# GE CT7-2A - Type: Engine model (FAA registry) - Registry code: 30184 - Manufacturer (registry): GE - Model: CT7-2A - Engine type: Turbo-shaft - Power: 1,625 hp - Data sheet: [TCDS E8NE](https://openairdocs.org/tcds/E8NE) (OpenAirDocs) - Holder: General Electric Company GE Aviation - Installed in: 3 registered aircraft - Page: https://openairdocs.org/engine/ge-ct7-2a 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 2004-07-09](https://openairdocs.org/ad/2004-07-09): PGB oil filter impending bypass button (IBB) · General Electric CT7-2A, CT7-2D, CT7-2D1 and 14 more. Effective May 11, 2004 - [AD 93-25-17](https://openairdocs.org/ad/93-25-17): Gas Generator Turbine (GGT) Disks and Cooling Plates · General Electric CT7-2A, CT7-5A2, CT7-6 and 2 more. Effective Feb 2, 1994 Historical (superseded or no longer in force): - [AD 2003-06-03](https://openairdocs.org/ad/2003-06-03) (historical): Propeller gearbox (PGB) oil filter · General Electric Aircraft Engines CT7-2A, CT7-2D, CT7-2D1 and 14 more. Effective Apr 24, 2003 ## Registered aircraft (3) - [N214AU](https://openairdocs.org/aircraft/N214AU): [Bank Of Utah Trustee](https://openairdocs.org/faa-owner/BANK%20OF%20UTAH%20TRUSTEE), [Salt Lake City, UT](https://openairdocs.org/faa-place/UT/Salt%20Lake%20City), built 1984, S/N 28129 - [N511EV](https://openairdocs.org/aircraft/N511EV): [Bank Of Utah Trustee](https://openairdocs.org/faa-owner/BANK%20OF%20UTAH%20TRUSTEE), [Salt Lake City, UT](https://openairdocs.org/faa-place/UT/Salt%20Lake%20City), built 1982, S/N 28105 - [N724HT](https://openairdocs.org/aircraft/N724HT): [Bank Of Utah Trustee](https://openairdocs.org/faa-owner/BANK%20OF%20UTAH%20TRUSTEE), [Salt Lake City, UT](https://openairdocs.org/faa-place/UT/Salt%20Lake%20City), built 1987, S/N 28175 ## NTSB investigations (1) From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [NTSB GAA26WA270](https://openairdocs.org/ntsb/GAA26WA270), Aug 2, 2026: Bell 214ST (N511EV), West Attica, Greece, destroyed, 2 fatal ## FAA accident and incident reports None matched to aircraft with this engine model. ## Service difficulty reports (83, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR 9EKA20200409001](https://openairdocs.org/sdr/9EKA20200409001), Apr 9, 2020: TUBE. BROKEN. WHILE CONDUCTING AN APPROACH ENGINE NO.1 POWER ROLLED BACK. OBSERVATIONS AND ACTIONS WERE: 1. SOUND OF ENGINE SPOOL DOWN 2. ENG.1 OUT LIGHT, FOLLOWED BY MASTER - [SDR 9EKA20160512006](https://openairdocs.org/sdr/9EKA20160512006), May 12, 2016: ECU. FAULTY. ENGINE 1 INDICATED EXCESSIVE TORQUE SPLIT WITH YAW MOTION OF THE ACFT. ENG 1 THROTTLE WAS MANUALLY BROUGHT DOWN TO 10% BELOW NR 2 & SAFELY RETURNED TO BASE. - [SDR 9EKA20160420005](https://openairdocs.org/sdr/9EKA20160420005), Apr 20, 2016: BEAM. CRACKED. DURING INSPECTION OF AIRFRAME FOR SUSPECTED CAUSE FOR TWO REV VIBRATIONS, FOUND A 4.9 INCH X1.25 INCH CRACK IN THE LT BAGGAGE COMPARTMENT & ENG DECK AT FS STATI - [SDR 9EKA20160224002](https://openairdocs.org/sdr/9EKA20160224002), Feb 24, 2016: BLADE. CRACKED. MAIN ROTOR BLADE HAS A 2 INCH CRACK IN THE CHORD DIRECTION OF THE TIP SHOE, CAUSED FROM EROSION, AS A RESULT FROM UNIMPROVED LANDING ZONES. - [SDR 9EKA20160219001](https://openairdocs.org/sdr/9EKA20160219001), Feb 19, 2016: STUD. SHEARED. TWO MAIN ROTOR TRANSMISSION MAST STUDS FOUND SHEARED OFF DURING 25 HOUR INSPECTION. - [SDR 9EKA20151201026](https://openairdocs.org/sdr/9EKA20151201026), Dec 1, 2015: CHIP DETECTOR. ACTIVATED. PILOT REPORTED MOMENTARY TAIL ROTOR GEAR BOX CHIP LIGHT ON MASTER CAUTION PANEL. - [SDR 9EKA20150916024](https://openairdocs.org/sdr/9EKA20150916024), Sep 16, 2015: ENGINE. FAILED. DURING CRUISE FLIGHT IN A SHALLOW RIGHT HAND TURN, NR 2 ENG EXPERIENCED HIGH SIDE FAILURE IMMEDIATELY, FOLLOWED BY UNCOMMANDED SHUTDOWN. ACFT RECOVERED 26 MILES - [SDR 9EKA2015FA0000414](https://openairdocs.org/sdr/9EKA2015FA0000414), Aug 28, 2015: CHIP DETECTOR. DAMAGED. ON RETURN TO BASE, NR 2 ENGINE CHIP DETECTOR CAUTION LIGHT ILLUMINATED AND STAYED ON, EMERGENCY PROCEDURES IAW THE RFM WERE C/W BY THE PIC, CONDUCTED TROUBLESHO - [SDR 9EKA02162015003](https://openairdocs.org/sdr/9EKA02162015003), Feb 13, 2015: TURBINE. CRACKED. DURING 25 HR SCHEDULED INSPECTION, CRACK WAS FOUND IN EXHAUST AREA OF NR 1 POWER TURBINE. MM WAS REFERENCED & NO CRACKS ARE ALLOWED, AWAITING PT CHANGE. - [SDR 9EKA02162015002](https://openairdocs.org/sdr/9EKA02162015002), Jan 30, 2015: HOSE. CHAFED. WHILE IN STEADY STATE CRUISE FLIGHT AT 70% TQ, MAIN TRANSMISSION OIL CAUTION LIGHT ILLUMINATED & THE OIL PRESS GAUGE FOR THE TRANSMISSION WAS OBSERVED DECREASIN - [SDR 9EKA02162015001](https://openairdocs.org/sdr/9EKA02162015001), Dec 25, 2014: SKIN. DEBONDED. TAIL BOOM, EMPENNAGE METALLIC SKIN, HONEYCOMB STRUCTURE ON RT SIDE JUST AFT OF THE FWD VOR ANTENNA MOUNT WL 74, BS 294 HAS DISBONDED. INSPECTION WAS PERFORMED I - [SDR 2013FA0000625](https://openairdocs.org/sdr/2013FA0000625), Nov 1, 2013: CASE. CRACKED. DURING INVESTIGATION OF AN OIL LEAK, A CRACK WAS FOUND IN THE MAIN TRANSMISSION UPPER LEFT HAND RING GEAR CASE . - [SDR 9EKA2013082300003](https://openairdocs.org/sdr/9EKA2013082300003), Aug 23, 2013: TAB. MISSING. WHILE CONDUCTING A "POST FLIGHT" INSPECTION, MECHANICS NOTICED THAT ONE OF THE MAIN ROTOR BLADES WAS MISSING A TRIM TAB. - [SDR 9EKA2013082200002](https://openairdocs.org/sdr/9EKA2013082200002), Aug 21, 2013: FITTING. CRACKED. CRACK ON THE VERTICAL SPAR OF THE TAIL IT IS LOCATED IN THE COLD WORK AREA JUST ABOVE THE OUTPUT QUILL OF THE 42 DEG GEARBOX. LOCATED ON THE LEFT SIDE AT BS 569 - [SDR LCFA20130429001](https://openairdocs.org/sdr/LCFA20130429001), Apr 29, 2013: TAIL BOOM. CRACKED. LEFT SIDE OF THE TAIL BOOM CRACKED IMMEDIATELY FORWARD AND BELOW THE FORWARD MOUNT OF THE LEFT VOR ANTENNA. LENGTH OF CRACK IS APPROXIMATELY 20/64" LONG AND EXT - [SDR LCFA2012F00259](https://openairdocs.org/sdr/LCFA2012F00259), Nov 16, 2012: BEARING SUPPORT. BROKEN. ROD END BEARING, FOUND BROKEN AFTER COMPLETION OF FLIGHT, ON POST INSPECTION. - [SDR LCFA2012F00073](https://openairdocs.org/sdr/LCFA2012F00073), Apr 11, 2012: ATTACH FITTING. CRACKED. WHILE PERFORMING AN URELATED MX WALK-AROUND INSPECTION, NOTED A CRACK ON THE UPPER LT MAIN FUSELAGE TO TAILBOOM ATTACHMENT FITTING. THIS IS A KNOWN ISSUE. - [SDR 3S8R201108230001](https://openairdocs.org/sdr/3S8R201108230001), Aug 23, 2011: FRAME. CRACKED. MAIN GEAR BOX FRAME HAS A CRACK ON THE LT SIDE RADIUS, STA 227.10, WL 65.00. - [SDR P4YA2011050900001](https://openairdocs.org/sdr/P4YA2011050900001), May 9, 2011: DRIVE SHAFT. CRACKED. DURING A 25HR CHECK, THE NR 6 TAIL ROTOR DRIVESHAFT MOUNTING FLANGE WAS DISCOVERED CRACKED ON THE OUTPUT SIDE OF THE IGB COUPLING. THE CRACKS ARE AROUND THE BOL - [SDR P4Y2008F00000](https://openairdocs.org/sdr/P4Y2008F00000), Jun 7, 2008: SKIN. CRACKED. STRUCTURAL DAMAGE TO AC LT SIDE TRANSMISSION AREA CAUSED BY CONTACT WITH FORKLIFT BASE DURING CARGO LOADING OPERATIONS. (K) - [SDR HEEA113269](https://openairdocs.org/sdr/HEEA113269), Dec 17, 2006: HOSE. RUPTURED. NR 1 HYDRAULIC PUMP CAPTION ILLUMINATED WITH PRESSURE AT ZERO, PRESSURE FLUCTUATED A COUPLE OF TIMES ACCOMPANIED WITH A LOUD NOISE. MAINTENANCE FOUND NR 1 SYSTE - [SDR HEEA111397](https://openairdocs.org/sdr/HEEA111397), Oct 6, 2006: OIL COOLER. CONTAMINATED. OIL COOLER CAUTION LIGHT ILLUMINATED IN FLIGHT WITH ASSOCIATED UTILITY HYD CAUTION LIGHT FLICKERING. APPROPRIATE EMERGENCY PROCEDURE PERFORMED. MAINTENANCE CLEA - [SDR HEEA111385](https://openairdocs.org/sdr/HEEA111385), Oct 4, 2006: SEAL. LEAKING. OIL PRESSURE WAS NORMAL AFTER TAKEOFF, ABOUT 35 MIN IN CRUISE FLIGHT, NR 2 ENGINE OIL PRESSURE HAD DROPPED TO 55 PSI, THEN ON ARRIVAL, NR 2 ENGINE OIL PRESSURE - [SDR HEEA111000](https://openairdocs.org/sdr/HEEA111000), Aug 31, 2006: PUMP. FAILED. NR 2 FUEL TRANSFER PUMP FAILED, CONTINUED WITH NO FURTHER PROBLEMS. MAINTENANCE REPLACED THE NR 2 TRANSFER PUMP. - [SDR ALG2006F00036](https://openairdocs.org/sdr/ALG2006F00036), Apr 17, 2006: WIRE. SHORTED. IN FLIGHT, BOTH ELEVATORS FAILED, AARS ROLL FAILED, SCAS PITCH FAILED, AND FBW ELEVATORS WENT FULL UP. THE AIRCRAFT ROLLED LT AND PITCHED UP. WITH FULL FWD AND - [SDR ALG2006F00035](https://openairdocs.org/sdr/ALG2006F00035), Mar 31, 2006: CURRENT LIMITER. INOPERATIVE. IN FLIGHT, EN ROUTE, THE FOLLOWING INDICATION WENT TO (0). NR 1 NG, NR 1 ENG PRESS, TEMP, C-BOX PRESS, NR 1 HYD PRESS, NR 2 HYD TEMP. NO CAUTION LIGHTS ILLUMINA - [SDR HEEA108122](https://openairdocs.org/sdr/HEEA108122), Feb 16, 2006: SWASHPLATE. OUT OF ADJUST. 3 MINUTES AFTER TAKEOFF, A LOW RUMBLE WAS HEARD FOLLOWED BY A VERTICAL VIBRATION. AIRCRAFT WAS FLOWN AND SHUT DOWN WAS ACCOMPLISHED. UPON INSPECTION THE AIRCRAF - [SDR HEEA107966](https://openairdocs.org/sdr/HEEA107966), Feb 7, 2006: WINDOW. MISSING. DURING TAKEOFF CREW HEARD POPPING NOISE AND NOTICED PILOT'S SKYLIGHT MISSING, APPARENTLY CAME OFF DURING TAKEOFF. - [SDR HEEA107922](https://openairdocs.org/sdr/HEEA107922), Jan 17, 2006: PACKING. CUT. DURING CRUISE FLIGHT NR 2 ENGINE OIL PRESSURE DECREASED TO APPROXIMATELY 15 PSI OVER ABOUT 60 SECONDS. ENGINE OIL PRESSURE EMERGENCY PROCEDURE WAS PERFORMED. AI - [SDR HEEA107418](https://openairdocs.org/sdr/HEEA107418), Dec 14, 2005: PUMP. POPPED. DURING CRUISE FLIGHT, THE NR 2 TRANSFER LIGHT ILLUMINATED AND CIRCUIT BREAKER POPPED. FOLLOWED EMERGENCY PROCEDURE AND LANDED. MAINTENANCE REPLACED NR 2 TRANSFE - [SDR ALG2005F00121](https://openairdocs.org/sdr/ALG2005F00121), Dec 6, 2005: FILTER. FAILED. ON TAKEOFF, NR 2 ENGINE FUEL FILTER LIGHT CAME ON, AND THE PILOT LANDED THE AC. THE MECHANIC REMOVED AND REPLACED NR 2 ENGINE FUEL FILTER ELEMENT, GROUND RUN AN - [SDR HEEA107317](https://openairdocs.org/sdr/HEEA107317), Dec 1, 2005: WIRE. CHAFED. SCAS FAILED IN FLIGHT. ATTEMPTED TO RESET IT BUT IT BLEW THE CIRCUIT BREAKER. SECURED OFF AND CONTINUED TO BASE WITHOUT INCIDENT. MAINTENANCE REPAIRED CHAFED WI - [SDR ALG2005F00056](https://openairdocs.org/sdr/ALG2005F00056), Jul 30, 2005: LINE. LEAKING. ENROUTE, A HOWLING NOISE STARTED AND BECAME LOUDER, THE PILOT NOTICED NR 1 HYD PRESSURE FLUCTUATED BETWEEN 200-300 PSI. THE PILOT TURNED OFF NR 1 HYD NOISE WENT - [SDR HEEA107351](https://openairdocs.org/sdr/HEEA107351), Jul 22, 2005: ENGINE. MALFUNCTIONED. IN CRUISE, NR 1 ENGINE NR AND NG AND MGT WENT HIGH, TORQUE AND NP SHOWED ZERO, REDUCED NR 1 THROTTLE AND PERFORMED CHECKLIST AND SHUT ENGINE DOWN. ROTOR RPM WEN - [SDR CA050309001](https://openairdocs.org/sdr/CA050309001), Mar 1, 2005: TUBE. CHAFED. (CAN) DURING ROUTINE MAINTENANCE, THE SUBJECT TUBE WAS FOUND WITH A (0.375 INCH X 0.187 INCH) HOLE THAT ORIGINATED FROM CHAFING WITH A HYDRAULIC OIL LINE. THE H - [SDR ALG2004F00059](https://openairdocs.org/sdr/ALG2004F00059), Oct 11, 2004: WARNING LIGHT. ACTIVATED. FIVE MINUTES AFTER TAKEOFF, AC815 TRANSMISSION CHIP LIGHT ILLUMINATED, PILOT RETURNED TO RIG. MECHANIC REMOVED, CLEANED, AND INSPECTED ALL TRANSMISSION CHIP PLU - [SDR HEEA096018](https://openairdocs.org/sdr/HEEA096018), Jun 22, 2004: BLEED VALVE. MALFUNCTIONED. WHILE HOVERING FOR TAKEOFF,NR 2 MGT STARTING RISING. MGT SPIKED AT 933 DEGREES THREE TIMES, THEN STAYED AT 933 DEGREES. AIRCRAFT WAS SENT DOWN AND MGT RETURNED - [SDR HEEA092089](https://openairdocs.org/sdr/HEEA092089), Jan 10, 2004: ECU. MALFUNCTIONED. SHORTLY AFTER TAKE OFF NR 1 ENGINE TORQUE FLUCTUATED. MAINTENANCE FOUND ECU DEFECTIVE. - [SDR HEEA092091](https://openairdocs.org/sdr/HEEA092091), Jan 9, 2004: ECU. MALFUNCTIONED. AFTER TAKEOFF TORQUE GUAGES FLUCTUATED. RETURNED TO BASE. - [SDR HEEA089035](https://openairdocs.org/sdr/HEEA089035), Aug 27, 2003: ENGINE. MALFUNCTIONED. ENROUTE FROM GB-426, AIRCRAFT LOST POWER ON NR 2 ENGINE. CONTINUED TO MCY AND PERFORMED SINGLE ENGINE LANDING. - [SDR ALGA087781](https://openairdocs.org/sdr/ALGA087781), Jun 26, 2003: STARTER. MALFUNCTIONED. WILL NOT ENGAGE EVERYTIME. REQUEST WARRANTY REPAIR. RO 33256 DMR 719713 - [SDR ALGA087782](https://openairdocs.org/sdr/ALGA087782), Jun 26, 2003: STARTER. FAILED. STARTER WILL NOT ENGAGE. REQUEST WARRANTY REPAIR. DMR 719714 RO33252 - [SDR MALA030287](https://openairdocs.org/sdr/MALA030287), May 29, 2003: PRESSURE SWITCH. FAILED. DURING CLIMBOUT ON FLIGHT 3183, RT MAIN PUMP LIGHT ILLUMINATED AFTER TAKEOFF. AIR RETURN TO MSP. MAINTENANCE REPLACED MAIN FUEL PRESSURE SWITCH P/N 8346-001, OP - [SDR HEEA086685](https://openairdocs.org/sdr/HEEA086685), May 22, 2003: EXCITER. MALFUNCTIONED. EXCITER PRODUCES SLOW LIGHT OFF. REPLACED. - [SDR HEEA086686](https://openairdocs.org/sdr/HEEA086686), May 22, 2003: PRESSURE SWITCH. MALFUNCTIONED. NR 2 ENGINE BLOWER LIGHT CAME ON AFTER ENGINE START. REPLACED. - [SDR HEEA086590](https://openairdocs.org/sdr/HEEA086590), May 12, 2003: SEAL. LEAKING. FIFTY TWO MINUTES AFTER TAKEOFF, NR 2 ENGINE OIL LIGHT ILLUMINATED WITH COINCIDING PRESSURE DROP OF NR 2 ENGINE OIL PRESSURE GAUGE. PRESSURE WENT TO ZERO WHILE - [SDR HEEA084413](https://openairdocs.org/sdr/HEEA084413), Feb 12, 2003: IGNITER. FAILED. ENGINE HARD TO START. REPLACED IGNITERS. - [SDR ALG2003F00029](https://openairdocs.org/sdr/ALG2003F00029), Dec 3, 2002: CARTRIDGE. INOPERATIVE. DURING CRUISE FLIGHT, NR 1 FUEL TRANSFER PUMP CAUTION LIGHT ILLUIMINATED, AIRCRAFT LANDING WAS UNEVENTFUL, MAINTENANCE WAS NOTIFIED. THE MECHANIC FOUND NR 1 FUE - [SDR HEEA080441](https://openairdocs.org/sdr/HEEA080441), Jul 9, 2002: BLEED VALVE. MALFUNCTIONED. NR 1 ENGINE HAS LOW POWER DUE TO MALFUNCTIONING BLEED VALVE. TO BE SENT TO VENDOR FOR REPAIR. - [SDR HEEA080115](https://openairdocs.org/sdr/HEEA080115), Jun 25, 2002: IGNITER. WORN. IGNITER WORN. TO BE SENT TO VENDOR FOR CREDIT. All 83: https://openairdocs.org/engine/ge-ct7-2a/reports.md --- 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.