CYLINDER AND PILOT VALVES TESTED IAW CMM.SDR CA030708010Shaft · stripped(CAN) DURING ATTEMPTED DISASSEMBLY, WE WERE UNABLE TO REMOVE THREADED SLEEVE PN 209011719003. FOUND INCORRECT HARDWARE STARKUP (WASHER PN 212010714003 MISSING). PRESUME SLEEVE BOTTOMED OUT, NUT MS14145L8 ALSO, AND HENCE THREADS STRIPPED ON TORQUE UP. HAD TO H
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