# GE CF6-80C2A2

- Type: Engine model (FAA registry)
- Registry code: 30098
- Manufacturer (registry): GE
- Model: CF6-80C2A2
- Engine type: Turbo-fan
- Power: 52,460 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-cf6-80c2a2

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
- [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

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 (26)

As reported by operators and repair stations, by the model named in the report.

- [SDR CA190708004](https://openairdocs.org/sdr/CA190708004), Jul 7, 2019: O-RING. FAILED. (CAN) PILOT CALLED OVER PHONE PATCH TO REPORT THAT THEY GOT THE ECAM MESSAGE FOR GREEN SYSTEM HYDRAULIC LOW LEVEL. THEY HAVE PERFORMED THE ECAM AND QRH, SO THE 
- [SDR CA190403011](https://openairdocs.org/sdr/CA190403011), Apr 2, 2019: ENGINE. STALLED. (CAN) AFTER TAKE OFF ENGINE #1 ENCOUNTERED AN ENGINE STALL AT INITIAL CLIMB PASSING 1500FT, THE CREW REPORTS THAT THEY HEARD A COUPLE OF `THUMPS`, AND THEN NOTI
- [SDR CA180925007](https://openairdocs.org/sdr/CA180925007), Sep 21, 2018: FITTING. CORRODED. (CAN) STRONG WHISTLE SOUND FROM RL DOOR IN CRUISE. AFTER INVESTIGATION INSIDE OF DOOR,FITTING FOUND CORRODED. FITTING REPLACED. (TC# 20180925007)
- [SDR CA180910001](https://openairdocs.org/sdr/CA180910001), Sep 7, 2018: PUMP. LEAKING. (CAN) CREW REPORTED DURING FLIGHT: `GREEN HYD QTY SHOW LOW QTY ON THE NEEDLE GAGE QTY ON ECAM IS STEADY` LATER REPORT: `HYD LOW QTY WARNING ON ECAM1 LANDING GEA
- [SDR CA180423016](https://openairdocs.org/sdr/CA180423016), Apr 21, 2018: COMPUTER. FALSE INDICATION. (CAN) DURING TAKEOOF ROLL AT 80KTS ECAM ENG INDICATION REJECTED TAKEOFF AT FULL STOP ECAM FWC AMBER CRT CAUTIONS NOT AVAIL. FWC 1 REPLACED AND CHECKED SERV, IAW
- [SDR CA160223002](https://openairdocs.org/sdr/CA160223002), Feb 22, 2016: STRUT. FAULTY. (CAN) ESTABLISHED ON FINAL FOR LANDING THE CREW SELECTED GEAR DOWN, THEY DID NOT GET A GREEN LIGHT FOR THE NOSE GEAR FROM EITHER SYS, RED LIGHTS ONLY FOR THE NO
- [SDR CA151013012](https://openairdocs.org/sdr/CA151013012), Oct 13, 2015: VALVE. FAILED. (CAN) DURING PUSHBACK OF ACFT FOR DEPARTURE, THE CREW TRIED TO SET THE PARKING BRAKE. THEY WERE UNSUCCESSFULL AND A LEAK WAS NOTED IN THE MAIN WHEEL WELL AREA. 
- [SDR CA151007011](https://openairdocs.org/sdr/CA151007011), Oct 1, 2015: ATTACH FITTING. BROKEN. (CAN) LEFT WING NR 3 SPOILER BROKEN AT ACTUATOR ATTACHMENT. SPOILER WAS FREE TO MOVE EXTEND/RETRACT DURING FLIGHT.
- [SDR CA150810001](https://openairdocs.org/sdr/CA150810001), Aug 7, 2015: PUMP. CRACKED. (CAN) CREW REPORTED HYDRAULIC FLUID ON BLUE SYS LOW LEVEL ECAM WARNING AND FAULT IN CRUISE. CREW DECLARED A PAN PAN, QRH PROCEDURE CARRIED AND ACFT DIVERTED. AC
- [SDR CA140919007](https://openairdocs.org/sdr/CA140919007), Sep 16, 2014: BATTERY. DAMAGED. (CAN) DURING ROUTINE VISIT IN AVIONIC SHOP FOR REGULAR BATTERY CHECK, THE CASE OF EPSU BATTERY WAS FOUND WITH A SMALL BURN. THE ASSY WAS OPENED AND CELLS NR 4 A
- [SDR CA140903013](https://openairdocs.org/sdr/CA140903013), Sep 3, 2014: COFFEEMAKER. ODOR. (CAN) CREW REPORTED FWD COFFEE MAKER BURNING ODOR IN FLIGHT. CIRCUIT BREAKER WAS PULLED AND ODOR DISSIPATED.
- [SDR CA130531004](https://openairdocs.org/sdr/CA130531004), May 26, 2013: SWITCH. SHORTED. (CAN) DURING TROUBLESHOOTING OF UPPER BEACON SYSTEM C/B POPPING. C/B WAS PUSHED IN AND A NOISE WAS HEARD & SPARK CAME OUT FROM PANEL 426VU. FOUND TOGGLE SWITCH 
- [SDR CA120827017](https://openairdocs.org/sdr/CA120827017), Aug 25, 2012: CONTROL PANEL. OVERHEATED. (CAN) DURING CRUISE FLIGHT, FLIGHT CREW REPORTED SMOKE COMING OUT OF ADF NR 2 CONTROL PANEL. ADF2 CIRCUIT BREAKER WAS PULLED BUT SMOKE CONTINUED TO COME OUT OF 
- [SDR CA120504003](https://openairdocs.org/sdr/CA120504003), Apr 25, 2012: BULKHEAD. CORRODED. (CAN) FOUND BULKHEAD AT FRAME 39, CORRODED AND PERFORATED BETWEEN STRINGERS 54-55L AND BELOW WATERLINE Z-2557.
- [SDR CA120330005](https://openairdocs.org/sdr/CA120330005), Mar 27, 2012: TANK. RUPTURED. (CAN) ACFT RETURNED TO BLOCK AFTER A LOUD BANG HEARD IN CLIMB FOLLOWED BY WATER QTY AND PRESSURE INDICATE ZERO ON FAP PANEL. ON ARRIVAL, FOUND WATER TANK RUPTUR
- [SDR CA120224006](https://openairdocs.org/sdr/CA120224006), Feb 19, 2012: ACTUATOR. CRACKED. (CAN) CLOSE TO 90KTS, ECAM MESSAGE "SPEED BRAKE WARNING", ENGINE SETTING WAS 96 PERCENT N1, REJECTED TAKEOFF CALLED, AFTER A FEW SECONDS, A SECOND ECAM MESSAGE 
- [SDR CA111116008](https://openairdocs.org/sdr/CA111116008), Nov 12, 2011: MEC. FAILED. (CAN) AFTER NORMAL ENGINE NR 2 START, NO THROTTLE RESPONSE N1 15 PERCENT, TGT 660 DEGREES, N2 60 PERCENT, FF 0.05. NR 2 ENGINE, MAIN ENGINE CONTROL (MEC) REPLAC
- [SDR CA110513007](https://openairdocs.org/sdr/CA110513007), May 9, 2011: BUSHING. SEIZED. WHEN PERFORMING TASK 292500-16-1 (OPS CHECK OF RAT UPLOCK MECHANISM) DURING A-06 CHECK, RAM AIR TURBINE (RAT) FAILED TO DEPLOY FROM EITHER THE CAPTAINS` AND FIR
- [SDR CA110420006](https://openairdocs.org/sdr/CA110420006), Apr 10, 2011: COVER. MISSING. (CAN) UPON ARRIVAL AT DESTINATION AIRPORT IT WAS DISCOVERED THAT THE FWD CARGO DOOR FWD LOCKS COVER WAS MISSING, PANEL 811AR. SUSPECT THAT IT WAS STRUCK DURING 
- [SDR CA110408004](https://openairdocs.org/sdr/CA110408004), Mar 22, 2011: WIRE. DAMAGED. (CAN) LEFT OUTER TANK BOOST PUMP 1 & 2 INDICATE LOW PRESS & LT INNER TANK BOOST PUMP NR 2 INDICATES LOW PRESS. FOUND WIRING DAMAGED IN LT WW JUST ON TOP OF GREE
- [SDR CA110203007](https://openairdocs.org/sdr/CA110203007), Jan 19, 2011: PANEL. DELAMINATED. (CAN) MCC CONTACTED AIRPORT AUTHORITIES REGARDING PIECE OF ALUMINUM FOUND ON THE RUNWAY POSSIBLY FROM A/C OR ANOTHER A/C THAT DEPARTED SINCE THE LAST FOD INSPEC
- [SDR CA101223006](https://openairdocs.org/sdr/CA101223006), Dec 10, 2010: ROD END. SEPARATED. (CAN) DURING OVERNIGHT ROUTINE MAINTENANCE AND TROUBLESHOOTING AN OPEN MEL ITEM FOR NR 2 & 3 SPOILER FAULT THAT WAS PLACED ON MEL (SYSTEM DEACTIVATED) PRIOR TO 
- [SDR CA101026002](https://openairdocs.org/sdr/CA101026002), Oct 25, 2010: DUCT. DAMAGED. DURING WALK AROUND, LEAK SOUND FROM NR 2 ENG - FOUND DUCT BESIDE PRSOV CRACKED. DUCT BLEED ELBOW CRACKED. DUCT HAS BEEN REPLACED.
- [SDR CA100917003](https://openairdocs.org/sdr/CA100917003), Sep 13, 2010: TUBE. CHAFED. FUEL VBV ACTUATOR TUBE AND HOSE FOUND CHAFING - PN 113254-3 (IPC 72-00-00, FIG 4, ITEM 80) ON VBV FEEDBACK CABLE. THIS CHAFING CAUSED A FUEL LEAK THAT WAS FOUND
- [SDR CA100630004](https://openairdocs.org/sdr/CA100630004), Jun 22, 2010: HOOK. WORN. DURING PERFORMANCE OF MPD TASK 292500-05-1, (GENERAL INSP OF CONTROL LINKAGE FOR CORROSION AND DAMAGE), RAT FAILED TO DEPLOY FROM BOTH THE CAPT`S OR F/O`S RELEA
- [SDR CA091109004](https://openairdocs.org/sdr/CA091109004), Nov 3, 2009: GENERATOR. CRACKED. (CAN) ON CHECKING APU OIL QUANTITY, MX FOUND THE APU COMPARTMENT OIL SOAKED. HSG OF THE APU GENERATOR WAS FOUND CRACKED AND LEAKING. UNIT HAS BEEN REPLACED.

## 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

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