N456FE

Part: PRESSURE SWITCH — FAILED (ENGINE OIL) · airframe 36,749 hrs · 16,445 cycles

REJECTED TAKE OFF AT 85KTS DUE TO ECAM WARNING WARNING, LOW OIL PRESSURE ENGINE NR 2. WARNING WENT AWAY WHEN THROTTLES RETARDED. CHECKED ALL ENGINE PARAMENTERS PRIOR TO 2ND TAKE OFF. ALL NORMAL, 2ND TAKE OFF NORMAL. R & R NR 2 ENGINE OIL PRESSURE TRAMSMITTER IAW MM 79-33-11-04, R & R NR 2 ENGINE LOW OIL PRESSURE SWITCH IAW MM 79-34-11-04. REQUIRES NR 2 ENGINE RUN AND LEAK CHECKED IAW MM 79-33-00-05.

Part: REGULATOR VALVE — FAILED (NR 2 ENGINE) · airframe 35,846 hrs · 15,865 cycles

GOT HIGH OIL PRESSURE NR 2 ENG ON T/O ROLL. REJECTED T/O AT LOW SPEED. SECOND TAKEOFF NORMAL. 1ST T/O 62PSI, 2ND T/O 58 PSI. R & R 2 ENGINE OIL PRESSURE REGULATOR VALVE REF AMM 79-21-04-04-0. PERFORMED OIL PRESSURE TEST NR 7, REF 71-00-00, RAN NR2 ENGINE IAW JRH. AFTER START OIL PRESSURE TURNED AMBER AND CLIMBED TO 64 PSI. ADJUSTED NR2 ENGINE OIL PRESSURE REGULATOR REF ENGINE MANUAL 71-00-00 TEST NR 7. RAN NR2 ENGINE IAW JRH. OIL PRESSURE STABILIZED AT 48 PSI AFTER 5 MINUTES. REGULATING VALVE COVER PLUG NEEDS SAFETY WIRE. SAFETIED NR 2 ENG MAIN OIL PRESS REG VLV PLUG REF AMM 79-21-04-04. RAN ENG IAW JRH. ALL PARAMETERS NORMAL. IDLE OIL PRESS STEADY AT 50 PSI. ACFT OK FOR SVC.

Part: OIL COOLER — FALSE ACTIVATION (OIL SYSTEM) · airframe 35,842 hrs · 15,862 cycles

GOT HIGH ENG OIL PRESSURE NR 2 ENG ON T/O ROLL. REJECTED T/O INDICATIONS WERE BACK TO NORMAL AFTER EXITING RUNWAY. RAN NR 2 ENG IAW JRH. NO DEFECTS NOTED. OIL NEVER ROSE ABOVE 58 PSI WITH THROTTLE ADVANCED AND WAS 50 TO 52 PSI AT IDLE. OIL TEMP WAS ALSO WITHIN LIMITS. GENERATING MTSI AND SUGGESTS FUEL/OIL COOLER. UPDATED ETIC, PART 6. R & R NR 2 ENGINE FUEL/OIL COOLER IN REF TO AMM 79-21-05-04.

Part: SKIN — DAMAGED (ZONE 500) · airframe 35,828 hrs · 15,856 cycles

LT WING - INBD FLAP - T/E SKIN FOUND DAMAGED. DUE TO NON APPROVED EXISTING REPAIRS THE T/E HAD TO BE REPLACED.

Part: PROFILE — MISREPAIRED (ZONE 500) · airframe 35,828 hrs · 15,856 cycles

PREVIOUS REPAIR FOUND AT T/E PROFILE BTW RIB4/5 NOT TO CONFORM WITH FAA APPROVED DATA. T/E WAS REPLACED IAW EA 6-5750-144066 INSTRUCTIONS.

Part: PROFILE — MISREPAIRED (ZONE 500) · airframe 35,828 hrs · 15,856 cycles

PREVIOUS REPAIR FOUND AT T/E PROFILE BETWEEN RIB13/15 NOT TO CONFORM WITH FAA APPROVED DATA. T/E WAS REPLACED IAW EA 6-5750-144066 INSTRUCTIONS.

Part: PROFILE — MISREPAIRED (ZONE 500) · airframe 35,828 hrs · 15,856 cycles

PREVIOUS REPAIR FOUND AT T/E PROFILE BTW RIB11/15 NOT TO CONFORM WITH FAA APPROVED DATA. T/E WAS REPLACED IAW EA 6-5750-144066 INSTRUCTIONS.

Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 35,828 hrs · 15,856 cycles

PREVIOUS REPAIR FOUND AT LT INBD FLAP LOWER SKIN BTW STGR 13 & REAR SPAR AND RIBS 12/14. NEW REPAIR PERFORMED IAW EA 6-5750-144069. REPAIR NR2.

Part: SKIN — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 35,828 hrs · 15,856 cycles

FWD CARGO COMPARTMENT DOOR - LOWER INTERNAL SKIN FOUND CORRODED. PANEL SKIN WAS REPLACED AS PER SRM 51-72-10.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 35,828 hrs · 15,856 cycles

FWD CARGO DOOR - CRACK FOUND AT INNER PLATE AT LOWER AFT CORNER. INNER SKIN REPAIRED IAW 6-5230-144190.

Part: CROSSBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 35,828 hrs · 15,856 cycles

AFT CARGO COMPT FLOOR - TRANSVERSAL BEAM AT FR58 FOUND CORRODED. CROSSBEAM WAS REPLACED IAW 51-72-10.

Part: FITTING — CORRODED (ZONE 800) · airframe 35,828 hrs · 15,856 cycles

FITTING LOCATED AT L1 DOOR FOUND CORRODED. REPLACED BY A NEW ONE.

Part: CROSSBEAM — DAMAGED (ZONE 100) · airframe 35,828 hrs · 15,856 cycles

FWD CARGO COMPARTMENT - CROOSBEAM UPPER FLANGE AT FR36 DAMAGED BTW Y480 & Y- 480. CROSSBEAM WAS REPAIRED IAW SRM 53-10-15 FIGURE207.

Part: CROSSBEAM — DAMAGED (ZONE 100) · airframe 35,828 hrs · 15,856 cycles

FWD CARGO COMPARTMENT - CROSSBEAM UPPER FLANGE AT FR25 DAMAGED BTW Y480 & Y- 480. CROSSBEAM WAS REPAIRED IAW SRM 53-10-15 FIG 207.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 35,828 hrs · 15,856 cycles

PREVIOUS REPAIRED DENTS NOT LISTED IN THE MCMRT AT RT FLAP INBD LOWER SKIN. DENT 1 - BTW RIB 5 & RIB 6 AND BTW FRONT SPAR & STRINGER 9. DENT 2 AND DENT 3 - BTW RIB 10 & RIB 11 AND STRINGER 11 & REAR SPAR. REPAIR OF THE DENTS IAW EA 6-5710-50143.

Part: FRAME — MISREPAIRED (ZONE 100) · airframe 35,828 hrs · 15,856 cycles

FWD CARGO COMPARTEMENT - PREVIOUS REPAIR FOUND AT FR20A NOT IAW FAA APPROVED DATA. NEW REPAIR TO THE FR20A PERFORMED IAW EA 6-5310-144063.

Part: FITTING — MISREPAIRED (ZONE 200) · airframe 35,828 hrs · 15,856 cycles

MAIN DECK FLOOR STRUCTURE - PREVIOUS REPAIR FOUND AT FITTING LOCATED BTWN FR11 & FR15A AT Y 1500. REPAIR DOES NOT CONFORM WITH AN EXISTING SRM REPAIR. FLOOR FITTING WAS REPLACED IAW SRM 51-72-10.

Part: SKIN — DENTED (NR 1 SLAT) · airframe 35,828 hrs · 15,856 cycles

RT WING - SLAT NR1 L/E - PREVIOUS DENT FOUND AT RIB 4. EVALUATED AND FOUND TO BE CONFORM WITH EA 6-5710-50155. DENT WAS FILLED USING THE GUIDELINES OF SRM 51-73-10.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 35,828 hrs · 15,856 cycles

SEAT TRACK Y954 FOUND CORRODED BTW FR18 & FR19. SEAT TRACK REPLACED BY A NEW ONE.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 35,828 hrs · 15,856 cycles

RIGHT THS TOP SKIN - CONNECTION PART AT THE INTERIOR OF THE SPAR BOX AT S11 FOUND CORRODED BTW RIB 3 & RIB 4. CONNECTION WAS REPLACED IAW 51-72-10 AFTER FABRICATION.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 35,828 hrs · 15,856 cycles

RT THS TOP SKIN - CONNECTION PART AT THE INTERIOR OF THE SPAR BOX AT STGR9 FOUND CORRODED BTW RIB3 & RIB4. CONNECTION WAS REPLACED IAW 51-72-10 AFTER FABRICATION.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 35,828 hrs · 15,856 cycles

RT THS BOTTOM SKIN - CONNECTION PART AT THE INTERIOR OF THE SPAR BOX AT STGR9 FOUND CORRODED BTW RIB3 & RIB4. CONNECTION WAS REPLACED IAW 51-72-10 AFTER FABRICATION.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 35,828 hrs · 15,856 cycles

RT THS TOP SKIN - CONNECTION PART AT THE INTERIOR OF THE SPAR BOX AT STGR10 FOUND CORRODED BTW RIB3 & RIB4. CONNECTION WAS REPLACED IAW 51-72-10 AFTER FABRICATION.

Part: SKIN — MISREPAIRED (CARGO DOOR) · airframe 35,828 hrs · 15,856 cycles

BULK CARGO DOOR - PREVIOUS REPAIR FOUND AT INTERNAL SKIN, LOCATED BTW FR67 & FR69 AND BTW BEAM1 & BEAM4, NOT CONFORM WITH SRM. NEW REPAIR WAS PERFORMED IAW SRM 52-30-00, FIG 206.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 35,828 hrs · 15,856 cycles

LT THS BOTTOM SKIN - CONNECTION PART AT THE INTERIOR OF THE SPAR BOX AT STGR11 FOUND CORRODED BTW RIB3 & RIB4. CONNECTION WAS REPLACED IAW 51-72-10 AFTER FABRICATION.

Part: SKIN — DEBONDED (RT WING TE FLAP) · airframe 35,828 hrs · 15,856 cycles

RT OTBD FLAP - LOWER SKIN BTW RIB2 AND RIB3 FOUND DEBONDED. REPAIRED IAW E.A. 6-5750-144062.

Part: SKIN — DEBONDED (RT WING TE FLAP) · airframe 35,828 hrs · 15,856 cycles

FLAP OTBD RT - LOWER SKIN SURFACE BTW RIB7 AND RIB 9 FOUND DEBONDED. FLAP OUTBOARD DISBONDED AREA WAS REPAIR IAW EA 6-5750-144062.

Part: SPACER — CRACKED (RT MLG WW) · airframe 35,828 hrs · 15,856 cycles

RIGHT MLG W/W - SPACER WITH CRACK LOCATED AT FR54 AND AT Y-450 AND Z-1357. AFTER HFEC AND ROTOTEST THE CRACKS REPORTED BY THE VISUAL INSP WERE NOT CONFIRMED. IT WAS JUST A FLAW IN THE SURFACE PROTECTION SYS.

Part: SKIN — DAMAGED (RT ELEVATOR) · airframe 35,828 hrs · 15,856 cycles

RIGHT ELEVATOR BOTTOM SKIN - PREVIOUS REPAIR FOUND AT T/E AT STA 144/ER1. REPAIR REQUIRES EVALUATION. PREVOUS REPAIR FOUND DAMAGED (DEBONDED) AND IT WAS REMOVED. NEW REPAIR HAS BEEN ACCOMPLISHED IAW SRM 55-21-11, FIG 210.

Part: SKIN — MISREPAIRED · airframe 35,828 hrs · 15,856 cycles

FLAP INBD LT LOWER SKIN - PREVIOUS REPAIR FOUND BETWEEN RIB13/14 AND STGR 8/11. REPAIR WAS EVALUATED AND FOUND NOT TO CONFORM TO THE SRM. NEW REPAIR ACCOMPLISHED IAW EA 6-5750-144069 INSTRUCTIONS.

Part: SKIN — DAMAGED (RT ELEVATOR) · airframe 35,828 hrs · 15,856 cycles

RT ELEVATOR TOP SKIN FOUND WITH DEBONDING AT T/E STA473/ER19. RT ELEVATOR HAS BEEN REPAIR IAW SRM 55-21-11, FIG 210.

Part: SKIN — DENTED (FUSELAGE) · airframe 35,828 hrs · 15,856 cycles

FUSELAGE SKIN - PREVIOUS DENT FOUND LOCATED BTW FR 2-3 IN LOWER SECTION. DENT WAS CUT-OFF AND REPAIRED IAW THE SRM 53-11-12, FIG 201 AND 53-10-12 FIG217.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 35,828 hrs · 15,856 cycles

FUSELAGE SKIN - PREVIOUS REPAIR FOUND LOCATED AT FR25A BTW S48-50R. EXISTING REPAIR WAS NOT IN COMPLIACE WITH THE SRM. NEW REPAIR ACCOMPLISHED IAW SRM 53-10-12, FIG 228.

Part: VANE — MISREPAIRED (LT WING TE FLAP) · airframe 35,828 hrs · 15,856 cycles

LT INBD FLAP VANE - T/E BOTTOM SKIN - PREVIOUS REPAIR FOUND BTW RIB 9-10. REPAIR WAS REMOVED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. FLAP VANE WAS REPLACED IAW AMM 27-50-15.

Part: VANE — MISREPAIRED (LT WING TE FLAP) · airframe 35,828 hrs · 15,856 cycles

LT INBD FLAP VANE - L/E SKIN WITH PREVIOUS REPAIR FOUND BETWEEN RIB 9-10. REPAIR WAS REMOVED AND FOUND NOT TO BE IAW THE SRM. FLAP VANE REPLACED AS PER AMM 27-50-15.

Part: SKIN — DAMAGED (RT ELEVATOR) · airframe 35,828 hrs · 15,856 cycles

RT ELEVATOR - TOP SKIN FOUND DEBONDED AT THE T/E STA 323/ER11. RT ELEVATOR HAS BEEN REPAIRED IAW SRM 55-21-11, FIG 210.

Part: LUG — CORRODED (RT WING) · airframe 35,652 hrs · 15,697 cycles

RT MLG RIB 5 FWD LUG EXCEEDED ALLOWABLE LIMITS IAW DWG AFTER REMOVAL OF LEVEL 1 CORROSION. FABRICATED AND INSTALLED NEW BUSHING IAW EA 6-5710-135199.

Part: PRESSURE SWITCH — FAILED (HYD SYSTEM) · airframe 33,240 hrs · 14,562 cycles

YELLOW HYD PUMP FAILED AT FLAP RETRACTION. PERFORMED NR 2 ENGINE RAN,VERIFIED YELLOW HYD SYS PRESSURE IS 2900 PSI ON ECAM, YELLOW SYS LOW PRESS LIGHT FLICKER MOMENTARILY DURING FLAPS EXTENSION AND RETRACTION, NEED PRESS SWITCH CPN 0030767, MPN BSG0001-5505 NIL IN SFS STORE. ACN RELEASED FOR SERVICE PER MEL/CDL: 29-34-01-B CATEGORY: C EXPIRATION: 07SEP08 "MEL 29-34-01-B: ENG 2 HYD PUMP LOW PRESSURE LIGHT(S) INOP. MONITOR ECAM HYD PWR PAGE FOR LOW PRESSURE WARNINGS. REFER TO MEL 29-34-01-B FOR (O) PROCEDURE TO VERIFY CORRECT PUMP OPERATION PRIOR TO DEPARTURE." C/0372261. REMOVED AND REPLACED Y SYS ENG PUMP SW (6GD) PER AMM 29-13-62-4. PERFORMED ENG RUN PER JRH, NO HYD LEAK FOUND, TEST NORMAL. HYDRAULIC IND 3000 PSI.

Part: SKIN — DELAMINATED (ZONE 600) · airframe 33,089 hrs · 14,491 cycles

RT WING, INBD FLAP TRAIL EDGE UPPER AND LOWER SURFACE DELAMINATED AT 15.0 INCH FROM INBD EDGE, MEASURING 5.0 BY 2.0 INCH REPAIRED THE DELAMINATED WEDGE PER EA NR 6-5720-117366.

Part: LONGERON — CORRODED (PAX DOOR) · corrosion level 2 · airframe 33,089 hrs · 14,491 cycles

LT PAX/CREW DOOR LONGERON POSITION NR 2 WITH MILD/EXFOLIATION CORROSION BETWEEN FR15A-16. REMOVED CORROSION PER SRM 51-74-10. APPLIED ALODINE TO THE REWORKED AREA PER SRM 51-21-10. MEASURED REMAINING THICKNESS PER NTM 51-10-04. THE ORIGINAL THICKNESS IS 0.063 INCH PER DWG:A52111307 ALLOWABLE DAMAGE IS 20 PERCENT PER SRM 52-10-00. EXCEEDED LIMIT. CUT OUT THE CORRODED AREA AND DEBURR THE CUT EDGES PER SRM 52-10-00. FABRICATED THE REPAIR PART PER SRM 52-10-00. DRILLED FASTENER HOLES TO THE REPAIR PART PER SRM 51-40-50. APPLIED ALODINE TO THE REPAIR PART PER SRM 51-21-10. APPLIED PRIMER TO THE REPAIR PART PER SRM 51-75-10. INSTALLED THE REPAIR PART PER SRM 51-40-21. APPLIED FINISH PER SRM 51-75-10.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,089 hrs · 14,491 cycles

FR 12 - FR 12A Y1456 LONGERON FOR SUPPORTING OF MAIN DECK FLOOR CORRODED. REPAIRED THE DAMAGE PER EA NR 5310-117358.

Part: ROLLER — INOPERATIVE (RT WING TE FLAP) · airframe 33,089 hrs · 14,491 cycles

RT INBD FLAP TRACK NR 2, UPON REMOVAL OF INBD FLAP FOUND 2 FRONT CARRIAGE ROLLER AND 1 REAR CARRIAGE ROLLER SEIZED. DISASSEMBLED ROLLERS PER CMM 27-51-54, CLEANED AND INSPECTED, FOUND ROLLERS WITH SURFACE CORROSION ON MATING SURFACE. REMOVED THE ROLLERS PER CMM 27-51-54. CLEANED THE ROLLERS PER CMM 27-51-54. LUBRICATED THE ROLLERS PER AMM 12-22-00-0. INSTALLED THE ROLLERS PER CMM 27-51-54.

Part: ARM — CORRODED (RUDDER HINGE) · corrosion level 3 · airframe 33,089 hrs · 14,491 cycles

NR 1 RUDDER HINGE ARM FORWARD ATTACH AREA FORWARD OF BEARINGS EXFOLIATED. REMOVED CORROSION AND POLISHED REWORK AREA PER SRM 51-76-10, APPLIED ALODINE TO THE REWORK AREA PER SRM 51-21-10. PERFORM HFEC TO REWORK AREA FOR CRACK, NO CRACK FOUND PER NTM 51-10-09/801 AND REPAIRED PER EA 6-5530-117380. MAJOR REPAIR PER GMM 6-2-100.

Part: FLOORBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 33,089 hrs · 14,491 cycles

MAIN DECK CROSSBEAM C14(FR14) -Y1220 TO -Y1300 LOWER FREE FLANGE WITH EXFOLIATION CORROSION. REMOVED THE PULLEY BRACKET PER AMM 20-29-11-0. REMOVED CORROSION PER SRM 51-74-10. APPLIED ALODINE TO THE REWORKED AREA PER SRM 51-21-10. MEASURED REMAINING THICKNESS IS 0.096 INCH PER NTM51-10-04. IT IS WITHIN THE LIMIT PER SRM 53-12-15-101. APPLIED FLAP PEENING INTENSITY=0.15MM.N TO THE REWORKED AREA PER SRM 51-29-00. APPLIED PAINT PER SRM 51-75-10. INSTALLED PULLEY BRACKET PER AMM 20-29-11-0. PERFORMED INSPECTION TO THE REWORKED AREA PER SRM 53-12-15-1-001-00.

Part: NONE — NONE (NOT AN SDR) · airframe 33,089 hrs · 14,491 cycles

NR 2 PYLON REPAIR INSTALLED ON PRECOOLER WEB DOES NOT MEET REQUIREMENTS PER SRM. REMOVED THE ORIGINAL REPAIR PART PER SRM 51-40-21. DRILLED CRACK STOP HOLES (4.8MM) PER SRM 54-52-31. FABRICATED REPAIR PART PER SRM 54-52-31. DRILLED FASTENER HOLES TO THE REPAIR PART PER SRM 54-52-31. INSTALLED THE REPAIR PART PER SRM 51-40-21.

Part: FLOORBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 33,089 hrs · 14,491 cycles

MAIN DECK CROSSBEAM C14, LBL 55.0, INNERGRANULAR CORROSION ON LOWER FLANGE. REMOVED CORROSION PER SRM 51-74-10. MEASURED REMAINING THICKNESS PER NTM 51-10-04. FOUND WITHIN LIMIT (REMAINING THICKNESS: 0.096 INCH). APPLIED FLAP PEENING PER SRM 51-29-00. REPAINTED AREA PER SRM 51-75-10.

Part: RIB — CRACKED (PYLON) · airframe 33,089 hrs · 14,491 cycles

WEB CRACKED LOWER END FORWARD OF RIB 18 LEFT SIDE NR 2 PYLON. DRILLED CRACK STOP HOLES PER SRM 51-40-21. REMOVED THE RELATED FASTENERS PER SRM 51-40-21. MANUFACTURED THE DOUBLER AND BROKE SHARP EDGES PER SRM 51-26-20. DRILLED FASTENER HOLES TO THE WEB AND THE DOUBLER PER SRM 51-40-50. INSTALLED THE DOUBLER PER SRM 51-40-21.

Part: RIB — CRACKED (ZONE 400) · airframe 33,089 hrs · 14,491 cycles

WEB CRACKED LOWER END FORWARD OF RIB 18 RIGHT SIDE NR 2 PYLON. DRILLED CRACK STOP HOLES PER SRM 54-52-31. REMOVED THE RELATED FASTENERS PER SRM 51-40-21. MANUFACTURED THE DOUBLERS AND BROKE SHARP EDGES PER SRM 51-26-20. DRILLED FASTENER HOLES TO THE WEB AND THE DOUBLERS PER SRM 51-40-50. INSTALLED THE DOUBLER PER SRM 51-40-21.

Part: WEB — CRACKED (ZONE 400) · airframe 33,089 hrs · 14,491 cycles

WEB CRACKED OUTBOARD OF PRECOOLER NR 1 PYLON. DRILLED CRACK STOP HOLES PER SRM 54-52-31. REMOVED THE RELATED FASTENERS PER SRM 51-40-21. MANUFACTURED THE DOUBLER AND BROKE SHARP EDGES PER SRM 51-26-20. DRILLED FASTENER HOLES TO THE WEB AND THE DOUBLER PER SRM 51-40-50. INSTALLED THE DOUBLER PER SRM 51-40-21.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,089 hrs · 14,491 cycles

AFT CARGO COMPARTMENT FLOORBEAM UPPER CHORD ALONG FR 63 LBL60 (153CM) WITH EXFOLIATION CORROSION. REMOVED THE RELATED BALL MAT TRAY PER AMM 25-52-22-4. CUT OUT AND REMOVED DAMAGED CROSSBEAM SECTION PER SRM 51-27-00. FABRICATED THE REPAIR PARTS PER SRM 53-10-15. DRILLED FASTENER HOLES TO THE REPAIR PART PER SRM 53-10-15. APPLIED ALODINE PER SRM 51-21-00. APPLIED PRIMER AND TOPCOAT TO THE REPAIR PARTS PER SRM 51-23-00. INSTALLED REPAIR PARTS PER SRM 51-40-21. RESTORED FINISH PER SRM 51-75-10. APPLIED CORROSION PREVENTIVE COMPOUND PER AMM 51-22-00. INSTALLED THE BALL MAT TRAY PER AMM 25-52-22-4.

Part: STRAP — CORRODED (FUSELAGE) · airframe 33,089 hrs · 14,491 cycles

FWD CARGO COMPT BELOW FLOOR LEVEL BETWEEN FR38.2 - FR39, STR 56L-STR 57(CTR) SKIN STRAP WITH LIGHT CORROSION. REMOVED THE RELATIVE FASTENERS FOR ACCESS PER SRM 51-40-21. REMOVED THE CORROSION PER SRM 51-74-10/201. APPLIED AN ALODINE COATING PER SRM 51-21-10/001. THE REMAINING THICKNESS IS 0.049 INCH (EXCEEDED LIMIT) PER NTM 51-10-04. REPAIR PER EA 6-5310-117360.

Part: ATTACH FITTING — CORRODED (PYLON) · airframe 33,089 hrs · 14,491 cycles

PYLON TO ENGINE AFT ATTACHMENT BEAM CORROSION ON MATING FACE. CLEAN THE BEAM CAREFULLY PER AMM 12-21-12. PERFORMED DVI FOR CORROSION (FOUND CORROSION). REMOVED CORROSION USING ABRASION BY HAND AS PER SRM 51-74-10,PARAGRAPH 7.B. MEASURED THE REWORKED AREA AND THE REMOVAL THICKNESS OF MATERIAL. PERFORMED MANTENANCE ACTIONS IAW EA 6-5450-117357.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 33,089 hrs · 14,491 cycles

FR15C-FR17-Y953 MAIN DECK SEAT TRACK CORRODED. REMOVED THE RELATIVE FASTENERS FOR ACCESS PER SRM 51-40-21. REMOVED THE CORROSION PER SRM 51-74-10/201. APPLIED ALODINE COATING PER SRM 51-21-10/001. NDT MEASURED THE REMAINING THICKNESS PER NTM 51-10-04. THE ORIGINAL THICKNESS OF THE REWORKED FLANGE IS 0.079 INCH, OUT OF THE ALLOWABLE LIMITS PER SRM 53-12-16 & 53-10-00. REMOVED THE DAMAGED SEAT TRACK PER SRM 51-40-21. FABRICATED A NEW SEAT TRACK PER DWG: A53611640. DRILLED FASTENER HOLES IN THE NEW PART PER SRM 51-40. APPLIED ALODINE PER SRM 51-21-10. INSTALLED THE NEW PARTS PER SRM 51-40-21. RESTORED FINISH PER AMM 51-75-10.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 33,089 hrs · 14,491 cycles

FR12-FR12A Y1456 LONGERON FOR SUPPORTING OF MAIN DECK FLOOR CORRODED. REPAIR THE DAMAGE PER EA 6-5310-117358.

Part: STRAP — CORRODED (FUSELAGE) · airframe 33,089 hrs · 14,491 cycles

FWD CARGO COMP BELOW FLOOR LEVEL BETWEEN FR 38.2 - FR 39, STGR 55R - STGR 56R SKIN STRAP WITH LIGHT CORROSION. REMOVED THE RELATIVE FASTENERS FOR ACCESS PER SRM 51-40-21. REMOVED THE CORROSION PER SRM 51-74-10/201. APPLIED AN ALODINE COATING PER SRM 51-21-10/001. THE REMAINING THICKNESS IS 0.049 INCH (EXCEEDED LIMIT) PER NTM 51-10-04. REPAIR PER EA6-5310-117360.

Part: BULKHEAD — CORRODED (MLG WW) · airframe 33,089 hrs · 14,491 cycles

NOSE WHEEL WELL-STA 1090/FR11, LIGHT SURFACE CORROSION FOUND ON W/W FWD WALL, LOCATED RBL8.0 BETWEEN STIFFENERS 5/6. REMOVED THE LIGHT CORROSION PER SRM 51-74-10. APPLIED ALODINE PER SRM 51-21-10. NO CRACK FOUND PER NTM 51-10-08. THE REMAINING THICKNESS IS 0.087 INCH PER NTM 51-10-04. REPAIR PER EA 6-5310-117363.

Part: ANGLE — UNKNOWN (FUSELAGE) · airframe 33,089 hrs · 14,491 cycles

FR 54-Y450 THE UPPER ANGLE FOR MOUNTING OF BULKHEAD LINING OF AFT CARGO COMPARTMENT. REMOVED THE RELATIVE FASTENERS FOR ACCESS PER SRM 51-40-21. REMOVED THE CORROSION PER SRM 51-74-10/201. APPLIED AN ALODINE COATING PER SRM 51-74-10/001. NDT MEASURED THE REMAINING THICKNESS PER NTM 51-10-04. THE ORIGINAL THICKNESS IS 0.098 INCH PER SRM 53-15-18/001 ALLOWABLE DAMAGE IS 10% PER SRM 53-10-00/101, IT IS NOT WITHIN THE LIMIT. MAKE THE REPAIR PART PER DWG: A53410767200. INSTALLED THE REPAIR PART PER SRM 51-40-21. RESTORED FINISH PER AMM51-75-10.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 33,089 hrs · 14,491 cycles

HFEC FOUND ONE CRACK ABOUT 17MM AT ZONE B OF FRAME 12A STIFFENER FITTING LT. ACCOMPLISH EO6-5340-7-5002 PART 2 AND PART 3.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,089 hrs · 14,491 cycles

FR 15A-FR 15C Y50 MAIN DECK SEAT TRACK CORRODED. REMOVED THE RELATIVE RASTENERS FOR ACCESS PER SRM 51-40-21. REMOVED THE CORROSION PER SRM 51-74-10/201. APPLIED AN ALODINE COATING PER SRM 51-21-10/001. NDT MEASURED THE REMAINING THICKNESS PER NTM 51-10-04. THE ORIGINAL THICKNESS IS 0.078 INCH, IT IS NOT WITHIN 0.012 IN ALLOWABLE CLEANUP LIMIT PER SRM 53-10-16/101. MAKE THE SEAT TRACK PER DWG: A53611640200. DRILLED FASTENER HOLES IN THE NEW PART PER SRM 51-40-21. APPLIED ALODINE PER SRM 51-21-10. APPLIED PAINT PER AMM 51-75-10. REPLACED AND INSTALLED THE SEAT TRACK PER SRM 51-40-21. RESTORED FINISH PER AMM 51-75-10.

Part: SKIN — CORRODED (FUSELAGE) · airframe 33,089 hrs · 14,491 cycles

BETWEEN C23 AND C24, S-50R FUSELAGE SKIN INTERNAL SURFACE CORRODED AROUND THE RIVET BUCKING HEAD. REMOVED CORROSION COMPLETELY PER SRM51-74-10. REPAIRED PER SRM 53-13-12 REPAIR SOLUTION NR 6, FIGURE 202.

Part: TRUNNION — CORRODED (NR 1 JACKSCREW) · airframe 33,089 hrs · 14,491 cycles

RT WING, UPON SCHEDULED INSP FOUND NR 1 FLAP SCREWJACK TRUNNION AND BUSHING WITH LIGHT PITTING CORROSION INSTALLED NEW FLAP SCREWJACK TRUNNION AND BUSHING PER AMM 27-54-37-4. PERFORMED OPS CHECK PER AMM 27-54-00-5, OPERATION NORMAL

Part: SKIN — DENTED (FUSELAGE) · airframe 33,089 hrs · 14,491 cycles

LOWER FUSE STA 3461/FR64-STA 3514/FR65, S31R-S34R 1 DENT ON EXTERNAL SKIN (13 INCH BY 0.5 INCH BY 0.007 INCH) SEE DETAILED EA6-5330-117353.

Part: SILL — CORRODED (FUSELAGE) · airframe 33,089 hrs · 14,491 cycles

AFT CARGO COMP DOOR SILL BEAM WITH MILD CORROSION ALONG FLOOR LEVEL FR 59A RBL62 (158CM). REMOVED THE RELATED STRUCTURE PER SRM 51-40-21.2. REMOVED CORROSION PER SRM 51-74-10. APPLIED ALODINE TO THE REMOVED AREA. MEASURED THE REMAINING THICKNESS PER NTM51-10-04.101, THE THICKNESS IS 0.081 INCH. THE DETAILED REPAIR SEE EA NR 6-5310-117355.

Part: ARM — CORRODED (RUDDER) · corrosion level 3 · airframe 33,089 hrs · 14,491 cycles

NR 6 RUDDER HINGE ARM EXFOLIATED AT RUDDER ATTACH FITTING, WILL REPLACE. REPLACED NR 6 RUDDER HINGE ARM P/N A5507853000466

Part: COUPLING — LEAKING (HYD SYSTEM) · airframe 30,970 hrs · 13,552 cycles

YELLOW SYSTEM HYD FLUID LOST DURING CRUISE. FOUND HYDRAULIC FLUID LEAKING FROM PRIORITY VALVE UNION IN STABILIZER COMPT AND PACKING WAS DAMAGED. REPLACED PACKING AND RESECURED UNION PER SMP REF IPC 27-44-04-10 ITEM 40. PERFORMED ENGINE RUN AND C/OUT, LEAK CHK FOUND SATISFACTORY.

Part: FRAME — CRACKED (THRUST REVERSER) · airframe 29,659 hrs · 12,912 cycles

COMPLY WITH EA 6-7832-92394 EXHAUST, T/R ASSY - REPAIR OF T/R AFT BARREL INNER FRAMES. COMPLIED WITH EA 6-7832-92394 EXHAUST - T/R ASSY - REPAIR OF T/R AFT BARREL INNER FRAMES.

Part: SKIN — CRACKED (LT WING TE) · airframe 29,659 hrs · 12,912 cycles

LOWER SURFACE OF LT WING TE AT THE I/B MOST OF OUTBD FLAP THERE IS A CRACK EMMINATING REPAIRED IAW AIRBUS REPAIR DRAWING R572.

Part: SKIN — DAMAGED (THRUST REVERSER) · airframe 29,659 hrs · 12,912 cycles

COMPLY WITH EA 6-7830-92391 EXHAUST THRUST REVERSER AFT INNER BARREL SKIN REPAIR NR 2 ENGINE RIGHT T/R. COMPLIED WITH EA 6-7830-92391A EXHAUST - THRUST REVERSER - AFT INNER BARREL SKIN REPAIR NR 2 ENGINE RIGHT T/R.

Part: BEARING — UNKNOWN (PYLON) · airframe 29,659 hrs · 12,912 cycles

COMPLY WITH EA 6-5720-92381 INSPECTION/CHECK OF PYLON AFT ATTACH FITTING UPPER BEARINGS ENT BY: 501863 RPT BY: 501863 FACT 20JAN06 07:25 BFM R COMPLIED WITH EA 6-5720-92381 INSPECTION CHECK OF PYLON AFT ATTACH FITTING UPPER BEARINGS RII:573074 ENT BY: 573371 RPT BY: 573371.

Part: FMC — FAILED (NR 1) · airframe 29,350 hrs · 12,734 cycles

DURING T/O FMC NR 1 FAILED AND RETURNED ON INITIAL FOLLOWED BY NUMEROUS FAULTS ON OVERHEAD PANEL, SLATS/FLAP 1 AND 2 FAULTED, ATS 1 AND 2 FAILED, PITCH NR 1 AND YAW DAMP NR 1 DROPPED OFF, FOLLOWED BY FUEL PUMPS ON NR 1. RT OUTER AND LT NR 2 OUTER PUMPS FAILED AND LEFT WINDOWS HEAT FAILED. NR 1 GEN FAILED AND APU WAS OFF ACN RELEASED FOR SERVICE PER MEL/CDL: 24-11-01CATEGORY: B EXPIRATION: 28JUL05 "MEL 24-11-01: GEN (IDENTIFY 1 OR 2) 1 INOP. TROUBLESHOT PER TSM 24-00-00 PG 155. CHECKED GEN FEEDER CABLE AND FOUND CABLE TERMINAL BLOCK TO IDG LOOSE. CLEANED, RETORQUED TERMINALS/CLEARED MEL.

Part: WIRE HARNESS — CHAFED (EGT) · airframe 29,322 hrs · 12,722 cycles

ENG NR 2 EGT ANALOG INDICATION CONSTANTLY SWINGS BETWEEN 440 DEG C TO 460 DEG C IN CRZ. NR 1 EGT STABLE AT 450 DEG C. ENG NR 2 EGT INDICATION ERRATIC AS WELL DURING APPROACH. T/S IN PROGRESS. PERFORMED T/S ACC TO TSM 77-21-00 AND AMM 77-21-03-5-A. FOUND EGT HARNESS CHAFING WITH COWLING AT POSITION 6 O'CLOCK. TEMPORARY REPAIRED WITH ELEC PLASTIC TA PE IAW ESMP. NR 2 ENG RUN UPPER JRH ALL PARAMETERS READ NORMAL BY AMT 418749. NR 2 ENG COWLING OPENED/CLOSED PER AMM 71-13-00.

Part: WARNING LIGHT — ILLUMINATED (NR 1 BLEED) · airframe 29,208 hrs · 12,671 cycles

BLEED AIR NR 1 FAULT WITH ANTI-ICE SELECTED AFTER SELECTING WITH ANTI ICE THEN BOTH PACKS WOULD FAULT AND NOT RESET COULD NOT MAINTAIN CABIN PRESSURE WITH APU BLEED NR 2 BLEED WAS DEFERRED NR 1 ENGINE BLEED WOULD NOT RESET. UNSCHEDULED LANDING T/S PER A310 TSM BITE NR 1 & 2 PSC PRIOR TO AND AFTER NR 1 ENG GROUND RUN, OPENED NR 1 ENG COWLING TO INSPECT BLEED AIR DUCTING FOR LEAK AND SECURITY NO DEFECT NOTED. GEAR PINS INSTALLED AND REMOVED AFTER ENGINE RUN. (OPEN)

Part: COMPUTER — MALFUNCTIONED (AUTOTHROTTLE SYS) · airframe 28,130 hrs · 12,219 cycles

USING TOGA FOR T/O ON A WET SLIPPERY RWY. THROTTLE 2 RACED TO TRP THRUST LIMIT BUT THROTTLE 1 REMAINED AT 40 PERCENT N1, DISCONTINUED T/O ATTEMPT. REMOVED AND REPLACED THRUST CONTROL COMPUTER AS PER AMM 22-36-34-4-02. PERFORMED AFS TEST/LAND TEST AS PER AMM ADJ/TEST REF.22-40-00-5. ALL TEST SATISFACTORY. DMI CLEARED. PLACARD REMOVED. PLS CHECKED CAT 3.

Part: SKIN — DELAMINATED (LT WING) · airframe 28,066 hrs · 12,189 cycles

LT WING OUTBOARD TE PANEL (BOTTOM SKIN - FOUND 6 LOCATIONS WITH DELAMINATION. AREAS OF DELAMINATION ARE AS FOLLOW (INBD TO OUBD): 1: 36.5 X 12, 2: 14 X 14, 3: 4 X 3, 4: 2.5 X 2.5, 5: 2 X 0.5, 6: 1.5 X 0.5 ......NOTED 2EA EXISTING REPAIRS ON UPPER SKIN, ADJA CENT TO ABOVE AREAS NR 1 AND 2.

Part: FMC — INOPERATIVE (INS/IRS NAV) · airframe 25,818 hrs · 11,148 cycles

AFTER ROTATION, GOT IRU AND GPS DO NOT AGREE ON ECAM POSITION UPDATE ACCOMPLISHED O/HEAD. ECAM WARNING STILL PRESENT AFTER UPDATE. ECAM WARNING CLEARED AND POSITIONS CAME INTO AGREEMENT O/HEAD SUBIC VOR DURING RETURN TO SFS. AFTER LANDING, IRU NR 1 DISPLAYED DRIFT 99.9, NR 2 DISPLAYED 99.9 DRIFTS AND NR 3 NO DISPLAY. REMOVED AND REPLACED FMC 1 AND 2 IAW MM 34-60-00 AND UPDATED WITH VERSION FX4-0303-001, OPS CHK SATIS. REMOVED AND REPLACED IRU NR 3 IAW MM 34-25-34 AND BAT NR 3 IAW MM 24-31-11, OPS CHK SATIS. REMOVED AND REPLACED FCC NR 1 DUE, FAULTED ON GROUND SCAN IAW MM 22-18-34, AFS/LAND TEST IAW MM 22-40-00.

Part: ELEVATOR — MALFUNCTIONED (EMPENNAGE) · airframe 25,580 hrs · 11,030 cycles

ELEVATOR PITCH FORCE VERY HIGH IN ALL FLIGHT PHASES, NO PITCH FEEL FAULT INDICATES. PERFORMED TSM 27-31-00 FIG 101 FROM STEPS 1 - 13, ALL NORMAL AND COMPARED TO AC 422 CONTROL COLUMN TENSION, THE SAME. CANNOT DUPLICATE ON GROUND. HOWEVER CANNOT PERFORM ADJ/TEST DUE TO NO EQPT/TESTER AVAIL SUBIC. A/C IN NORMAL CONFIG. SUSPECT NEED TO CHECK AGAIN THE E2LO & E2RO ELEV AFT CABLES FOR PROPER TENSION THAT WAS REPLACED ON DEC 11, THEN THE TROUBLE STARTED TO APPEAR. FOR CONTINUATION ** S/D ** COMING

Part: BLEED VALVE — MALFUNCTIONED (NR 2 ENGINE) · airframe 24,575 hrs · 10,549 cycles

CRUISE IN WX AT 350 MACH 80 A/I ON, EXPERIENCED ENGINE COMPRESSOR STALL ON NR 2 ENGINE. REMOVED EVBC.

Part: FRAME — CORRODED (FUSELAGE) · airframe 24,159 hrs · 10,254 cycles

CORROSION ON FRAME 80. *S/D* Removed and replaced FRAME STR 23 LT and 35 RT PER EA 6-5310-41803 & ABI 19R539-7059813 & 19R53970599.