# GE CF6-80C2A8 - Type: Engine model (FAA registry) - Registry code: 30105 - Manufacturer (registry): GE - Model: CF6-80C2A8 - Engine type: Turbo-fan - Power: 57,860 lb thrust - Data sheet: [TCDS E13NE](https://openairdocs.org/tcds/E13NE) (OpenAirDocs) - Holder: General Electric Company GE Aerospace - Installed in: 0 registered aircraft - Page: https://openairdocs.org/engine/ge-cf6-80c2a8 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 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 ## 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 None registered with this engine model now. ## 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 (32) As reported by operators and repair stations, by the model named in the report. - [SDR P5CA2021011000011](https://openairdocs.org/sdr/P5CA2021011000011), Jan 9, 2021: BLEED VALVE. MALFUNCTIONED. BLEED NR 3 EICAS MESSAGE ON TAKE OFF ROLL. FWD TO MEL 36-11-03, MDDR 140670, CAT C. DEACT NR 3 HP BLEED. REMOVED AND REPLACED HPC (OFF PART: PN 773289-18, SN 20 - [SDR CA190722001](https://openairdocs.org/sdr/CA190722001), Jul 20, 2019: LINE. LEAKING. (CAN) PILOT REPORTS GREEN SYSTEM LOW QUANTITY MESSAGE ON ECAM, QRH HAS BEEN PERFORMED, QUANTITY LEVEL IS AT THE RED DOT, SAME. DISPATCH FOUND THAT THE AIRCRAFT - [SDR CA190708001](https://openairdocs.org/sdr/CA190708001), Jul 5, 2019: ACTUATOR. FAULTED. (CAN) AT TAKEOFF PHASE, MESSAGE ON ECAM, LDG DOOR NOT CLOSE. AIRCRAFT DIVERT. AS PER INVESTIGATION, FOUND L/H NOSE DOOR UPLOCK FAULT WITH MICROSWITCHES. MICROSW - [SDR CA190401010](https://openairdocs.org/sdr/CA190401010), Mar 31, 2019: CONTROL LEVER. FAULTED. (CAN) AFTER TAKEOFF L/G LEVER INTERLOCK ECAM UNABLE TO RAISE GEAR ON SYSTEM 1 AND 2 ACCOMPLISHED CB RESET #U52 AS PER QRH SYSTEM RESET AND WAS UNSUCCESSFUL ON S - [SDR CA190327021](https://openairdocs.org/sdr/CA190327021), Mar 26, 2019: SWITCH. FAULTED. (CAN) EN ROUTE ECAM YELLOW SERVO JAM. ECAM ACTIONS HAD ALREADY BEEN PERFORMED. YELLOW SERVO CTL SWITCHED OFF. SUSPECT AN INDICATION PROBLEM. CREW IS CHECKING TH - [SDR CA160108004](https://openairdocs.org/sdr/CA160108004), Jan 6, 2016: WIRE. DAMAGED. (CAN) WIRES LOCATED IN THE WHEEL WELL NEAR A CANISTER. THE WIRE ROUTING WAS TOO SLACK AND WITH TIME THE LOOSE PROTECTED WIRES GOT WORN OUT. - [SDR CA151223004](https://openairdocs.org/sdr/CA151223004), Dec 22, 2015: WATER HEATER. SPARKS. (CAN) WATER HEATER WAS PRODUCING SPARKS WHEN F/A DID RESET THE UNIT IN FLIGHT. - [SDR CA151223003](https://openairdocs.org/sdr/CA151223003), Dec 21, 2015: TUBE. BROKEN. (CAN) ENGINE NR 2 THROTTLE JAMMED DUE TO A RUPTURE THRUST REVERSER AIR TUBE. THE SAME TUBE WAS INSTALLED ON SEPT 02, 2015 IN THE EXACT LOCATION FOR THE SAME REA - [SDR CA151203006](https://openairdocs.org/sdr/CA151203006), Nov 20, 2015: VALVE. FAILED. (CAN) ECAM YELLOW SYS LOW PRESSURE IN FLIGHT. 10 SECONDS AFTER, LOSS OF MOST OF THE YELLOW SYSTEM HYDRAULIC FLUID AND ASSOCIATED PITCH FEEL, SPOILER, YAW DAMPER - [SDR CA150930003](https://openairdocs.org/sdr/CA150930003), Sep 25, 2015: CDU. CRACKED. (CAN) CDU HOUSING CRACKED DURING TESTING OF THRUST REVERSER. OPERATED OK FOR 1 CYCLE AND THEN CRACKED AND SEPARATED ON CYCLE 2. - [SDR CA150426001](https://openairdocs.org/sdr/CA150426001), Apr 25, 2015: INDICATOR. OVERHEATED. (CAN) APPROXIMATELY 5 MINUTES AFTER FULL ACFT ELECTRICAL POWER WAS APPLIED, THE RUDDER TRIM INDICATOR BEGAN EMMITING SMOKE AND PRODUCED A HEAVY ELECTRICAL BURNI - [SDR CA140812009](https://openairdocs.org/sdr/CA140812009), Aug 10, 2014: BOLT. MISSING. (CAN) A/C HAD INFLIGHT TURNBACK LT MLG DOOR NOT CLOSING. MAINTENANCE FOUND LH MLG UPLOCK (FIN 321212) ROD ASSY (REF A310 IPC 32-36-44-02 ITEM 100) ADRIFT FROM R - [SDR CA140124007](https://openairdocs.org/sdr/CA140124007), Jan 23, 2014: FAIRING. RUPTURED. (CAN) DURING WALK AROUND INSPECTION, IT WAS FOUND THAT THE RT VERTICAL STABILIZER TO FUSELAGE FAIRING WAS DAMAGED, REFER IPC 53-19-69, ITEM 250. AFTER INSPECTIO - [SDR CA140124006](https://openairdocs.org/sdr/CA140124006), Jan 22, 2014: WIRE. SHORTED. (CAN) DURING FLIGHT LT INNER FUEL PUMP FAULT MESSAGE TRIGGERED. TROUBLESHOOTONG CARRIED OUT AND THE FOLLOWING FINDING WERE OBSERVED, GREEN HYD PUMP NR 2 WIRING - [SDR CA131219016](https://openairdocs.org/sdr/CA131219016), Dec 14, 2013: PIN. CRACKED. (CAN) PIN IS CRACKED. REPORTED TO MFG AND WAITING FOR MFG INSTRUCTIONS. - [SDR CA131213008](https://openairdocs.org/sdr/CA131213008), Dec 12, 2013: HINGE PIN. CRACKED. (CAN) DURING THE A-CHECK, WHILE PERFORMING LUBRICATION OF THE LT MLG, THE FWD ATTACHMENT PIN WAS FOUND WITH CRACKS AND A PORTION BROKEN OFF. THIS PIN IS PART OF - [SDR CA130826003](https://openairdocs.org/sdr/CA130826003), Aug 24, 2013: LINE. CRACKED. (CAN) DURING FLIGHT THE GREEN HYDRAULIC FLUID NOTICED TO BE DECREASING, FOLLOWED BY ECAM LOW LEVEL WARNING. LANDING MANUALLY EXTENDED FOR LANDING. ACFT HAD TO B - [SDR CA130822012](https://openairdocs.org/sdr/CA130822012), Aug 22, 2013: MANIFOLD. LEAKING. (CAN) O-RING FAILURE BETWEEN MANIFOLD ASSY FIN 291112, PN A2901150800000 AND BOSS FITTING MS21902-10. CAUSING ACFT TURN BACK DUE HYDRAULIC LOSS. IPC REF 24-24-0 - [SDR CA130610006](https://openairdocs.org/sdr/CA130610006), Jun 4, 2013: EEC. MALFUNCTIONED. (CAN) AT THE TOP OF DESCENT, UPON THRUST REDUCTION TO FLIGHT IDLE, BOTH THRUST LEVERS WENT TO IDLE BUT THE NR 2 ENGINE N1 STAYED AT 70 PERCENT N1. STARTING AROU - [SDR CA130417001](https://openairdocs.org/sdr/CA130417001), Apr 12, 2013: CDU. DAMAGED. (CAN) NR 1 ENGINE THRUST REVERSER FAULT ON LANDING. FOUND OTBD REVERSER SLEEVE NOT FULLY STOWED. THRUST REVERSER WAS DEACTIVATED IAW MEL. ON DEPARTURE, THE NR 1 - [SDR CA130318011](https://openairdocs.org/sdr/CA130318011), Mar 11, 2013: SKIN. CRACKED. (CAN) DURING VISUAL INSPECTION, FOUND AFT CARGO DOOR ACTUATOR FITTING AT FRAME 61A AND INNER SKIN CRACKED BETWEEN LONGERON 1 AND 1A. - [SDR CA130318014](https://openairdocs.org/sdr/CA130318014), Mar 11, 2013: BEARING. CORRODED. (CAN) DURING INSPECTION UNABLE TO OPEN RT OVERWING EMERGENCY EXIT DOOR, FROM THE INSIDE NOR FROM THE OUTSIDE. DOOR HAD TO BE PRYED UP IN ORDER TO OPEN. FOUND SL - [SDR CA130204003](https://openairdocs.org/sdr/CA130204003), Feb 2, 2013: ACTUATOR. FAILED. (CAN) ON APPROACH THE CREW OBSERVED AN UNSAFE INDICATION OF THE NOSE GEAR UPON SELECTING GEAR DOWN FOR LANDING. THE CREW DECLARED AN EMERGENCY AND FOLLOWED THE - [SDR CA121203005](https://openairdocs.org/sdr/CA121203005), Nov 30, 2012: CONTROL PANEL. OVERHEATED. (CAN) IN CRUISE AT FL 370, VHF 2 CONTROL PANEL GREEN LIGHT WAS INTERMITTENT, THEN BECAME EXTINGUISHED. CREW NOTICED AN ELECTRICAL SPARK FOLLOWED IMMEDIATELY BY - [SDR CA121127002](https://openairdocs.org/sdr/CA121127002), Nov 23, 2012: BOLT. WORN. (CAN) ON APPROACH, THE SLATS EXTENDED NORMALLY BUT NO FURTHER MOVEMENT OF THE FLAP LEVER WAS POSSIBLE AFTERWARDS. THE SLAT/FLAP LEVER WAS STUCK IN THE UP POSITI - [SDR CA120914010](https://openairdocs.org/sdr/CA120914010), Sep 10, 2012: DUCT. FRACTURED. (CAN) ACFT ARRIVED WITH 2 SNAGS RELATED TO AIR CONDITIONNING. CABIN TEMP HARD TO COOL DOWN AND LOW FLOW PLUS BOTH PACKS SURGING ON THE GROUND. REF W/O 1089584. - [SDR CA120224005](https://openairdocs.org/sdr/CA120224005), Feb 7, 2012: CONTROL PANEL. SMOKE. (CAN) FOUND SMOKE EMANATING FROM RUDDER AND AILERON TRIM CONTROL PANEL DURING COCKPIT PRE-DISPATCH CHECK. PART WAS REPLACED. - [SDR CA111026013](https://openairdocs.org/sdr/CA111026013), Oct 25, 2011: OVEN. BURNED. (CAN) FWD GALLEY NR 2 OVEN BURNING ODOR. MEL 25-20, CAT D RAISED BY KLM IN AMS. UPON INVESTIGATION, FOUND FAN SEIZED. REPLACED OVEN IAW AMM 25-34-00. OPS CHECKE - [SDR CA110719003](https://openairdocs.org/sdr/CA110719003), Jul 18, 2011: BEARING. SEIZED. ON CLIMB OUT, ON FLAP RETRACTION, CREW RECEIVED A FLAP SYS 1 & 2 FAULT WITH FLAP JAM MESSAGE. ACFT RETURNED TO DEPARTURE AIRPORT AND LANDING WAS UNEVENTFUL. INV - [SDR CA101223007](https://openairdocs.org/sdr/CA101223007), Dec 21, 2010: SEAL. LEAKING. (CAN) ON DEPARTURE OUT DURING CLIMB AFTER SLECTING FLAPS UP ECAM WARNING "BLUE SYSTEM, LOW QTY" ACCOMPANIED BY "BLUE SYSTEM, LOW AIR PRESSURE". CREW FOLLOWED QR - [SDR 2011F00121](https://openairdocs.org/sdr/2011F00121), Mar 6, 2010: BLADE. BROKEN. HPT STAGE 1 BLADE FOUND BROKEN AND MISSING DURING ROUTINE BSI, ON FOLLOWING CF6-80C2A8 ENGINES SN 659611, 659399, 659526, 659392, 659408, 659612, 659414. SECOND - [SDR CA091203003](https://openairdocs.org/sdr/CA091203003), Dec 2, 2009: DUCT. CRACKED. (CAN) PIREP DEFECT 1037394 - FUEL MIGRATING FROM LT INNER TANK TO CTR TANK. MX FOUND THE APU BOOST PUMP CANNISTER DELIVERY DUCT CRACKED. REPLACED PER MM 49-32-1 ## 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.