# Lycoming T5313B - Type: Engine model (FAA registry) - Registry code: 41613 - Manufacturer (registry): LYCOMING - Model: T5313B - Engine type: Turbo-shaft - Power: 1,400 hp - Data sheet: [TCDS E17EA](https://openairdocs.org/tcds/E17EA) (OpenAirDocs) - Holder: Ozark Aeroworks LLC - Installed in: 8 registered aircraft - Page: https://openairdocs.org/engine/lycoming-t5313b 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 2022-10-02](https://openairdocs.org/ad/2022-10-02): Engine Controls · Honeywell International T53-L-703, T53-L-13B S/SB, T53-L-13B S/SA and 14 more. Effective Jun 28, 2022 - [AD 2009-15-13](https://openairdocs.org/ad/2009-15-13): Combustion chamber housings (CCHs) · Honeywell International T5313B, T5317A, T5317A-1 and 2 more. Effective Aug 25, 2009 - [AD 2006-11-16](https://openairdocs.org/ad/2006-11-16): Fuel control regulator assemblies · Honeywell International T53-L-703, T53-L-13B/D, T53-L-13B and 8 more. Effective Jul 5, 2006 - [AD 2006-01-05](https://openairdocs.org/ad/2006-01-05): Turboshaft engine · Honeywell International T53-L-703, T53-L-13B/D, T53-L-13B S/SB and 12 more. Effective Feb 16, 2006 - [AD 2002-15-04](https://openairdocs.org/ad/2002-15-04): Compressor impellers · Honeywell International T53-L-703, T53-L-13B/D, T53-L-13B and 4 more. Effective Sep 10, 2002 - [AD 2002-09-09](https://openairdocs.org/ad/2002-09-09): Centrifugal Compressor Impeller · Honeywell International T53-L-703, T53-L-13B/D, T53-L-13B and 10 more. Effective Jun 13, 2002 - [AD 97-21-07 R1](https://openairdocs.org/ad/97-21-07-R1): Accessory Drive Carrier Assembly · Honeywell International T53-L-703, T5313B, T5317A and 1 more. Effective Jul 6, 1998 - [AD 97-07-05](https://openairdocs.org/ad/97-07-05): Accessory Drive Assembly · Honeywell International T53-L-703, T5311A, T5311B and 4 more. Effective Jun 24, 1997 - [AD 96-17-01](https://openairdocs.org/ad/96-17-01): Suspect second stage power turbine disks · Honeywell International T5313B. Effective Sep 9, 1996 - [AD 95-10-04](https://openairdocs.org/ad/95-10-04): Centrifugal Compressor Impeller · Honeywell International T5313B, T5317A, T5317A-1 and 1 more. Effective May 25, 1995 - [AD 77-17-08](https://openairdocs.org/ad/77-17-08): Fuel Regulator P1 Multiplier Lever · Honeywell International T53-L-703, T5307A, T5309A and 7 more. Effective Mar 30, 1978 - [AD 75-22-02](https://openairdocs.org/ad/75-22-02): Secondary Failure N2 Accessory Drive Shaft · Honeywell International T5307A, T5309A, T5309B and 6 more. Effective Oct 29, 1975 - [AD 75-12-12](https://openairdocs.org/ad/75-12-12): Second Stage Gas Producer Cylinder Retaining Bolt · Honeywell International T5313A and T5313B. Effective Jun 18, 1975 - [AD 75-01-05](https://openairdocs.org/ad/75-01-05): Compressor Impeller Assembly Vane · Honeywell International T5313B. Effective Jan 17, 1975 - [AD 71-08-06](https://openairdocs.org/ad/71-08-06): Overspeed Pickup Housing Assembly · Honeywell International T5313A and T5313B. Effective Apr 16, 1971 Historical (superseded or no longer in force): - [AD 2002-03-01](https://openairdocs.org/ad/2002-03-01) (historical): Reduction Gearbox Assembly · Honeywell International T5311A, T5311B, T5313B and 2 more. Effective Mar 21, 2002 - [AD 87-12-05](https://openairdocs.org/ad/87-12-05) (historical): Gas Producer Turbine and Power Turbine Disks · Honeywell International T5313B. Effective Jul 20, 1987 ## Registered aircraft (8) - [N16315](https://openairdocs.org/aircraft/N16315): [Army Aviation Heritage Foundation And Flg Museum](https://openairdocs.org/faa-owner/ARMY%20AVIATION%20HERITAGE%20FOUNDATION%20AND%20FLG%20MUSEUM), [Hampton, GA](https://openairdocs.org/faa-place/GA/Hampton), built 1971, S/N 70-16315 - [N204UH](https://openairdocs.org/aircraft/N204UH): [R&R Conner Aviation LLC](https://openairdocs.org/faa-owner/R%26R%20CONNER%20AVIATION%20LLC), [Conner, MT](https://openairdocs.org/faa-place/MT/Conner), built 1962, S/N 62-2034 - [N30111](https://openairdocs.org/aircraft/N30111): [Sky Walker Aviation LLC](https://openairdocs.org/faa-owner/SKY%20WALKER%20AVIATION%20LLC), [Indianapolis, IN](https://openairdocs.org/faa-place/IN/Indianapolis), built 1968, S/N 68-16563 - [N353RC](https://openairdocs.org/aircraft/N353RC): [N353rc LLC](https://openairdocs.org/faa-owner/N353RC%20LLC), [Chelan, WA](https://openairdocs.org/faa-place/WA/Chelan), S/N 6600782 - [N6261C](https://openairdocs.org/aircraft/N6261C): [Vi1 LLC](https://openairdocs.org/faa-owner/VI1%20LLC), [Brewster, WA](https://openairdocs.org/faa-place/WA/Brewster), built 1968, S/N 68-15521 - [N839PF](https://openairdocs.org/aircraft/N839PF): [Rice Aircraft Services Inc](https://openairdocs.org/faa-owner/RICE%20AIRCRAFT%20SERVICES%20INC), [Olivehurst, CA](https://openairdocs.org/faa-place/CA/Olivehurst), built 1970, S/N 8232 - [N849DB](https://openairdocs.org/aircraft/N849DB): [D & B Aviation Brokerage Services LLC](https://openairdocs.org/faa-owner/D%20%26%20B%20AVIATION%20BROKERAGE%20SERVICES%20LLC), [Wilmington, DE](https://openairdocs.org/faa-place/DE/Wilmington), built 1970, S/N 8494 - [N850M](https://openairdocs.org/aircraft/N850M): [Jones Aviation](https://openairdocs.org/faa-owner/JONES%20AVIATION), [Biggs, CA](https://openairdocs.org/faa-place/CA/Biggs), built 1966, S/N 66-16875 ## NTSB investigations (4) 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 ERA25LA380](https://openairdocs.org/ntsb/ERA25LA380), Feb 26, 2025: Bell Helicopter UH-1D (N849DB), DeLand, FL, substantial damage. Probable cause: The pilot’s loss of helicopter control during landing approach in strong wind conditions, which resulted in tail rotor contact with the ground during landing. - [NTSB WPR13FA411](https://openairdocs.org/ntsb/WPR13FA411), Sep 16, 2013: Bell UH 1B (N204UH), Detroit, OR, substantial damage, 1 fatal. Probable cause: The fatigue failure of the upper two tailboom attachment points, which resulted in the tailboom separating from the fuselage during logging operations. Contributing to the accident was poor… - [NTSB ANC84LA089](https://openairdocs.org/ntsb/ANC84LA089), Jun 12, 1984: Bell 205A-1 (N58116), Talkeetna, AK, substantial damage - [NTSB ANC76AA132](https://openairdocs.org/ntsb/ANC76AA132), Sep 13, 1976: Bell 205A-1 (N58116), Drift River, AK, substantial damage ## FAA accident and incident reports (6) 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 20250818015689I](https://openairdocs.org/incident/20250818015689I), Aug 18, 2025: Bell Helicopter Corp UH-1D (N849DB), Deland, FL, Substantial damage. On 08/18/2025, the airman listed was operating a helicopter ([privacy data omitted]) at Deland municipal airport (ded). The pilot mismanaged the collective… - [Accident 20250216018269A](https://openairdocs.org/incident/20250216018269A), Feb 16, 2025: Bell Helicopter Corp UH-1D (N849DB), Deland, FL, Minor damage. On 02/16/2025 a UH-1D struck it's tail and tail rotor during a repositioning flight at Deland municipal airport (ded). The FAA was notified of the accident via… - [Accident 20130916018889A](https://openairdocs.org/incident/20130916018889A), Sep 16, 2013: Bell UH-1B (N204UH), Detroit, OR, Destroyed, 1 fatal. After releasing an external load of logs in a 200 foot hover, the entire tail boom separated from the fuselage of N204UH. The helicopter immediately crashed… - [Incident 20060314005899I](https://openairdocs.org/incident/20060314005899I), Mar 14, 2006: Bell UH1H (N850M), St. James City, FL, Minor damage. (-23) Flight departed buckingham field at approximately 0900 hours. First flight of day to build time and practice landings on helipads. Flying pilot landed in… - [Accident 19840612024259A](https://openairdocs.org/incident/19840612024259A), Jun 12, 1984: Bell 205A1 (N58116), Talkeetna, AK, Substantial damage. Helicopter experienced intensive vibration. Autorotation was accomplished. 32 inches of rotor blade skin missing. - [Accident 19760913034699A](https://openairdocs.org/incident/19760913034699A), Sep 13, 1976: Bell 205A1 (N58116), Drift River, AK, Substantial damage. Plt rprtd wind gusting 15K.wind estimated 50-60K aftr accident. ## Service difficulty reports (147, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR CA130528009](https://openairdocs.org/sdr/CA130528009), May 27, 2013: TUBE. CRACKED. (CAN) CRACKED TUBE UNDERNEATH FITTING SLEEVE, TUBE POPPED OUT OF FITTING AND BLEW OUT MOST OF FLUID. - [SDR CA130212025](https://openairdocs.org/sdr/CA130212025), Feb 12, 2013: FUEL CELL. LEAKING. (CAN) FUEL CELL FOUND WEEPING FROM MULTIPLE LOCATIONS IN THE MIDDLE OF THE SIDES. ACFT FUEL RT FUEL CELL HAD A SLOW LEAK SO THE CELL WAS REMOVED AND INSPECTED. - [SDR CA130212027](https://openairdocs.org/sdr/CA130212027), Aug 14, 2012: GASKET. BLOWN. (CAN) WHILE IN CRUISE FLIGHT THE PILOT GOT AN INDICATION OF NO TRANSMISSION OIL PRESSURE ON THE WARNING LIGHT AND PRESSURE GAUGE. HE PROCEEDED TO LAND. WHEN HE - [SDR CA080811004](https://openairdocs.org/sdr/CA080811004), Aug 8, 2008: TUNING UNIT. CRACKED. (CAN) TUBE ASSY WAS REPLACED EARLIER IN APRIL 2008 DURING WINTER MAINT. SINCE SINGLE HYDR SYS PARTS ARE HARD TO FIND ITEMS, SERVICEABLE PART WAS INSTALLED WITH - [SDR CA080718001](https://openairdocs.org/sdr/CA080718001), Jul 13, 2008: BEARING. DAMAGED. (CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPS, UPON DESCENT WITH AN EXTERNAL LOAD, THE MASTER CAUTION WARNING INDICATION ILLUMINATED. THE PIC CHECKED THE CAUT - [SDR CA080722001](https://openairdocs.org/sdr/CA080722001), Jul 13, 2008: BEARING. DAMAGED. (CAN) UPON DESCENT WITH AN EXTERNAL LOAD, MASTER CAUTION WARNING INDICATION ILLUMINATED. THE PIC CHECKED THE CAUTION PANEL TO FIND A TRANSMISSION OIL PRESSURE C - [SDR CA080702005](https://openairdocs.org/sdr/CA080702005), Jun 26, 2008: TURBINE. DAMAGED. (CAN) PILOT CONDUCTED TAKE-OFF SCHEDULED TO CONDUCT LONGLINE OPERATIONS. APPROX 2 MINS AFTER TAKE-OFF THE PILOT HEARD A LOUD BANG FOLLOWED BY TORQUE YAWING. THE - [SDR CA080606002](https://openairdocs.org/sdr/CA080606002), Jun 3, 2008: BLADE. CRACKED. (CAN) PILOT REPORTED PEDAL VIBRATIONS THROUGHOUT THE DAYS FLYING. AD-2008-10-03 CLEAN AND INSPECT T/R BLADES WAS SCHEDULED FOR THE 25 HRS AME INSP PORTION OF TH - [SDR CA080409005](https://openairdocs.org/sdr/CA080409005), Apr 9, 2008: CIRCUIT BREAKER. INOPERATIVE. (CAN) WHILE DOING A PREFLIGHT CHECK DURING FLIGHT TRAINING IT WAS NOTED THAT THE LT BOOST PUMP CIRCUIT BREAKER WAS NOT ABLE TO BE CYCLED. THE CIRCUIT BREAKER WA - [SDR CA071203006](https://openairdocs.org/sdr/CA071203006), Dec 3, 2007: MOUNT. CRACKED. (CAN) LT ENGINE TRIPOD AFT TUBING MOUNT FOUND CRACKED DURING 100 HRS INSPECTION JUST BELOW ENGINE MOUNTING PLATE AFT TUBE JUNCTION. NOTE: THIS MOUNT WAS MODIFIE - [SDR CA070828004](https://openairdocs.org/sdr/CA070828004), Aug 21, 2007: BEARING. WORN. (CAN) PILOT WAS FLYING HELICOPTER AND FELT TWO SLIGHT YAWS TO THE RT APPROXIMATELY 30 TO 40 SECONDS APART. AT FIRST THE PILOT SUSPECTED IT MIGHT HAVE BEEN A GUS - [SDR CA070727003](https://openairdocs.org/sdr/CA070727003), Jul 25, 2007: O-RING. FAILED. (CAN) LOST OF HYDRAULIC IN FLIGHT, EMERGENCY LANDING, FAULT FOUND IN THE ACCUMULATOR, O-RING P/N MS28775-212 REPLACED A/C GROUND RUN AND LEAK CHECK COMPLETED AN - [SDR CA080204006](https://openairdocs.org/sdr/CA080204006), Jun 14, 2007: WIRE. SHORTED. (CAN) PILOT REPORTED SPARKS AND A SMALL AMOUNT OF SMOKE FROM THE OVERHEAD CONSOL. UPON INVESTIGATION IT WAS FOUND THAT THE LT OVERHEAD CONSOL PANEL HAD CHAFED T - [SDR CA070506001](https://openairdocs.org/sdr/CA070506001), Apr 23, 2007: NUT. DAMAGED. (CAN) ON APRIL 23, 2007 DURING A TEST FLIGHT FOR MAINTENANCE THAT WAS PERFORMED, THE PILOT EXPERIENCED AN UNCONTROLLED YAW TO THE RIGHT WHILE IN A 4 FOOT HOVER. - [SDR CA070321008](https://openairdocs.org/sdr/CA070321008), Mar 21, 2007: BEAM. CRACKED. (CAN) WEB P/N 205-030-163-395 FOUND CRACKED AT INDUCTION BAFFLE SUPPORT WL 80.13. THE CRACK WAS APPROX 1 INCH IN LENGTH AND .5 INCH DOWN . REPAIR SCHEME IN PROG - [SDR 2006FA0001088](https://openairdocs.org/sdr/2006FA0001088), Nov 19, 2006: ADAPTER. DAMAGED. DURING INSPECTION AND REGREASE OF THE M/R TRANS DRIVE SHAFT, A CHECK OF THE TORQUE OF THE DRIVE SHAFT ADAPTOR BOLT WAS ACCOMPLISHED AND IT WAS DISCOVERED THAT T - [SDR CA070228005](https://openairdocs.org/sdr/CA070228005), Sep 25, 2006: BLADE. MISSING. (CAN) VIBRATION ON OIL COOLER BLOWER, FURTHER INVESTIGATION REVEALED ONE BLADE MISSING. SERVICEABLE OIL COOLER BLOWER INSTALLED, A/C RETURNED TO SERVICE. (TC NR - [SDR CA060728003](https://openairdocs.org/sdr/CA060728003), Jul 14, 2006: BEARING. FAILED. (CAN) THE TAIL ROTOR DRIVESHAFT HANGER HAD BEEN INSTALLED THE NIGHT BEFORE THE FAILURE. WE SUSPECT AN INNER COUPLING FAILURE. THE SUSPECT COUPLING HAD BEEN RECO - [SDR CA060706002](https://openairdocs.org/sdr/CA060706002), Jul 4, 2006: BLADE. CRACKED. (CAN) CRACK ON BOTH SIDES OF BLADE BOLT BORE. TRAVELLING IN CHORDWISE DIRECTION. THE LEADING EDGE CRACK TRAVELS RIGHT TO THE LEADING EDGE AND THE TRAILING EDGE - [SDR CA060622005](https://openairdocs.org/sdr/CA060622005), Jun 21, 2006: CABLE. MELTED. (CAN) DURING TURN AROUND CHECK BY THE AME, THE WIRES TO THE STARTER GENERATOR WERE FOUND TO BE SUBJECTED TO HEAT DAMAGE. THERE WAS NO INDICATION TO THE PILOT OF - [SDR CA060605010](https://openairdocs.org/sdr/CA060605010), May 13, 2006: TRANSMISSION. MAKING METAL. (CAN) METAL PARTICLES FOUND IN TRANSMISSION INTERNAL FILTER AFTER ROUTINE INSPECTION. NO CHIP LIGHT INDICATION. OIL DRAINED WITH NEW FILTER INSTALLED, AIRCRAFT - [SDR CA060315007](https://openairdocs.org/sdr/CA060315007), Mar 2, 2006: YOKE. CRACKED. CRACKS ORIGINATING IN ATTACHMENT BOLT HOLES. - [SDR CA051001001](https://openairdocs.org/sdr/CA051001001), Sep 30, 2005: CROSSTUBE. CRACKED. (CAN) HIGH SKID GEAR. UPON LANDING THE FRONT CROSS TUBE CRACKED IN THE MIDDLE OF THE TUBE, BETWEEN THE MOUNTING SADDLES. FROM THE INFORMATION WE HAVE AT THIS TI - [SDR CA050924001](https://openairdocs.org/sdr/CA050924001), Sep 21, 2005: BLADE. FAILED. (CAN) AS THE A/C WAS APPROACHING STAGING WITH A SLING LOAD, THE PILOT HEARD A LOUD BANG FOLLOWED BY A LOUD SCREECHING NOISE FROM THE ENGINE. THE A/C LANDED IMME - [SDR CA040821001](https://openairdocs.org/sdr/CA040821001), Aug 20, 2004: SPHERICAL BEARIN. FAILED. (CAN) A/C WAS CLIMBING AFTER FILLING THE WATER BUCKET WHEN HE LOST COMPLETE TAIL ROTORAUTHORITY.THE A/C MADE SEVERAL 360 DEGREE TURNS AFTER COMING TO REST IN A - [SDR CA040901005](https://openairdocs.org/sdr/CA040901005), Jul 18, 2004: VOLT REGULATOR. FAILED. (CAN) VOLTAGE REGULATOR DELIVERING OVER 30 VOLTS. THE AIRCRAFT WAS READY TO TAKE OFF WHEN THE PILOT SMELLED A STRONG ODOR IN THE COCKPIT. ASSUMING IT WAS THE BA - [SDR CA040901003](https://openairdocs.org/sdr/CA040901003), Jul 4, 2004: BLADE. CRACKED. (CAN) MAIN ROTOR BLADE FOUND CRACKED ON THE TOP SURFACE 90 INCHES FROM THE TIP. ABOUT 70 HOURS BEFORE, A CRACK ON THE BLADE PAINT WAS FOUND, AT THAT TIME NO CRA - [SDR CA040203011](https://openairdocs.org/sdr/CA040203011), Jan 27, 2004: SHAFT. WORN. (CAN) UPON SUSPECTING A PROBLEM WITH FUEL CONTROL UNIT. REMOVED FCU FROM THE ENGINE TO INSPECT THE SPLINES IAW MFG SBT5313-107. FOUND THE INTERNAL SPLINES KNIFE - [SDR CA040209012](https://openairdocs.org/sdr/CA040209012), Jan 27, 2004: SHAFT. WORN. (CAN) FUEL CONTROL RECEIVED FROM CUSTOMER FOR INSPECTION FOLLOWING PREVIOUS RECORDS ABOUT PUMP FAILURE (WSDR 20040128006). FUEL CONTROL HAS TSO- 3195.3 AND WAS - [SDR 2004FA0000148](https://openairdocs.org/sdr/2004FA0000148), Jan 9, 2004: FITTING. DAMAGED. UPON OPENING PACKED FOR FITTING ASSEMBLY FOUND THREADS ON LONG SIDE OF FITTING PULLED LOOSE. PART REJECTED BEFORE INSTALLATION. - [SDR CA030915008](https://openairdocs.org/sdr/CA030915008), Sep 7, 2003: BOOT. TORN. (CAN) DURING THE INSPECTION AFTER THE LAST FLIGHT OF THE DAY, THE ENGINEER INSPECTED THE MAIN DRIVESHAFT BOOTS FOR LEAKAGE. THERE WAS NO VISUAL SIGN OF A GREASE - [SDR CA031001006](https://openairdocs.org/sdr/CA031001006), Aug 25, 2003: FITTING. CRACKED. (CAN) PART REMOVED FROM SERVICE.NEW PART INSTALLED. - [SDR CA030912003](https://openairdocs.org/sdr/CA030912003), Jul 28, 2003: GEAR. FAILED. (CAN) A/C PERFORMING NORMAL APPROACH. DURING FINAL, A LIGHT WHINING SOUND HEARD AS POWER APPLIED. AS POWER INCREASED, SOUND INCREASED. AT APPROX 8 FT FROM TOUCH - [SDR AUS20030596](https://openairdocs.org/sdr/AUS20030596), Apr 3, 2003: COMPRESSOR. FOD. (AUS) ENGINE VARIABLE INLET GUIDE VANES (VIGV) AND COMPRESSOR BLADES DAMAGED BY FOD. INVESTIGATION FOUND THAT DAMAGE HAD BEEN CAUSED BY AN OBJECT WITH A DIAMETE - [SDR CA021113003](https://openairdocs.org/sdr/CA021113003), Oct 31, 2002: NOZZLE. UNAPPROVED PART. (CAN) MILITARY PARTS FOUND INSTALLED ON ENGINE S/N LE-07616. INSTALLED PART MANUFACTURER CODE NUMBER IS 81996 (US MILITARY). IT SHOULD BE 91547. (HONEYWELL OEM) - [SDR AUS20021231](https://openairdocs.org/sdr/AUS20021231), Oct 15, 2002: FITTING. FAULTY. (AUS) TAILBOOM LH LOWER ATTACHMENT FITTING ON FUSELAGE HAD OVERSIZE HOLES ALLOWING THE HILOK' PINS TO LOOSEN. SUSPECT CAUSED BY POOR REPAIR WORK. - [SDR CA021001010](https://openairdocs.org/sdr/CA021001010), Sep 20, 2002: DRIVE SHAFT. CHAFED. (CAN) AT TIME OF RE-GREASING THE T/R DRIVESHAFT COUPLINGS. T/R DRIVESHAFT WAS REMOVED FROM TUNNEL UNDER ENGINE. FOUND CONTACT WAS MADE WITH TUNNEL AT ENTRANCE D - [SDR CA021007007](https://openairdocs.org/sdr/CA021007007), Sep 18, 2002: HANGER ASSY. CRACKED. (CAN) HANGER CRACKED AT BOTH ATTACH POINTS FOR THE FLEX COUPLING ATTACH. - [SDR CA021003007](https://openairdocs.org/sdr/CA021003007), Sep 13, 2002: HOSE. LEAKING. (CAN) HOSE ASSEMBLY FAILED RESULTING IN LOSS OF HYDRAULIC FLUID. THE LOSS OF FLUID RESULTED IN LOSS OF HYDRAULIC BOOST TO FLIGHT CONTROLS. AIRCRAFT WAS LANDED U - [SDR CA020918006](https://openairdocs.org/sdr/CA020918006), Sep 6, 2002: BULKHEAD. CRACKED. (CAN) THE ROTOR CONTROL BELLCRANK BULKEAD CRACKED IN MULTIPLE PLACES. - [SDR CA020918010](https://openairdocs.org/sdr/CA020918010), Sep 2, 2002: BULKHEAD. CRACKED. (CAN) T/R FLIGHT CONTROL BELLCRANK SUPPORT ATTACHES TO BULKHEAD. THE BULKHEAD IS REINFORCED BY LOWER ANGLE AND UPPER ANGLE, SUSPECT THAT THE LOWER ANGLE CRACKED - [SDR CA020729002](https://openairdocs.org/sdr/CA020729002), Jul 11, 2002: INDICATOR. FAILED. (CAN) FROM REPORTS: THE AIRCRAFT WAS HOVERING WITH A WATER BUCKET OVER A FIRE. ROTOR SPEED DECAYED AND PILOT MADE A FORCED LANDING IN A CLEARING. THE AIRCRAFT L - [SDR CA020918008](https://openairdocs.org/sdr/CA020918008), Jul 10, 2002: ENGINE. FLAMED OUT. (CAN) DURING ROUTINE FLIGHT AFTER FUELING FROM A SUPPLIED SEALED DRUM OF PRE-MIXED JET FUEL (FSII) ADDED. THE ENGINE FLAMED OUT AND A FORCED LANDING RESULTING I - [SDR CA020726017](https://openairdocs.org/sdr/CA020726017), Jul 1, 2002: BLADE. BENT. (CAN) THE LT WING TIP OF A CL-415 WATER BOMBER CONTACTED THE FORWARD ROTOR BLADE OF THE 205. THE 205 WAS PARKED AND TIED DOWN. THE CL-415 WAS DESCRIBED AS TRAVE - [SDR CA020627007](https://openairdocs.org/sdr/CA020627007), Jun 20, 2002: FUEL CELL. CONTAMINATED. (CAN) CRYSTALS WERE FOUND IN THE FUEL CELL WHILE IT WAS FIRE-FIGHTING HOUSE LAKE FIRE. THE CRYSTALS WERE FOUND DUE TO A BLOCKED EJECTOR PUMP. SOURCE OF THE CRYS - [SDR CA020607007](https://openairdocs.org/sdr/CA020607007), Jun 2, 2002: ENGINE. FAILED. (CAN) A/C WAS IN PROGRESS OF FIREFIGHTING WHEN ENGINE 'FIRE WARNING' ILLUMINATED. AFTER VERIFYING FIRE VIBRATION, PILOT DECIDED TO CARRY OUT AN EMERG LDG. ON DE - [SDR CA020611003](https://openairdocs.org/sdr/CA020611003), May 30, 2002: VALVE SEAT. FAILED. (CAN) DURING THE SCHEDULED 25 HOUR INSPECTION THE AME NOTED THAT THE VALVE SEAT HAD UNSCREWED ITSELF FROM THE FILTER BODY AND DAMAGED THE FILTER, WAFER. THE VAL - [SDR CA020507009](https://openairdocs.org/sdr/CA020507009), Apr 30, 2002: MOUNT. CRACKED. (CAN) DURING MAIN ROTOR TRANSMISSION REMOVAL FOUND CRACK EXTENDING FROM LOWER MOST BOLT HOLE OF 5TH MOUNT ATTACHMENT ANGLE, RT SIDE OF TRANSMISSION PYLON AREA.C - [SDR CA020507010](https://openairdocs.org/sdr/CA020507010), Apr 17, 2002: BEAM. CRACKED. (CAN) SMALL CRACK FOUND ON TOP "T" CAP OF LT VERTICAL MAIN BEAM ASSEMBLY. CRACK WAS OBSERVED WERE "T" CAP TRANSITIONS FROM UNDER THE ENGINE DECK GOING FORWARD T - [SDR CA020501002](https://openairdocs.org/sdr/CA020501002), Apr 11, 2002: FITTING. CRACKED. (CAN) CRACK FOUND AT BOTTOM OF BEAM (FITTING HOUSING) WHERE 5TH MOUNT IS HOUSED, 3/4 INCH LONG. BELL MAINTENANCE MANUAL SPECIFIES NO CRACKS IN THIS AREA. All 147: https://openairdocs.org/engine/lycoming-t5313b/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 SE00585AT](https://openairdocs.org/stc/SE00585AT): Installation of Aeronautical Accessories, Inc. PC Safety Valve Kit. Bell Helicopter Textron Inc - [STC SE00029EN](https://openairdocs.org/stc/SE00029EN): Installation of Pratt & Whitney Engine Services Inc. SmartCycle Plus Engine Monitoring System, P/N EMU-K-010-1 on specific T53 engine models. Pratt & Whitney Engine Services Inc - [STC SE01440NY](https://openairdocs.org/stc/SE01440NY): Conversion of Honeywell engine model T5313B to Honeywell engine model T5317A utilizing Aero Design, Ltd. conversion instructions C1437.02 dtd 4/30/01. Dart Aerospace Limited --- 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.