# Garrett TPE331-10UA - Type: Engine model (FAA registry) - Registry code: 29040 - Manufacturer (registry): GARRETT - Model: TPE331-10UA - Engine type: Turbo-prop - Power: 840 hp - Data sheet: [TCDS E4WE](https://openairdocs.org/tcds/E4WE) (OpenAirDocs) - Holder: Honeywell Aerospace US LLC - Installed in: 0 registered aircraft - Page: https://openairdocs.org/engine/garrett-tpe331-10ua 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 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 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 None registered with this engine model now. ## 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 20111209028549I](https://openairdocs.org/incident/20111209028549I), Dec 9, 2011: Swearingen SA226TC (N200PT), Ft Lauderdale, FL, No damage. PIC landed the aircraft and slowed to speed suitable for activating the nose wheel steering .once nose wheel steering was activated the aircraft nosed over to… ## Service difficulty reports (375, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR CA190801009](https://openairdocs.org/sdr/CA190801009), Jul 31, 2019: SOLENOID. MALFUNCTIONED. (CAN) CREW WERE LINED UP FOR TAKEOFF, AS THEY ADVANCED THE SPEED LEVERS THE L/H ENGINE SHUT DOWN. THE AIRCRAFT TAXIED BACK TO THE MAINTENANCE HANGAR ON ONE ENGI - [SDR CA190614012](https://openairdocs.org/sdr/CA190614012), Jun 10, 2019: CARRIER ASSY. DAMAGED. (CAN) ENGINE HAD A SOAP SAMPLE COME BACK THAT INDICATED MAJOR ALLOY STEAL, MANUFACTURER INDICATED ON THE SOAP IT REQUIRED INSPECTION RIGHT AWAY DUE TO THE FINDI - [SDR CA190508001](https://openairdocs.org/sdr/CA190508001), Feb 12, 2019: O-RING. CHAFED. (CAN) LOWER ENGINE COWLING OIL COOLER INTAKE IS HEATED WITH ENGINE OIL. ABOVE THE OIL RING (INTAKE LIP) THERE IS A RUBBER TRANSITION DUCT THAT CONNECTS THE INTA - [SDR CA180207026](https://openairdocs.org/sdr/CA180207026), Feb 17, 2017: GEAR. DAMAGED. (CAN) THE AIRCRAFT WAS IN FIGHT AND THE PILOTS NOTICED A CHIP LIGHT CAME ON FOR THE RT ENGINE. THE AIRCRAFT CAME TO BASE AND MAINTENANCE DID A OIL SAMPLE AND IN - [SDR CA160314011](https://openairdocs.org/sdr/CA160314011), Mar 10, 2016: TURBINE BLADES. BROKEN. (CAN) THE ACFT WAS IN THE HANGER FOR A ROUTINE DAILY INSPECTION WHEN MAINTENANCE NOTICED THAT WHEN HE LOOKED UP THE EXHAUST PIPE ON THE ENGINE THAT HE COULD SEE - [SDR CA160311004](https://openairdocs.org/sdr/CA160311004), Mar 9, 2016: WINDOW FRAME. CORRODED. (CAN) DURING AN AIRFRAME STRUCTURE INSPECTION REQUIRED, ST-UN-M002, 5-2, WHICH IS ON A 25000 TTAF INSPECTION CYCLE, THE BOTTOM OF THE LT OTBD WINDSHIELD POST WA - [SDR CA160127008](https://openairdocs.org/sdr/CA160127008), Jan 23, 2016: INDICATOR. SHORTED. (CAN) 5 MINUTES AFTER TAKEOFF, CREW NOTED BOTH AC BUSS LIGHTS ILLUMINATED AND SMOKE BEGAN TO COME FROM THE RT FUEL QUANTITY GAUGE. THE NR 1 AC BUSS CIRCUIT BREA - [SDR CA150910008](https://openairdocs.org/sdr/CA150910008), Sep 9, 2015: WINDSHIELD. CRACKED. (CAN) AT CRUISING ALTITUDE FL20 THE LT WINDSHIELD DEVELOPED SUDDEN SUBSTANTIAL CRACKING. PILOT SLOWED THE ACFT REDUCED PRESSURIZATION AND DESCENDED TO 10000 FT - [SDR CA150910007](https://openairdocs.org/sdr/CA150910007), Sep 7, 2015: WIRE. BROKEN. (CAN) ALL 3 GEAR LIGHTS FAILED TO ILLUMINATE ON GEAR DOWN SELECTION AND GEAR LIGHTS FAILED TO TEST WHEN TESTED IN FLIGHT. AFTER 2 GEAR CYCLES AND WHEN INDICATOR - [SDR CA150123003](https://openairdocs.org/sdr/CA150123003), Jan 23, 2015: EXHAUST DUCT. CRACKED. (CAN) WHILE PERFORMING NR 1 PHASE INSPECTION, FOUND NR 1 ENGINE AFT TURBINE EXHAUST HOUSING HAS A CRACK AT 1:00 POSITION ALONG SIDE A WELDED REPAIRED AREA. - [SDR CA141110012](https://openairdocs.org/sdr/CA141110012), Nov 7, 2014: BOLT. DAMAGED. (CAN) DURING ROUTINE MAINTENANCE A PORTION OF BOLT 6924B1 WAS FOUND IN THE COWLING MISSING ITS HEAD (9 O CLOCK POSITION BOLT). THIS BOLT IS ONE OF 3 THAT LOCATE - [SDR CA140904010](https://openairdocs.org/sdr/CA140904010), Sep 3, 2014: SCREW. DAMAGED. (CAN) FOLLOWING NORMAL TAKEOFF, ON CLIMBOUT PASSING 7500FT THE FLIGHT CREW EXPERIENCED AN OVERSPEED ON THE RT ENGINE, THE PROPELLER SPEED LEVER WAS PULLED BACK - [SDR CA140702011](https://openairdocs.org/sdr/CA140702011), Jun 3, 2014: FUEL CONTROL. MALFUNCTIONED. (CAN) ON THE FIRST OCCURRENCE, THE ACFT LANDED AND WHEN FULL REVERSE WAS SELECTED, THE ENGINE APPEARED TO LOSE POWER. THE STOP AND FEATHER WAS PULLED AND THE AC - [SDR CA140723002](https://openairdocs.org/sdr/CA140723002), May 20, 2014: SUN GEAR. DAMAGED. (CAN) UPON HAVING A CHIP LIGHT IN THE COCKPIT THERE WAS A OIL SAMPLE TAKEN THAT VERIFIED THERE WAS AN ISSUE WITH THE ENGINE. THE ENGINE WAS REMOVED AND FORWARDE - [SDR CA140303020](https://openairdocs.org/sdr/CA140303020), Mar 1, 2014: SWITCH. FAILED. (CAN) DURING PRE-FLIGHT CHECKS, THE PILOT CHECKED THE ANNUNCIATOR PANEL WITH THE PRESS TO TEST SWITCH AND SEVERAL LIGHTS DID NOT ILLUMINATE. MAINTENANCE WAS CAL - [SDR CA140212007](https://openairdocs.org/sdr/CA140212007), Feb 2, 2014: BOLT. FAILED. (CAN) AIRCRAFT EXPERIENCED AN ELEVATOR MALFUNCTION ON LANDING. IN THE FLARE THE CREW LOST ALL ABILITY TO MANEUVER THE ELEVATOR LEAVING THE CONTROL COLUMN WITH N - [SDR CA130925005](https://openairdocs.org/sdr/CA130925005), Sep 22, 2013: MASTER CYLINDER. LEAKING. (CAN) THE FLIGHT CREW NEEDED TO APPLY FULL RT RUDDER TO KEEP ACFT STRAIGHT DURING TAKE-OFF. THE TAKEOFF WAS REJECTED AND DURING TAXI A FIRE WAS OBSERVED AT THE - [SDR CA130621006](https://openairdocs.org/sdr/CA130621006), Jun 19, 2013: MIXING VALVE. FAILED. (CAN) ACFT EXPERIENCED A WING OVERHEAT LIGHT IN CRUISE. DURING THE INVESTIGATION INTO THE CAUSE OF THE OVERHEAT LIGHT INDICATION, MAINTENANCE DISCOVERED THE CON - [SDR KY7A20130304001](https://openairdocs.org/sdr/KY7A20130304001), Feb 27, 2013: FCU. INTERMITTENT. FLIGHT CREW REPORTED THAT AFTER DEPARTING, THEY EXPERIENCED A MOMNENTARY "SURGE" OF E1 TORQUE ON CLIMBOUT AT 12000 FT MSL, FOLLOWED BY STABILIZATION OF ENGINE O - [SDR CA120615004](https://openairdocs.org/sdr/CA120615004), Jun 15, 2012: TURBINE WHEEL. CRACKED. (CAN) THE ENGINE WAS REMOVED FROM THE ACFT FOR A SCHEDULED O/H. WHEN THE ENGINE WAS TORN DOWN FOR INSPECTION OF ALL COMPONENTS, THE NR1 T-WHEEL WAS SENT TO THE - [SDR 2012FA0000356](https://openairdocs.org/sdr/2012FA0000356), Jun 6, 2012: DOWNLOCK SWITCH. DEFECTIVE. ON LANDING THE PILOT NOTICE THE LT DOWNLOCK FAILED TO ILLUMINATE. A FLY BY WAS PERFORMED AND A NORMAL LANDING WAS PERFORMED WITH NO OTHER PROBLEMS. - [SDR CA120223004](https://openairdocs.org/sdr/CA120223004), Dec 30, 2011: ATTACH FITTING. CRACKED. (CAN) DURING A BLOCK INSPECTION IT WAS NOTICED VISUALY THAT THE FRONT SPAR REAR WING ATTACH FITTING WAS CRACKED. ONCE THE FITTING WAS REMOVED, ADDITIONAL DEFECT - [SDR CA111024009](https://openairdocs.org/sdr/CA111024009), Sep 24, 2011: SPUR GEAR. DAMAGED. (CAN) MX NOTIFIED OF A CHIP LIGHT ON THE ACFT AND WHEN THEY INSPECTED THE CHIP DETECTOR IT WAS NOTICED TO HAVE ALOT OF METAL ON THE DETECTOR. THE OIL FILTER WAS - [SDR CA110812004](https://openairdocs.org/sdr/CA110812004), Aug 2, 2011: ATTACH FITTING. CRACKED. DURING REMOVAL OF THE CRACKED AFT WING TO FUSELAGE ATTACH FITTING THE FORWARD HALF OF THE ASSY WAS DAMAGED. ON REMOVAL, IT WAS DISCOVERED THAT THE FITTING WAS C - [SDR CA110803028](https://openairdocs.org/sdr/CA110803028), Aug 1, 2011: FUEL CONTROL. LEAKING. MX WAS TROUBLESHOOTING A DEFECT RELATED TO POWER LEVER SPLIT IN CRUISE, THE MAX POWER ADJUSTMENT CAP WAS REMOVED FROM THE BACK OF THE FCU. THE BACK OF THE FUEL - [SDR CA110812003](https://openairdocs.org/sdr/CA110812003), Aug 1, 2011: ATTACH FITTING. CRACKED. DURING THE 6750 BLOCK INSP, A TECH THOUGHT THAT NOTICED A CRACK ON THE AFT WING TO FUSELAGE ATTACH FITTING. THE CRACK WAS CONFIRMED BY EDDY CURRENT PRIOR TO PAR - [SDR 2011FA0000779](https://openairdocs.org/sdr/2011FA0000779), Jun 26, 2011: FUEL. INADEQUATE. WHILE DEMONSTRATING EXTERNAL LOAD CAPABILITY DIRECTLY ABOVE A JUNGLE HELIPAD, THE ENGINE BEGAN TO LOOSE RPM AND THE ACFT LANDED BACK ON THE PAD. THE LANDING WAS - [SDR CA110404004](https://openairdocs.org/sdr/CA110404004), Apr 4, 2011: PINION GEAR. DAMAGED. (CAN) ENG TPE331-10UA-511G, SN P-54019 WAS IN THE TURBINE SHOP FOR ITS SCHEDULED OVERHAUL. WHEN THE INSPECTION WAS CARRIED OUT ON THE HIGH SPEED PINION IT WAS N - [SDR CA101028004](https://openairdocs.org/sdr/CA101028004), Oct 27, 2010: TRUSS. DAMAGED. (CAN) MAINTENANCE FOUND THAT THE ANTI-ICE VALVE HAD BEEN RUBBING UP AGAINST THE ENGINE TRUSS, CAUSING A SCREW ON THE ELECTROMAGNETIC RECEPTACLE ASSEMBLY TO COME - [SDR CA101007014](https://openairdocs.org/sdr/CA101007014), Oct 7, 2010: MOUNT. CRACKED. UPON ROUTINE SERVICING, MX FOUND LT LOWER ENGINE FRAME TO BE CRACKED THROUGH BOTH INBD AND OTBD, PART WAS REMOVED FOR REPAIR. ALMOST IDENTICAL TO INCIDENT ON SE - [SDR CA101012004](https://openairdocs.org/sdr/CA101012004), Oct 6, 2010: HOUSING. CRACKED. OUTPUT HSG CRACK LINE MX WAS DOING A ROUTINE INSP ON ENGINE, WHEN ONE OF THE MECHANICS NOTICED A CRACK ON THE SIDE OF THE ACCY DRIVE HSOUSING. THE TURBINE SHOP - [SDR CA101007013](https://openairdocs.org/sdr/CA101007013), Sep 30, 2010: FRAME. CRACKED. UPON ROUTINE ENG SERVICING, FOUND RT LOWER ENGINE FRAME ASSY TO BE CRACKED THROUGH MAIN BAR ON BOTH INBD AND OTBD. - [SDR CA100929007](https://openairdocs.org/sdr/CA100929007), Sep 16, 2010: WINDSHIELD. CRACKED. ON APPROACH, THE CREW NOTICED THE CAPTAINS HEATED WINDSHIELD HAD CRACKED. THE CREW RETURNED TO DEPARTURE. THE ACFT WAS FERRIED TO MAIN BASE AND THE WINDOW WAS R - [SDR DALA1022685507](https://openairdocs.org/sdr/DALA1022685507), Sep 12, 2010: WIRE. DAMAGED. DURING L CHECK, MX FOUND SEAT EMERGENCY LIGHTS AT ROWS 21-23ABC INOPERATIVE. MX REPAIRED WIRES BY SEATS 22C & 23C, AND REPLACED THE FUSE ON M11612 POWER SUPPLY. - [SDR CA101207005](https://openairdocs.org/sdr/CA101207005), May 5, 2010: WINDSHIELD. FAILED. (CAN) DURING DESCENT THROUGH 14000 ASL AIRCRAFT EXPERIENCED MOMENTARY MODERATE TURBULENCE FOLLOWED BY A DEEP `POP` SOUND, DRAWING ATTENTION TO THE RIGHT WINDSHI - [SDR CA100114006](https://openairdocs.org/sdr/CA100114006), Jan 12, 2010: WINDSHIELD. CRACKED. (CAN) WHILE IN CRUISE, RT WINDSHIELD CRACKED. CREW DIVERTED TO MAIN BASE. REPLACED WINDSHIELD. TOTAL TIME 944.3 HOURS, 2 YEARS IN SERVICE APPROX. NUMEROUS FAILU - [SDR CA091222007](https://openairdocs.org/sdr/CA091222007), Dec 11, 2009: WINDSHIELD. CRACKED. (CAN) APROX 60 NM NORTH WEST, IN CRUISE THE CREW HEARD A LOUD CRACKING NOISE AND NOTICED THE LT HEATED WINDSHIELD HAD SHATTERED. THE CREW IMMEDIATELY STARTED DE - [SDR CA091222006](https://openairdocs.org/sdr/CA091222006), Dec 10, 2009: WINDSHIELD. CRACKED. (CAN) ON DECENT FOR LANDING. THE CREW NOTICED THE CAPTAINS HEATED FRONT WINDSHIELD HAD A LARGE CRACK THAT SPIDERED DOWN THE WINDOW. - [SDR CA091210008](https://openairdocs.org/sdr/CA091210008), Dec 8, 2009: SWITCH. FAILED. (CAN) AFTER TAKE-OFF, GEAR WAS SELECTED UP AND 3 GREEN LIGHTS REMAINED, THERE WAS NO APPARENT MOVEMENT OF GEAR. GEAR WAS THEN CYCLED SEVERAL TIMES, AND LANDING - [SDR CA091202011](https://openairdocs.org/sdr/CA091202011), Dec 1, 2009: RELAY. MALFUNCTIONED. (CAN) CREW ARRIVED AFTER ONE HOUR FLIGHT REPORTING ABNORMAL LT GENERATOR VOLT METER INDICATION. THE GEN FAIL LIGHT FUNCTIONED NORMALLY WITH THE GENERATOR OFF OR - [SDR CA091125007](https://openairdocs.org/sdr/CA091125007), Nov 21, 2009: TRUNNION. CORRODED. (CAN) FOUND CORROSION PITTING IN TRUNNION BORES ON BOTH SIDES OF NLG TRUNNION, WHICH HOUSE THE DRAG BRACE PINS. PITTING IS 0.030 INCHES DEEP LONGITUDINALLY IN E - [SDR CA091209003](https://openairdocs.org/sdr/CA091209003), Nov 17, 2009: BEARING RACE. FAILED. (CAN) THE ACFT CAME IN FOR A CHIP LIGHT SNAG AND WHEN THE MX DEPARTMENT INSPECTED CHIP DETECTOR IT WAS NOTED TO HAVE QUITE A BIT OF METAL ON THE DETECTOR. ENG S - [SDR CA091118009](https://openairdocs.org/sdr/CA091118009), Nov 10, 2009: STOP. BROKEN. (CAN) ON APPROACH WHEN THE GEAR WAS SELECTED DOWN ONLY 2 MAINS WENT GREEN. CREW DIDN’T GET THE RED IN TRANSIT ON NOSE GEAR EITHER, THEY RECYCLED THE GEAR SEVERA - [SDR CA091113005](https://openairdocs.org/sdr/CA091113005), Nov 6, 2009: BEARING RACE. FAILED. (CAN) ACFT SUFFERED A RT GENERATOR FAILURE ON DECENT. THE GENERATOR FAIL LIGHT ILLUMINATED IN THE COCKPIT BUT NO ADVERSE RESULTS FROM THE FAILURE OCCURED. MX RE - [SDR CA091117006](https://openairdocs.org/sdr/CA091117006), Nov 5, 2009: LINE. CRACKED. (CAN) UPON SELECTING GEAR DOWN ON FINAL, ACFT EXPERIENCED 2 HYD WARNING LIGHTS, CREW DECLARED AN EMERGENCY. ON THE INITIAL GEAR EXTENSION THE ACFT INDICATED ALL - [SDR CA091015006](https://openairdocs.org/sdr/CA091015006), Oct 14, 2009: WINDSHIELD. CRACKED. (CAN) A LOUD THUD WAS HEARD AND THE CREW NOTICED THE COPILOTS WINDOW WAS SHATTERED. THEY DECENDED AND ASKED FOR PRIORITY HANDLING, BUT DID NOT DECLARE AN EMERGE - [SDR CA090925005](https://openairdocs.org/sdr/CA090925005), Sep 22, 2009: LINE. CHAFED. (CAN) ON APPROACH THE CREW HAD JUST SELECTED FULL FLAP ON THE FINAL LANDING CHECKS WHEN THEY NOTICED SMOKE IN THE COCKPIT. SINCE THEY WERE LESS THAN 3 MILE FINA - [SDR CA090917004](https://openairdocs.org/sdr/CA090917004), Sep 17, 2009: SHUTOFF VALVE. FAILED. (CAN) AFTER THE ENGINE WAS OVERHAULED AND WAS INSTALLED IN THE TEST CELL, WHEN TRYING TO DO A START, ENG WOULD NOT LIGHT OFF. IT WAS NOTED THAT THERE WAS NO FUE - [SDR CA090918004](https://openairdocs.org/sdr/CA090918004), Sep 15, 2009: HOSE. RUPTURED. (CAN) UPON CLIMBOUT THE AIRCRAFT HYDRAULIC WARNING LIGHTS ILLUMINATED AND HYDRAULIC PRESSURE WAS LOST. THE AIRCRAFT RETURNED TO THE AIRPORT AND PERFORMED A FLAP - [SDR CA090918011](https://openairdocs.org/sdr/CA090918011), Sep 13, 2009: SWITCH. FAILED. (CAN) UPON TAXI THE FLIGHT CREW NOTED THAT THE NOSE WHEEL STEERING WAS UNRESPONSIVE. THE TEST FUNCTION WORKED FINE. THE AIRCRAFT RETURNED TO THE GATE WHERE MAIN All 375: https://openairdocs.org/engine/garrett-tpe331-10ua/reports.md ## 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 SE01461NY](https://openairdocs.org/stc/SE01461NY): Propeller pitch control system modification. Hartzell HC-E4N-5D/D9690(B) propeller installed per STC SA01462NY. Not approved on serial numbers TC-398 through TC-418. Hartzell Propeller Inc - [STC SE00691CH](https://openairdocs.org/stc/SE00691CH): Modification of a turboprop engine to a turboshaft configuration by incorporation of AlliedSignal (Garrett) TSE331-3U turboshaft gearbox components and other associated changes. National Flight Services, 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.