N411FE

Part: SWITCH — FAILED (NLG) · airframe 36,582 hrs · 21,182 cycles

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. WHEN JACKED LT GEAR BOGIE WOULD NOT TILT NOSE FWD WITHOUT STANDING ON IT. FOUND LT PITCH DAMPNER WAY UNDERSERVICED WITH NR 2. SERVICED IAW MM 12-12-32-00. ALSO LUBED ALL GEAR DUE TO BEING VERY DRY IAW MM 12-22-32-00. PERFORMED GEAR SWING IAW MM 32-31-00-5, ON SYS 1 OR 2, NO NOSE DOWN GREEN ARROW OR UNLOCK LIGHT. ALL OTHER GEAR NORMAL. CONTINUED. SWAPPED CONNECTORS 40GBA AND 79GBA AND PROBLEM FOLLOWS. R & R NR 1 SYS BODY ASSY AND SWITCH 40GB IAW MM 32-00-00-04. BOTH SYS OPERATE NORMAL, PERFORMED GEAR SWING IN BOTH SYS 1 AND 2 IAW 32-31-00-5. OPS CHECK NORMAL.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,500 hrs · 21,133 cycles

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 NR 4. HEAT TREAT THE REPAIR PARTS FROM 2024-0 TO 2024-T42 CONDITION IAW SRM51-25-00. DRILL FASTENER HOLES AND DEBURR IAW SRM 51-40-40. APPLY ALODINE TO THE REPAIR PARTS AND REPAIR AREA IAW SRM51-21-10 AND SRM51-23-00 APPLY PAINT. INSTALL THE REPAIR PARTS IAW SRM 51-40-21. APPLY SEALANT TO THE REPAIR AREA IAW SRM 51-76-10 AND APPLY PAINT IAW SRM51-23-00. THIS REPAIR MUST BE INSPECTED IAW SRI 53-13-12-2-001-00 AND SRI 53-13-12-2-002-00.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,500 hrs · 21,133 cycles

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 REPAIR NR 4. HEAT TREAT THE REPAIR PARTS FROM 2024-0 TO 2024-T42 CONDITION IAW SRM51-25-00. DRILL FASTENER HOLES AND DEBURR IAW SRM51-40-40. APPLY ALODINE TO THE REPAIR PARTS AND REPAIR AREA IAW SRM51-21-10 AND SRM51-23-00 APPLY PAINT. INSTALL THE REPAIR PARTS IAW SRM51-40-21. APPLY SEALANT TO THE REPAIR AREA IAW SRM51-76-10 AND APPLY PAINT IAW SRM 51-23-00. THIS REPAIR MUST BE INSPECTED IAW SRI53-14-12-2-001-00 AND SRI53-14-12-2-002-00.

Part: FRAME — DAMAGED (ZONE 200) · airframe 36,500 hrs · 21,133 cycles

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 6-5310-141632.

Part: FRAME — GOUGED (ZONE 200) · airframe 36,500 hrs · 21,133 cycles

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.

Part: BEAM — CRACKED (ZONE 200) · airframe 36,500 hrs · 21,133 cycles

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 RELATED PARTS IAW SRM51-40-21.

Part: HOUSING — BROKEN (SWITCH) · airframe 36,271 hrs · 21,010 cycles

ON ARRIVAL INTO MEM, THE NOSE GEAR INDICATED UNSAFE ON BOTH SYSTEM 1 AND 2. COMPLIED WITH QRH AND USED THE MLG GRAVITY EXTEND CHECKLIST. WHEN THAT WAS COMPLETED THE UNSAFE WARNING REMAINED. THEN WENT DOWNSTAIRS TO VISUALLY CHECK. IT INDICATED DOWN AND LOCKED SO WE LANDED WITH THAT INDICATION FOUND SWITCH 40 GB HOUSING BROKEN. REMOVED REPLACED HOUSING AND SWITCH IAW MM 32-00-00-4. NEEDS GEAR SWING AND OPS CHECK. COMPLIED WITH NOSE GEAR SWING IAW MM 32-31-00-5. ALL INDICATIONS NORMAL ON FLIGHT DECK. OK FOR SERVICE.

Part: HOUSING — CRACKED (MLG SWITCH) · airframe 36,271 hrs · 21,010 cycles

ON ARRIVAL, NOSE GEAR INDICATED UNSAFE ON BOTH SYSTEM 1 AND 2. COMPLIED WITH QRH AND USED MLG GRAVITY EXTEND CHECKLIST. WHEN COMPLETED UNSAFE WARNING REMAINED, VISUALLY CHECKED. INDICATED DOWN AND LOCKED. LANDED WITH INDICATION. FOUND SWITCH 40 GB HOUSING BROKEN. REMOVED & REPLACED HOUSING AND SWITCH IAW MM 32-00-00-4. COMPLIED WITH NOSE GEAR SWING IAW MM 32-31-00-5. ALL INDICATIONS NORMAL. OK FOR SERVICE.

Part: TRANSMITTER — LEAKING (HYD SYSTEM) · airframe 34,927 hrs · 20,223 cycles

DURING CRUISE, GREEN HYDRAULICS SHOWED "0" PRESSURE AND "LO RSVR QUANTITY" ON ECAM. QUANTITY CONFIRMED ON OVERHEAD PANEL. DURING MANUAL GEAR EXTENSION, QUANTITY RETURNED TO GREEN BAND (BELOW TOP HAT). FOUND HYD PRESSURE TRANSMITTER IN LT WHEEL WELL LEAKING. REMOVED AND REPLACED LT PRESSURE TRANSMITTER (GREEN SYS). RESERVICED GREEN SYSTEM AND WORKED AIR OUT OF SYSTEM. RESTORATION TO NORMAL CONFIGURATION CHECKS GOOD.

Part: TRANSMITTER — MALFUNCTIONED (HYD SYSTEM) · airframe 34,927 hrs · 20,223 cycles

DURING CRUISE, GREEN HYDRAULICS SHOWED "0" PRESSURE AND "LO RSVR QUANTITY" ON ECAM. QUANTITY CONFIRMED ON OVERHEAD PANEL. DIVERTED TO ATL. DURING MANUAL GEAR EXTENSION, QUANTITY RETURNED TO GREEN BAND (BELOW TOP HAT). INSTALLED ALL THREE GEAR PINS IN AIRCRAFT. FOUND HYD PRESSURE TRANMITTER IN LT WHEEL WELL LEAKING. REMOVED AND REPLACED LT PRESSURE TRANMITTER (GREEN SYS). RESERVICED GREEN SYSTEM AND WORKED AIR OUT OF SYSTEM A300-200 M/M 29-32-13-4. SDR PREVIOUSLY SUBMITTED UNDER TRACKING #07-3392. DISREGARD THIS SDR-ADMINISTRATOR.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 34,616 hrs · 20,031 cycles

PREVIOUS REPAIR LOCATED ON L-SIDE FUSELAGE SKIN BETWEEN FR 21-22 BETWEEN STR 34-36 LT AT LAP SEAM HAS AN EXTERNAL DOUBLER MEASURING 6.25 BY 9 IN REPAIR DETERMINED NOT TO BE IAW A310-200 SRM 53-10-12 FIG 205, REPAIR REWORKED IAW A310-200 SRM EA 6-5330-110187.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 34,616 hrs · 20,031 cycles

PREVIOUS REPAIR LOCATED ON R/SIDE FUSELAGE SKIN BETWEEN FR 66 TO 67 BETWEEN STR 35TO 38 RT HAS AN EXTERNAL REPAIR DOUBLER MEASURING 8.8 BY 11.9. REPAIR REVIEWED AND FOUND NOT TO BE IAW A310-200 SRM 53-10-12 FIG 226 SHEET 2. REWORKED REPAIR IAW A310-200 SRM 53-10-12, FIG 226 SHEET 2 REF N00503.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 34,578 hrs · 20,000 cycles

1 CRACK EXIST IN FLOORBEAM VERTICAL STIFFENER AT FR 36 BETWEEN SEAT TRACK L4 AND L5, MEASURING 0.450" P/N 537B1041000 A310-200 AMM 53-10-15-6. REMOVED 1 CRACK IN FLOORBEAM VERTICAL STIFFENER AT FRAME 36 BETWEEN SEAT TRACK L4 AND L5 IAW A310-200 SRM 53-10-15 FIG 201. FABRICATED AND INSTALLED REPAIR IAW A310-200 SRM 53-10-15 PG 201.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 34,578 hrs · 20,000 cycles

1 CRACK FOUND .75" IN UPPER SUPPORT LEG ON AFT SIDE OF FLOORBEAM FR 58 BETWEEN SEAT TRACK 4L AND 5L EXTENDING INTO FLOORBEAM WEBBING UNDER CLS ADAPTER IAW A310-200 AMM 53-16-11-6. REMOVED DAMAGED AREA AND REPAIRED IAW AB DWG R53270150 AND EA 6-5310-107708.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 34,578 hrs · 20,000 cycles

1 CRACK EXIST IN FLOORBEAM VERTICAL STIFFENER AT FRAME 36 BETWEEN SEAT TRACK L2 AND L3 MEASURING .5" REF R537B1041000 A310-200 AMM 53-10-15-6. REMOVED CRACK PER A310 SRM SUPP 53-10-15 FIG 201. NDT C/W PER NTM 51-10-08, NO CRACK INDICATIONS NOTED. FABBED REPAIR PARTS PER A310 SRM SUPP 53-10-15, FIG 201. PROTECTED SURFACES WITH ALODINE, PRIMER, AND TOPCOAT PER A310 SRM 57-75-10. INSTALLED REPAIR COMPLETE PER A310 SRM SUPP 53-10-15, FIG 201.

Part: TRACK — MISREPAIRED (FUSELAGE) · airframe 34,578 hrs · 20,000 cycles

PREVIOUS REPAIR LOCATED ON AFT CARGO ROLLER TRACK LEFT NR 2 HAS A 9 INCH LONG REPAIR SECTION WITH 2 REPAIR ANGLES ON THE OUTBD SIDE MEASURING 7 INCH LONG EACH BETWEEN FRAMES 54.3 TO55/58 PREVIOUSLY INSTALLED REPAIR WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-15 FIG 203. REMOVED AND REINSTALLED 2 EACH FLOOR PANELS PER A310-200 AMM 53-10-33-4. REMOVED AND REPLACED 2 EACH REPAIR ANGLES PER A310 SRM 53-10-15 FIG 203.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 34,578 hrs · 20,000 cycles

FORWARD CARGO COMPARTMENT, FLOORBEAM (C25) FORWARD FACE OF BEAM LOCATED BETWEEN R2 AND R3 SEAT TRACK HAS A .400 INCH CRACK IN VERTICAL STIFFENER. REPAIRED FLOORBEAM IAW A310/200 SRM SUPPLEMENT 53-10-15. REMOVED AND REINSTALLED FLOORBOARD IAW A310/200 AMM SUPPLEMENT 53-10-21-4.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 34,578 hrs · 20,000 cycles

FWD CARGO COMPARTMENT, OVER HEAD FLOORBEAM [ C34 ] FWD FACE OF BEAM , LOCATED BETWEEN L4 AND L5 SEAT TRACK HAS A 0.425 INCH CRACK IN VERTICAL STIFFENER. REMOVED AND REINSTALLED FLOOR BOARD 231KF AND 231QF TO FOM REPAIR IAW A310-200 AMM 53-10-25-4. REPAIRED FLOORBEAM C34 BETWEEN L4 AND L5 SEAT TRACK IAW A310-200 SRM 53-10-15.

Part: CONTROL UNIT — MALFUNCTIONED (BRAKE SYS) · airframe 34,320 hrs · 19,878 cycles

ON CLIMB-OUT, AUTO BRAKE FAIL LIGHT CAME ON, LIGHT STAYED ON UNTIL LEVEL OFF AND THEN AFTER A PERIOD OF TIME THE LIGHT WENT OUT. LIGHT THEN CAME ON AFTER A PERIOD OF TIME. CYCLE REPEATED ITSELF OFF AND ON SEVERAL TIMES. PERFORMED BITE TEST ON BSCU FAULT CODE 202 WAS DISPLAYED. REPLACED BSCU IAW AMM 32-42-72-4 BITE TESTED BSCU. NO FAULT CODES DISPLAYED. RT ECAM ALSO DISPLAYED NORMAL ON MTC PANEL BITE TEST. OK FOR SERVICE PREMATURE REMOVAL/INSTALLATION OFF MFG C20101610-003.

Part: PITOT TUBE — DIRTY (PITOT/STATIC SYS) · airframe 33,866 hrs · 19,655 cycles

RIGHT AFTER ROTATION BOTH ATS LEVERS DROPPED OFF. ADC FAILED ON CAPT SIDE SWITCHED OVER TO OTHER SYSTEM REENGAGED ATS LEVERS AS PER ECAM THROTTLE RETARDED TO IDLE AS SOON AS ATHR BUTTON PUSHED. NO ECAM FOR ADC. ALSO NR 1 FLT DIRECTOR FAILED. CAPTS ALTIMETER OF FLAG INTERMITTENT IN VIEW. REMOVED AND REPLACED CAPT ALTIMETER IAW MM 34-12-21-4. OPS CHK NORMAL. PERFORMED FLUSHOUT OF NR 1 ADC PITOT TUBES FOUND DEBRIS IN PITOT TUBE AND ASSOCIATED TUBING BACK TO ADC. REMOVED AND REPLACED NR 1 ADC PER M/M 34-11-34-4. PERFORMED PITOT LEAK CK PER M/M 34-10-00-5.

Part: ADC — FAILED (E/E BAY) · airframe 33,866 hrs · 19,654 cycles

JUST AFTER ROTATION BOTH ATS LEVERS DROPPED OFFLINE AND WOULD NOT RESET. YAW DAMP DROPPED OFF, WOULD NOT RESET. CAPTS PFD, ADC FAILED. SWITCHED OVER TO F/O SYSTEM. HAD NUMEROUS AIRSPEED WINDSHEAR VMO MMO WARNINGS EVEN THOUGH USING STBY SYSTEMS. AT THAT POINT APPEARED TO BE GETTING GOOD AIRSPEED INFORMATION ON FO'S SYSTEM. PER MTP PANEL FAULTS FOUND NR 1 IRS, ADS, FAC, TCC, FMC, AND PMC. FOUND NR 1 ADC DOA. PERFORMED BITE TEST AND ADC RETURNED ON PFD. REMOVED AND REPLACED NR 1 ADC, 1 FAC PER M/M 22-25-12-4, OPS CK NORMAL PERFO SWAPPED NR 1 FCC'S = NORMAL PER MTP PANEL. REMOVED AFS/LAND TEST = LAND FAQILS = NR 1 FCC FAIL SWAPPED NR 1 FCC'S = PERFOMED AFS/LAND TEST OPS CK NORMAL PER MTP PANEL.

Part: COMPUTER — FAULTED (NR 1 FEEL) · airframe 33,597 hrs · 19,535 cycles

ON T/O AT LAX, DID A RTO AT 90 KTS THE ECAM ALERT WAS BOTH PITCH 1/2 AND BOTH RUDDERS 1/2 FAULTED. REMOVED AND REPLACED NR 1 AND NR 2 FEEL LIMITATION COMPUTERS PER M/M 27-23-26-4. OPS CK'S NORMAL. PERFORMED AFTER BRAKE OVERHEAT INSP REF MM 05-51-16-0-01. A/C OK TO CONTINUE.

Part: INDICATOR — SMOKE (RUDDER TRIM) · airframe 33,161 hrs · 19,292 cycles

N CRUISE BURNING SMELL IN COCKPIT, DIVERTED AND LANDED. STRONGEST SMELL FROM THROTTLE QUADRANT AREA, FIRE CREW TEMP DETECTOR SHOWED HIGHEST HEAT IN THAT LOCATION. NEVER ANY VISIBLE SPARKS OR FLAMES, SOME SMOKE. INSPECTED THROTTLE QUADRANT AREA AND FOUND THE RUDDER TRIM INDICATOR BURNED UP. NO OTHER DAMAGE FOUND IN THE AREA. REMOVED AND REPLACED THE RUDDER TRIM INDICATOR. OP CHECK NORMAL PER MM 27-22-22-4G 27-12-00, 27-27-00. PREMATURE REMOVAL/INSTALLATION OFF MFG 35-930-1001.

Part: ACCESS PANEL — DAMAGED (RT WING) · airframe 32,683 hrs · 19,002 cycles

ACCESS PANEL 650GB HAS 1 ELONGATED HOLE, COMPLIED WITH EA6-5710-90863.

Part: ACCESS PANEL — DAMAGED (WING) · airframe 32,683 hrs · 19,002 cycles

ACCESS PANEL 650 FB HAS 1 ELONGATED HOLE, COMPLIED WITH EA6-5710-90863.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,894 hrs · 18,536 cycles

MDCC SEAT TRACK L4 FRAME 74-80 HAS 5EA CORRODED AREAS. REPAIRED SEAT TRACK BY SPLICING IAW A310 SRM 51-22-00, 51-40-21 AND 53-10-16.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,894 hrs · 18,536 cycles

AFT CARGO COMPT FS 63 FLOOR STRUCTURE, ON LEFT SIDE 3EA AREAS OF CORROSION ON TOP SURFACE AND UNDERNEATH FLOOR STRUCTURE. REMOVED AND REPLACED FLOOR STRUCTURE BEAM IAW A310 SRM 51-40-21.

Part: ANGLE — CORRODED (FUSLEAGE) · corrosion level 2 · airframe 31,894 hrs · 18,536 cycles

BULK CARGO COMPT FLOOR STRUCTURE FS 67 2EA AREAS OF CORROSION NOTED ON TOP AND BOTTOM SURFACES. REMOVED AND REPLACED PROFILE ANGLE IAW A310 SRM 51-40-21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,894 hrs · 18,536 cycles

MDCC SEAT TRACK R1 BETWEEN FRAME 73-80 HAS 7EA DISCREPANT AREAS 5EA AREAS THAT ARE CORRODED AND GOUGED AND 2EA AREAS THAT ARE GOUGED. REMOVED AND REPLACED R1 SEAT TRACK FRAME 73-80 IAW A310 SRM 51-40-21 AND SRM 53-10-16.

Part: STRUCTURE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,894 hrs · 18,536 cycles

AFT CARGO COMPT FWD OF FS 54.2 BILGE AREA NOTED SPOT OF CORROSION AROUND THE HOLE PLUG. REPAIRED BILGE AREA IAW EA 6-5330-55370.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,894 hrs · 18,536 cycles

BULK CARGO COMPT FLOOR STRUCTURE FS 65 ON LT SIDE, MID AND RT SIDE AREA NOTED CORROSION ON TOP AND UNDERNEATH SURFACES. REMOVED AND REPLACED BEAM IAW A310 SRM 53-10-15.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 31,894 hrs · 18,536 cycles

MDCC SEAT TRACK SECTION AT R2, BETWEEN FR54 TO 8 INCHES AFT OF FR54.1 HAS DAMAGE TO THE SCALLOP LUGS. (ON EDGES AND BENEATH LUGS) REMOVED DAMAGE AND FOUND TO BE CRACKED IAW SRM 51-73-10. REMOVED AND REPLACED SEAT TRACK IAW SRM 51-40-21.

Part: FLOORBEAM — CORRODED (ZONE 100) · airframe 31,894 hrs · 18,536 cycles

AFT CARGO COMPARTMENT, BETWEEN FR 54 AND 54.2, FLOOR STRUCTURE RT SIDE, 3 AREAS OF CORROSION ON CLIP NUTS HOLE TOP AND UNDERNEATH SURFACE. REMOVED CORROSION IAW A310 SRM 51-74-10, AND FOUND TO BE WITHIN LIMITS IAW A310 SRM 53-10-15, TREATED PRIMED AND TOP COATED IAW A310 SRM 51-75-10.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 31,894 hrs · 18,536 cycles

SEAT TRACK AT FR 36 AFT APPROX 8 INCHES IS GOUGED. BLENDED AREA PER A310 SRM 51-22-00 AND FOUND TO BE OUT OF LIMITS PER A310 SRM 53-10-16. REPAIRED BY REMOVING DAMAGED SECTION OF TRACK AND SPLICING IN A REPAIR SECTION PER A310 SRM 51-40-21 AND 53-10-16.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · airframe 31,894 hrs · 18,536 cycles

BULK CARGO FR 64 FLOOR STRUCTURE ON LT CORNER UNDERNEATH, NOTED CORROSION. REMOVED CORROSION PER A310 SRM 51-74-10 AND FOUND TO BE WITHIN LIMITS PER A310 SRM. TREATED, PRIMED, AND TOP COATED PER A310 SRM 51-23-10.

Part: FLOORBEAM — CRACKED (ZONE 100) · airframe 31,894 hrs · 18,536 cycles

FWD CARGO FLOORBEAM STRUCTURE FR33 NOTED INDICATION OF CRACK. REMOVED DAMAGED AREA IAW A310 SRM 53-10-15, AND REPAIRED BY INSTALLING A DOUBLER IAW A310 SRM 53-10-15.

Part: ADAPTER — CRACKED (ZONE 200) · airframe 31,894 hrs · 18,536 cycles

TRACK ADAPTER AT FR61 Y-450 IS CRACKED APPROX 6 INCHES LONG. REMOVED AND REPLACED TRACK ADAPTER IAW A310 SRM 51-40-21.

Part: FLOORBEAM — CRACKED (ZONE 100) · airframe 31,894 hrs · 18,536 cycles

BULK CARGO COMPT FLOOR STRUCTURE ON FR67 AT RT SIDE CORNER UNDERNEATH NOTED CRACK. REMOVED AND REPLACED BEAM IAW A310 SRM 51-40-21.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 31,894 hrs · 18,536 cycles

SEAT TRACK 0, SECTION BETWEEN FR73 TO FR80 HAS TWO DISCREPANT AREAS. TRACK 0 AT APPROX 12 INCHES AFT FROM FR 77 HAS 2 GOUGES INSIDE OF SCALLOPED AREA. TRACK 0 APPROX 10 INCHES AFT OF FR78 HAS CORROSION ON TOP OF TRACK AND IN SCALLOPED AREA. REMOVED CORROSION IAW SRM 51-22-00 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16. REPAIRED TRACK BY REMOVING DAMAGED SECTION AND SPLICING IN A REPAIR SECTION IAW A310 SRM.

Part: ADAPTER — CRACKED (ZONE 200) · airframe 31,894 hrs · 18,536 cycles

TRACK ADAPTER AT FR61 Y-450 IS CRACKED APPROX 6 INCHES LONG. REMOVED AND REPLACED TRACK ADAPTER IAW A310 SRM 51-40-21.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · airframe 31,894 hrs · 18,536 cycles

BULK CARGO COMPT. FLOOR STRUCTURE, ON RT SIDE FR 66 TO FR 63 CORROSION ON TOP AND BENEATH SURFACE. REMOVED CORROSION IAW SRM 51-70-10 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16. REMOVED AND REPLACED BEAM IAW SRM 51-40-21.**** S/D COMING ****

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · airframe 31,894 hrs · 18,536 cycles

BULK CARGO COMPT. FLOOR STRUCTURE FR66 LT SIDE , MID AND RT SIDE AREA NOTED CORROSION ON TOP AND UNDERNEATH SURFACE. REMOVED CORROSION IAW SRM 51-74-10, AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16. REMOVED AND REPLACED BEAM IAW SRM 51-40-21.**** S/D COMING ****

Part: FAIRING — DENTED (ZONE 400) · airframe 31,894 hrs · 18,536 cycles

NR 1 ENGINE PYLON FAIRING DENTED, FORWARD PYLON TO NACELLE FAIRING. REPAIRED FAIRING BY REFORMING TO ORIGINAL CONTOUR AND INSPECTING USING HFEC PER AIRBUS NTM FOR CRACKS, NO CRACKS WERE NOTED. ALL WORK DONE PER EA 6-5480-73051A PART 3 AND A310 SRM 54-50-00 FIG 201.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 31,894 hrs · 18,536 cycles

DAMAGED SEAT TRACK ADAPTER AT FRAME 61 CENTER LINE REF EA 6-5320-81893. REMOVED AND REPLACED TRACK ADAPTER IAW A310 SRM 51-40-21 AND EA 6-5320-81893. **** S/D COMING ****

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 31,894 hrs · 18,536 cycles

MAIN CARGO DECK AT FRAME 47 BETWEEN TRACKS 1R AND 2R, DUMMY TRACK IS CRACKED. REMOVED AND REPLACED DUMMY TRACK AT FRAME 47 BETWEEN TRACKS 1R AND 2R IAW A310 SRM 51-40-21.**** S/D COMING ****

Part: DUMMY RAIL — CRACKED (FUSELAGE) · corrosion level 2 · airframe 31,894 hrs · 18,536 cycles

MCD AT FR 53 BETWEEN SEAT TRACKS 2L AND 3L, DUMMY TRACK IS CRACKED UNDERNEATH AT T-CAP RADIUS. REMOVED AND REPLACED CROSSBEAM, P/N A5381293420000 IAW A310 SRM 51-40-21.

Part: COALESCER BAG — ODOR (LT & RT A/C PACK) · airframe 31,367 hrs · 18,236 cycles

WHEN T/O POWER WAS APPLIED BOTH PILOTS NOTICED A VERY STRONG OIL BURNING ODOR. REJECTED T/O AT 90 KTS, COMPLETED QRH CHECK LIST AND TAXIED TO GATE. WHEN TAXIING IN POWER ODOR RETURNED. REMOVED AND REPLACED BOTH LT AND RT A/C PACK WATER SEPARATOR COALESCER BAGS IAW A310-200 AMM 21-51-16-3. PERFORMED HIGH POWER RUNS ON ENGINES NR 1 AND NR 2. ALSO ALTERNATED A/C PACKS AND BLEED AIR SOURCES FROM ENGINES IAW A300/A310 JET RUN HANDBOOK, NO OIL ODOR NOTED. OPS CHECK GOOD.

Part: ENGINE — STALLED (NR 1) · airframe 28,398 hrs · 16,645 cycles

NR 1 ENG WILL NOT ACCELERATE IN NORMAL MANOR (REPEAT WRITE UP).

Part: COMPUTER — FAILED (E/E BAY) · airframe 27,815 hrs · 16,403 cycles

AT T/O LOST ADC1, FD1, ATS2, REG1, PITOT HEAT AND TAT, PITCH TRIM. REMOVED AND REPLACED PROX DET PROC UNIT. TEST OK.

Part: CONTROLLER — FAILED (CABIN)

KUL - ON CLIMBOUT, NR 1 PRESSURE CONT FAILED, NR 2 PRESS CONT COULD NOT CONTROL CABIN. IAW ECAM PROCEDURES SELECTED MANUAL CONTROL, UNABLE TO STOP CABIN RATE OF CLIMB/DECENT. CABIN PRESS DISPLAY ON ECAM SHOWED OUTFLOW VALVE NR 1 AFT CYCLING RANDOMLY. EME DESCENT ACCOMP, TURNBACK. SWAPPED NR 1 AND NR 2 AFT OUTFLOW VALVES, PERFORMED AUTO AND MANUAL CONTROL TEST ON BOTH SYS IAW A-310 MM 21-30-00, ALL TEST NORMAL. NR 2 CABIN PRESS SYS CONSIDERED INOP DUE TO OUTFLOW VALVE FLUX. DEFERRED PER MEL 21-44 CONTROL NR 0904005 CAT 'C' EXP 9-14-95, MXP C/W SYS NR 2 REG DEACTIVATED. REMOVED AND REPLACED NR 1 PRESS CONTROLLER AS PRECAUTIONARY MEASURE, CONTROLLER BITE CHECK NORMAL.

Part: CONTROLLER — FAILED (NR 2)

AFTER T/O, A/C TEMP WENT EXTREMELY HIGH AND THE PRESS CONTROLLER NR 2 FAILED. SWITCHED AUTOMATICALLY TO NR 1, WHICH DIDN'T CONTROL THE CABIN EITHER. MANUAL PRESS WAS TRIED AND DIDN'T WORK EITHER. NR 2 AFT, FWD AND MANUAL PRESS VALVES WOULD NOT EVEN MOVE AT TOUCHDOWN. VALVES SEEMED TO BE UNJAMMED, TEMPERATURE WENT TO FULL COLD AND THE COCKPIT FULL OF FOG. CABIN PRESS BEFORE TOUCHDOWN WAS MINUS 3,000 FT EVENTHOUGH LANDING ELEVATION WAS PLUS 20 FT, V/S ZERO AND DELTA PRESSURE WAS BLINKING AND SHOWING 8.6 PSI. REMOVED AND REPLACED NR 1 PRESS CONTROLLER. BITE TESTED BOTH NR 1 AND NR 2 SYS, PERFORMED PRESS SYS FUNCTIONAL CK NORMAL PER MM 21-30-00.

Part: WINDOW — CRACKED (RT COCKPIT)

RIGHT FRONT WINDOW CRACKED, (FIRST OFFICER'S) OUTER PANE CRACKED. REMOVED AND REPLACED FIRST OFFICER WINDOW PER MM 56-11-11 UP TO 3 (8). COMPLETED INSTALLATION PER 56-11-11 PG 420 THROUGH STEP E. SEALANT APPLIED AT OPS CHECKED GOOD.