# Lycoming T5311B - Type: Engine model (FAA registry) - Registry code: 41607 - Manufacturer (registry): LYCOMING - Model: T5311B - Engine type: Turbo-shaft - Power: 1,100 hp - Data sheet: [TCDS E1EA](https://openairdocs.org/tcds/E1EA) (OpenAirDocs) - Holder: Ozark Aeroworks LLC - Installed in: 2 registered aircraft - Page: https://openairdocs.org/engine/lycoming-t5311b 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 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 2002-09-09](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 97-07-05](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 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 74-09-03](https://openairdocs.org/ad/74-09-03): Compressor Rotor Discs · Honeywell International T5309C, T5311A and T5311B. Effective May 2, 1974 Historical (superseded or no longer in force): - [AD 2002-03-01](https://openairdocs.org/ad/2002-03-01) (historical): Reduction Gearbox Assembly · Honeywell International T5311A, T5311B, T5313B and 2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) - [N204RA](https://openairdocs.org/aircraft/N204RA): [Rotak LLC](https://openairdocs.org/faa-owner/ROTAK%20LLC), [Anchorage, AK](https://openairdocs.org/faa-place/AK/Anchorage), built 1965, S/N 2034 - [N67FU](https://openairdocs.org/aircraft/N67FU): [Rotak LLC](https://openairdocs.org/faa-owner/ROTAK%20LLC), [Anchorage, AK](https://openairdocs.org/faa-place/AK/Anchorage), built 1967, S/N 2064 ## 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 (35) As reported by operators and repair stations, by the model named in the report. - [SDR CA190806009](https://openairdocs.org/sdr/CA190806009), Jul 31, 2019: BOLT. BROKEN. (CAN) DURING CRUISE FLIGHT THE PILOT HEARD "WHAT SOUNDED LIKE A SMALL BANG, A SOUND THAT IN THE PAST I HAD BEEN A METAL DRINK BOTTLE OR CELLPHONE DROPPING ONTO - [SDR CA130820004](https://openairdocs.org/sdr/CA130820004), Aug 15, 2013: BOLT. SHEARED. (CAN) DURING CRUISE FLIGHT, THE ACFT DEVELOPED A SUDDEN AND SEVERE VIBRATION. THE PILOT IMMEDIATELY LANDED AND SHUTDOWN. INSPECTION OF THE ACFT SHOWED THE INBD - [SDR CA130326007](https://openairdocs.org/sdr/CA130326007), Mar 26, 2013: NUT. DAMAGED. (CAN) DURING SCHEDULED MAINTENANCE OF TAIL ROTOR DRIVESHAFT, NEW BOLTS AND NUTS BEING INSTALLED, A NEW NUT WAS FOUND TO HAVE NO SELF LOCKING ABILITY ON ANY BOLT - [SDR CA110516029](https://openairdocs.org/sdr/CA110516029), May 16, 2011: PANEL. DELAMINATED. DURING A VISUAL INSPECTION OF THE ABOVE NOTED ACFT THE CENTER ROOF SECTION WAS FOUND SEVERLY DELAMINATED. THE ROOF PANEL WAS REMOVED AND THE AREA FUTHER INSPECT - [SDR CA110516030](https://openairdocs.org/sdr/CA110516030), May 16, 2011: PANEL. DELAMINATED. DURING A VISUAL INSPECTION OF THE ACFT THE ENGINE DECK WAS FOUND TO BE DELAMINATED AND THE HONEYCOMB WAS FOUND TO BE SOFT IN THE ENTIRE PANEL. PANEL WAS REMOVED - [SDR CA110204009](https://openairdocs.org/sdr/CA110204009), Jan 31, 2011: VOLT REGULATOR. FAILED. DURING CRUISE FLIGHT THE PILOT NOTICED THE AMMETER FLUCTUATE AND THE GENERATOR LIGHT FLICKER. THE PILOT BEGAN TO DESCEND WHEN THE GENERATOR LIGHT, LT BOOST PUMP - [SDR CA090512011](https://openairdocs.org/sdr/CA090512011), May 8, 2009: BULKHEAD. CRACKED. (CAN) DURING A VISUAL INSP, A CRACK WAS FOUND AT THE BOTTOM OF THE RT ANGLE AT TAILBOOM TO FUSELAGE JUNCTION (PN 204-030-713-101). AFTER REMOVAL OF THE TAILBOOM - [SDR CA081017008](https://openairdocs.org/sdr/CA081017008), Oct 3, 2008: LONGERON. CRACKED. (CAN) DURING A VISUAL INSPECTION OF THE ACFT THE AME NOTICED A CRACK IN THE UPPER LT TAILBOOM LONGERON APROX. 3 INCHES AFT OF THE TAILBOOM ATTACHMENT FITTING. A - [SDR CA071010005](https://openairdocs.org/sdr/CA071010005), Aug 28, 2007: BLADE. CRACKED. (CAN) ON TUESDAY THE 28TH OF AUGUST 2007, AT APPROX 19:00, LANDED AT THE STAGING AREA. THE PILOT COMMENTED THAT THERE WAS A VIOLENT LATERAL VIBRATION. AT THIS T - [SDR CA070122011](https://openairdocs.org/sdr/CA070122011), Jan 22, 2007: COLLECTIVE STICK. RATCHETING. (CAN) PILOT COMPLAINED OF RATCHETING FEEL TO COLLECTIVE CONTROL STICK. AIRCRAFT RETURNED TO BASE. INSPECTION REVEALED THAT THE COLLECTIVE FRICTION SURFACE ROLL - [SDR CA060818004](https://openairdocs.org/sdr/CA060818004), Aug 14, 2006: BOLT. LOOSE. (CAN) DURING A 100 HOUR INSPECTION THE ENGINEER NOTED A LARGE AMOUNT OF PLAY IN THE CLEVIS OF THE TAIL ROTOR FLIGHT CONTROL ROD. INVESTIGATION REVEALED AN UNDER - [SDR CA050715002](https://openairdocs.org/sdr/CA050715002), Jul 10, 2005: TURNBUCKLE. UNSECURE. LOCKWIRE LEFT UNLOCKWIRED RESULTING IN TURNBARREL BECOMING UNDONE RESULTING IN TAILROTOR PITCH CHANGE FAILURE. SPEED RIGS WERE LOCK WIRED ON THE ONE END BUT THE - [SDR CA050418007](https://openairdocs.org/sdr/CA050418007), Apr 11, 2005: RELAY. DEFECTIVE. ON SHUTDOWN ENGINE CONTINUED TO MOTOR OVER SLOWLY. CONTACTS STUCK. RCR REPLACED AND PROBLEM SOLVED. - [SDR CA050418008](https://openairdocs.org/sdr/CA050418008), Apr 8, 2005: NUT. CRACKED. UPON INSP NOTICED CRACKED JAN NUT ON LINEAR ACTUATOR. - [SDR CA050418006](https://openairdocs.org/sdr/CA050418006), Apr 4, 2005: HOUSING. WORN. (CAN) DURING INSPECTION THE TAIL ROTOR CONTROL WAS REMOVED AND INSPECTED FOR WEAR. WEAR WAS FOUND BEYOND LIMITS IN THE HOUSING. THIS ITEM IS A 1000 HOUR OVERHAU - [SDR CA050427008](https://openairdocs.org/sdr/CA050427008), Apr 1, 2005: BLADE. DAMAGED. VOID, CHORDWISE STATION 155 TO 157, HALF INCH WIDE THREE INCHES LONG. BELL HELICOPTER VERDICT THAT BLADE STILL SERVICEABLE. BHT ALLOWS VOID IN THIS AREA. 6 INCH - [SDR CA030923010](https://openairdocs.org/sdr/CA030923010), Sep 12, 2003: YOKE. CRACKED. (CAN) TAIL ROTOR HUB ASSY WAS SENT FOR OVERHAUL. YOKE WAS SENT FOR NDT AS PART OF O/H AND WAS FOUND TO BE CRACKED. - [SDR CA040301002](https://openairdocs.org/sdr/CA040301002), Aug 17, 2003: COMPRESSOR. FAILED. (CAN) THE AIRCRAFT DEPARTED A STAGING AREA, SHORTLY AFTER TAKEOFF, THE AIRCRAFT HAD AN ENGINE FAILURE AND CRASHED IN TALL TREES. THE PILOT WAS THE ONLY OCCUPANT - [SDR CA030610011](https://openairdocs.org/sdr/CA030610011), Jun 7, 2003: SPAR. CRACKED. (CAN) ENGINEER OPENED TAIL ROTOR DRIVESHAFT COVER TO CHANGE COUPLINGS AND FOUND A CRACK HAD DEVELOPED IN THE VERTICAL FIN SPAR. STARTING AT THE TOP LIGHTENING H - [SDR CA030317016](https://openairdocs.org/sdr/CA030317016), Mar 14, 2003: NUT. CRACKED. (CAN) ON VISUAL INSPECTION NUT WAS FOUND TO BE CRACKED AT WORM GEAR THREAD. THESE PARTS HAVE A 1000 HR NDT INSPECTION. THIS COMPANY INCLUDE A 300 HR VISUAL THIS - [SDR CA030421004](https://openairdocs.org/sdr/CA030421004), Jan 31, 2003: LONGERON. CRACKED. (CAN) UPPER LT ATTACH LONGERON CRACKED AFT OF HOT BONDED DOUBLER. CRACK APPEARS TO HAVE STARTED AT A RIVET HOLE. THE CRACK WAS DISCOVERED DURING A ENGINE REMOVA - [SDR CA030421005](https://openairdocs.org/sdr/CA030421005), Jan 31, 2003: LONGERON. CRACKED. (CAN) MODIFICATION OF THE DOOR ASSEMBLY WAS COMPLETED PRIOR IAW BHT. TB204-79-11. THE CRACKED PIECES WERE REPLACED WITH NEW PIECES AND REINSTALLED IAW TB 204-79 - [SDR CA021105012](https://openairdocs.org/sdr/CA021105012), Nov 4, 2002: BELLCRANK. CRACKED. (CAN) AT 1000 HR INSPECTION BELLCRANK FOR THE CYCLIC WAS REMOVED FOT GREASING OF THE BEARINGS. BELLCRANK WAS FOUND TO BE CRACKED AT ONE BEARING. CRACK WAS COMPL - [SDR CA011109007](https://openairdocs.org/sdr/CA011109007), Oct 24, 2001: SEGMENT. MISSING. (CAN) UPON INSTALLATION OF THE NEW CHAIN, THE ENGINEER NOTICED A SPACE BETWEEN SOME CHAIN LINKS. CHAIN IS MISSING A SEGMENT. - [SDR CA000801011](https://openairdocs.org/sdr/CA000801011), Jul 22, 2000: CASE. CRACKED. (CAN) WHILE CARRYING OUT A DAILY INSPECTION, THE AME NOTICED A CRACK ON THE TRANSMISSION SUPPORT CASE WHERE THE LIFT LINK ATTACHES. - [SDR AU000186](https://openairdocs.org/sdr/AU000186), Jan 25, 2000: BLADE. FAILED. (AUS) THIRD STAGE COMPRESSOR DISC AND BLADES DESTROYED. DOWNSTREAM COMPRESSOR DAMAGE. NO DAMAGE TO THE FIRST TWO STAGES. - [SDR CA991027081](https://openairdocs.org/sdr/CA991027081), Sep 15, 1999: FLOORBEAM. CRACKED. (CAN) DURING REMOVAL OF FLOORBOARDS DURING SCHEDULED MAINTENANCE, THE LEFT MAIN BEAM WEB WAS FOUND CRACKED. REPAIR CARRIED OUT IAW BELL DATA. SUBMITTER SUSPECTE - [SDR CA990719005](https://openairdocs.org/sdr/CA990719005), Jun 30, 1999: HOUSING. WORN. (CAN) PILOT NOTICED BALL WAS OUT OF TURN/SLIP INDICATOR SO THEN PILOT INPUTTED THE RIGHT PEDAL TO CORRECT. HOWEVER, THE ROTORCRAFT DID NOT RESPOND TO RIGHT PEDA - [SDR CA990728048](https://openairdocs.org/sdr/CA990728048), Jun 29, 1999: BEARING. WRONG PART. (CAN) UNIT SENT TO O/H. WHEN SG WAS DISASSEMBLED, IT WAS NOTED THAT THE WRONG BEARINGS WERE INSTALLED (NOT THE MANUFACTURER'S BEARINGS). UNAPPROVED PARTS REPLAC - [SDR CA990119011](https://openairdocs.org/sdr/CA990119011), Dec 29, 1998: CROSS TUBE. CRACKED. (CAN) CROSS TUBE SHEARED ON LANDING CAUSING DAMAGE TO FUSE AND TAIL BOOM. CRACK IS BELIEVED TO HAVE STARTED AT AN INTERNAL CORROSION PIT OR VOID. - [SDR CA981109011](https://openairdocs.org/sdr/CA981109011), Oct 27, 1998: DAMPENER. CRACKED. (CAN) STARTER/GENERATOR IN SHOP FOR REPAIR WAS FOUND TO HAVE WRONG DAMPENER BACKPLATE INSTALLED CAUSING INSUFFICIENT SPRING PRELOAD WHICH RESULTED IN EXCESS WEA - [SDR CA990412006](https://openairdocs.org/sdr/CA990412006), Oct 20, 1998: MOUNT. WORN. (CAN) DURING INSPECTION, GRAY PASTE WAS NOTED UNDER THE SERVICE DECK OF THE ENGINE MOUNTS. REMOVAL OF THE ENGINE AND DECK DISCLOSED THE CRACKED BEAM CAP. THE EN - [SDR CA980519006](https://openairdocs.org/sdr/CA980519006), May 8, 1998: VALVE. BROKEN. (CAN) ON RUN-UP, UNABLE TO SWITCH HYDRAULICS TO MANUAL. HYDRAULIC BYPASS VALVE CANNON PLUG RECEPTACLE BROKEN OFF AT ITS BASE. INTERIOR CONNECTIONS BROKEN ALLOWI - [SDR CA971223001](https://openairdocs.org/sdr/CA971223001), Dec 11, 1997: CAP ANGLE. BROKEN. (CAN) UPPER CAP ANGLE FOUND BROKEN AND A CRACK HAD DEVELOPED IN THE MAIN PANEL. CRACK APPROX 2 INCHES TO 2.50 INCHES IN FRONT OF P/N 204-060-651-001, TUBE ASSY - [SDR CA960814201](https://openairdocs.org/sdr/CA960814201), Aug 4, 1996: INNER RING. CRACKED. (CAN) ON DAILY INSPECTION, CRACK FOUND IN L.H. TRUNNION MOUNTING EAR OF THE SWASHPLATE INNER RING. ## 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 SE00028EN](https://openairdocs.org/stc/SE00028EN): Installation of Pratt & Whitney Engine Services Inc. SmartCycle Plus Engine Monitoring System, P/N EMU-K-010-1 on specified 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.