Airbus A310

Service difficulty reports · 606

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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 = 'A310'
  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 05FDEA01542Fitting · corrodedFS 20A STR 41R TO STR 45R HAS 1EA FITTING WITH CORROSION (OFF ACFT PART) PART NR A5377265020202. PART WAS REMOVED ON N00500 ITEM NR 22 ON JPF LOCATED AND DRILLED FITTING P/N A5377265020202 IAW A310/200 SRM 51-40-21. RESTORED PROTECTIVE COATING IAW A310/200 Jun 8, 2005 · N404FE · Airbus A310 · Fuselage Miscellaneous StructureSDR 05FDEA01528Panel · corrodedNR 2 PYLON PNL 423EL HAS SEVERAL AREAS OF CORROSION AND WEAR MARKS ALONG FASTENER HOLES IN EDGE OF PANELS. REMOVED CORROSION AND WEAR MARKS FROM NR 2 PYLON PNL NR 423EL IAW A310-200 SRM 51-74-10. MATERIAL LOSS IS OUT OF LIMITS IAW A310-200 SRM 54-50-00. RJun 7, 2005 · N404FE · Airbus A310 · Nacelle/Pylon, Plate/SkinSDR 05FDEA01527Support Bracket · crackedFOUND ANGLE SUPPORT BRACKET FOR MAIN HYDRAULIC LINE CRACKED INBD SIDE OF PYLON AT RIB 20. REMOVED AND REPLACED ANGLE ON NR 2 PYLON IAW A310 SRM 51-40-21 AND 51-72-10.Jun 7, 2005 · N404FE · Airbus A310 · Nacelle/Pylon Miscellaneous StructureSDR 05FDEA01526Buttstrap · corrodedCORROSION AROUND NUTPLATE RIVETS ON PANEL SPLICE FOR 326GL, 1 AREA ON ONE END AND 4 AREAS ON OTHER END OF PANEL. REMOVED CORROSION ON PANEL 326GL BUTTSTRAP. MATERIAL LOSS FOUND TO BE OUT OF LIMITS PER A310 SRM 55-40-00. REMOVED AND REPLACED BUTTSTRAPS PER AJun 7, 2005 · N404FE · Airbus A310 · Fuselage Main, Plate/SkinSDR 05FDEA01525Buttstrap · corrodedCORROSION AT TWO NUT PLATE HOLES ON PANEL SPLICE FOR 326JL. REMOVED CORROSION ON PANEL 326JL BUTTSTRAP. MATERIAL LOSS FOUND TO BE OUT OF LIMITS PER A310 SRM 55-40-00. REMOVED AND REPLACED BUTTSTRAP PER A310 SRM 51-40-21.Jun 7, 2005 · N404FE · Airbus A310 · Fuselage Main, Plate/SkinSDR 05FDEA01524Skin · groovedRT WING I/B FORE FLAP, CENTER LWR L/E HAS A 1.5 INCH GROOVE WORN INTO SKIN. REMOVED AND REINSTALLED , OPS TEST FLAP IAW A310-200 AMM 27-50-15-4 OPS TEST GOOD. REPAIRED FORE FLAP PER EA 6-5750-89216 AND A310-200 SRM 51-25-00. MAJOR REPAIR IAW FED-EX GMM 6-2Jun 7, 2005 · N404FE · Airbus A310 · Trailing Edge FlapsSDR 05FDEA01312Panel · wornOFF A/C PART LEFT WING PNL 512AT HAS WEAR MARKS ON BOTTOM SIDE OF PNL. COMPLIED WITH EA6-5740-89200.May 16, 2005 · N403FE · Airbus A310 · Wing, Plate/SkinSDR 05FDEA01083Skin · corrodedIN A/C BAY, FROM FRAME 46 TO 47, STRINGER 46R TO 43R HAS SEVERAL AREAS OF CORROSION. REMOVED CORROSION PER A310 SRM 51-74-10. FOUND ALL AREAS TO BE WITHIN LIMITS IN AREA STR 44R BETWEEN FR 46 AND 47. C/W EA 6-5310-87784. INSTALLED FASTENERS PER A310 SRM Apr 22, 2005 · N402FE · Airbus A310 · Fuselage Main, Plate/SkinSDR 05FDEA01075Skin · corrodedIN AC BAY, FROM FRAME 39 TO 40 AND FROM STR 55-51 RT HAS AREAS OF CORROSION ON SKIN. REMOVED CORROSION PER SRM 51-74-10. FOUND ALL AREAS TO BE WITHIN LIMITS PER EA6-5310-87784. C/W EA 6-5310-87784. INSTALLED FASTENERS PER A310 SRM 51-40-21. RESTORED SURFAApr 22, 2005 · N402FE · Airbus A310 · Fuselage Main, Plate/SkinSDR 05FDEA01074Stringer · corrodedIN ACM BAY STR 46 RT BETWEEN FR 43 TO FR 47 HAS AREAS OF CORROSION. REMOVED CORROSION PER A310 SRM 51-74-10. C/W EA 6-5310-87784. FOUND ALL AREAS TO BE WITHIN LIMITS PER A310 SRM 53-10-00 AND EA 6-5310-87784. RESTORED SURFACE PROTECTION PER A310 SRM 51-7Apr 22, 2005 · N402FE · Airbus A310 · Fuselage Main, Longeron/StringerSDR 05FDEA01073Skin · corrodedIN A/C BAY, FROM FRAME 45 TO FRAME 46 AND STR 46R TO 41R AREA HAS NUMEROUS SPOTS OF CORROSION ON SKIN. REMOVED CORROSION PER A310 SRM 51-74-10. FOUND TO BE WITHIN LIMITS PER A310 SRM 53- 15-12. INSTALLED FASTENERS PER A310-SRM 51-40-21. RESTORED SURFACE PApr 22, 2005 · N402FE · Airbus A310 · Fuselage Main, Plate/SkinSDR 05FDEA01071Stringer · corrodedAFT CARGO COMPT JUST AFT OF FR 54.3 ON STR 51 RT HAS 1EA AREA OF CORROSION. REMOVED CORROSION FROM AFT OF FR 54.3 RT STG 51 IAW A310-200 SRM. FOUND MATERIAL TO BE WITHIN LIMITS IAW A310-200 SRM 53-10-00 PG 123 ITEM 24. INSTALLED REMOVED PARTS AND FASTENERS Apr 22, 2005 · N402FE · Airbus A310 · Fuselage Main, Longeron/StringerSDR 05FDEA01070Stringer · corrodedAFT CARGO COMPT BETWEEN FR 60 AND FR 61 ON STR 50 RT HAS AREA OF CORROSION. REMOVED FASTENERS AND REMOVED CORROSION FROM STG50 BETWEEN FR60 AND FR61 IAW A310-200 SRM 51-40-21 AND SRM 51-74-10; CHECKED LIMITS AND FOUND MATERIAL THICKNESS TO BE WITHIN LIMITS, TApr 22, 2005 · N402FE · Airbus A310 · Fuselage Main, Longeron/StringerSDR 05FDEA01068Stringer · corrodedAFT CARGO COMPT, BETWEEN FR 54.2 AND FR 54.3 ON STR 56 RT HAS 3 AREAS OF CORROSION. REF FEDEX EA 6-5310-88741, REMOVED SHEAR TIE, REMOVED FASTENERS IAW A310-200 SRM 51-40-21. REMOVED CORROSION, CHECK MATERIAL LOSS IAW A310-200 SRM 53-10-00 PG 123 ITEM 24. FApr 22, 2005 · N402FE · Airbus A310 · Fuselage Main, Longeron/StringerSDR 05FDEA01066Skin · damagedWHILE WORKING EO 6-5710-7-5008PT3, LT WING FOR LANDING ASSY FOR PANEL 575CB 4 EA HOLES NOTED ARE LARGER THAN DRAWING SIZE. THIS IS AN INCOMING CONDITION. HOLE NR 9 .263 INCH, EM PLANK .6 INCH, NR 10 .328 INCH, EM RIB .610 INCH, EM PLANK .760 INCH, NR17 .328 IApr 22, 2005 · N402FE · Airbus A310 · Wing, Plate/SkinSDR 05FDEA01065Panel · damagedRT WING FAIRING 633BB 2 MOUNTED BRACKETS REQUIRES INSTALLATION. NOTE 7 EA HOLES IN WING PLANK ARE COUNTERSUNK. RT WING BRACKETS FOR FAIRING 633BB REAMED HOLES TO 2ND OVERSIZE, SEALED FITTINGS (2EA.). INSTALLED CONICAL WASHERS, AND FITTINGS IAW A310 SRM 5Apr 22, 2005 · N402FE · Airbus A310 · Wing, Plate/SkinSDR 05FDEA01064Vane · chafedRIGHT FLAP VANE LEADING EDGE HAS 2 CHAFED AREAS. REMOVED RT WING FLAP VANE IAW A310-200 AMM 27-50-15-4. COMPLIED WITH EA 6-5750-87216. INSTALLED RT FLAP VANE IAW A310-200 AMM 27-50-15-4. OPS CHECKED GOOD IAW A310-200 AMM 27-54-00-5.Apr 22, 2005 · N402FE · Airbus A310 · Leading Edge DevicesSDR 05FDEA01063Frame · corrodedCORROSION ON FRAME IN RT WHEEL WELL AFT OF FRAME 47 ON DIAGONAL FRAME. REMOVED CORROSION AND REPROTECTED SURFACE IAW A310-200 SRM 51-74-10 AND 51-23-10. MATERIAL LOSS WITHIN LIMITS PER FEDEX EA 6-5310-87818.Apr 22, 2005 · N402FE · Airbus A310 · Fuselage Main, FrameSDR 05FDEA01062Mount · corrodedNR 2 ENGINE FWD MOUNT FITTING HAS PITTED CORROSION ON BOLT HOLES, SPIGOT HOLE, LOWER AND UPPER MATING SURFACE. REMOVED CORROSION IN ALL AREAS LISTED. FABBED AND INSTALLED 3 EA BUSHINGS AND REPROTECTED SURFACES IAW A310 SRM 54-51-81 AND FEDEX EA 6-5450-87748Apr 22, 2005 · N402FE · Airbus A310 · Engine Mount SectionSDR 05FDEA00999Flap Track · damagedCOMPLY WITH EA 6-5720-86138 REV NO POS P2 WING INSPECTION FLAP TRACK MOVABLE FAIRING. LT NR 2, 4, 5 AND RT NR 3,5. COMPLIED WITH EAN 6-5720-86138 AND REPORTED FINDINGS TO FED EX VIA MAXI MERLIN.Apr 14, 2005 · N402FE · Airbus A310 · Trailing Edge FlapsSDR 05FDEA00998Arm · gougedNR 7 RUDDER HINGE ATTACHMENT BRACE ( A-FRAME) HAS GOUGE MARKS AND WEAR MARKS AT ATTACHMENT BOLT. REMOVED AND REPLACED NR 7 HINGE ARM IAW A310-200 AMM 55-36-47-4-01 AND 27-21-21-4-01.Apr 14, 2005 · N446FE · Airbus A310 · Rudder Miscellaneous StructureSDR CA050411001Power Unit · failed(CAN) 45 MINUTES AFTER TAKEOFF, BURNING ODOR WAS REPORTED IN THE PASSENGER CABIN AT ROW 17-18. ODOR DISAPPEARED AFTER 10 MINUTES. DURING INVESTIGATION FOUND LIGHT TRANSFORMER ON POWER UNIT 18 BURNED AND FUSE BLOWN. SUSPECT PROBLEM BEING CAUSED BY LIGHT SOCKApr 9, 2005 · Airbus A310 · Passenger Compartment LightingSDR 05FDEA00868Skin · damagedWHILE WORKING EO 6-5710-7-5004 PT 4, RT WING FOR LANDING ASSY FOR PANEL 675CB, 2 EA HOLES NOTED ARE LARGER THAN DRAWING SIZE. THIS IS AN INCOMING CONDITION. HOLE NR 10 .390", EDGE MARGIN RIB .610", PLANK .760", NR 17 .390", EDGE MARGIN RIB .570", PLANK .840"Apr 6, 2005 · N402FE · Airbus A310 · Wing, Plate/SkinSDR 05FDEA00851Floorbeam · damagedREPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. FLOORBEAM NR 35 C R OF CENTER LINE. COMPLIED WITH FEDEX EA NR 6-5310-87772 AND CLASSIFIED AS A MINOR REPAIR PER FEDEX EA NR 6-5310-87772 AND FEDEX GMM 6-2-100.Apr 5, 2005 · N419FE · Airbus A310 · Fuselage Main, Floor BeamSDR 05FDEA00850Floorbeam · damagedREPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. FLOORBEAM NR 34 R L OF CENTER LINE. COMPLIED WITH FEDEX EA NR 6-5310-87772 AND CLASSIFIED AS A MINOR REPAIR PER FEDEX EA NR 6-5310-87772 AND FEDEX GMM 6-2-100.Apr 5, 2005 · N419FE · Airbus A310 · Fuselage Main, Floor BeamSDR 05FDEA00849Skin · damagedREPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. LT ELEVATOR UPPER SURFACE T/E 6' O/B FROM I/B END (ITEM 35 OF LIST). REPAIRED ELEVATOR IAW E NR #6-5520-87201. REPAIR IS CLASSIFIED AS MINOR AS PER EA6-5520-87201 AND FEDEX GApr 5, 2005 · N419FE · Airbus A310 · Elevator, Plate/SkinSDR 05FDEA00833Skin · damagedREPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. ITEM NR 22 ON LIST FUSELAGE LOWER RT SIDE AT FR 58 THIS REPAIR WAS ACCOMPLISHED IAW FEDEX EA NR 6-5530-49627A REVISE DATE 04/25/00. THIS REPAIR IS CLASSED AS A MAJOR REPAIR Apr 4, 2005 · N419FE · Airbus A310 · Fuselage Main, Plate/SkinSDR 05FDEA00831Skin · delaminatedLT ELEVATOR TOP SURFACE STA 473/ER19 HAS 3EA AREAS OF CORROSION. COMPLIED WITH FEDEX EA NR 6-5520-87163.Apr 4, 2005 · N419FE · Airbus A310 · Elevator, Plate/SkinSDR 05FDEA00830Rib · corrodedVERTICAL STAB RT SIDE 6" BELOW RIB 21 TO RIB 1 HAS CORROSION ON REAR CHORD SPAR CHORD FLANGE IN FASTERNER HOLES, AROUND FASTERNER HOLE AREA EXTENDING TO STAB SKIN AS MARKED. REMOVED NUPLATES IAW A310-200 SRM 51-40-21. REMOVED CORROSION IAW A310-200 SRM 51-74Apr 4, 2005 · N419FE · Airbus A310 · Vertical Stabilizer, Spar/RibSDR 05FDEA00829Latch · damagedREPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. NR 2 ENGINE NACELLE O/B T/R BELOW AFT UPPER LATCH. (ITEM NR 51 OF LIST) REMOVED EXISTING REPAIR DOUBLER PER A310 SRM 51-40-21 AND COMPLIED WITH FEDEX EA # 6-7830-87224, THIS RApr 4, 2005 · N419FE · Airbus A310 · Engine Thrust ReverserSDR 05FDEA00828Skin · delaminatedLT ELEVATOR TOP SURFACE BETWEEN STA468/ER16 AND STA474/ER20 IS DELAMINATION. COMPLIED WITH EA NR 6-5520-87163.Apr 4, 2005 · N419FE · Airbus A310 · Elevator, Plate/SkinSDR 05FDEA00797Door · corrodedNR 1 PYLON PANEL 416AR HAS AREA AROUND SCOOP AND EXTENDING UNDER SCOOP WITH CORROSION. REMOVED AND REPLACED DOOR ASSY PER A310-200 AMM 54-50-00-4, DUE TO CORROSION OUT OF LIMITS PER A310-200 SRM 54-50-00 TABLE 102, SHEET 2.Apr 2, 2005 · N419FE · Airbus A310 · Nacelle/Pylon, Main FrameSDR 05FDEA00778Anti-Ice Valve · malfunctionedNR 2 ENG ANTI-ICE FAULT WHEN ENG NR 2 ANTI-ICE TURNED ON. PULLED AND RESET C/B. NO JOY. RELEASED FOR SERVICE PER MEL/CDL: 30-21-01-C CATEGORY: C EXPIRATION: 11APR05 "MEL 30-21-01-C: ENGINE 2 ANTI-ICE VALVE INOP. ENGINE NACELLE VALVE SECURED OPEN." NO TIMApr 1, 2005 · N423FE · Airbus A310 · Air Intake Anti/De-Ice SystemSDR 05FDEA00764Adapter · brokenCLS ADAPTER AT FS 74 TRACK L4 HAS BROKEN CLEVIS. REMOVED AND REPLACED CLS ADAPTER IAW A310-200 SRM 51-72-10.Mar 31, 2005 · N402FE · Airbus A310 · Fuselage, Seat/Cargo Attach FittingsSDR 05FDEA00767Spar · corrodedVERT STAB FRONT SPAR ANTENNA HAS PITTING CORROSION IN SEVERAL AREAS. REMOVED AND REPLACED 1 EA ANTENNA IAW A310-200 AMM 23-11-11-4. OPS CHECK NOT REQUIRED HF SYSTEM IS DEACTIVATED.Mar 31, 2005 · N402FE · Airbus A310 · UHF Communications SystemSDR 05FDEA00766Panel · corrodedOFF AIRCRAFT PART, NR 1 PYLON ACCESS PANEL NR 413BL HAS MODERATE CORROSION AROUND ALL FASTENERS HOLES INTERIOR SIDE OF PANEL. REPLACED PANEL ASSY IAW A310-200 SRM 51-72-10.Mar 31, 2005 · N402FE · Airbus A310 · Nacelle/Pylon, Plate/SkinSDR 05FDEA00765Seat Track · corrodedSEAT TRACK '0' AT FR 75A AND 76 HAS CORROSION. REMOVED AND REPLACED SEAT TRACK. REINSTALLED FLOORBOARDS IAW A310-200 SRM 51-72-10 AND 51-40-21.Mar 31, 2005 · N402FE · Airbus A310 · Fuselage, Seat/Cargo Attach FittingsSDR 05FDEA00763Structure · damagedREPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR AND MINOR CLASSIFICATION. RT WING RT I/B T/E LOWER SURFACE AFT OF NR 2 FLAP TRACK BEAM. COMPLIED WITH EA 6-5750-87747 PART 1. NO DEFECTS NOTED PER NTM 51-10-08. REPAIR IS CLASSIFIED AS A MINOR REPAIMar 31, 2005 · N419FE · Airbus A310 · Trailing Edge FlapsSDR 05FDEA00762Stiffener · corrodedAVIONICS COMPARTMENT LEFT SIDE AT FRAME 12 TO 12A AT FLOOR BOARD LEVEL, AREA HAS CORROSION APPROX 8 INCHES BY 8 INCHES ON RIBS AND STRINGER, STR 44L. REMOVED SKIN STIFFENER AT LT AVIONICS COMPARTMENT BETWEEN FR 12 AND 12A STR 44L IAW A310-200 DRAWING A536-108Mar 31, 2005 · N402FE · Airbus A310 · Fuselage Miscellaneous StructureSDR 05FDEA00761Angle · crackedNR 1 ENGINE OUTBD T/R COWL LOWER FWD CORNER ANGLE IS CRACKED. REMOVED RIVETS IAW A310-200 SRM 51-40-21. CUTOUT CRACKED FLANGE IAW ROHR CF6-80A SRM 54-05-02. VERIFIED REPAIR FILLER AND ANGLE IAW ROHR CF6-80A SRM 54-05-02. FABBED FILLER AND REPAIR IAW ROHR CMar 31, 2005 · N402FE · Airbus A310 · Engine Cowling SystemSDR 05FDEA00760Stringer · corrodedAFT CARGO COMPT, AFT OF FS 54 ON R-STRINGER 51 HAS AREA OF CORROSION. REMOVED STRINGER END FITTING AT FS 54 ON STRINGER 51R IAW A310-200 SRM 51-74-21. REMOVED CORROSION FROM STRINGER 51 AFT OF FS 54 IAW A310-200 SRM 51-74-10. VERIFIED ALLOWABLE LIMITS AND MMar 31, 2005 · N402FE · Airbus A310 · Fuselage Main, Longeron/StringerSDR 05FDEA00759Stringer · corrodedBULK CARGO COMPT, JUST AFT FS 63 ON R STRINGER 53 1 AREA OF CORROSION. REMOVED DISCREPANT SECTION OF STRINGER AND REPLACED PER A310-200 SRM 51-10-14 IN BULK CARGO COMPARTMENT AFT OF FRAME 63 ON R STRINGER 53.Mar 31, 2005 · N402FE · Airbus A310 · Fuselage Main, Longeron/StringerSDR 05FDEA00758Stringer · corrodedCORROSION ALONG STRINGER 52L BETWEEN FRAMES 60 AND 61, AFT CARGO UNDER FLOOR. REMOVED CORROSION IAW A310-200 SRM 51-74-10. MATERIAL THICKNESS AFTER WENT OUT OF LIMITS IAW A310-200 SRM 51-10-04. CUT AND SPLICED STRINGER 52L AT FRAMES 60 AND 61 IAW A310-200 Mar 31, 2005 · N402FE · Airbus A310 · Fuselage Main, Longeron/StringerSDR 05FDEA00757Attach Bracket · corrodedBULK CARGO COMPT, BETWEEN FR 64 AND 65 ABOUT RT STRINGER 46 FLOOR PANEL ATTACH BRACKET HAS 3 SCREW HOLE CORRODED BENEATH NUTPLATE AREA. REMOVED AND REPLACED PROFILE IAW A310-200 SRM 51-72-10.Mar 31, 2005 · N402FE · Airbus A310 · Fuselage Miscellaneous StructureSDR 05FDEA00756Wedge · damagedREPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION, LT WING COMPOSITE REPAIR LOWER SURFACE INBD T/E FLAP WEDGE 5 INCH FWD OF AFT EDGE AND 28 INCH O/B OF I/B EDGE. COMPLIED WITH EA6-5750-87746 PT1 NO ANOMALIES NOTED AS PER FEDEX GMMar 31, 2005 · N419FE · Airbus A310 · Trailing Edge FlapsSDR 05FDEA00755Floorbeam · crackedFLOORBEAM IS CRACKED 66 INCH RIGHT OF CENTER LINE AT FRAME 54.3 UNDER CEILING PANEL 152BC IN AFT CARGO, (PANEL NOT REMOVED FOR C-CHECK). REMOVED FLOOR PANEL 252DF AND CEILING PANEL 152BC FOR ACCESS IAW A310-200 SRM 51- 40-21. CUT OUT DAMAGED AREA, FABRICATEMar 31, 2005 · N402FE · Airbus A310 · Fuselage Main, Floor BeamSDR 05FDEA00754Stringer · corrodedAREA BEHIND BULK CARGO AT FRAME 72 LEFT SIDE APPROX STR 41L, STRINGER HAS 5 SQ INCHES OF CORROSION. REMOVED CORROSION, AREA OUT OF LIMITS, REMOVED DAMAGED STRINGER SECTION AND REPLACED WITH NEW SECTION PER A310-200 SRM 51-74-10 AND 53-10-14.Mar 31, 2005 · N402FE · Airbus A310 · Fuselage Main, Longeron/StringerSDR 05FDEA00753Stringer · corrodedN00674 AREA BEHIND BULK CARGO AT FRAME 74 LEFT SIDE APPROX FR 49L HAS 7 SQ IN OF CORROSION. REMOVED CORROSION AFT OF FRAME 74 FOUND TO BE OUT OF LIMITS IAW A310-200 SRM 53-10-00 FIG 104, TABLE 102. REMOVED AND REPLACED STRINGER SECTION WITH NEW 48L FS 72-Mar 31, 2005 · N402FE · Airbus A310 · Fuselage Main, Longeron/StringerSDR 05FDEA00752Stringer · corrodedAREA BEHIND BULK CARGO BETWEEN FRAME 75 AND 76 APPROX AREA STR 49L, STRINGER HAS 5 SQ INCHES OF CORROSION. REMOVED CORROSION AFT OF FRAME 75 FOUND TO BE OUT OF LIMITS IAW A310-200 SRM 53-10-00 FIG 104, TABLE 102. REMOVED AND REPLACED STRINGER SECTION WITH NEMar 31, 2005 · N402FE · Airbus A310 · Fuselage Main, Longeron/StringerSDR 05FDEA00751Stringer · corrodedAREA BEHIND BULK CARGO BETWEEN FRAMES 72-74 LEFT SIDE AT STRINGER 48 HAS 15 SQ INCHES OF CORROSION. REMOVED CORROSION FR 72-74 FOUND TO BE OUT OF LIMITS IAW A310-200 SRM 53-10-00 FIG 104. REMOVED AND REPLACED STRINGER SECTION 48L FR 72 TO 78 IAW A310-200 SMar 31, 2005 · N402FE · Airbus A310 · Fuselage Main, Longeron/Stringer
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