# Lycoming AL5512 - Type: Engine model (FAA registry) - Registry code: 41581 - Manufacturer (registry): LYCOMING - Model: AL5512 - Engine type: Turbo-shaft - Power: 4,075 hp - Data sheet: [TCDS E4NE](https://openairdocs.org/tcds/E4NE) (OpenAirDocs) - Holder: Honeywell Aerospace US LLC - Installed in: 4 registered aircraft - Page: https://openairdocs.org/engine/lycoming-al5512 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. None matched. ## Registered aircraft (4) - [N233CH](https://openairdocs.org/aircraft/N233CH): [Columbia Helicopters Inc](https://openairdocs.org/faa-owner/COLUMBIA%20HELICOPTERS%20INC), [Aurora, OR](https://openairdocs.org/faa-place/OR/Aurora), S/N MM820 - [N240CH](https://openairdocs.org/aircraft/N240CH): [Columbia Helicopters Inc](https://openairdocs.org/faa-owner/COLUMBIA%20HELICOPTERS%20INC), [Aurora, OR](https://openairdocs.org/faa-place/OR/Aurora), S/N MM819 - [N242CH](https://openairdocs.org/aircraft/N242CH): [Columbia Helicopters Inc](https://openairdocs.org/faa-owner/COLUMBIA%20HELICOPTERS%20INC), [Aurora, OR](https://openairdocs.org/faa-place/OR/Aurora), built 1983, S/N MJ023 - [N245CH](https://openairdocs.org/aircraft/N245CH): [Columbia Helicopters Inc](https://openairdocs.org/faa-owner/COLUMBIA%20HELICOPTERS%20INC), [Aurora, OR](https://openairdocs.org/faa-place/OR/Aurora), built 1983, S/N MJ022 ## 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 (33) As reported by operators and repair stations, by the model named in the report. - [SDR CHIA202511059838](https://openairdocs.org/sdr/CHIA202511059838), Nov 5, 2025: ENGINE. OVERTEMP. DURING DESCENT TO DROP OFF PASSENGERS AND CARGO, THE NR 2 ENGINE PTT BEGAN TO RISE TO 905C AND THE N1 WAS AT 102% FOR AT LEAST 15 SECONDS. ACFT RETURNED TO BASE - [SDR CHIA202407187623](https://openairdocs.org/sdr/CHIA202407187623), Jul 18, 2024: CONTROL BOX. ACTIVATION ERROR. THREE MINS AFTER TAKEOFF, THE COPILOT NOTED A SPLIT IN TORQUE SHOWING THE #1 ENGINE HAD ROLLED BACK TO 40% TORQUE. THE ENGINE WAS BEEPED UP AND THE AIRCRAFT WAS - [SDR CHIA2020091064669](https://openairdocs.org/sdr/CHIA2020091064669), Sep 6, 2020: CONTROL BOX. FAILED. PILOT ACCOUNT: DURING FIRE FIGHTING MISSION, NR 2 ENGINE ROLLED BACK TO INTERMEDIATE SETTING (LESS THAT FLIGHT RPM WITH RRPM DECAY, ABOVE GROUND IDLE). THIS OCC - [SDR CHIA202009064669](https://openairdocs.org/sdr/CHIA202009064669), Sep 6, 2020: CONTROL BOX. FAILED. INTERIM SUPPLEMENTAL INFORMATION: THE OVERSPEED CONTROL BOX LISTED BELOW HAS BEEN RETURNED TO THE OEM (HONEYWELL) AND IS PRESENTLY UNDER EVALUATION BY THE OEM A - [SDR CHIA2020090624671](https://openairdocs.org/sdr/CHIA2020090624671), Sep 2, 2020: CONTROL BOX. FAILED. NR 2 ENGINE ROLLBACK ON APPROACH TO WATER SOURCE. ENGINE SECURED PER EMERGENCY ABNORMAL CHECKLIST. COULD NOT FIND ANY DEPENDENCY DURING T/S. REMOVED AND REPLACE - [SDR CHIA202009174694](https://openairdocs.org/sdr/CHIA202009174694), Sep 17, 2019: ENGINE. POWER LOSS. ON APPROACH TO DIP SITE NR 2 ENGINE FAILED TO RESPOND. NR 2 HUNG BACK AT AROUND 20% TQ, PILOTS WENT INTO EMERGENCY ENGINE TRIM & MANUALLY BEEPED ENGINE WITH NO - [SDR CHIR020165022375](https://openairdocs.org/sdr/CHIR020165022375), May 2, 2016: CASE. DEBONDED. (P2-CH) NR 2 ENGINE CHIP LIGHT, CONFIRMED METAL CONTAMINATION ON CHIP PLUG AND OIL FILTER. AFTER RECEIPT AT REPAIR STATION, DIFFUSER AND GP AREA INSPECTED PRIOR - [SDR CHIR050220162375](https://openairdocs.org/sdr/CHIR050220162375), May 2, 2016: COMPRESSOR. DEBONDED. THE ENGINES OEM WAS ABLE TO CONFIRM THE PLASMA REPAIR OF THE COMPRESSOR CASE WAS DONE TO APPROVED DATA. NO DETERMINATION OF THE CAUSE FOR THE FAILURE HAS BEEN M - [SDR CHIR201603312325](https://openairdocs.org/sdr/CHIR201603312325), Mar 31, 2016: MANIFOLD. LEAKING. NR 1 ENGINE FIRE WARNING IN-FLIGHT AT END OF DAYS OPERATIONS AT HOVER. MECHANIC CONFIRMED FIRE AFTER ACFT WAS SET DOWN. FIRE AT 12:00 ON TOP AND BACK OF BURNER - [SDR CHIR201511172182](https://openairdocs.org/sdr/CHIR201511172182), Nov 11, 2015: BOLT. BROKEN. DURING DISASSEMBLY OF COMPONENT, SCUFFING ON BOTH THE SPIRAL BEVEL GEAR AND PINION GEAR WAS NOTED. THE CUSTOMER HAD REPORTED A SINGLE BOLT BROKEN UPON ON-WING T - [SDR CHIR2015090102057](https://openairdocs.org/sdr/CHIR2015090102057), Aug 28, 2015: BOLT. CRACKED. DURING DISASSEMBLY OF COMPONENT IT WAS NOTICED THERE IS SEVERE SCUFFING ON BOTH THE SPIRAL BEVEL RING GEAR AND THE SPIRAL BEVEL PINION GEAR. AT DISASSEMBLY, 2 B - [SDR CHIR2014040400236](https://openairdocs.org/sdr/CHIR2014040400236), Apr 4, 2014: NOZZLE. MISOVERHAULED. T3 NOZZLE WAS RECEIVED OVERHAULED, INSTALLED IN ENGINE AND RAN IN TEST CELL. DURING TEST CELL A COAST DOWN NOISE WAS NOTED. DURING DISASSEMBLY, PIECES OF THE NO - [SDR CHIR201412120057](https://openairdocs.org/sdr/CHIR201412120057), Dec 9, 2013: CASE. OVERTEMP. THE ENGINE WAS ORIGINALLY REMOVED FOR HIGH PTIT. HIGH PTIT WAS CONFIRMED IN THE TEST CELL. DURING DISASSEMBLY IT WAS NOTED THAT THERE WAS EVIDENCE OF PLASMA SPR - [SDR CHIR201310071464](https://openairdocs.org/sdr/CHIR201310071464), Oct 3, 2013: IMPELLER. DAMAGED. THE ENGINE WAS ORIGINALLY REMOVED FOR HIGH PTIT. HIGH PTIT WAS CONFIRMED IN THE TEST CELL. DURING DISASSEMBLY IT WAS NOTED THAT THERE WAS EVIDENCE OF PLASMA SPR - [SDR CHIR20131609001](https://openairdocs.org/sdr/CHIR20131609001), Sep 12, 2013: INVERTER. OUT OF ADJUST. OPERATOR HAS EXPERIENCED ISSUES WITH MALADJUSTED TORQUE INVERTER, SIGNAL CONDITIONERS, ALSO KNOWN AS RATIO DETECTOR POWER SUPPLY, RDPS, ASSOCIATED WITH THE ENGI - [SDR CHIAMJ017/09/002](https://openairdocs.org/sdr/CHIAMJ017%2F09%2F002), Aug 22, 2009: ACTUATOR. RESTRICTED. DURING (FLIGHT CONTROLS TRAVEL AND FLIGHT BOOST SYS CK) AS PART OF PRE-FLIGHT CHECKS (DESCRIBED IN FLIGHT MANUAL PART 1, SECTION 2 PAGE 2-11 ITEM 29 (A)) PILOTS - [SDR MJ01709002](https://openairdocs.org/sdr/MJ01709002), Aug 22, 2009: TRUNNION. BINDING. DURING THE "FLIGHT CONTROLS TRAVEL AND FLIGHT BOOST SYS CHECK" AS PART OF THE PRE-FLIGHT CK, COMPANY PILOTS NOTICED ABNORMAL RESISTANCE OF LONGITUDINAL CYCLIC C - [SDR 2005FA0000871](https://openairdocs.org/sdr/2005FA0000871), Jun 8, 2005: ADAPTER. CRACKED. DURING OVERHAUL OF ENGINE AWN ADAPTER, NDT FOUND .450 INCH TOTAL LENGTH CRACK IN THE BOLT HOLE OF LUG NR 1. IN THE BORE OF LUG, CRACK LENGTH IS .300 OF INCH AND - [SDR CA050315012](https://openairdocs.org/sdr/CA050315012), Mar 10, 2005: VENT. FAILED. (CAN) DURING REFUELING, A LOUD BANG WAS HEARD FROM CABIN OF AIRCRAFT. FUEL WAS THEN SEEN LEAKING RAPIDLY FROM AIRCRAFT. PILOTS NOTED FUEL INSIDE CABIN SECTION B - [SDR CA040410001](https://openairdocs.org/sdr/CA040410001), Apr 1, 2004: DRIVE ASSY. CRACKED. (CAN) DURING INSPECTION IAW AD 2004-06-51 A CRACK WAS DETECTED IN THE UPPER EXTENSION 37 INCHES FROM THE TOP. SHAFT WAS REMOVED FROM SERVICE AND RETURNED TO MFG - [SDR CHI2003F00004](https://openairdocs.org/sdr/CHI2003F00004), Jul 27, 2003: ENGINE. MAKING METAL. DURING FLIGHT NR 2 ENGINE CHIP LIGHT CAMP ON. PILOTS REF EMERGENCY CHECKLIST AND IT INSTRUCTED THEM TO MONITOR ENGINE OIL PRESSURE AND TEMP, THEN LAND AS SOON A - [SDR CHI2003F00003](https://openairdocs.org/sdr/CHI2003F00003), Jul 23, 2003: ENGINE. MAKING METAL. ENGINE CHIP LIGHT CAME ON IN FLIGHT, PILOTS REFERENCED EMERGENCY CHECKLIST AND IT INSTRUCTED THEM TO MONITOR ENGINE TEMP AND OIL PRESSURE AND TO LAND AS SOON AS - [SDR CA030716007](https://openairdocs.org/sdr/CA030716007), Jun 25, 2003: ENGINE. FAILED. (CAN) LOUD BANG, SMOKE, NR 2 ENGINE STOPPED. AIRCRAFT RETURNED TO BASE SINGLE ENGINE. SMALL PIECES OF ENGINE FOUND CONTAINED IN NACELLE THAT APPEAR TO HAVE BEEN - [SDR CHI2003F00000](https://openairdocs.org/sdr/CHI2003F00000), Jun 4, 2003: BAR. CRACKED. DURING NORMAL ROTOR HEAD MAINTENANCE, THE TWO REPORTED TIE BARS WERE FOUND WITH NUMEROUS DEFECTS. THE DEFECTS CONSISTED OF SEVERAL CRACKED PLATES AT THE TIE BAR - [SDR CHI2003F00002](https://openairdocs.org/sdr/CHI2003F00002), Mar 14, 2003: COMPRESSOR WHEEL. CRACKED. TWO CRACKS WERE FOUND IN THE 1ST STAGE COMPRESSOR DISC (PN210133105) DURNG AN INSPECTION. THE CRACKS ARE LOCATED IN TWO OF THE COMPRESSOR BLADE RETENTION SLOTS. - [SDR CA000501009](https://openairdocs.org/sdr/CA000501009), Apr 12, 2000: TRANSMISSION. MAKING METAL. (CAN) DURING DESCENT, CHIP WARNING LITE ILLUMINATED. MAINTENANCE PERSONNEL THEN CLEANED CHIP PLUG & CHANGED FILTER. SERVICEABILITY CHECK CARRIED OUT AS PER BOEI - [SDR CHIR3488](https://openairdocs.org/sdr/CHIR3488), Aug 16, 1999: DRIVESHAFT. CRACKED. TWO CRACKS IN OUTBOARD ADAPTER END. CRACKS GO THROUGH AN OUTBOARD RIVET HOLE AND EXTEND AT A 45 DEGREE ANGLE INBOARD AND OUTBOARD TO THE ADAPTER EDGE. P/N 114D3 - [SDR CA990818003](https://openairdocs.org/sdr/CA990818003), Aug 3, 1999: BEARING. FAILED. (CAN) AFTER SHUTDOWN (FOLLOWING LOGGING OPERATIONS), A LOT OF BLACK GREASE AND METAL HAD BEEN SLUNG FROM THE SWASHPLATE SEAL AND PIECES OF BEARING CAGE WERE FOU - [SDR CHIA3099](https://openairdocs.org/sdr/CHIA3099), Jun 13, 1998: PUMP. WORN. DURING TAKEOFF CHECK, PILOT NOTICED NR 2 FUEL PRESS 12 PSI LOWER THAN NR 1. THIS IS LOWER THAN IT NORMALLY OPERATES WITH ENG AT FLY AND BOTH FUEL TANK BOOST PUM - [SDR CA970707007](https://openairdocs.org/sdr/CA970707007), Jun 23, 1997: TURBINE ROTOR. BLADE FRACTURED. (CAN) ENGINE WAS SHUTDOWN IN FLIGHT AND AIRCRAFT RETURNED TO POINT OF DEPARTURE. INSPECTION FOUND COMPRESSOR BLADE FROM THE FIRST TURBINE ROTOR HAD SEPARATED AN - [SDR CHI1512](https://openairdocs.org/sdr/CHI1512), Oct 26, 1995: ENGINE. DAMAGED. INFLIGHT ENGINE SHUT-DOWN DURING LOGGING OPERATION. NO VISIBLE DAMAGE TO INLET OF ENG OR FIRST STAGES OF COMPRESSOR. COMPR WOULD ROTATE, BUT WITH DIFFICULTY, & - [SDR CHI1477](https://openairdocs.org/sdr/CHI1477), Aug 21, 1995: SWITCH. BROKE. DURING REMOVAL OF ENGINE SCREEN AND NOSE BOX COWL, NOTICED NR 1 ENGINE TRANSMISSION TEMP SWITCH WAS HANGING BY THE CANNON PLUG WHERE IT HAD BROKEN IN HALF AT TH - [SDR CHI1478](https://openairdocs.org/sdr/CHI1478), Aug 8, 1995: SWITCH. BROKEN. PILOTS REPORTED INTERMITTENT NR 1 ENGINE TRANSMISSION HOT LIGHT. DURING TROUBLESHOOTING, FOUND M2001-517 TEMP SWITCH BROKE IN HALF AND WIRES PULLED OUT AT CANNO --- 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.