# Service difficulty reports: GE CF6-80A3

A list on [GE CF6-80A3](https://openairdocs.org/engine/ge-cf6-80a3.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 4 · 161 reports

- [SDR ABXA202109139090](https://openairdocs.org/sdr/ABXA202109139090.md): Cable · binding · Sep 9, 2021 · N768AX · Boeing 767281 · Engine Fuel Indicating System
  > 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 FEEDBACK CABLE TO HAVE HIGH PULL FORCE.R&R RH ENG VSV FEEDBACK CABLE IAW AMM 75-31-03. AIRCRAFT RET
- [SDR FDEA201310072434](https://openairdocs.org/sdr/FDEA201310072434.md): Engine · failed · Oct 7, 2013 · N426FE · Airbus A310203 · Engine (Turbine/Turboprop)
  > 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 NR 2 EGT, NR 1 EGT STAYED BEWTEEN 600 TO 700 DEGREES. DURING RETURN, MAX EGT 1000 FT. REMOVED AND
- [SDR FDEA201308101829](https://openairdocs.org/sdr/FDEA201308101829.md): Engine · failed · Aug 10, 2013 · N428FE · Airbus A310203 · Turbine Engine Oil System
  > 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 DIVERT WITH POSSIBLE OIL PRESSURE FLUCTUATION. DID NOT SHUT NR 1 DOWN, PRESSURE STAYED ABOVE 40 P
- [SDR FDEA201209013204](https://openairdocs.org/sdr/FDEA201209013204.md): Outflow Valve · inoperative · Sep 1, 2012 · N410FE · Airbus A310203 · Pressure Regulator/Outflow Valve
  > 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 VALVE STUCK OPEN. REPLACED OUTFLOW VALVE IAW AMM CH 21-31-12-04-01. OPS CKS GOOD. ACFT OK FOR
- [SDR FDEA201208243148](https://openairdocs.org/sdr/FDEA201208243148.md): Structure · damaged · Aug 24, 2012 · N428FE · Airbus A310203 · Spoilers
  > 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.25D ON NR 6 SPOILER USING RESIN & CARBON FIBER IAW SRM 57-76-11, PAR 12C. COMPLIED WITH EA 6-5750-1
- [SDR FDEA201208233141](https://openairdocs.org/sdr/FDEA201208233141.md): Controller · failed · Aug 23, 2012 · N443FE · Airbus A310203 · Leading Edge Slat Control System
  > 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, SFCC1 - SLATS JAM - SEE TSM 27-80-02 (FIRST TIME OCCURANCE) THIS CHECKS DRIVE LINE AND COMPONENT
- [SDR FDEA201208233144](https://openairdocs.org/sdr/FDEA201208233144.md): Filter · clogged · Aug 23, 2012 · N403FE · Airbus A310203 · Engine Fuel Distribution
  > 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 NR 2 ENGINE AT TAKE OFF POWER IAW JRH. NO ECAM MESSAGES NOTED OK TO CONTINUE.
- [SDR FDEA201208032826](https://openairdocs.org/sdr/FDEA201208032826.md): Controller · faulted · Aug 3, 2012 · N410FE · Airbus A310203 · Cabin Pressure Controller
  > 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. ALL DOORS & OUTFLOW VALVES INDICATED, SHOWED CLOSED. FOUND NR 2 CABIN PRESSURE CONTROLLER FAULTING
- [SDR FDEA201207152579](https://openairdocs.org/sdr/FDEA201207152579.md): Skin · cracked · Jul 15, 2012 · N429FE · Airbus A310203 · Wing, Plate/Skin
  > 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 EA 6-5740.
- [SDR FDEA201207152580](https://openairdocs.org/sdr/FDEA201207152580.md): Skin · damaged · Jul 15, 2012 · N403FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 CONJUNCTION WITH WORK CARD T 6-5330-29226 C P3. COMPLIED WITH EA 6-5330-160142 - FUSELAGE - MAIN
- [SDR FDEA201207032460](https://openairdocs.org/sdr/FDEA201207032460.md): Floorbeam · failed · Jul 3, 2012 · N403FE · Airbus A310203 · Fuselage Main, Floor Beam
  > 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 IAW GMM 6-2-100.
- [SDR FDEA201206192267](https://openairdocs.org/sdr/FDEA201206192267.md): Seat Track · damaged · Jun 19, 2012 · N403FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > 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.md): Seat Track · damaged · Jun 19, 2012 · N403FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > 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.md): Access Door · cracked · Aug 8, 2011 · N435FE · Airbus A310203 · Auxiliary Power Unit (APU) Doors
  > 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. INSTALLED NEW MATING FLANGE IAW SRM 51-40-21 AT AFT APU DOORS AFT MATING FLANGE.
- [SDR FDEA201108053112](https://openairdocs.org/sdr/FDEA201108053112.md): Support Bracket · cracked · Aug 5, 2011 · N435FE · Airbus A310203 · Engine Thrust Reverser
  > 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. REMOVED CRACKED UPPER COWL GUIDE SUPPORT BRACKET IAW SRM 54-40-21 AND SRM 54-04-01 PG.11. FABRICATE
- [SDR FDEA201107162734](https://openairdocs.org/sdr/FDEA201107162734.md): Skin · misrepaired · Jul 16, 2011 · N436FE · Airbus A310203 · Trailing Edge Flaps
  > 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 57-52-12 REV 79, FIGURE 205. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 112.
- [SDR FDEA201105251980](https://openairdocs.org/sdr/FDEA201105251980.md): Duct · chafed · May 25, 2011 · N429FE · Airbus A310203 · Engine Thrust Reverser
  > 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.md): Floor Support · corroded · Dec 4, 2010 · N443FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > 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 51-72-10, PAGE 1-3.
- [SDR FDEA201012044573](https://openairdocs.org/sdr/FDEA201012044573.md): Dummy Rail · worn · Dec 4, 2010 · N443FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > 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.md): Stiffener · corroded · Dec 4, 2010 · N443FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > 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 53-12-13 PB 201, FABRICATED 3 EA SPLICE ANGLES IAW SRM 53-12-13, PB 211-213, FIG 201, SHEET 3. R & R
- [SDR FDEA201012044575](https://openairdocs.org/sdr/FDEA201012044575.md): Crossbeam · corroded · Dec 4, 2010 · N443FE · Airbus A310203 · Fuselage Main, Structure
  > 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 IAW SRM 51-72-10 PAR 5&6 AND SRM 51-40-21, PAGES 1,2,3.
- [SDR FDEA201012034559](https://openairdocs.org/sdr/FDEA201012034559.md): Crossbeam · corroded · Dec 3, 2010 · N443FE · Airbus A310203 · Fuselage Main, Structure
  > 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, STRINGER 13R IAW SRM 51-40- 21.
- [SDR FDEA201012034561](https://openairdocs.org/sdr/FDEA201012034561.md): Floor Support · corroded · Dec 3, 2010 · N443FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > 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 51-72-10, PAGE 1-THRU 3.
- [SDR FDEA201012034571](https://openairdocs.org/sdr/FDEA201012034571.md): Seat Track · corroded · Dec 3, 2010 · N443FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > 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 -10,PAGE 1-3.
- [SDR FDEA201011044247](https://openairdocs.org/sdr/FDEA201011044247.md): Controller · failed · Nov 4, 2010 · N404FE · Airbus A310203 · Cabin Pressure Controller
  > 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 CONTROL CHECKLIST. COULD NOT CONTROL THE CABIN PRESSURE RETURNED TO DEPARTURE AIRPORT. TRIED SYS
- [SDR FDEA201011034246](https://openairdocs.org/sdr/FDEA201011034246.md): Switch · failed · Nov 3, 2010 · N411FE · Airbus A310203 · Landing Gear Position and Warning
  > 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 FLIGHT. TRIED SYS NR1 AS WELL AS SYS NR 2. NO RETRACTION OF LANDING GEAR. ACFT IAW MM 07-11-00-00
- [SDR FDEA201010073975](https://openairdocs.org/sdr/FDEA201010073975.md): Brake · smoke · Oct 7, 2010 · N430FE · Airbus A310203 · Landing Gear Brake System
  > 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. SHUTDOWN AND TOWED BACK TO RAMP. BRAKE TEMPS APPROX 280 DEG MAX (NR3, 150 DEG) IDENTIFIED SMOKE COM
- [SDR FDEA201010063957](https://openairdocs.org/sdr/FDEA201010063957.md): Floorbeam · cracked · Oct 6, 2010 · N445FE · Airbus A310203 · Fuselage Main, Floor Beam
  > 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 BETWEEN SEAT TRACKS 3R AND 2R IAW SRM 53-10-15, NDT VERIFIED NO CRACK INDICATIONS IAW NTM 51-10-02
- [SDR FDEA201010013845](https://openairdocs.org/sdr/FDEA201010013845.md): Engine · leaking · Oct 1, 2010 · N428FE · Airbus A310203 · Turbine Engine Oil System
  > 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 FOR ANOTHER 5-10 MINUTES THEN IT BEGAN TO DROP. FINALLY SHUT ENGINE DOWN A FL220. ENGINE CONTINUED
- [SDR FDEA201009303801](https://openairdocs.org/sdr/FDEA201009303801.md): Fitting · corroded · Sep 30, 2010 · N411FE · Airbus A310203 · Fuselage Main, Attach Fittings
  > 134AR ACCESS DOOR SURROUNDING INTEGRAL FITTING FOUND CORROSION (FR23- 24, STGR49R-STGR54L) REMOVE CORROSION IAW SRM 51-74-10. MEASURE THE REMAINING THICKNESS IAW NTM51-10-04 AND NTM51-10-08 CHECK FOR CRACK. MAKE THE REPAIR PARTS IAW SRM53-13-12-201 REPAIR
- [SDR FDEA201009303802](https://openairdocs.org/sdr/FDEA201009303802.md): Fitting · corroded · Sep 30, 2010 · N410FE · Airbus A310203 · Wing, Attach Fittings
  > LT WING RIB 5 MLG FWD LUG CORROSION EXCEED LIMIT COMPLIED WITH EA 6-5710-141613.
- [SDR FDEA201009303803](https://openairdocs.org/sdr/FDEA201009303803.md): Skin · corroded · Sep 30, 2010 · N410FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 0.035" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-08 COMPLIED WITH EA NR6-5310-141622.
- [SDR FDEA201009293796](https://openairdocs.org/sdr/FDEA201009293796.md): Bracket · corroded · Sep 29, 2010 · N410FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > 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 FOUND IAW NTM 51-10-08 AND NTM 51-10-18 WITHIN ALLOWABLE DAMAGE IAW EA 6-5310-141616. RESTORED F
- [SDR FDEA201009293798](https://openairdocs.org/sdr/FDEA201009293798.md): Fitting · corroded · Sep 29, 2010 · N411FE · Airbus A310203 · Fuselage Main, Attach Fittings
  > 136 AR ACCESS DOOR SURROUNDING INTEGRAL FITTING FOUND CORROSION (FR38.1- FR38.2, STGR49R-STGR54L) REMOVE CORROSION IAW SRM51-74-10. MEASURE THE REMAINING THICKNESS IAW NTM51-10-04 AND NTM51-10-08 CHECK FOR CRACK. MAKE THE REPAIR PARTS IAW SRM53-14-12-201 RE
- [SDR FDEA201009273728](https://openairdocs.org/sdr/FDEA201009273728.md): Frame · gouged · Sep 27, 2010 · N411FE · Airbus A310203 · Fuselage Main, Frame
  > 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, PARA6 AND EA6-5310-141632. INSTALL THE REPAIR PART IAW SRM53-10-13-201 PARA6 AND EA6-5310-141632.
- [SDR FDEA201009273729](https://openairdocs.org/sdr/FDEA201009273729.md): Frame · damaged · Sep 27, 2010 · N411FE · Airbus A310203 · Fuselage Main, Frame
  > 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 SRM53-10-13-201, PARA6 AND EA6-5310-141632. INSTALL THE REPAIR PART IAW SRM 53-10-13-201, PARA6 AND EA 6-5310-
- [SDR FDEA201009273730](https://openairdocs.org/sdr/FDEA201009273730.md): Beam · cracked · Sep 27, 2010 · N411FE · Airbus A310203 · Fuselage Main, Structure
  > 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 BEAM IAW SRM51-40-21. DRILL FASTENER HOLES ON THE NEW PART IAW SRM51-40-40. INSTALL THE NEW PART AND
- [SDR FDEA201009263727](https://openairdocs.org/sdr/FDEA201009263727.md): Seat Track · damaged · Sep 26, 2010 · N445FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > 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.md): Skin · corroded · Sep 21, 2010 · N410FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > FWD CARGO COMPT. - 134AR ACCESS DOOR SURROUNDING CUTOUT SKIN INTERIOR SURFACE FOUND CORROSION (FR23-FR24, STGR49R-52R) REMOVED CORROSION IAW SRM 51-74-10 REMAINING THINKNESS IS 0.033" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-08 MADE THE REPAIR PARTS IA
- [SDR FDEA201009203549](https://openairdocs.org/sdr/FDEA201009203549.md): Frame · corroded · Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, Frame
  > 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 CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616. R
- [SDR FDEA201009203551](https://openairdocs.org/sdr/FDEA201009203551.md): Frame · corroded · Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, Frame
  > 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 51-10-04. NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-531
- [SDR FDEA201009203553](https://openairdocs.org/sdr/FDEA201009203553.md): Frame · corroded · Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, Frame
  > 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 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-531
- [SDR FDEA201009203556](https://openairdocs.org/sdr/FDEA201009203556.md): Frame · corroded · Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, Frame
  > 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 51-10-04. NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310
- [SDR FDEA201009203557](https://openairdocs.org/sdr/FDEA201009203557.md): Frame · corroded · Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, Frame
  > 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 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310
- [SDR FDEA201009203558](https://openairdocs.org/sdr/FDEA201009203558.md): Frame · corroded · Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, Frame
  > 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 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-1
- [SDR FDEA201009203590](https://openairdocs.org/sdr/FDEA201009203590.md): Frame · corroded · Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, Frame
  > 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 CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA6-5310-141626 FLAP
- [SDR FDEA201009193542](https://openairdocs.org/sdr/FDEA201009193542.md): Frame · corroded · Sep 19, 2010 · N410FE · Airbus A310203 · Fuselage Main, Frame
  > 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 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-53
- [SDR FDEA201009173534](https://openairdocs.org/sdr/FDEA201009173534.md): Skin · damaged · Sep 17, 2010 · N425FE · Airbus A310203 · Trailing Edge Flaps
  > 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 - LT OTBD FLAP T/E -REPAIR TRACKING EA.
- [SDR FDEA201009153423](https://openairdocs.org/sdr/FDEA201009153423.md): Frame · failed · Sep 15, 2010 · N425FE · Airbus A310203 · Fuselage Main, Frame
  > 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 9-8 IN LONG. PREVIOUSLY INSTALLED REPAIR LOCATED IN BULK CARGO ON FRAME 67 BETWEEN STRINGERS 43 TO
- [SDR FDEA201009153424](https://openairdocs.org/sdr/FDEA201009153424.md): Skin · misrepaired · Sep 15, 2010 · N425FE · Airbus A310203 · Trailing Edge Flaps
  > 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 MEASURES 5.4 IN X 6.6 IN. PREVIOUSLY INSTALLED REPAIR LOCATED AT LT WING INBD FLAP UPPER MAIN SKIN AT R

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## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy
FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
WHERE engine_model_key = 'CF680A3'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/engine/ge-cf6-80a3/reports

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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.