# Garrett TPE331-10UGR - Type: Engine model (FAA registry) - Registry code: 29069 - Manufacturer (registry): GARRETT - Model: TPE331-10UGR - Engine type: Turbo-prop - Power: 940 hp - Data sheet: [TCDS E4WE](https://openairdocs.org/tcds/E4WE) (OpenAirDocs) - Holder: Honeywell Aerospace US LLC - Installed in: 2 registered aircraft - Page: https://openairdocs.org/engine/garrett-tpe331-10ugr 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 2018-22-01](https://openairdocs.org/ad/2018-22-01): Turbine Section · Honeywell International TPE331-10, TPE331-10N, TPE331-10R and 8 more. Effective Dec 10, 2018 - [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 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 2015-18-03](https://openairdocs.org/ad/2015-18-03): Engine propeller shaft coupling failures · Honeywell International TPE331-10, TPE331-10R, TPE331-10U and 8 more. Effective Nov 13, 2015 - [AD 2012-02-06](https://openairdocs.org/ad/2012-02-06): First stage turbine disks · Honeywell International TPE331-10, TPE331-10AV, TPE331-10GP and 12 more. Effective Mar 15, 2012 - [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 2009-17-05](https://openairdocs.org/ad/2009-17-05): First stage turbine disks · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 20 more. Effective Sep 1, 2009 - [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 2004-09-29](https://openairdocs.org/ad/2004-09-29): First Stage Turbine Disks · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 20 more. Effective Jun 15, 2004 - [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 98-12-09](https://openairdocs.org/ad/98-12-09): Fuel Manifold · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 29 more. Effective Aug 7, 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 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 93-02-01](https://openairdocs.org/ad/93-02-01): Stratoflex Fuel Manifold Assemblies · Honeywell International TPE331-10, TPE331-10A, TPE331-10B and 21 more. Effective Mar 18, 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 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 88-12-10](https://openairdocs.org/ad/88-12-10) (historical): Turbine Rotor · Honeywell International TPE331-10, TPE331-10R, TPE331-10U and 6 more. Effective Jun 6, 1988 - [AD 92-02-19 PL](https://openairdocs.org/ad/92-02-19-PL) (historical): Fuel Manifold Assembly Leak · Honeywell International TPE331-10, TPE331-10A, TPE331-10AV and 29 more ## Information bulletins (advisory) (2) - [SAIB NE-16-19](https://openairdocs.org/saib/NE-16-19): Turbine Engine Compressor Section Stator Nozzle Distress. Issued Jul 22, 2016 - [SAIB NE-16-18](https://openairdocs.org/saib/NE-16-18): Power Lever Loss of Power Control. Issued Jul 11, 2016 ## Registered aircraft (2) - [N1050H](https://openairdocs.org/aircraft/N1050H): [Bush Monster LLC](https://openairdocs.org/faa-owner/BUSH%20MONSTER%20LLC), [Caldwell, ID](https://openairdocs.org/faa-place/ID/Caldwell), built 2024, S/N 001 - [N999XT](https://openairdocs.org/aircraft/N999XT): [Beck Nicholas G](https://openairdocs.org/faa-owner/BECK%20NICHOLAS%20G), [Ione, CA](https://openairdocs.org/faa-place/CA/Ione), built 2012, S/N 9 ## 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 (29) As reported by operators and repair stations, by the model named in the report. - [SDR CA150727015](https://openairdocs.org/sdr/CA150727015), Jul 19, 2015: CONNECTOR. FAILED. (CAN) LEFT TTL INTRODUCES LACK OF TEMP AT ALL POWER SETTINGS. FOUND CONNECTOR PLUG THAT ATTACHES TO THE TTL COMPUTER WAS SHORTING OUT INTERNALLY. THIS CAUSED TH - [SDR CA131218020](https://openairdocs.org/sdr/CA131218020), Dec 17, 2013: B-NUT. DEFECTIVE. (CAN) IN CRUISE FLIGHT, AT 13,000 FT CREW OBSERVED A RT ENGINE OIL PRESSURE ANNUNCIATOR RED CAPTION ACCOMPANIED BY LOW PRESSURE OF THE RT OIL PRESSURE GAUGE. PR - [SDR CA131015001](https://openairdocs.org/sdr/CA131015001), Oct 13, 2013: ADAPTER. CRACKED. (CAN) DURING A MAINTENANCE INSPECTION ON THE LT ENGINE STARTER GENERATOR ASSY, THE MOUNTING ADAPTER WAS OBSERVED WITH A CRACK THROUGH THE WEB ADJACENT TO A MOUN - [SDR CA130325006](https://openairdocs.org/sdr/CA130325006), Mar 19, 2013: BEARING. FAILED. (CAN) INTERVIEWED THE MAINTENANCE PERSONNEL INVOLVED WITH THE RECTIFICATION OF THE DEFECT. IT WAS DETERMINED TO BE A REAR BEARING FAILURE, FAN END, OF THE START - [SDR CA121107004](https://openairdocs.org/sdr/CA121107004), Nov 5, 2012: COMBUST CHAMBER. CRACKED. (CAN) CREW REPORTED THAT WHEN POWER LEVER ADVANCED ENGINE COULD ONLY ACHIVE 40 PERCENT TORQUE RT. TAKEOFF RUN ABORTED AND ACFT RETURNED TO HANGAR. MAINTENANCE C - [SDR CA120913005](https://openairdocs.org/sdr/CA120913005), Jul 10, 2012: BOLT. LOOSE. (CAN) FOLLOWING ENGINE STARTUP THE FLIGHT CREW WERE NOT ABLE TO GET THE GENERATOR TO COME ONLINE. THE ENGINE WAS SHUTDOWN WITHOUT ANY OTHER INDICATIONS. MAINTEN - [SDR CA120109005](https://openairdocs.org/sdr/CA120109005), Jan 6, 2012: CONNECTOR. ARCED. (CAN) AFTER BEING CLEARED FOR TAKEOFF AND WHILE TAXIING IN FOR RUNWAY 24L, THE F/O WAS PERFORMING THE "BEFORE TAKEOFF" CHECKLIST. AT THE ITEM "WINDSHIELD & PITO - [SDR CA111011015](https://openairdocs.org/sdr/CA111011015), Oct 11, 2011: CONTROL CABLE. MISINSTALLED. (CAN) DURING A MX INSPECTION OF THE RUDDER TRIM TAB CONTROL SYS, IT WAS NOTED THAT THE RUDDER TRIM CABLES WERE CROSSED IN THE L/E OF THE RUDDER ABOVE THE LOWER - [SDR CA111017005](https://openairdocs.org/sdr/CA111017005), Oct 10, 2011: LINE. BROKEN. (CAN) LINE FOUND BROKEN ON NR 1 ENGINE WHILE PERFORMING OTHER MX ON ENGINE. - [SDR CA110921003](https://openairdocs.org/sdr/CA110921003), Sep 21, 2011: PICCOLO TUBE. CRACKED. (CAN) DURING A HMV THE NR 2 ENG INTAKE COWL WAS REMOVED, UPON FURTHER INSPECTION OF THE COWL LOOSE RIVETS WERE NOTICED BEHIND THE INTAKE LIP. THE TECH PROCEDED - [SDR CA110617008](https://openairdocs.org/sdr/CA110617008), Jun 14, 2011: HOSE. CHAFED. THE ACFT EXPERIENCED A LOSS OF HYD PRESSURE ON THE RT HYD SYS DUE TO A CHAFED HOSE. THE FAILED NON RETURN VALVE DID NOT ALLOW THE REMAINING OPS LT HYD PUMP TO M - [SDR CA110114007](https://openairdocs.org/sdr/CA110114007), Jan 12, 2011: LINE. LOOSE. HYDRAULIC LEAK NOTED IN RT WHEEL WELL BAY. INVESTIGATION REVEALED ONE LEAKING LINE AND ONE BADLY CHAFED LINE. THE LINES HAD BECOME LOOSE IN A PHENOLIC BLOCK AND - [SDR CA110104008](https://openairdocs.org/sdr/CA110104008), Dec 28, 2010: ANTENNA. FAILED. DUAL GPS HAVE BEEN INSTALLED ON A/C UNDER LSTC C-LSA09-302/D ON THIS A/C. GPS ANTENNAS, ADAPTERS AND DISPLAYS ARE THIS ITEMS THAT WERE INSTALLED UNDER LSTC. DUR - [SDR CA110627022](https://openairdocs.org/sdr/CA110627022), Dec 8, 2010: PIN. INOPERATIVE. ACFT ARRIVED WITH A NLG STEERING SNAG. NLG WAS CHANGED WITH A SERVICABLE ASSY. THE ACFT TOOK OFF THE NEXT MORNING ON SCHEDULED DEPARTURE, IT RETURNED WITH A SNA - [SDR CA101203003](https://openairdocs.org/sdr/CA101203003), Dec 3, 2010: BOLT. BROKEN. DURING COMPLETION OF SB 53-A-JA870510 INSP OF NLG RETRACTION JACK UPPER MOUNTING FITTING SECURING BOLTS ONE OF THE UPPER BOLTS WAS FOUND BROKEN. THE BOLT WAS RE - [SDR CA101118001](https://openairdocs.org/sdr/CA101118001), Nov 12, 2010: TACH GENERATOR. FAILED. RPM INDICATION FELL OFFLINE ON THE TAKEOFF ROLL. - [SDR CA101028003](https://openairdocs.org/sdr/CA101028003), Oct 25, 2010: STRUCTURE. CORRODED. (CAN) PASSENGER DOOR SEAL HAD SMALL TEAR IN IT CAUSING A PRESSURIZATION LEAK AROUND THE PASSENGER ENTRY DOOR. UPON INSPECTION OF DOOR SEAL SOME CORROSION WAS NO - [SDR CA101015006](https://openairdocs.org/sdr/CA101015006), Oct 14, 2010: SKIN. CORRODED. DURING INTERNAL DVI OF THE LT WING TANK IT WAS NOTED THAT THERE WAS CORROSION UNDER THE LT BOOST PUMP IN THE INTERNAL FUEL TANK OF THE LT WING. UPON FURTHER INV - [SDR CA091119005](https://openairdocs.org/sdr/CA091119005), Nov 18, 2009: WIRE. DAMAGED. (CAN) ON APPROACH , WHEN LANDING GEAR WAS LOWERED, THERE WAS NO "DOWN AND LOCKED" INDICATION ON THE NLG. THE PILOT`S ABORTED LANDING AND RETURNED TO BASE. ON AP - [SDR CA091029005](https://openairdocs.org/sdr/CA091029005), Oct 29, 2009: PUMP. FAILED. (CAN) SUSPECT THAT THE HIGH PRESSURE FUEL PUMP DRIVE FAILED IN THE ENG GEARBOX CAUSING THE ENG TO SHUTDOWN IN FLIGHT. WHEN WE SPIN THE PROP NOISES ARE COMING FR - [SDR CA090728010](https://openairdocs.org/sdr/CA090728010), Jul 26, 2009: CONTACTOR. FAULTY. THE ACFT WAS ON A TRAINING FLIGHT IN CRUISE, THE LT GENERATOR AND STARTER LIGHT FLICKERED AND THEN STAYED ON. THE LT ENG WAS SHUTDOWN AND THE ACFT RETURNED TO B - [SDR CA090709004](https://openairdocs.org/sdr/CA090709004), Jul 4, 2009: BEARING. FAILED. (CAN) ACFT WAS IN CRUISE MODE WHEN ENG FLAMED OUT AND CHIP DETECTOR LIGHT CAME ON. ENG DID NTS AS REQUIRED AND WAS FEATHERED BY CREW. TEARDOWN OF THE ENG INDICA - [SDR CA090618011](https://openairdocs.org/sdr/CA090618011), Jun 15, 2009: SPRING. DAMAGED. (CAN) AD 006-12-99 WAS CARRIED OUT IN 2000. NO FAULTS FOUND. NO REPEAT INSP REQUIRED IAW AD. REMOVED TAILCONE TO DO A GENERAL INTERNAL INSP. VISUAL SAW UPPER AN - [SDR CA090609009](https://openairdocs.org/sdr/CA090609009), Jun 8, 2009: ROD. FAULTY. (CAN) DURING GEAR RETRACTION DURING CLIMB, IT WAS NOTED THAT RT MAIN LANDING GEAR FAILED TO FULLY RETRACT. IT WAS ALSO VISUALLY CONFIRMED. THE GEAR WAS SELECTED - [SDR CA090512008](https://openairdocs.org/sdr/CA090512008), May 4, 2009: O-RING. TWISTED. (CAN) OIL LEAKAGE OCCURRED ON 2 SEPARATE OCCASIONS ON PROPELLER. OIL FOUND LEAKING FROM CYL PLUG AND START LATCH HOLES. UPON DISSEMBLY OF THE PROP DOME FOUND PI - [SDR CA080912008](https://openairdocs.org/sdr/CA080912008), Sep 12, 2008: FITTING. CORRODED. (CAN) THIS DOOR WAS INSTALLED AS A REPLACEMENT DUE TO SEVERE CORROSION FOUND ON ORIGINAL DOOR. REPLACEMENT DOOR INSPECTED AND CORROSION DISCOVERED UNDER SEVERAL - [SDR CA080828004](https://openairdocs.org/sdr/CA080828004), Aug 28, 2008: FITTING. WORN. (CAN) TAPER PINS PN SP28N14 FOUND SLIGHTLY LOOSE AT SPRING END FITTING ASSY. - [SDR CA080828005](https://openairdocs.org/sdr/CA080828005), Aug 27, 2008: SPUR GEAR. DAMAGED. (CAN) FRONT GEAR CASE ON ENG REMOVED FOR TORQUE RING REPLACEMENT. PITTING FOUND ON SPUR AND HELICAL GEAR ASSY. CONSULTATION WITH ENGINE OVERHAUL FACILITY IS ON - [SDR CA080912007](https://openairdocs.org/sdr/CA080912007), Aug 17, 2008: ATTACH FITTING. CORRODED. (CAN) SEVERE CORROSION NOTED AT MAIN CABIN DOOR ATTACH FITTINGS. CORROSION ALSO NOTED UNDER SEVERAL DOOR SEAL CLIPS. DOOR DEEMED BEYOND ECOMONICAL REPAIR AND RE ## 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 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 --- 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.