# Garrett TPE331-6 - Type: Engine model (FAA registry) - Registry code: 29046 - Manufacturer (registry): GARRETT - Model: TPE331-6 - Engine type: Turbo-prop - Power: 750 hp - Data sheet: [TCDS E4WE](https://openairdocs.org/tcds/E4WE) (OpenAirDocs) - Holder: Honeywell Aerospace US LLC - Installed in: 6 registered aircraft - Page: https://openairdocs.org/engine/garrett-tpe331-6 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 2018-17-15](https://openairdocs.org/ad/2018-17-15): Turbine Engine Combustion Section · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 39 more. Effective Oct 22, 2018 - [AD 2018-13-05](https://openairdocs.org/ad/2018-13-05): Turbine Engine Reduction Gear · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 18 more. Effective Jul 26, 2018 - [AD 2016-21-07](https://openairdocs.org/ad/2016-21-07): Fuel control drive · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 26 more. Effective Nov 28, 2016 - [AD 2016-18-17](https://openairdocs.org/ad/2016-18-17): Compressor impeller · Honeywell International TPE331-10, TPE331-10AV, TPE331-10GP and 22 more. Effective Nov 4, 2016 - [AD 2011-18-51 R1](https://openairdocs.org/ad/2011-18-51-R1): Main shaft bearing · Honeywell International TPE331-1, TPE331-10, TPE331-10A and 82 more. Effective Oct 19, 2011 - [AD 2006-14-03](https://openairdocs.org/ad/2006-14-03): New flight cycle counting method for first, second, and third-stage turbine rotors · Honeywell International TPE331-1, TPE331-10, TPE331-10A and 48 more. Effective Aug 9, 2006 - [AD 2002-25-02](https://openairdocs.org/ad/2002-25-02): First stage compressors implellers · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 35 more. Effective Jan 21, 2003 - [AD 2002-21-15](https://openairdocs.org/ad/2002-21-15): Second stage turbine stator inner seal support · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 9 more. Effective Nov 26, 2002 - [AD 98-04-15](https://openairdocs.org/ad/98-04-15): Turbine Stators · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 9 more. Effective Apr 27, 1998 - [AD 97-15-10](https://openairdocs.org/ad/97-15-10): Engine Inlet Ice Protection · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 39 more. Effective Sep 22, 1997 - [AD 95-16-08](https://openairdocs.org/ad/95-16-08): Life Limited Turbine Components · Honeywell International TPE331-1, TPE331-10, TPE331-10A and 62 more. Effective Sep 5, 1995 - [AD 94-26-07](https://openairdocs.org/ad/94-26-07): Fuel Control Governor Drive · Honeywell International TPE331-10, TPE331-10A, TPE331-10B and 32 more. Effective Apr 18, 1995 - [AD 94-09-08](https://openairdocs.org/ad/94-09-08): Third Stage Stator Turbine Assemblies · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 7 more. Effective May 20, 1994 - [AD 93-15-11](https://openairdocs.org/ad/93-15-11): Propeller Pitch Control (PPC) Gasket · Honeywell International TPE331-1, TPE331-10, TPE331-10A and 58 more. Effective Sep 7, 1993 - [AD 92-26-08](https://openairdocs.org/ad/92-26-08): Third Stage Stator Assemblies · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 7 more. Effective Jul 15, 1993 - [AD 93-05-09](https://openairdocs.org/ad/93-05-09): Third Stage Turbine Stator Assemblies · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 9 more. Effective Jun 28, 1993 - [AD 89-07-07 R1](https://openairdocs.org/ad/89-07-07-R1): Oil Scavenge Pump Assembly · Honeywell International TPE331-1, TPE331-10, TPE331-10R and 26 more. Effective Oct 30, 1989 - [AD 84-10-06 R1](https://openairdocs.org/ad/84-10-06-R1): Fuel Pump Assemblies · Honeywell International TPE331-1, TPE331-10, TPE331-10B and 45 more. Effective Dec 26, 1984 - [AD 84-01-04](https://openairdocs.org/ad/84-01-04): Third Stage Turbine Wheels · Honeywell International TPE331-1, TPE331-1U, TPE331-1UA and 11 more. Effective Jan 25, 1984 - [AD 73-26-07 R3](https://openairdocs.org/ad/73-26-07-R3): Fuel Pump Shaft Internal Drive Splines · Honeywell International TPE331-1, TPE331-1U, TPE331-1UA and 39 more. Effective Jul 31, 1980 - [AD 78-25-08 R3](https://openairdocs.org/ad/78-25-08-R3): Turbine Rotor · Honeywell International TPE331-1, TPE331-1U, TPE331-1UA and 11 more. Effective Jun 12, 1980 - [AD 78-05-02](https://openairdocs.org/ad/78-05-02): Propeller Pitch Control Cam Follower Pin · Honeywell International TPE331-1, TPE331-1U, TPE331-1UA and 11 more. Effective Apr 5, 1979 - [AD 76-16-01](https://openairdocs.org/ad/76-16-01): Bearing Oil Transfer Tube · Honeywell International TPE331-1, TPE331-1U, TPE331-1UA and 11 more. Effective Aug 6, 1976 - [AD 75-10-05](https://openairdocs.org/ad/75-10-05): Torque Sensor Assembly Mounting Arm · Honeywell International TPE331-1, TPE331-2, TPE331-3U and 3 more. Effective Jul 11, 1975 - [AD 74-10-10](https://openairdocs.org/ad/74-10-10): Fuel Control Assembly Support Bracket · Honeywell International TPE331-1, TPE331-2, TPE331-3U and 2 more. Effective Jul 11, 1975 - [AD 74-24-05](https://openairdocs.org/ad/74-24-05): Propeller Pitch Control Sleeve Assembly · Honeywell International TPE331-3U, TPE331-3UW, TPE331-5 and 1 more. Effective Nov 26, 1974 Historical (superseded or no longer in force): - [AD 2018-02-14](https://openairdocs.org/ad/2018-02-14) (historical): Turbine Engine Combustion Section · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 38 more. Effective Feb 28, 2018 - [AD 2015-12-04](https://openairdocs.org/ad/2015-12-04) (historical): Fuel control unit (FCU) · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 26 more. Effective Jul 22, 2015 - [AD 2011-18-51](https://openairdocs.org/ad/2011-18-51) (historical): Main shaft bearing · Honeywell International TPE331-1, TPE331-10, TPE331-10A and 82 more - [AD 2006-15-08](https://openairdocs.org/ad/2006-15-08) (historical): Woodward fuel control unit (FCU) assemblies · Honeywell International TPE331-1, TPE331-10, TPE331-10AV and 26 more. Effective Aug 24, 2006 - [AD 91-04-02](https://openairdocs.org/ad/91-04-02) (historical): Third stage stator assembly · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 7 more - [AD 90-21-01](https://openairdocs.org/ad/90-21-01) (historical): Third stage stator assembly · Honeywell International TPE331-1, TPE331-2, TPE331-2UA and 7 more ## Information bulletins (advisory) (1) - [SAIB NE-16-18](https://openairdocs.org/saib/NE-16-18): Power Lever Loss of Power Control. Issued Jul 11, 2016 ## Registered aircraft (6) - [N312MB](https://openairdocs.org/aircraft/N312MB): [N312mb LLC](https://openairdocs.org/faa-owner/N312MB%20LLC), [Wilmington, DE](https://openairdocs.org/faa-place/DE/Wilmington), built 1981, S/N BE-113 - [N3532](https://openairdocs.org/aircraft/N3532): [North Delta Ag Aviation LLC](https://openairdocs.org/faa-owner/NORTH%20DELTA%20AG%20AVIATION%20LLC), [Sledge, MS](https://openairdocs.org/faa-place/MS/Sledge), built 1977, S/N BE-31 - [N3538](https://openairdocs.org/aircraft/N3538): [New Mountain Aviation LLC](https://openairdocs.org/faa-owner/NEW%20MOUNTAIN%20AVIATION%20LLC), [Englewood, CO](https://openairdocs.org/faa-place/CO/Englewood), built 1978, S/N BE-57 - [N5530T](https://openairdocs.org/aircraft/N5530T): [Speedster LLC](https://openairdocs.org/faa-owner/SPEEDSTER%20LLC), [Kalispell, MT](https://openairdocs.org/faa-place/MT/Kalispell), built 2009, S/N 001 - [N700BA](https://openairdocs.org/aircraft/N700BA): [Aviation Inventory Resources Inc](https://openairdocs.org/faa-owner/AVIATION%20INVENTORY%20RESOURCES%20INC), [Alvarado, TX](https://openairdocs.org/faa-place/TX/Alvarado), built 1980, S/N BE-84 - [N948HB](https://openairdocs.org/aircraft/N948HB): [New Mountain Aviation LLC](https://openairdocs.org/faa-owner/NEW%20MOUNTAIN%20AVIATION%20LLC), [Englewood, CO](https://openairdocs.org/faa-place/CO/Englewood), built 1980, S/N BE-98 ## NTSB investigations (2) 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 CEN22FA215](https://openairdocs.org/ntsb/CEN22FA215), May 28, 2022: Grumman American Avn. G-164 (N178LB), Whiskerville, AR, destroyed, 1 fatal. Probable cause: The pilot misjudged the approach during the emergency landing, likely due to the full chemical load, and impacted a ditch, resulting in substantial damage and postimpact fire. Contributing to the… - [NTSB CEN21LA132](https://openairdocs.org/ntsb/CEN21LA132), Feb 18, 2021: Beech B100 (N312MB), Lubbock, TX, substantial damage. Probable cause: The failure of the right-side window inner pane for reasons that could not be determined based on available evidence. ## FAA accident and incident reports (2) 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 20220528006269A](https://openairdocs.org/incident/20220528006269A), May 28, 2022: Grumman American Avn. Corp G-164B (N178LB), Whiskerville, AR, Destroyed, 1 fatal. On may 28, 2022, at approximately 1340 CST, a 1977 Grumman American aviation; model: G-164B serial number: 178B; registered as N178LB, was destroyed when it… - [Incident 20210217000589I](https://openairdocs.org/incident/20210217000589I), Feb 17, 2021: Beech B100 (N312MB), Lubbock, TX, Minor damage. Window delaminated and shattered in flight. ## Service difficulty reports (31) As reported by operators and repair stations, by the model named in the report. - [SDR ZP7A20140301001](https://openairdocs.org/sdr/ZP7A20140301001), Mar 1, 2014: ENGINE. SHUTDOWN. DURING DESCENT, AT 13,900 FT, EXPERIENCED A BRIEF LT ENGINE ROLLBACK. ALL IGNITERS AND PUMPS WERE ON AT THE TIME. RELIT ON ITS OWN, LEAVING THE LT BLEED AIR FAI - [SDR 2007FA0000196](https://openairdocs.org/sdr/2007FA0000196), Feb 20, 2007: COVER. BROKEN. PILOT REPORTED HIGH OIL CONSUMPTION, INSPECTED LT ENGINE SCAVENGE PUMP AND FOUND THE PUMP COVER BROKEN AND MISSING PIECES. ALSO FOUND THE SCAVENGE PUMP OIL TUBE - [SDR 2006FA0001132](https://openairdocs.org/sdr/2006FA0001132), Oct 26, 2006: ENGINE. FAILED. DURING GROUND RUN FRO A POSSIBLE GENERATOR PROBLEM. WITH THE ENGINE AT FLIGHT IDLE AND SPEED LEVERS FORWARDTHE RT ENGINE HAD A UNCONTAINED ENGINE FAILURE. 2 PIE - [SDR YJ42006F00000](https://openairdocs.org/sdr/YJ42006F00000), Jun 27, 2006: STARTER GEN. SLIPPED. DURING A CHECKRIDE, THE CHIEF PILOT SHUTDOWN THE RT ENGINE IN FLIGHT. WHEN ATTEMPTING RE-START, THE FUEL LEVER JAMMED IN THE CUTOFF POSITION. THE CREW CONDUCTED - [SDR 2006FA0000586](https://openairdocs.org/sdr/2006FA0000586), May 18, 2006: STARTER GEN. SEIZED. RT ENGINE WOULD NOT START. TROUBLESHOT AND FOUND RT STARTER GENERATOR SEIZED DUE TO BRUSHES WORN BEYOND LIMITS AND PIGTAILS ARCHING TO ARMATURE. (K) - [SDR CA060503005](https://openairdocs.org/sdr/CA060503005), Dec 20, 2005: PLENUM. CRACKED. (CAN) AC TOOK OFF, AC CRASHED, POST-CRASH FIRE OCCURRED. AC WAS DESTROYED. BOTH PILOTS FATALLY INJURED. DURING TEAR-DOWN OF RT ENG (WHICH WAS FOUND TO BE OPERAT - [SDR CA060503006](https://openairdocs.org/sdr/CA060503006), Dec 20, 2005: PLENUM. CRACKED. (CAN) AIRCRAFT TOOK OFF FROM AIRPORT RUNWAY 15 OR A COURIER FLIGHT. THE AIRCRAFT CRASHED ABOUT 500 METERS EAST OF, AND APPROXIMATELY ABEAM, THE SOUTH END OF RUN - [SDR 20010105CW001](https://openairdocs.org/sdr/20010105CW001), Dec 4, 2000: SHAFT. SHEARED. LT ENGINE FLAMED OUT 5 MILES FROM AIRPORT, TRIED TO RESTART, NO RESTART. PROBLEM WAS SHEAR TORSION SHAFT IN GEAR BOX. REPLACED TORSION SHAFT IN GEAR BOX. FUNCTI - [SDR 20000920SH006](https://openairdocs.org/sdr/20000920SH006), Aug 31, 2000: DRIVE SHAFT. WORN. DURING ROUTINE INSPECTION, STARTER DRIVESHAFT WAS FOUND WORN BEYOND SERVICEABLE LIMITS AT 310.5 HOURS AFTER ENGINE OVERHAUL. (X) - [SDR CA000905002](https://openairdocs.org/sdr/CA000905002), Aug 22, 2000: TUBE. CRACKED. (CAN) THE ENGINE WAS SHUTDOWN IN FLIGHT AS A PRECAUTION DUE TO AN OIL LEAK AND LOW OIL PRESSURE. ONCE ON THE GROUND, THE SOURCE OF THE OIL LEAK COULD NOT POSITI - [SDR 20000814SH012](https://openairdocs.org/sdr/20000814SH012), Jul 25, 2000: ENGINE. MAKING METAL. DURING A PHASE INSPECTION, THE LEFT ENG OIL FILTER WAS FOUND TO HAVE EXCESSIVE METAL IN OIL FILTER. ANALYSIS ON OIL AND FILTER WAS COMPLETED. METAL WAS FOUND TO - [SDR CA000606003](https://openairdocs.org/sdr/CA000606003), Jun 1, 2000: VALVE. MALFUNCTIONED. (CAN) DURING CRUISE, THE CREW STARTED TO TRANSFER TIP FUEL WITH NO PROBLEM. WHEN THE CREW SELECTED TIP TRANSFER OFF, THE RT TIP TANK CONTINUED TO FLOW UNTIL TIP - [SDR 20000623SH015](https://openairdocs.org/sdr/20000623SH015), May 20, 2000: FITTING. DETERIORATED. OIL SUPPLY LINE FOR OIL COOLER, FITTING THREADS IN CASE DETERIORATED ALLOWING FITTING TO BLOW OUT. THIS ALLOWED ENGINE OIL TO PUMP OUT. PILOT SHUT ENGINE DOWN W - [SDR 20000515SH028](https://openairdocs.org/sdr/20000515SH028), May 3, 2000: BEARING. FAILED. COMPRESSOR BEARING FAILED 14.7 HOURS AFTER OVERHAUL CAUSING MAJOR FAILURE DAMAGE TO ENGINE. (X) - [SDR CA000215006](https://openairdocs.org/sdr/CA000215006), Feb 9, 2000: SWITCH. FROZEN. (CAN) THE CREW SELECTED GEAR DOWN ON APPROACH AND THE GEAR FAILED TO EXTEND. THE CREW ELECTED TO OVERSHOOT AND RETURN TO THEIR MAIN BASE. ON APPROACH TO THE MAI - [SDR CA000209006](https://openairdocs.org/sdr/CA000209006), Feb 8, 2000: ACTUATOR. FROZEN. (CAN) THE LANDING GEAR FAILED TO EXTEND WHEN SELECTED DUE TO A FROZEN DOOR ACTUATOR CLUTCH. THE CREW THEN INITIATED AN EMERGENCY EXTENSION WHICH WAS UNSUCCESSFU - [SDR CA000120006](https://openairdocs.org/sdr/CA000120006), Jan 17, 2000: ROLLER. MISSING. (CAN) THE CREW TRIED TO EXTEND THE LANDING GEAR USING THE EMERGENCY EXTENSION SYSTEM, AFTER A LANDING GEAR MALFUNCTION. THE LANDING GEAR COULD NOT BE EXTENDED A - [SDR CA980602013](https://openairdocs.org/sdr/CA980602013), May 12, 1998: LINE. CRACKED. (CAN) ON SHORT FINAL, WHILE DOING PRE-LANDING CHECK, THE CREW NOTICED OIL ON THE RIGHT ENGINE COWL. NORMAL LANDING CARRIED OUT. INVESTIGATION REVEALED A CRACKED - [SDR CA980317020](https://openairdocs.org/sdr/CA980317020), Mar 13, 1998: ACTUATOR. FAILED. (CAN) OVERHAULED GEAR DOOR ACTUATOR INSTALLED TO RECTIFY A PREVIOUS PROBLEM. GROUND TEST OK. TEST FLIGHT FORWARD GEAR DOORS FAILED TO OPEN AND GEAR MANUALLYLOWE - [SDR CA980317019](https://openairdocs.org/sdr/CA980317019), Mar 12, 1998: ACTUATOR. FAILED. (CAN) DURING DEPARTURE THE FORWARD GEAR DOORS WOULD NOT OPEN, PREVENTING GEAR RETRACTION. INVESTIGATION FOUND THE FORWARD GEAR DOOR ACTUATOR WAS DEVELOPING INSU - [SDR 98ZZZX1276](https://openairdocs.org/sdr/98ZZZX1276), Feb 17, 1998: ENGINE. SEIZED. RIGHT ENGINE INSTALLATION AFTER REPAIRS FOR BIRD INGESTION AND COMPLETION OF HSI. AIRCRAFT WAS ON A FLIGHT CHECK FOR THE REQUIRED IN-FLIGHT NTS CHECK. ENG WAS S - [SDR 97ZZZX4851](https://openairdocs.org/sdr/97ZZZX4851), Nov 4, 1997: PLENUM. FAILED. ENG FAILURE AT T/O. CREW HEARD A LOUD POP, THE RT ENG ITT TEMP ROSE AND FLAMES FROM THE RT ENG. UNABLE TO KILL THE ENG USING THE EMERG CUTOFF LEVER, LEVER WAS J - [SDR CA971113013](https://openairdocs.org/sdr/CA971113013), Oct 24, 1997: GASKET. FAILED. (CAN) DURING CRUISE, CREW NOTICED FLUCTUATING OIL PRESSURE ON LT ENGINE. OIL PRESSURE MONITORED AND AIRCRAFT LANDED. FRETTED AND DETERIORATED TURBINE SCAVANGE P - [SDR CA970226002](https://openairdocs.org/sdr/CA970226002), Feb 21, 1997: BULL GEAR. FAILED. (CAN) DURING CRUISE, THE RIGHT HAND ENGINE SUDDENLY FEATHERED. ENGINE SECURED. INSPECTION FOUND THAT THE BULL GEAR HAD FAILED EITHER IN THE GEAR TOOTH BASE AND/ - [SDR CA961205011](https://openairdocs.org/sdr/CA961205011), Nov 28, 1996: GEAR DOOR. FROZEN. (CAN) ICE CONTAMINATION IN THE GEAR DOOR ACTUATOR CAUSED THE PILOT ABORT THE APPROACH. SUBSEQUENT CYCLING OF THE GEAR PRODUCED A GEAR DOWN AND LOCKED CONDITION - [SDR CA961128010](https://openairdocs.org/sdr/CA961128010), Nov 26, 1996: SWITCH. FROZEN. (CAN) ON APPROACH WHEN GEAR SELECTED DOWN, NO RESPONSE. GEAR LOWERED MANUALLY. IT IS ASSUMED THAT THE NOSE GEAR DOWN LOCK SWITCH HAD PICKED UP WATER CONTAMINATI - [SDR CA961203001](https://openairdocs.org/sdr/CA961203001), Nov 6, 1996: SWITCH. BROKEN WIRE. (CAN) DURING APPROACH THE PILOT COULD NOT GET AN INDICATION OF THE NOSE GEAR DOWN AND LOCKED. EMERGENCY EXTENSION PERFORMED AND THE AIRCRAFT LANDED SAFELY. MAIN - [SDR CA961113002](https://openairdocs.org/sdr/CA961113002), Nov 5, 1996: WIRE. BROKEN. (CAN) ON APPROACH WHEN GEAR SELECTED DOWN, DID NOT GET A GREEN LIGHT ON THE NOSE GEAR. GEAR CYCLED WITH NO CHANGE. EMERGENCY EXTENSION USED. INVESTIGATION REVEA - [SDR CA970130004](https://openairdocs.org/sdr/CA970130004), Nov 5, 1996: SWITCH. WIRE BROKEN. (CAN) ON APPROACH THE CREW WERE UNABLE TO GET A GREEN LIGHT ON THE NOSE GEAR. THE SYSTEM WAS CYCLED AND A SUCCESSFUL LANDING WAS MADE. INVESTIGATION REVEALED A - [SDR CA960619002](https://openairdocs.org/sdr/CA960619002), Jun 13, 1996: SWITCH. SHORTED. (CAN) ON GEAR EXTENSION, 3 GREEN LIGHTS SHOWED MOMENTARILY THEN WENT OUT AS THE GEAR DOORS CLOSED. FORWARD LEFT GEAR DOOR SWITCH FAILED AND SHORTED TO GROUND IN - [SDR 95ZZZX5254](https://openairdocs.org/sdr/95ZZZX5254), Aug 24, 1995: SHROUD. MISINSTALLED. THE LEFT ENGINE WAS VERY SLOW TO START. INVESTIGATION REVEALED THE FUEL NOZZLE SHROUD WAS INSTALLED 180 DEGREES FROM CORRECT POSITION WHICH BLOCKED FUEL FLOW TH ## 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 SE00265AT](https://openairdocs.org/stc/SE00265AT): Install Ayres Fuel Manifold Purge Assembly Kit, P/N 21757-1 in accordance with "Installation Instructions - Ayres P/N 21757-1 Fuel Manifold Purge Assy-Kit" Dwg. No. 21757-1(1), Revision none, dated April 20, 1993, or later FAA approved revision. Thrush Aircraft Inc - [STC SE00229AT](https://openairdocs.org/stc/SE00229AT): Installation of Garrett TPE331-10 Combustor and Turbine in TPE331-6 engine. National Flight Services, Inc - [STC SE68WE](https://openairdocs.org/stc/SE68WE): Deletion of fireshield installation kit. 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