# Garrett TFE731-3AR

- Type: Engine model (FAA registry)
- Registry code: 29095
- Manufacturer (registry): GARRETT
- Model: TFE731-3AR
- Engine type: Turbo-fan
- Power: 3,880 lb thrust
- Data sheet: [TCDS E6WE](https://openairdocs.org/tcds/E6WE) (OpenAirDocs)
- Holder: Honeywell Aerospace US LLC
- Installed in: 1 registered aircraft
- Page: https://openairdocs.org/engine/garrett-tfe731-3ar

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 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 2005-05-15](https://openairdocs.org/ad/2005-05-15): (LPT) stage 1 disks · Honeywell International TFE731-2, TFE731-2C, TFE731-3 and 5 more. Effective Apr 18, 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 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 95-07-02](https://openairdocs.org/ad/95-07-02): Low Pressure Turbine Disks · Honeywell International TFE731-3, TFE731-3A, TFE731-3AR and 3 more. Effective Jun 19, 1995
- [AD 94-23-05](https://openairdocs.org/ad/94-23-05): Honeywell International TFE731-3A and TFE731-3AR. Effective Dec 1, 1994
- [AD 94-07-03](https://openairdocs.org/ad/94-07-03): Turbine Nozzles · Honeywell International TFE731-2A, TFE731-3, TFE731-3A and 4 more. Effective Jun 6, 1994
- [AD 92-21-06](https://openairdocs.org/ad/92-21-06): Low Pressure Turbine (LPT) Rotor Disks · Honeywell International TFE731-2, TFE731-3, TFE731-3A and 2 more. Effective Nov 27, 1992
- [AD 90-24-06](https://openairdocs.org/ad/90-24-06): Thermocouple Lead Assemblies · Honeywell International TFE731-2, TFE731-2A, TFE731-3 and 8 more. Effective Nov 13, 1990
- [AD 90-03-04](https://openairdocs.org/ad/90-03-04): High Pressure Turbine Rotor Discs · Honeywell International TFE731-3, TFE731-3A, TFE731-3AR and 1 more. Effective Feb 22, 1990
- [AD 88-18-03](https://openairdocs.org/ad/88-18-03): High Pressure Turbine Rotor Disc · Honeywell International TFE731-3, TFE731-3A, TFE731-3AR and 1 more. Effective Jul 21, 1989
- [AD 86-03-01](https://openairdocs.org/ad/86-03-01): Turbine Interstage Transition Ducts · Honeywell International TFE731-2, TFE731-3, TFE731-3A and 4 more. Effective Feb 24, 1986
- [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 (1)

- [N257SJ](https://openairdocs.org/aircraft/N257SJ): [N257sj Aviation Corp](https://openairdocs.org/faa-owner/N257SJ%20AVIATION%20CORP), [Middletown, DE](https://openairdocs.org/faa-place/DE/Middletown), built 1985, S/N 55-118

## NTSB investigations

None matched to aircraft with this engine model.

## 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.

- [Incident 20220226023389I](https://openairdocs.org/incident/20220226023389I), Feb 26, 2022: Gates Learjet Corp 55 (N55AR), Boston, MA, Minor damage. During departure from runway 27, aircraft ingested a bird into the #1 engine just after rotation. There was a slight loss of power, Accompanied by a vibration…

## Service difficulty reports (30)

As reported by operators and repair stations, by the model named in the report.

- [SDR CA151216021](https://openairdocs.org/sdr/CA151216021), Dec 13, 2015: TIMER. FAULTY. (CAN) AC EXPERIENCED SUDDEN INCREASE IN DRAG AND CONTROL VIBRATION WHILE IN CRUISE FLT AFTER LEAVING ICING CONDITIONS. UPON RETURN TO BASE THERE WAS ICE BUILD U
- [SDR DBCA2014092600004](https://openairdocs.org/sdr/DBCA2014092600004), Sep 26, 2014: CONNECTOR. DIRTY. ON DEPARTURE THE NR 1 ENG DEEC TRIPPED TO MANUAL MODE. CREW RETURNED & LANDING WAS UNEVENTFUL. DOWNLOADED THE NR 1 DEEC DATA & CONTACTED TECH SUPPORT. REVIEWED 
- [SDR FJTA14064811](https://openairdocs.org/sdr/FJTA14064811), Jun 3, 2014: UNKNOWN. UNKNOWN. DURING CRUISE AT FL360, THE CABIN LOST PRESSURIZATION. THE CABIN STOPPED CLIMB AT APPROX 10,500 FT & WOULD NOT RESPOND UP OR DOWN FOR THE DURATION OF THE DESCEN
- [SDR 9JLA2014043003864](https://openairdocs.org/sdr/9JLA2014043003864), Apr 14, 2014: CONTROL QUADRANT. FAULTY. CREW REPORTED THE THE LT THRUST REVERSER WAS INTERMITTENT OR SLOW TO DEPLOY. TROUBLESHOOTING WAS ABLE TO DUPLICATE THE DISCREPANCY BY APPLYING A SIDE LOAD TO TH
- [SDR CA130131005](https://openairdocs.org/sdr/CA130131005), Jan 29, 2013: GYRO. FAILED. (CAN) PRIOR TO DESCENT THE FLIGHT CREW REPORTED THE LOSS OF DIRECTION INFORMATION ON THE NR 1 HSI. FLIGHT CONTINUED TO DESTINATION WITH USE OF NR 2 HSI INFORMAT
- [SDR CA111114007](https://openairdocs.org/sdr/CA111114007), Nov 10, 2011: POTENTIOMETER. SHORTED. (CAN) CO-PILOTS INSTRUMENT BACKLIGHTING INOPERATIVE. FOUND CO-PILOTS LIGHT DIMMER UNIT INOPERATIVE DUE TO EDGE LIGHTED PANEL, LIGHTING POTENTIOMETER WIPER RUBBI
- [SDR CA110621012](https://openairdocs.org/sdr/CA110621012), Jun 15, 2011: LINE. LEAKING. FLIGHT CREW REPORTED SMELL OF RUBBER AFTER T/O, WHICH WENT AWAY SLOWLY. ACFT INSPECTED AND NO EVIDENCE OF RUBBER SMELL WAS NOTED. FOUND FREON LINE LEAKING -OIL 
- [SDR CA090212004](https://openairdocs.org/sdr/CA090212004), Feb 11, 2009: DRIVE UNIT. LEAKING. (CAN) FLAP POWER DRIVE UNIT FOUND LEAKING FROM SOLENOID VALVE, THIS IS THE (4TH) UNIT WE HAVE HAD THE SAME FAULT ON, NO SDR WAS SUBMIITTED ON THE PREVIOUS UNITS
- [SDR 2007FA0000976](https://openairdocs.org/sdr/2007FA0000976), Oct 29, 2007: ROTOR. SEPARATED. IAW SERVICE BULLETIN TFE731-72-5175. BLADE SEPARATION ON ONE LPT3 BLADE AS LISTED IN TABLE 1 OF S/B 72-5175.
- [SDR DELR200700001](https://openairdocs.org/sdr/DELR200700001), Jan 4, 2007: BOLT. SHEARED. AFTER REMOVAL OF SAFTY WIRE TO REMOVE BOLT, THE MOUNT BOLT WAS FOUND SHEARED AT THE NECK OF THE BOLT. THREADED SECTION OF BOLT WAS REMOVED WITH AN EASYOUT IAW C
- [SDR FAA1031001](https://openairdocs.org/sdr/FAA1031001), Oct 27, 2006: SKIN. DELAMINATED. DEBOND AREA APPROX. 7 IN X 7 IN ON THE RT OB ELEVATOR LOWER COMPOSITE SKIN. ELEVATOR WAS SENT TO MFG FOR EVALUATION AND WAS DEEMED (BEYOND ECONOMICAL REPAIR). A
- [SDR DXTA200501093](https://openairdocs.org/sdr/DXTA200501093), Nov 19, 2005: PUMP. FAILED. ON TAKEOFF ROLL THE FUEL 2 LOW PRESS LIGHT CAME ON. ABORTED TAKEOFF AT 60 KNOTS. R & R FAULTY FUEL BOOST PUMP WITH OVERHAULED UNIT IAW HAWKER 800XP MM CHAP 28-2
- [SDR CA051103009](https://openairdocs.org/sdr/CA051103009), Oct 31, 2005: ACTUATOR. INOPERATIVE. (CAN) AFTER T/O AND UPON GEAR RETRACTION, NOSE GEAR UNSAFE LIGHT REMAINED ILLUMINATED. MULTIPLE GEAR SELECTIONS HAD NO EFFECT. CREW ELECTED TO CIRCLE FOR ABOUT 
- [SDR 31177050304](https://openairdocs.org/sdr/31177050304), May 3, 2004: PUMP. FAILED. DURING DESCENT FROM CRUISE, RIGHT ENGINE FLAMED OUT. ENGINE WAS SUCCESSFULLY RESTARTED. DIVERTED TO KBDL. REPLACED RIGHT ENGINE FUEL PUMP DUE TO LOW PRESSURE. R
- [SDR DJFA2004004](https://openairdocs.org/sdr/DJFA2004004), Apr 4, 2004: REGULATOR VALVE. FAILED. DURING THE CLIMB THE PILOTS NOTICED THE NR 3 ENGINE OIL PRESSURE LIGHT ILUMINATED. OIL PRESSURE WAS DESCENDING THREW 25 PSI. AT THAT POINT THE PILOTS SHUT DOWN 
- [SDR DJFA2004003](https://openairdocs.org/sdr/DJFA2004003), Apr 4, 2004: REGULATOR VALVE. FAILED. DURING THE CLIMB THE PILOTS NOTICED THE NR 3 ENGINE OIL PRESSURE LIGHT ILLUMINATED. OIL PRESSURE WAS DESCENDING THREW 25 PSI. AT THAT POINT THE PILOTS SHUT DOWN
- [SDR DXTA200300132](https://openairdocs.org/sdr/DXTA200300132), Oct 2, 2003: COMPRESSOR. DAMAGED. AT FLIGHT LEVER 370, NR 1 ENGINED EXPERIENCE A LOUD BANG WITH ITT SPIKING AT 1016 DEGREES WITH AIRFRAME VIBRATION. N1 AND N2 ROSE, ITT THEN FELL TO 450 DEGREES 
- [SDR T0DR200300002](https://openairdocs.org/sdr/T0DR200300002), Aug 9, 2003: FAIRLEAD. BROKEN. RUDDER JAMMED UPON ROTATION. (RUDDER SYS JAM) CHECKLIST. ALL KNOWN SYSTEMS SUSPECTED OF HAVING BRG ON RUDDER SYS. ALL OTHER FLIGHT CONTROL SYS OPERATED NORMALLY
- [SDR 3298S](https://openairdocs.org/sdr/3298S), Jul 24, 2003: BLADE. MISSING. 3298S- AIRCRAFT EXPERIENCED VIBRATION IN FLIGHT. NR 2 ENGINE WAS SHUTDOWN IN-FLIGHT. AIRCRAFT ARRIVED SAFETLY. VISUAL INSPECTION OF NR 2 ENGINE REVEALED A 1.0 T
- [SDR R5XR2000003](https://openairdocs.org/sdr/R5XR2000003), Apr 22, 2003: HOUSING. MISOVERHAULED. WHILE PERFORMING MODIFICATION TO 70821, THE EDM PROCEDURE BROKE THROUGH THE WALL OF THE HOUSING DUE TO ERROR IN SETUP OF EDM MACHINE.
- [SDR R5XR2000004](https://openairdocs.org/sdr/R5XR2000004), Apr 22, 2003: HOUSING. MISOVERHAULED. WHILE PERFORMING MODIFICATION TO 70821, THE EDM PROCEDURE BROKE THROUGH THE WALL OF THE HOUSING DUE TO ERROR IN SETUP OF EDM MACHINE.
- [SDR 032031](https://openairdocs.org/sdr/032031), Mar 20, 2003: RESTRICTOR VALVE. BYPASSING. MAIN ACCOMPLISHED PREFLT INSP AND THEN PILOTS PROCEEDED TO DO THEIR PREFLT INSP. UPON NORMAL EXTENSION OF SPEED BRAKE PANELS, THEY RETRACTED WITH HIGH SPEED AS 
- [SDR 032031A](https://openairdocs.org/sdr/032031A), Mar 20, 2003: RESTRICTOR VALVE. BYPASSING. DURING PREFLT INSP, MAINT CREW NOTED THAT SPOILERS FULLY DEPLOYED IN LESS THAN 1 SECOND WITH SPOILER SWITCHES SET TO "IN-FLT" MODE. NORMAL DEPLOY TIME IN THIS M
- [SDR CA030218012](https://openairdocs.org/sdr/CA030218012), Feb 17, 2003: TERMINAL BLOCK. OVERHEATED. (CAN) MFG DESIGN FLAW, INSTRUMENT LIGHTING SYS WAS DISCOVERED WHEN NEW AIR DATA DISPLAY UNIT WAS INSTALLED FOR RVSM UPGRADE. SYMPTOM WAS ADDU LIGHT WOULD GO INT
- [SDR ROCK012303](https://openairdocs.org/sdr/ROCK012303), Jan 23, 2003: SWITCH. INOPERATIVE. PILOT'S TRIM SWITCH BECAME INTERMITTENT AND THEN FAILED TO OPERATE COMPLETELY IN FLIGHT. CO-PILOT AND ALTERNATE TRIM SYSTEMS BOTH REMAINED FUNCTIONAL. TESTED AN
- [SDR 778](https://openairdocs.org/sdr/778), Nov 17, 2002: CONTROL CABLE. BROKEN. NR 1 ENGINE TELEFLEX CABLE BROKE INSIDE ITS HOUSING MAKING IT IMPOSSIBLE FOR THE PILOTS TO HAVE CONTROL OF THE ENGINE AS FAR AS MAKING CHANGES TO THE SPEED AND 
- [SDR 029041702](https://openairdocs.org/sdr/029041702), Apr 17, 2002: LINE. CRACKED. PILOTS STARTED TAXI OUT TO TAKEOFF. IN PROCESS CONDUCTED THE LANDING SPOILER EXTENSION OPERATIONAL TEST WHICH SURGES AND SLAMS THE HYDRAULIC SYSTEM FAIRLY HARD.
- [SDR APJ2002F00000](https://openairdocs.org/sdr/APJ2002F00000), Feb 17, 2001: OIL CAP. NOT SEATED. APPROXIMATELY 1.5 HOURS INTO FLIGHT AT 35,000 FT THE OIL PRESSURE GAUGE FLUCTUATED FOR THE RIGHT SIDE ENGINE AND PROCEEDED TO INDICATE MINIMUM PRESSURE. AS A PR
- [SDR 20010320CW007](https://openairdocs.org/sdr/20010320CW007), Dec 8, 2000: CONTROL UNIT. MALFUNCTIONED. ON APPROACH, LANDING GEAR WAS LOWERED AND CDS MESSAGE LEFT AND RIGHT INBOARD BRAKE FAILED. CONTINUED WITH NORMAL CHECKLIST. THE AMBER MESSAGE WAS REPLACED BY A 
- [SDR CA000511046](https://openairdocs.org/sdr/CA000511046), May 3, 2000: SEAT BACK. CRACKED. (CAN) PILOTS SEAT BACK REST FOUND CRACKED.

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