# GE CF6-80A3 - Type: Engine model (FAA registry) - Registry code: 30096 - Manufacturer (registry): GE - Model: CF6-80A3 - Engine type: Turbo-fan - Power: 48,970 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-cf6-80a3 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 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 2018-07-05](https://openairdocs.org/ad/2018-07-05): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 11, 2018 - [AD 2011-23-04](https://openairdocs.org/ad/2011-23-04): Forward engine mount assembly side links · General Electric CF6-45A, CF6-45A2, CF6-50A and 14 more. Effective Dec 12, 2011 - [AD 2009-08-06](https://openairdocs.org/ad/2009-08-06): Stage 1 high-pressure turbine (HPT) rotor disks · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 18, 2009 - [AD 2009-07-10](https://openairdocs.org/ad/2009-07-10): High-pressure turbine rotor (HPTR) · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 6, 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 2008-02-17](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 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 2005-06-07](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 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 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 2001-06-09](https://openairdocs.org/ad/2001-06-09): Aft Engine Mount Link Assemblies · General Electric CF6-80A3. Effective May 1, 2001 - [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 95-17-16](https://openairdocs.org/ad/95-17-16): Compressor Rear Frame · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective Nov 7, 1995 - [AD 94-07-04](https://openairdocs.org/ad/94-07-04): High Pressure Turbine Disk · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 23, 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 92-04-08](https://openairdocs.org/ad/92-04-08): Stage 1 Disk/Shafts · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective Mar 27, 1992 - [AD 91-23-13](https://openairdocs.org/ad/91-23-13): Fan Disks · General Electric CF6-50A, CF6-50C, CF6-50C1 and 12 more. Effective Nov 22, 1991 - [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 91-01-04](https://openairdocs.org/ad/91-01-04): Fan Disk · General Electric CF6-45A, CF6-45A2, CF6-50A and 19 more. Effective Jan 22, 1991 - [AD 90-23-05](https://openairdocs.org/ad/90-23-05): Engine Aft Mount, · General Electric CF6-80A3. Effective Dec 3, 1990 - [AD 89-16-08](https://openairdocs.org/ad/89-16-08): Manifold · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective Aug 31, 1989 - [AD 86-15-04](https://openairdocs.org/ad/86-15-04): Stage 1 High Pressure Turbine (HPT) Disks · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective Jul 23, 1986 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 2006-12-24](https://openairdocs.org/ad/2006-12-24) (historical): Five-link forward mount assembly · General Electric CF6-45A, CF6-45A2, CF6-50A and 14 more. Effective Jul 21, 2006 - [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 2003-01-05](https://openairdocs.org/ad/2003-01-05) (historical): Dovetail slots · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective Jan 28, 2003 - [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 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 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 98-15-17](https://openairdocs.org/ad/98-15-17) (historical): Link Assembly · General Electric CF6-80A3. Effective Aug 7, 1998 ## Information bulletins (advisory) (2) - [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 ## 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 (161, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR ABXA202109139090](https://openairdocs.org/sdr/ABXA202109139090), Sep 9, 2021: CABLE. BINDING. ON TAXI OUT, R ENG STARTED SURGE +/- 2% N2, +/- 100 FF, +/- 40 EGT, +/- 1% N1. AIRCRAFT BACK TO BLOCK AND GROUNDED BY MAINTENANCE. MAINTENANCE FOUND R/H ENG VSV - [SDR FDEA201310072434](https://openairdocs.org/sdr/FDEA201310072434), Oct 7, 2013: ENGINE. FAILED. DURING CLIMBOUT, NR 1 ENGINE OVERTEMPED. HEARD A LOUD POP WITH A YAW TO THE LEFT. ALL ENG INDICATIONS WERE NORMAL EXCEPT EGT WHICH WAS 700 DEGREES HIGHER THEN N - [SDR FDEA201308101829](https://openairdocs.org/sdr/FDEA201308101829), Aug 10, 2013: ENGINE. FAILED. DURING CLIMB ENG NR 1 OIL LOW QTY ADVISORY CAME ON, SHOWED 2 QUARTS. ALL OTHER INDICATIONS NORMAL. IAW QRH, MONITORED QTY. ABOUT 15 MINUTES LATER, DECIDED TO DI - [SDR FDEA201209013204](https://openairdocs.org/sdr/FDEA201209013204), Sep 1, 2012: OUTFLOW VALVE. INOPERATIVE. RT NR 1 PRESSURE REGULATOR FAULT DURING CLIMB, FWD NR 1 OUTFLOW VALVE STUCK FULL OPEN. QRH NO HELP. CABIN WOULD NOT PRESSURIZE. TROUBLESHOT TO NR 1 FWD OUTFLOW - [SDR FDEA201208243148](https://openairdocs.org/sdr/FDEA201208243148), Aug 24, 2012: STRUCTURE. DAMAGED. LT WING NR 6 SPOILER HAS HOLE APPROX .25W X .56L X .25D. LOCATED 12.125" FROM OTBD EDGE AND 21" FROM T/E OF SPOILER REPAIRED ONE HOLE MEASURING .25W X .56L X .2 - [SDR FDEA201208233141](https://openairdocs.org/sdr/FDEA201208233141), Aug 23, 2012: CONTROLLER. FAILED. SLATS FAILED TO EXTEND ON APPROACH. CHECKED NR 1 AND NR 2 SFCCS. NR 1 SFCC FAULTS JAM, NR 2 SFCC FAULTS LT RETRACT SWITCH. ADDED MPN 49-079-05 QTY 2 EA CG, SFCC - [SDR FDEA201208233144](https://openairdocs.org/sdr/FDEA201208233144), Aug 23, 2012: FILTER. CLOGGED. REJECTED TAKEOFF AT 70 KTS FOR NR 2 ENGINE FUEL FILTER CLOG ALERT ON ECAM. REPLACED NR 2 ENGINE MAIN FUEL FILTER IAW MM 73-12-03-02 IDLE LEAK CHECKED GOOD. RAN - [SDR FDEA201208032826](https://openairdocs.org/sdr/FDEA201208032826), Aug 3, 2012: CONTROLLER. FAULTED. PASSING THROUGH 10,000 FT, RECEIVED CABIN ALT ALERT. DESCENDED TO 10,000. ACFT WOULD NOT PRESSURIZE IN AUTO WITH REGULATORS NR 1, NR 2 OR IN MANUAL POSITION. AL - [SDR FDEA201207152579](https://openairdocs.org/sdr/FDEA201207152579), Jul 15, 2012: SKIN. CRACKED. LT WING FIXED L/E INBD CUT OUT FOR SHUTTER DOOR NR 1 TOP EXTERNAL SKIN CRACKED 1.25" APPROXIMATELY. REPAIRED SKIN IAW SRM 51-40-21 DWGS A57246236, A57246240 AND - [SDR FDEA201207152580](https://openairdocs.org/sdr/FDEA201207152580), Jul 15, 2012: SKIN. DAMAGED. DURING INSPECTION OF CIRCUMFERENTIAL SKIN JOINT AT FR 54 BETWEEN STGR 45 LT AND STGR 44 LT FASTENER HOLE 1EA WITH PRIOR BUSHING REPAIR IS ELONGATED. WORK IN CON - [SDR FDEA201207032460](https://openairdocs.org/sdr/FDEA201207032460), Jul 3, 2012: FLOORBEAM. FAILED. MAIN CABIN FLOORBEAM MISREPAIRED. REPAIRED IAW EA 6-5310-161396 COMPLING WITH PART 2 OF EA AND RDAS REF 70563824/003/2012 ISSUE A. REPAIR CLASSIFIED AS MAJOR IA - [SDR FDEA201206192267](https://openairdocs.org/sdr/FDEA201206192267), Jun 19, 2012: SEAT TRACK. DAMAGED. FLOOR SEAT TRACK 2R HAS 5 EA ELONGATED HOLES FROM FRAME 54 TO 54.2 AT RT FLANGE. R & R SEAT TRACK 2R BETWEEN FRAMES 54 AND 54.2 IAW SRM 51-72-10. - [SDR FDEA201206192268](https://openairdocs.org/sdr/FDEA201206192268), Jun 19, 2012: SEAT TRACK. DAMAGED. FLOOR CLEVIS ADAPTER BETWEEN SEAT TRACK 2R AND 3R INSTALLED NOT ALIGN AND HAS 2 EA ELONGATED FASTENER HOLES. R & R DUMMY TRACK IAW SRM 51-72-10. - [SDR FDEA201108083139](https://openairdocs.org/sdr/FDEA201108083139), Aug 8, 2011: ACCESS DOOR. CRACKED. APU RT ACCESS DOOR 316AR AFT MATING FLANGE ON TAILCONE ASSY DEFORMED BELOW LATCH RECEPTACLE, MEASURED 4 IN LENGTH. REMOVED MATING FLANGE IAW SRM 51-40-21. INSTA - [SDR FDEA201108053112](https://openairdocs.org/sdr/FDEA201108053112), Aug 5, 2011: SUPPORT BRACKET. CRACKED. NR1 ENGINE THRUST REVERSER TRANSLATING COWL UPPER GUIDE SUPPORT SLIDER BRACKET CRACKED. REMOVED NR 1 ENG O/B TRANSLATING SLEEVE IAW A310-200 AMM 78-32-11-04. RE - [SDR FDEA201107162734](https://openairdocs.org/sdr/FDEA201107162734), Jul 16, 2011: SKIN. MISREPAIRED. REPAIR FOUND AT LT WING T/E FLAP LOWER SURFACE OTBD AREA RIB 9 & RIB 10. FOUND PREVIOUSLY NOT REPAIRED IAW ANY APPROVED DATA. NEW REPAIR ACCOMPLISHED IAW SRM 57 - [SDR FDEA201105251980](https://openairdocs.org/sdr/FDEA201105251980), May 25, 2011: DUCT. CHAFED. ENG 2, LT T/R COWL INNER DUCT AFT EDGE GOT CHAFING ATTACH TO CORE COWL AREA UPPER SIDE. - [SDR FDEA201012044572](https://openairdocs.org/sdr/FDEA201012044572), Dec 4, 2010: FLOOR SUPPORT. CORRODED. FLOOR SUPPORT STRUCTURE Y-770, FROM FR14 TO FR 10 IS CORRODED ON THE TOP SIDE OF THE BEAM. R & R FLOOR SUPPORT Y-770, BETWEEN FR 10 AND FR 14 IAW A310-200 SRM 5 - [SDR FDEA201012044573](https://openairdocs.org/sdr/FDEA201012044573), Dec 4, 2010: DUMMY RAIL. WORN. DUMMY TRACK 4L, FR54.2 EXCEEDED THE ALLOWABLE WEAR LIMITS. REPAIR DUMMY TRACK 4L AT FR54.2 IAW EO 5310-7-3322 PT2 INSTRUCTIONS. - [SDR FDEA201012044574](https://openairdocs.org/sdr/FDEA201012044574), Dec 4, 2010: STIFFENER. CORRODED. LAV SERVICE BOX AND SKIN STIFFENER HAS EXCESSIVE CORROSION EXTENDING ON FR 12 STR 37L. REMOVED CORROSION FROM SKIN STIFFENER FOUND TO BE OUT OF LIMITS IAW SRM 5 - [SDR FDEA201012044575](https://openairdocs.org/sdr/FDEA201012044575), Dec 4, 2010: CROSSBEAM. CORRODED. REAR FUSELAGE FR 86, 5" INCHES INBD OF STR 15L, AFT CROSSBEAM HAS 2 EA PLACES OF EXFOLIATION CORROSION, APPR 2" INCHES SQUARE. R & R CROSSBEAM AT FR 86, STR 15L - [SDR FDEA201012034559](https://openairdocs.org/sdr/FDEA201012034559), Dec 3, 2010: CROSSBEAM. CORRODED. 2EA PLACES OF CORROSION FOUND ON AFT CROSSBEAM IN REAR FUSELAGE FRAME 85, 5" INCHES INBD OF STRINGER 13R (2" SQUARE INCHES). R & R CROSSBEAM AT FRAME 85, STRING - [SDR FDEA201012034561](https://openairdocs.org/sdr/FDEA201012034561), Dec 3, 2010: FLOOR SUPPORT. CORRODED. MAIN DECK FLOOR SUPPORT STRUCTURE Y1456, TOPSIDE IS CORRODED FROM FR 14 TO FR 12A. REMOVED AND REPLACED FLOOR SUPPORT, Y 1456, FROM FR 11 TO FR 15A IAW SRM 51-7 - [SDR FDEA201012034571](https://openairdocs.org/sdr/FDEA201012034571), Dec 3, 2010: SEAT TRACK. CORRODED. MAIN CARGO DECK, R/T SEAT TRACK 5R, FROM FR 14 TO FR 18 HAS EXFOLIATED CORROSION. REMOVED AND REPLACED SEAT TRACK 5R, Y-1959, FROM FR 14 TO FR 18 IAW SRM 51-72 - [SDR FDEA201011044247](https://openairdocs.org/sdr/FDEA201011044247), Nov 4, 2010: CONTROLLER. FAILED. CLIMBING THROUGH 10,500 FT THE EXCESS CAB ALT WARNING OCCURED. LEVELED OFF AT 11,000 FT. EXECUTED THE QRH EXCESS CAB ALT WARNING CHECKLIST, CAB PRESS MANUEL CON - [SDR FDEA201011034246](https://openairdocs.org/sdr/FDEA201011034246), Nov 3, 2010: SWITCH. FAILED. ON DEPARTURE RECEIVED LANDING GEAR RETRACTION FAULT. DOWN AND LOCKED "GREEN" LIGHTS NEVER WENT OUT. FOUND ACFT IN SYS 2 ON ARRIVAL. TALKED TO CAPTAIN OF INBD FL - [SDR FDEA201010073975](https://openairdocs.org/sdr/FDEA201010073975), Oct 7, 2010: BRAKE. SMOKE. AFTER LANDING, TOWER REPORTED SMOKE COMING FROM RT MAIN GEAR. TAXIED CLEAR, STOPPED AND HAD FIRE DEPT CHECK ORIGIN. THEY REPORTED FLUID DRIPPING ONTO GEAR. SHUT - [SDR FDEA201010063957](https://openairdocs.org/sdr/FDEA201010063957), Oct 6, 2010: FLOORBEAM. CRACKED. FOUND A CRACK FLOOR SUPPORT AT FRAME 54.2 ON RT SIDE BETWEEN SEAT TRACKS 2R AND 3R, CRACK IS (.25") LONG. REMOVED DAMAGE AREA AT FRAME 54.2 ON RT FLOOR SUPPORT - [SDR FDEA201010013845](https://openairdocs.org/sdr/FDEA201010013845), Oct 1, 2010: ENGINE. LEAKING. DURING CLIMB OUT NOTICED OIL QTY NR 1 ENGINE WAS AT 4 QTS. REDUCED POWER TO 60 PERCENT N1, QTY CONTINUED TO DROP TO 0 QTS OVER NEXT 10 MINUTES. PRESSURE GOOD FO - [SDR FDEA201009303801](https://openairdocs.org/sdr/FDEA201009303801), Sep 30, 2010: FITTING. CORRODED. 134AR ACCESS DOOR SURROUNDING INTEGRAL FITTING FOUND CORROSION (FR23- 24, STGR49R-STGR54L) REMOVE CORROSION IAW SRM 51-74-10. MEASURE THE REMAINING THICKNESS IA - [SDR FDEA201009303802](https://openairdocs.org/sdr/FDEA201009303802), Sep 30, 2010: FITTING. CORRODED. LT WING RIB 5 MLG FWD LUG CORROSION EXCEED LIMIT COMPLIED WITH EA 6-5710-141613. - [SDR FDEA201009303803](https://openairdocs.org/sdr/FDEA201009303803), Sep 30, 2010: SKIN. CORRODED. FWD CARGO - FUSELAGE SKIN INTERIOR SURFACE FOUND CORROSION BETWEEN FR38 12" TO FR38.1 , STGR50R-54L REMOVED CORROSION IAW SRM 51-74-10. REMAINING THICKNESS IS 0 - [SDR FDEA201009293796](https://openairdocs.org/sdr/FDEA201009293796), Sep 29, 2010: BRACKET. CORRODED. 2 EA REINFORCE BRACKETS FOUND CORROSION AT FR12A , STGR 40L-44L. REMOVED CORROSION IAW SRM 51-74-10. REMAINING THICKNESS IS 0.045" IAW NTM 51-10-04. NO CRACK FO - [SDR FDEA201009293798](https://openairdocs.org/sdr/FDEA201009293798), Sep 29, 2010: FITTING. CORRODED. 136 AR ACCESS DOOR SURROUNDING INTEGRAL FITTING FOUND CORROSION (FR38.1- FR38.2, STGR49R-STGR54L) REMOVE CORROSION IAW SRM51-74-10. MEASURE THE REMAINING THICKN - [SDR FDEA201009273728](https://openairdocs.org/sdr/FDEA201009273728), Sep 27, 2010: FRAME. GOUGED. GOUGE FOUND ON FR54.1 FRAME BETWEEN STGR13L-14L 1.CUT OUT THE DAMAGED SECTION OF FRAME 54.1 BETWEEN STGR13L-15L AND MAKE THE REPAIR PART IAW SRM53-10-13-201, PA - [SDR FDEA201009273729](https://openairdocs.org/sdr/FDEA201009273729), Sep 27, 2010: FRAME. DAMAGED. 2 DISTORTIONS FOUND ON FR54.2 FRAME BETWEEN STGR13L-15L 1.CUT OUT THE DAMAGED SECTION OF FRAME 54.1 BETWEEN STGR13L-15L AND MAKE THE REPAIR PART IAW SRM53-10-13 - [SDR FDEA201009273730](https://openairdocs.org/sdr/FDEA201009273730), Sep 27, 2010: BEAM. CRACKED. LT AFT CREW DOOR FRAME FR73A TO FR75A, STRINGER 11 LONGITUDINAL BEAM NDT FOUND CRACK INDICATION FROM 5 FASTENER HOLES. REMOVE THE COVER PLATE AND DOOR FRAME BEA - [SDR FDEA201009263727](https://openairdocs.org/sdr/FDEA201009263727), Sep 26, 2010: SEAT TRACK. DAMAGED. MAIN CABIN AT FRAME 52 RT SEAT TRACK 4 HAS A MISDRILLED HOLE THAT GOES THROUGH FITTING. REPAIRED SEAT TRACK 4R USING SPLICED REPAIR IAW SRM 53-10-16. - [SDR FDEA201009213591](https://openairdocs.org/sdr/FDEA201009213591), Sep 21, 2010: SKIN. CORRODED. FWD CARGO COMPT. - 134AR ACCESS DOOR SURROUNDING CUTOUT SKIN INTERIOR SURFACE FOUND CORROSION (FR23-FR24, STGR49R-52R) REMOVED CORROSION IAW SRM 51-74-10 REMAIN - [SDR FDEA201009203549](https://openairdocs.org/sdr/FDEA201009203549), Sep 20, 2010: FRAME. CORRODED. AVIONICS COMPT - FR12A, S45-44L FRAME LOWER FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.112" IAW NTM 51-10-04 NO CRAC - [SDR FDEA201009203551](https://openairdocs.org/sdr/FDEA201009203551), Sep 20, 2010: FRAME. CORRODED. AVIONICS COMPT - FRAME 13, STINGER 44L-45L FRAME LOWER FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.048" IAW NTM 51-10 - [SDR FDEA201009203553](https://openairdocs.org/sdr/FDEA201009203553), Sep 20, 2010: FRAME. CORRODED. AVIONICS COMPT - FRAME 13A, STRINGER 45L-44L, FRAME LWR FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.107" IAW NTM 51-1 - [SDR FDEA201009203556](https://openairdocs.org/sdr/FDEA201009203556), Sep 20, 2010: FRAME. CORRODED. AVIONICS COMPT - FRAME 15A STRINGER 45L-44L FRAME LWR FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.107" IAW NTM 51-10- - [SDR FDEA201009203557](https://openairdocs.org/sdr/FDEA201009203557), Sep 20, 2010: FRAME. CORRODED. AVIONICS COMPT - FRAME 16, STRINGER 45L-44L FRAME LWR FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10, REMAINING THINKNESS IS 0.085" IAW NTM 51-10- - [SDR FDEA201009203558](https://openairdocs.org/sdr/FDEA201009203558), Sep 20, 2010: FRAME. CORRODED. AVIONICS COMPT - FRAME 16A, STRINGER 45L-44L FRAME LWR FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10 REMAINING THINKNESS IS 0.089" IAW NTM 51-10- - [SDR FDEA201009203590](https://openairdocs.org/sdr/FDEA201009203590), Sep 20, 2010: FRAME. CORRODED. FWD CARGO COMPT. - FRAME WEB FOUND CORROSION AT STR49R-50R , FR37 BLENDED OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.055" IAW NTM 51-10-04 NO CRAC - [SDR FDEA201009193542](https://openairdocs.org/sdr/FDEA201009193542), Sep 19, 2010: FRAME. CORRODED. AVIONICS COMPT- FRAME 14A, STRINGER 42L-44L FRAME BOTTOM FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.048" IAW NTM 51- - [SDR FDEA201009173534](https://openairdocs.org/sdr/FDEA201009173534), Sep 17, 2010: SKIN. DAMAGED. LEFT WING OTBD FLAP LOWER SKIN DISBONDED 7.5 IN LENGTH X 1.5 IN WIDE AT T/E,48 IN INBD FROM OTBD EDGE. REPAIRED LT WING T/E SKIN IAW EA 6-5750-135278 - WINGS - - [SDR FDEA201009153423](https://openairdocs.org/sdr/FDEA201009153423), Sep 15, 2010: FRAME. FAILED. PREVIOUS FRAME REPAIR LOCATED IN BULK CARGO COMPARTMENT UNDEFLOOR ON FRAME 67 BETWEEN STRINGERS 43 TO 46 RT HAS A REPAIR AGLE ON AFT SIDE OUTER FLANGE MEASURING - [SDR FDEA201009153424](https://openairdocs.org/sdr/FDEA201009153424), Sep 15, 2010: SKIN. MISREPAIRED. PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LT WING INBD FLAP UPPER SKIN AT RIB 10 TO 11 AND BETWEEEN THE REAR SPAR AND AUXILIARY SPAR ON STRINGERS 6 AND 7 MEAS All 161: https://openairdocs.org/engine/ge-cf6-80a3/reports.md ## STCs that may be installed (OpenAirDocs) (3) 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 SE00969CH](https://openairdocs.org/stc/SE00969CH): Install AeroControlex P/N 2605290-001 variable stator feedback control cable. AeroControlex Group TransDigm 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.