N807FD

Part: POWER SUPPLY — FAILED (EMERGENCY LIGHTS) · airframe 67,163 hrs · 17,874 cycles

EMERGENCY LIGHTS INOPERATIVE. REMOVED AND REPLACED THE POWER SUPPLY AND BATTERY 29WLI IAW AMM 33-51-14-04-09. OPS CHECKED GOOD.

Part: JACKSCREW — LACK OF LUBE (TE FLAPS) · airframe 66,300 hrs · 17,373 cycles

WHEN SELECTING FLAPS TO 15, NOTICE BINDING LEAVING THE SLATS/FLAPS 15/0 GATE AT FLAPS 15 RECEIVED FLAP FAULT SYS 1 AND 2. CYCLED THE FLAP HANDLE, NO CHANGE. QRH PROCDURES COMPLETED. LANDED FLAPS 0. REMOVED AND REPLACED THE FLAP/SLAT HANDLE COMMAND SENSOR UNIT IAW AMM 27-51-17-04. HANDLE NO LONGER BINDING, OPERATES SMOOTH WITH FORCE MEASUREMENT WITHIN LIMITS. FAULT REMAINS. OPS CHECK OF SENSOR. BOTH SFCC'S HAVE FLAP BINDING FAULTS AND BOTH SFCC FAULT LIGHTS ILLUMINATED WHEN TRYING TO OPERATE FLAPS. APPEARS THAT THE OVER TORQUE INDICATOR ON THE RIGHT SYSTEM TORQUE LIMITER IS ACTIVATED. FOUND TORQUE LIMITER ON RIGHT FLAP SYSTEM TRIPPED, FOUND THE NR 2 FLAP JACKSCREW ON RIGHT WING TRIPPED. RESET BOTH AND LOWERED FLAPS. NR 2 JACKSCREW NEEDS GEARBOX FLUIDS. CHECKED AND SCREW ITSELF IS DRY. COMPLIED WITH LUBRICATION OF BOTH WING JACKSCREWS IAW AMM 12-22-27. OPS CHECKED GOOD IAW AMM 27-54-00.

Part: FLOOR SUPPORT — CORRODED (FRAMES 12A-14) · corrosion level 2 · airframe 66,004 hrs · 17,141 cycles

MAIN DECK FRAMES 12A - 14, Y953 FLOOR SUPPORT FOUND CORRODED. REPLACED THE FLOOR SUPPORT IAW SRM 51-40-21. MAJOR REPAIR IAW GMM 6-2-100.

Part: SKIN — DENTED (FRAMES 65-66) · airframe 66,004 hrs · 17,141 cycles

FUSELAGE SKIN FOUND A DENTED BETWEEN FRAMES 65 - 66, STRINGER 36 - 37R. REPAIRED IAW SRM 53-10-12- 201 PARA 6 FIG225 SHEET 2 . MAJOR REPAIR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (FRAME 44) · airframe 66,004 hrs · 17,141 cycles

TEE ANGLE AT STIFFENER 8 LT FOUND CRACK. REPAIRED THE TEE ANGLE IAW EA 6-5710-T0330412 P1. MAJOR REPAIR IAW GMM 6-2-100

Part: ANGLE — CRACKED (FRAME 47) · airframe 66,004 hrs · 17,141 cycles

FRAME 47 RT INTERNAL ANGLE\ FOUND CRACKED. REPAIRED THE ANGLE IAW EA 6-5710-T0312253 C P3. MAJOR REPAIR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (FRAME 47) · airframe 66,004 hrs · 17,141 cycles

ANGLE AT FRAME 47 LT SIDE FOUND CRACKED. REPAIRED IAW EA 6-5710-T0312253 C P3. MAJOR REPAIR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (FRAME 44) · airframe 66,004 hrs · 17,141 cycles

TEE ANGLE AT STIFFENER 8 RT FOUND CRACKED. REPAIRED IAW EA 6-5710-T0330412 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SKIN — CRACKED (LT WING) · airframe 66,004 hrs · 17,141 cycles

LEFT WING BOTTOM SKIN FOUND CRACKED AT 581AB CUTOUT. REPAIRED IAW EA 6-5730-T0330205 P1 AND DWG R57249152. MAJOR REPAIR IAW GMM 6-2-100.

Part: ATTACH FITTING — CRACKED (CARGO DOOR) · airframe 66,004 hrs · 17,141 cycles

AFT CARGO DOOR ACTUATOR ATTACH FITTING FOUND CRACK BY HFEC INSPECTION. REPLACED THE ATTACH FITTING IAW SRM 51-40-21.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 66,004 hrs · 17,141 cycles

MAIN DECK FR11-FR14 Y770 FLOOR SUPPORT CORRODED.

Part: ATTACH FITTING — CRACKED (CARGO DOOR) · airframe 66,004 hrs · 17,141 cycles

FWD CARGO DOOR ACTUATOR ATTACH FITTING WITH CRACK SIGNAL. REPLACED THE ATTACH FITTING IAW SRM 51-40-21.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 65,474 hrs · 16,802 cycles

DURING CRUISE FLIGHT AT FL 360, BEGAN TO SEE AN ORANGE GLOW IN LOWER LT CORNER OF CAPTAINS FWD WIND SCREEN. TURNED OUT TO BE WINDSHIELD HEAT ARCING, SO TURNED OFF CAPTAINS WINDSHIELD HEAT. ABOUT THE SAME TIME, CAPTAINS FWD, OUTER WINDSHIELD SHATTERED. REMOVED CAPTAINS WINDSHIELD IAW AMM 56-11-11-04. R & R LT WINDSHIELD TEMP CONTROLLER 19DG IAW AMM 30-42-11-04. INSTALLED CAPTAINS WINDSHIELD IAW AMM 56-11-11-04. WINDOW HEAT OPERATES NORMAL IAW AMM 30-42-00 PB 501. AERO SEALANT ON OIL REF WRI 56-10 0120. REMOVED WINDSHIELD PPG PN NP175201-3 & SN 01018H7896.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 65,259 hrs · 16,662 cycles

CRACK ON CAPTAINS' OUTER FRONT WINDSHIELD. WINDOW HEAT WAS ON, BUT TURNED OFF ONCE CRACK DEVELOPED. R & R CAPTAINS WINDSHIELD. R & R LT WINDOW TEMP CONTROLLER -19DG. R & R LT WINDOW HEATING PROTECTION UNIT -87DG.

Part: SKIN — CORRODED (LT WING) · corrosion level 2 · airframe 64,081 hrs · 15,881 cycles

LEFT WING UPPER SURFACE SKIN FOUND CORROSION AT THE FRONT OF NR 2 SPOILER. REPAIRED LT WING UPPER SURFACE SKIN IAW EA 6-5730-T0311884 P1. TITLE WING PLATES & SKINS LHS WING TOP SKIN PANEL 2 TE OVERHANG CORROSION REPAIR BETWEEN RIBS 5 - 7. MAJOR REPAIR IAW GMM 6-2-100.

Part: TEE FITTING — CRACKED (RT WING) · airframe 64,081 hrs · 15,881 cycles

CENTER WING INSP REAR SPAR INTERNAL ANGLE & TEE FITTING RT NR 10 FASTENER HOLE WITH CRACK SIGNAL. REPAIRED IAW EA 6-5710-T0312253 TITLE WINGS BASIC WING STRUCTURE SB A310-57-2047 FRAME 47 HOLES CRACKED. MAJOR REPAIR IAW GMM 6-2-100.

Part: BRACKET — CRACKED (LT AILERON) · airframe 64,081 hrs · 15,881 cycles

LEFT AILERON OTBD HINGE PANEL BRACKET CRACKED REPAIRED LT AILERON OTBD HINGE PANEL BRACKET IAW EA 6-5750-T0312135. WINGS FLIGHT SURFACES FRONT SPAR LOWER DOUBLER BROKEN AT LT AILERON LOWER SURFACE LE MAJOR REPAIR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (FRAME 47) · airframe 64,081 hrs · 15,881 cycles

ANGLE & TEE FITTING CRACKED FRAME 47. REPAIRED IAW IAW EA 6-5710-T0312253. MAJOR REPAIR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (FRAME 47) · airframe 64,081 hrs · 15,881 cycles

ANGLE & TEE FITTING CRACKED FRAME 47. REPAIRED IAW EA 6-5710-T0312253. MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FRAME 47) · airframe 64,081 hrs · 15,881 cycles

ANGLE & TEE FITTING CRACKED FRAME 47. REPAIRED IAW EA 6-5710-T0312253. MAJOR REPAIR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (FRAME 47) · airframe 64,081 hrs · 15,881 cycles

REAR SPAR INTERNAL ANGLE & TEE FITTING RT NR 1 FASTENER HOLE WITH A CRACK SIGNAL. REPAIREDSPAR ANGLE & TEE FITTING IAW EA 6-5710-T0312253. MAJOR REPAIR IAW GMM 6-2-100.

Part: FLOORBEAM — CORRODED (FRAME 37) · corrosion level 2 · airframe 64,081 hrs · 15,881 cycles

FORWARD CARGO COMPARTMENT FLOORBEAM TEE CORRODED AT FRAME 37, Y140 - Y805. REPAIRED THE FLOORBEAM IAW EA 6-5310-T0311889. MAJOR REPAIR IAW GMM 6-2-100.

Part: FLOORBEAM — DELAMINATED (FRAME 60) · corrosion level 2 · airframe 64,081 hrs · 15,881 cycles

AFT CARGO BAY FLOORBEAM TEE FOUND DELAMINATION AT FRAME 60 Y-805 - Y-1470. CUT THE DELAMINATED BEAM IAW SRM 53-10-15 FIG 207 CHECKED THE CRACKS TO CUTOUT PER NTM 51-10-08 MADE THE REPAIR PARTS IAW SRM 53-10-15 FIG 207 WET INSTALLED THE REPAIR IAW SRM 51-40-21 FILLED EDGES OF REPAIR BEAM ,SPLICE ,RIVET HEADS APPLIED COATING AND CIC MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (WING) · airframe 64,081 hrs · 15,881 cycles

CENTER WING INSP REAR SPAR INTERNAL ANGLE & TEE FITTING LT NR 10 FASTENER HOLE WITH CRACK SIGNAL. REPAIRED CENTER WING INSP REAR SPAR INTERNAL ANGLE & TEE FITTING LT NR 10 FASTENER HOLE PER EA 6-5710-T0312253. MAJOR REPAIR IAW GMM 6-2-100

Part: RIB — CORRODED (RT WING) · corrosion level 2 · airframe 63,793 hrs · 15,656 cycles

RT RIB 5 BORE & AFT FACE HAVE CORROSION. COMPLIED WITH EA 6-5710-T0307063 P 1 WINGS & BASIC WING STRUCTURE, RT RIB 5 LUG CORROSION.

Part: RIB — CORRODED · corrosion level 2 · airframe 63,793 hrs · 15,656 cycles

LT RIB 5 HAS CORROSION IN BORE & FACE. COMPLIED WITH EA 6-5710-T0307003 WINGS & BASIC STRUCTURE, LT RIB 5 LUG CORROSION.

Part: FUEL — CONTAMINATED (LT WING) · airframe 63,735 hrs · 15,612 cycles

EN ROUTE LT OUTER PUMP 1 & PUMP 2 FAILED IN FLIGHT. BOTH PUMPS SHOWED LOW PRESS. FOLLOWED ECAM TO TURNOFF. THAWED LO FUEL PUMPS & TANK WITH 3 COLD BUSTERS FOR 5 HOURS. PERFORMED LO TANK PUMPS OPERATIONAL TESTED IAW AMM IAW 28-21-00-05, BOTH PUMPS CHECKED NORMAL. SUMP APPROX 2 GALLONS FROM LT OUTER TANK IAW MM 12-32-28-03. FIRST GALLON CONTAINED APPROX 4 OZ'S OF WATER, SECOND GALLON WAS FREE OF WATER. RAN APU IAW JRH USING LT OUTER TANKS ONE AT A TIME, THEN BOTH. BOTH LT OUTER TANKS PUMPS, OPERATIONS CHECKED OK, 20 PSI INDICATED ON ENG PAGE OF ECAM. TRANSFERRED ALL FUEL FROM LT OUTER TANK TO OTHER TANKS. SUMP ALL FUEL TANKS WITH NO WATER FOUND.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 63,573 hrs · 15,513 cycles

MDIS 807 53-00 0008007 30NOV13 BQN CLOSE R FOUND FWD FUSELAGE FLOOR SUPPORT MEMBER BETWEEN C9 & C10, ONE FRAME LT 09 88 WITH SEVERAL CRACKS. A536 11977200 ID WEB IAW SRM 53-11-15 PAGE 4 ITEM 475 PN A53611977200 & ATTACHED FITTING ITEM 185 PN A53610270220. PART 01DEC13 16:35 MC1 RT ADDED MPN A5361197720000, CPN QTY 1 WEB MSN 1341240 PART 01DEC13 19:57 MC1 R ADDED MPN NSA343035, CPN QTY 1 XTRUSION MSN 1341264 ADDED MPN A5361119820610 QTY 1 FITTING MSN 1341288. CRACK IN THE FLOOR BEAM STRUCTURE AFT OF FRAME 7 AT Y 790. ITEM ADDRESS IAW EA 6-5310-T0304395, PART 1, ALL STEPS OF PART 1 COMPLIED WITH. C 0576372 OILS 02DEC13 13:10 BQN R OIL REFERENCE EA6-5310-T0304395 R & R DAMAGED SUPPORT MEMBERS BETWEEN C7 & C10. IAW A310 SRM 51-72-10 & 51-40-20. IAW WRI'S 53-00/8015, 53-00/8016, 53-10/8017 AND 53-00/8018. REPLACED WEB A5361197720000 REPLACED FITTING A5361119820610 AT C7 YC 790 REPLACEDT T FITTING A5361197620000, SEE ALSO ER 13-07772 FINAL CLOSED.

Part: FITTING — CRACKED (WING) · airframe 62,155 hrs · 14,645 cycles

PERFORMED NDT IAW E6-5710-7-3324 A PT1, CRACKS WERE FOUND AT HOLE NR 1 AND HOLE NR 2 OF FRAME 40 LT UPPER CORNER FITTING.

Part: FITTING — CRACKED (WING) · airframe 62,155 hrs · 14,645 cycles

PERFORMED NDT IAW E6-5710-7-3324 A PT2 , CRACKS WERE FOUND AT HOLE NR 1 AND HOLE NR 2 OF FRAME 40 RT UPPER CORNER FITTING.

Part: POWER SUPPLY — FAILED (ZONE 100) · airframe 61,616 hrs · 14,340 cycles

L1 & R1 DOORS ESCAPE SLIDE RELEASE WARNING LIGHTS SYSTEM INOPERATIVE. R & R AUTONOMOUS STANDBY POWER SUPPLY UNIT (70WN). OPS CHECKED GOOD REF MM 52-73-18-04. OK FOR SERVICE.

Part: BATTERY — FAILED (EMERGENCY LIGHT) · airframe 61,419 hrs · 14,196 cycles

ON PREDISPATCH CK, FOUND ON COURIER COMPARTMENT EMERGENCY LT TEST INOP. REMOVED AND REPLACED EMG POWER SUPPLY UNIT AND EMERGENCY SUPPLY BATTERY, REF MM 33-51-14-04-09. OPS CK GOOD. OK FOR SERVICE. (CLOSED)

Part: JACKSCREW — OUT OF POSITION (STABILIZER)

DURING O/H, MX PERFORMED ON THE SCREW JACK ASSY, FE140 SN 125, IDENTIFICATION OF THE WRONG POSITIONING OF THE RATCHET WHEEL (ITEM 3-620 OF CMM 27-44-13), ASSEMBLED ON THE OPPOSITE POSITION COMPARED TO THE SPEC MENTIONED ON THE CMM 27-44-13. LETTER LT-S9-11-106 + TECH REPORT (RF-DSC-438/11 V00) THIS MISASSEMBLY LEADS TO AN INOPERATIVE NO-BACK OF THE SCREW JACK ASSY ON COMPRESSIVE LOAD DIRECTION ONLY. THE PROBABLE CAUSE COULD BE A MISASSEMBLY OF THE RATCHET WHEEL DURING THE LAST REPAIR OF THE SCREW JACK ASSY IN A REPAIR STATION THAT REMAINS UNDETERMINED. OPEN

Part: SKIN — DAMAGED (RUDDER) · airframe 60,154 hrs · 13,519 cycles

ACCOMPLISH TERMINATING ACTION REPAIR OF RUDDER. NEW REVISION "C" PART 2 OF EA 6-5540-118407 ACCOMPLISHED TERMINATING ACTION REPAIR OF RUDDER IAW EA NR 6-5540-118407 C PT2 AND RAS/DAHAM/4024327/2008 ISSUE A DATED OCT 20, 2009

Part: SUPPORT — FAILED (ZONE 200) · airframe 58,327 hrs · 12,378 cycles

FOUND SUPPORT STRUT WITH LESS EDGE MARGIN BETWEEN FRAME 71-72, STRG 26 RT. REPLACEMENT OF STRUT IAW SRM 51-72-10.

Part: STRINGER — DAMAGED (ZONE 200) · airframe 58,327 hrs · 12,378 cycles

SEVERAL OLD MISDRILLED HOLES ON STRINGER 15 LT, BETWEEN FRAME 35-36. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: SKIN PANEL — CORRODED (ZONE 200) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

EXFOLIATION CORROSION FOUND ON LT FWD PAX DOOR FRAMING AFT PANEL AT FRAME 16A, STRG 25 (IN A HOLE ATTACHING THE SCUFF PLATE). REPAIR PERFORMED BY PARTIALLY REPLACEMENT THE AFFECTED SKIN PANEL: CUT OUT OF THE AFT DOOR SKIN PANEL AT STRG 23 AND INSTALLING NEW ONE AS PER DRW R536-11030 ISSUE B IAW EA 6-5312-81098 AND RAS/AS/0006/2005 ISSUE B.

Part: LONGERON — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

HEAVY CORROSION ON LONGITUDINAL PROFILE (LONGERON) BETWEEN FRAME 66-69 LHS, Y140 OF BULK CARGO COMPARTMENT FLOOR STRUCTURE. REPLACEMENT OF LONGERON IAW SRM 51-72-10.

Part: FRAME — DAMAGED (ZONE 200) · airframe 58,327 hrs · 12,378 cycles

OLD REPAIR ON FRAME 13, STRG 14 LT, FUSELAGE NOSE SECTION. THE REINFORCEMENT REPAIR ANGLE AT FRAME SEGMENT WAS CHAFED AND AFTER REWORK OUT OF LIMIT. REPAIR PERFORMED BY INSTALLING NEW REPAIR ANGLE AT OLD REPAIR AS PER PRINCIPLE IN SRM 53-10-13.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

HEAVY CORROSION ON CROSSBEAM AT FRAME 69 LT, BULK CARGO COMP FLOOR STRUCTURE. CROSSBEAM REPAIR PERFORMED IAW SRM 53-10-15.

Part: STRINGER — DAMAGED (ZONE 200) · airframe 58,327 hrs · 12,378 cycles

FOUND SEVERAL MISDRILLED HOLES ON T-STRINGER 26 RT, AT FRAME 71. REPAIR PERFORMED BY INSTALLING NEW PARTIAL STRINGER PROFILE FABRICATED WITH COUPLINGS IAW ENG-STATEMENT: REA 0492-009.

Part: DOOR FRAME — DAMAGED (ZONE 200) · airframe 58,327 hrs · 12,378 cycles

DURING LT FWD PAX DOOR FRAMING AFT PANEL REPLACEMENT, A DOUBLE HOLE WAS PERFORMED AT FRAME 18, STRG 26 IN LOWER BEAM WEB AT ITS REAR END AND IN STRG 26 COUPLING. REPAIR PERFORMED BY CUT OUT OF LOWER BEAM WEB IAW EA 6-5312-81117 AND RAS/AS/0017/2005 ISSUE A.

Part: SKIN PANEL — CHAFED (ZONE 500) · airframe 58,327 hrs · 12,378 cycles

FOUND CHAFING MARKS ON LT SLAT NR 2 ON LEADING EDGE BETWEEN SLAT TRACK 5 AND TRACK 6. REPAIR PERFORMED BY FLUSH DOUBLER SKIN INSERT IAW SRM 57-41-12/FIG 204.

Part: SKIN — DENTED (NR 3 SLAT) · airframe 58,327 hrs · 12,378 cycles

DENT ON OUTER SKIN LOWER GIRDER AREA AT OUTBOARD BAY OF RT SLAT NR 3. THE DEPTH OF DENT IS 2, 4MM, SPAN WISE WIDE OF 30MM AND CHORD WISE WIDE OF 38MM. REPAIR PERFORMED BY FILLING DENT WITH FILLERALU (MAT 05-051) OR HYSOL EA9394 AS PER SRM 51-73-10 / PARA.3.C, NIL CRACK FINDINGS DURING HFEC INSPECTION. ALL IAW EA 6-5744-81083 AND RAS/SA/155/2004 ISSUE A.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

HEAVY CORROSION ON CROSSBEAM AT FRAME 55/58. CROSSBEAM SPLICE REPAIR PERFORMED IAW SRM 53-10-15/FIG 207.

Part: WEB — CRACKED (ZONE 100) · airframe 58,328 hrs · 12,378 cycles

THE WEB PLATE BETWEEN FRAME 86-87 RT, STRINGER 36 IS CRACKED. REPLACEMENT OF WEB PLATE IAW SRM 51-72-10.

Part: FRAME — DAMAGED (ZONE 200) · airframe 58,327 hrs · 12,378 cycles

FOUND OLD ENLARGED HOLE (DIA 6MM) AT CONNECTING SEGMENT FRAME 55/58, STRG 25 LT. REPLACEMENT OF CONNECTING SEGMENT IAW SRM 51-72-10.

Part: SHEAR PLATE — CRACKED (ZONE 200) · airframe 58,327 hrs · 12,378 cycles

CRACKED SHEAR PLATE AT STR 26 LT, BETWEEN FRAME 79-80. REPLACEMENT OF SHEAR PLATE IAW SRM 51-72-10.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

CORROSION ON LONGITUDINAL PROFILE (LONGERON) BETWEEN FRAME 67-69, STRG 44 RTS. REPLACEMENT OF LONGERON IAW SRM 51-72-10.

Part: RIB — NONE (TE FLAP) · airframe 58,327 hrs · 12,378 cycles

OLD REPAIR ON LT INBOARD FLAP AT END RIB 21. CUSTOMER DECISION TO FINAL REPAIR PER SB A310-57-2055, REPLACEMENT OF END RIB 21.

Part: RIB — NONE (ZONE 600) · airframe 58,327 hrs · 12,378 cycles

OLD REPAIR ON RT INBOARD FLAP AT END RIB 21. CUSTOMER DECISION TO FINAL REPAIR PER SB A310-57-2055, REPLACEMENT OF END RIB 21.

Part: SHEAR PLATE — CRACKED (ZONE 100) · airframe 58,327 hrs · 12,378 cycles

CRACKED SHEAR PLATE BETWEEN FRAME 21-22, STRG 44 LT, FWD CARGO COMP. REPLACMENT OF SHEAR PLATE IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

CORROSION ON STRINGER 51 AT FRAME 54.3 LT. REPAIR PERFORMED BY REPLACING STRINGER PARTIAL, SPLICE WITH ORIGINAL REINFORCEMENT BETWEEN FRAME 54.2-54.3 AND STRINGER SPLICE REPAIR IAW SRM 53-10-14/FIG 201 BETWEEN FRAME 54.3-55/58.

Part: SHEAR PLATE — CRACKED (ZONE 100) · airframe 58,327 hrs · 12,378 cycles

CRACKED SHEAR PLATE BETWEEN FRAME 38.1-38.2, STRG 44 LT, FWD CARGO COMP. REPLACMENT OF SHEAR PLATE IAW SRM 51-72-10.

Part: SKIN PANEL — WORN (ZONE 500) · airframe 58,327 hrs · 12,378 cycles

ELONGATED HYDRAULIC FITTING HOLES ( 2 AND 4 ) AT PYLON SUPPORT BRACKET, BOTTOM WING SKIN LT, RIB 8. REPAIR PERFORMED BY OVERSIZING HOLES AND INSTALLATION OF BUSHINGS IAW EA 6-5720-81089 AND RAS/BAE/100174/2005 ISSUE A.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 58,327 hrs · 12,378 cycles

FOUND OLD CUTTED STRINGER FLANGE AT STRINGER 54 RT, BETWEEN FRAME 21-22, NOT CONFORM TO SRM REPAIR CRITERIAS. REPLACEMENT OF STRINGER IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

CORROSION ON STRINGER 42 RT, BETWEEN FRAME 72-73. STRINGER SPLICE REPAIR IAW SRM 53-10-14/FIG 201.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

CORROSION ON CONNECTING SEGMENT STRG 51 LT, BETWEEN FRAME 54.2-54.3. REPLACEMENT OF CONNECTING SEGMENT IAW SRM 51-72-10.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

HEAVY CORROSION ON CROSSBEAM AT FRAME 63 RT, CARGO COMP FLOOR STRUCTURE. CROSSBEAM REPAIR PERFORMED IAW SRM 53-10-15.

Part: DOOR FRAME — DAMAGED (ZONE 200) · airframe 58,327 hrs · 12,378 cycles

DURING LT FWD PAX DOOR FRAMING AFT PANEL REPLACEMENT, A DOUBLE HOLE WAS PERFORMED AT FRAME 18, STRG 26 IN LOWER BEAM WEB AT ITS REAR END AND IN STRG 26 COUPLING. REPLACEMENT OF STRINGER 26 COUPLING BY NEW ONE IAW EA 6-5312-81117 AND RAS/AS/0017/2005 ISSUE A.

Part: STRUT — DAMAGED (ZONE 100) · airframe 58,328 hrs · 12,378 cycles

FOUND DAMAGED AT CROSS STRUT BETWEEN FRAME 68, STRG 38-45 LT. REPLACEMENT OF THE CROSS STRUT IAW SRM 51-72-10.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

HEAVY CORROSION ON LONGITUDINAL PROFILE (LONGERON) BETWEEN FRAME 66-69 LHS, Y805 OF BULK CARGO COMPARTMENT FLOOR STRUCTURE. REPLACEMENT OF LONGERON IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

DURING NON ROUTINE DR0115, FOUND CORROSION ON STRINGER 51 LT, BETWEEN FRAME 54.1-54.2. PARTIAL STRINGER REPLACEMENT WITH SPLICE REPAIR PERFORMED, BETWEEN FRAME 54.1-54.2 IAW SRM 53-10-14/FIG 201 AND 54.2-54.3 (DR0115).

Part: STIFFENER — CRACKED (ZONE 100) · airframe 58,327 hrs · 12,378 cycles

FOUND CRACK ON STIFFENER AT FRAME 12A LT, STRG 27. REPLACEMENT OF STIFFENER AS PER DWG A536-10318/SH 05.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

HEAVY CORROSION ON CROSSBEAM AT FRAME 66. CROSSBEAM SPLICE REPAIR PERFORMED IAW SRM 53-10-15/FIG 207.

Part: STRINGER CLIP — FAILED (ZONE 100) · airframe 58,327 hrs · 12,378 cycles

FOUND FRAME-STRINGER-CONNECTING ANGLES WITH LESS EDGE MARGIN AT STRINGER 26 RT BETWEEN FRAME 67-68, 69-70 AND 71-72 AND ON STRG 26 LT BETWEEN FRAME 70-71 AND 71-72. REPLACEMENT WITH FABRICATED ENLARGED REPAIR ANGLES IAW SRM 51-72-10.

Part: SKIN PANEL — MISREPAIRED (ZONE 100) · airframe 58,327 hrs · 12,378 cycles

FOUND OLD DOUBLER REPAIR BETWEEN FRAME 11-11A, STRG 27-28 LT, NOT CONFORM TO REPAIR REFERENCE AS PER SRM 53-12-12/FIG 201. DOUBLER REPAIR RENEWED IAW SRM 53-12-12/FIG 201.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

HEAVY CORROSION ON LONGITUDINAL PROFILE (LONGERON) BETWEEN FRAME 66-69 AD, BULK CARGO COMP FLOOR STRUCTURE. REPLACEMENT OF LONGERON IAW SRM 51-72-10.

Part: STRINGER — DAMAGED (ZONE 100) · airframe 58,327 hrs · 12,378 cycles

OLD DAMAGE ON STRINGER 30 RT, BETWEEN FRAME 54.2-54.3. STRINGER SPLICE REPAIR IAW SRM 53-10-14/FIG 201.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 58,327 hrs · 12,378 cycles

OLD EXTERNAL DOUBLER REPAIR ON INBOARD FLAP RT ON LOWER SIDE BETWEEN RIB 10-11, NOT CONFORM TO OLD RECORDS AS PER SRM 57-52-12/FIG 204: EXTERNAL DOUBLER IS ON LOWER SURFACE INSTEAD OF UPPER SURFACE, NO FILLER ON UPPER SURFACE INSTALLED AND NO RIVETS ON TRAILING EDGE. REPAIR OF INBOARD FLAP TRAILING EDGE IAW SRM 57-53-12/FIG 208, APPROVED BY EA 6-5752-81107 AND RAS/DABRE/7009414/2005 ISSUE A.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

HEAVY CORROSION ON CROSSBEAM AT FRAME 67. CROSSBEAM REPLACED IAW SRM 51-72-10.

Part: SKIN PANEL — FAILED (ZONE 100) · airframe 58,327 hrs · 12,378 cycles

FOUND OLD EXTERNAL SKIN DOUBLER REPAIR AT FRAME 33 BETWEEN STRG 49-51 LT, NOT CONFORM TO PTOF CONVERSION: FRAME AND STRAP INSTALLATION FRAME 33 TO DRW, R537B1150-006. REPAIR PERFORMED BY NEW ENLARGED DOUBLER FOLLOW THE PRINCIPLE OF SRM 53-10-12/FIG 225/SH 2, APPROVED BY RAS/DABRE/7004561/2004 ISSUE A.

Part: SKIN PANEL — CRACKED (ZONE 500) · airframe 58,327 hrs · 12,378 cycles

CRACK IN TRAILING EDGE OF BOTTOM SKIN PANEL NR 2, ON LT ZONE 575CB TWO HOLES WITH CRACKS IN SKIN. FOR LOCATION SEE EA 6-5710-81091/PG 3 CRACK LENGTH IN HOLES ABOUT 2 AND 4MM. DOUBLER PLATE INSTALLED, REPAIR PERFORMED IAW. DRW. R573-49237 AND EA 6-5710- 81091.

Part: SKIN PANEL — CRACKED (ZONE 600) · airframe 58,327 hrs · 12,378 cycles

CRACK IN TRAILING EDGE OF BOTTOM SKIN PANEL NR 2, ON RT ZONE 675CB ONE HOLE WITH CRACK IN SKIN. FOR LOCATION SEE EA 6-5710-81091/PG 4 (CRACK LENGTH IN HOLE ABOUT 3MM). DOUBLER PLATE INSTALLED, REPAIR PERFORMED IAW DRW R573-49237 AND EA 6-5710-81091.

Part: BEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,327 hrs · 12,378 cycles

CORROSION ON TOP SURFACE OF AFT CARGO COMP SILL BEAM FLANGE BETWEEN FRAME 59-59A AROUND A RIVET NUT. REMAINING THICKNESS AFTER REWORK IS 0,8MM, NOMINAL: 2,0MM. REPAIR PERFORMED BY CUT OUT AFFECTED AREA AND INSTALLING FILLER AND REPAIR ANGLE IAW ENG-STATEMENT: REA 0492-007 AND EA 6-5317-81087.

Part: BEAM — CORRODED (PAX DOOR) · corrosion level 2 · airframe 58,324 hrs · 12,375 cycles

FOUND CORROSION ON LONGITUDINAL WEB OF BEAM 3 OF PAX DOOR NR 1 RT, BETWEEN XP=590 AND XP=715MM. REMAINING THICKNESS IS 0,5MM, AS THE NOMINAL THICKNESS IS 2,0MM. AFFECTED AREA IS ABOUT 1600MM X MM. REPAIR PERFORMED BY CUTTING CORRODED AREA. INSTALLING A MACHINED ANGLE DOUBLER ON THE WEB OF BEAM 3 AND A REINFORCING STRIP ON THE INTERNAL FLANGE IAW EA 6-5211-81114 AND RAS/AS/0005/2005 ISSUE A.

Part: SMOKE DETECTOR — MALFUNCTIONED (E/E BAY) · airframe 57,270 hrs · 11,744 cycles

ON DEPARTURE AND LEVEL AT 9000, GOT ECAM AND MASTER WARNING FOR AVIONICS SMOKE, DUE TO PROXIMITY TO AIRPORT IMMEDIATELY WENT ON OXYGEN TO RETURN TO KMEM. UNABLE TO CONFIRM ACTUAL SMOKE AND ON APPROACH ECAM ALERT CLEARED. REMOVED AND REPLACED AVI COMPARTMENT SMOKE DETECTOR 13WA AVIONICS COMPARTMENT AS PER MM 26-15-12-4. REPLACED AVIONICS COMP SMOKE DET'S 11WA AND 12WA PER A/C M/M 26-15-12-4, AVIONICS COMP SMOKE DET SYS. TESTS OK PER A/C M/M 26-15-00-5.

Part: SHEAR PIN — FAILED (MLG) · airframe 55,894 hrs · 10,956 cycles

AFTER TAKEOFF FROM KMIA,WHEN THE MLG RETRACTED THE LT MLG DOOR SHOWED UNLOCKED ON FWD PANEL, OVERHEAD PNL,AND ECAM.WHILE GERAR HANDLE WAS IN THE UP POSITION THE AMBER DOOR LIGHT WAS ON AND THE RED GEAR UNLK LIGHT WAS ON.WHEN LDG GEAR HANDLE WAS MOVED TO NEUTRAL, THE MLG GREEN LIGHT ILLUMINATED. FOUND LT MLG SIDE BRACE ACTUATOR MOUNT PIN MISSING, GOUGE IN SIDE BRACE. BLENDED OUT DAMAGED AREA WITHIN LIMITS IAW E.A 6-3210-95470. INSTALLED ATTACH PIN, REPLACED SHEAR PIN, REINSTALLED GEAR DOWNLOCK IND. MECH. IAW A310 M/M32-61-14-4. R&R BRACE STRUT ACTUATOR.