# Garrett TFE731-2

- Type: Engine model (FAA registry)
- Registry code: 29086
- Manufacturer (registry): GARRETT
- Model: TFE731-2
- Engine type: Turbo-fan
- Power: 3,500 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-tfe731-2

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 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 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 81-24-08](https://openairdocs.org/ad/81-24-08): Turbine Interstage Transition Ducts · Honeywell International TFE731-2, TFE731-3, TFE731-3A and 2 more. Effective Jan 6, 1982
- [AD 80-16-04](https://openairdocs.org/ad/80-16-04): Tie Rod · Honeywell International TFE731-2, TFE731-3 and TFE731-3R. Effective Aug 7, 1980
- [AD 78-22-10](https://openairdocs.org/ad/78-22-10): Low Pressure Rotor Thrust Ball Bearings · Honeywell International TFE731-2, TFE731-3 and TFE731-3R. Effective Nov 13, 1978
- [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
- [AD 74-23-05](https://openairdocs.org/ad/74-23-05): Fuel Pumps · Honeywell International TFE731-2. Effective Nov 14, 1974
- [AD 74-11-06](https://openairdocs.org/ad/74-11-06): Fuel Control Computer · Honeywell International TFE731-2. Effective Sep 23, 1974
- [AD 74-18-16](https://openairdocs.org/ad/74-18-16): Fuel Control Computer · Honeywell International TFE731-2. Effective Sep 6, 1974
- [AD 74-18-12](https://openairdocs.org/ad/74-18-12): Fuel Control Orifice Assembly · Honeywell International TFE731-2. Effective Sep 3, 1974
- [AD 74-13-09](https://openairdocs.org/ad/74-13-09): Fuel Pump Assemblies · Honeywell International TFE731-2. Effective Jul 31, 1974
- [AD 89-22-16](https://openairdocs.org/ad/89-22-16): Engine Acceleration or Deceleration · Honeywell International TFE731-2, TFE731-5, TFE731-5AR and 1 more

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
- [AD 86-11-05](https://openairdocs.org/ad/86-11-05) (historical): Fan Rotor Discs · Honeywell International TFE731-2, TFE731-3 and TFE731-3R

## Registered aircraft (3)

- [N277MK](https://openairdocs.org/aircraft/N277MK): [Casmos LLC](https://openairdocs.org/faa-owner/CASMOS%20LLC), [Wilmington, DE](https://openairdocs.org/faa-place/DE/Wilmington), built 1980, S/N 341
- [N725CJ](https://openairdocs.org/aircraft/N725CJ): [Club Jet Investments LLC](https://openairdocs.org/faa-owner/CLUB%20JET%20INVESTMENTS%20LLC), [Wilmington, DE](https://openairdocs.org/faa-place/DE/Wilmington), built 1974, S/N 25
- [N970GW](https://openairdocs.org/aircraft/N970GW): [Laguera Construction Inc](https://openairdocs.org/faa-owner/LAGUERA%20CONSTRUCTION%20INC), [Wilmington, DE](https://openairdocs.org/faa-place/DE/Wilmington), built 1983, S/N 6500019

## 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 CEN11LA265](https://openairdocs.org/ntsb/CEN11LA265), Mar 24, 2011: Dassault-Breguet Falcon 10 (N303FZ), Sellersburg, IN, substantial damage. Probable cause: The pilot's failure to maintain control of the airplane during landing in strong and gusty wind conditions.

## 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 20110323004619A](https://openairdocs.org/incident/20110323004619A), Mar 23, 2011: Dassault-Breguet FALCON 10 (N303FZ), Sellersburg, IN, Substantial damage. Upon landing, the aircraft caught a gust of wind from the left side that lifted the aircraft off the ground and displaced it to the right of the runway…

## Service difficulty reports (201, newest 50)

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

- [SDR 2025FA0000623](https://openairdocs.org/sdr/2025FA0000623), Sep 3, 2025: BRAKE ASSY. MISOVERHAULED. INTERNAL CONTAMINATION BLOCKING THE BLEED PORTS AND STATOR MISALIGNMENT WERE DISCOVERED DURING INSTALLATION/ROUTINE MAINTENANCE OF ELEVEN (11) BRAKE ASSEMBLIES 
- [SDR 2025FA0000358](https://openairdocs.org/sdr/2025FA0000358), May 15, 2025: BOOT. BURNED. UPON POST FLIGHT WALK AROUND INSPECTION BY FLIGHT CREW, IT WAS DISCOVERED THAT THE LEFT HORIZONTAL STABILIZER ANTI-ICE BOOT HAD SHORTED OUT AND BURNT A HOLE IN 
- [SDR G1IA202402130057](https://openairdocs.org/sdr/G1IA202402130057), Feb 10, 2024: CONNECTOR. DIRTY. PERFORMED VISUAL INSPECTION OF #1 ENGINE FIRE DETECTION LOOP ROUTING AND CONDITION PER LEAR 45 AMM. PERFORMED OPERATIONAL CHECK OF THE ENGINE FIRE DETECTION SYS
- [SDR 2022F00351](https://openairdocs.org/sdr/2022F00351), Aug 19, 2022: HYDRAULIC LINE. LEAKING. AFTER TAKEOFF FROM KFXE, I RAN THE AFTER TAKE OFF CHECKLIST. I CHECKED THE HYDRAULIC PRESSURE, AND IT WAS NORMAL. UPON REACHING 10,000FT, THE CREW NOTICED THE "
- [SDR O9IA202107185571](https://openairdocs.org/sdr/O9IA202107185571), Jul 17, 2021: FCU. FAULTED. IN CRUISE FLIGHT, THE FLIGHT CREW NOTICED THAT THE LH THROTTLE WAS STUCK IN THE MCR POSITION. ALL ATTEMPTS TO REDUCE THE THROTTLE WERE UNSUCCESSFUL. UPON CONSUL
- [SDR KC8A20170907006](https://openairdocs.org/sdr/KC8A20170907006), Aug 31, 2017: OIL SYSTEM. LEAKING. DURING CLIMB THROUGH FL310, THE LEFT ENGINE OIL PRESSURE DROPPING STEADILY, FOLLOWED BY A LOW OIL PRESSURE LIGHT AND MASTER WARNING. THE ENGINE WAS SHUT DOWN AN
- [SDR T6FA20160322001](https://openairdocs.org/sdr/T6FA20160322001), Mar 20, 2016: SEAL. LACK OF LUBE. AIRCRAFT WAS CLIMBING THROUGH FL380, THE CREW GOT AN AMBER AP AIL MISTRIM CAS MSG. AUTOPILOT WAS DISENGAGED TO FIND THAT THEY HAD NO AILERON CONTROL. CONTROL WH
- [SDR CA160104006](https://openairdocs.org/sdr/CA160104006), Dec 17, 2015: BOLT. FAILED. (CAN) AFTER LANDING THE CREW DEPLOYED THE TR AND TR DEPLOYED NORMALLY BUT COULD NOT APPLY TR POWER TO LEFT HAND ENGINE. SELECTED TR STOWED BY PIGGY BACK LEVER B
- [SDR O9IA20150713001](https://openairdocs.org/sdr/O9IA20150713001), Jul 12, 2015: FUEL CONTROL. FAULTY. RIGHT ENG FUEL COMPUTER LIGHT ILLUMINATED IN FLIGHT FOLLOWED BY ROLL BACK OF RT ENG. ENG SUBSEQUENTLY SHUTDOWN. ACFT RETURNED TO BASE ON SINGLE ENG. DOWNLOAD OF
- [SDR 2015F00084](https://openairdocs.org/sdr/2015F00084), Jun 2, 2015: WASHER. MISINSTALLED. RIGHT ENG FIRE LIGHT ILLUMINATED IN CLIMB. LIGHT INTERMITTENTLY ILLUMINATED UNTIL IT REMAINED CONSTANT. PILOT FOLLOWED CHECKLIST & IT STARTED ILLUMINATING INTER
- [SDR CA150114004](https://openairdocs.org/sdr/CA150114004), Jan 13, 2015: RUB STRIP. DEPARTED. (CAN) RH ENGINE FOD INJESTION, WING TO FUSELAGE FAIRING LEADING EDGE RUBBING STRIP CAME LOOSE AND WENT THROUGH ENGINE IN FLIGHT. PROBLEM KNOWN BY LEARJET (KNOW 
- [SDR CA140729006](https://openairdocs.org/sdr/CA140729006), Jul 25, 2014: CONTROL UNIT. FAILED. (CAN) DURING SHORT FINAL CREW NOTED LH/RH OUTBD BRAKE FAIL CAS MESSAGE. ON TOUCHDOWN BRAKES APPLIED BUT SEEMED INEFFECTIVE. CREW ELECTED TO USE EMERG BRAKES. TH
- [SDR 2014F00127](https://openairdocs.org/sdr/2014F00127), Jun 24, 2014: GASKET. LEAKING. LEFT ENGINE FIRE LIGHT ILLUMINATED DURING CLIMBOUT, PASSING THROUGH 5000 MSL. THROTTLE WAS REDUCED AND INDICATION WENT AWAY. ACFT RETURNED TO BASE, UNEVENTFUL L
- [SDR CA140107010](https://openairdocs.org/sdr/CA140107010), Jan 6, 2014: CONTROL UNIT. MALFUNCTIONED. (CAN) ACFT DISPATCHED WITH A BRAKE SYSTEM FAULT, WHITE BRAKE FAULT CAS MESSAGE, REF MEL/DDG 32-3. ON RETURN DURING DEFECT TROUBLESHOOTING, DAMAGE WAS OBSERVED O
- [SDR 2014FA0000006](https://openairdocs.org/sdr/2014FA0000006), Jan 5, 2014: GENERATOR. FAILED. MECHANIC REMOVED RT ENGINE COWL AND FOUND SIGNIFICANT INTERNAL AND EXTERNAL DAMAGE TO THE RT GENERATOR. AFT SECTION OF THE GENERATOR CASE WAS SEPARATED, GENERAT
- [SDR CA131215001](https://openairdocs.org/sdr/CA131215001), Dec 13, 2013: WHEEL. FAILED. (CAN) DURING A POST FLIGHT INSPECTION, CREW NOTICED A FLAT TIRE AND THEN NOTICED A LARGE PORTION OF THE INBD WHEEL HALF MISSING. THERE WERE NO SIGNS OF OVERHEAT
- [SDR 2013FA0000475](https://openairdocs.org/sdr/2013FA0000475), Aug 20, 2013: FUEL CONTROL. MALFUNCTIONED. CREW REPORTED LT ENGINE THROTTLE STUCK AND UNABLE TO RETARD. AFTER MOVING THE THROTTLE THEY WERE ABLE TO BRING TO IDLE FOR LANDING. REMOVED FUEL CONTROL AND FOU
- [SDR G41A20130731004](https://openairdocs.org/sdr/G41A20130731004), Jul 27, 2013: SOLENOID. SHORTED. DURING CLIMB, NR 1 ENGINE EXPERIENCED A SUDDEN SURGE FOLLOWED BY A ROLLBACK OF APPROXIMATELY 15 PERCENT N1. CAPTAIN NOTICED LT FUEL COMPUTER LIGHT ON & CO-PILOT
- [SDR 2013F00048](https://openairdocs.org/sdr/2013F00048), Feb 3, 2013: TERMINAL. BROKEN. A FEW MINUTES AFTER TAKEOFF, MASTER CAUTION LIGHT CAME ON DUE TO THE LOSS OF THE RT GENERATOR. AT THE SAME TIME SEVERAL CIRCUIT BREAKERS TRIPPED RESULTING IN TH
- [SDR 2013F00018](https://openairdocs.org/sdr/2013F00018), Jan 15, 2013: SWIVEL FITTING. BLEW OUT. AFTER TAKEOFF PILOT REPORTED NO HYD PRESSURE. UPON LANDING SAFELY AND TROUBLESHOOTING THE ISSUE , FOUND THE MLG ACTUATOR RETRACT SWIVEL FITTING HAD FAILED. R & 
- [SDR CA120812001](https://openairdocs.org/sdr/CA120812001), Aug 4, 2012: WHEEL HALF. DAMAGED. (CAN) AIRCREW REPORTED TIRE BLOW OUT ON ROLL OUT AFTER LANDING. TIRE WAS SERVICED DAY BEFORE FLIGHT NO-DEFECTS WERE REPORTED. THE NR 3 MAIN WHEEL WAS FOUND TO B
- [SDR CA120130008](https://openairdocs.org/sdr/CA120130008), Jan 28, 2012: UPLOCK. FAILED. (CAN) THE PART IN QUESTION WAS INSTALLED TO REPLACE A UNIT THAT WAS LEAKING HYDRAULICS. IT WAS INSTALLED AND TESTED IAW WITH ALL MM REQUIREMENTS AND RELEASED TO
- [SDR CA110923012](https://openairdocs.org/sdr/CA110923012), Sep 22, 2011: PULLEY. OUT OF TOLERANCE. (CAN) DURING A MX WALK AROUND, FOUND A .7500" FREEPLAY IN THE RT AILERON. DURING INVESTIGATION, FOUND THAT THE RT AILERON PULLEY AND SHAFT WERE MOVING INDEPENDE
- [SDR CA110801001](https://openairdocs.org/sdr/CA110801001), Jul 30, 2011: CONVERTER. FAILED. DURING PRE-FLIGHT, CREW MEMBERS NOTICED AN ELECTRICAL BURN ODOR. AFTER MX INVESTIGATION, THE EFB DC STEP DOWN CONVERTER WAS IDENTIFIED AS THE SOURCE. CONVERTERS
- [SDR CA110715001](https://openairdocs.org/sdr/CA110715001), Jul 12, 2011: FIRE LOOP. OUT OF POSITION. ENGINE FIRE INDICATION AFTER TAKEOFF. ACFT RETURNED TO AIRPORT. MX ENGINEERS SENT TO TROUBLESHOOT, DUPLICATED FAULT ON GROUND WITH HIGH POWER SETTINGS ONLY. INS
- [SDR CA110701002](https://openairdocs.org/sdr/CA110701002), Jun 29, 2011: PUMP. FAILED. MAY 14, 2011, CREW REPORTED LOW OIL PRESSURE ON TOUCHDOWN (64 PSI) FOR A FEW SECONDS AND THEN BACK TO NORMAL. OIL PUMP WAS REPLACED WITH AN O/H UNIT. CREW REPOR
- [SDR CA110311003](https://openairdocs.org/sdr/CA110311003), Mar 9, 2011: STARTER GEN. FAILED. (CAN) DURING THE DESCENT TO AIRPORT, AT APPROX. 110 MILES OUT CREW NOTICED VIBRATION. THEY WERE UNABLE TO DETERMINE FROM WHICH SIDE OR IF IT WAS COMING FROM THE
- [SDR 2011F00031](https://openairdocs.org/sdr/2011F00031), Feb 9, 2011: GENERATOR. FAILED. LT AND RT GENERATOR LIGHTS ILLUMINATED. THE GENERATOR FAILURE (DUAL) CHECKLIST WAS PERFORMED. CREW ELECTED TO DIVERT. THE FLIGHT WAS COMPLETED WITH LANDING, WIT
- [SDR DBCA2010110800029](https://openairdocs.org/sdr/DBCA2010110800029), Nov 8, 2010: ACTUATOR. MALFUNCTIONED. ON TAXI FOR DEPARTURE CREW NOTED LT THRUST REVERSER UNLOCK LIGHT WOULD NOT EXTINGUISH AFTER TEST. CREW RETURNED TO RAMP. MX PINNED THRUST REVERSERS IAW AMM 78-3
- [SDR O9I2010F00000](https://openairdocs.org/sdr/O9I2010F00000), Aug 16, 2010: FIRE LOOP. SHORTED. RETURNING WITH A PATIENT ON BOARD, RECEIVED A FIRE LIGHT ON NR 1 ENGINE DESCENDING THROUGH FL370 FROM OUR CRUISE ALTITUDE OF FL390. THE F/O WAS FLYING AND PILOT
- [SDR CA100721007](https://openairdocs.org/sdr/CA100721007), Jul 20, 2010: ALTERNATOR. FAILED. PILOTS REPORTED THAT THEY HAD A DOUBLE GENERATOR FAILURE ENROUTE. THEY WERE ABLE TO RESET THE LT GENERATOR BUT COULD NOT RESET THE RT GENERATOR. UPON ARRIVAL, M
- [SDR CA100721008](https://openairdocs.org/sdr/CA100721008), Jul 19, 2010: SKIN. DEBONDED. A DISBOND BLISTER WAS FOUND ON THE UPPER SKIN AT THE CTR ATTACH FITTING OF THE RT DELTA FIN ROOT AREA. A TAP TEST REVEALED THAT THE DISBOND WAS APPROX 16 SQ". T
- [SDR CA100701006](https://openairdocs.org/sdr/CA100701006), Jul 1, 2010: CONTROL ROD. CHAFED. (CAN) DURING A SCHEDULED INSP, THE RUDDER NON ADJUSTABLE ROD WAS FOUND CHAFING AGAINST A STAINLESS STEEL BRAIDED HYDR LINE AT ZONE 324. ROD REPLACED WITH SERVIC
- [SDR CA100706007](https://openairdocs.org/sdr/CA100706007), Jun 25, 2010: SHUTOFF VALVE. FAILED. (CAN) WHEN RETRIEVING ITEM FROM THE TAIL LOCKER, OBSERVED THE LATCH TO BE VERY HOT TO THE TOUCH. UPON FURTHER INVESTIGATION, DISCOVERED AN ELEVATED TEMPERATURE 
- [SDR CA100525008](https://openairdocs.org/sdr/CA100525008), May 21, 2010: PRESSURE SWITCH. LEAKING. PILOT REPORTED AN HYD LOW CAS MESSAGE IN FLIGHT. UPON INVESTIGATION ON GROUND BY MX, IT WAS DISCOVERED THAT THERE WAS HYD FLUID ON LOWER FUSELAGE. IT WAS LATER 
- [SDR J7SA452041100520](https://openairdocs.org/sdr/J7SA452041100520), May 20, 2010: DOWNLOCK SWITCH. OUT OF RIG. LT MAIN GEAR INDICATOR DID NOT MATCH GEAR HANDLE POSITION. CREW CYCLED SEVERAL TIMES AND LIGHT EVENTUALLY ILLUMINATED ON LT GEAR DOWN POSITION. CREW PERFORMED T
- [SDR CA100204007](https://openairdocs.org/sdr/CA100204007), Feb 2, 2010: DOWNLOCK SWITCH. OUT OF RIG. (CAN) GEAR SWING CARRIED OUT AFTER REPLACEMENT OF STEERING MOTOR. FOUND SERVICEABLE. ACFT ACCEPTANCE TEST FLIGHT WAS CARRIED OUT AND CREW EXPERIENCED NO DOWN LO
- [SDR CA100127001](https://openairdocs.org/sdr/CA100127001), Jan 23, 2010: THROTTLE CABLE. SHEARED. (CAN) ACFT WAS LEAVING AT ABOUT 0330AM. AT THE THRESHOLD, PILOT STARTED TO PUSH THE THROTTLES FWD, WHEN HE NOTICED THAT AT 60 PERCENT N1 THE RT ENGINE WAS ABNOR
- [SDR CA100122006](https://openairdocs.org/sdr/CA100122006), Jan 21, 2010: SLEEVE. CRACKED. (CAN) DURING THE COMPLETION OF SB45-27-40 IT WAS DETERMINED THAT NR 3 (RT INBD) FLAP ACTUATOR BALLSCREW SLEEVE WAS CRACKED APPROX 0.250 INCHES LONG, CTR OF THE 
- [SDR CA090717005](https://openairdocs.org/sdr/CA090717005), Jul 14, 2009: AXLE. CORRODED. (CAN) DURING THE INSTALLATION OF A LANDING GEAR SB (SB45-32-29R1) IT WAS REQUESTED THAT INSP OF THE INTERNAL SURFACES OF THE LANDING GEAR AXLE BEAM ASSY FOR POS
- [SDR CA090714004](https://openairdocs.org/sdr/CA090714004), Jul 13, 2009: WIRE. BURNED. (CAN) DURING POST-FLIGHT CHECK, NOTICED LT LANDING LIGHT WAS INOPERATIVE. FURTHER TROUBLESHOOTING FOUND BURNED WIRE, RAA0238-14, APPROX 12 INCHES AFT OF LT AFT 
- [SDR CA090414002](https://openairdocs.org/sdr/CA090414002), Apr 13, 2009: FLEX DUCT. CRACKED. (CAN) AFTER PILOT REPORTED A "WING/STAB LEAK" MASTER CAUTION MESSAGE, INVESTIGATION OF THE PROBLEM ENDED WHEN A TECH FOUND THE LT HORIZ STABILIZER`S ANTI-ICE FL
- [SDR CA090414004](https://openairdocs.org/sdr/CA090414004), Apr 13, 2009: FLEX DUCT. CRACKED. (CAN) AFTER PILOT REPORTED A "WING/STAB LEAK" MASTER CAUTION MESSAGE, INVESTIGATION OF THE PROBLEM REVEALED THAT THE LT HORIZ STAB ANTI ICE FLEXIBLE DUCT (LOCAT
- [SDR CA090306005](https://openairdocs.org/sdr/CA090306005), Feb 28, 2009: DRIVE UNIT. LEAKING. (CAN) UNIT WAS LEAKING FLUID, THIS IS THE 5TH UNIT WHICH HAS LEAKED AFTER INSTALATION, 0-LEAK RATE GIVEN BY AIRCRAFT MFR.
- [SDR CA090223018](https://openairdocs.org/sdr/CA090223018), Feb 19, 2009: DISPLAY. ODOR. (CAN) THE CREW POWERED UP THE ACFT TO GET THEIR PREFLIGHT CHECK DONE. A FEW SECONDS AFTER POWER UP, THE DU NR 2 WENT BLANK AND A STRONG ELECTRICAL ODOR WENT THR
- [SDR CA090223017](https://openairdocs.org/sdr/CA090223017), Feb 18, 2009: PUMP. FAILED. (CAN) DURING TROUBLESHOOTING, WHITE CAS MESSAGE, L-CAB PRESS FAIL, MX NOTED UN-COMMANDED PRESSURIZATION DURING GROUND RUNS. TROUBLESHOOTING OF SYS, FOUND DEBRIS
- [SDR J7SA452022081221](https://openairdocs.org/sdr/J7SA452022081221), Dec 21, 2008: GENERATOR. FAILED. R/H ENGINE VIBRATION NECESSITATED IN-FLIGHT SHUTDOWN. DURING VIBRATION THE 'EMER BATT' AND EMER SWITCH LIGHTS WOULD BLINK. AIRCRAFT DIVERTED TO KFLL. MAINTENANC
- [SDR CA081222007](https://openairdocs.org/sdr/CA081222007), Dec 19, 2008: AUDIO PANEL. MALFUNCTIONED. (CAN) DURING THE BASIC INSPECTION WITH AIRCRAFT POWER ON, FUMES AND LIGHT SMOKE WHERE NOTICED IN THE COCKPIT. AFTER INSPECTION THE AUDIO WARNING PANEL BOX WAS F
- [SDR CA081024006](https://openairdocs.org/sdr/CA081024006), Oct 10, 2008: GROUND WIRE. OPEN. (CAN) ON LANDING, A WHITE CAS MESSAGE (SECONDARY TRIM FAULT) APPEARED. SYS TROUBLESHOT AND FOUND AN OPEN GROUND WIRE AT RBA0664N-22 AT SPLICESP322. SPLICE REPAI
- [SDR CA080821012](https://openairdocs.org/sdr/CA080821012), Aug 17, 2008: WINDSHIELD. BROKEN. (CAN) WHILE IN CRUISE AT FLT 400 ENROUTE, THE RT WINDSHIELD OUTTER PLY SHATTERED, CAUSING A LOUD BANG. NO DEPRESSURISATION OCCUR, RT WINDSHILED HEAT BECAME INOP

All 201: https://openairdocs.org/engine/garrett-tfe731-2/reports.md

## STCs that may be installed (OpenAirDocs) (1)

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 SE1040EA](https://openairdocs.org/stc/SE1040EA): Installation of hydraulically actuated target type thrust reverser system. Northrop Grumman Comm Aircraft Div

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