# GE CF6-80C2A5 - Type: Engine model (FAA registry) - Registry code: 30104 - Manufacturer (registry): GE - Model: CF6-80C2A5 - Engine type: Turbo-fan - Power: 60,100 lb thrust - Data sheet: [TCDS E13NE](https://openairdocs.org/tcds/E13NE) (OpenAirDocs) - Holder: General Electric Company GE Aerospace - Installed in: 3 registered aircraft - Page: https://openairdocs.org/engine/ge-cf6-80c2a5 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 2021-26-22](https://openairdocs.org/ad/2021-26-22): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Mar 14, 2022 - [AD 2022-02-18](https://openairdocs.org/ad/2022-02-18): Engine Mount Section · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 3 more. Effective Feb 25, 2022 - [AD 2021-14-11](https://openairdocs.org/ad/2021-14-11): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 25 more. Effective Aug 27, 2021 - [AD 2021-03-02](https://openairdocs.org/ad/2021-03-02): Fuel Control/Turbine Engines · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Mar 31, 2021 - [AD 2016-08-10](https://openairdocs.org/ad/2016-08-10): Accessory heat shield · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Jun 1, 2016 - [AD 2014-21-01](https://openairdocs.org/ad/2014-21-01): Fuel manifold · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Nov 28, 2014 - [AD 2013-08-20](https://openairdocs.org/ad/2013-08-20): Fuel tube · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 14 more. Effective May 31, 2013 - [AD 2012-03-12](https://openairdocs.org/ad/2012-03-12): No. 3 bearing packing · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 21 more. Effective Apr 5, 2012 - [AD 2009-21-07](https://openairdocs.org/ad/2009-21-07): Thrust and thrust control · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 21 more. Effective Dec 1, 2009 - [AD 2009-07-03](https://openairdocs.org/ad/2009-07-03): Eddy current inspection (ECI) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Apr 30, 2009 - [AD 2009-04-10](https://openairdocs.org/ad/2009-04-10): Critical life-limited parts · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 30 more. Effective Mar 30, 2009 - [AD 2008-21-11](https://openairdocs.org/ad/2008-21-11): Low-pressure turbine (LPT) cases · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 25 more. Effective Nov 28, 2008 - [AD 2008-02-17](https://openairdocs.org/ad/2008-02-17): Thrust reverser actuation systems · General Electric CF6-50A, CF6-50C, CF6-50C1 and 16 more. Effective Feb 28, 2008 - [AD 2007-11-20](https://openairdocs.org/ad/2007-11-20): Fuel shroud retaining rings · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 22 more. Effective Jul 10, 2007 - [AD 2007-05-14](https://openairdocs.org/ad/2007-05-14): Cast titanium weld- repaired forward engine mount platforms · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Apr 9, 2007 - [AD 2006-16-06](https://openairdocs.org/ad/2006-16-06): Certain stage 1 high- pressure turbine (HPT) rotor disks · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Sep 5, 2006 - [AD 2005-17-05](https://openairdocs.org/ad/2005-17-05): High pressure compressor rotor (HPCR) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 25 more. Effective Sep 27, 2005 - [AD 2005-06-07](https://openairdocs.org/ad/2005-06-07): Directional pilot valve (DPV) assembly · General Electric CF6-80A1, CF6-80A3, CF6-80C2A1 and 5 more. Effective Apr 25, 2005 - [AD 2004-22-07](https://openairdocs.org/ad/2004-22-07): Stage 2 nozzle guide vanes (HPT S2 NGVs) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Dec 1, 2004 - [AD 2003-12-08](https://openairdocs.org/ad/2003-12-08): Directional pilot valve · General Electric CF6-80A1, CF6-80A3, CF6-80C2A1 and 5 more. Effective Jul 23, 2003 - [AD 2003-02-07](https://openairdocs.org/ad/2003-02-07): Low pressure turbine (LPT) shrouds · General Electric CF6-50A, CF6-50C, CF6-50C1 and 30 more. Effective Mar 3, 2003 - [AD 2002-25-08](https://openairdocs.org/ad/2002-25-08): High pressure compressor rotor · General Electric CF6-45A, CF6-45A2, CF6-50A and 40 more. Effective Jan 23, 2003 - [AD 2002-22-12](https://openairdocs.org/ad/2002-22-12): Titeflex hoses · BAE Systems ATP, Avro 146-RJ100A, Avro 146-RJ70A and 122 more. Effective Dec 13, 2002 - [AD 2000-12-08](https://openairdocs.org/ad/2000-12-08): Mount Link Assemblies · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 4 more. Effective Aug 28, 2000 - [AD 2000-03-04](https://openairdocs.org/ad/2000-03-04): General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 19 more. Effective Apr 10, 2000 - [AD 99-01-01](https://openairdocs.org/ad/99-01-01): Accessory Gearbox (AGB) idler adapters · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 19 more. Effective Jan 21, 1999 - [AD 98-22-06](https://openairdocs.org/ad/98-22-06): Fan Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 41 more. Effective Nov 23, 1998 - [AD 97-22-14](https://openairdocs.org/ad/97-22-14): (HPCR) 3-9 Spool · General Electric CF6-50A, CF6-50C, CF6-50C1 and 29 more. Effective Nov 17, 1997 - [AD 96-16-07](https://openairdocs.org/ad/96-16-07): Rear Right Hand Mount Link · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 17 more. Effective Aug 28, 1996 - [AD 95-10-11](https://openairdocs.org/ad/95-10-11): Fan Reversers · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 17 more. Effective May 31, 1995 - [AD 94-20-06](https://openairdocs.org/ad/94-20-06): Oil System · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Dec 27, 1994 - [AD 94-06-03](https://openairdocs.org/ad/94-06-03): High Pressure Turbine Disk · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Apr 29, 1994 - [AD 93-14-18](https://openairdocs.org/ad/93-14-18): High pressure turbine (HPT) thermal shields · General Electric CF6-45A, CF6-45A2, CF6-50A and 40 more. Effective Oct 4, 1993 - [AD 91-15-25](https://openairdocs.org/ad/91-15-25): High Pressure Compressor Rotor · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 16 more. Effective Sep 6, 1991 - [AD 91-11-05](https://openairdocs.org/ad/91-11-05): High Pressure Compressor Rotor · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 16 more. Effective Jul 5, 1991 - [AD 91-05-21](https://openairdocs.org/ad/91-05-21): High Pressure Turbine · General Electric CF6-80C2A5, CF6-80C2B6, CF6-80C2B6F and 1 more. Effective Mar 27, 1991 Historical (superseded or no longer in force): - [AD 2020-20-13](https://openairdocs.org/ad/2020-20-13) (historical): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Nov 12, 2020 - [AD 2018-15-04](https://openairdocs.org/ad/2018-15-04) (historical): Turbine/Turboprop Engine--Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Oct 2, 2018 - [AD 2009-05-02](https://openairdocs.org/ad/2009-05-02) (historical): Drainless fuel manifold assemblies · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Mar 31, 2009 - [AD 2004-04-07](https://openairdocs.org/ad/2004-04-07) (historical): Stage 1 HPT rotor disks · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Mar 12, 2004 - [AD 2002-07-12](https://openairdocs.org/ad/2002-07-12) (historical): Life Limits Section of Continued Airworthiness (ICA) - Selected Critical Life-limited Parts · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 27 more. Effective May 15, 2002 - [AD 2001-10-07](https://openairdocs.org/ad/2001-10-07) (historical): High Pressure Turbine Rotor Disks · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 19 more. Effective Jun 18, 2001 - [AD 2000-08-12](https://openairdocs.org/ad/2000-08-12) (historical): Life-limited Parts · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 10 more. Effective Oct 23, 2000 - [AD 2000-16-12](https://openairdocs.org/ad/2000-16-12) (historical): High Pressure Compressor Rotor Stage 3-9 Spools · General Electric CF6-45A, CF6-45A2, CF6-50A and 39 more. Effective Sep 5, 2000 - [AD 2000-04-14](https://openairdocs.org/ad/2000-04-14) (historical): Fuel tube flange seating · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 12 more. Effective May 1, 2000 - [AD 99-24-15](https://openairdocs.org/ad/99-24-15) (historical): High Pressure Compressor Rotor (HPCR) Stage 3-9 Spools · General Electric CF6-45A, CF6-45A2, CF6-50A and 39 more. Effective Jan 28, 2000 - [AD 99-18-20](https://openairdocs.org/ad/99-18-20) (historical): Inadvertent In-flight Thrust Reverser · General Electric Aircraft Engines CF6-50 Series (all), CF6-80A1, CF6-80A3 and 6 more. Effective Nov 2, 1999 - [AD 99-18-19](https://openairdocs.org/ad/99-18-19) (historical): Inadvertent Thrust Reverser · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 7 more. Effective Sep 24, 1999 - [AD 99-08-13](https://openairdocs.org/ad/99-08-13) (historical): General Electric CF6-80A, CF6-80A1, CF6-80A2 and 26 more. Effective May 13, 1999 - [AD 91-20-02](https://openairdocs.org/ad/91-20-02) (historical): Fuel Manifolds · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 12 more. Effective Nov 25, 1991 - [AD 90-26-01](https://openairdocs.org/ad/90-26-01) (historical): Fuel Manifold Systems · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 11 more. Effective Dec 20, 1990 ## Information bulletins (advisory) (5) - [SAIB 2023-15](https://openairdocs.org/saib/2023-15): Falsified Forms from AOG Technics. Issued Dec 19, 2023 - [SAIB NE-11-27](https://openairdocs.org/saib/NE-11-27): Fuel Injector Nozzle - CF6-80 Improperly Welded Fuel Nozzles. Issued Apr 5, 2011 - [SAIB NE-10-37](https://openairdocs.org/saib/NE-10-37): Engine Fuel and Control: FADEC Fuel Metering Valve Resolver Feedback Faults. Issued Jul 12, 2010 - [SAIB NE-08-44](https://openairdocs.org/saib/NE-08-44): Engine Thrust Reverser Transcowl Clevis Pin. Issued Sep 3, 2008 - [SAIB NE-07-01](https://openairdocs.org/saib/NE-07-01): Dual engine flameouts on twin engine airplanes. Issued Oct 12, 2006 ## Registered aircraft (3) - [N731FD](https://openairdocs.org/aircraft/N731FD): [Federal Express Corp](https://openairdocs.org/faa-owner/FEDERAL%20EXPRESS%20CORP), [Memphis, TN](https://openairdocs.org/faa-place/TN/Memphis), built 1993, S/N 709 - [N732FD](https://openairdocs.org/aircraft/N732FD): [Federal Express Corporation](https://openairdocs.org/faa-owner/FEDERAL%20EXPRESS%20CORPORATION), [Memphis, TN](https://openairdocs.org/faa-place/TN/Memphis), built 1993, S/N 713 - [N733FD](https://openairdocs.org/aircraft/N733FD): [Federal Express Corp](https://openairdocs.org/faa-owner/FEDERAL%20EXPRESS%20CORP), [Memphis, TN](https://openairdocs.org/faa-place/TN/Memphis), built 1993, S/N 715 ## 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 (164, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR FDEA202404180470](https://openairdocs.org/sdr/FDEA202404180470), Apr 18, 2024: BLEED VALVE. FAILED. ON DEPARTURE PASSING 3000 FT RECEIVED ECAM ALERT BLEED HP VALVE FAULT NR 1. REFERENCED QRH BLEED VALVE FAULT. RESET OF HP BLEED VALVE UNSUCCESSFUL. RECEIVED BLE - [SDR FDEA202208181996](https://openairdocs.org/sdr/FDEA202208181996), Aug 18, 2022: ENGINE. SMOKE. AT CRUISE WE NOTICED SOME SORT OF SMOKE IN THE COCKPIT. DECLARED EMERGENCY AND DIVERTED TO PIT. NO SMOKE INDICATOR LIGHTS. EMERGENCY DECLARED. NR 1 ENGINE REMOV - [SDR FDEA202106171561](https://openairdocs.org/sdr/FDEA202106171561), Jun 17, 2021: ENGINE. FAILED. AT CRUISE ECAM INDICATION OF OIL FILTER CLOG FOR NR 1 ENGINE. PROCEEDED IAW ECAM AND SHUT THE MOTOR DOWN AFTER THREE MINUTES UNSUCCESSFULLY TO GET THE WARNING T - [SDR FDEA202102180410](https://openairdocs.org/sdr/FDEA202102180410), Feb 18, 2021: BLEED VALVE. FAULTED. CLIMBING OUT OF KIND AT 9000 FT GOT BLEED VALVE 1 FAULT. COMPLIED WITH ECAM AND TRIED A RESET OF BLEED VALVE. RESET WAS UNSUCCESSFUL. FOLLOWED ECAM AND QRH PROC - [SDR FDEA2020080541766](https://openairdocs.org/sdr/FDEA2020080541766), Aug 4, 2020: BOLT. FAILED. VBV UNISON RING BOLTS AT POSITION 7,8,9 OCLCOCK, TORQUE STRIPE HAS BEEN COMPROMISED SHGN 04AUG20 07:13 TORQUE CHECKED GOOD ON BOLTS #7 AND# 9 BOLTS NEED TORQUE - [SDR FDEA202007301718](https://openairdocs.org/sdr/FDEA202007301718), Jul 30, 2020: COUPLING. FAILED. DURING DEPARTURE, ECAM FOR HIGH NAC 250 DEG C, TROUBLSHOT NR 2 ENG IAW QRH. NO CHANGE WITH THROTTLE MOVE OR BLEED VALVE OFF. REACHED TOP OF CLIMB FL290 & TEMP D - [SDR FDEA2020060321106](https://openairdocs.org/sdr/FDEA2020060321106), Jun 2, 2020: ENGINE. FAILED. AFTER TOUCHDOWN IN KMEM NR 1 ENGINE BEGINE TO ROLL BACK & SHUT DOWN. AFTER TAXING IN ONTO THE RAMP, RAMP TWR & ANOTHER AIRCRAFT LET US KNOW THERE WERE FLAMES EX - [SDR FDEA2020022420371](https://openairdocs.org/sdr/FDEA2020022420371), Feb 22, 2020: ENGINE. LEAKING. PDIS 657 26-12 2254 22FEB20 MCI OPEN U LOGPAGES:3134646 AT CRUISE EXPERIENCED SMOKE AND FUMES IN COCKPIT AND (CABIN.) WHILE RUNNING QRH CHECKLIST, RECEIVED INTE - [SDR FDEA201703020769](https://openairdocs.org/sdr/FDEA201703020769), Mar 2, 2017: MEC. FAILED. DURING CRUISE, DESCENT, AND LANDING, THE NR 2 ENGINE LAGGED TARGET POINTER BY 20% N1. BOTH WITH AUTO THROTTLES ON AND OFF. THE NR 2 ENGINE N1 STUCK AT 92.4 % IN - [SDR FDEA201409052463](https://openairdocs.org/sdr/FDEA201409052463), Sep 5, 2014: SWITCH. DEFECTIVE. ON DEPARTURE ENG NR 2 REV PRESSURIZED ECAM WARNING, PRIOR WRITE UP. DID NOT RESET REVERSER ON MEL. REPLACED THE LT AND RT CDU SWITCH ASSYS PER M/M. - [SDR FDEA201311022669](https://openairdocs.org/sdr/FDEA201311022669), Nov 2, 2013: TURBINE. DAMAGED. ENROUTE, NR 2 ENGINE STARTED A SEVERE VIBRATION, COMPLIED WITH JRH. PRECAUTIONARY SHUTDOWN. DIVERTED. REMOVED AND REPLACED NR 2 ENGINE DUE TO TURBINE DAMAGE IAW - [SDR FDEA201208042844](https://openairdocs.org/sdr/FDEA201208042844), Aug 4, 2012: DOOR. OUT OF ADJUST. ON CLIMB OUT, AT 29,000 R1 FWD ENTRY DOOR ECAM ALERTED DOOR NOT CLOSED. JUMPSEATER REPORTED DOOR CHIME WAS SOUNDING AND DOOR LOCKS WERE INDICATING "HALF" LOCKED - [SDR FDEA201203281158](https://openairdocs.org/sdr/FDEA201203281158), Mar 28, 2012: PRESSURE SWITCH. FAILED. IN-FLIGHT ENG NR 1 SHUTDOWN DUE TO ENG OIL CLOG LIGHT WOULD NOT GO OUT. REF FIM 79-00-20, FIG 109. PERFORMED INSPECTION CHECK OF MASTER CHIP DETECTOR IAW AMM CH - [SDR FDEA201106092172](https://openairdocs.org/sdr/FDEA201106092172), Jun 9, 2011: BLADES. DAMAGED. ON CLIMBOUT, HEARD VERY LOUD BANG, ACFT YAWED RT AND NR 2 ENGINE SPOOLED DOWN, NO RED ECAM. NR2 ENG FLUCUATED AT IDLE WITH HIGH EGT FOR ABOUT 30 SECS. ECAM SHOW - [SDR FDEA201012044594](https://openairdocs.org/sdr/FDEA201012044594), Dec 4, 2010: LINE. LEAKING. HYD YELLOW RESERVIOR LO LEVEL - ECAM QTY AND OVERHEAD GAUGE INDICATIONS SHOWED YELLOW SYS QTY. DECLARED TO RED DOT. YELLOW PUMP LO PRESS WITH SUBSEQUENT LOSS OF - [SDR FDEA201007152515](https://openairdocs.org/sdr/FDEA201007152515), Jul 15, 2010: INDICATOR. FAILED. ENROUTE CAPT NOTICED NR2 EGT POINTER BELOW THE ZERO POSITION. DIGITAL READOUT SHOWED (4) GREEN DASHES. R & R NR2 EGT INDICATOR IAW MM 77-21-21-04-0. OPS CHECK G - [SDR FDEA200906031908](https://openairdocs.org/sdr/FDEA200906031908), Jun 3, 2009: ENGINE. LEAKING. ON TAKEOFF ROLL JUMP SEATERS DETECTED AN OIL ODOR AND SAW HAZY SMOKE. NOT ELECTRICAL, BUT IRRITATING. DURING CLIMB AND RETURNED TO MEM, ODOR DISSAPATED. 15 INCH - [SDR CA090522001](https://openairdocs.org/sdr/CA090522001), May 16, 2009: HOSE. LEAKING. (CAN) AFTER LANDING, DURING TAXI, THE GREEN HYD FLUID HAS BEEN LOST. THE ACFT HAS BEEN TOWED TO THE GATE. HOSE HAS BEEN REPLACED ON LT MLG DRAG BRACE. HYD SYS H - [SDR CA090514004](https://openairdocs.org/sdr/CA090514004), May 7, 2009: DISPLAY. SMOKE. (CAN) CREW DETECTED SMOKE IN FLIGHT DECK. DETERMINED IT WAS COMING FROM THE TCAS DISPLAY UNIT. ODOR DISSIPATED WHEN THE CIRCUIT BREAKER FOR TCAS MONITOR WAS PUL - [SDR FDEA200903210981](https://openairdocs.org/sdr/FDEA200903210981), Mar 21, 2009: WIRE HARNESS. FAILED. AT TOP OF DESCENT NR 2 ENG OIL PRESS INDICATED 0 PSI ON ECAM AND MECHANICAL GAUGE. SHUT DOWN ENGINE. WINDMILLED FOR 33 MINUTES INDICATING 0 OIL PRESSURE OIL TEM - [SDR FDEA200812265299](https://openairdocs.org/sdr/FDEA200812265299), Dec 26, 2008: UNKNOWN. UNKNOWN. LEVEL CRUISE AT FL 250, ENG 2 FUEL CLOG LIGHT CAME ON WITH ASSOCIATED ECAM ALERT. REDUCED ENG 2 POWER TO IDLE IAW ECAM. STARTED RETURN TO MEM. AFTER 7-8 MINS AT - [SDR AALA200803046](https://openairdocs.org/sdr/AALA200803046), Dec 6, 2008: FAN BLADE. DAMAGED. LIM INFLIGHT, DURING TAKEOFF BIRDS INGESTED INTO NUMBER ONE ENGINE. CREW REPORTED ENGINE INDICATIONS OF FLUCTUATION. RETURNED TO LIM AND LANDED WITHOUT INCIDENT - [SDR AALA200802527A](https://openairdocs.org/sdr/AALA200802527A), Nov 17, 2008: FAN BLADE. BIRD INGESTION. INFLIGHT - AT ROTATION CREW REPORTED LOUD BANG AND VIBRATION FROM NUMBER TWO ENGINE DUE TO BIRDSTRIKE. RETURNED TO SJU AND LANDED WITHOUT INCIDENT. REPLACED NUM - [SDR CA080804001](https://openairdocs.org/sdr/CA080804001), Jul 31, 2008: FLASHER. BURNED. (CAN) UPPER SLOWER BEACON AND STROBE LIGHTS INOP. FOUND FLASHER UNIT U/S (RECEPTACLE CONNECTOR BURNED & PARTIALLY MELTED INSIDE). CONNECTING ELECTRICAL PLUG INS - [SDR CA080728005](https://openairdocs.org/sdr/CA080728005), Jul 21, 2008: CIRCUIT BREAKER. BURNED. (CAN) DURING TROUBLESHOOTING OF THE INOPERATIVE LT OUTER TANK FUEL PUMP (DEACTIVATED IAW MEL) THE CIRCUIT BREAKER 3QA WAS FOUND BURNED, BODY CRACKED AND ONE LEG - [SDR AALA200801370](https://openairdocs.org/sdr/AALA200801370), May 22, 2008: FUEL FILTER. DIRTY. MCO INFLIGHT T1075/22MAY. NR TWO ENGINE FUEL CLOG LIGHT ILLUMINATED. FOLLOWED FUEL CLOG PROCEDURE AND INDICATION EXTINGUISHED. APPLIED TAKEOFF POWER AND LIGHT I - [SDR AALA200800484](https://openairdocs.org/sdr/AALA200800484), Mar 3, 2008: PRESSURE SWITCH. INOPERATIVE. BWI INFLIGHT T613/03MAR JFK TO MIA - NUMBER TWO ENGINE FUEL FILTER CLOG LIGHT ILLUMINATED. LANDED BWI WITHOUT INCIDENT. REPLACED THE NUMBER TWO ENGINE FUEL FILT - [SDR CA080213001](https://openairdocs.org/sdr/CA080213001), Feb 8, 2008: GENERATOR. CRACKED. (CAN) DURING TROUBLESHOOTING FOR HIGH OIL CONSUMPTION ON THE APU, FOUND A 7 INCHES CRACK ON THE GENERATOR HOUSING. THE IDG WAS REPLACED AND THE UNIT WAS SENT TO - [SDR CA071127002](https://openairdocs.org/sdr/CA071127002), Nov 21, 2007: COFFEEMAKER. SPARKS. (CAN) DURING FLIGHT, THE F/A REPORTED THE FWD COFFEE MAKER/WATER BOILER OVERHEATING AND NOTICED SOME SPARK COMING FROM THE UNIT. THE UNIT WAS DEACTIVATED. THE U - [SDR CA071127001](https://openairdocs.org/sdr/CA071127001), Nov 20, 2007: PUMP. CRACKED. (CAN) DURING CRUISE, THE YELLOW HYD SYS OVERHEAT ECAM MESSAGE CAME ON. LATER THE HYD RESERVOIR (LO LEVEL) WARNING CAME ON THE ECAM. NORMAL QRH PROCEDURE WAS PER - [SDR 07FDEA04371](https://openairdocs.org/sdr/07FDEA04371), Sep 28, 2007: REGULATOR VALVE. FAILED. DURING TAKEOFF ROLL BELOW APPROX 60 KNOTS ENG NR 1 REV PRESSURIZED AT APPROX 80 PERCENT N1. REJECTED TAKEOFF. RELEASED FOR SERVICE PER MEL/CDL: 78-30-01-A CATEG - [SDR CA070731001](https://openairdocs.org/sdr/CA070731001), Jul 27, 2007: SEAL. LEAKING. (CAN) DURING TAXI-IN AT THE GATE, A LARGE FUEL LEAKAGE WAS OBSERVED COMING FROM THE HMU FUEL DRAIN BELOW NR 2 ENGINE. ENGINE WAS SHUTDOWN, BUT LEAKAGE CONTINUED - [SDR AALA20071228](https://openairdocs.org/sdr/AALA20071228), Jul 2, 2007: BEARING. LEAKING. MIA - IMMEDIATELY AFTER TAKEOFF SMOKE ALARMS SOUNDED AND SMOKE REPORTED IN THE CABIN. RETURNED TO MIA AND LANDED WITHOUT INCIDENT. ACCOMPLISHED RIGHT ENGINE CHA - [SDR 07FDEA01660](https://openairdocs.org/sdr/07FDEA01660), Apr 29, 2007: ENGINE. BIRD INGESTION. HIGH SPEED REJECT CLE 24L AT 135 KTS. A SEAGULL WENT IN THE NR 2 ENG FOLLOWED BY A HEAVY VIBRATION. NR 2 ENG INDICATIONS APPEARED NORMAL AFTER STOPPING THE AIRC - [SDR CA070411002](https://openairdocs.org/sdr/CA070411002), Apr 5, 2007: SWITCH. STICKING. (CAN) DURING CLIMB THE AIRCRAFT HAD A (KRUGER) FAULT ECAM WARNING.QAH CARRIED OUT BUT WARNING REMAINED ON. AIRCRAFT RETURNED TO THE STATION. DURING TROUBLESHOOT - [SDR CA070404004](https://openairdocs.org/sdr/CA070404004), Apr 4, 2007: HOSE. PUNCTURED. (CAN) GREEN HYDRAULIC ECAM MESSAGE LOW LEVER WARNING CAME ON AFTER TAKE OFF. ON ARRIVAL, MAINTENANCE FOUND THE RT MAIN LANDING GEAR DOWN LOCK ACTUATOR FLEX LINE - [SDR CA061121001](https://openairdocs.org/sdr/CA061121001), Nov 19, 2006: ENGINE. FAILED. (CAN) AFTER TAKE OFF AND DURING LEVEL AT 40,000 FT CREW GOT ECAM MESSAGE MIN EQUIPMENT SMOKE WITH OVERHEAD WITH OVERHEAD LIGHT ON AND ODOR IN THE CABIN AND COCK - [SDR AALA20061067](https://openairdocs.org/sdr/AALA20061067), Nov 14, 2006: WHEEL. OUT OF BALANCE. INFLIGHT T1700/14NOV AT LIFT OFF AIRCRAFT BEGAN TO VIBRATE. LANDING GEAR WAS LT DOWN. 2 TO 4 MINUTES LATER VIBRATION GRADUALLY STOPPED. GEAR WAS LT DOWN FOR DUR - [SDR AALA20060961](https://openairdocs.org/sdr/AALA20060961), Oct 30, 2006: ENGINE. MALFUNCTIONED. JFK INFLIGHT T837/30 OCT - AFTER TAKEOFF THE AFT LAVATORY FIRE SMOKE ALARM WENT OFF. FLIGHT ATTENDANT REPORTED SOMETHING BURNING IN AFT LAVATORY. ALSO REPORTED - [SDR CA060906006](https://openairdocs.org/sdr/CA060906006), Sep 3, 2006: WARNING SYSTEM. MULTIPLE IND. (CAN) AT 50 KNOTS, FLIGHT CREW REJECTED TAKE OFF DUE TO NAV ADC, GPS DISAGREE WARNING. DURING TAXI TO THE GATE, FAULT CLEARED IT`S SELF. FMS WAS RESET IAW MM, G - [SDR 06FDEA2650](https://openairdocs.org/sdr/06FDEA2650), Jul 21, 2006: ECU. MALFUNCTIONED. AFTER TAKEOFF APPROXIMATELY AT 500' AGL, GOT A MASTER CAUTION ECAM MESSAGE FOR FADEC 2 FAULT. COMPLIED WITH CHECKLIST. RETURNED TO KMEM BECAUSE OF KBTR SHORT RW - [SDR CA060502002](https://openairdocs.org/sdr/CA060502002), Apr 27, 2006: WIRE. BURNED. (CAN) DURING ROUTINE INSPECTION, FOUND THE ELECTRICAL OUTLET WIRE FIN 8ME CHAFED ON FRAME 17 BETWEEN STR 28 AND 29 RT SIDE. THE GROMMET PROTECTION HAD FALLEN OF - [SDR CA060502003](https://openairdocs.org/sdr/CA060502003), Apr 22, 2006: WIRE. BURNED. (CAN) DURING AIRCRAFT TOWING, THE NAV 2 POSITION LIGHT CB POPPED. UNABLE TO RESET. DURING INVESTIGATION, FOUND THE 4 WIRES FROM THE LIGHT UNIT ASSY (7LA) BURNED - [SDR 06FDEA0812](https://openairdocs.org/sdr/06FDEA0812), Feb 23, 2006: HYDRAULIC LINE. CHAFED. PDIS 671 29-11 0007374 22FEB06 OAK OPEN R LOGPAGES: 01086620 ECAM ALERT AT FL320 GREEN HYD SYS QNT LOW ALERT. MANUAL GEAR EXTENSION ACCOMPLISHED. FLUID DRIPPING - [SDR 06FDEA0813](https://openairdocs.org/sdr/06FDEA0813), Feb 23, 2006: GCU. FAULTY. PDIS 682 24-30 0004948 22FEB06 MEM CLOSE R LOGPAGES: 01107636 GEN NR1 FAULT AFTER TAKEOFF WOULD NOT RESET. APU WAS INOP (ON MEL) FACT 23FEB06 07:18 MEM R VERIFI - [SDR AALA20060072](https://openairdocs.org/sdr/AALA20060072), Jan 30, 2006: PUMP. FAILED. JFK INFLIGHT T1473/30JAN, RIGHT HAND FUEL FILTER LIGHT ILLUMINATED DURING CLIMB. RETURNED TO JFK AND LANDED WITHOUT INCIDENT. RIGHT HAND ENGINE FUEL FILTER PULL - [SDR AALA20050711](https://openairdocs.org/sdr/AALA20050711), Oct 27, 2005: DUCT. CONTAMINATED. AFTER LANDING GEAR EXTENSION THERE WAS A SLIGHT ODOR OF PLASTIC AND SMOKE DETECTORS 2R AND 4R WERE ALARMING. LANDED WITHOUT INCIDENT. REPLACED GREEN, BLUE, AND - [SDR 05FDEA03488](https://openairdocs.org/sdr/05FDEA03488), Oct 25, 2005: SMOKE DETECTOR. MALFUNCTIONED. INTERMITTENT AVIONICS SMOKE WARNING. DID NOT SMELL ANY SMOKE. REMOVED AND REPLACED AVIONICS SMOKE DETECTOR 11WA IAW A 300 MM 26-15-12-4. OPS CHECKS GOOD. SERVIC - [SDR AALA20050623](https://openairdocs.org/sdr/AALA20050623), Sep 26, 2005: ENGINE. BIRD INGESTION. MIA INFLIGHT T903/26SEPT - NR 2 ENGINE INGESTED A BIRD DURING CLIMB. EXPERIENCED SOME VIBRATION WITHIN LIMITS. RETURNED TO MIA AND LANDED WITHOUT INCIDENT. PERF - [SDR 05FDEA02326](https://openairdocs.org/sdr/05FDEA02326), Aug 8, 2005: SUPPORT BRACKET. CRACKED. NR 1 ENG HYDRAULIC CASE DRAIN LINES SUPPORT BRACKET CRACKED ACCESS THRU 473CL PNL. All 164: https://openairdocs.org/engine/ge-cf6-80c2a5/reports.md ## STCs that may be installed (OpenAirDocs) (6) 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 SE01543CH](https://openairdocs.org/stc/SE01543CH): Replace Hamilton Sundstrand P/N 778839-13, 778839-14, 778839-19, 778839-20, 778839-37, 778839-38, 816682-1, 840618-2, 880724 carbon bushings with Cook Airtomic P/N AIR22947 Slotted Entry Busing in the High Pressure Shutoff Valve. Cook Airtomic - [STC SE01478CH](https://openairdocs.org/stc/SE01478CH): Installation of Cook Airtomic alignment joint p/n AIR 22912. Cook Airtomic - [STC SE00969CH](https://openairdocs.org/stc/SE00969CH): Install AeroControlex P/N 2605290-001 variable stator feedback control cable. AeroControlex Group TransDigm Inc - [STC SE01471AT](https://openairdocs.org/stc/SE01471AT): Replace right and left side Rohr, Inc. fire detection harness on GE CF6-80C2 engine. Unison Industries. Lists CF6-80C2 Series - [STC SE00463LA](https://openairdocs.org/stc/SE00463LA): Install fireproof blankets on the engine fan reverser intermediate fireseal, in lieu of fireproof intumescent coating. This STC is jointly by owned by Hi Temp Insulation and MRA Systems acting through Middle River Aircraft Systems, 103 Chesapeake Park Plaza, Baltimore, MD 21220. Hi Temp Insulation Inc - [STC SA2227SO](https://openairdocs.org/stc/SA2227SO): Installation of wiring and associated components for utilization of the Rolls Royce, Inc., ARINC, interface/readers UT1317 or UT1317/1, for the purpose of acquisition, recording, and analysis in real time of engine/aircraft/ systems. (767 SERIES POWERED BY RR RB-11-524 SERIES. Rolls Royce, Inc. Lists CF6-80 Series --- 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.