GE CF6-80A3

Service difficulty reports · 161

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duckdb -csv -c "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"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SDR ABXA202109139090Cable · bindingON 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 RETSep 9, 2021 · N768AX · Boeing 767281 · Engine Fuel Indicating SystemSDR FDEA201310072434Engine · failedDURING 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 ANDOct 7, 2013 · N426FE · Airbus A310203 · Engine (Turbine/Turboprop)SDR FDEA201308101829Engine · failedDURING 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 PAug 10, 2013 · N428FE · Airbus A310203 · Turbine Engine Oil SystemSDR FDEA201209013204Outflow Valve · inoperativeRT 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 Sep 1, 2012 · N410FE · Airbus A310203 · Pressure Regulator/Outflow ValveSDR FDEA201208243148Structure · damagedLT 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 6-5750-1Aug 24, 2012 · N428FE · Airbus A310203 · SpoilersSDR FDEA201208233141Controller · failedSLATS 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 COMPONENTAug 23, 2012 · N443FE · Airbus A310203 · Leading Edge Slat Control SystemSDR FDEA201208233144Filter · cloggedREJECTED 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.Aug 23, 2012 · N403FE · Airbus A310203 · Engine Fuel DistributionSDR FDEA201208032826Controller · faultedPASSING 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 FAULTINGAug 3, 2012 · N410FE · Airbus A310203 · Cabin Pressure ControllerSDR FDEA201207152579Skin · crackedLT 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.Jul 15, 2012 · N429FE · Airbus A310203 · Wing, Plate/SkinSDR FDEA201207152580Skin · damagedDURING 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 Jul 15, 2012 · N403FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201207032460Floorbeam · failedMAIN 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.Jul 3, 2012 · N403FE · Airbus A310203 · Fuselage Main, Floor BeamSDR FDEA201206192267Seat Track · damagedFLOOR 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.Jun 19, 2012 · N403FE · Airbus A310203 · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201206192268Seat Track · damagedFLOOR 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.Jun 19, 2012 · N403FE · Airbus A310203 · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108083139Access Door · crackedAPU 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.Aug 8, 2011 · N435FE · Airbus A310203 · Auxiliary Power Unit (APU) DoorsSDR FDEA201108053112Support Bracket · crackedNR1 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. FABRICATEAug 5, 2011 · N435FE · Airbus A310203 · Engine Thrust ReverserSDR FDEA201107162734Skin · misrepairedREPAIR 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.Jul 16, 2011 · N436FE · Airbus A310203 · Trailing Edge FlapsSDR FDEA201105251980Duct · chafedENG 2, LT T/R COWL INNER DUCT AFT EDGE GOT CHAFING ATTACH TO CORE COWL AREA UPPER SIDE.May 25, 2011 · N429FE · Airbus A310203 · Engine Thrust ReverserSDR FDEA201012044572Floor Support · corrodedFLOOR 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.Dec 4, 2010 · N443FE · Airbus A310203 · Fuselage Miscellaneous StructureSDR FDEA201012044573Dummy Rail · wornDUMMY TRACK 4L, FR54.2 EXCEEDED THE ALLOWABLE WEAR LIMITS. REPAIR DUMMY TRACK 4L AT FR54.2 IAW EO 5310-7-3322 PT2 INSTRUCTIONS.Dec 4, 2010 · N443FE · Airbus A310203 · Fuselage Miscellaneous StructureSDR FDEA201012044574Stiffener · corrodedLAV 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 & RDec 4, 2010 · N443FE · Airbus A310203 · Fuselage Miscellaneous StructureSDR FDEA201012044575Crossbeam · corrodedREAR 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.Dec 4, 2010 · N443FE · Airbus A310203 · Fuselage Main, StructureSDR FDEA201012034559Crossbeam · corroded2EA 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.Dec 3, 2010 · N443FE · Airbus A310203 · Fuselage Main, StructureSDR FDEA201012034561Floor Support · corrodedMAIN 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.Dec 3, 2010 · N443FE · Airbus A310203 · Fuselage Miscellaneous StructureSDR FDEA201012034571Seat Track · corrodedMAIN 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.Dec 3, 2010 · N443FE · Airbus A310203 · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201011044247Controller · failedCLIMBING 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 Nov 4, 2010 · N404FE · Airbus A310203 · Cabin Pressure ControllerSDR FDEA201011034246Switch · failedON 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 07-11-00-00Nov 3, 2010 · N411FE · Airbus A310203 · Landing Gear Position and WarningSDR FDEA201010073975Brake · smokeAFTER 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 COMOct 7, 2010 · N430FE · Airbus A310203 · Landing Gear Brake SystemSDR FDEA201010063957Floorbeam · crackedFOUND 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 51-10-02Oct 6, 2010 · N445FE · Airbus A310203 · Fuselage Main, Floor BeamSDR FDEA201010013845Engine · leakingDURING 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 CONTINUEDOct 1, 2010 · N428FE · Airbus A310203 · Turbine Engine Oil SystemSDR FDEA201009303801Fitting · corroded134AR 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 REPAIRSep 30, 2010 · N411FE · Airbus A310203 · Fuselage Main, Attach FittingsSDR FDEA201009303802Fitting · corrodedLT WING RIB 5 MLG FWD LUG CORROSION EXCEED LIMIT COMPLIED WITH EA 6-5710-141613.Sep 30, 2010 · N410FE · Airbus A310203 · Wing, Attach FittingsSDR FDEA201009303803Skin · corrodedFWD 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.Sep 30, 2010 · N410FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201009293796Bracket · corroded2 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 FSep 29, 2010 · N410FE · Airbus A310203 · Fuselage Miscellaneous StructureSDR FDEA201009293798Fitting · corroded136 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 RESep 29, 2010 · N411FE · Airbus A310203 · Fuselage Main, Attach FittingsSDR FDEA201009273728Frame · gougedGOUGE 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.Sep 27, 2010 · N411FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201009273729Frame · damaged2 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-Sep 27, 2010 · N411FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201009273730Beam · crackedLT 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 ANDSep 27, 2010 · N411FE · Airbus A310203 · Fuselage Main, StructureSDR FDEA201009263727Seat Track · damagedMAIN 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.Sep 26, 2010 · N445FE · Airbus A310203 · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009213591Skin · corrodedFWD 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 IASep 21, 2010 · N410FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201009203549Frame · corrodedAVIONICS 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. RSep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201009203551Frame · corrodedAVIONICS 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 6-531Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201009203553Frame · corrodedAVIONICS 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 6-531Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201009203556Frame · corrodedAVIONICS 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 6-5310Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201009203557Frame · corrodedAVIONICS 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 6-5310Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201009203558Frame · corrodedAVIONICS 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 6-5310-1Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201009203590Frame · corrodedFWD 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 Sep 20, 2010 · N410FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201009193542Frame · corrodedAVIONICS 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 6-53Sep 19, 2010 · N410FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201009173534Skin · damagedLEFT 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.Sep 17, 2010 · N425FE · Airbus A310203 · Trailing Edge FlapsSDR FDEA201009153423Frame · failedPREVIOUS 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 Sep 15, 2010 · N425FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201009153424Skin · misrepairedPREVIOUS 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 RSep 15, 2010 · N425FE · Airbus A310203 · Trailing Edge Flaps
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