# Alliedsign TFE731-40 - Type: Engine model (FAA registry) - Registry code: 02519 - Manufacturer (registry): ALLIEDSIGN - Model: TFE731-40 - Engine type: Turbo-fan - Power: 4,250 lb thrust - Data sheet: [TCDS E1NM](https://openairdocs.org/tcds/E1NM) (OpenAirDocs) - Holder: Honeywell Aerospace US LLC - Installed in: 6 registered aircraft - Page: https://openairdocs.org/engine/alliedsign-tfe731-40 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 2019-05-07](https://openairdocs.org/ad/2019-05-07): Turbine Engine Compressor Section · Honeywell International TFE731-20AR, TFE731-20BR, TFE731-20R and 4 more. Effective Apr 25, 2019 - [AD 2014-12-52](https://openairdocs.org/ad/2014-12-52): Engines · Honeywell International TFE731-20AR, TFE731-20BR, TFE731-20R and 11 more. Effective Jul 28, 2014 - [AD 2012-16-14](https://openairdocs.org/ad/2012-16-14): LPT2 rotor blades · Honeywell International TFE731-20AR, TFE731-20BR, TFE731-20R and 5 more. Effective Oct 1, 2012 - [AD 2008-02-19](https://openairdocs.org/ad/2008-02-19): High pressure (HP) turbine rotor assemblies · Honeywell International TFE731-20AR, TFE731-20BR, TFE731-20R and 15 more. Effective Mar 6, 2008 Historical (superseded or no longer in force): - [AD 2017-20-01](https://openairdocs.org/ad/2017-20-01) (historical): Turbine Engine Compressor Section · Honeywell International TFE731-20 and TFE731-40. Effective Nov 2, 2017 ## Registered aircraft (6) - [N136MV](https://openairdocs.org/aircraft/N136MV): [Transnet Aviation Group LLC](https://openairdocs.org/faa-owner/TRANSNET%20AVIATION%20GROUP%20LLC), [Short Hills, NJ](https://openairdocs.org/faa-place/NJ/Short%20Hills), built 2001, S/N 311 - [N291FJ](https://openairdocs.org/aircraft/N291FJ): [Nhs Management LLC](https://openairdocs.org/faa-owner/NHS%20MANAGEMENT%20LLC), [Tuscaloosa, AL](https://openairdocs.org/faa-place/AL/Tuscaloosa), S/N 291 - [N299PR](https://openairdocs.org/aircraft/N299PR): [Meregrass Inc](https://openairdocs.org/faa-owner/MEREGRASS%20INC), [Dublin, TX](https://openairdocs.org/faa-place/TX/Dublin), built 2000, S/N 299 - [N50YT](https://openairdocs.org/aircraft/N50YT): [International Aviation Technical Services Inc](https://openairdocs.org/faa-owner/INTERNATIONAL%20AVIATION%20TECHNICAL%20SERVICES%20INC), [Torrance, CA](https://openairdocs.org/faa-place/CA/Torrance), built 1996, S/N 269 - [N68YB](https://openairdocs.org/aircraft/N68YB): [Czzc Aviation LLC](https://openairdocs.org/faa-owner/CZZC%20AVIATION%20LLC), [Tucson, AZ](https://openairdocs.org/faa-place/AZ/Tucson), built 1999, S/N 290 - [N763PP](https://openairdocs.org/aircraft/N763PP): [Top Air Texas LLC](https://openairdocs.org/faa-owner/TOP%20AIR%20TEXAS%20LLC), [Glendale, CA](https://openairdocs.org/faa-place/CA/Glendale), built 1999, S/N 278 ## NTSB investigations None matched to aircraft with this engine model. ## FAA accident and incident reports None matched to aircraft with this engine model. ## Service difficulty reports (85, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR FVJA202505287730](https://openairdocs.org/sdr/FVJA202505287730), May 20, 2025: PUMP. FAULTED. ENGINE OIL PRESSURE CLIMBED INTO RED ZONE ON INDICATOR AND WOULD NOT RESPOND TO THROTTLE CHANGES. PAX REPORTED EVIDENCE OF SMOKE IN THE CABIN. CREW SHUT DOWN EN - [SDR 2020FA0000521](https://openairdocs.org/sdr/2020FA0000521), Nov 2, 2020: OIL SYSTEM. MALFUNCTIONED. WE HAD TO MANUALLY SHUT THE LEFT ENGINE DOWN TO 616KK. ON DECENT THROUGH THE MID 30'S, WE BEGAN TO EXPERIENCE A LEFT ENGINE PRESSURE SWING VARYING BETWEEN OVER - [SDR BONA20201002001](https://openairdocs.org/sdr/BONA20201002001), Sep 29, 2020: FIRE LOOP. FALSE INDICATION. DURING CLIMBOUT AT APPROXIMATELY 42,000 FEET, CREW OBSERVED A LT ENGINE FIRE WARNING. THEY REDUCED POWER ON THE AFFECTED ENGINE AND THE WARNING CLEARED WITHOUT - [SDR CA151208006](https://openairdocs.org/sdr/CA151208006), Dec 4, 2015: PUMP. LEAKING. (CAN) LOSS OF MAIN HYDRAULIC SYSTEM PRESSURE. NEITHER ENGINE DRIVEN PUMP WERE ABLE TO MAINTAIN SYSTEM PRESSURE. UPON INSPECTION, FOUND BOTH PUMPS TO HAVE LEAKAG - [SDR CA150924006](https://openairdocs.org/sdr/CA150924006), Sep 24, 2015: LEVER. UNSECURE. (CAN) A SPECIAL INSPECTION OF THE SPOILER RVDT ADJUSTABLE LEVER ASS`Y WAS CARRIED ON AIRCRAFT 45-467. THIS INSPECTION REVEALED NO SAFETY WIRE WAS INSTALLED ON T - [SDR JGVR20150217001](https://openairdocs.org/sdr/JGVR20150217001), Feb 17, 2015: GASKET. FAILED. DURING ENGINE REMOVAL FOR MPI, FOUND THE NR 2 ENGINE HP BLEED AIR DUCT ASSY 90 DEGREE CONNECTION, WITH A BLOWN OUT GASKET AND THE LEAKING BLEED AIR MELTED A POR - [SDR CA130823010](https://openairdocs.org/sdr/CA130823010), Aug 21, 2013: SHROUD. MISINSTALLED. (CAN) DURING MAINTENANCE PERFORMING AN APU REMOVAL, THE APU EXHAUST STUB WAS FOUND INCORRECTLY INSTALLED. THIS LEAD TO HOT EXHAUST ON THE FRAME AT BS 492.75 ON - [SDR CA130221004](https://openairdocs.org/sdr/CA130221004), Feb 14, 2013: APU. SHUTDOWN. (CAN) PILOT HAD UN-COMMANDED SHUTDOWN OF APU ON THE GROUND. APU WOULD NOT RESTART AFTER. MAINTENANCE DIAGNOSTIC COMPUTER SHOWED HIGH APU OIL TEMPERATURE. INSPEC - [SDR CA130121013](https://openairdocs.org/sdr/CA130121013), Jan 18, 2013: EXCITER. FAILED. (CAN) ENGINE DEEC DOWNLOAD C/O. FOUND "IGN B FAULT" CHANNEL B OF IGNITION EXCITER FAILED. - [SDR CA130110002](https://openairdocs.org/sdr/CA130110002), Dec 31, 2012: FRAME. BURNED. (CAN) GROUND CABLE FOR GPU PLUG ARCED OUT AT ANCHOR NUT BURNING FRAME UNDER ANCHOR NUT AND CAUSED RIVETS TO COME LOOSE. GPU PLUG FAILED INTERMITTENTLY CAUSING F - [SDR CA121231003](https://openairdocs.org/sdr/CA121231003), Dec 14, 2012: RELAY. DEFECTIVE. (CAN) PRIMARY PITCH TRIM FAILED TO TRIM NOSE UP, RELAY 72C FOUND DEFECTIVE AND REPLACED. - [SDR CA121121003](https://openairdocs.org/sdr/CA121121003), Nov 21, 2012: BOTTLE. FAILED. (CAN) DURING ROUTINE DI, NOTICED EMERGENCY BLOW DOWN BOTTLE WAS INDICATING ZERO. INVESTIGATION REVEALED BOTTLE HAD FAILED AT CONNECTION MANIFOLD ASSY. BOTTLE CO - [SDR CA121004001](https://openairdocs.org/sdr/CA121004001), Aug 28, 2012: TRANSDUCER. WEAK. (CAN) N2 TRANSDUCER SIGNAL WAS WEAK, OUT OF LIMITS THIS CAUSED THE DEEC TO REDUCE FUEL FLOW. REPLACEMENT OF N2 TRANSDUCER CORRECTED ISSSUE. - [SDR CA120503006](https://openairdocs.org/sdr/CA120503006), Apr 17, 2012: ACTUATOR. LEAKING. (CAN) NOTICED HYDRAULIC FLUID LEAKING FROM SINTERED PLUG AT END OF ACTUATOR. REPLACED ACTUATOR WITH REPAIRED UNIT. - [SDR CA120221010](https://openairdocs.org/sdr/CA120221010), Feb 19, 2012: STARTER GEN. OVERHEATED. (CAN) GENERATOR OVERHEAT INDICATION IN COCKPIT. CREW SHUTOFF GENERATOR. POST FLIGHT INDICATION OF GENERATOR BEARING FAILURE. - [SDR PJEA2011F00000](https://openairdocs.org/sdr/PJEA2011F00000), Nov 7, 2011: WINDSHIELD. CRACKED. UPON LANDING, AFTER AN UNEVENTFUL .8 HR NIGHT FLIGHT. PILOTS REPORTED THAT THE RT WINDSHIELD WAS CRACKED HALF WAY AROUND. AFTER FURTHER INVESTIGATION IT WAS DET - [SDR BKEA2012F00005](https://openairdocs.org/sdr/BKEA2012F00005), Nov 2, 2011: DRIVE UNIT. INOPERATIVE. FLAPS WOULD NOT RETRACT AFTER TAKEOFF. AIRCRAFT DIVERTED FOR MAINTENANCE. FOUND DRIVE UNIT INOPERATIVE. - [SDR 2011FA0000682](https://openairdocs.org/sdr/2011FA0000682), Oct 12, 2011: SELECTOR VALVE. FAILED. CREW WAS PERFORMING NIGHT PROFICIENCY FLIGHT. UPON 1ST LANDING, AIRCRAFT TAXIED AROUND FOR SECOND TAKEOFF. ON POWER UP FOR TAKEOFF ROLL, THE RIGHT ENGINE THRUST - [SDR CA111004008](https://openairdocs.org/sdr/CA111004008), Oct 1, 2011: IGNITER. CRACKED. (CAN) APU IGNITER PLUG, WAS FOUND CRACKED ON THE END SHELL BETWEEN THE TIP AND THREADED PORTION. THE DEFECT WAS DISCOVERED DURING THE SCHEDULED MX CHECK OF THE - [SDR CA111003008](https://openairdocs.org/sdr/CA111003008), Sep 26, 2011: PLUG. SHEARED. (CAN) MAIN HYD TANK DRAIN PLUG SHEARED/SEPARATED AT O-RING GROVE THREADS REMAINED IN TANK AND PLUG HEAD FELL OFF. PLUG IS DRILLED FOR A MAGNET SO THREADED PORTI - [SDR CA110822015](https://openairdocs.org/sdr/CA110822015), Aug 5, 2011: SEAL. FAILED. (CAN) DURING TAXI, CREW NOTICED CAVITATING SOUND FOLLOWED VERY SHORTLY AFTER BY A LT & RT HYD LOW PRESSURES LIGHTS ILLUMINATING. THE LOW MAIN HYD RESERVOIR LIGH - [SDR CA110822016](https://openairdocs.org/sdr/CA110822016), Jul 31, 2011: CLAMP. LOOSE. (CAN) DURING CLIMB ALL PRESSURIZATION SEEMED NORMAL AND AT THE 18,000 CHECK SCHEDULING WAS NORMAL. AT 32,000 FT THE CREW GOT A CABIN ALTITUDE WARNING AND THE OX - [SDR CA110913005](https://openairdocs.org/sdr/CA110913005), Jul 8, 2011: GPS. FAILED. (CAN) CREW NOTICED THAT THE GPS TIME/DATE STAMP HAD RESET ITSELF TO THE ORIGINAL 1992 ALGORITHM. ONCE ACFT WOW: WENT "BLACK" ACFT, PULLED BOTH GPS C/B`S, POWERE - [SDR CA110913006](https://openairdocs.org/sdr/CA110913006), Jul 8, 2011: GPS. FAILED. (CAN) CREW NOTICED THAT THE GPS TIME/DATE STAMP HAD RESET ITSELF TO THE ORIGINAL 1992 ALGORITHM. ONCE AIRCRAFT W.O.W: WENT "BLACK" AIRCRAFT, PULLED BOTH GPS C/B - [SDR CA110913007](https://openairdocs.org/sdr/CA110913007), Jul 8, 2011: CIRCUIT CARD. FAILED. (CAN) CREW NOTICED THAT THE GPS TIME/DATE STAMP HAD RESET ITSELF TO THE ORIGINAL 1992 ALGORITHM. ONCE ACFT WOW: WENT "BLACK" ACFT, PULLED BOTH GPS C/B`S, POWERE - [SDR 2011FA0000229](https://openairdocs.org/sdr/2011FA0000229), Mar 6, 2011: STARTER GEN. VIBRATION. STARTER GENERATOR DEVELOPED VIBRATIONS IN FLIGHT. STARTER GEN CONTINUED TO WORK. AFTER REMOVAL, AT FIRST LOOK IT SEEMED THAT BEARING HAD DETERIORATED. MFG TOOK - [SDR CA101202011](https://openairdocs.org/sdr/CA101202011), Dec 2, 2010: BRACKET. CRACKED. FOUND BOTH AIR SPRING UPPER SUPPORT BRACKETS ON AIR STAIR DOOR CRACKED DURING A C-CHECK. ALTHOUGH NOT A SAFETY OF FLIGHT ISSUE, THIS IS THE SECOND OF OUR ACFT T - [SDR A8JA0006](https://openairdocs.org/sdr/A8JA0006), Jul 16, 2010: FIRE DETECTOR. DEFECTIVE. AFTER RECEIVING TAKEOFF CLEARANCE, THE CREW POSITIONED THE ACFT FOR TAKEOFF AND INITIATED THE APU SHUTDOWN SEQUENCE IAW THE TAKEOFF CHECKLIST. UPON REACHING TAK - [SDR 2010FA0000579](https://openairdocs.org/sdr/2010FA0000579), Jun 16, 2010: HYDRAULIC SYSTEM. FLUID LOSS. LOSS OF MAIN HYD SYSTEM FLUID AND LT GEN. - [SDR 2010FA0000627](https://openairdocs.org/sdr/2010FA0000627), Jun 14, 2010: WINDSHIELD. CRACKED. RT WINDSHIELD OUTSIDE CRACK FOUND WHEN ACFT DESCENT FROM FL430 TO FL250 ,AND THEN TURNOFF THE WINDSHIELD HEATER, NO-PERSSURE LOSS, AND SAFE LANDING BACK HOME.TH - [SDR CA100614007](https://openairdocs.org/sdr/CA100614007), Jun 11, 2010: RETAINER. BROKEN. DURING POST FLIGHT INSP, FOUND BROKEN TAB RETAINER IN LOWER COWLING. FURTHER INVESTIGATION REVEALED THE TAB WAS FROM THE OIL COOLER SUPPLY LINE HOLD DOWN RETAIN - [SDR 2010FA0000632](https://openairdocs.org/sdr/2010FA0000632), May 12, 2010: BRAKE. WORN. NR 1 BRAKE ASSY WORN BEYOND LIMITS AFTER ONLY 19.1 HRS AND 10 CYCLES SINCE O/H UNDER W/O RC1997713.1 DATED 3/22/10. INSTALLED O/H BRAKE ASSY PN 5006575-1, SN MA - [SDR BKE2010F00000](https://openairdocs.org/sdr/BKE2010F00000), Apr 16, 2010: FITTING. FAILED. APPROX 11:30 PST, FLIGHT LEVEL 390, CAPTAIN REPORTED FLUCTUATING OIL PRESSURE, SECURED RT ENGINE AND DIVERTED. DISPATCHED MX CREW TO ACFT, INSP REVEALED OIL PRE - [SDR CA100208001](https://openairdocs.org/sdr/CA100208001), Feb 5, 2010: LINE. CRACKED. (CAN) THE ACFT WAS ENROUTE WHEN IT EXPERIENCED A LOSS OF NR 1 HYD PUMP, PRESSURE FOLLOWED SHORTLY THEREAFTER BY LOW HYD RESERVOIR AND LOW NR 2 HYD PUMP PRESSURE - [SDR BKEA201001181](https://openairdocs.org/sdr/BKEA201001181), Jan 18, 2010: LINE. UNSERVICEABLE. PILOT REPORTED AT 40K FT, ABOUT 4 HOURS INTO THE FLIGHT BACK, WHEN THEY HAD A VIBRATION. PILOT NOTICED A SPLIT IN THE GENERATORS AND AN INCREASE IN VIBES ON THE - [SDR 2009FA0001043](https://openairdocs.org/sdr/2009FA0001043), Dec 17, 2009: STARTER GEN. FAILED. STARTER GENERATOR FAILED, NO INDICATION OF VOLTAGE PRESENT. PN 23065-018-1, SN 98004. REMOVED AND REPLACED STARTER GENERATOR, SYS OPS CHECK GOOD IAW AMM 24-30-0 - [SDR 2009FA0001044](https://openairdocs.org/sdr/2009FA0001044), Dec 17, 2009: PUMP. LEAKING. DISCOVERED A LARGE AMOUNT OF HYDRAULIC FLUID HAD LEAKED FROM THE RT ENG. FURTHER INVESTIGATION SHOWED A LEAK COMING FROM THE RT HYD PUMP CASE DRAIN INDICATING T - [SDR CA090501002](https://openairdocs.org/sdr/CA090501002), Apr 28, 2009: MOTOR. SHORTED. (CAN) ON APPROACH FLAPS WOULD NOT EXTEND PAST 12 INCHES. FLAPS WOULD NOT RETRACT AFTER LANDING. FLAP/SLAT ELECTRONIC CONTROL UNIT HAD LOCKED OUT FLAPS DUE TO PO - [SDR CA090225001](https://openairdocs.org/sdr/CA090225001), Feb 20, 2009: FLEX LINE. BURST. (CAN) DURING CLIMB OUT THROUGH 1000` THE CREW REPORTED A BANG LIKE A BALLOON POPING. THE "DOOR SEAL" ANNUNCIATOR ILLUMINATED AND THEN THERE WAS AN INCREASE IN A - [SDR CA090130011](https://openairdocs.org/sdr/CA090130011), Jan 23, 2009: ACTUATOR. MALFUNCTIONED. AFTER TAKEOFF THE GEAR LANDING GEAR WAS SELECTED UP. ALL 3 "DOWN AND LOCKED" LIGHTS EXTINGUISHED BUT THE "IN TRANSIT" RED LIGHT REMAINED ILLUMINATED AND THE TOW - [SDR 2008FA0000904](https://openairdocs.org/sdr/2008FA0000904), Dec 9, 2008: TURBINE BLADES. DAMAGED. THE THIRD STAGE LP TURBINE DISK ON NR 2 ENG HAD A BLADE (PN 30606901) BREAK IN FLIGHT DAMAGING THE EXHAUST NOZZLE AND THE AFTER BODY OF THE ENG. THE BLADES OF T - [SDR CA080924007](https://openairdocs.org/sdr/CA080924007), Sep 24, 2008: LINE. CHAFED. (CAN) DURING INSP IN THE RT WW THE MAIN FUEL LINE TO THE RT ENGINE WAS FOUND TO BE CHAFING ON THE LAV SINK HEATED DRAIN LINE. THE DAMAGE WAS BEYOND LIMITS AND T - [SDR CA080924008](https://openairdocs.org/sdr/CA080924008), Sep 24, 2008: LINE. CHAFED. (CAN) IT WAS REPORTED THAT FUEL WAS SLOWLY TRANSFERRING FROM THE RT WING INTO THE CENTER TANK WHEN THE ACFT WAS STATIC. THE MOTIVE FLOW LINE PN 25W653120-634 AT - [SDR CA080903009](https://openairdocs.org/sdr/CA080903009), Sep 3, 2008: FITTING. LEAKING. (CAN) WHILE CARRYING OUT AN AUTO SLAT CHECK, DURING AN A-CHECK, THE STATIC SYS WAS REQUIRED TO SIMULATE 25,000 FT AGL. AN EXCESSIVE LEAK RATE WAS NOTICED ON THE - [SDR CA080818003](https://openairdocs.org/sdr/CA080818003), Aug 6, 2008: O-RING. FAILED. (CAN) RT BLEED LEAK LIGHT ILLUMINATED IN CLIMB OUT. AC RETURNED TO BASE. CONFIRMED LT BLEED LEAK ON GROUND DURING HIGH POWER ENGINE RUNS. COULD NOT DUPLICATE RT - [SDR CA080808004](https://openairdocs.org/sdr/CA080808004), Jul 22, 2008: LINE. CRACKED. (CAN) ON APPROACH INTO TORONTO PEARSON THE CREW NOTICED THAT THE AUX HYDRAULIC LOW PRESSURE ANNUNCIATOR AND FLUID LOW LEVEL LIGHT ILLUMINATED ON THE ACFT. AFTER - [SDR CA080627003](https://openairdocs.org/sdr/CA080627003), Jun 25, 2008: FITTING. LOOSE. (CAN) ON DESCENT THE LT AND RT HYDR PUMP LIGHTS FLICKERED ON AND OFF. LOW HYD RESERVOIR ALSO ILLUMINATED. ALL SYS FUNCTIONED NORMAL AND AFTER ACFT WAS STABILIZE - [SDR 2007FA0000870](https://openairdocs.org/sdr/2007FA0000870), Sep 12, 2007: BLADE. BROKEN. BROKEN TURBINE BLADE. ENGINE SENT TO MFG FOR INVESTIGATION. (K) - [SDR CA070907002](https://openairdocs.org/sdr/CA070907002), Sep 6, 2007: HOSE. CRACKED. (CAN) DURING PITOT STATIC CHECKS IT WAS FOUND THE SYSTEM WAS SLIGHTLY LEAKING. FURTHER VISUAL INSPECTION FOUND THE STATIC HOSE GOING TO THE ADC WAS WEATHER CRAC - [SDR CA071212001](https://openairdocs.org/sdr/CA071212001), Dec 27, 2006: ENGINE. MAKING METAL. (CAN) ON DESERT TO BASE CREW NOTICED NR 2 ENGINE OIL PRESSURE AND TEMPERATURE CLIMBING, POWER REDUCED TO IDLE. OIL PRESSURE DROPPED TO BELOW MINIMUMS (IN YELLOW All 85: https://openairdocs.org/engine/alliedsign-tfe731-40/reports.md --- 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.