N431FE

Part: ACTUATOR — LEAKING (K FLAPS) · airframe 50,381 hrs · 23,778 cycles

DURING RETRACTION OF THE LANDING GEAR, LEFT ECAM ANNUNCIATED GREEN HYD SYS QUANTITY/PRESSURE LOSS. COMPLIED WITH ECAM AND QRH MANUALLY EXTENDING THE LANDING GEAR FOR UNEVENTFUL LANDING AT DEPARTURE AIRPORT. FOUND LT KRUGER FLAP ACTUATOR SWIVEL BLOWN OUT. REPLACED ACTUATOR ASSY IAW AMM 27-88-11-04. SERVICED HYD QUANTITY AND GROUND RAN AIRCRAFT. CYCLED FLAPS AND ALL FLIGHT CONTROLS EXTENSIVELY. NO LEAKS OR DEFECTS NOTED. ACFT OK FOR CONTINUED SERVICE.

Part: SKIN — MISREPAIRED (BS 1187) · airframe 49,430 hrs · 23,151 cycles

SKIN AT R1 PASSENGER DOOR LOWER AT FS 1187 FRAME 14A. MISREPAIRED. REPAIR CARRIED OUT AS PER E.A. 6-5210-143668, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SUPPORT FITTING — CRACKED (RT WING TE FLAP) · airframe 49,430 hrs · 23,151 cycles

RT WING NR 2 FLAP TRACK FORWARD FIXED FAIRING FORWARD SUPPORT FITTING FOUND CRACKED. REMOVED AND REPLACED AS PER SRM 51-40-21 REV 79. REPAIR CLASSIFIED MINOR AS PER GMM 6-2-100 REV 112.

Part: FLOOR PANEL — DAMAGED (CARGO DECK) · airframe 49,430 hrs · 23,151 cycles

MAIN DECK CARGO COMPARTMENT BETWEEN FRAME 53 AND FRAME 54 RT OTBD FLOOR PANEL FOUND DAMAGED. FABRICATED FLOOR PANEL PER DWG SRZ 35-005 REV J AND INSTALLED AS PER AMM 53-10-25 REV 30. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REV 112.

Part: FLOOR PANEL — BROKEN (CARGO BAY) · airframe 49,430 hrs · 23,151 cycles

FORWARD CARGO FLOOR PANEL 132YF FOUND BROKEN. FLOOR PANEL REMOVED AND REPLACED AS PER AMM 53-10-29 REV.30 FLOOR PANEL FABRICATED AS PER DWG SRZ-25-005 REV J. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REV 112.

Part: SUPPORT FITTING — BROKEN (RT WING TE FLAP) · airframe 49,430 hrs · 23,151 cycles

RT WING NR 3 FLAP TRACK FORWARD FIXED FAIRING FWD SUPPORT FITTING BROKEN. REMOVED AND REPLACED AS PER SRM 51-40-21 REV 79. FUEL LEAK CHECK CARRIED OUT AS PER AMM 28-11-00-05-0 REV 30. FOUND SATISFACTORY. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REV 112.

Part: SPAR — CRACKED (ZONE 600) · airframe 49,430 hrs · 23,151 cycles

HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSP CARRIED OUT AND FOUND HOLE ITEM 29 ON RT WING REAR SPAR, NEAR RIB 1 WITH CRACK INDICATION. RT WING REAR SPAR CRACKED FASTENER HOLE REAMED TO DIAMETER 0.560 INCH IAW EO 6-5710-7-3322, PART 1, WORK STEP 4G. HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSPECTION CARRIED OUT IAW NTM REV 74, PART 6. 57-10-12 NO CRACK AND NO DAMAGE FOUND ON REWORKED HOLE. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 112.

Part: SPAR — DAMAGED (ZONE 200) · airframe 49,430 hrs · 23,151 cycles

HIGH FREQUENCY EDDY CURRENT INSPECTION CARRIED OUT AT LT CENTER TANK REAR SPAR AND FOUND DAMAGED AT APPROX 6 O`CLOCK. REPAIRED IAW EO 6-5710-7-3322B1 PT 1. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100 REV112.

Part: SPAR — CRACKED (ZONE 600) · airframe 49,430 hrs · 23,151 cycles

HIGH FREQUENCY EDDY CURRENT INSPECTION CARRIED OUT AND FOUND RT WING REAR SPAR LOWER CHORD NEAR RIB 1 HAS A CRACKED INDICATION. RT WING REAR SPAR REAMED TO DIAMETER 0.560" IAW EO 6-5710-7-3322 PART 1, WORK STEP 4.G. HIGH FREQUENCY EDDY CURRENT INSPECTION CARRIED OUT IAW NTM REV 74 PART 6. 57-10-12. NO CRACK AND NO DAMAGE FOUNDE. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 112.

Part: SKIN — DAMAGED (ZONE 500) · airframe 49,430 hrs · 23,151 cycles

HIGH FREQUENCY EDDY CURRENT INSPECTION CARRIED OUT AT LT WING REAR SPAR AND FOUND DAMAGE. REPAIRED IAW EO 6-5710-7-3322 B1 PT 1. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100 REV112.

Part: SKIN — DAMAGED (ZONE 200) · airframe 49,430 hrs · 23,151 cycles

HIGH FREQUENCY EDDY CURRENT INSPECTION CARRIED OUT ON SKIN & FOUND DAMAGED. REPAIRED IAW EO 6-5310-7-3318 PT 15. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REV 112.

Part: SKIN — DAMAGED (ZONE 200) · airframe 49,430 hrs · 23,151 cycles

HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSP CARRIED OUT ON RT AFT CREW DOOR. UPPER FORWARD CUTOUT FOUND DAMAGED. REPAIRED PER EO#6-5310-7-3318 PT 18 STEP 8. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REV 112.

Part: SKIN — DAMAGED (ZONE 200) · airframe 49,430 hrs · 23,151 cycles

HIGH FREQUENCY EDDY CURRENT INSPECTION CARRIED OUT. LOWER FORWARD DOOR CUTOUT FOUND DAMAGED. REPAIRED IAW EO 6-5310-7-3318, PT 17. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 112.

Part: SKIN — DAMAGED (ZONE 200) · airframe 49,430 hrs · 23,151 cycles

HIGH FREQUENCY EDDY CURRENT INSPECTION CARRIED OUT ON CREW DOOR CUTOUT & FOUND DAMAGED. REPAIRED IAW EO 6-5310-7-3318 PT 15. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REV 112.

Part: FLOORBEAM — CRACKED (ZONE 100) · airframe 49,430 hrs · 23,151 cycles

FORWARD CARGO COMPARTMENT MAIN DECK FLOORBEAM AT FRAME 36, RBL 27 FOUND CRACKED. REPAIR CARRIED OUT AS PER SRM 53-10-15 FIG.203 SHT 1 REV. 18 REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REV 112.

Part: COMPUTER — MALFUNCTIONED · airframe 47,487 hrs · 21,872 cycles

OAK - ON TAKEOFF ROLL AT ABOUT 75 KNOTS ATS LEVER TRIPPED OFF DISPLAYED ECAM MESSAGE. REJECTED TAKEOFF COMPLIED WITH QRH AND ECAM. ATS LEVER WOULD NOT RESET. COMPLIED WITH MEL AND DEPARTED WITH ATS LEVER OFF. R & R THE TCC IAW MM 22-36-34-4 AFS TEST AND LAND TEST PASSED. DUE TO HISTORY ACFT CK CAT 3A.

Part: COMPUTER — MALFUNCTIONED (ATS) · airframe 47,487 hrs · 21,872 cycles

ON TAKEOFF ROLL AT ABOUT 75 KNOTS ATS LEVER TRIPPED OFF DISPLAYED ECAM MESSAGE. REJECTED TAKEOFF COMPLIED WITH QRH AND ECAM. ATS LEVER WOULD NOT RESET. COMPLIED WITH MEL AND DEPARTED WITH ATS LEVER OFF. REMOVED AND REPLACED THE TCC PER MM 22-36-34-4 AFS TEST AND LAND TEST PASSED.

Part: STRUCTURE — CORRODED · airframe 47,377 hrs · 21,808 cycles

LWR SURFACE OF CENTER WING BOX LT SIDE AT FR 47 BETWEEN SUPPORT STRUCTURE Y953 AND Y1456 HAS APPROX 12 SQ IN OF CORROSION EXTENDING UNDER 12 EA LOCK FASTENERS. DESEALED, CLEANED AND RESEALED 20 EA FASTENER CWT BOTTOM SURFACE LT SIDE ON FR 47 IAW SRM 51-76-20, LEAK CHECK GOOD IAW AMM 28-11-00-5, REMOVED FASTENERS ON LWR SURFACE CENTER WING TANK SKIN LT SIDE AT FR 47. REMOVED CORROSION, REPROTECTED AREA AND INSTALLED OVERSIZE FASTENERS PER EA 6-5710-1 24237, SRM 51-74-10 AND 51-29-10.

Part: SUPPORT — CORRODED (WING BOX) · airframe 47,377 hrs · 21,808 cycles

LWR SURFACE OF CENTER WING BOX LT SIDE AT FR 47 BETWEEN SUPPORT STRUCTURE Y1456 AND Y1908 HAS APPROX 20 SQ IN OF CORROSION EXTENDING UNDER 18 EA LOCK FASTENER. DESEALED, CLEANED AND RESEALED 18 FASTENERS CWT BOTTOM SURFACE LT SIDE ON FR 47 IAW A310 SRM 51-76-10, LEAK CHECK GOOD IAW A310-200 AMM 28-11-00-5. REMOVED FASTENERS ON LWR SURFACE CENTER WING TANK SKIN LT SIDE AT FR 47. REMOVED CORROSION, REPROTECTED AREA AND INSTALLED OVERSIZED FASTENERS PER FED EX EA 6-5710-124237, SRM 51-74-10 AND 51-29-00.

Part: FITTING — CORRODED (ZONE 400) · airframe 47,377 hrs · 21,808 cycles

NR 2 PYLON SPIGOT BEARING RECEPTACLE CORRODED REMOVED AND REPLACED NR 2 PYLON SPIGOT FITTING PER EA NR 6-5450-124230.

Part: FITTING — CORRODED (ZONE 400) · airframe 47,377 hrs · 21,808 cycles

NR 1 PYLON SPIGOT RECEPTACLE FITTING HAS CORROSION ON INSIDE THE HOLE. REMOVED AND REPLACED NR 1 PYLON SPIGOT FITTING PER EA NR 6-5450-124229.

Part: FRAME — CHAFED (ZONE 200) · airframe 47,377 hrs · 21,808 cycles

LT FRAME 34, STRINGER 14, FRAME HAS CHAFE MARK ON OUTSIDE RADIUS OF CORNER .015 INCH DEEP FRAME THICKNESS AT .245 INCH. BLENDED AREA AND PERFORMED REPAIR AT FR 34, STRINGER 14 LT IAW EA 6-5310-124228, RELEASE DATE 18 FEBRUARY, 2009.

Part: FRAME — CHAFED (ZONE 200) · airframe 47,377 hrs · 21,808 cycles

LT FRAME 34, STRINGER 13 - FRAME HAS CHAFE MARK ON OUTSIDE RADIUS OF CORNER .014 INCH DEEP FRAME THICKNESS AT .245 INCH. BLENDED AREA AND PERFORMED REPAIR AT FR 34, STRINGER 13 LT IAW EA 6-5310-124228, RELEASE DATE 18 FEBRUARY, 2009.

Part: FRAME — CHAFED (ZONE 200) · airframe 47,377 hrs · 21,808 cycles

LT FRAME 34,STRINGER 16 - FRAME HAS CHAFE MARK ON OUTSIDE RADIUS OF CORNER. .187 IN DIA BY .075 DEEP FRAME THICKNESS AT .245 INCH. BLENDED AREA AND PERFORMED REPAIR AT FR 34, STRINGER 16 LT IAW EA 6-5310-124228, RELEASE DATE 18 FEBRUARY, 2009.

Part: LUG — CORRODED (ZONE 600) · airframe 47,377 hrs · 21,808 cycles

RT WING MLG BAY RIB NR 5 FWD LUG HAS CORROSION IN HOLE BORE AND ON FWD AND AFT SPOTFACE. REMOVED LEVEL 1 CORROSION AND REPAIRED RT RIB NR 5 LUG IAW EA 6-5710-124226 .

Part: LUG — CORRODED (ZONE 500) · airframe 47,377 hrs · 21,808 cycles

LT WING MLG BAY RIB NR 5 FWD LUG HAS CORROSION IN HOLE BORE AND ON FWD AND AFT SPOTFACE. REMOVED LEVEL 1 CORROSION AND REPAIRED LT RIB NR 5 LUG IAW EA 6-5710-124226.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 47,377 hrs · 21,808 cycles

MAIN DECK SEAT TRACK NR 5 LT HAS 2 GOUGED SCALLOPS LOCATED 5 INCHES AFT OF FR 54.2 AND 12 INCHES AFT OF FR 54.2. REMOVED AND REPLACED SEAT TRACK SECTION AT TRACK NR 5 LT BETWEEN FR 54.2 AND FR 58 IAW A310-200 SRM 51-72-10.

Part: WEB — CRACKED (ZONE 100) · airframe 47,377 hrs · 21,808 cycles

AVIONICS COMPARTMENT RT UPPER FLOOR STRUCTURE BETWEEN FR 9 AND 10 INTERCOSTAL WEB HAS 1 INCH CRACK AT FWD LOWER CORNER. REMOVED AND FABRICATED WEB IAW DWG A553610270. INSTALLED WEB IAW A310-200 SRM 51-40- 21.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 47,377 hrs · 21,808 cycles

MAIN CABIN FLOORBEAM FR 14 LT, Y1600 HAS CORROSION ON TOP CAP. .030 IN DEEP BY 2.50 IN BY .500 IN. REMOVED LEVEL 1 CORROSION. REWORKED AREA AFTER CORROSION REMOVED AND INSTALLED FLOOR CROSSBEAM FLANGE REPAIR AT FR 14 LT, Y1600 IAW A310 SRM 53-12-15, FIG 206, SHEET 3, PAGE 224.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 47,377 hrs · 21,808 cycles

MDCC SEAT TRACK 2R HAS SCALLOPS BROKEN OUT AT FR 60 REMOVED DAMAGED TRACK AND REPLACED WITH NEW TRACK SECTION IAW SRM 53-10-16 FIG 202.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 47,377 hrs · 21,808 cycles

MDCC SEAT TRACK 4R HAS ELONGATED SCALLOPS AT FR 62. REPLACED SEAT TRACK 4R FROM FR 62 TO FR 65 IAW SRM 51-23-10 AND 51-75-10 AND SRM 53-10-16 FIG 208 SHEET 1. INSTALLED REPLACEMENT SEAT TRACK AND SPLICED IAW SRM 53-10-16 FIG 208.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 47,377 hrs · 21,808 cycles

MAIN DECK CARGO COMPT SEAT TRACK 2R HAS SCALLOPS BROKEN OUT AT FR 62 REMOVED DAMAGED TRACK AND REPLACED WITH NEW TRACK SECTION IAW SRM 53-10-16 FIG 202.

Part: SKIN — DENTED (ZONE 100) · airframe 47,377 hrs · 21,808 cycles

LOWER FUSELAGE SKIN BETWEEN FR 57/58 AND FR 59,STRINGER 42 RT HAS 1 DENT MEASURING 2.00 INCH BY 1.00 INCH BY .038 IN DEEP. EVALUATED AND DETERMINED DENT TO BE OUT OF LIMITS IAW SRM 53-10-00,TABLE 102. REMOVED DAMAGED SECTION OF SKIN AND INSTALLED EXTERNAL SKIN DOUBLER REPAIR BETWEEN FR 57/58 AND FR 59, STRINGERS 41 RT AND STRINGER 43 RT IAW SRM 53-17-15, FIG 205, PAGE 225/226.

Part: FITTING — LOOSE (BLEED AIR SYS) · airframe 47,164 hrs · 21,659 cycles

ON CLIMB-OUT PASSING 15000 FT GOT NR 2 BLEED FAULT. COMPLIED WITH ECAM, RETURNED TO DFW. FOUND SENSE LINE FOR NUMBER 2 ENG PNEU PRESSURE REGULATOR LOOSE AT PYLON FITTING SECURED FITTING. PERFORMED FUNCTIONAL CHECK OF THE NUMBER 2 ENG BLEED REF MM 36-11-00-6.

Part: UNKNOWN — UNKNOWN (FUEL SYS) · airframe 46,085 hrs · 21,034 cycles

IN CRUISE FLT, LT INNER FUEL GAUGE READ 5 K LESS THAN RT. RAN CK LIST RESET SYSTEM C/B'S IAW QRH STILL SHOWED IMBALANCE. DIVERTED DUE TO SUSPECTED LEAK. WING DIPPED ON FINAL AS IF RIGHT WING WAS HEAVY. GAUGES SHOWED 6000 LB LOSS IN LEFT INNER IN CHOCKS. CK'D STICKS ON LT AND RT INNER LT INNER APPROX 5000 LESS THAN RT. TESTED FUEL QTY SYS PER M/M 28-42 -00-05 FAULTS LA,111,122 ,952. FUELED A/C TO 40000 WHILE TAKING READING LT INNER JUMPED 5000 HIGHER WITH NO FUEL BEING ADDED AND TOTALIZER SHOWED 45000 TRANSFERRED FUEL OUT OF LT INNER AND FUELED LT INNER TO KNOWN QTY FROM RT INNER. RAN ALL PUMPS AND CK'D FOR MIGRATION NONE NOTED FUELED LT INNER TO 26000 AND CK'D FOR LEAKS. NONE NOTED.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

STRUCTURES-A300/A310 REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. CABIN FLOOR TRACK Y-450 WORN BETWEEN FRAMES 60 AND 61. REPAIRED PER SRM 53-10-16 FIG 208 SHEET 1. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR".

Part: SKIN — DENTED (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. DENT BETWEEN FS 64-65 AND BETWEEN STRINGER 40-41 RT REPAIRED PER SRM 53-10-12 FIG 226 SHEET 2. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR".

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

STRUCTURES-A300/A310 REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. CABIN FLOOR TRACK Y-952 WORN BETWEEN FRAMES 60 AND 61 REPAIRED PER SRM 53-10-16 FIG 201 SHEET 1.

Part: SKIN — DENTED (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. DENT BETWEEN FS 64-65 AND BETWEEN STRINGER 42-43 RT SEE N462 FOR RDF DATA WAS REPAIRED PER SRM 53-10-12 FIG 226 SHEET 2 SPECIFIC MAINTENANCE REQUIREMENTS. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR".

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

STRUCTURES-A300/A310 REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. CABIN, FLOOR TRANSVERSAL BEAM BETWEEN TRACKS Y-450 AND Y-953 AT FRAME 43 FOUND CRACKED REPLACED PER AMM 53-10-00.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

STRUCTURES-A300/A310 REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. CABIN FLOOR,TRANSVERSAL BEAM BETWEEN TRACKS Y-450 AND Y-953 AT FRAME 44 FOUND CRACKED REPLACED PER AMM 53-10-00.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

STRUCTURES-A300/A310 REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. CABIN FLOOR TRACK Y-450 WORN BETWEEN FRAMES 60 AND 61. REPAIRED PER SRM 53-10-16 FIG 208 SHEET 1.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

STRUCTURES-A300/A310 REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. CABIN, FLOOR TRACK Y-952 WORN BETWEEN FRAMES 60 AND 61. REPAIRED PER SRM 53-10-16 FIG 208 SHEET 1. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR".

Part: SKIN — MISREPAIRED (T/E FLAP) · airframe 45,297 hrs · 20,618 cycles

STRUCTURES-A300/A310 REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. BY: 067708 (N252) PREVIOUS COMPOSITE REPAIR FOUND LOCATED ON RT INB FLAP, UPPER SURFACE OUTB END, FLAP RIB 19. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED PER FEDEX EA 6-5710-104670. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR".

Part: SKIN — MISREPAIRED (PAX DOOR) · airframe 45,297 hrs · 20,618 cycles

PREVIOUS REPAIR FOUND LOCATED ON R1 DOOR LOWER FWD END FS 1187 AND FR 14A EXTERNAL DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 52-10-00 FIG. 204 EPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: SKIN — MISREPAIRED (PAX DOOR) · airframe 45,297 hrs · 20,618 cycles

PREVIOUS REPAIR FOUND LOCATED ON R1 DOOR LOWER AFT END FS 1260 AND FR 16 EXTERNAL DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 52-10-00 FIG. 204 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: FITTING — UNKNOWN (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

PREVIOUS REPAIR FOUND LOCATED RT FS 2105-2208, FS 38(1)-38(2) AND STR 49-55, EXTERNAL DOUBLER AROUND AFT AIR CONDITIONING ACCESS HOLE. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. FITTING REPLACED PER SRM 51-72-10, DRWG R53706164 AND SRM 51-40-21. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR

Part: SKIN — DAMAGED (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

PREVIOUS REPAIR FOUND LOCATED LT FS 1019-1061, FS 11-12 AND STR 27-29 EXTERNAL DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR COVERED BY RAS/AS/185/97. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR".

Part: SKIN — MISREPAIRED (RT WING) · airframe 45,297 hrs · 20,618 cycles

STRUCTURES-A300/A310 REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. PREVIOUS COMPOSITE REPAIR LOCATED ON RT WING LEADING EDGE, WS 1182, RIB 19, REPAIR LOCATED BETWEEN NUMBER 2 AND 3 SLAT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EVALUATED AND FOUND NOT TO CONFORM SRM REPAIR NEW REPAIR PERFORMED PER FEDEX EA 6-5710-104672. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MINOR ".

Part: STRINGER — MISREPAIRED (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. PREVIOUS STRINGER REPAIR FOUND IN AFT PIT, LT SIDE, FS 3437-3484, FS 64 AND STRINGER 56. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR EVALUATED AND FOUND NOT TO SRM. REPAIRED PER SRM 53-10-14 FIG 201A. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR".

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

PREVIOUS REPAIR FOUND LOCATED RT FS 1236-1260, FS 15A-16 AND STRINGER 39-40 EXTERNAL DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM. REPAIR , NEW REPAIR ACCOMPLISHED PER SRM 53-12-12 FIG 201. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR".

Part: SKIN — MISREPAIRED (RT ELEVATOR) · airframe 45,297 hrs · 20,618 cycles

STRUCTURES-A300/A310 REPAIR IDENTIFICATION AND SUPPLEMENTAL MAINTENANCE COMPLY WITH EO 6-5100-7-5000 REV NR B POS PT1. PREVIOUS COMPOSITE REPAIR FOUND LOCATED ON RT ELEVATOR LOWER SURFACE AFT OF NUMBER 5 ATTACH POINT. REPAIR REQUIRES EVALUATION REPAIR EVALUATED AND NOT FOUND TO CONFORM TO AN EXISTING SRM. NEW REPAIR ACCOMPLISHED PER FEDEX EA 6-5510-104671. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MINOR".

Part: SEAT TRACK — MISREPAIRED (FUSELAGE) · airframe 45,297 hrs · 20,618 cycles

PREVIOUS MCD SEAT TRACK REPAIR FOUND LT SIDE, FS 3104-3181, FS 54.3-55/58 AND Y195.9. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM PER SRM. REPLACED SEAT TRACK PER SRM 51-72-10. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR".

Part: ENGINE — LEAKING (NR 2) · airframe 44,100 hrs · 19,990 cycles

DURING CRUISE, NR 2 ENGINE TRIM LIGHT/ECAM ILLUMINATED NR 2 ENGINE, NOTICED N1 AND N2 INOP, OIL QUANTITY ZERO, OIL PRESSURE IN YELLOW, 14 PSI. ECAM ALERT FOR ENGINE SHUTDOWN, OIL PRESSURE ZERO. FLIGHT TIME ON ONE ENGINE -2 5 MINUTES. HYD LOW PRESS LIGHTS AND SPOILER FAULT LIGHTS DID NOT ILLUMINATE, ALTHOUGH ENGINE SYSTEM PAGE ON ECAM SHOWED ZERO OIL PRESSURE. REMOVED AND REPLACED NR 2 ENG PER ENG CHANGE WORK CARDS.

Part: SKIN — DAMAGED (RT WING) · airframe 43,372 hrs · 19,592 cycles

ELONGATED HOLES IN THE RT LWR WING SKIN AT 1 FASTENER HOLE FOR MANHOLE COVER 650KB.

Part: DISPLAY — INTERMITTENT (COCKPIT) · airframe 42,959 hrs · 19,369 cycles

ON TAKEOFF ROLL BOTH SGU`S WENT BLANK AT APPROX 85 KNOTS, THEN REAPPEARED AT 105-110 KNOTS THEY WENT BLANK AGAIN EXCEPT FOR SYSTEM DATA NOT AVAILABLE CAUTION ON EACH DISPLAY, SGU'S HAD BEEN RESET ON PRE FLIGHT DUE TO SAME PROBLEM T/O AT 110KNOTS WITH NO ADDITIONAL PROBLEMS. REPLACED SDAC IAW A310 AMM CH 31-55-22-4. OPS CKS GOOD.

Part: FUEL TANK — CRACKED (ZONE 500) · airframe 42,657 hrs · 19,233 cycles

AT BLOCK IN, FOUND LT OUTER WING FUEL TANK LEAKING FROM BOTTOM OF WING JUST OUTBD OF RIB NR 20, JACK 05, TRACK 08. FUEL COMING OUT OF DRAIN HOLE ON BOTTOM OF WING JUST FWD OF OVAL ACCESS PANEL. MX FOUND LT NR 8 SLAT TRACK CANISTER TO HAVE APPROX 1 - 2 INCH CRACK. AFTER FURTHER INVESTIGATION A SLAT TRACK ROLLER WAS FOUND IN AREA. IT IS BELIEVED THAT THE FREE MOVING ROLLER CAUSED THE DAMAGE TO THE CANISTER. INSPECTION OF SLAT SYSTEM REVEALED NO MISSING ROLLER AND APPEARS THAT ROLLER WAS IN AREA FROM PREVIOUS MAINTENANCE TO SLAT SYSTEM. CANISTER HAD WELD REPAIR ACCOMPLISHED IN SHOP AND WAS REINSTALLED ON A/C.

Part: ANGLE — DAMAGED (FUSELAGE) · airframe 42,467 hrs · 19,125 cycles

AFT PRESSURE BULKHEAD FR80 OUTER ANGLE LABELED LEFT NR 8 HAS INCOMING ELONGATED HOLES. FABBED REPLACEMENT ANGLE P/N A5398182321000 IAW ACFT DRAWING A53981823 ANGLE TO BE INSTALLED ON N CARD N00035 REF SDR 04-1346.

Part: PRESSURE BLKHD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,467 hrs · 19,125 cycles

AFT PRESSURE BULKHEAD FR 80 LEFT WEB ASSY HAS AREAS OF EXCESSIVE CORROSION. FABRICATED NEW WEB IAW AIRBUS DRWG A53981860, INSTALLED NEW WEB ASSY IAW A310 SRM 51-40-21 ON ATTACH ANGLE. WORK PERFORMED ON NRC N00269.

Part: WEB — DAMAGED (FUSELAGE) · airframe 42,467 hrs · 19,125 cycles

WEBBING AT FRAME 80 HAS THREE ELONGATED HOLES COMMON TO STRINGER 57. .300 X .280 HOLE WITH ED OF .250 FROM CENTER. ELONGATED HOLE .225 X .190. ELONGATED HOLE .225 X .180.

Part: PRESSURE BLKHD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,467 hrs · 19,125 cycles

REAR PRESSURE BULKHEAD FWD FACE ON THE AFT SIDE OF FR 82 FROM S38L TO S38R HAS AREAS OF CORROSION. LEVEL 2 CORROSION. REF N CARD N00035. COMPLIED WITH EA 6-5310-78353 PT1

Part: FITTING — DAMAGED (FUSELAGE) · airframe 42,467 hrs · 19,125 cycles

STRINGER 57 O/B END FITTING AT FRAME 80 HAS TWO ELONGATED HOLES. .300 X .280. .225 X .190. FABBED REPLACEMENT PART IAW AIRBUS DWG A53981973 ANGLE (END FITTING). ANGLE INSTALLED ON WORK CARD NON ROUTINE N00035.

Part: ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,467 hrs · 19,125 cycles

AFT PRESSURE BULKHEAD FR 80 INNER ANGLE {LABELED NR 3} HAS EXFOLIATED CORROSION. REPLACED ANGLE ON FR 80 INNER ANGLE NR 3 LT IAW A310 SRM 51-72-10 AND 53-19-17.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 42,467 hrs · 19,125 cycles

STRINGER 57 I/B END FITTING AT FRAME 80 HAS TWO ELONGATED HOLES. .300 X .200. .225 X .190. NO ACTION REQUIRED OLD PART IS BEING REPLACED AT STR 57 FR 80 REF DRAWING R53970100 ITEM 40 PART A5398020620300 REF N00035 FOR INSTALLATION OF END FITTING.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 42,467 hrs · 19,125 cycles

AFT PRESSURE BULKHEAD FR 80 INNER ANGLE LABELED LT NR 2 AND SHIM ARE CORRODED [EXFOLIATED]. REPLACED ANGLE AND SHIM ON FR 80 INNER ANGLE LT NR 2 IAW A310 SRM 51-72-10 AND 53-19-17.

Part: BULKHEAD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,467 hrs · 19,125 cycles

AFT PRESSURE BULKHEAD FR 80 RIGHT WEB ASSY HAS AREAS OF CORROSION. INSTALLED NEW WEB ON ATTACH ANGLE IAW SRM 51-40-21. WORK PERFORMED ON NRC N00272.

Part: BULKHEAD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,467 hrs · 19,125 cycles

REAR PRESSURE BULKHEAD FWD FACE ON THE AFT SIDE OF FR 80/82 FROM S38L TO S38R HAS AREAS OF CORROSION. COMPLIED WITH EA 6-5310-78353 PT1.

Part: SPAR — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 42,467 hrs · 19,125 cycles

RIGHT HORIZONTAL UPPER TRAILING EDGE SPAR I/B OF RIB 5 HAS LEVEL 2 CORROSION, APPROX 6 INCHES L X .800 INCH W, NOTE: PREVIOUS STRAP REPAIR INSTALLED I/B OF DAMAGE TO RIB 3. REMOVED PREVIOUS REPAIR, REMOVED CORROSION, MAT'L LOSS GREATER THAN 10 PERCENT, FABRICATED NEW REPAIR ANGLE. INSTALLED NEW REPAIR ANGLE AND TREATED, PRIMED AND APPLIED TOP COATING IAW A310 SRM 55-11-21, 51-23-20, AND 51-74-10.