Airbus A310-324

Service difficulty reports · 1,439

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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 aircraft_model_key = 'A310324'
  ORDER BY difficulty_date DESC"

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SDR 08FDEA03910Seat Track · damagedMAIN DECK CARGO SEAT TRACK NR 4LT BETWEEN FR 59.2 AND FR 59.3 HAS 2 AREAS OF DAMAGED SCALLOPS REMOVED DAMAGED SECTION OF SEAT TRACK AND INSTALLED REPLACEMENT TRACK AT NR 4 LT BETWEEN FR 58 AND FR 60.5 IAW A310-300 SRM 51-40-210AND 53-17-16Sep 17, 2008 · N808FD · Airbus A310324 · Fuselage, Seat/Cargo Attach FittingsSDR FDEA200809063752Tire · failedON DEPT TLV, ATC ADVISED COMPANY THAT RUBBER WAS FOUND ON RWY AFTER TAKEOFF. FRA CONFIRMED THAT A STARBOARD SIDE WAS DAMAGED. FOUND NR 8 TIRE LOST COMPLETE REINFORCED PLY, NO DAMAGE ON FLAPS OR GEAR FOUND. REMOVED AND REPLACED NR 7 TIRE FOR OVERLOAD.Sep 6, 2008 · N801FD · Airbus A310324 · TireSDR 08FDEA03752Tire · failedON DEPT TLV, ATC ADVISED COMPANY THAT RUBBER WAS FOUND ON RWY AFTER T/O. FRA CONFIRMED THAT A STARBOARD SIDE WAS DAMAGED. FOUND NR 8 TIRE LOST COMPLETE REINFORCED PLY, NO DAMAGE ON FLAPS OR GEAR FOUND. REMOVED AND REPLACED NR 7 TIRE FOR OVERLOAD.Sep 6, 2008 · N801FD · Airbus A310324 · TireSDR FDEA200808263598Computer · failedDURING APPROACH WITH THE LANDING GEAR DOWN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT LIGHTS ON O/H. DISCONTINUED AP AND FOLLOWED QRH. WHEN THE SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURAug 26, 2008 · N805FD · Airbus A310324 · Leading Edge Slat Control SystemSDR FDEA200808263597Computer · malfunctionedDURING APPROACH WITH THE LDG GEAR DN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT LIGHTS ON O/H. DISCONTINUED AP AND FOLLOWED QRH. WHEN THE SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURED AGAINAug 26, 2008 · N805FD · Airbus A310324 · Leading Edge Slat Control SystemSDR FDEA200808263602Limiter · failedDURING APPROACH WITH LANDING GEAR DOWN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT O/H. SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURED AGAIN THE SLATS STUCK AT 15 DEGREES. FOLLOWED QRH FOR Aug 26, 2008 · N805FD · Airbus A310324 · Leading Edge Slat Control SystemSDR 08FDEA03601Computer · failedON APPROACH TO KBUR APPROX 5000' MSL, WHEN SELECTING 20 DEGREES FLAP, T/E FLAPS STUCK AT 15 DEGREES WITH SYS 1 AND 2 FLAP FAULT LIGHTS ILLUMINATED. DIVERTED TO LAX. LANDED WITH 30/15 IAW QRH PROCEEDURES. PERFORMED THE REMAINING OF THE T/S AND FOUND NO DEFEAug 26, 2008 · N810FD · Airbus A310324 · Trailing Edge Flap Control SystemSDR 08FDEA03602Limiter · malfunctionedDURING APPROACH WITH LANDING GEAR DOWN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT O/H. SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURED AGAIN THE SLATS STUCK AT 15 DEGREES. FOLLOWED QRH FOR Aug 26, 2008 · N805FD · Airbus A310324 · Leading Edge Slat Control SystemSDR 08FDEA03598Slat System · failedDURING APPROACH WITH THE LDG GEAR DN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT LIGHTS ON O/H. DISCONTINUED AP AND FOLLOWED QRH. WHEN THE SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURED AGAAug 26, 2008 · N805FD · Airbus A310324 · Leading Edge Slat Control SystemSDR 08FDEA03597Slat System · malfunctionedDURING APPROACH WITH THE LDG GEAR DN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT LIGHTS ON O/H. DISCONTINUED AP AND FOLLOWED QRH. WHEN THE SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURED AGAAug 26, 2008 · N805FD · Airbus A310324 · Leading Edge Slat Control SystemSDR 08FDEA03529Selector Valve · failedLDG GEAR DID NOT EXTEND WITH GEAR HANDLE, GRAVITY EXTENSION OK PER CREW DEBRIEF, WHEN GEAR HANDLE CYCLED THERE WAS NO ASSOCIATED AUDIABLE SOUND NORMALLY HEARD DURING GEAR EXTENSION. CREW DID NOT TRY SELECTING LDG GEAR POSITON DET SYSTEM TO "2" DURING ATTEMPTAug 21, 2008 · N804FD · Airbus A310324 · Landing Gear Retraction/Extension SystemSDR 08FDEA03353Skin · damagedUPON INSPECTION OF RUDDER BY THERMOGRAPHY IAW EO 6-5530-7-5004 PT 2 PARA 8 STEP C AND D THE FOLLOWING DEFECTS WERE NOTED IN ADDITION TO ORIGINAL FINDINGS REF EA 6-5740-118399 THE UPPER RT PORTION OF THE RUDDER HAS 1 ADDITIONAL AREA OF MOISTURE MEASURING .960 WAug 9, 2008 · N812FD · Airbus A310324 · Rudder, Plate/SkinSDR 08FDEA03264Skin · dentedEXTERNAL LT FUSELAGE SKIN HAS 2 DENTS. NR 1 AT FRAME 60 BETWEEN STRINGER 43 AND 44L 4 INCHES ABOVE BOTTOM SKIN LAP MEASURES 6 INCHES LONG BY .800 INCHES WIDE BY .037 INCHES DEEP. NR 2 DENT AT FRAME 61 BETWEEN STRINGER 43 AND 44L 3 INCHES ABOVE SKIN LAP MEASUAug 5, 2008 · N812FD · Airbus A310324 · Fuselage Main, Plate/SkinSDR 08FDEA03263Skin · dentedDENT IN RT NR 1 LEADING EDGE SLAT, DENT MEASURES 4 INCH LONG BETWEEN RIBS 7 AND 8, 35 INCHES FROM INBD EDGE, 5 1/2 INCHES BELOW PAINTED SURFACE, AND 5/32 INCH DEEP. REMOVED DAMAGE AND REPAIRED DENT ON RT NR 1 LEADING EDGE SLAT BETWEEN RIBS 7 AND 8, 35 INCH FRAug 5, 2008 · N812FD · Airbus A310324 · Wing, Plate/SkinSDR FDEA200807122844Jackscrew · leakingSLATS STUCK AT 0 DEG, C/W QRH. EMERGENCY DECLARED, LANDED UNEVENTFULLY AT SYR. REMOVED AND REPLACED RIGHT NR 2 JACKSCREW ASSY PER A310-300MM ATA 27-84-22-4.Jul 12, 2008 · N805FD · Airbus A310324 · Leading Edge Slat Control SystemSDR 08FDEA02844Jackscrew · stuckSLATS STUCK AT O DEG, C/W QRH, EMERGENCY DECLARED, LANDED UNEVENTFULLY AT SYR. REMOVED AND REPLACED RIGHT NR 2 JACKSCREW ASSY PER A310-300MM ATA 27-84-22-4.Jul 12, 2008 · N805FD · Airbus A310324 · Leading Edge Slat Control SystemSDR 08FDEA02261Line · leakingHYD GREEN SYSTEM LOW LEVEL IN FLIGHT. ECAM WARNING, MANUAL EXTENTION OF L/G. FOUND UPPER HYD LINE TO RT AILERON DROOP ACTUATOR LEAKING. REPAIRED SAME HYD LINE IAW AMM 20-23-11-0, LEAK CHECK GOOD. REPLENISHED GREEN HYDRAULIC SYSTEM IAW AMM 29-10-00-3. CRJun 13, 2008 · N810FD · Airbus A310324 · Hydraulic System, MainSDR 08FDEA02212Skin · delaminatedLEFT WING INBD FLAP T/E AREA IS DENTED AND DELAMINATED APPROX 18 INCHES FROM THE OUTBD EDGE. REPAIRED THE LEFT INBD FLAP BY REMOVING THE DAMAGED AREA ; FABRICATING; AND BONDING A NEW CORE AND DOUBLERS IAW A310 SRM 57-52-12 AND FEDEX EA 6-5750-118501 TITLED "Jun 10, 2008 · N815FD · Airbus A310324 · Trailing Edge FlapsSDR 08FDEA02148Skin · corrodedFWD CARGO PIT DOOR LOWER INTERNAL SKIN PLATE IS CORRODED IN NUMEROUS PLACES. REMOVED AND REPLACED THE FWD CARGO DOOR INTERNAL SKIN PLATE IAW A310 SRM 51-40-21. MATERIAL ID IAW A310 SRM 52-31-00; PG 4; SHEET 2; ITEM 20, P/N A52372043200. THIS SDR WAS GENERAJun 4, 2008 · N815FD · Airbus A310324 · Cargo/Baggage DoorsSDR 08FDEA02016Skin · gougedNR 2 ENG LT T/R AFT LATCH INNER CUTOUT CHAFED BY LATCH HANDLE. COMPLIED WITH EA 6-7830-118504 THRUST REVERSER, NR 2 ENGINE LT T/R LWR BIFURCATION DECK ASSY, OUTER SKIN GOUGE.May 28, 2008 · N815FD · Airbus A310324 · Engine Thrust ReverserSDR 08FDEA01997Skin · gougedFWD CARGO DOOR CUT OUT FUSELAGE SKIN EDGE IS GOUGED AT THE UPPER FWD CORNER. COMPLIED WITH EA 6-5310-118494 FUSELAGE SKIN AT FRAME 20 AND STRINGER 28 R REPAIR.May 23, 2008 · N815FD · Airbus A310324 · Fuselage Main, Plate/SkinSDR 08FDEA01922Floor Panel · damagedTHERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 77 TO FRAME 80/82, LBL 45 TO LBL 63. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 77 TO FRAME 80/8May 20, 2008 · N815FD · Airbus A310324 · Fuselage Floor PanelSDR 08FDEA01920Floor Panel · damagedTHERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 67 TO FRAME 69, RBL 54 TO RBL 72. MATERIAL ID IS A402H35039-003, PO604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 67 TO FRAME 69 USINGMay 20, 2008 · N815FD · Airbus A310324 · Fuselage Floor PanelSDR 08FDEA01919Floor Panel · damagedTHERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 66 TO FRAME 67, RBL 57 TO RBL 71. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 66TO 67 USING THE OMay 20, 2008 · N815FD · Airbus A310324 · Fuselage Floor PanelSDR 08FDEA01916Floor Panel · damagedTHERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 54.2 TO FRAME 55/58, RBL-17 TO RBL-37. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 54.2 TO FRAME May 20, 2008 · N815FD · Airbus A310324 · Fuselage Floor PanelSDR 08FDEA01914Floor Panel · damagedTHERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK AT FRAME 65 TO FRAME 66, LBL-57 TO LBL-71. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 65 TO FRAME 66 USING TMay 20, 2008 · N815FD · Airbus A310324 · Fuselage Floor PanelSDR 08FDEA01913Floor Panel · damagedTHERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 62 TO FRAME 65, LBL-57 TO LBL-72. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 62 TO FRAME 65 USINMay 20, 2008 · N815FD · Airbus A310324 · Fuselage Floor PanelSDR 08FDEA01912Floor Panel · damagedTHERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 66 TO 67; LBL 57 TO LBL 71. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CABIN FROM FRAME 66 TO FRAME 67 USING THE OLD May 20, 2008 · N815FD · Airbus A310324 · Fuselage Floor PanelSDR 08FDEA01911Floor Panel · crackedMAIN CABIN FLOOR PANEL AT FRAME 51, RBL 37 IS CRACKED. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED NEW FLOORBOARD PANEL FOR THE MAIN CABIN FROM FRAME 51 TO FRAME 54 USING THE OLD PANEL AS A TEMPLATE IAW FEDEX DWG SRMay 20, 2008 · N815FD · Airbus A310324 · Fuselage Floor PanelSDR 08FDEA01909Floor Panel · crackedMAIN CABIN FLOOR PANEL AT FRAME 48 IS CRACKED AT RBL 57. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED NEW FLOORBOARD PANEL FOR THE MAIN CABIN AT FRAME 48 USING THE OLS PANEL AS A TEMPLATE IAW FEDEX DWG SRZ 25-005, REMay 20, 2008 · N815FD · Airbus A310324 · Fuselage Floor PanelSDR 08FDEA01908Floor Panel · delaminatedMAIN WHEEL WELL CATWALK PANEL NR 148 BF IS DELAMINATED. MATERIAL ID IS A402H35039-003 PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL AT THE MAIN WHEEL WELL CATWALK PANEL NR 148 BF USING THE OLD PANEL AS A TEMPLATE IAW FEDEX DWG SRZMay 20, 2008 · N815FD · Airbus A310324 · Fuselage Floor PanelSDR 08FDEA01883Rib · crackedLEFT WING TIP RIB WY 495 IS CRACKED. REPLACED LEFT WING TIP RIB WY 495 IAW WORK INSTRUCTIONS FOUND IN EO 6-5710-7-5012 E OCN 01 PI.May 19, 2008 · N815FD · Airbus A310324 · Wing, Rib/BulkheadSDR 08FDEA01840Intercostal · bentEMPENAGE THRU DOOR 312 AR, RIGHT INTERCOSTAL BETWEEN FRAME 85 AND 86 IS BENT. REMOVED OLD INTERCOSTAL IAW A310 SRM 51-40-21. INSTALLED NEW INTERCOSTAL IAW A310 SRM 51-40-21.May 13, 2008 · N815FD · Airbus A310324 · Fuselage Miscellaneous StructureSDR 08FDEA01835Panel · corrodedRIGHT WING FUEL PANEL ASSY NR 650 CB CLAMP RING HAS AREAS OF FRETTING. BLENDED AREA SMOOTH IAW SRM 51-73-10. FOUND TO BE OUT OF LIMITS IAW SRM 57-20-16. REMOVED AND REPLACED THE CLAMP RING.May 13, 2008 · N815FD · Airbus A310324 · Wing, Plate/SkinSDR 08FDEA01834Panel · corrodedRIGHT WING FUEL PANEL ASSY NR 650 FB CLAMP RING HAS AREAS OF FRETTING. BLENDED AREA SMOOTH IAW 57-73-10. FOUND TO BE OUT OF LIMITS IAW SRM 57-20-16. REMOVED OLE CLAMP RING AND REPLACED WITH A NEW RING.May 13, 2008 · N815FD · Airbus A310324 · Wing, Plate/SkinSDR 08FDEA01825Attach Fitting · chafedNR 2 PYLON AFT LOWER FAIRING PANEL NR 485 AL, FWD UPPER LT ATTACH PLATE IS CHAFED ON THE INNER SURFACE. REMOVED CHAFED ATTACH PLATE & INSTALLED A NEW ATTACH PLATE PER SRM 51-40-21 PARA 6. LOCATED & DRILLED PER SRM 51-40-44. ALODINED PER AMM 51-23-10-0.May 12, 2008 · N815FD · Airbus A310324 · Nacelle/Pylon, Attach FittingsSDR 08FDEA01824Attach Angle · chafedNR 2 PYLON LOWER FAIRING PANEL NR 485 AL, RT UPPER ATTACH ANGLE IS CHAFED IN SEVERAL PLACES. REMOVED THE NR 2 PYLON LOWER FAIRING UPPER ATTACH ANGLE PER FEDEX SRM 51-40-21. LOCATED & DRILLED NEW UPPER ATTACH ANGLE IAW SRM 51-40-44. ALODINED & PRIMED NEW ATTMay 12, 2008 · N815FD · Airbus A310324 · Nacelle/Pylon Miscellaneous StructureSDR 08FDEA01823Attach Angle · chafedNR 2 PYLON AFT LOWER FAIRING PANEL NR 485 AL, LT UPPER ATTACH ANGLE IS CHAFED IN SEVERAL PLACES. REMOVED DAMAGED LONGERON & INSTALLED NEW LONGERON PER SRM 51-40-21 PARA 6 - 7. LOCATED DRILLED HOLES PER SRM 51-40-44. ALODINED & PRIMED PER AMM 51-23-00.May 12, 2008 · N815FD · Airbus A310324 · Nacelle/Pylon, Attach FittingsSDR 08FDEA01822Rib · crackedNR 2 PYLON AFT LOWER FAIRING PANEL NR 485 AL, RIB IS CRACKED AT THE LOWER ATTACH ANGLE. REMOVED CRACKED ANGLE AND REPLACED WITH A NEW ANGLE PER SRM 51-40-21 PARA 6 & 7. LOCATED & DRILLED HOLES PER SRM 51-40-44. APPLIED PRIMER PER AMM 51-23-10-0.May 12, 2008 · N815FD · Airbus A310324 · Nacelle/Pylon, Frame/Spar/RibSDR 08FDEA01805Skin · corrodedFWD CARGO PIT DOOR LOWER EXTERNAL SKIN PLATE IS CORRODED IN NUMEROUS PLACES. REMOVED AND REPLACED THE FWD CARGO DOOR LOWER EXTERNAL SKIN PLATE IAW SRM 51-40-21.May 8, 2008 · N815FD · Airbus A310324 · Cargo/Baggage DoorsSDR 08FDEA01794Support Bracket · wornRIGHT AIR CONDITIONING FAIRING SUPPORT BRACKET IS WORN, 9 INCH AFT OF FRAME 43. REMOVED DAMAGED BRACKET REF A310 SRM 51-40-21. FORMED AND LOCATED FASTENER HOLES IAW AIRBUS DWG 53410426. ALODINED AND PRIMED NEW BRACKETS REF A310 SRM 51-21-10. PAINTED NEW BRMay 8, 2008 · N815FD · Airbus A310324 · Fuselage Miscellaneous StructureSDR 08FDEA01793Panel · chafedNR 1 PYLON PANEL NR 414 ER HAS CHAFING ON THE MATING SURFACE. REPAIRED THE IAW SRM 54-52-51, FIG 203.May 8, 2008 · N815FD · Airbus A310324 · Nacelle/Pylon, Plate/SkinSDR 08FDEA01733Attach Fitting · corrodedRADAR MOUNT ATTACH FITTING ON THE FWD FACE OF THE FRONT PRESSURE BULKHEAD STRUCTURE IS CORRODED. REMOVED THE ANGLE IN REF TO SRM 51-40-21; PARA 7. FABBED A NEW ANGLE IN REF TO DWG 11A92420400 & INSTALLED NEW ANGLE IN REF TO SRM 51-40-21 PARA 7.May 2, 2008 · N815FD · Airbus A310324 · Fuselage Main, Attach FittingsSDR 08FDEA01315Drain Line · crackedNR 2 ENGINE DRAIN MANIFOLD TUBE CRACKED REMOVED DRAIN MANIFOLD IAW FEDEX AMM 71-70-14-4. WELDED DRAIN MANIFOLD IAW EA 6-7170- 118466, POWER PLANT, DRAIN MANIFOLD ASSEMBLY CRACK, REPAIR. REINSTALLED DRAIN MANIFOLD IAW FEDEX AMM 71-70-14-4.Apr 6, 2008 · N803FD · Airbus A310324 · Engine DrainsSDR 08FDEA01153Web · corrodedLEFT AFT ENTRY DOOR HAS CORROSION ON THE VERTICAL WEB AROUND A GROMMET HOLE. REMOVED AND REPLACED LT VERTICAL WEB ON THE AFT ENTRY DOOR IAW SRM 51-40-21 PG 7.Mar 26, 2008 · N803FD · Airbus A310324 · Passenger/Crew DoorsSDR 08FDEA01103Liner · corrodedCORROSION AROUND THE AFT CARGO DOOR LINER FASTENER RECEPTACLE BETWEEN FRAME 62 AND FRAME 63 ON THE DOOR FRONT AND BACK SIDE OF THE DOOR. REMOVED CORROSION IAW A310-300SRM 51-22-00 AND FOUND TO BE OUT OF LIMITS IAW A310-300 SRM 52-30-00. MATERIAL ID 2024-T3 PMar 21, 2008 · N803FD · Airbus A310324 · Cargo/Baggage DoorsSDR 08FDEA01102Door Frame · corrodedCORROSION AROUND THE AFT CARGO DOOR LINER FASTENER RECEPTICAL; LOWER PART OF FRAME 60 ON THE DOOR FRONT AND BACK SIDE OF THE DOOR. REMOVED CORROSION IAW A310-300 SRM 51-22-00 AND FOUND TO BE OUT OF LIMITS IAW A310-300 SRM 51-21-00. MATERIAL ID 2024-T3 0.050 Mar 21, 2008 · N803FD · Airbus A310324 · Cargo/Baggage DoorsSDR 08FDEA01101Liner · corrodedEXFOLIATED CORROSION AROUND THE AFT CARGO DOOR LINER FASTENER INSERT BETWEEN FRAME 59 AND FRAME 60 ON THE DOOR; FRONT AND BACK SIDE OF THE FRAME. MATERIAL ID 2024-T3 0.050 PO 602303.2 IAW A310-300 SRM 52-32-00; PG 35 AND 51-31-00; PG 21- 22. CUT OUT DAMAGE Mar 21, 2008 · N803FD · Airbus A310324 · Cargo/Baggage DoorsSDR 08FDEA01093Panel · damagedLEFT RUDDER PANEL, 4TH FASTENER FROM THE TOP OF THE RUDDER HAS WATER IN 5 CONNECTED CELLS; 2 INDIVIDUAL CELLS AND DELAMINATION 1.8" BY 1.7", MARKED IN WHITE MARKER. REPAIRED LT RUDDER PANEL SKIN 4TH FASTENER FROM TOP BY REMOVING DELAMINATED AREA & APPLIED REPMar 21, 2008 · N803FD · Airbus A310324 · Rudder, Plate/SkinSDR 08FDEA01094Panel · damagedLEFT RUDDER PANEL, 3RD FASTENER FROM THE TOP OF THE RUDDER HAS WATER IN 7 CONNECTED CELLS; 4 CONNECTED CELLS; 2 CONNECTED CELLS AND 5 INDIVIDUAL CELLS, DELAMINATION 3.4 INCH BY 2.8 INCH. REPAIRED REMOVING DELAMINATED AREA & BONDING A NEW CORE & LAY UP REPAIMar 21, 2008 · N803FD · Airbus A310324 · Rudder, Plate/Skin
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