# Lycoming T5317A - Type: Engine model (FAA registry) - Registry code: 41614 - Manufacturer (registry): LYCOMING - Model: T5317A - Engine type: Turbo-shaft - Power: 1,500 hp - Data sheet: [TCDS E17EA](https://openairdocs.org/tcds/E17EA) (OpenAirDocs) - Holder: Ozark Aeroworks LLC - Installed in: 2 registered aircraft - Page: https://openairdocs.org/engine/lycoming-t5317a 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 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 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 ## Registered aircraft (2) - [N205RH](https://openairdocs.org/aircraft/N205RH): [Sacramento Executive Helicopters Inc](https://openairdocs.org/faa-owner/SACRAMENTO%20EXECUTIVE%20HELICOPTERS%20INC), [Rancho Cordova, CA](https://openairdocs.org/faa-place/CA/Rancho%20Cordova), built 1973, S/N 30127 - [N68EC](https://openairdocs.org/aircraft/N68EC): [Copter Lease LLC Trustee](https://openairdocs.org/faa-owner/COPTER%20LEASE%20LLC%20TRUSTEE), [Albuquerque, NM](https://openairdocs.org/faa-place/NM/Albuquerque), built 1968, S/N 30008 ## 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 (91, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR CA150818010](https://openairdocs.org/sdr/CA150818010), Aug 14, 2015: SHAFT. SHEARED. (CAN) SHAFT SHEARED DURING FLIGHT. MOTOR ASSEMBLY REPLACED. - [SDR CA150713024](https://openairdocs.org/sdr/CA150713024), Jul 11, 2015: HYDRAULIC LINE. RUPTURED. (CAN) DURING FLIGHT THE PILOT EXPERIENCED A LOSS OF NR 2 HYD PRESS. PILOT RETURN TO THE BASE AFTER ISOLATING THE SYS. ONCE THE ACFT LANDED SAFELY, THE INVESTIGA - [SDR CA150316004](https://openairdocs.org/sdr/CA150316004), Mar 15, 2015: BLADE. CRACKED. (CAN) DURING INSPECTION OF ACFT BLOWER FAN, IT WAS NOTED THAT 4 OF THE FAN BLADES WERE CRACKED AT THE BASE. - [SDR CA150225006](https://openairdocs.org/sdr/CA150225006), Feb 23, 2015: SHIELD. LEAKING. (CAN) DURING DAILY INSPECTION, NOTICED THAT THE HANGER BEARING ASSEMBLY GREASE SHIELD WAS LEAKING. UNIT WAS REPLACED WITH SERVICEABLE, GND RUN CARRIED OUT & NO - [SDR CA131009002](https://openairdocs.org/sdr/CA131009002), Aug 24, 2013: BLADE. SEPARATED. (CAN) A SUDDEN MEDIUM FREQUENCY VIBRATION WAS FELT IN FLIGHT. A PRECAUTIONARY LANDING WAS CARRIED OUT. AFTER VISUAL INSPECTION, IT WAS DISCOVERED THAT THE TIP C - [SDR CA130705006](https://openairdocs.org/sdr/CA130705006), Jul 3, 2013: FITTING. CRACKED. (CAN) AME WAS PERFORMING POST FLIGHT/DAILY INSPECTION FOLLOWING LAST FLIGHT OF DAY. DURING INSPECTION, A SMALL VERTICAL LINE WAS NOTED ON THE LT LUG OF THE FITT - [SDR CA130116020](https://openairdocs.org/sdr/CA130116020), Jan 16, 2013: PANEL. INOPERATIVE. (CAN) DURING TROUBLESHOOTING OF THE FUEL QTY INDICATING SYS FOR A CALIBRATION DEFECT. THE ACFT WAS SUBSEQUENTLY DEFUELED AND THE AME NOTICED THAT THERE WAS NO L - [SDR CA121206010](https://openairdocs.org/sdr/CA121206010), Dec 3, 2012: MOUNT. LOOSE. (CAN) FOUND DURING INSPECTION, THAT ATTACHMENT BOLTS, HAD COME LOOSE. THE INSPECTION WAS CARRIED OUT IAW INSTRUCTIONS FOR AIRWORTHINESS STC SH08-8. ALSO, THE HO - [SDR CA120817001](https://openairdocs.org/sdr/CA120817001), Aug 7, 2012: LONGERON. CRACKED. (CAN) TOP LT LONGERON ON ACFT LOCATED IN AFT COMPARTMENT WAS CRACKED BEHIND DOUBLER ON TOP LT TAILBOOM ATTACHMENT. CRACK WAS FOUND DURING DAILY INSPECTION, MACH - [SDR CA120817004](https://openairdocs.org/sdr/CA120817004), Jun 6, 2012: TACHOMETER. FAILED. (CAN) CO-PILOT DUAL TACH N2 ENGINE RPM NEEDLE, FLUCUATES FROM 0 TO 50 PERCENT THEN STICKS. - [SDR CA120223006](https://openairdocs.org/sdr/CA120223006), Jan 28, 2012: CAP. FRACTURED. (CAN) FAILURE OF CAP, IN ORDER TO EXAMINE THE FRACTURE SURFACE OF A STRUCTURAL LONGERON, HERE-IN REFERRED TO AS A CAP. THE CAP, PN 205-030-207-005 AND THE ASSOC - [SDR CA120116003](https://openairdocs.org/sdr/CA120116003), Jan 16, 2012: GIMBAL RING. DAMAGED. (CAN) DURING 100 HRS INSPECTION, 2 SMALL DAMAGED SCREWS WHERE FOUND IN THE BOTTOM OF THE MAIN TRANSMISSION BAY STILL ATTACHED WITH LOCKING WIRE. FURTHER INSPECT - [SDR CA111220005](https://openairdocs.org/sdr/CA111220005), Dec 20, 2011: BLADE. CRACKED. (CAN) 3 CRACKS DEVELOPED ON BOTTOM SIDE OF BLADE SKIN, PN 212-015-501-115, SN A6009 (TSN) 3521.9, 1 CRACK 5.5", THE OTHER 2 CRACKS ARE 2.5" - 3.5" RESPECTIVELY. - [SDR CA110909011](https://openairdocs.org/sdr/CA110909011), Aug 14, 2011: GOVERNOR. FAILED. (CAN) ACFT LEVELED OFF AFTER CLIMB, A BANG WAS HEARD THEN ACFT YAWED, ROTOR LOW HORN AND LIGHT SOUNDED. ENGINE FAILURE WAS CONFIRMED- N1 WAS AT 25 PERCENT AND T - [SDR CA111222011](https://openairdocs.org/sdr/CA111222011), Mar 6, 2011: DIFFUSER. USED. (CAN) UPON LANDING AND PERFORMING A POST FLIGHT VISUAL INSPECTION THE AME FOUND THE BOTTOM STRUT ON THE EXHAUST DIFFUSER CRACKED WITH A SECTION OF MATERIAL MISS - [SDR CA101122028](https://openairdocs.org/sdr/CA101122028), Nov 22, 2010: BAFFLE. DETACHED. BAFFLE DIVIDING FORWARD AND AFT SECTIONS OF FUEL CELL, FOUND DETACHED. FUEL IS ABLE TO MOVE AROUND POTENTIALLY CAUSING C OF G ISSUES. IN LOW FUEL SITUATIONS, SL - [SDR CA090806005](https://openairdocs.org/sdr/CA090806005), Jul 30, 2009: GOVERNOR. UNKNOWN. EXCESSIVE ENGINE DROOP. - [SDR CA090702013](https://openairdocs.org/sdr/CA090702013), Jul 1, 2009: FITTING. CRACKED. DURING A POST FLIGHT INSP, THE TAIL ROTOR DRIVE FITTING WAS FOUND CRACKED. TIME ON THE FITTING IS UNKNOWN. CRACK WAS FOUND RADIATING FROM THE BORE OF THE BARREL - [SDR CA090619003](https://openairdocs.org/sdr/CA090619003), Jun 16, 2009: QUILL ASSY. SHEARED. ACFT WOULD NOT START, UPON FURTHER INVESTIGATION THE QUILL DRIVE FROM STARTER/GENERATOR TO ENGINE FOUND SHEARED. - [SDR CA090126003](https://openairdocs.org/sdr/CA090126003), Jan 25, 2009: O-RING. LEAKING. (CAN) REPORTS OF A LOW FUEL CAUTION LIGHT COMING ON EARLY AND SMALL FUEL DRIP PROMPTED MX TO REMOVE THE LT FUEL CELL SUMP PLATE TO INSPECT THE LOW LEVEL FUEL SW - [SDR CA081120004](https://openairdocs.org/sdr/CA081120004), Nov 16, 2008: MOUNT. CRACKED. (CAN) CRACK DISCOVERED ON LT FWD STRUT MOUNT FITTING. - [SDR CA080731002](https://openairdocs.org/sdr/CA080731002), Jul 29, 2008: BEARING. ROUGH. (CAN) UPON A SCHEDULED INSPECTION OF THE TRANSMISSION WAFFER FILTER AN EXCESSIVE AMOUNT OF FERROUS METAL WAS FOUND. THERE HAD BEEN NO METAL FOUND ON THE CHIP DE - [SDR CA081023005](https://openairdocs.org/sdr/CA081023005), Jul 27, 2008: FITTING. CRACKED. (CAN) WHILE CONDUCTING 100 HR INSP NOTED AREA IN LT LOWER TAIL BOOM LONGERON AT FWD FITTING TO BE CRACKED. NDT CONFIRMED A CRACK INDCATION OF 1.5 INCHES LONG IN - [SDR CA080604011](https://openairdocs.org/sdr/CA080604011), May 28, 2008: ATTACH FITTING. CRACKED. (CAN) WHILE CONDUCTING A 25 HR INSP, A CRACK WAS NOTED ON THE LIFT LINK BEAM LUG. THE PART WAS REMOVED AND TT OF THE BEAM IS UNKNOWN AT THIS TIME. CRACK WAS FOU - [SDR CA080326001](https://openairdocs.org/sdr/CA080326001), Mar 25, 2008: WIRE. CHAFED. (CAN) DURING START UP THE STARTER RELAY CIRCUIT BREAKER WAS POPPING NOT ALLOWING THE STARTER TO START. IT WAS FOUND THAT THERE WERE 2 WIRES LABELED K2D20 AND K3 - [SDR CA080117002](https://openairdocs.org/sdr/CA080117002), Jan 17, 2008: BEARING. UNSERVICEABLE. (CAN) FOUND TAIL ROTOR HUB ASSY OB BEARING CAGE INSERT OUT OF IS SOCKET. ASSY SEND FOR O/H. (TC NR 20080117002) - [SDR CA080124003](https://openairdocs.org/sdr/CA080124003), Jan 17, 2008: CROSSTUBE. CRACKED. (CAN) WHILE THE ENGINEER WAS CONDUCTING THE DI, A CRACK IN THE AFT DART CROSSTUBE WAS DISCOVERED. THE DART CROSSTUBE FOLLOWS 300/600 HR INSP CYCLE. CROSSTUBE WA - [SDR CA071214009](https://openairdocs.org/sdr/CA071214009), Dec 10, 2007: MOUNT. CRACKED. (CAN) RT ENGINE BIPOD INSPECTED FOR SUSPICIOUS CRACK IN FRONT TUBING DURING 100 HRS INSPECTION. NDT REVEALED CRACK MOUNT AT WELDED JOINT. NOTE: THIS MOUNT WAS M - [SDR CA071127011](https://openairdocs.org/sdr/CA071127011), Nov 5, 2007: FITTING. CRACKED. (CAN) ON ROUTINE INSPECTION, A CRACK WAS NOTED IN THE LIFT LINK FITTING. TRANSMISSION WAS REMOVED AND SENT FOR REPAIR. THE TSO FOR THE COMPLETE TRANSMISSION WAS - [SDR CA070724005](https://openairdocs.org/sdr/CA070724005), Jul 23, 2007: CONTROL LEVER. BROKEN. (CAN) THIS IS THE INITIAL REPORT. INFORMATION NOT HERE YET. THE PILOT COULD ONLY GET 92 PERCENT NR RP, LANDED THE AIRCRAFT NO INCIDENT, AFTER SHUTDOWN THE ENGIN - [SDR CA070807005](https://openairdocs.org/sdr/CA070807005), Jul 17, 2007: CONNECTOR. BURNED. (CAN) TRAINING FLIGHT, NOTICED SMOKE COMING UP FROM CENTER CONSOLE BEHIND VHF NR 2 RADIO. PUT DOWN, A/C ON GROUND. CO-PILOT JUMPED OUT TO CHECK IN BATT COMPARTM - [SDR CA070524001](https://openairdocs.org/sdr/CA070524001), May 17, 2007: PUMP. FAILED. (CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPERATIONS, UPON DESCENT WITH AN EXTERNAL LOAD: THE MASTER CAUTION WARNING INDICATION WAS ILLUMINATED. THE LOAD WAS - [SDR CA070412004](https://openairdocs.org/sdr/CA070412004), Mar 30, 2007: GOVERNOR. DAMAGED. (CAN) DURING THE DAILY INSPECTION PERFORMED BY THE ENGINEER, THE SCREW HOLDING THE GOV SERVO LEVER PLATE IN PLACE WAS ENTIRELY BACKED OUT OF THE HOLE. THIS PART - [SDR CA070418003](https://openairdocs.org/sdr/CA070418003), Mar 21, 2007: MOUNT. CRACKED. (CAN) ENGINE MOUNT WAS INSTALLED NEW IAW STC SH99-11. POWER PLANT WAS ALIGNED IAW MM SUPPLEMENT. THE MM SUPPLEMENT INCLUDES AN INSP EVERY 100 HRS OR ANNUALLY. N - [SDR CA061222004](https://openairdocs.org/sdr/CA061222004), Dec 4, 2006: NUT. CRACKED. (CAN) THE ACORN NUTS WERE SENT OUT FOR NDT IAW THE REQUIREMENT OF THE OVERHAUL OF THE M/R HEAD ASSY. THE NDT SHOP FOUND A CRACK DEVELOPING NEAR THE BASE IN THE - [SDR CA060907005](https://openairdocs.org/sdr/CA060907005), Aug 30, 2006: ACTUATOR. FAILED. (CAN) DURING LONG LINE SLINGING OPERATIONS, UPON APPROACHING A DROP ZONE WITH A LOAD. THE COLLECTIVE WAS RAISED TO CUSHION LANDING OF THE LOAD, THEN LOWERED TO - [SDR CA060727001](https://openairdocs.org/sdr/CA060727001), Jul 27, 2006: NUT. CRACKED. (CAN) THIS IS AN ON CONDITION ITEM. SO HISTORY MAY NOT BE ACCURATE. M/R HUB ASSY HAS 18437.6 TIME SINCE NEW. M/R HEAD ASSY WAS IN FOR O/H AND REQUIRES ACORN NUT - [SDR CA060602004](https://openairdocs.org/sdr/CA060602004), May 29, 2006: DRAG BRACE. CRACKED. (CAN) THE DRAG BRACE WAS IN THE COMPONENT SHOP GETTING ITS 1200 HR INSPECTION/24 MONTH INSPECTION. THE DRAG BRACE ASSEMBLY WAS PREPARED FOR NDT MAGNETIC PARTICL - [SDR CA060524001](https://openairdocs.org/sdr/CA060524001), May 19, 2006: FITTING. CRACKED. AIRCRAFT WAS ON SEISMIC DRILL MOVE JOB. THE ENGINEER WAS DOING HIS DAILY INSPECTION WHEN NOTICED THAT ONE EAR OF THE LIFT LINK FITTING WAS APPEARED CRACKED. A C - [SDR CA060331005](https://openairdocs.org/sdr/CA060331005), Mar 27, 2006: SADDLE. CRACKED. CRACK WAS FOUND ON SKID TUBE AT FORWARD CROSSTUBE MOUNTING SADDLE. THERE WAS NO REPORT OF A HARD LANDING WITH THIS AIRCRAFT AT THIS TIME. TIMES FOR THESE SKID T - [SDR CA050816005](https://openairdocs.org/sdr/CA050816005), Aug 12, 2005: MOUNT. CRACKED. (CAN) THE ENGINE MOUNT WAS MODIFIED BY STC SH99-11 WHICH ALLOWS THE MOUNT TO BECOME ADJUSTABLE. THE ADJUSTABLE PORTION OF THE MOUNT IS RIVETED TO ONE LEG AND IT - [SDR CA050816006](https://openairdocs.org/sdr/CA050816006), Aug 12, 2005: MOUNT. CRACKED. (CAN) THE ENGINE MOUNT WAS MODIFIED BY STC SH99-11 WHICH ALLOWS THE MOUNT TO BECOME ADJUSTABLE. THE ADJUSTABLE PORTION OF THE MOUNT IS RIVETED TO ONE LEG AND IT - [SDR CA050707005](https://openairdocs.org/sdr/CA050707005), Jun 24, 2005: HUB. WORN. (CAN) DURING LAG PIN REPLACEMENT BLADE WAS REMOVED. UPON REMOVAL OF BLADE HUB WAS INSPECTED AND THE PROBLEM WAS FOUND. THE UPPER SURFACE OF THE LOWER HUB HALF K - [SDR CA051115006](https://openairdocs.org/sdr/CA051115006), Jul 5, 2004: STRUCTURE. CRACKED. ON MAINTENANCE SHUTDOWN DURING A NORMAL HELI LOGGING DAY, DURING INSP OF FLIGHT CONTROLS THE APPRENTICE NOTICED SOME SMOKING COMING FROM THE BOTTOM CORNER OF TH - [SDR 2004FA0000423](https://openairdocs.org/sdr/2004FA0000423), Mar 25, 2004: PIN. UNSERVICEABLE. THE LEADING EDGE OF THE LT SIDE TEETER PIN WAS DAMAGED (MUSHROOMED). FURTHER INSPECTION SHOWED THAT THE HEAD SIDE OF THE INSIDE DIAMETER OF THE LINER THAT THE T - [SDR CA040127014](https://openairdocs.org/sdr/CA040127014), Dec 28, 2003: PUMP. FAILED. (CAN) WHILE HELICOPTER WAS CONDUCTING AERIAL LIFT WORK THE PILOT NOTED THE ENGINE FUEL PUMP LIGHT CAME ON. HE RETURNED TO THE STAGING AREA AND LANDED UNEVENTFUL - [SDR CA040128006](https://openairdocs.org/sdr/CA040128006), Dec 28, 2003: PUMP. WORN. (CAN) FUEL CONTROL P/N 1-170-240-93, S/N 5ADS1907 WAS RECEIVED DUE TO DAMAGED MAIN DRIVE SHAFT SPLINE. DISASSEMBLED AND INSPECTED FCU AND FOUND DAMAGED PUMP ASS - [SDR AUS20031090](https://openairdocs.org/sdr/AUS20031090), Oct 10, 2003: COMPRESSOR. UNSERVICEABLE. (AUS) ENGINE COMPRESSOR SECTION CONTAINED COMPONENTS FROM AN ENGINE INVOLVED IN AN AIRCRAFT CRASH. ENGINE HAD BEEN ASSEMBLED FROM COMPONENTS FROM FIVE DIFFERENT - [SDR CA040204006](https://openairdocs.org/sdr/CA040204006), Sep 11, 2003: FUEL CONTROL. FAILED. (CAN) ENGINE STOPPED IN-FLIGHT. - [SDR FZO2003F00000](https://openairdocs.org/sdr/FZO2003F00000), Jul 18, 2003: DRIVE SHAFT. CHAFED. PILOT FELT HARMONIC VIBRATION DURING REDUCE POWER DECENT INTO DIP SITE. FOUND T/R DRIVE SHAFT PN 204-040-623-011 RUBBING ON 205-060-923-001 BOOT ASSY. BOOT SEAL All 91: https://openairdocs.org/engine/lycoming-t5317a/reports.md ## STCs that may be installed (OpenAirDocs) (2) 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 --- 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.