# Garrett TFE731-3C - Type: Engine model (FAA registry) - Registry code: 29098 - Manufacturer (registry): GARRETT - Model: TFE731-3C - Engine type: Turbo-fan - Power: 3,700 lb thrust - Data sheet: [TCDS E6WE](https://openairdocs.org/tcds/E6WE) (OpenAirDocs) - Holder: Honeywell Aerospace US LLC - Installed in: 3 registered aircraft - Page: https://openairdocs.org/engine/garrett-tfe731-3c 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 2010-06-11](https://openairdocs.org/ad/2010-06-11): Second stage low-pressure compressor rotor (LPCR) discs · Honeywell International TFE731-2, TFE731-2A, TFE731-2C and 16 more. Effective Apr 21, 2010 - [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 - [AD 2005-13-07](https://openairdocs.org/ad/2005-13-07): Turbine rotor discs. · Honeywell International TFE731-2, TFE731-2A, TFE731-2B and 12 more. Effective Jul 27, 2005 - [AD 2001-23-09](https://openairdocs.org/ad/2001-23-09): Fan Rotor Discs · Honeywell International TFE731-2, TFE731-2A, TFE731-2B and 14 more. Effective Dec 21, 2001 - [AD 2000-15-09](https://openairdocs.org/ad/2000-15-09): HPC Impeller · Honeywell International TFE731-2, TFE731-2A, TFE731-2B and 20 more. Effective Oct 10, 2000 - [AD 98-17-01 R1](https://openairdocs.org/ad/98-17-01-R1): Flex Fuel Tube · Honeywell International TFE731-2, TFE731-2A, TFE731-2B and 14 more. Effective Nov 29, 1999 - [AD 97-04-03](https://openairdocs.org/ad/97-04-03): First stage low pressure turbine (LPT) seal plates · Honeywell International TFE731-2A, TFE731-3C and TFE731-3CR. Effective May 5, 1997 - [AD 96-05-03](https://openairdocs.org/ad/96-05-03): Fan rotor disks · Honeywell International TFE731-2, TFE731-2A, TFE731-2B and 13 more. Effective Apr 2, 1996 - [AD 96-04-01](https://openairdocs.org/ad/96-04-01): Fan Rotor Assembly · Honeywell International TFE731-2, TFE731-2A, TFE731-2B and 12 more. Effective Mar 15, 1996 - [AD 82-23-03 R1](https://openairdocs.org/ad/82-23-03-R1): High Pressure Compressor Impellers · Honeywell International TFE731-2, TFE731-2A, TFE731-2B and 12 more. Effective Dec 9, 1983 - [AD 75-07-10](https://openairdocs.org/ad/75-07-10): Transfer Gearbox Vertical Bevel Gear Bearing · Honeywell International TFE731-2, TFE731-2A, TFE731-2B and 12 more. Effective May 1, 1975 Historical (superseded or no longer in force): - [AD 98-17-01](https://openairdocs.org/ad/98-17-01) (historical): Honeywell International TFE731-2, TFE731-2A, TFE731-2B and 14 more. Effective Oct 13, 1998 - [AD 96-18-13](https://openairdocs.org/ad/96-18-13) (historical): Fan rotor disk · Honeywell International TFE731-2, TFE731-2A, TFE731-3 and 10 more. Effective Nov 12, 1996 ## Registered aircraft (3) - [N255RV](https://openairdocs.org/aircraft/N255RV): [Solomon Mark Trustee](https://openairdocs.org/faa-owner/SOLOMON%20MARK%20TRUSTEE), [Wilmington, DE](https://openairdocs.org/faa-place/DE/Wilmington), built 1983, S/N 095 - [N980DM](https://openairdocs.org/aircraft/N980DM): [Falcon Fawzi LLC](https://openairdocs.org/faa-owner/FALCON%20FAWZI%20LLC), [Ft Lauderdale, FL](https://openairdocs.org/faa-place/FL/Ft%20Lauderdale), built 1993, S/N 238 - [N98DH](https://openairdocs.org/aircraft/N98DH): [Aviation 900b LLC](https://openairdocs.org/faa-owner/AVIATION%20900B%20LLC), [Davie, FL](https://openairdocs.org/faa-place/FL/Davie), built 1991, S/N 219 ## 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 (36) As reported by operators and repair stations, by the model named in the report. - [SDR 2JKA20240425002](https://openairdocs.org/sdr/2JKA20240425002), Apr 20, 2024: ENGINE. FLAMED OUT. TOOK OFF FROM KAUS AT 17:36 UTC. DURING CRUISE, AROUND 2 HRS AFTER DEPARTURE, FLYING AT FL 400, FUEL ON BOARD WAS 4500 LBS, VMC CONDITIONS, AND NO TURBULENCE, H - [SDR WNDA2016FA0000105](https://openairdocs.org/sdr/WNDA2016FA0000105), Mar 1, 2016: ACM. OVERHEATED. ON CLIMBOUT AFTER TAKEOFF, PILOT NOTICED SMOKE IN THE CABIN FOLLOWED BY RT PAC OVERHEAT LIGHT. AFTER FURTHER INVESTIGATION BY MAINTENANCE FOUND THE RT AIR CYCLE - [SDR T8VA2016F00013](https://openairdocs.org/sdr/T8VA2016F00013), Oct 15, 2015: ACTUATOR. FAILED. PRIMARY TRIM FAILED IN FLIGHT. IAW CHECKLIST SWITCH TO SECONDARY TRIM. SECONDARY TRIM FAILED. ACCOMPLISHED DUAL TRIM FAILURE CHECKLIST. DECLARED AN EMERGENCY AN - [SDR CA150415004](https://openairdocs.org/sdr/CA150415004), Apr 8, 2015: LINK. BENT. (CAN) UPON A THRUST REVERSER DETAILED INSPECTION & LUBRICATION, THE LT OTBD UPPER AFT THRUST REVERSER DOOR LINK WAS FOUND BENT. UPON FURTHER INVESTIGATION FOUND - [SDR CA140217005](https://openairdocs.org/sdr/CA140217005), Feb 15, 2014: ENGINE. FAILED. (CAN) LEFT ENGINE FAILURE, ENROUTE, LT ENGINE WENT FROM CRUISE POWER TO IDLE AND WAS UNRESPONSIVE TO THROTTLE LEVER MOVEMENT. AFTER A COUPLE OF MINUTES THE ENGI - [SDR CA121231002](https://openairdocs.org/sdr/CA121231002), Dec 22, 2012: CONNECTOR. DAMAGED. (CAN) GEAR UNSAFE LIGHT ON AFTER RETRACTION AFTER T/O. CREW CYCLED L/G 2X, BOTH TIMES THE GEAR DID NOT RETRACT PROPERLY, FOLLOWED ABNORMAL PROCEDURES CHECKLIST - [SDR CA121012012](https://openairdocs.org/sdr/CA121012012), Oct 9, 2012: TRUNNION. GOUGED. (CAN) DURING REPLACEMENT OF THE RT MLG OLEO, THE OTBD GEAR DOOR WAS REMOVED. WHEN REINSTALLING THE DOOR IT WAS NOTICED THAT THE RT MAIN GEAR TRUNNION WAS GOUGED - [SDR 2012FA0000599](https://openairdocs.org/sdr/2012FA0000599), Aug 30, 2012: STEERING UNIT. OUT OF LIMITS. CREW REPORTED THAT NOSEWHEEL STEERING SEEMED "SLOPPY" AROUND NEUTRAL THAN PREVIOUS. INSPECTED ACFT. FUNCTIONAL TESTED NOSE WHEEL STEERING WITH NO OBVIOUS DISCRE - [SDR 2012FA0000571](https://openairdocs.org/sdr/2012FA0000571), Aug 15, 2012: ANNUNCIATOR. FALSE INDICATION. AT FL170, CREW RECEIVED A FUEL LOW PRESSURE, HYD PRESSURE LOW, FUEL F/W SHUTOFF, AND AN EMERGENCY PRESSURE INDICATIONS. IN ADDITION, THE MASTER WARNING SWITCH L - [SDR FCPA20110816](https://openairdocs.org/sdr/FCPA20110816), Aug 11, 2011: CHIP DETECTOR. CONTAMINATED. AFTER DEPARTURE DURING CLIMBOUT, THE RIGHT ENGINE CHIP DETECTOR LIGHT ILLUMINATED. AIRCRAFT FLIGHT MANUAL INDICATES TO SHUT DOWN ENGINE (WHEN PRACTICAL) AND LAN - [SDR 2010FA0000963](https://openairdocs.org/sdr/2010FA0000963), Sep 5, 2010: FUEL CONTROL. OUT OF ADJUST. LT ENGINE SHUTDOWN IN CRUISE AT 30,000 FT. FLIGHT CREW ABLE TO RESTART NO FURTHER DEFECTS NOTED. FUEL CONTROL REPLACED WITH O/H UNIT, OPS CHECKS PROVIDED SATISF - [SDR CA100908001](https://openairdocs.org/sdr/CA100908001), Aug 4, 2010: SEAL. WORN. WHILE CRUISING AT FL380, AUTOPILOT HEADING CONTROL BEGAN BEHAVING ABNORMALLY. WHEN THE FLIGHT CREW DISCONNECTED THE AUTOPILOT THEY WERE UNABLE TO MOVE AILERON C - [SDR JGVR2010F00103](https://openairdocs.org/sdr/JGVR2010F00103), May 7, 2010: ATTACH BRACKET. CORRODED. ( JGVR ) DURING A SCHEDULED A-CHECK INSPECTION, CORROSION WAS FOUND ON THE LT AILERON ACTUATOR ATTACH BRACKET. STARTED REMOVING CORROSION AND FOUND CORROSION MI - [SDR Y9PA199HE5.29.09](https://openairdocs.org/sdr/Y9PA199HE5.29.09), May 29, 2009: VALVE. FAILED. CREW NOTICED CABIN DUCT TEMP HI LIGHT ON MASTER WARNING PANEL, CABIN AIR COMING INTO CABIN WAS HOT, CREW FOLLOWEWD ACFT CHECK LIST TO EXTINGUISH THE WARNING LIG - [SDR Y9PAN199HE4.24.09](https://openairdocs.org/sdr/Y9PAN199HE4.24.09), Apr 24, 2009: HINGE FITTING. MISLOCATED. UPON DEPARTURE, AFTER GEAR RETRACTION, THE GEAR UNSAFE LIGHT REMAINED ILLUMINATED INDICATING ONE OF THE GEAR HAD NOT COMPLETELY RETRACTED INTO THE UPLOCK. OBTAI - [SDR 2009FA0000276](https://openairdocs.org/sdr/2009FA0000276), Apr 3, 2009: SYMBOL GENERATOR. FAILED. BOUGHT AN EXCHANGED SG-603 SYMBOL GENERATOR WITH AN 8130 THAT SAID REPAIRED ON IT. INSTALLED PART IN AIRCRAFT, IT HAD THE VERY SAME FAILURE AS THE INCOMING FAIL - [SDR DBCA20081219605SA](https://openairdocs.org/sdr/DBCA20081219605SA), Dec 18, 2008: O-RING. CUT. DURING CRUISE FLIGHT, CREW NOTICED NR 1 ENG OIL PRESSURE DECREASING FROM 42 PSI TO 35 PSI. CREW REDUCED POWER ON NR 1 ENGINE AND CONTINUED TO MONITOR OIL PRESSU - [SDR CA080326003](https://openairdocs.org/sdr/CA080326003), Mar 24, 2008: COUPLING. MISINSTALLED. (CAN) CREW WROTE UP, CABIN PAC STUCK ON FULL COLD. TROUBLESHOOTING CARRIED OUT AND FOUND THAT THE COUPLING FOR CABIN TEMP CONTROL HAD DISCONNECTED FROM THE ENVI - [SDR CA060822001](https://openairdocs.org/sdr/CA060822001), Aug 5, 2006: BOLT. BROKEN. (CAN) ON DAILY INSPECTION, FOUND (1) BOLT BROKEN ON NR 4 MAIN WHEEL ASSY. (TC NR 20060822001) - [SDR CA060224008](https://openairdocs.org/sdr/CA060224008), Feb 24, 2006: TURNBUCKLE. CHAFED. DURING A SCHEDULED PHASE 5 INSPECTION ON CESSNA 650 C-FIMO, THE TECHNICIAN DISCOVERED THAT THE LT AND RT AILERON OUTBOARD AFT CABLE CHAFED THROUGH THE LOKCLAD A - [SDR ZN3R556712](https://openairdocs.org/sdr/ZN3R556712), Jan 3, 2006: STATOR. SEPARATED. ENGINE 4TH LPC STATOR HAD INNER RING FRACTURE, LEADING TO A SINGLE VANE SEPARATING FROM THE STATOR ASSEMBLY. THE VANE CAUSED DAMAGE TO THE HPC AREA OF THE ENGIN - [SDR CA051018001](https://openairdocs.org/sdr/CA051018001), Oct 17, 2005: TURNBUCKLE. CHAFED. DURING PHASE 1-5 INSPECTION ON AIRCRAFT, TECHNICIANS DISCOVERED THAT THE LT AND RT AILERON CABLES WERE FOULING. THE RESULT WAS THAT THE LT TURNBUCKLE WAS CHAFED - [SDR DJFA2005148](https://openairdocs.org/sdr/DJFA2005148), Oct 6, 2005: LINE. LEAKING. CREW REPORTED THAT RT ENGINE OIL LOW PRESSURE ANNUNCIATOR HAD ILLUMINATED WHILE IN CRUISE FLIGHT APPROX AN HOUR AND A HALF AFTER TAKE OFF. RT ENGINE OIL PRESSUR - [SDR CA050714001](https://openairdocs.org/sdr/CA050714001), Jul 6, 2005: RETAINER. MISSING. (CAN) WHILE DOING A VISUAL INSPECTION, IT WAS FOUND THAT THE RT FLAP FLEXSHAFT RETAINER WAS MISSING (BROKEN OFF). NEW RETAINER WAS INSTALLED. - [SDR CA050407002](https://openairdocs.org/sdr/CA050407002), Apr 4, 2005: PUMP. FAILED. (CAN) AFTER TAKE-OFF, THE LT HYDRAULIC PRESSURE LOW ANNUNCIATION ILLUMINATED IN CLIMB. AIRCRAFT RETURN TO MAINTENANCE BASE. LT ENGINE HYDRAULIC DRIVEN PUMP REPL - [SDR DJFA2004029](https://openairdocs.org/sdr/DJFA2004029), Oct 21, 2004: FUEL CONTROL. UNSERVICEABLE. CREW REPORTED THAT WHILE AT V2 RIGHT FUEL COMPUTER ANNUNCIATOR ILLUMINATED AND THE NR 2 ENGINE ROLLED BACK TO 70 PERCENT AND STARTED SURGING. THE AIRCRAFT ROLLE - [SDR DJFA2004019](https://openairdocs.org/sdr/DJFA2004019), Aug 11, 2004: SEAL. LEAKING. DURING CLIMB THE NR 1 ENGINE FIRE LIGHT CAME ON. THE CREW RETARDED THE THROTTLES AND THE LIGHT WENT OUT. THEY RETURNED TO THE DEPARTURE AIRPORT WITH NO PROBLEMS - [SDR DBCR122D](https://openairdocs.org/sdr/DBCR122D), Jun 14, 2004: ENGINE. FAILED. AFTER TAKEOFF, FLIGHT CREW NOTICED LOUD RUMBLE FOLLOWED BY NR 1 ENGINE SPOOLING DOWN. ITT INDICATED 1000 DEGREE CENTIGRADE WITH OVERTEMP LIGHT. FLIGHT CREW SECU - [SDR DBCA122D3](https://openairdocs.org/sdr/DBCA122D3), May 14, 2004: ENGINE. FOD. AFTER TAKEOFF, FLIGHT CREW NOTICED LOUD RUMBLE FOLLOWED BY NR 1 ENGINE SPOOLING DOWN. ITT INDICATED 1000 DEGREE CENTIGRADE WITH OVERTEMP LIGHT. FLIGHT CREW SECU - [SDR CA040213002](https://openairdocs.org/sdr/CA040213002), Feb 12, 2004: TORQUE TUBE. MISINSTALLED. (CAN) RECEIVED A RUDDER TORQUE TUBE NOT PROPERLY ASSEMBLED, FROM A MANUFACTURER. A RIB WAS NOT INSTALLED CORRECTLY DURING A MANUFACTURING PROCESS. - [SDR CA031113008](https://openairdocs.org/sdr/CA031113008), Nov 13, 2003: CONTROL CABLE. FRAYED. (CAN) DURING A SCHEDULE INSPECTION ON RT WING OB FLIGHT SPOILER. THE OB RT SPOILER ACTUATING CABLE (FOR THE FLT SPOILER ACTUATOR) WAS FOUND FRAYED UNDER A PULLE - [SDR CA031113007](https://openairdocs.org/sdr/CA031113007), Nov 12, 2003: TORQUE TUBE. CHAFED. (CAN) DURING A PHASE 5 INSPECTION A TASK INVOLVE THE REMOVAL OF THE AFT VERTICAL FIN TOP FAIRING, TO INSPECTED INSIDE THIS AREA. MAINTENANCE PERSONNEL FOUND THE - [SDR CA030520001](https://openairdocs.org/sdr/CA030520001), May 16, 2003: WIRE. BROKEN. (CAN) AFTER THE AIRCRAFT TOOK-OFF PILOT SELECTED THE GEAR HANDLE TO THE UP POSITION. DURING CLIMB PILOT REPORT LT MAIN LANDING INDICATION STILL SHOWN GEAR DOWN - [SDR CA020829002](https://openairdocs.org/sdr/CA020829002), Aug 28, 2002: CONTROL CABLE. FRAYED. (CAN) DURING PHASE "A" INSPECTION. MAINTENANCE PERSONNEL WHEN THROUGH THE TAIL CONE AREA TO COMPLETE A VISUAL INSPECTION. ON THE LT SIDE OF THE TAIL CONE TECHNI - [SDR 2002F00434](https://openairdocs.org/sdr/2002F00434), May 1, 2002: O-RING. DEFECTIVE. LT ENGINE HAD A LOSS OF OIL PRESSURE, SHUT DOWN LT ENGINE. LANDED IN MCO. CESSNA SERVICE CENTER TROUBLESHOT PROBLEM TO BAD O-RING ON LT ENGINE OIL CAP (OUTBOARD - [SDR O9I2002F00001](https://openairdocs.org/sdr/O9I2002F00001), Apr 30, 2002: TIP CAP. DELAMINATED. THE TRAILING EDGE OF THE RIGHT HORIZONTAL STABILIZER TIP CAP (PN 24W45002050251) WAS FOUND TO BE DELAMINATING ON THE TRAILING EDGE . THIS IS A COMPOSITE ASSEMBL --- 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.