N421FE
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
97 reports on file, 1998-10-17 – 2009-04-17.
Part: FRAME — DAMAGED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
AFT CARGO COMPARTMENT, EXISTING HOLES WRONGLY DRILLED AT FR 63A, STGR 27 RT. THE FRAME WAS REPAIRED AS PER SRM 53-17-13 FIG 203.
Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
SEAT TRACK WITH CORROSION BTW FR 72 AND FR 73 AT Y0. SEAT TRACK REPAIRED AS PER SRM 53-10-16 FIG 202.
Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
SEAT TRACK WITH CORROSION BETWEEN FR 76 AND FR 77 AT Y1448. SEAT TRACK REPLACED AS PER SRM 51-72-10.
Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
SEAT TRACK WITH SPOTS OF CORROSION BETWEEN FR72-73 AT Y-1456. THE SEAT TRACK WAS REPLACED AS PER SRM 51-72-10.
Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
SEAT TRACK WITH SPOTS OF CORROSION BTW FR 69-FR 70 AT Y-450. SEAT TRACK REPAIRED BTW FR 68-69 AS PER SRM SUPP 53-10-16 FIG 202.
Part: SEAT TRACK — CORRODED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
SEAT TRACK WITH SPOTS OF CORROSION BTW FR58-69 AT Y-953. SEAT TRACK WAS REPAIRED BTW FR 62-63 AND BETWEEN FR 64-65 AS PER SRM 53-10-16 FIG 202.
Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
SEAT TRACK WITH SPOTS OF CORROSION BTW FR 69-71, AT Y-953. THE SEAT TRACK WAS REPLACED AS PER SRM 51-72-10.
Part: SKIN — DAMAGED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
FUSELAGE, EVALUATE BLENDING AT STGR 43 LT BTW FR 20 AND FR 21. SKIN WAS REPAIRED AS PER SRM 53-10-12 FIG 216 SHEET 1.
Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
N1322 AFT CARGO COMPT - FLOORBEAM WITH CORROSION AT FR 63 AND BTW 44-55 LH. THE BEAM WAS REPLACED IN ACCORDANCE WITH 51-72-10.
Part: SEAT TRACK — WORN (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
SEAT TRACK WITH WEAR BETWEEN FR62-63 AT Y0. SEAT TRACK REPAIRED BTW FR 62 AND FR 63 AND BETWEEN FR 64 AND FR 65 AS PER SRM SUPP 53-10-16 FIG 202.
Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
SEAT TRACK WITH CORROSION AND WEAR BETWEEN FR 54.2 AND FR 58 AT Y450. THE RELEVANT SEAT TRACK WAS REPLACED AS PER SRM 51-72-10.
Part: HINGE FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
AFT CARGO DOOR HINGE FITTING WAS FOUND WITH CORROSION AT FRAME 62. THE FITTING WAS REPAIRED AS PER FEDEX EA 6-5310-129288.
Part: HINGE FITTING — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
AFT CARGO DOOR HINGE FITTING WAS FOUND WITH CORROSION AT FRAME 63. THE FITTING WAS REPAIRED AS PER EA 6-5310-129288.
Part: ROLLER TRACK — CORRODED (FUSELAGE) · airframe 44,932 hrs · 16,897 cycles
TRACK AT ROLLERS LT SIDE BTW FRAMES 54.2 TO 55 AT STGR 43 WITH CORROSION. ROLLER TRACK REPAIRED AS PER SRM 53-10-15 FIG 203.
Part: FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
RT WING FLAP OTBD, FITTING AT BUSHINGS OF NR 4 TRUNNION WITH CORROSION. THE CORROSION WAS BLENDED AS PER EA 6-5710-127419.
Part: SKIN — CORRODED (CENTRE WING BOX) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
CENTER WING BOX LOWER SKIN EXTERNAL SURFACE FOUND WITH SEVERAL SPOTS OF CORROSION - REFER TO EA6-5710-129280 FOR DETAILS. REPAIR WAS ACCOMPLISHED AS PER EA 6-5710-129280.
Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
ZONE 100 - FUSELAGE - PREVIOUS REPAIR AT FLOORBEAM LOCATED AT FR 55/58 AT Y-1200. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF IT WAS ACCOMPLISHED USING FAA APPROVED DATA. THE REPAIR WAS REMOVED BECAUSE THE FLOORBEAM WAS REPLACED AS PER THE SRM 51-72-10 DUE TO CORROSION.
Part: CROSSBEAM — CRACKED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
CROSSBEAM AT FR36 CRACKED AT Y-953. CROSSBEAM AT FR 36 WAS REPAIRED AS PER SRM SUPP 53-10-15 FIG 201 SHEET2A.
Part: BEAM — CORRODED (PAX DOOR) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
RT FWD PAX DOOR, SPOTS OF CORROSION AT BEAM 3. BEAM 3 WAS REPLACED AS PER SRM 51-72-10.
Part: BEAM — CORRODED (ZONE 800) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
RT FWD PAX DOOR - SPOTS OF CORROSION AT BEAM 3. BEAM 3 WAS REPLACED AS PER SRM 51-72-10.
Part: TRACK — CORRODED (ZONE 400) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
NR 1 PYLON, RIB 18, LUG ATTACHMENT WING TO PYLON WITH CORROSION AT ATTACHMENT ROLLER TRACK OF BEARING. REPAIR ACCOMPLISHED AS PER FEDEX EA 6-5450-127411.
Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
FWD COMPT, CORROSION FOUND BETWEEN FRAMES 24 TO 25 AND STGR 55 RT TO 53 LT. THE FITTING WAS REPAIRED AS PER EA 6-5310-127421.
Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
N938 AFT CARGO COMPT - FLOORBEAM AT FRAME 55/58 WITH SEVERAL SPOTS OF CORROSION BTW STGR 44 AND 45LH- THE FLOORBEAM WAS REPLACED IN ACORDANCE WITH SRM 51-72-10.
Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
BULK CARGO COMPT, RT FLOOR PANELS LONGITUDINAL SECTION WITH CORROSION AT FR 67 AND FR 65 UNDER STRINGER 49. SECTION LONGITUDINAL WAS REPLACED AS PER SRM 51-72-10.
Part: SKIN — CRACKED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
COCKPIT PLATE FOUND CRACKED AT COCKPIT FLOOR NEXT TO Y-790 BTW FR 0 AND FR 1. THE CRACKED PANEL WAS REPAIRED AS PER FEDEX EA 6-5310-127415.
Part: SEAT TRACK — WORN (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
SEAT TRACK NEXT TO Y0, NEXT TO FR 33 FOUND WORN. SEAT TRACK REPAIRED AS PER FEDEX EA 6-5310-127412.
Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
BULK COMPT - CORROSION AT BULK COMPT FLOORBEAM OF FR 64 ABOVE STRINGER 49 RT. FLOORBEAM WAS REPLACED AS PER SRM 51-72-10.
Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
BULK COMPT, CORROSION AT BULK CARGO COMPT FLOORBEAM AT FR 65 ABOVE STRINGER 49 RT. FLOORBEAM REPLACED AS PER SRM 51-72-10.
Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
AREA 100, FUSELAGE, PREVIOUS STRINGER REPAIR FOUND LOCATED BTW FR 21 AND FR 22 AT STGR 51 RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF IT WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR WAS ACCOMPLISHED PER SRM 53-10-14 FIG 201.
Part: TRACK — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
PREVIOUS REPAIR (DUMMY TRACK) FOUND LOCATED BETWEEN FR 38.1 AND FR 40 AT Y0. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 53-15-16 FIG 203 SHEET 2.
Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
AREA 100, FUSELAGE, PREVIOUS REPAIR (STRINGER) FOUND LOCATED BTW FR 21 AND FR 22 AT STGR 49 RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF IT WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 53-10-14 FIG 201.
Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
AREA 100, FUSELAGE, PREVIOUS REPAIR FOUND LOCATED BTW FR 21 AND FR 22 AT STGR 48 RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF IT WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 53-10-14 FIG 201.
Part: SKIN — DENTED (AILERON) · airframe 44,932 hrs · 16,897 cycles
RT WING AILERON, LOWER SKIN FOUND DAMAGED. LOWER SKIN OF AILERON REPAIRED IN ACCORDANCE WITH SRM 57-61-12 FIG 201.
Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
AREA 100 - FUSELAGE - PREVIOUS REPAIR AT STRINGER FOUND LOCATED BTW FR21 AND FR 22 AT STGR 50 RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF IT WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR WAS ACCOMPLISHED AS PER SRM 53-10-14 FIG 201.
Part: SKIN — WORN (ZONE 500) · airframe 44,932 hrs · 16,897 cycles
LT WING FIX LEADING EDGE BTW SCREWJACK 3 AND SCREWJACK 4 WITH WEAR. FIX L/E REPAIRED AS PER EA 6-5710-127425.
Part: CROSSBEAM — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
N544 - FUSELAGE - PREVIOUS REPAIR AT CROSSBEAM LOCATED BETWEEN FR 37 AT Y1680. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF IT WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR WAS EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR WAS ACCOMPLISHED AS PER FEDEX EA 6-5310-127419.
Part: SKIN — CORRODED (ZONE 300) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
THS - SUPERFICIAL CORROSION AT BASE OF HOLES NR 2 AND NR 3 OF GROUP A, RT SIDE. CORROSION BLENDED OUT AS PER EA 6-5510-127414.
Part: STRUCTURE — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
FUSELAGE, PREVIOUS REPAIR FOUND LOCATED BTW FR 23 AND FR 24 BTW STGR 49 RT AND 52 RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR EVALUATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO EXISTING FEDEX EA 6-5310-77945, BECAUSE RIVETS WERE INSTALLED IN PLACE OF FASTENERS IN THE DOUBLER. IN ORDER TO MAKE REPAIR CONFORM TO EXISTING FEDEX EA 6-5310-77945, RIVETS WERE REPLACED BY FASTENERS.
Part: CROSSBEAM — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
N542 - FUSELAGE - PREVIOUS REPAIR IN CROSSBEAM LOCATED BETWEEN FR 36 AT Y1680. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF IT WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR ACCOMPLISHED AS PER FEDEX EA 6-5310-127419.
Part: ROLLER TRACK — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
PREVIOUS REPAIR FOUND ON ROLLER TRACK LOCATED BTW FR 22-23 AT Y-100. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR WAS ACCOMPLISHED PER SRM 53-10-15 FIG203.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
PREVIOUS REPAIR FOUND LOCATED BETWEEN FR 38.1 AND 38.2, BTW STGR 54 LT AND 50 RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO EXISTING APPROVED DATA. NEW REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH FEDEX EA 6-5310-12981.
Part: SKIN — MISREPAIRED (LT WING TE FLAP) · airframe 44,932 hrs · 16,897 cycles
PREVIOUS REPAIR AT INBD FLAP LOWER SKIN LOCATED BETWEEN RIB 7 AND RIB 9. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF IT WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR WAS ACCOMPLISHED AS PER SRM 57-52-12 FIG 205.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
PREVIOUS REPAIR FOUND LOCATED BETWEEN FR 20 ANBD FR 21 STGR 47 LT AND STGR 51 RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 53-10-12 FIG 228.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 44,932 hrs · 16,897 cycles
PREVIOUS REPAIR FOUND LOCATED AT FR 13 STGR 28 LT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NO TO CONFORM TO AN SRM REPAIR, NEW REPAIR WAS ACCOMPLISHED AS PER FEDEX EA 6-5330-129283.
Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,932 hrs · 16,897 cycles
AREA 100 - PREVIOUS REPAIR AT FLOORBEAM FOUND LOCATED AT FR 63 BTW Y420 AND Y-420. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF IT WAS ACCOMPLISHED USING FAA APPROVED DATA. THE REPAIR WAS REMOVED BECAUSE THE FLOORBEAM WAS REPLACED DUE TO SEVERAL OTHER CORROSION DAMAGE, AS PER SRM 51-72-10.
Part: DAMPENER — LEAKING (MLG) · airframe 44,848 hrs · 16,835 cycles
AIR TURN BACK DUE TO GEAR WOULD NOT RETRACT IN SYS 1 OR 2. ECAM L/G RETRACTION FAULT, LANDED AT 266.9 NOT OVERWEIGHT. ON WALK AROUND FOUND RT PITCH DAMPNER TRIPPED. ACFT BEING MOVED TO THE HANGAR FOR JACKING. REMOVED AND INSTALLED SERVICEABLE RT MLG PITCH DAMPNER REF MM 32-11-15-4. PERFORMED GEAR EXTENSION AND RETRACTION FOR BOTH SYSTEMS (1) AND (2) REF MM 32-31-00-5 (4) TIMES EACH, OPS CHECK NORMAL. LOWERED ACFT FROM JACKS, REF MM 07-11-00-0.
Earlier reports · 1998–2008 · 51 reports
2008
Part: ENGINE — FAILED (NR 2) · airframe 44,681 hrs · 16,728 cycles
NUMBER TWO ENGINE HUNG START AT 36 PERCENT N2, EGT 506'. ABORTED START FOLLOWED QRH PROCEDURES. SECOND START ATTEMPT NUMBER TWO ENGINE HUNG AT 38 PERCENT N2. START AIR PRESSURE 30 PSI. REJECTED START AT 529'. OBSERVED PEAK EGT 538'. ENGINE REMOVAL APPROVED. DUE TO HIGH DRAG OF THE N2 SPOOL. MOCC/POWERPLANT/MARC. REPLACED NR 2 ENGINE IAW W/C 44T0704-2 REV 14. OPERATIONAL AND LEAK CHECKS GOOD PER JRM AND AMM 72-00 TEST 13. OK FOR SERVICE.
Part: ENGINE — HUNG START (NR 2) · airframe 44,681 hrs · 16,728 cycles
NUMBER TWO ENGINE HUNG START AT 36 PERCENT N2, EGT 506'. ABORTED START FOLLOWED QRH PROCEDURES. SECOND START ATTEMPT NUMBER TWO ENGINE HUNG AT 38 PERCENT N2. START AIR PRESSURE 30 PSI. REJECTED START AT 529'. OBSERVED PEAK EGT 538'. ENGINE REMOVAL APPROVED BY PROPULSION ENGR. DUE TO HIGH DRAG OF THE N2 SPOOL. REPLACED NR 2 ENGINE IAW W/C 44T0704-2 REV 14 OPERATIONAL AND LEAK CHECKS GOOD PER JRM AND AMM 72-00 TEST 13. OK FOR SERVICE.
2007
Part: FLOORBEAM — MISREPAIRED (FUSELAGE) · airframe 43,277 hrs · 15,891 cycles
REWORK OF FR 14 REPAIR DOUBLER TO FLOOR CROSSBEAM REQUIRED DUE TO INSUFFICIENT ED ON FASTENER HOLES COMMON TO STAND OFF BRACKETS. REMOVED REPAIR DOUBLER (ANGLE) AND FILLER SHIM IAW A310-200 SRM 51-40-21. FABRICATED NEW REPAIR DOUBLER (ANGLE) AND FILLER SHIM IAW A310-200 SRM 53-12-15 FIG 201 AND 202. APPLIED SURFACE PROTECTION TO REPAIR DOUBLER (ANGLE) AND FILLER SHIM IAW A310-200 SRM 51-21-10 AND SRM 51-75-10. INSTALLED NEWLY FABRICATED REPAIR DOUBLER (ANGLE) AND FILLER SHIM IAW A310-200 SRM 53-12-15.
Part: FLOORBEAM — MISREPAIRED (FUSELAGE) · airframe 43,277 hrs · 15,891 cycles
PREVIOUS REPAIR LOCATED ON MAIN CABIN FLOORBEAM FRAME 35 BETWEEN SEAT TRACKS 2 AND 3 RT FWD AND AFT UPPER FLANGE HAS 2 EACH REPAIR ANGLES THE FWD ANGLE IS 10.3" BY 1" AND THE AFT ANGLE IS 12.4" BY 1.82". REPAIR FOUND NOT TO BE IAW EA6-5321-29300. REMOVED EXISTING REPAIR ANGLES AND REPAIRED FLOORBEAM PER FEDEX EA6-5310-107718.
Part: STIFFENER — CRACKED (FUSELAGE) · airframe 43,277 hrs · 15,891 cycles
MDCC - FLOORBEAM C37, FWD FACE, VERTICAL STIFFENER AT TOP HAS .5 INCH CRACK LOCATED BETWEEN NR 4L AND 5L SEAT TRACK ROUTED OUT CRACKED VERTICAL STIFFENER IAW A310/200 SRM 53-10-15 NDT VERIFIED CRACK. REMOVAL FABRICATED REPAIR ANGLES IAW A310/200 SRM, 53-10-15. INSTALLED REPAIR ANGLES IAW A310/200 SRM 53-10-15.
Part: FLOORBEAM — MISREPAIRED (FUSELAGE) · airframe 43,277 hrs · 15,891 cycles
PREVIOUS REPAIR LOCATED ON MAIN CABIN FLOORBEAM FRAME 34 BETWEEN SEAT TRACKS 2 AND 3 RT FWD AND AFT UPPER FLANGE HAS 2 EACH REPAIR ANGLES THE FWD ANGLE IS 10.25" BY 1" AND THE AFT ANGLE IS 12.2" BY 1.82" PREVIOUSLY INSTALLED REPAIR LOCATED AT MAIN CABIN FLOORBEAM FRAME 34 BETWEEN SEAT TRACKS 2 AND 3 RT WAS DETERMINED NOT TO BE IAW FEDEX EA6-5321-29300. REMOVED AND REINSTALLED FLOOR PANEL PER A310/200 AMM SUPPLEMENT 53-10-23-4, REMOVED EXISTING REPAIR ANGLES AND REPAIRED FLOORBEAM PER FEDEX EA6-5310-107718.
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 43,277 hrs · 15,891 cycles
MDCC FLOORBEAM AT FR 14 LT 64 INCHES FROM CENTER HAS 1 SPOT OF CORROSION ON FORWARD BOTTOM FACE 15" LONG BY 1" WIDE. REMOVED CORROSION IAW SRM 51-74-10 CHECKED LIMITS IAW SRM 53-12-15, OUT OF LIMITS. FABBED REPAIR IAW A310/200 SRTM 53-12-15 PB210 FIG 201. REPROTECTED REPAIR IAW A310-200 SRM 51-75-10. INSTALLED REPAIR IAW A310-200 SRM 51-40-21 AND SRM 53-12-15.
Part: SEAT TRACK — WORN (FUSELAGE) · airframe 43,277 hrs · 15,891 cycles
MDCC DUMMY TRACK NR 1 FR 38.2 - FR 40 CENTER LINE OF AIRPLANE IS WORN MORE THAN .039 IAW EO6-5310-7-3322, WORN LESS THAN .078 REMOVED AND REINSTALLED FLOOR BOARDS PER A310-200 SRM 51-40-21. REMOVED AND REINSTALLED DUMMY TRACK PER A310-200 SRM 51-40-21. REPAIRED DUMMY TRACK PER A310-200 SRM 53-15-16.
Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 43,277 hrs · 15,891 cycles
UPON REMOVAL OF CEILING PANEL 131EC FOR AGING ACFT INSPECTION, FOUND MDCC FLOOR SUPPORT C36 BETWEEN L4 AND L5 SEAT TRACK TO BE CRACKED TOP OF VERTICAL STIFFENER LENGTH OF CRACK .400 INCH ROUTED OUT CRACK IAW A310/200 SRM 53-10-15. FABRICATED 2 REPAIR ANGLES AND INSTALLED IAW A310-200 SRM 53-10-15. REPROTECTED AREA IAW A310-200 SRM 51-75-10.
Part: FLOORBEAM — MISREPAIRED (FUSELAGE) · airframe 43,277 hrs · 15,891 cycles
PREVIOUS REPAIR LOCATED ON MAIN CABIN FLOORBEAM FRAME 36 BETWEEN SEAT TRACKS 2 AND 3 RT FWD AND AFT UPPER FLANGE HAS 2 EACH REPAIR ANGLES THE FWD ANGLE IS 10.25" BY 1 " AND THE AFT ANGLE IS 12.2" BY 1.82" PREVIOUSLY INSTALLED REPAIR LOCATED AT MAIN CABIN FLOORBEAM FRAME 36 BETWEEN SEAT TRACK 2 AND 3 RT WAS DETERMINED NOT TO BE IAW FEDEX EA6-5321-29300. REMOVED EXISTING REPAIR ANGLES AND REPAIRED FLOORBEAM PER FEDEX EA6-5310-107718.
2006
Part: LANDING GEAR — MALFUNCTIONED (NOSE) · airframe 42,375 hrs · 15,465 cycles
LOUD BANG AND PRONOUNCED VIBRATION WAS FELT FROM THE NOSE WHEEL WELL AREA. UPON GEAR RETRACTION, UNSAFE GEAR DOOR ( NOSE WHEEL ) AMBER LIGHT REMAINED ON BOTH PANELS, QRH WAS FOLLOWED. GEAR HANDLE WAS NOT SELECT ED TO NEUTRAL. ONCE DECIDED TO EXTEND GEAR FOR LANDING, NOSE WHEEL EXTENDED WHEN THE GEAR HANDLE WAS BETWEEN THE UP POSITION AND NEUTRAL ( NOT NORMAL ). WHEN STATUS PAGE SELECTED, IT SHOWED L/G RETRACTION NOT AVAIL OR INOP.
Part: ENGINE — FAILED (NR 2) · airframe 42,354 hrs · 15,456 cycles
NR 2 ENGINE FAILED AT ROTATION. ENGINE CHANGE APPROVED, NR 2 ENGINE REPLACEMENT IN WORK.
Part: DOOR — OPEN (MLG) · airframe 42,345 hrs · 15,452 cycles
AFTER TAKEOFF UPON GEAR RETRACTION LANDING GEAR DOOR SYS FAULT LIGHT ILLUMINATED, ACCOMPANIED WITH NOSE GEAR DOOR LIGHT ON OVERHEAD PANEL. LOUD NOISE AND VIBRATION CONFIRMED, GEAR DOORS WERE NOT CLOSED. REPLACED NOSE GEAR DOOR UPLOCK RIGHT ASSY OP CHECK GOOD REF MM 32.31.14.4 AND MM 32.33.00.5. PREMATURE REMOVAL/INSTALLATION OFF MFG A25431001-2.
2005
Part: INDICATOR — FAILED (NR 2 EPR) · airframe 41,315 hrs · 14,879 cycles
AFTER SETTING 40 N1 AND ADVANCING THROTTLES FOR TAKEOFF THE 2 EPR GAUGE FAILED. REJECTED TAKEOFF AND RETURNED TO THE RAMP, NEEDED EPR'S FOR MANUAL THROTTLE SETTING. TROUBLESHOOTING IN PROGRESS. AWAITING PARTS. PERFORMED WIRING CHECK BETWEEN 2 ENG EEC TO 2 EPR INDICATOR FOUND WIRE R77150029 AND SHIELDED WIRE AT 2 EPR IND CONNECTOR SHORTED. REPAIRED AS PER SMP. AWAITING EEC AND ENG RUN. ENG RAN CARRIED OUT AS PER A310 JRH BY AMT 439456 EPR AND ALL OTHER PARAMETERS NORMAL. ACFT OK FOR SERVICE.
Part: INDICATION SYS — MALFUNCTIONED (NR 2 ENGINE OIL) · airframe 41,071 hrs · 14,778 cycles
WHILE CLIMBING THROUGH FL 130 NR 2 ENG OIL QTY WENT TO ZERO (BOTH GAUGE AND ECAM) ENG OIL PRESSURE AND TEMP INDICATED NORMAL. ENGINE 2, OIL QTY INDICATIONS INOP. (1 OR 2) VERIFY AND RECORD IN EAML THAT OIL TANK QTY HAS BEEN VERIFIED PRIOR TO EACH DEPARTURE. VERIFIED NR 2 ENG OIL TANK QTY FULL.
2004
Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 39,847 hrs · 14,230 cycles
MDIS 421 53-10 0009108 21SEP04 SIN CLOSE U- QA PICKUP FLOORBEAM AT FWD FACE OF FR 33, BETWEEN -Y450 AND -Y953 WITH HAIR LINE CRACK. ENT BY: 275296 RPT BY: 275296 FACT 21SEP04 02:26 SIN U FLOORBEAM REPAIR C/O IAW SRM 53-10-15 FIG 201 SH 4A. RII BY L1160. ENT BY: 275296 RPT BY: 275296.
Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 39,847 hrs · 14,230 cycles
FUSELAGE FRAME 13A FWD AND AFT FACE AT STRINGER 44 LT FOUND SIGNS OF CORROSION. REPAIR C/O AS PER EA 6-5310-77954. RII L4724 (SIAEC).
Part: FITTING — CORRODED (CARGO BAY) · corrosion level 2 · airframe 39,847 hrs · 14,230 cycles
THE FOLLOWING FWD CARGO COMPT FWD MANHOLE POCKETS HAD CORROSION AT LOCATIONS: (A) AFT OF FS 23 RT SIDE CTR PORTION 2 OFF POCKETS BETWEEN STR 51 RT AND STR 49RT. REPAIR C/W AS PER EA 6-310-77945 AND ALSO REFER TO N00411 AND N00412. RII BY L3167(SIAEC) Y: 275296 RPT BY: 275296.
Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 39,847 hrs · 14,230 cycles
FUSELAGE FRAME 14A FWD AND AFT FACE AT VICINITY OF STRINGER 44 LT FOUND CORRODED. REPAIR C/W AS PER EA 6-5310-77955. RII BY L4724.
Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 39,847 hrs · 14,230 cycles
THE FOLLOWING FWD CARGO COMPT AFT MANHOLE POCKETS HAD CORROSION AT LOCATIONS: (A) ON LT SIDE OF MANHOLE 6 OFF POCKETS CORROSION BETWEEN FS 38.1 TO FS 38.2. REPAIR C/W AS PER EA 6-5310-77946 AND ALSO REFER TO N00411, N00412 AND N00488. RII BY L3167(SIAEC).
Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 39,847 hrs · 14,230 cycles
FOUND CORROSION AT FUSELAGE FRAME 12A AFT FACE AT VICINITY OF STRINGER 44LH. REPAIR C/W AS PER EA 6-5310-77952. RII BY L4724.
Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,847 hrs · 14,230 cycles
AFT FUSELAGE SKIN EXTERIOR BETWEEN FRAME 90-91 AND STRINGER 5 LT TO 8 LT CORROSION FOUND ON FASTENERS HEAD AND SKIN EXTERIOR SURFACE. ENT BY: 275296 RPT BY: 275296 FACT 20SEP04 05:35 SIN U REPAIR CARRIED OUT PER EA 6-5310-77951. RII BY L3420(SIAEC). ENT BY: 275296 RPT BY: 275296
Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,847 hrs · 14,230 cycles
MDIS 421 53-10 0009094 03SEP04 SIN OPEN U FUSELAGE STRINGER 44 LT FRAME 13A TO 16A FOUND CORRODED AT MULTIPLE LOCATIONS. ENT BY: 086361 RPT BY: 086361 SHGN 03SEP04 07:32 SIN U SDR HAS BEEN SUBMITTED. ENT BY: 086361 RPT BY: 086361**** S/D COMING ****.
Part: STRINGER — CORRODED (ZONE 100) · airframe 39,847 hrs · 14,230 cycles
FUSELAGE STRINGER 44 LT FRAME 13A TO 16A FOUND CORRODED AT MULTIPLE LOCATIONS REF SRM 53-10-00 FIG 102. CORROSION IS OUT OF LIMIT. (OPEN)
Part: CROSSBEAM — CRACKED (ZONE 100) · airframe 39,847 hrs · 14,230 cycles
QA PICKUP FLOORBEAM AT FWD FACE OF FR 33 BETWEEN Y450 AND Y953 WITH HAIR LINE CRACK.
Part: PLATE — CORRODED (ZONE 100) · airframe 39,847 hrs · 14,230 cycles
THE FWD CARGO COMPARTMENT AFT MANHOLE BETWEEN FR38.1 AND FR38.2 ON THE LT SIDE OF THE MANHOLE BETWEEN STR55 AND STR53RT. EXISTING POCKETS REPAIRED WITH EXTERNAL DOUBLER. REPAIRED POCKETS AND NEW POCKETS FOUND WITH CORROSION MORE THAN 50 PERCENT OF FITTING THICKNESS.**** S/D COMING ****
Part: PLATE — CORRODED (ZONE 100) · airframe 39,847 hrs · 14,230 cycles
THE FWD CARGO COMPARTMENT FWD MANHOLE BETWEEN FR23 AND FR 24 ON RT SIDE BETWEEN STR RT 51 AND STR RT 49. THE EXISTING POCKETS REPAIRED WITH EXTERNAL DOUBLER AND NEW POCKETS FOUND CORROSION MORE THAN 50 PERCENT OF FITTING THICKNESS. ON LT SIDE OF MAN HOLE BETWEEN STR 55 AND STR 53RH 01 OFF POCKET ON INNER ROW RIVET FOUND CORROSION MR 50 PERCENT THICKNESS OF FITTING. SNRM: N00411, THE FOLLOWING CARGO COMPARTMENT FWD MANHOLE POCKETS FOUND, CORROSION AT LOCATIONS : (A) AFT OF FR23 ( RTSIDE FWD) 2 OFF POCKETS BETWEEN STR51RT AND STR 49 RT. (B) FWD OF FR 24( LTSIDE AFT ) 2 OFF POCKETS BETWEEN STR55 AND STR 53 RT.**** S/D COMING ****
Part: TIRE — FAILED (NLG) · airframe 39,349 hrs · 14,004 cycles
ON T/O NOSE WHEEL TIRE FAILED AT V1=144 KTS, GW = 297.0. FOUND RIGHT TIRE BURST AND TORN TREAD. REMOVED AND REPLACED LT & RT NOSE TIRE ASSY PER MM 12-37-32-0-04. PREMATURE REMOVAL/INSTALLATION OFF MFG 286351003-1-51.
Part: TIRE — FAILED (MLG) · airframe 39,349 hrs · 14,004 cycles
ON TAKEOFF, NOSE WHEEL TIRE FAILED AT V1=144 KTS, GW = 297.0. FOUND RIGHT TIRE BURST AND TORN TREAD. REMOVED AND REPLACED LT & RT NOSE TIRE ASSY PER MM 12-37-32-0-04. PREMATURE REMOVAL/INSTALLATION, OFF MFG 286351003-1-51, POS 1 SRL W1879A, TAG 542768, ON MFG 286351003-1-51, SRL W3039, TAG 462894, PREMATURE REMOVAL/INSTALLATION OFF MFG Z32-002-02, POS 2 SRL F243, TAG 542769, ON MFG 286351003-1-51, SRL 09920, TAG 998810.
2002
Part: SKIN — CORRODED (VERTICAL STAB) · airframe 36,589 hrs · 12,706 cycles
WIDESPREAD CORROSION ON FUSELAGE SKIN ON THE OUTBOARD SIDES OF THE VERTICAL STAB LT & RT ATTACHMENT. R/R ALL TRACES OF CORROSION.
Part: PYLON — CRACKED (N/A) · airframe 36,589 hrs · 12,706 cycles
CRACK FOUND ON HOLE #7 AND #6 ON OVERWING REFUEL APARTURE. ** S/D ** COMING
Part: FITTING — CORRODED (RT PYLON) · airframe 36,589 hrs · 12,700 cycles
RT WING PYLON SPIGOT BALL JOINT FOUND WITH BROWN STAIN ALL AROUND THE CIRCUMFERENCE OF FITTING.
Part: FITTING — CORRODED (ENGINE PYLON) · airframe 36,589 hrs · 12,700 cycles
RT WING PYLON SPIGOT BALL JOINT FOUND WITH BROWN STAIN ALL AROUND THE CIRCUMFERENCE OF FITTING. CLEARED IAW EA 6-5450-59029.
Part: FITTING — CORRODED (LT PYLON) · airframe 36,589 hrs · 12,706 cycles
LT WING PYLON AFT FITTING BALL JOINT ASSY FACE FOUND WITH BROWN STAIN. CONFIRMED CORROSION ON 12 JUNE 2002. INSTALLED NEW FITTING ASSY PER S/B A310-54-2021 EA. 6-5150-59026.
Part: NUT — CORRODED (RT PYLON) · airframe 36,589 hrs · 12,706 cycles
RT WING PYLON AFT FITTING BALL JOINT ASSY NUT FOUND WITH GREENISH STAIN. CONFIRMED CORROSION ON 12 JUNE 2002. INSTALLED NEW FITTING ASSY PER AIRBUS S/B A310-54-2021.
Part: FITTING — CORRODED (LT PYLON) · airframe 36,603 hrs · 12,711 cycles
LT WING PYLON FWD SPIGOT BALL JOINT FOUND WITH BROWN STAINS ALL ROUND THE CIRCUMFERENCE OF FITTING. CONFIRMED CORROSION ON 12 JUNE 2002.
Part: FITTING — CORRODED (#1 LEFT DOOR) · airframe 36,176 hrs · 12,528 cycles
L/MAIN ENTRY DOOR EXTERIOR HANDLE CUTOUT CORRODED AT HORZ WEB & AFT VERT WEB. R&R FITTINGS PER SRM 51-72-10 & REFITTED DOOR HANDLES & LIFT RODS.
Part: SKIN — CORRODED (PAX DOOR) · airframe 36,176 hrs · 12,528 cycles
LT MAIN ENTRY DOOR EXTERIOR HANDLE CUTOUT CORRODED AT HORIZ WEB & AFT VERTICAL WEB.
2001
Part: PYLON — CRACKED (LOWER SPAR) · airframe 35,242 hrs · 12,102 cycles
NR 103 CRACK ON LH PYLON LWR SPAR BETWEEN RIB 6&7. R&R PER EO 6-5410-7-3000 A3 PART 3.
Part: PYLON — CRACKED (LOWER SPAR) · airframe 35,242 hrs · 12,102 cycles
NR 100 CRACK ON RH PYLON LWR SPAR BETWEEN RIB 9 & 10. ** S/D ** COMING
Part: PYLON — CRACKED (LOWER SPAR) · airframe 35,242 hrs · 12,102 cycles
NR 102 CRACK ON LH PYLON LWR SPAR BETWEEN RIB 9 & 10. R&R PER EO 6-5450-7-3302B PART 5.
Part: PYLON — CRACKED (LOWER SPAR) · airframe 35,242 hrs · 12,102 cycles
NR 103 CRACK ON LH PYLON LWR SPAR BETWEEN RIB 6 & 7. ** S/D ** COMING
Part: PYLON — CRACKED (LOWER SPAR) · airframe 35,242 hrs · 12,102 cycles
NR 100 CRACK ON RH PYLON LWR SPAR BETWEEN RIB 9 & 10. R&R PER EO 6-5450-7-3320B PART 6.`
Part: PYLON — CRACKED (LOWER SPAR) · airframe 35,242 hrs · 12,102 cycles
NR 102 CRACK ON LH PYLON LWR SPAR BETWEEN RIB 9 & 10. ** S/D ** COMING
Part: SMOKE DETECTOR — ACTIVATED (MAIN CARGO DECK) · airframe 34,881 hrs · 11,933 cycles
AFT T/O AFT AND MID MAIN DECK CARGO SMOKE IND FOLLOW BY MIN EQUIP BAY SMOKE IND. SUSPECT OIL IN BLD DUCT FROM APU SHUTDOWN FOR LOW OIL.
Part: BATTERY — DISCHARGED (NR 1) · airframe 34,880 hrs
NR 1 BATTERY INOP. REMOVED AND REPLACED NR 1 BATTERY PER MM 24-31-11-4. OPS CK GOOD.
Part: UNKNOWN — ODOR (COCKPIT) · airframe 34,232 hrs · 1,125 cycles
JUST PRIOR TO DESCENT, A STRONG BURNING ODOR SMELL IN COCKPIT. AC RELEASED PER MEL 34-32A 1WX RADAR SYS INOP.
2000
Part: WARNING SYSTEM — ILLUMINATED (NR 1 ENGINE T/R) · airframe 34,014 hrs · 11,524 cycles
00-372 NR 1 ENGINE AMBER THRUST REVERSER UNLOCK LIGHT ILLUM. PLACED ON MEL 78-2. ** S/D ** COMING
1999
Part: PAD — FAILED (PAX DOOR)
ECAM WARNING RT FWD CABIN DOOR NOT CLOSED. INSPECTED R-1 DOOR. REMOVED AND REPLACED RUBBER PAD, CK R-1 DOOR PER MM 52-10-20-6. NO DEFECTS FOUND, OK FOR SERVICE.
1998
Part: INDICATOR — FAILED (NR 1 ENGINE)
98-0286, NR 1 ENG OIL INDICATORS DECREASED TO 0 AT FL350, BOTH ECAM AND ANALOG. REMOVED AND REPLACED ENGINE OIL QTY DUAL INDICATOR.
Part: CONTACTOR — FAILED (COCKPIT)
DURING T/O ROLL, JUST TO V1 CAPT PFD, ND WENT BLANK AS WELL AS THE ALT, HSI, GPWS WARN AC BUS OFF LIGHT BLINK AC EMER ON INVER LIGHT BLINK. WARNING HORN CAME ON WITH BLINK LIGHTS ONLY ECAM WAS FWS CRT AMBER CAUTION FAA SHOW 700 FT NO FLAP IND DURING LAND. REMOVED AND REPLACED RELAY 25XC, 6XE CONTACTORS 11XC, 12XC AND 1XC CB. RESTORED POWER, ALL OPS CKS NORM.