N815FD

Part: CROSSBEAM — CORRODED (ZONE 100) · airframe 31,835 hrs · 10,221 cycles

FR63 AFT CARGO LBL 10 "T" EXTRUSION EXFOLIATED ON LOWER FWD SIDE INSTALLED SPLICE REPAIR "T EXTRUSION AND L EXTRUSION" AT FR63 AFT CARGO LBL 10 TO RBL 12 ON LOWER FWD SIDE IAW SRM 53-10-15, PAGE 259/260, FIGURE 209, SHEET 1.

Part: FITTING — CORRODED (NR 1 PYLON) · airframe 31,835 hrs · 10,221 cycles

NR1 ENG PYLON RIB 18 FWD SIDE CORRODED ABOVE THE BRG REMOVED NR1 PYLON AFT ATTACH FITTING AT RIB 18 IAW AMM 54-51-75-04. REMOVED CORROSION FROM RIB 18 LUG IAW SRM 51-74-10 , CHECKED FOR LIMITS FOUND OUT OF LIMITS IAW SRM 54-51-71, PAGE 110. INSTALLED NEW FITTING ON NR1 PYLON IAW AMM 54-51-75-04.

Part: PANEL — CRACKED (NR 2 PYLON) · airframe 31,835 hrs · 10,221 cycles

NR 2 PYLON OTBD SIDE AT RIB 8 FWD SCEW HOLE HAS A 0.250 CRACK GOING UPWARDS. TRIMMED OUT CRACK AND REPAIRED PYLON NR 2 SIDE PANEL IAW SRM 54-51-31 FO\IG 201 PAGE 203 TO 207. THIS REPAIR MUST BE INSPECTED AT DEFINED INTERVALS . THE INSP INSTRUCTION REF IS SRI54-51-31-2-001-00.

Part: SEAT TRACK — CORRODED (ZONE 400) · corrosion level 2 · airframe 31,835 hrs · 10,221 cycles

SEAT TRACK 2L IS CORRODED IN 2 EA LOCATIONS BETWEEN FR 19 AND FR14 REMOVED CORROSION AT SEAT TRACK 2L IAW SRM 53-10-16, PAGE 103, FIG 101. AREA FOUND OUT OF LIMIT. R & R SEAT TRACK IAW SRM 53-10-16 AND SRM 51-40-21.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 31,835 hrs · 10,221 cycles

SEAT TRACK 3R IS CORRODED BETWEEN FR 18 AND FR 17 APPROX 3 SQ. INCH REMOVED CORROSION WITH 58 PERCENT MATERIAL LOSS FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16, PAGE 108, FIG 101. R & R SEAT TRACK 3R BETWEEN FR 17 AND FR 18 IAW SRM 53-10-16, PAGE 108, FIG 101 AND SRM A310 51-40-21PG 9.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 31,835 hrs · 10,221 cycles

SEAT TRACK 2R IS CORRODED BETWEEN FR 16 AND FR 15 APPROX 12 INCH LONG REMOVED CORROSION WITH 65 PERCENT MATERIAL LOSS IAW SRM 53-10-16, PAGE 108, FIG 101 R & R SEAT TRACK NR 2R BETWEEN FR16 AND FR 15 IAW SRM 53-10-16, FIG 101 AND SRM 51-40-21.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 31,835 hrs · 10,221 cycles

MAIN CARGO DECK , FWD CABIN SEAT TRACK NR3 LT HAS CORROSION FR 15 TO FR16. REMOVED CORROSION WITH 55 PERCENT MATERIAL LOSS FOUND OUT OF LIMITS IAW SRM 53-10-16, PAGE 108, FIG 101 . R & R SEAT TRAC 3L BETWEEN FR15 AND FR16 IAW SRM 53-10-16 PAGE 108, FIG 101 AND SRM 51-40-21.

Part: SKIN — DENTED (ZONE 200) · airframe 31,835 hrs · 10,221 cycles

LT SIDE FUSELAGE SKIN BETWEEN FRAMES 73 TO 73A AND BETWEEN STRINGERS 29 TO 31 LT HAS A DENT AND CREASE MEASURING 9 IN X 305 IN AND .019 IN DEEP. ALSO THE DENT CROSSED OVER STRINGER 30 LT. EVALUATED DAMAGE AND FOUND DENT BETWEEN FR 73 AND 73A AND BETWEEN STRINGER 29 AND 30 LT TO BE WITHIN LIMITS AFTER DRESS OUT IAW SRM 53-10-12,PB 101, FIG 110, PAGES 133/134. PERFORMED CUT OUT OF DAMAGED SECTION OF SKIN BETWEEN FR 73 TO 73A AND BETWEEN STRINGERS 30 TO 31 LT AND INSTALLED EXTERNAL PERMANENT SKIN REPAIR IAW SRM 53-10-12, FIG 225, SHEET 3, PAGE 365/366. FOLLOW UP TRACKING REQUIREMENTS IAW SRI 53-10-12-2-005-00, PARA 3.E, TABLE 211 AND FIG 207. INITIAL AT 43,750 FLIGHT CYCLES, REPEAT EVERY 10,400 FC METHOD ULTRASONIC AND EDDY CURRENT.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 31,835 hrs · 10,221 cycles

SEAT TRACK 4L BETWEEN FRAME 62 AND FRAME 65 HAS 2 AREAS OF GOUGES AROUND SCALLOPS, APPROX .009" DEEP. REMOVED DAMAGED AREAS BY BLENDING OUT GOUGES ON SCALLOPS OF SEAT TRACK 4L BETWEEN FRAME 62 AND FRAME 65 IAW SRM 51-73-10, PGS 7 THRU 10. CHECKED LIMITS AND FOUND TRACK TO BE OUT OF LIMITS IAW SRM 53-10-16, PAGE 103 FIG 101. REMOVED DAMAGED SEAT TRACK AND REPAIRED IAW SRM 53-10-16, FIG 208, PG 249/250. ALODINED IAW SRM 51-21-10, PG 1-10, PRIMED AND TOPCOATED IAW SRM 51-75-10, PGS 201-206.

Part: SLAT SYSTEM — MALFUNCTIONED · airframe 31,752 hrs · 10,148 cycles

SLOWING THRU 200 KTS TRIED TO EXTEND SLATS. AS SOON AS HANDLE MOVED FROM DETENT, GOT LOUD GRINDING NOISE. ALSO GOT ECAM WARNING FOR SLAT 1 & SLAT 2 FAULT. RECYCLED HANDLE. WARNINGS CLEARED; SLOWED TO 180 KTS, EXTENDED SLATS NORMALLY WITH NO WARNINGS AND NO GRINDING NOISES. T/S AND REVEIWED HISTORY OF SLAT FAULTS, OPENED GEAR DOORS, REMOVED LT AND CTR AC BAY DOORS TO ACCESS SLAT COMPONENTS FWD OF SLAT PCU. FOUND RT SLAT TORQUE LIMITER IN OVERTORQUED CONDITION WITH RED INDICATOR POPPED OUT, LT TORQUE LIMITER FOUND NORMAL CONDITION. MANUALLY RESET RT TORQUE LIMITER. SUSPECT PROBLEM ORIGINATING FROM RT SIDE SLAT COMPONENTS DUE TO CURRENT FINDING AND NOTING OF BOTH TORQUE LIMITERS WERE RECENTLY RESET PRIOR TO FAULT REPEATING WITH ONLY THE RT SIDE INDICATING OVERTORQUE. PANELS REMOVED ARE IN AREA. FAULT BALL INDICATIONS OF NR 1 & NR 2 SFCC'S BOTH SHOWED JAM INDICATION, RESET FAULT BALL INDICATORS FOR FURTHER T/S. PERFORMED ADJ/TEST SLAT SYSTEM PER AMM 27-84-00-05 NO DEFECTS NOTED. BITE CHECK OF BOTH SFCC 1 AND 2 PERFORMED PER TSM 27-80-00 NO FAULTS FOUND.

Part: THRUST REVERSER — MALFUNCTIONED (NR 2) · airframe 31,432 hrs · 9,928 cycles

ON TAKEOFF AT 60 KIAS, THE NR 2 THRUST REVERSER UNLOCKED LIGHT WITH ACCOMPANIED ECAM WARNING ILLUMINATED. TAKEOFF REJECTED, ECAM AND QRH CHECKLISTS COMPLETE. MEL 16MAR10 RELEASED FOR SERVICE PER MEL: 78-30-01-C CATEGORY: C EXPIRATION: 26MAR10, "MEL 78-30-01-C: ENG 2THRUST REVERSER - INOP. THRUST REVERSER IS DEACTIVATED IN FWD THRUST POSITION. " ALSO PERFORMED REJECTED TAKEOFF INSP, NO DEFECTS NOTED IAW AMM 32-40-00-6. REPLACED LT AND RT RVDT MODULES IAW AMM 78-31-40-4 06, OPS CHECKS IS GOOD, INDICATION IN COCKPIT CKS GOOD. OK FOR SERVICE. PREMATURE REMOVAL/INSTALLATION.

Part: COALESCER BAG — DIRTY (COCKPIT AIR) · airframe 31,194 hrs · 9,767 cycles

OIL ODOR IN THE COCKPIT AFTER DEPARTURE THAT DID NOT SUBSIDE. RETURNED TO DEPARTURE. R & R NR 1 & 2 WATER SEPARATOR COALESCER BAGS AS PRECAUTION TO REMOVE ANY RESIDUE THAT MIGHT CAUSE ODOR IN COCKPIT IAW AMM 21-51-16-3. AFTER REPLACEMENT, PERFORMED AN AIR COOLING SYS SERVICING. CLEANED AIR CON DUCTS IAW AMM 21-51-00-3, PERFORMED BOTH APU & ENG BLEED AIR SYS CLEANING IAW AMM 21-51-00-3. RAN APU IAW JRH, & PERFORMED ENGINE RUN IAW JRH CH 6. ALL INDICATIONS NORMAL. ACFT OK FOR SERVICE. APU INLET & COMPT INSP, NO OIL FOUND.

Part: SWITCH — FAILED (NLG) · airframe 30,558 hrs · 9,301 cycles

ON APPROACH, BEFORE LANDING CHECK LIST COMPLETE, AT 200' ABOVE THE GROUND WE HAD A "TO LOW GEAR]" ALERT FWD PANEL SHOWED 3 GREEN, OVERHEAD INITIALLY SHOWED 3 GREEN BUT NOW SHOWED NO NOSE GEAR GREEN. WENT AROUND AND THE ACFT SHOWED 3 GREEN ON BOTH PANELS THROUGH LANDING. ENT BY: 715474 RPT BY: 078544 SHGN 17DEC08 16:30 YVR R IN WORK. REPLACED SWITCH 79GB ON NOSE GEAR TELESCOPIC DRAG STRUT IAW MM 32-00-00-4, OPS CHECKED IAW MM 32-61-00-5. CHECKED GOOD, 3 GREEN ARROWS ON FWD PANEL AND ON OVERHEAD PANEL ARE ON.

Part: SENSOR — FAILED (ZONE 300) · airframe 30,487 hrs · 9,255 cycles

DURING T/O ROLL RECEIVED ECAM WARNING OF PITCH TRIM NOT IN T/O RANGE, REJECTED T/O. AFTER CONFIRMING PITCH TRIM PROPERLY SET (VIA PERFORMING COMPUTER NUMBERS) TESTED T/O CONFIG TEST AND STILL RECEIVED SAME WARNING ON ECAM. PITCH TRIM SHOWS IN GREEN BAND ON TROM WHEEL BUT OUT OF GREEN RANGE ON ECAM FLT CONTROL PAGE. REMOVED AND REPLACED THS POSITION SENSOR 11CT IAW A310-300 MM 27-45-11-4 AND MM 27-45-00-5, OPS CKS NORMAL. PERFORMED THS TAKEOFF WARNING TEST IAW A310-300 MM 27-00-00, OPS CKS NORMAL. A/C OK FOR SERVICE. CREATED OIL TO RECHECK 11CT SENSOR AT NEXT 'A' CK. WITH TEST SET 31-590-100 (NOT AVAIL IND).

Part: SKIN — DELAMINATED (ZONE 400) · airframe 30,057 hrs · 9,003 cycles

LEFT WING INBD FLAP T/E AREA IS DENTED AND DELAMINATED APPROX 18 INCHES FROM THE OUTBD EDGE. REPAIRED THE LEFT INBD FLAP BY REMOVING THE DAMAGED AREA ; FABRICATING; AND BONDING A NEW CORE AND DOUBLERS IAW A310 SRM 57-52-12 AND FEDEX EA 6-5750-118501 TITLED "WING - LEFT WING FLAP T/E UPPER AND LOWER SKIN".

Part: SKIN — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 30,057 hrs · 9,003 cycles

FWD CARGO PIT DOOR LOWER INTERNAL SKIN PLATE IS CORRODED IN NUMEROUS PLACES. REMOVED AND REPLACED THE FWD CARGO DOOR INTERNAL SKIN PLATE IAW A310 SRM 51-40-21. MATERIAL ID IAW A310 SRM 52-31-00; PG 4; SHEET 2; ITEM 20, P/N A52372043200. THIS SDR WAS GENERATED TO CORRECT THE VERBIAGE IN THE DISCREPANCY AND IN THE CORRECTIVE ACTION OF SDR TRACKING NR 08-1805 AND NON-ROUTINE NR N00434. THE VERBIAGE "EXTERNAL SKIN PLATE" WAS CORRECTED TO READ "INTERNAL SKIN PLATE".

Part: SKIN — GOUGED (THRUST REVERSER) · airframe 30,057 hrs · 9,003 cycles

NR 2 ENG LT T/R AFT LATCH INNER CUTOUT CHAFED BY LATCH HANDLE. COMPLIED WITH EA 6-7830-118504 THRUST REVERSER, NR 2 ENGINE LT T/R LWR BIFURCATION DECK ASSY, OUTER SKIN GOUGE.

Part: SKIN — GOUGED (ZONE 100) · airframe 30,057 hrs · 9,003 cycles

FWD CARGO DOOR CUT OUT FUSELAGE SKIN EDGE IS GOUGED AT THE UPPER FWD CORNER. COMPLIED WITH EA 6-5310-118494 FUSELAGE SKIN AT FRAME 20 AND STRINGER 28 R REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 30,057 hrs · 9,003 cycles

THERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 67 TO FRAME 69, RBL 54 TO RBL 72. MATERIAL ID IS A402H35039-003, PO604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 67 TO FRAME 69 USING THE OLD FLOOR PANEL AS A TEMPLATE IAW FEDEX DWG SRZ 25-005, REV F. MARKED PANEL NR 251 BH IAE FEDEX DWG SRZ 25-005, REV F AND GMM 7-0-1000. PANEL PART ID IS FXR532B388400100.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 30,057 hrs · 9,003 cycles

THERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 66 TO 67; LBL 57 TO LBL 71. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CABIN FROM FRAME 66 TO FRAME 67 USING THE OLD PANEL AS A TEMPLATE IAW FEDEX DWG SRZ 25-005, REV F. MARKED PANEL NR 251 BH IAW FEDEX DWG SRZ 25-005, REV F AND FEDEX GMM 7-0-1000. PANEL PART ID IS FXR 532B88300200.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 30,057 hrs · 9,003 cycles

THERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK AT FRAME 65 TO FRAME 66, LBL-57 TO LBL-71. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 65 TO FRAME 66 USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ 25-005, REV F. MARKED PANEL NR 251 BH IAW FEDEX DWG NR SRZ 25-005, REV F AND GMM 7-0-1000. PANEL PART ID IS FXR532B38300200.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 30,057 hrs · 9,003 cycles

MAIN CABIN FLOOR PANEL AT FRAME 51, RBL 37 IS CRACKED. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED NEW FLOORBOARD PANEL FOR THE MAIN CABIN FROM FRAME 51 TO FRAME 54 USING THE OLD PANEL AS A TEMPLATE IAW FEDEX DWG SRZ 25-005, REV F. MARKED PANEL NR 252 EK IAW FEDEX DWG SRZ 25-005, REV F AND GMM 7-0-1000. PANEL PART ID IS FX R532B376600100.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 30,057 hrs · 9,003 cycles

THERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 66 TO FRAME 67, RBL 57 TO RBL 71. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 66TO 67 USING THE OLD FLOOR PANEL AS A TEMPLATE IAW FEDEX DWG SRZ 25-005, REV F. MARKED PANEL NR 252 BH IAW FEDEX DWG SRZ 25-005, REV F AND GMM 7-0-1000. PANEL PART ID IS FDX532B388300100.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 30,057 hrs · 9,003 cycles

THERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 54.2 TO FRAME 55/58, RBL-17 TO RBL-37. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 54.2 TO FRAME 55/58 USING THE OLD FLOOR PANEL AS A TEMPLATE IAW FEDEX DWG SRZ 25-005, REV F. MARKED PANEL NR 252 GF IAW FEDEX DWG SRZ 25-005, REV F AND GMM 7-0-1000. PANEL PART ID IS FXR532B385600500.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 30,057 hrs · 9,003 cycles

THERE IS A BROKEN FLOOR FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 62 TO FRAME 65, RBL 57 TO RBL 74. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 62 TO FRAME 65 USING THE OLD PANEL AS A TEMPLATE IAW FEDEX DWG SRZ 25-005, REV F. MARKED PANEL NR 252 YG IAW FEDEX DWG SRZ 25-005, REV F AND GMM 7-0-1000. PANEL PART ID IS FXR532B382900200.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 30,057 hrs · 9,003 cycles

MAIN WHEEL WELL CATWALK PANEL NR 148 BF IS DELAMINATED. MATERIAL ID IS A402H35039-003 PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL AT THE MAIN WHEEL WELL CATWALK PANEL NR 148 BF USING THE OLD PANEL AS A TEMPLATE IAW FEDEX DWG SRZ 25-005, REV F. MARKED PANEL NR 148 BF IAW FEDEX DWG SRZ 25-005, REV F AND GMM 7-0-1000. PANEL PART ID IS FXA2901115300100.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 30,057 hrs · 9,003 cycles

THERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 77 TO FRAME 80/82, LBL 45 TO LBL 63. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 77 TO FRAME 80/82 USING THE OLD FLOOR PANEL AS A TEMPLATE IAW FEDEX DWG SRZ 25-005, REV F. MARKED PANEL NR 251 ZF IAW FEDEX DWG SRZ 25-005, REV F AND GMM 7-0-1000. PANEL PART ID IS FDX532B384800400.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 30,057 hrs · 9,003 cycles

THERE IS A BROKEN FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 62 TO FRAME 65, LBL-57 TO LBL-72. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED A NEW FLOOR PANEL FOR THE MAIN CARGO DECK FROM FRAME 62 TO FRAME 65 USING THE OLD PANEL AS A TEMPLATE IAW FEDEX DWG SRZ 25-005, REV F. MARKED PANEL NR 251YG IAW FEDEX DWG SRZ 25-005, REV F AND GMM 7-0-1000. PANEL PART 9ID IS FXR532B382400200.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 30,057 hrs · 9,003 cycles

MAIN CABIN FLOOR PANEL AT FRAME 48 IS CRACKED AT RBL 57. MATERIAL ID IS A402H35039-003, PO 604814.1 IAW FEDEX DWG SRZ 25-005, REV F. FABRICATED NEW FLOORBOARD PANEL FOR THE MAIN CABIN AT FRAME 48 USING THE OLS PANEL AS A TEMPLATE IAW FEDEX DWG SRZ 25-005, REV F MARK PANEL NR 242AJ IAW FEDEX DWG SRZ 25-005, REV F AND GMM 7-0-1000. PANEL PART ID IS FX A532B375200100.

Part: RIB — CRACKED (ZONE 500) · airframe 30,057 hrs · 9,003 cycles

LEFT WING TIP RIB WY 495 IS CRACKED. REPLACED LEFT WING TIP RIB WY 495 IAW WORK INSTRUCTIONS FOUND IN EO 6-5710-7-5012 E OCN 01 PI.

Part: PANEL — CORRODED (RT WING) · airframe 30,057 hrs · 9,003 cycles

RIGHT WING FUEL PANEL ASSY NR 650 CB CLAMP RING HAS AREAS OF FRETTING. BLENDED AREA SMOOTH IAW SRM 51-73-10. FOUND TO BE OUT OF LIMITS IAW SRM 57-20-16. REMOVED AND REPLACED THE CLAMP RING.

Part: INTERCOSTAL — BENT (ZONE 100) · airframe 30,057 hrs · 9,003 cycles

EMPENAGE THRU DOOR 312 AR, RIGHT INTERCOSTAL BETWEEN FRAME 85 AND 86 IS BENT. REMOVED OLD INTERCOSTAL IAW A310 SRM 51-40-21. INSTALLED NEW INTERCOSTAL IAW A310 SRM 51-40-21.

Part: PANEL — CORRODED (RT WING) · airframe 30,057 hrs · 9,003 cycles

RIGHT WING FUEL PANEL ASSY NR 650 FB CLAMP RING HAS AREAS OF FRETTING. BLENDED AREA SMOOTH IAW 57-73-10. FOUND TO BE OUT OF LIMITS IAW SRM 57-20-16. REMOVED OLE CLAMP RING AND REPLACED WITH A NEW RING.

Part: PANEL — CHAFED (ZONE 500) · airframe 30,057 hrs · 9,003 cycles

LT WING FUEL PANEL ASSY 550 AT CLAMP RING HAS AREAS OF FRETTING. REMOVED & REPLACED THE CLAMP RING IAW SRM 57-20-16.

Part: RIB — CRACKED (NR 2 PYLON) · airframe 30,057 hrs · 9,003 cycles

NR 2 PYLON AFT LOWER FAIRING PANEL NR 485 AL, RIB IS CRACKED AT THE LOWER ATTACH ANGLE. REMOVED CRACKED ANGLE AND REPLACED WITH A NEW ANGLE PER SRM 51-40-21 PARA 6 & 7. LOCATED & DRILLED HOLES PER SRM 51-40-44. APPLIED PRIMER PER AMM 51-23-10-0.

Part: PANEL — CHAFED (ZONE 400) · airframe 30,057 hrs · 9,003 cycles

NR 2 PYLON AFT LOWER FAIRING PANEL 485 AL; FWD UPPER RT ATTACH PLATE IS CHAFED ON THE INNER SURFACE. REMOVED ATTACH PLATE & INSTALLED A NEW ATTACH PLATE PER SRM 51-40-21 PARA 6. LOCATED & DRILLED HOLES PER SRM 51-40-21 PARA 6. ALODINED PER SRM 51-21-10. PRIMED PER SRM 54-23-10. APPLIED PAINT PER AMM 51-33-10-0.

Part: ATTACH ANGLE — CHAFED (NR 2 PYLON) · airframe 30,057 hrs · 9,003 cycles

NR 2 PYLON AFT LOWER FAIRING PANEL NR 485 AL, LT UPPER ATTACH ANGLE IS CHAFED IN SEVERAL PLACES. REMOVED DAMAGED LONGERON & INSTALLED NEW LONGERON PER SRM 51-40-21 PARA 6 - 7. LOCATED DRILLED HOLES PER SRM 51-40-44. ALODINED & PRIMED PER AMM 51-23-00.

Part: ATTACH FITTING — CHAFED (NR 2 PYLON) · airframe 30,057 hrs · 9,003 cycles

NR 2 PYLON AFT LOWER FAIRING PANEL NR 485 AL, FWD UPPER LT ATTACH PLATE IS CHAFED ON THE INNER SURFACE. REMOVED CHAFED ATTACH PLATE & INSTALLED A NEW ATTACH PLATE PER SRM 51-40-21 PARA 6. LOCATED & DRILLED PER SRM 51-40-44. ALODINED PER AMM 51-23-10-0.

Part: SKIN — DELAMINATED (ZONE 100) · airframe 30,057 hrs · 9,003 cycles

FOUND EVIDENCE OF A CRACK STARTING AT A FASTENER HOLE ON THE RIGHT EXTERNAL SIDE OF THE FUSELAGE SKIN BETWEEN STRINGER 21R & STRINGER 22R & FRAMES 40 TO 41. BLENDED AREA IN REF TO SRM 51-74-10. ORIGINAL MATERIAL THICKNESS 0.061 IAW SRM 53-14-12. MATERIAL REMOVED WAS 0.002. MATERIAL REMAINING IS 0.059. FOUND TO BE WITHIN LIMITS IAW SRM 53-10-12; DIA 0.112. ACCOMPLISHED HFEC INSPECTION PER NTM PART 6; 51-10-8; NO CRACK NOTED. ALODINED IAW SRM 51-21-10. PRIMED & TOP COATED IN REF TO AMM 51-23-10-0.

Part: ATTACH ANGLE — CHAFED (NR 2 PYLON) · airframe 30,057 hrs · 9,003 cycles

NR 2 PYLON LOWER FAIRING PANEL NR 485 AL, RT UPPER ATTACH ANGLE IS CHAFED IN SEVERAL PLACES. REMOVED THE NR 2 PYLON LOWER FAIRING UPPER ATTACH ANGLE PER FEDEX SRM 51-40-21. LOCATED & DRILLED NEW UPPER ATTACH ANGLE IAW SRM 51-40-44. ALODINED & PRIMED NEW ATTACH ANGLE IAW AMM 51-23-10-0. RECEIVED CLIP. LOCATED & DRILLED CLIP IAW SRM 51-40-40. INSTALLED CLIP & UPPER ATTACH ANGLE IAW SRM 51-40-21.

Part: PANEL — CHAFED (NR 1 PYLON) · airframe 30,057 hrs · 9,003 cycles

NR 1 PYLON PANEL NR 414 ER HAS CHAFING ON THE MATING SURFACE. REPAIRED THE IAW SRM 54-52-51, FIG 203.

Part: SUPPORT BRACKET — WORN (FUSELAGE) · airframe 30,057 hrs · 9,003 cycles

RIGHT AIR CONDITIONING FAIRING SUPPORT BRACKET IS WORN, 9 INCH AFT OF FRAME 43. REMOVED DAMAGED BRACKET REF A310 SRM 51-40-21. FORMED AND LOCATED FASTENER HOLES IAW AIRBUS DWG 53410426. ALODINED AND PRIMED NEW BRACKETS REF A310 SRM 51-21-10. PAINTED NEW BRACKET REF A310 SRM 51-23-10. INSTALLED NEW BRACKET REF A310 SRM 51-40-21.

Part: LONGERON — CHAFED (ZONE 400) · airframe 30,057 hrs · 9,003 cycles

NR 1 PYLON AFT LOWER FAIRING PANEL 475 AL; UPPER LT ATTACH ANGLE IS CHAFED ON THE INNER SURFACE. BLENDED CHAFED AREA PER SRM 51-77-10. FOUND TO BE OUT OF LIMITS PER SRM 54-55-51 TABLE 101 SHEET 1. ORIGINAL MATERIAL 0.071. MATERIAL REMAINING 0.047. MATERIAL REMOVED 0.024. REMOVED DAMAGED LONGERON AND REPLACED WITH A NEW LONGERON PER SRM 51-40-21; PARA 6. ALODINED; PRIMED PER AMM 51-10-0. LOCATED & DRILLED PER SRM 51-40-44.

Part: SKIN — CORRODED (CARGO DOOR) · airframe 30,057 hrs · 9,003 cycles

FWD CARGO PIT DOOR LOWER EXTERNAL SKIN PLATE IS CORRODED IN NUMEROUS PLACES. REMOVED AND REPLACED THE FWD CARGO DOOR LOWER EXTERNAL SKIN PLATE IAW SRM 51-40-21.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 30,057 hrs · 9,003 cycles

RADAR MOUNT ATTACH FITTING ON THE FWD FACE OF THE FRONT PRESSURE BULKHEAD STRUCTURE IS CORRODED. REMOVED THE ANGLE IN REF TO SRM 51-40-21; PARA 7. FABBED A NEW ANGLE IN REF TO DWG 11A92420400 & INSTALLED NEW ANGLE IN REF TO SRM 51-40-21 PARA 7.

Part: RIB — CRACKED (LT WINGLET) · airframe 29,880 hrs · 8,905 cycles

LT WINGLET RIB CRACKED REPLACE, REPAIR RIB.

Part: COMPUTER — MALFUNCTIONED (NR 1) · airframe 29,870 hrs · 8,900 cycles

UPON FLAP RETRACTION GOT SLAT SYS 1 AND SLAT SYS 2 FAULTS ALONG WITH FLAP SYS 1 FAULT. AT SAME TIME LOST ALL SPD LIMIT INDICATORS ON PFDS. ALL FAULTS RESET UPON LOWERING GEAR FOR PRECAUTIONARY LANDING. A/C IN WORK, IND MX. COULD NOT DUPLICATE FAULTS - JACKED A/C AND CHECKED AOA SENSORS, PITOT SYSTEM , R&R FAC NR 1, 5 GOOD LEGS.

Part: OUTFLOW VALVE — FAILED (CABIN PRESSURE) · airframe 29,717 hrs · 8,811 cycles

AFTER T/O, OVERBOARD VALVE FAULTED. REMOVED AND REPLACED OVERBOARD EXTRACT VALVE (75HR) IAW MM 21-23-13-4. OPS CHK NORMAL.

Part: STRUCTURE — CONTAMINATED · airframe 29,486 hrs · 8,681 cycles

CTR TANK FUEL QUANTITY FLUCTUATES IN FLIGHT FROM 60 LBS TO 1080 LBS. SHOWED 1.0 IN CTR FOR TAKEOFF. STAB TRIM WAS ADJUSTED ACCORDINGLY. NOSE WAS VERY LIGHT ON TAKEOFF ROLL AND TOOK EXCESSIVE NOSE DOWN TRIMMING TO GET AIRCRAFT IN TRIM. ONCE IN FLIGHT RECHECKED T/O SETTING AND THEY ARE CORRECT. VERIFIED FUEL QTY IN CENTER TANK. NO FLUCTUATION AND FUEL QUANTITY READS NORMAL. FOUND WATER TRAPPED IN THS COMPARTMENT MEASURED 14 INCHES DEEP, AFT PRESSURE BULKHEAD. APPROX 60 GALLONS. BLEW OPEN DRAIN AT MAST AND DRAINED ALL WATER FROM COMPARTMENT. ENSURED DRAIN IS OPEN AND COMPARTMENT IS EMPTY OF WATER AMM 51-80-41-6.

Part: RIB — MISALIGNED (ZONE 300) · airframe 29,282 hrs · 8,575 cycles

THS TIPS ON LT AND RT SIDE WERE DAMAGED AND SENT TO AN OUTSIDE VENDOR FOR REPAIR, SO TIPS FROM N812FD WERE CANNIBALIZED FOR USE ON N815FD, BUT THE THS RIB FASTENER HOLES MISMATCH TO TIP HOLES. REPAIR PERFORMED BY REPLACEMENT OF RIB ON LT AND RT THS IAW EA 6-5514-92191A AND RAS/CASA/4427/2005 ISSUE A.

Part: ANGLE — CORRODED (ZONE 200) · corrosion level 2 · airframe 29,282 hrs · 8,575 cycles

FOUND CORRODED ANGLE AT FRAME 101 REAR SIDE OF FIREWALL, STRG 5 RT. REPLACEMENT OF ANGLE IAW SRM 51-72-10.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 29,282 hrs · 8,575 cycles

HEAVY CORROSION ON CORNER FITTING FRAME 54.2 BETWEEN P41-45 LT. REPLACEMENT OF FITTING IAW SRM 51-72-10.

Part: ANGLE — MISMANUFACTURED (ZONE 200) · airframe 29,282 hrs · 8,575 cycles

LESS EDGE MARGIN (5-6 MM) AT ANGLE, STR 26 RT BETWEEN FRAME 65-66 AND FRAME 67-68 AND ON LT BETWEEN FRAME 70-71, STRG 26. IT'S IMPOSSIBLE TO INSTALL DAN5-6X FASTENERS DURING PTOF. REPAIR PERFORMED BY INSTALLING REPAIR ANGLE FABRICATED IN EFW-DRS (RE0074-201 AND RE0074-200) IAW SRM 51-72-10.

Part: PLATE — DAMAGED (ZONE 200) · airframe 29,282 hrs · 8,575 cycles

DAMAGED SHEARPLATE (DENTED AND CRACKED) BETWEEN FRAME 38.1-38.2. REPLACEMENT OF SHEAR PLATE IAW SRM 51-72-10.

Part: FRAME — DAMAGED (ZONE 200) · airframe 29,282 hrs · 8,575 cycles

NICK ON FRAME 61, STRG 15 LT AND THREE OPEN FASTENER HOLES. REPAIR PERFORMED BY BLEND OUT NICK AND CLOSING BLIND OPEN FASTENER HOLES IAW EA 6-5317-92170 AND RAS/DATLS/0002688/2005 ISSUE A.

Part: PLATE — CRACKED (ZONE 100) · airframe 29,282 hrs · 8,575 cycles

CRACKED SHEAR PLATE BETWEEN FRAME 32-33, STRG 44 RT. REPLACEMENT OF SHEARPLATE IAW SRM 51-72-10.

Part: STRAP — DAMAGED (ZONE 100) · airframe 29,282 hrs · 8,575 cycles

DAMAGED SEALING STRAP AT FWD CARGO DOOR CUT OUT, FRAME 25A RT, OUT OF LIMIT IAW SRM 51-10-10. REPLACEMENT OF STRAP IAW SRM 51-72-10.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 29,282 hrs · 8,575 cycles

HEAVY CORROSION ON CROSSBEAM FRAME 61 AFT CARGO COMP FLOOR STRUCTURE, RT. REPLACEMENT OF CROSSBEAM IAW SRM 51-72-10.

Part: FITTING — GOUGED (ZONE 400) · airframe 29,282 hrs · 8,575 cycles

GOUGE AT AFT PYLON TO ENGINE FITTING, RT PYLON. REPAIR PERFORMED BY SMOOTH BLEND OUT TO ELIMINATE SHARP EDGES AND REPROTECTION AS PER SRM WITH CADMIUM PLATING AND HIGH TEMPERATURE PAINT IAW EA 6-5451-92173 AND RAS 039403/010/2005.

Part: FITTING — CORRODED (ZONE 400) · corrosion level 2 · airframe 29,282 hrs · 8,575 cycles

CORROSION ON THE WHOLE LOWER SURFACE OF THE LT PYLON PYRAMID, FWD PYLON TO ENGINE ATTACH FITTING. REPAIR PERFORMED AS PER SRM 54-51-81 BY BLENDING OUT CORROSION, REPROTECTION BY CADMIUM PLATING AND HIGH TEMPERATURE PAINT IAW EA 6-5451-92174 AND RAS 039464/014/2005 ISSUE A.

Part: SKIN — CHAFED (ZONE 600) · airframe 29,282 hrs · 8,575 cycles

CHAFING DAMAGE AT ONE POSITION AND CRACK WITH DEFORMATION AT ANOTHER LOCATION ON FIXED LEADING EDGE D-NOSE SKIN RT, BETWEEN TRACK 3 AND TRACK 4. REPAIR PERFORMED BY BLENDING OUT DAMAGES AT BOTH POSITIONS, REMOVING FASTENER OF HOLE IN AREA OF CRACK WITH ROTOTEST TO INSURE THE CRACK DOES NOT PROPAGATE FROM THE OTHER SIDE AWAY FROM THE SKIN EDGE, AREAS NDT INSPECTED, ALL IAW EA 6- 5740-92207 AND RAS/BAE/1001695/2005 ISSUE B.

Part: PLATE — CORRODED (ZONE 200) · corrosion level 2 · airframe 29,282 hrs · 8,575 cycles

HEAVY CORRODED AND CRACKED SHEAR PLATES BETWEEN FRAME 79-80, STRG 26 LT AND RT. REPLACEMENT OF SHEAR PLATES LT AND RT IAW SRM 51-72-10.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 29,282 hrs · 8,575 cycles

HEAVY CORROSION ON CROSSBEAM FRAME 63 LT, Y1110 AND Y1160 IN AFT CARGO COMPARTMENT FLOOR STRUCTURE. CROSSBEAM SPLICE REPAIR PERFORMED IAW SRM 53-10-15/FIG 207.

Part: BEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 29,282 hrs · 8,575 cycles

FOUND CORROSION ON AFT CARGO DOOR SILL BEAM BETWEEN FRAME 59-59A. SILL BEAM REPAIR PERFORMED BY CUT OUT AND INSTALLING A FILLER IAW SRM 53-17-18/FIG 202, APPROVED BY EA 6-5317-92153 AND RAS/DATLS/0002685/2005 ISSUE A.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 29,282 hrs · 8,575 cycles

FOUND CORROSION ON LONGITUDINAL PROFILE BETWEEN FRAME 63-64, Y-805 RT, AFT CARGO COMPARTMENT FLOOR STRUCTURE. REPLACEMENT OF LONGITUDINAL PROFILE IAW SRM 51-72-10.

Part: SKIN — DELAMINATED (ZONE 600) · airframe 29,282 hrs · 8,575 cycles

FOUND DELAMINATION ON CORE FILLER AT TRAILING EDGE SKIN OF INBOARD FLAP RT. DELAMINATED CORE FILLER REPAIRED IAW SRM 57-53-12/FIG 209/SH 2/VERSION 3.

Part: PANEL — CORRODED (ZONE 200) · corrosion level 2 · airframe 29,282 hrs · 8,575 cycles

FOUND EXFOLIATION CORROSION ON FAIL/SAFE RING AT LOWER AFT CORNER OF FWD PAX DOOR RT, FRAME 15-16A. REPAIR PERFORMED BY REWORK, NDT INSPECTION AND FILLING THE REWORKED AREA WITH SEALANT IAW EA 6-5312-92165 AND RAS/AS/0181/2005 ISSUE A.

Part: CROSSBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 29,280 hrs · 8,574 cycles

CORRODED AND OLD REPAIRED CROSSBEAM AT FRAME 58 IN BULK CARGO COMPARTMENT. REPLACEMENT OF CROSSBEAM IAW SRM 51-72-10.

Part: LONGERON — CORRODED (ZONE 200) · corrosion level 2 · airframe 29,280 hrs · 8,574 cycles

HEAVY CORROSION ON LONGERON Y730, BETWEEN FRAME 11-14, OUT OF LIMIT IAW SRM 53-10-00/TB 102. REPLACEMENT OF LONGERON (SUPPORT) IAW SRM 51-72-10.

Part: SKIN — CORRODED (ZONE 300) · corrosion level 2 · airframe 29,280 hrs · 8,574 cycles

CORROSION PITS ON TOP REAR SKIN OF THS LT. REMAINING THICKNESS IS WITHIN LIMITS GIVEN IN SRM BUT MAXIMUM AFFECTED SURFACE AREAS ARE >400 MMXMM AND THEREFORE ARE OUT OF LIMIT AS PER SRM 55-10-00/CONFIG 2/TB 101, PIT AREAS BETWEEN 200 AND 1500 MMXMM) REWORK AREAS DOCUMENTED AND APPROVED PER EA 6-5510-92156 AND RAS/CASA/4264/2005 ISSUE A.

Part: HINGE FITTING — CORRODED (ZONE 300) · airframe 29,280 hrs · 8,574 cycles

CORROSION ON AFT LUG OF HINGE FITTING NR 5 AND CHAFING MARKS INSIDE ATTACH, OUT OF LIMIT. REPAIR PERFORMED BY REPLACEMENT OF HINGE FITTING NR 5 IAW AMM 55-36-46 AND BLEND OUT SCRATCHES WITH FLAP PEENING INSIDE HINGE FITTING ATTACH IAW SRM 51-29-00.

Part: LONGERON — CORRODED (ZONE 200) · corrosion level 2 · airframe 29,280 hrs · 8,574 cycles

HEAVY CORROSION ON LONGERON Y1959 LT, BETWEEN FRAME 12A-19, OUT OF LIMIT IAW SRM 53-10-00/TB 102. REPLACEMENT OF LONGERON (SUPPORT) IAW SRM 51-72-10.

Part: LONGERON — CORRODED (ZONE 200) · corrosion level 2 · airframe 29,280 hrs · 8,574 cycles

HEAVY CORROSION ON LONGERON Y-1959 RT, BETWEEN FRAME 12A -19, OUT OF LIMIT IAW SRM 53-10-00/TB 102. REPLACEMENT OF LONGERON IAW SRM 51-72-10.

Part: SKIN PANEL — MISREPAIRED (ZONE 100) · airframe 29,280 hrs · 8,574 cycles

FOUND OLD EXTERNAL DOUBLER REPAIR ON FUSELAGE SKIN BETWEEN FRAME 34-35, STRG 42-44 RT, NOT CONFORM TO REPAIR DRW R537-06202 ISSUE B AND RAS/DABRE/1540.1/96 ISSUE A. REPAIR REMOVED, SKIN CUT AND NEW DOUBLER INSTALLED IAW EA 6-5314-92180A AND RAS/DABRE/7005554/2005 ISSUE B.

Part: SKIN PANEL — CORRODED (ZONE 200) · corrosion level 2 · airframe 29,280 hrs · 8,574 cycles

CORROSION PITS ON TOP SKIN PANEL BETWEEN FRAME 80-95, STRG 6 RT TO 6 LT. REPAIR PERFORMED BY REWORK AND FLAP PEENING IAW EA 6-5319-92157 AND RAS/DAHAM/4019752/2005 ISSUE A.

Part: WEB — DAMAGED (ZONE 100) · airframe 29,280 hrs · 8,574 cycles

BOTH CROSS SHEETS AT FRAME 69 IN BULK CARGO COMPARTMENT DENTED AND CRACKED. REPLACEMENT OF BOTH CROSS SHEETS LT AND RT IAW SRM 51-72-10.

Part: SKIN — CORRODED (ZONE 300) · corrosion level 2 · airframe 29,280 hrs · 8,574 cycles

CORROSION PITS ON TOP FWD SKIN OF THS LT REMAINING THICKNESS IS WITHIN LIMITS GIVEN IN SRM BUT MAXIMUM AFFECTED SURFACE AREAS ARE >400 MMXMM AND THEREFORE ARE OUT OF LIMIT AS PER SRM 55-10-00/CONFIG 2/TB 101(PIT AREAS BETWEEN 200 AND 1500 MMXMM) REWORK AREAS DOCUMENTED AND APPROVED PER EA 6-5510-92156 AND RAS/CASA/4264/2005 ISSUE A.

Part: PROFILE — CHAFED (ZONE 200) · airframe 29,280 hrs · 8,574 cycles

FOUND AN OLD REPAIR (CUT OUT) FLANGE WITH CHAFING MARKS AT FRAME 16 LT, OUT OF LIMIT. REPLACEMENT OF FLANGE IAW SRM 51-72-10.

Part: FITTING — CRACKED (ZONE 100) · airframe 29,280 hrs · 8,574 cycles

CRACKED CORNER FITTING AT AFT CARGO DOOR CUT OUT (SILLBEAM) BETWEEN FRAME 63-63A. REPLACEMENT OF CORNER FITTING IAW SRM 51-72-10.

Part: LONGERON — CORRODED (ZONE 200) · corrosion level 2 · airframe 29,280 hrs · 8,574 cycles

HEAVY CORROSION ON EXTRUSION (LONGERON) Y-953 RT, BETWEEN FRAME 12A-14, OUT OF LIMIT IAW SRM 53-10-00/TB 102. EXTRUSION REPAIR PERFORMED BY INSTALLING REINFORCING PROFILES IAW SRM 53-12-15/FIG 207.

Part: SKIN PANEL — CHAFED (ZONE 600) · airframe 29,280 hrs · 8,574 cycles

CHAFING MARKS ON RT WING LEADING EDGE D-NOSE SKIN BETWEEN TRACK 5 AND 6 AND AREA AROUND JACK 3, OUT OF SRM LIMITS. PARTIAL SKIN REPLACMENT BETWEEN TRACK 5 AND 6 AND AROUND JACK 3 IAW SRM 57-41-12/FIG 203, 204 SRM REQUIRES MATERIAL DTD5070 TO ACCOMPLISH REPAIR, EA 6-57-41-92182 AND RAS/BAE/1001398/2005 ISSUE A AUTHORIZES ALTERNATE MATERIAL AL-P2014A.

Part: TRU — SMOKE (NR 2) · airframe 28,930 hrs · 8,364 cycles

WHEN POWERING UP NOTICED SMOKE WAS COMING FROM THE AVIONICS DEPT, SHUT DOWN A/C. CHECKED OUT THE AREA, THE SMOKE WAS GONE. POWERED UP THE A/C AGAIN ECAM SHOWED T/R UNIT 2 INOP. INSPECTED THE AREA AGAIN, FOUND NO EVIDENCE OF SMOKE OR DAMAGE WIRING. REMOVED AND REPLACED NR 1, NR 2 T/R AND ESS TRU PER M/M 24-32-11-4 OPS CK GOOD. OFF MFG F11QY3714 POS TR2, SRL 1863R, TAG 2B2564, ON MFG F11QY3714, SRL 2.299R, TAG 53A793 R/I OFF MFG F11QY3714 POS TR1, SRL 8062-091, TAG 03A666, ON MFG F11QY3714 SRL 1074, TAG 148A13R/I 29MAY07 15:32. R/I OFF MFG F11QY3714, POS ETR SRL 8004-160, TAG 47887A, ON MFG F11QY3714 SRL 1.970R, TAG B86825.

Part: INDICATOR — PILOT ERROR (AIRSPEED) · airframe 27,724 hrs · 7,675 cycles

AT APPROXIMATELY 95 KIAS, REJECTED T/O FOR NO AIRSPEED INDICATIONS ON F/O'S PFD. GR WT 250.8 27, DEGREES C. WINDS 180/5. DRY RUNWAY. FOUND PITOT COVER ON F/O'S SIDE. REMOVED PER A310 SMP.

Part: CONTROL UNIT — MALFUNCTIONED (FLT CONTROLS) · airframe 27,532 hrs · 7,562 cycles

ON T/O ROLL AT 80KT'S, SPOILER FAULT 2, 3, 7, BOTH SIDES. LIGHT WENT OUT AS SOON AS THROTTLES WERE BROUGHT BACK TO IDLE. FOUND CODES ON EFCU 1/2 :M1 3/7 M2 3/7. PERFORMED TEST T/O CONFIG WARNING MM 27-00-00-5 AND W/C SPOILERS AND SPEED BRAKES OP'S 42X0305 BOTH TEST PASSED. REMOVED AND REPLACED 1CP AND 2CP FOR PRECAUTIONARY PER A310-300-AMM-27-61-34-4. OPS CHECK NORMAL PER A310-300-AMM-27-61-00-5. HANGAR WILL REPLACE 24GG, 23GG, 27GG AND 28GG. REMOVED AND REPLACED 23GG, 24GG, 27GG AND 28GG NR 5, NR 6, NR 7, NR 8 MAIN GEAR TACHOMETERS REF A310-300 MM 32-42-5 7-4 AND PERFORMED OPERATIONAL TEST OF ANTI-SKID SYSTEM REF A310-300 MM 32-42-00-5, OPS CHECKS GOOD.

Part: WARNING MESSAGE — FALSE ACTIVATION (SPOILERS) · airframe 27,532 hrs · 7,562 cycles

ON T/O ROLL AT 20KTS, SPOILER FAULTS ON 3, 2, 7 BOTH SIDES. RERACKED BOTH EFCUS AND SFCC COMPUTERS PER SMP, EFCU COMPUTERS WERE LOOSE IN RACK MOUNTS.

Part: COMPUTER — MALFUNCTIONED (SPOILERS) · airframe 27,532 hrs · 7,562 cycles

ON T/O ROLL AT 20KTS, SPOILER FAULTS ON 3,2,7 BOTH SIDES. RERACKED BOTH EFCUS AND SFCC COMPUTERS PER SMP, EFCU COMPUTERS WERE LOOSE IN RACK MOUNTS.

Part: PUMP — FAILED (FUEL BOOST) · airframe 27,390 hrs · 7,480 cycles

1.5 HR INTO FLT, FL320 RT CTR PUMP FAULT, QRH'D 1/2 HR LATER CTR TK QTY FAILED (2300LBS SHOWING) AND SOME FEEDING FROM OUTERS. REMOVED AND REPLACED CENTER TANK RT BOOST PUMP IAW A310-300 MM 28-21-36. OPS CHECK GOOD PER ABOVE MM REF. REMOVED AND EPLACED FQI COMPUTER IAW A310 MM 28-42-38 AS A PRECAUTIONARY. RELEASED FOR SERVICE PER MEL/CDL: 28-28-26-01-B CATEGORY: C EXPIRATION: 26MAR06 "MEL 28-28-26-01-B: CGCC - INOP." REMOVED AND REPLACED FUEL QUANTITY ATTITUDE SENSOR PER MM 28-42-43-4. PERFORMED DIAGNOSTIC TEST PER MM 28-42-00-5. OP CKS NORMAL.

Part: COMPUTER — MALFUNCTIONED (FUEL SYSTEM) · airframe 27,390 hrs · 7,480 cycles

1.5 HR INTO FLT, FL320 RT CTR PUMP FAULT, QRH 0.5 HR LATER CTR TK QTY FAILED AT 2.3 W/SOME FEEDING FROM OUTERS. RT CENTER BOOST PUMP IN W/W GOOD POWER AT PUMP. NEED BOOST PUMP. REMOVED AND REPLACED CTR2 BOOST PUMP MFG 2052C23 S/N 6715. SUSPECT CTR TANK LOW LEVEL SENSOR 35/36 QJ BAD. REMOVED AND REPLACED FQIC PRECAUTIONARY MFG SIC5083-2, S/N122 -ACN RELEASED PER MEL 28-28-26-01-B CAT: C EXP: 26MAR06 "MEL 28-28-26-01-B: CGCC - INOP."

Part: THRUST REVERSER — INOPERATIVE (NR 2) · airframe 27,211 hrs · 7,355 cycles

DURING ENGINE RUNUP FOR T/O AT APPROX 40 PERCENT N1 REV NR 2 UNLOCK LT CAME ON. TRIED AGAIN WITH SAME RESULT MEL. ACN RELEASED FOR SERVICE PER MEL/CDL: 78-30-01-C CATEGORY: C EXPIRATION: 19DEC05 "MEL 78-30-01-C: ENGINE (IDENTIFY 1 OR 2) 2 THRUST REVERSER - INOP. THRUST REVERSER IS DEACTIVATED IN FORWARD THRUST POSITION."