# Pratt & Whitney PT6T-3 - Type: Engine model (FAA registry) - Registry code: 51520 - Manufacturer (registry): P & W - Model: PT6T-3 - Engine type: Turbo-shaft - Power: 900 hp - Data sheet: [TCDS E22EA](https://openairdocs.org/tcds/E22EA) (OpenAirDocs) - Holder: Pratt & Whitney Canada Corp. - Installed in: 1 registered aircraft - Page: https://openairdocs.org/engine/pratt-whitney-pt6t-3 Model codes come from the FAA registry's reference file. ## ADs that may apply (OpenAirDocs) Matched to this engine model by model name and maker. Each AD's applicability may narrow it by serial number, part number or equipment. - [AD 79-11-03](https://openairdocs.org/ad/79-11-03): Automatic Fuel Control · Pratt & Whitney Canada PT6T-3 and PT6T-6. Effective May 31, 1979 - [AD 78-17-05](https://openairdocs.org/ad/78-17-05): Automatic Fuel Control Unit · Pratt & Whitney Canada PT6T-3, PT6T-3A and PT6T-6. Effective Aug 31, 1978 - [AD 76-02-08](https://openairdocs.org/ad/76-02-08): Fuel Pump · Pratt & Whitney Canada PT6T-3, PT6T-3A and PT6T-6. Effective Feb 5, 1976 ## Registered aircraft (1) - [N359EH](https://openairdocs.org/aircraft/N359EH): [Tvpx Aircraft Solutions Inc Trustee](https://openairdocs.org/faa-owner/TVPX%20AIRCRAFT%20SOLUTIONS%20INC%20TRUSTEE), [North Salt Lake, UT](https://openairdocs.org/faa-place/UT/North%20Salt%20Lake), built 1972, S/N 30546 ## NTSB investigations (1) From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [NTSB WPR18LA242](https://openairdocs.org/ntsb/WPR18LA242), Aug 25, 2018: Bell 212 (N512TA), Dardanelle, CA, substantial damage. Probable cause: An in-flight failure of the trunnion bearing and subsequent failure of the drive link and swashplate support, which resulted in the loss of helicopter control. ## FAA accident and incident reports (1) From the FAA Accident/Incident Data System. Reports are matched to registry aircraft by N-number and event date, checked against the reported make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [Accident 20180825015309A](https://openairdocs.org/incident/20180825015309A), Aug 25, 2018: Bell 212 (N512TA), Dardanelle, CA, Destroyed. The helicopter was conducting water dropping activities in support of a U.S. Forest service fire fighting operation, under an exclusive use contract. A 150 ft… ## Service difficulty reports (421, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR 2026FA0000648](https://openairdocs.org/sdr/2026FA0000648), Aug 17, 2026: COUPLING. CRACKED. CRACKED AROUND METAL ON COUPLING - [SDR 2025FA0000642](https://openairdocs.org/sdr/2025FA0000642), Sep 12, 2025: STATIC INVERTER. OVERHEATED. THE CREW CAME OUT FOR A TRAINING FLIGHT, STARTED THE AIRCRAFT JUST FINE AND IDLED ON DECK FOR A FEW MINUTES. UPON TAKE OFF THE #1 INVERTER SWITCH TURNED ITSELF - [SDR RV1R2020010800019](https://openairdocs.org/sdr/RV1R2020010800019), Sep 30, 2019: ELASTOMER. FAILED. FAILED ELASTOMER FOUND DURING REMOVAL FOR MAST SEAL REPLACEMENT. THIS PART CAN ONLY BE INSPECTED WITH MR HUB DISASSEMBLED AND THE ONLY REQUIREMENT FOR THIS INSP - [SDR 2019FA0000239](https://openairdocs.org/sdr/2019FA0000239), Aug 1, 2019: BELLCRANK. LOOSE. THE HELICOPTER EXPERIENCED A TORQUE AND RPM FLUCTUATION SHORTLY AFTER TAKE-OFF. A FAULTY AUTOMATIC FUEL CONTROL UNIT WAS REPLACED. DURING THE ENGINE RIGGING PRO - [SDR CA190622001](https://openairdocs.org/sdr/CA190622001), Jun 14, 2019: AMPLIFIER. FAILED. (CAN) IT WAS REPORTED TO BELL:DURING BUCKETING OPERATIONS AT APPROX 300 FEET ABOVE GROUND LEVEL, THE PILOT OBSERVED THAT THE #2 ENGINE FIRE LIGHT HAD ILLUMINATE - [SDR QMLA2016072516085](https://openairdocs.org/sdr/QMLA2016072516085), Jul 25, 2016: WINDSHIELD. CRACKED. ON NR 1 ENGINE START UP THE CO-PILOT WINDSCREEN CRACKED APPROX. 28" ALONG THE LOWER EDGE. THE PILOT SHUT DOWN THE ENGINE AND WROTE UP THE DISCREPANCY. MECHANICS - [SDR CA160126003](https://openairdocs.org/sdr/CA160126003), Jan 25, 2016: HANGER ASSY. CRACKED. (CAN) CRACKS WERE FOUND ON EACH BOLT HOLE THAT CONNECTS THE TAIL ROTOR DRIVESHAFT HANGER BEARING AND COUPLING ASSY, PN 212-040-600-009 TO THE TAIL BOOM HANGER F - [SDR CA151110008](https://openairdocs.org/sdr/CA151110008), Nov 3, 2015: FILTER. FAILED. (CAN) DURING A ROUTINE 100 HR P3 FILTER INSPECTION THE ENGINEER REMOVED THE P3 FILTER FROM THE POWER SECTION AND NOTICED THE SCREEN MATERIAL HAD SEPARATED FROM - [SDR CA151103005](https://openairdocs.org/sdr/CA151103005), Oct 26, 2015: CARGO HOOK. FAILED. (CAN) INADVERTENT RELEASE OF A LOAD DURING LONGLINE OPERATION. SUSPECT THAT THE SWIVEL USED DID NOT OPERATE CORRECTLY AND IN TURN ALLOWED THE LONGLINE TO TWIST - [SDR CA150911005](https://openairdocs.org/sdr/CA150911005), Sep 2, 2015: ENGINE. POWER LOSS. (CAN) WHILE ON APPROACH THE ACFT LOST POWER FROM NR 2ENGINE. CREW MADE A EMERGENCY CALL OUT AND TOOK APPROPRIATE EMERGENCY ACTION TO STABILIZE THE FLIGHT FOR SI - [SDR CA150820005](https://openairdocs.org/sdr/CA150820005), Aug 12, 2015: FUEL CONTROL. MALFUNCTIONED. (CAN) ACFT WAS LANDING WHEN 1 OF ITS ENGINES LOST POWER. PILOT THEN LANDED THE ACFT UNEVENTFULLY. P3 LINE WAS FOUND BROKEN. THE TUBING WAS REPLACED AND ACFT RET - [SDR CA150727014](https://openairdocs.org/sdr/CA150727014), Jul 24, 2015: CLUTCH. SLIPPED. (CAN) ON HOIST OPERATION, THE RESCUE SPECIALIST REPORTED A SLIPPAGE FROM THE HOIST CABLE WHILE DESCENDING ON THE SITE. THE UNIT IS NOT INCLUDED IN THE LIST OF A - [SDR CA150709001](https://openairdocs.org/sdr/CA150709001), Jun 26, 2015: BEARING. SEPARATED. (CAN) THE QUALITY OF RIDE IN THE HELICOPTER DEGRADED AND THE HUMS SYSTEM ALSO HAD INDICATED AN ISSUE. DURING THE INVESTIGATION, IT WAS FOUND THAT THE PIVOT BEAR - [SDR CA150710012](https://openairdocs.org/sdr/CA150710012), Jun 25, 2015: ENGINE. FAILED. (CAN) DURING APPROACH AT 400-500 FT ALTITUDE, PILOT HEARD A BANGING SOUND, NR 2 ENGINE OIL PRESSURE DROPPED, TEMPERATURE WAS RAISING, CHIP LIGHT ILLUMINATED. PI - [SDR CA150529005](https://openairdocs.org/sdr/CA150529005), May 27, 2015: CROSSTUBE. BROKEN. (CAN) CROSS TUBE BROKE AT LT AIRFRAME SUPPORT, UNDER THE STEEL WEAR PLATES. - [SDR CA150602010](https://openairdocs.org/sdr/CA150602010), May 16, 2015: ENGINE. OVERTEMP. (CAN) REPORTED THAT DURING A TRAINING FLIGHT, ENGINE NR 1 OVERTEMPED WHEN GOVERNOR WAS SWITCHED FROM AUTO TO MAN WITH N1 AT 70 PERCENT. GROUND INSPECTION PERFOR - [SDR CA150325021](https://openairdocs.org/sdr/CA150325021), Mar 19, 2015: PACKING. LEAKING. (CAN) DURING A ROUTINE PASSENGER FLIGHT, AT FULL THROTTLE, AN OIL PRESSURE CAUTION WARNING CAME ON FOLLOWED BY AN ITT SURGE ABOVE 900 DEG C. CREW ELECTED TO SHU - [SDR CA141202017](https://openairdocs.org/sdr/CA141202017), Nov 8, 2014: COMPRESSOR. DAMAGED. (CAN) ACFT CAME BACK FROM A FLIGHT FOR REFUEL. ENGINE START AFTER THE REFUEL WAS OK. AS THE PILOT STARTED PULLING THE COLLECTIVE, THE LT PS WAS SURGING/VIBRATIO - [SDR CA141202002](https://openairdocs.org/sdr/CA141202002), Nov 3, 2014: ENGINE. MAKING METAL. (CAN) BEFORE TAKEOFF, PILOT REPORTED THAT THE CHIP DETECTOR CAUTION LIGHT WAS ILLUMINATED, THUS THE PILOT PROCEEDED TO SHUTDOWN THE ENGINE AND THE FLIGHT WAS AB - [SDR 9EKA20141030012](https://openairdocs.org/sdr/9EKA20141030012), Oct 29, 2014: OIL COOLER. CRACKED. DURING 1000 HOUR INSPECTION OF OIL COOLERS MULTIPLE CRACKS ON VANE WELDS WERE FOUND. - [SDR CA140917001](https://openairdocs.org/sdr/CA140917001), Sep 16, 2014: PRESSURE SWITCH. LEAKING. (CAN) DURING POST FLIGHT INSPECTION NR 1 ENGINE DECK WAS FOUND TO HAVE FOIL/OIL RESIDUE ON IT BUT NO SOURCE OF THE LEAK WAS FOUND. WITH THE INDUCTION COWL REMOV - [SDR CA140908028](https://openairdocs.org/sdr/CA140908028), Sep 4, 2014: YOKE. UNSERVICEABLE. (CAN) DURING THE DAILY INSPECTION IT WAS NOTICED THAT 1 TAIL ROTOR YOKE FEATHERING BEARING OUTER RACE STAKE HAD FAILED. UPON FURTHER INVESTIGATION ALL 4 TAIL RO - [SDR CA140721023](https://openairdocs.org/sdr/CA140721023), Jul 19, 2014: FITTING. CRACKED. (CAN) WHILE PERFORMING A DAILY INSPECTION OF THE ACFT, THE AME NOTICED A THIN BLACK LINE ON THE OUTER END OF THE DRAG BRACE FITTING. AFTER FURTHER INVESTIGATION - [SDR CA140716009](https://openairdocs.org/sdr/CA140716009), Jul 13, 2014: CROSSTUBE. CRACKED. (CAN) PILOT ON FIRE FIGHTING OPERATIONS HEARD LOUD SNAP SOUND ON LANDING AND ABORTED THE TAKE-OFF. HIGH FORWARD CROSSTUBE FOUND CRACKED OTBD OF LT SADDLE FITTIN - [SDR CA140710003](https://openairdocs.org/sdr/CA140710003), Jul 8, 2014: TORQUE TUBE. SHEARED. (CAN) DURING A NORMAL APPROACH OF 75% TORQUE THE PILOT NOTICED THE MAST TORQUE INCREASE TO OVER 110% WHILE THE ENGINE TORQUES REMAINED UNCHANGED. HE LANDED IN A - [SDR CA140701013](https://openairdocs.org/sdr/CA140701013), Jun 28, 2014: OIL SYSTEM. FAILED. THE ENGINE NR 2 LOST OIL IN FLIGHT. THE PILOT PERFORMED AN IFSD OF ENGINE NR 2 AND AN UNEVENTFUL EMERGENCY LANDING WITH 1 ENGINE INOPERATIVE (OEI). ON GROUND TR - [SDR SAJF2014062603020](https://openairdocs.org/sdr/SAJF2014062603020), Jun 16, 2014: ENGINE. LEAKING. DURING FLIGHT AFTER 5 HOURS AFTER TAKEOFF, THE PILOT OBSERVED LOW OIL QTY ON NR 2 ENG & NORMAL OIL PRESS WAS MAINTAINED. AFTER INTERVAL DISCUSSION, PILOT CHOSE - [SDR CA140602018](https://openairdocs.org/sdr/CA140602018), May 8, 2014: GEARBOX. MAKING METAL. (CAN) THE PILOT SHUTDOWN THE ENGINES AND ABORTED THE TAKEOFF DUE TO A CHIP DETECTOR INDICATION ON THE COMBINING GEARBOX. - [SDR CA140826021](https://openairdocs.org/sdr/CA140826021), Mar 23, 2014: COTTER PIN. OBSTRUCTED. (CAN) DURING A TRAINING FLIGHT, PILOTS NOTICED THAT ENGINE NR 2 FAIL WARNING LIGHT APPEARED. ITT WAS 136 CELSIUS. PILOTS STARTED EMERGENCY PROCEDURE AND THE HEL - [SDR CA140305006](https://openairdocs.org/sdr/CA140305006), Mar 5, 2014: BEARING. FAILED. (CAN) ON A COMBINING GEAR BOX REMOVAL, AME NOTICED A LARGE AMOUNT OF BLACK FRETTING MATERIAL BETWEEN THE C BOX AND BLOWER JOINT FLANGE. ONCE CLEANED UP THE AME - [SDR CA140224024](https://openairdocs.org/sdr/CA140224024), Feb 13, 2014: BEARING. FAILED. (CAN) ON C BOX REMOVAL THE OIL COOLER BLOWER ON NR 2 SIDE HAD BOTH FWD AND REAR BEARINGS BEGINNING TO FAIL. GREASE HAD BEEN EJECTED FROM FWD BEARING ALONG WITH - [SDR CA131216016](https://openairdocs.org/sdr/CA131216016), Dec 13, 2013: FRAME. CRACKED. (CAN) WHILE SCHEDULED MAINTENANCE WAS CARRIED OUT ON THE STABILIZER BAR, THE CENTER FRAME WHICH HAS 111.3 HRS REMAINING TO IT`S SCHEDULED RETIREMENT LIFE OF 10, - [SDR CA131216002](https://openairdocs.org/sdr/CA131216002), Dec 3, 2013: COUPLING. LOOSE. (CAN) THE PILOT REPORTED THAT BOTH POWER SECTION CHIP LIGHTS CAME ON IN FLIGHT. HE DECLARED AN EMERGENCY AND LANDED. MAINTENANCE FOUND A LITTLE FUZZ ON BOTH CHI - [SDR CA131118006](https://openairdocs.org/sdr/CA131118006), Nov 5, 2013: GEAR. FAILED. (CAN) THE ACFT RETURNED TO BASE WITHOUT COMPLETING ITS MISSION DUE TO ENGINE NR 2 CHIP WARNING. THE AFFECTED POWER SECTION WAS APPARENTLY SHUTDOWN. POST FLIGHT - [SDR CA131007008](https://openairdocs.org/sdr/CA131007008), Sep 29, 2013: FUEL HEATER. LEAKING. (CAN) SIGNIFICANT FUEL LEAK NOTED ON NR 1 ENGINE DURING GROUND OPERATIONS. LEAK CONFIRMED AS CRACKED WELD ON OIL TO FUEL HEATER. - [SDR CA130920017](https://openairdocs.org/sdr/CA130920017), Sep 20, 2013: BEARING. BROKEN. (CAN) UPON DISASSEMBLY OF POWER TURBINE, THE NR 4 MAIN BEARING WAS FOUND WITH 2 OF THE 4 MOUNTING CORNERS BROKEN OFF AND A 3RD CRACKED. THERE WAS SOME WEAR ON T - [SDR CA130911017](https://openairdocs.org/sdr/CA130911017), Sep 4, 2013: ENGINE. SHUTDOWN. (CAN) JUST AFTER TAKEOFF, THE PILOT ELECTED TO PERFORM AN ENGINE SHUTDOWN. THE REASON OF THE FORCED ENGINE SHUTDOWN IS UNKNOWN. - [SDR CA131104006](https://openairdocs.org/sdr/CA131104006), Jul 23, 2013: BEARING. WORN. (CAN) POWER SECTION WAS REMOVED FROM OPERATORS ACFT DUE TO METAL GENERATION. THIS ENGINE HAD A TSN OF 1415.93 AND WAS IN FOR ITS FIRST SHOP VISIT SINCE MFG. THE - [SDR CA130815004](https://openairdocs.org/sdr/CA130815004), Jul 20, 2013: ROD END. WORN. (CAN) BEARING LINER GONE, EXCESSIVE WEAR BETWEEN BALL AND BEARING OUTER HSG. - [SDR CA130726004](https://openairdocs.org/sdr/CA130726004), Jul 19, 2013: BLADE. DEBONDED. (CAN) WHILE CARRYING OUT A 25 HOUR INSPECTION, PERFORMED A TAP TEST WITH A BELL TAP HAMMER, FOUND THE EROSION STRIP PARTIALLY DEBONDED. TAIL ROTOR HUB AND BLADE - [SDR CA130410013](https://openairdocs.org/sdr/CA130410013), Apr 10, 2013: FUEL LINE. CHAFED. (CAN) DURING A AFCU REPLACEMENT ON NR 1 ENGINE, THE FUEL TUBE, FROM AFCU TO MFCU WAS FOUND CHAFING ON BRAKET, PN 412-060-024-101, PARTS OF TB 212-11-211. - [SDR CA130416012](https://openairdocs.org/sdr/CA130416012), Apr 4, 2013: ENGINE. SHUTDOWN. (CAN) IN PREPARATION OF THE ENGINE SHUTDOWN, ENGINES THROTTLES WERE BROUGHT DOWN TO FLIGHT IDLE, APPROXIMATELY 80 PERCENT NR, ALLOWING FOR COOLING PERIOD. ALL O - [SDR CA130327004](https://openairdocs.org/sdr/CA130327004), Mar 18, 2013: INVERTER. FAILED. (CAN) DURING A TRAINING FLIGHT THE INVERTER FAILURE NR 2 WARNING LIGHT CAME ON. AT APPROXIMATELY THE SAME TIME SMOKE WAS DETECTED IN THE CABIN. EMERGENCY WAS DE - [SDR CA130128024](https://openairdocs.org/sdr/CA130128024), Jan 28, 2013: WIRE. CHAFED. (CAN) PILOT REPORTED LATERAL CYCLIC IMPULSES FELT IN ALL FLIGHT REGIMES WITH AUTO PILOT SELECTED ON ONLY. EXTENSIVE TROUBLESHOOTING WAS CARRIED OUT OVER A 3 WEE - [SDR CA130117002](https://openairdocs.org/sdr/CA130117002), Dec 31, 2012: BLADES. BROKEN. (CAN) AFTER TAKING OFF FROM HELIPAD AT 400 FT ABOVE GROUND LEVEL, AN ABNORMAL NOISE SIMILAR TO ENGINE SURGE NOISE WAS HEARD BY PILOTS FOLLOWED BY ODOR OF FUEL I - [SDR CA121206003](https://openairdocs.org/sdr/CA121206003), Dec 4, 2012: FITTING. WORN. (CAN) UPON PURGING WITH GREASE OF THE MAIN ROTOR GRIP IT WAS NOTICED THAT GREASE WOULD NOT COME OUT OF THE VENT FITTING AT THE TOP OF THE GRIP. THE ROTOR HUB WA - [SDR CA121115006](https://openairdocs.org/sdr/CA121115006), Nov 10, 2012: LINK. FAILED. (CAN) DURING 600 HR INSPECTION OF ACFT, LIFT LINK BEARINGS WERE FOUND SPINNING WITHIN BORE. OEM HAS NO REQUIRED INSPECTION OF THIS COMPONENT AND THIS IS NOT AN - [SDR CA121022005](https://openairdocs.org/sdr/CA121022005), Sep 27, 2012: LINE. BROKEN. (CAN) THIS HELICOPTER HAS EXPERIENCED ITS SECOND BROKEN P3 AIR LINE, IN 600 HOURS ON ENGINE NR 1. THE PREVIOUS EVENT WAS WITH PS TH0727 IN THE SAME POSITION ON - [SDR CA120824003](https://openairdocs.org/sdr/CA120824003), Aug 22, 2012: TRANSISTOR. FAILED. (CAN) WHEN THE DIM FUNCTION ON THE CONSOLE IS UTILIZED FOR THE INSTRUMENT LIGHTING, THE CIRCUIT BREAKER TRIPS. TRANSISTOR, PN 130-007-1 USED IN THE SYS HAS FOUN - [SDR CA120808006](https://openairdocs.org/sdr/CA120808006), Jul 30, 2012: BEARING CAGE. MAKING METAL. (CAN) MIDDLE BEARING OUTTER RACE SPALLING. BEARING CAGE BROKEN. All 421: https://openairdocs.org/engine/pratt-whitney-pt6t-3/reports.md ## STCs that may be installed (OpenAirDocs) (3) Approved for this engine model: the STC's model list names it on its data sheet, or a series that includes it. In force first, then newest. The registry doesn't record which STCs an aircraft has. - [STC SE1123GL](https://openairdocs.org/stc/SE1123GL): Installation of a Shadin Co Digital Fuel Flow Transducer. Shadin Avionics - [STC SE00022EN](https://openairdocs.org/stc/SE00022EN): Installation of Oil Tank Filler Neck Check Valve. Helicopter Support Inc Services Div - [STC SE659NE](https://openairdocs.org/stc/SE659NE): Installation of oil tank filler neck check valve, P/N TSA-76A. Aviation Components Support --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.