N404FE

Part: CONTROLLER — FAILED (CABIN PRESSURE) · airframe 35,480 hrs · 29,761 cycles

CLIMBING THROUGH 10,500 FT THE EXCESS CAB ALT WARNING OCCURED. LEVELED OFF AT 11,000 FT. EXECUTED THE QRH EXCESS CAB ALT WARNING CHECKLIST, CAB PRESS MANUEL CONTROL CHECKLIST. COULD NOT CONTROL THE CABIN PRESSURE RETURNED TO DEPARTURE AIRPORT. TRIED SYS 2 CONTROL WITH NO SUCCESS IN CONTROLLING CABIN. ECAM DISPLAY AGREED WITH OVERHEAD PANEL. FOUND CABIN PRESS CONTROLLER SYSTEM 1 FAILING BITE CHECK. REMOVED AND REPLACED 105HM CABIN PRESSURE CONTROLLER, OPS CHECKS GOOD AT THIS TIME. REF AMM 21-31-11-04. REMOVED AND REPLACED RELAY 159GB AS A PRECAUTIONARY MEASURE. REF ESWPM. REMOVED SYSTEM 2 106HM CABIN PRESSURE CONTROLLER AND MARKED BROKEN PIN AND WIRE WITH EXTRACTION TOOL. RETERMINATED PIN 13D AS PER WIRING DIAGRAM 21-31-01. PERFORMED CABIN PRESSURE CONTROL AND MONITORING ADJUSTMENT/TEST AS PER MM 21-31-00-05 OPS CHECK NORMAL.

Part: RIB — DAMAGED (NR 1 PYLON) · airframe 35,171 hrs · 29,536 cycles

UPON REMOVAL OF AFT MOUNT NR 1 PYLON FOUND FWD OTBD FASTENER TO BE DAMAGED. REPAIRED AFT MOUNT NR 1 PYLON IAW EA 6-5450-135200 BY THE FOLLOWING REPAIR INSTRUCTION. R & R TAPERED SHIM BY NEW ONE AND BY TECHNICAL DISPOSITION REF 70534938/007/2010 ISSUE B DATED 9TH JUN 2010.

Part: BEARING RACE — CORRODED (NR1 PYLON) · airframe 35,171 hrs · 29,536 cycles

LT PYLON SPIGOT RECEPTACLE FITTING HAS CORROSION AROUND ENTIRE CIRCUMFERANCE OF BEARING RACE AND INSIDE RACE ACCOMPLISHED S/B IAW EA 6-5450-135184 NACELLES/PYLONS NR 1 PYLON SPIGOT FITTING.

Part: FRAME — DAMAGED (ZONE 200) · airframe 35,171 hrs · 29,536 cycles

TOOLING DAMAGE LOCATED AT FR14, STRINGER 12L COMPLIED WITH REPAIR ON FR14 AT STR 12L IAW EA 6-5310-135211, BY SMOOTH REWORK AREA , PERFORMING DVI IAW NTM 51-10-08 ENSURING NO DAMAGE EXIST , PERFORMED ROTOTEST INSP IAW NTM 51-10-01, IMPROVED SURFACE ROUGHNESS NEAR FASTENER HOLES, PERFORMED SPOT FACING IAW SRM 51-71-80 , PERFORMED A DVI IAW NTM 51-70-00 AND ROTOTEST IAW NTM 51-10-01 AND NTM 51-10-18 . REINSTALLED FASTENERS REF PROPER INSTRUCTIONS.

Part: SKIN — DENTED (CARGO DOOR) · airframe 35,171 hrs · 29,536 cycles

BULK CARGO DOOR EXT SKIN OUTER SIDE HAS 1SQ IN DENT LOCATED 29 IN FROM FWD END AND 4.5 IN FROM BOTTOM. COMPLIED WITH EA NR 6-5230-135206 BULK CARGO DOOR SKIN DENT REF SNRM N00578 FOR WORK DETAILS.

Part: FERRULE — CRACKED (NR 2 PYLON) · airframe 35,171 hrs · 29,536 cycles

NR 2 PYLON FERRULE HAS CRACKS AT FWD OTBD LOCATION AND HAS PREVIOUS REPAIRS ON IT. REPAIRED NR 2 PYLON FERRULE IAW EA6-548-135179 (NR 2 PYLON PRECOOLER DUCT FERRULE) AND SB 54-2028 NACELLES/PYLONS.

Part: FERRULE — CRACKED (NR 1 PYLON) · airframe 35,171 hrs · 29,536 cycles

NR 1 PYLON HAS A CRACKED FERRULE AT THE FWD INBD CORNER. REPAIRED NR1 PYLON FERRULE IAW EA6-548-135179, (NR1 PYLON PRECOOLER DUCT FERRULE) AND SB 54-2028, NACELLES / PYLONS.

Part: STRINGER — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

AFT CARGO BILGE STR 57 HAS CORROSION FROM FR 54.2 TO FR 54.3, APPROX 18 SQ IN. REMOVED LEVEL 1 CORROSION. REMOVED DAMAGED STRINGER SECTION AND INSTALLED STRINGER REPAIR ON STR 57 BETWEEN FR 54.2 AND FR 54.3 IAW SRM 53-10-14, FIG 201.

Part: FITTING — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

AFT CARGO BILGE LT SIDE FRAME TO FLOORBEAM SUPPORT FITTING HAS LEVEL 1 CORROSION IN AND AROUND FASTENER HOLE UNDER PROFILE APPROX 3 SQ IN. R & R FITTING IAW SRM 51-72-10, PGS 201-204.

Part: SEAT TRACK — DAMAGED (MAIN CABIN) · airframe 35,171 hrs · 29,536 cycles

UPON REMOVAL OF SEAT TRACK LOCATED AT FR 20 6IN. GOUGES ON SCALLOP CUT-OUTS WERE FOUND TO BE WITHIN LIMITS. R & R SEAT TRACK SEGMENT WITH FABBED SEGMENT DUE TO OUT OF TOLERANCE HOLES WHICH OCCURED DURING REMOVAL IAW SRM 51-72-10 PG 201-204 AND EA 6-5313-135201.

Part: STRINGER — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

AFT CARGO BILGE STR 56 RT HAS CORROSION FROM FR 54.2 TO FR 54.3, APPROX 18 SQ INCH. REMOVED LEVEL 1 CORROSION. REMOVED DAMAGED STR SECTION AND INSTALLED STRINGER. REPAIR ON STR 56 RT BETWEEN FR 54.2 AND FR 54.3 IAW SRM 53-10-14, FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

BULK CARGO 4 IN AFT OF FR 65 ON STR 53 LT HAS AREA OF CORROSION,1 SQ INCH. REMOVED LEVEL 1 CORROSION. REMOVED DAMAGED STR SECTION AND INSTALLED STR REPAIR ON STR 53 LT BETWEEN FR 65 AND FR 66 IAW SRM 53-10-14, FIG 201.

Part: FITTING — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

AFT CARGO FLOORBEAM TO FRAME FITTING HAS LEVEL 1 CORROSION IN AND AROUND (3EA) UPPER FASTENER HOLES DIRECTLY UNDER OTBD ROLLER TRAY APPROX 5 SQ IN. R & R FITTING IAW SRM 51-40-21, P22.

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 35,171 hrs · 29,536 cycles

LT INBD FLAP T/E AT MIDSPAN HAS 2EA DISBONDED AREAS ON TOP AND BOTTOM SKINS APPROX 24" (INCHES) LENGTH TOTAL. REMOVED PREVIOUS REPAIR DOUBLER, LT INBD FLAP T/E UPPER SKIN MIDSPAN IAW SRM 51-77-11. CUT OUT DISBONDED UPPER SKIN IAW SRM 57-53-12, PAR 13 B(5). CUT OUT DIMENSIONS 19.25"L X 3.75"W . REMOVED DAMAGED CORE AND INSTALLED CORE REPAIR PLUG IAW SRM 57-53-12, PG 247, STEP 14. THE HONEYCOMB PLUG REPAIRED THE LOWER SKIN. FABRICATED AND INSTALLED REPAIR DOUBLER FOR UPPER SURFACE. (DIMENSIONS ARE 36"L X 5.5"W) IAW SRM 57-53-12, PAR 2.B. TREATED, PRIMED AND TOPCOATED REPAIR AREA IAW SRM 51-21-1- AND 51-75-10, PAR. 4. COMPLIED WITH EA 6-5750-135207. THIS IS A MAJOR REPAIR IAW GMM 6-2-100. THIS WORK INFORMATION IS ON FILE UNDER WO 48090 AT CWF.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 35,171 hrs · 29,536 cycles

FUSELAGE INTERNAL STRUCTURE ZONE 170, STR 44 R HAS SURFACE CORROSION BETWEEN FR 78-79, APPROX 4.50" X 1.75". REMOVED CORROSION IAW SRM 51-74-10. FOUND TO BE OUT OF LIMITS IAM SRM 53-10-00 TABLE 102. REPAIRED STR 44R BETWEEN FR 78-79, IAW SRM 53-10-14, FIG 201.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 35,171 hrs · 29,536 cycles

AFT CARGO DOOR EXT SKIN OUTER SIDE AT BOTTOM AFT CORNER HAS 1 IN CRACK AND GOUGED R & R DAMAGED SECTION CORNOR ON AFT CARGO DOOR IAW SRM 51-72-10 AND SRM 51-40-21.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 35,171 hrs · 29,536 cycles

AFT CARGO DOOR BOTTOM EXT SKIN OUTER SIDE BETWEEN 2EA AFT LATCH HOOKS HAS 1 IN LENGTH CRACK AND 1 SQ IN BULGE OF SKIN. R & R LT SECTION AT THE BOTTOM OF AFT CARGO DOOR IAW SRM 51-72-10 AND SRM 52-40-30.

Part: SKIN — CHAFED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

EXTERNAL FUSELAGE SKIN AT FR 38 AND STR 42R HAS 1 EA TOOL MARK SURROUNDING FASTENER 1 IN LENGTH X 1 IN WIDTH X 0.007 IN DEPTH. TOOL MARK BLENDED, FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. DAMAGE CUTOUT AND WAS NDT INSPECTED IAW NTM 51-10-08 AND NO CRACKS FOUND. DOUBLER AND FILLER FABRICATED AND INSTALLED IAW SRM 53-10-12, FIG 224.

Part: BEAM — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

AFT CARGO DOOR LOWER TORQUE BOX, UPPER LONGITUDINAL BEAM IS CORRODED ON INSIDE SURFACE, JUST FWD OF FRAME 60. (APPROX 2 SQ. INCHES) R & R AFT CARGO DOOR LOWER DOOR SILL BEAM IAW DWG R53970189 FROM FRAME 59R TO 64R.

Part: FLOORBEAM — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

AFT CARGO FLOORBEAM FRAME 60, 45" RT OF CTRLINE, UPPER CHORD LOWER SURFACE IS EXFOLIATED AROUND FASTENER HOLE APPROX 4 SQ IN TOTAL. R & R FR 60 CROSSMEMBER SEC BEAM RT AT AFT CARGO DOOR SILL BEAM IAW SRM 51-72-10.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 35,171 hrs · 29,536 cycles

AFT CARGO BILGE STR 47R HAS CORROSION ON VERTICAL LEG JUST FWD OF FRAME 59 APPROX 2 SQ IN TOTAL. REMOVED CORROSION IAW SRM 51-74-10, PAGE 205. CHECKED LIMITS FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00 TABLE 6. REPAIRED STRINGER 47R BETWEEN FRAME 59 AND 58 IAW SRM 53-10-14, FIG 201.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 35,171 hrs · 29,536 cycles

AFT CARGO BILGE STR 50 R HAS CORROSION ON VERTICAL LEG FROM FRAME 55/58 TO FRAME 59 APPROX 20 SQ IN TOTAL. REMOVED CORROSION IAW SRM 51-74-10, PAGE 205. CHECKED LIMITS AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00, TABLE 102 DAMAGE CODE C. REPAIRED STR 50 R BETWEEN FR 55/58 AND FR 59 IAW SRM 53-10-14 FIG 201.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 35,171 hrs · 29,536 cycles

AFT CARGO BILGE STR 48 R HAS CORROSION ON VERTICAL LEG AND TOP LEDGE FROM FR 55/58 TO FR 59, APPROX 8 SQ IN TOTAL. REMOVED CORROSION IAW SRM 51-74-10 PAGE 205. CHECKED LIMITS AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00 TABLE 102 DAMAGE CODE C. REPAIRED STR 48 R BETWEEN FR 55/58 TO FR 59 IAW SRM 53-10-14, FIG 201.

Part: FLOORBEAM — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

BULK CARGO PIT FLOORBEAM FR 64 TOP L/E OF FLANGE CORRODED 1.5 SQ INCH. LT OF CTR LINE. REMOVED CORROSION IAW SRM 51-74-10 , FOUND OUT OF LIMITS IAW SRM 53-10-00, FIG 104, TABLE 102. REPAIRED FLOORBEAM IAW SRM53-10-15, FIG 207

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 35,171 hrs · 29,536 cycles

UPPER DECK SEAT TRACK 4R HAS CORROSION ON INBD FLANGE AT FRAME 26, 12". (APPROX 2 SQ IN TOTAL). R & R SEAT TRACK AT FRAME 26, 12" 4R IAW SRM 53-10-16 PG 244.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 35,171 hrs · 29,536 cycles

BULK CARGO PIT FLOOR , FRAME 66 AT CTR LINE FLOORBEAM TOP SURFACE CORRODED. R & R FLOORBEAM AT FR 66 IAW SRM 51-72-10 PAGE 1-2 AND SRM 53-17-15, PAGE A68, FIG 11.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 35,171 hrs · 29,536 cycles

MDCC LT SEAT TRACK Y450, 3" FWD OF FRAME 80 THERE IS ONE AREA OF CORROSION INSIDE THE SCALLOPED AREA (APPROX .7500 SQ INCH). ONE AREA OF CORROSION ON TOP OF A SCALLOP EAR (APPROX .5 SQ. INCH.). REPAIRED SEAT TRACK LT Y450 USING SPLICING METHOD BETWEEN FRAME 80 AND FRAME 79 IAW SRM 53-10-16, PB 201, PARA 10, FIG 208, DUE TO CORROSION BEING OUT OF LIMITS IAW SRM 53-10-16 PB201, FIG 208.

Part: SKIN — CRACKED (NR 1 PYLON) · airframe 35,171 hrs · 29,536 cycles

NR1 PYLON OTBD LATERAL WALL AT RIB 4A PRECOOLER HAS 1 EA CRACK. REPAIRED NR1 PYLON PRECOOLER LATERAL WALL AT RIB 4A IAW SRM 54-52-31, PB201, FIG 202.

Part: STRUCTURE — CRACKED (FAN COWL) · airframe 35,171 hrs · 29,536 cycles

NR 1 PYLON LT FWD SIDE SKIRT HAS 0.125" CRACK AFT EDGE UPPER CORNER OF LT FAN COWL. STOP DRILLED CRACK IAW SRM 54-56-10 FIG 201, NDT VERIFIED NO CRACK INDICATIONS IAW NTM 51-60-00 BEYOND STOP DRILL. FABRICATED, LOCATED, AND DRILLED DOUBLER IAW SRM 54-56-10 FIG 201. INSTALLED DOUBLER IAW SRM 54-56-10, FIG 201. INSTALLED DOUBLER IAW SRM 54-56-10, FIG 201.

Part: STRUCTURE — CRACKED (ZONE 400) · airframe 35,171 hrs · 29,536 cycles

NR 1 PYLON LOWER AFT AREA SECTION MEMBER HAS 1.5 IN LONG CRACK. R & R MEMBER ON NR 1 PYLON LOWER AFT AREA AT RIB 19 IAW SRM 51-72-10, PARAGRAPH 3A.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 35,171 hrs · 29,536 cycles

UPPER DECK SEAT TRACK 5R HAS CORROSION ON UPPER SURFACE BOTH FLANGES AND INSIDE SCALLOPS (APPROX 10 SQ IN TOTAL) FROM FRAME 18 TO FRAME 19. R & R SEAT TRACK 5R FROM FRAME 18 TO FRAME 19 IAW SRM 51-72-10. ALSO IAW SRM 53-12-16 PAGE 4G/4H.

Part: STRINGER — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

BULK CARGO FRAME 65 AT STRINGER 54 RT HAS 2 SQ IN OF CORROSION REMOVED LEVEL 1 CORROSION. CUT OUT DAMAGED SECTION OF STRINGER 54 RT BETWEEN FR 65 AND FR 66 AND INSTALLED STRINGER REPAIR IAW SRM 53-10-14, FIG 201, PAGE 203/204.

Part: STRINGER — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

BULK CARGO AT FR 68, STRINGER 56 RT HAS CORROSION ON INSIDE OF STRINGER. REMOVED LEVEL 1 CORROSION. CUT OUT DAMAGED SECTION OF STR 56 RT BETWEEN FR 66 AND FR 67 AND BETWEEN FR 68 AND FR 69 AND INSTALLED STRINGER REPAIR IAW SRM 53-10-14, FIG 201, PAGE 203/204.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 35,171 hrs · 29,536 cycles

UPPER DECK SEAT TRACK FROM FR 62 TO FR 65,TRACK 5 LT HAS CORROSION ON INBD FLANGE. REMOVED LEVEL 1 CORROSION. CUT OUT DAMAGED SECTION OF SEAT TRACK BETWEEN FR 62 AND 12 INCHES AFT OF FR 65 AND INSTALLED SEAT TRACK SPLICE REPAIR AT TRACK NR 5 LT IAW SRM 53-10-16, FIG 208, PAGE 247/248.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

BULK CARGO FR 65 AT STRINGER 52 LT HAS CORROSION ON STRINGER SPLICE. 1 SQ INCH REMOVED LEVEL 1 CORROSION. REMOVED DAMAGED SPLICE SECTION AND INSTALLED NEW SPLICE AT FR 65, STRINGER 52 LT IAW SRM 53-10-14, FIG 201 AND SRM 51-75-10.

Part: STRINGER — CORRODED (ZONE 100) · airframe 35,171 hrs · 29,536 cycles

AFT CARGO BILGE STRINGER 54 RT HAS CORROSION ON VERTICAL LEG FROM FR 59 TO FR 60. REMOVED LEVEL 1 CORROSION. CUT OUT DAMAGED SECTION OF STRINGER 54 RT BETWEEN FR 59 AND FR 60 AND INSTALLED STRINGER REPAIR IAW SRM 53-10-14, FIG 201,PAGE 203/204.

Part: PUMP — FAILED (HYD SYTEM) · airframe 35,020 hrs · 29,436 cycles

LOST YELLOW HYD SYS QUANTITY AT CRUISE C/W ECAM AND C/W QRH. EDP RUPTURED. PER MM 29-00-00-3, INSPECTED CLOGGING INDICATORS OF CASE DRAIN, DELIVERY AND RETURN FILTERS. NONE OUT. VISUALLY INSPECTED CASE DRAIN FILTER, NO CONTAMINATION OR DECOMPOSED FLUID FOUND. REMOVED AND REPLACED CASE DRAIN FILTER IAW MM 29-11-36-4. PRECAUTIONARY. REMOVED AND REPLACED YELLOW EDP IAW MM 29-11-32-4. SYSTEM BLEED ACCOMPLISHED IAW MM29-00-00-4. YELLOW SYS CHECK PERFORMED PER MM 29-00-00-6. SYSTEM OPERATES NORMALLY, NO LEAKS NOTED.

Part: LAP JOINT — MISREPAIRED (ZONE 200) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS EXTERNAL LAP SEAM REPAIR LOCATED AT UPPER CROWN FUSELAGE SKIN AT FRAME 67 AND BETWEEN STRINGERS 4 TO 7 RT THE REPAIR FILLER MEASURES 7.8 INCHES BY 11.9 INCHES WITH 2 ROWS OF FASTENERS PAST THE DOUBLER WITH A .900 INCH MILL STEP AROUND THE OUTER ROW AND THE REPAIR DOUBLER MEASURES 8.5 INCH BY 9.8 INCH. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT SKIN REPAIR IAW A310 SRM 53-10-12, FIG 217, SHEET 3. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: FRAME — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS FRAME REPAIR LOCATED IN AFT CARGO ON FRAME 54.2 UNDER FLOOR BETWEEN STRINGERS 54 LT AND 57 HAS 1 REPAIR ANGLE ON THE LOWER AFT SIDE MEASURING 11.7" BY 3" WITH A LOWER FLANGE CUT OUT OF 2.6" BY 1" REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT FRAME REPAIR IAW FED-EX EA 6-5310-117993, DATED 31 DEC 07. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 56 LT BETWEEN FRAMES 54 TO 54.2 HAS 1 REPAIR SECTION MEASURING 27.5" LONG AND 4 REPAIR ANGLES, INBD BOTTOM ANGLE IS 20.4 INCH LONG, THE STACKED INBD ANGLE IS 16.3 INCH LONG, THE OUTBD BOTTOM ANGLE IS 19.2 INCH LONG AND THE STACKED OUTBD ANGLE IS 13.9 INCH LONG REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER REPAIR IAW A310 SRM 53-10-14, FIG 201A. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IOS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: FLOORBEAM — CORRODED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

AFT CARGO COMPT LT SIDE FRAME 58 FLOOR LEVEL CROSS MEMBER HAS CORROSION ON UPPER SURFACE REMOVED DAMAGED SECTION ON LT SIDE OF CROSSBEAM AT Y140 AND INSTALLED CROSSBEAM REPAIR IAW A310 SRM 53-10-15, FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER

Part: STRINGER — FAILED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 51 LT BETWEEN FRAMES 55/58 TO 63 HAS 2 EA REPAIR SECTIONS THE FWD REPAIR SECTION IS BETWEEN FRAMES 55/58 TO 61 MEASURING 46" LONG AND THE AFT REPAIR SECTION IS BETWEEN FRAMES 60 TO 63 MEASURING 46.7" LONG WITH 2EA REPAIR SPLICES MEASURING 7.8" LONG EACH REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER REPAIR IAW A310 SRM 53-10-14,FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — FAILED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 53 RT BETWEEN FRAMES 61 TO 63 HAS 2 REPAIR SECTION MEASURING 16" LONG FOR THE FORWARD REPAIR SECTION AND 19.7" LONG ON THE AFT SECTION WITH 2 REPAIR SPLICES MEASURING 8" LONG. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER REPAIR IAW A310 SRM 53-10-14, FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — FAILED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 57 BETWEEN FRAMES 68 TO 70 HAS 1 REPAIR SECTION MEASURING 18.8" LONG AND 2 REPAIR SPLICES MEASURING 7.6" LONG REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED. CORRECT REPAIR IAW FED-EX EA NR 6-5310-113429, DATED 16 DECEMBER 2007. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — FAILED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 53 LT BETWEEN FRAMES 62 TO 64 HAS 1 REPAIR SECTION MEASURING 17.1" LONG AND 2 REPAIR SPLICES MEASURING 7.9" LONG REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER REPAIR IAW A310 SRM 53-10-14, FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — FAILED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 54 RT BETWEEN FRAMES 55/58 TO 60 HAS 1 REPAIR SECTION MEASURING 29" LONG AND 1 REPAIR SPLICE MEASURING 7.9" LONG. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER REPAIR IAW A310 SRM 53-10-14, FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — FAILED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 55 LT BETWEEN FRAMES 55/58 TO 60 HAS 1 REPAIR SECTION MEASURING 29.1" LONG AND 1 REPAIR SPLICE MEASURING 7.7" LONG. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER REPAIR IAW A310 SRM 53-10-14, FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — FAILED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 52 RT BETWEEN FRAMES 60 TO 62 HAS 1 REPAIR SECTION MEASURING 16.3" LONG AND 2 REPAIR SPLICES MEASURING 7.4" LONG. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER REPAIR IAW A310 SRM 53-10-14, FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — FAILED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 55 LT BETWEEN FRAMES 61 TO 64 HAS 1 REPAIR SECTION MEASURING 42" LONG AND 2 REPAIR SPLICES MEASURING 7.8" LONG. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER REPAIR IAW A310 SRM 53-10-14, FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 56 LT BETWEEN FRAMES 66 TO 69 HAS 1 REPAIR SECTION MEASURING 47.1" LONG AND 2 REPAIR SPLICES MEASURING 8" LONG. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER SPLICE REPAIR IAW A310 SRM 53-10-14, FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 56 LT BETWEEN FRAMES 62 TO 63 HAS 1EA REPAIR SPLICE MEASURING 14.1" LONG AND 1 REPAIR FILLER MEASURING 16.6" LONG AND 1 REPAIR SECTION FROM FRAME 55/58 TO 63 MEASURES 88.5" LONG REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER SPLICE REPAIR IAW A310 SRM 53-10-14, FIG 201A. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 56 LT BETWEEN FRAMES 68 TO 70 HAS 1 REPAIR SECTION MEASURING 16" LONG AND 2EA REPAIR SPLICES MEASURING 8" LONG REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER SPLICE REPAIR IAW A310 SRM 53-10-14,FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: FLOOR SUPPORT — MISREPAIRED (ZONE 200) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN COURIER AREA FLOOR SUPPORT "T" CAP RT SIDE BETWEEN FR 14 TO 15A , NR 4 LONGERON FROM CENTER -Y1956 HAS 2EA REPAIR ANGLES MEASURING 7.2" LONG AND 1 REPAIR SECTION MEASURING 17.2" LONG. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUSLY INSTALLED REPAIR AND INSTALLED CORRECT REPAIR IAW A310 SRM 53-12-15,FIG 207. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 200) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED AT UPPER LT SIDE FUSELAGE SKIN AT FRAME 64 BETWEEN STRINGER 21 TO 22A LT ON LAP SEAM REPAIR DOUBLER MEASURE 6.9" BY 5.6" REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUSLY INSTALLED REPAIR AND INSTALLED CORRECT FUSELAGE SKIN LAPSEAM REPAIR IAW A310 SRM 53-10-12, FIG 216,SHEET 1 AND 2. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: FLOORBEAM — MISREPAIRED (ZONE 200) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN FLOORBEAM FR 37 LT SIDE BETWEEN SEAT TRACKS NR 4 LT Y1456 AND NR 5 LT Y1959 HAS 1 REPAIR ANGLE MEASURING 8.5" LONG BY 2.5" WIDE ON THE UPPER FORWARD FLANGE WITH 2 STOP DRILLED HOLES ON FLOORBEAM REPAIR NOT IAW EA REQUIREMENTS. REMOVED PREVIOUSLY INSTALLED REPAIR AND INSTALLED CORRECT FLOORBEAM REPAIR IAW FED EX EA 6-5122-50302, DATED MAY 3, 2000. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: FLOORBEAM — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS CROSSBEAM REPAIR LOCATED IN FWD CARGO UNDERFLOOR AT FRAME 38.2 BETWEEN ROLLER TRACKS LT NR 2 Y805 AND RT NR 2 -Y805 HAS 1 REPAIR SECTION MEASURING 27.4" LONG AND 2 REPAIR ANGLES MEASURING 11" LONG LT SIDE AND 8.5" LONG RT SIDE REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUSLY INSTALLED REPAIR AND INSTALLED CORRECT CROSSBEAM REPAIR IAW A310 SRM 53-10-15, FIG 207. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: FLOOR SUPPORT — MISREPAIRED (ZONE 200) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN COURIER AREA FLOOR SUPPORT "T" CAP RT SIDE BETWEEN FR 14 TO 15A , NR 5 LONGERON FROM CENTER -Y1959 HAS 4 REPAIR ANGLES BOTH THE INBD AND OUTBD SIDE HAVE 2 STACKED REPAIR ANGLES THE BOTTOM ANGLE MEASURES 12" LONG AND THE STACKED ANGLES ARE 7.9" AND 1 REPAIR SECTION MEASURES 17.1" LONG REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUSLY INSTALLED REPAIR AND INSTALLED CORRECT REPAIR IAW A310 SRM 51-71-50, FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — MISREPAIRED (ZONE 400) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 55 RT BETWEEN FR 55/58 TO 60 HAS 1 EA REPAIR SECTION MEASURING 29" LONG AND 1 EA REPAIR SPLICE MEASURING 7.9" LONG REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUSLY INSTALLED REPAIR AND INSTALLED CORRECT STRINGER REPAIR IAW A310 SRM 53-10-14, FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 56 RT BETWEEN FRAMES 55/58 TO 60, HAS 1 EA REPAIR SECTION MEASURING 28.7" LONG, 1 EA REPAIR SPLICE MEASURING 13.8" LONG AND 1 EA REPAIR FILLER 16.1" LONG REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUSLY INSTALLED REPAIR AND INSTALLED CORRECT STRINGER REPAIR IAW A310 SRM 53-10-14, FIG 201A. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS EXTERNAL LAPSEAM REPAIR LOCATED AT LOWER RT SIDE FUS SKIN FR 39, BTWN STR 47 TO 51 RT, REPAIR FILLER MEASURES 8.8" BY 6.4", REPAIR DOUBLER MEASURES 8.5" BY 16.9" REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUSLY INSTALLED REPAIR AND INSTALLED CORRECT REPAIR IAW A310 SRM 53-15-12, FIG 201, SHEETS 1 AND 2. THIS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER THIS IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 52 LT BETWEEN FRAMES 63 TO 65, HAS 1 EACH REPAIR SECTION MEASURING 28.9" LONG AND 1 EACH REPAIR SPLICE MEASURING 7.2" LONG. PREVIOUSLY INSTALLED REPAIR LOCATED AT BULK CARGO ON STRINGER 52 LT BETWEEN FRAMES 63 TO 65 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-14 FIG 201, DUE TO INCORRECT REPAIR SPLICE MATERIAL INSTALLED, BASED ON A VISUAL INSPECTION WITH THE REPAIR INSTALLED. REMOVED EXISTING REPAIR SPLICE AND REPAIRED PER SRM 53-10-14 FIG 201. THIS IS A REPAIR WITH NO AIRBUS ISSUED PART NUMBER, REPAIR IDENTIFIED BY THE AGING AIRCRAFT INSPECTION PROGRAM.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 3 · airframe 33,499 hrs · 28,336 cycles

FWD CARGO COMPARTMENT CROSSMEMBER AT FRAME 34 HAS EXFOLIATION CORROSION AT CENTER AND RT ROLLER TRAY MATING SURFACE REMOVED CORROSION IAW A310 SRM 51-74-10. FOUND TO BE OUT OF LIMITS IAW A310 SRM 53- 10-15. FABRICATED CROSSMEMBER AND SPLICE ANGLES IAW A310 SRM 53-14-15. INSTALLED CROSSMEMBER AND SPLICE ANGLES IAW A310 SRM 53-10-15.

Part: FLOORBEAM — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS CROSSBEAM REPAIR LOCATED IN BULK CARGO UNDER FLOOR AT FRAME 65 BETWEEN RT Y210 TO LT Y1470, HAS 1 EACH REPAIR SECTION MEASURING 53.4" LONG AND 2 EACH REPAIR ANGLES MEASURING 8.8" LONG ON THE LT SIDE AND 9.5" LONG ON THE RT SIDE PREVIOUSLY INSTALLED REPAIR LOCATED IN BULK CARGO AT FR 65 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-15 FIG 207, DUE TO INCORRECT THICKNESS BASED ON VISUAL EVALUATION WITH THE REPAIR INSTALLED. REMOVED EXISTING REPAIR AND REPAIRED IAW A310 SRM 53-10-15 FIG 207. THIS IS A REPAIR WITH NO AIRBUS ISSUED PART NUMBER, REPAIR IDENTIFIED BY THE AGING AIRCRAFT INSPECTION PROGRAM.

Part: FLOORBEAM — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS CROSSBEAM REPAIR LOCATED IN BULK CARGO UNDER FLOOR AT FRAME 64 RIGHT SIDE BETWEEN Y140 AND Y805, HAS 1 EACH REPAIR SECTION MEASURING 25.2" LONG AND 2 EACH REPAIR ANGLES MEASURING 9.2" LONG ON THE FWD AND AFT SIDES PREVIOUSLY INSTALLED REPAIR LOCATED AT BULK CARGO FR 64 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-15 FIG 207 DUE TO INCORRECT THICKNESS BASED ON VISUAL EVALUATION WITH THE REPAIR INSTALLED. REMOVED EXISTING REPAIR AND REPAIRED IAW A310 SRM 53-10-15 FIG 207. THIS IS A REPAIR WITH NO AIRBUS ISSUED PART NUMBER, REPAIR IDENTIFIED BY THE AGING AIRCRAFT INSPECTION PROGRAM.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 3 · airframe 33,499 hrs · 28,336 cycles

FWD CARGO COMPARTMENT AT FR 36 CROSSMEMBER HAS EXFOLIATION CORROSION AT CENTER AND RT ROLLER TRAY MATING SURFACE REMOVED CORROSION IAW A310 SRM 51-74-10 FOUND TO BE OUT OF LIMITS IAW A310 SRM 53-10-15. FABRICATED CROSSMEMBER AND SPLICE ANGLES IAW A310 SRM 53-14-15. INSTALLED CROSSMEMBER AND SPLICE ANGLES IAW A310 SRM 53-10-15.

Part: SEAT TRACK — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN SEAT TRACK NR 4 LT Y1456 BETWEEN FRAMES 50 TO 52, HAS 4 EACH REPAIR SPLICES MEASURING 7.4" LONG BY 3" TALL AND 1 EACH REPAIR SECTION 17" LONG. PREVIOUSLY INSTALLED REPAIR LOCATED AT MAIN CABIN SEAT TRACK NR 4 LT Y1456 BETWEEN FRAMES 50 TO 52 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-16 FIG 205, DUE TO INCORRECT REPAIR INSTALLED, BASED ON A VISUAL EVALUATION WITH THE REPAIR INSTALLED. REMOVED EXISTING REPAIR AND REPAIRED SEAT TRACK PER A310 SRM 53-10-16 FIG 205. THIS IS A REPAIR WITH NO AIRBUS ISSUED PART NUMBER, REPAIR IDENTIFIED BY THE AGING AIRCRAFT INSPECTION PROGRAM.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 51 LT BETWEEN FRAMES 65 TO 66, HAS 1 EACH REPAIR SECTION MEASURING 7.8" LONG AND 1 EACH REPAIR SPLICE MEASURING 7.5" LONG. PREVIOUSLY INSTALLED REPAIR LOCATED AT BULK CARGO ON STRINGER 51 LT BETWEEN FRAMES 65 TO 66 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-14 FIG 201, DUE TO INCORRECT REPAIR SPLICE MATERIAL INSTALLED, BASED ON A VISUAL EVALUATION WITH THE REPAIR INSTALLED. REMOVED EXISTING REPAIR SPLICE AND REPAIRED PER A310 SRM 53-10-14 FIG 201. THIS IS A REPAIR WITH NO AIRBUS ISSUED PART NUMBER, REPAIR IDENTIFIED BY THE AGING AIRCRAFT INSPECTION PROGRAM.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CABIN UNDER FLOOR BEHIND BULK CARGO ON STRINGER 44 RT BETWEEN FRAMES 74 TO 75, HAS 1 EACH REPAIR SPLICE MEASURING 9.6" LONG WITH A 2.1" CUTOUT ON STRINGER. PREVIOUSLY INSTALLED REPAIR LOCATED IN AFT CARGO UNDER FLOOR ON STRINGER 44 RT BETWEEN FR 74 TO 75 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-14 FIG 201 DUE TO INCORRECT THICKNESS. REMOVED EXISTING REPAIR AND REPAIRED IAW A310 SRM 53-10-14 FIG 201. THIS IS A REPAIR WITH NO AIRBUS ISSUED PART NUMBER, REPAIR IDENTIFIED BY THE AGING AIRCRAFT INSPECTION PROGRAM.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 53 RT BETWEEN FRAMES 63 TO 65, HAS 1 EACH REPAIR SECTION MEASURING 32.1" LONG AND 1 EACH REPAIR SPLICE MEASURING 7.9" LONG PREVIOUSLY INSTALLED REPAIR LOCATED AT BULK CARGO ON STRINGER 53 RT BETWEEN FRAMES 63 TO 65 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-14 FIG 201, DUE TO INCORRECT REPAIR SPLICE MATERIAL INSTALLED, BASED ON A VISUAL EVALUATION WITH THE REPAIR INSTALLED. REMOVED EXISTING REPAIR SPLICE AND REPAIRED PER A310 SRM 53-10-14 FIG 201. THIS IS A REPAIR WITH NO AIRBUS ISSUED PART NUMBER, REPAIR IDENTIFIED BY THE AGING AIRCRAFT INSPECTION PROGRAM.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 55 LT BETWEEN FRAMES 65 T0 68, HAS 1 EACH REPAIR SECTION MEASURING 36.8" LONG AND 2 EACH REPAIR SPLICES MEASURING 7.8" LONG ON THE FORWARD SPLICE AND 8.1" LONG ON THE AFT SPLICE. PREVIOUSLY INSTALLED REPAIR LOCATED AT BULK CARGO ON STRINGER 55 LT BETWEEN FRAMES 65 TO 68 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-14 FIG 201, DUE TO INCORRECT REPAIR MATERIAL INSTALLED, BASED ON A VISUAL INSPECTION WITH THE REPAIR INSTALLED. REMOVED EXISTING REPAIR AND REPAIRED STRINGER PER A310 SRM 53-10-14 FIG 201. THIS IS A REPAIR WITH NO AIRBUS ISSUED PART NUMBER, REPAIR IDENTIFIED BY THE AGING AIRCRAFT INSPECTION PROGRAM.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 53 LT BETWEEN FRAMES 68 TO 70, HAS 1 EACH REPAIR SECTION MEASURING 13.2" LONG AND 2 EACH REPAIR SPLICES MEASURING 8" LONG. PREVIOUSLY INSTALLED REPAIR LOCATED AT BULK CARGO ON STRINGER 53 LT BETWEEN FRAMES 68 TO 70 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-14 FIG 201, DUE TO INCORRECT MATERIAL THICKNESS OF REPAIR SPLICES INSTALLED, BASED ON A VISUAL EVALUATION WITH THE REPAIR INSTALLED. REMOVED 2 EACH REPAIR SPLICES AND REPAIRED PER A310 SRM 53-10-14 FIG 201. THIS IS A REPAIR WITH NO AIRBUS ISSUED PART NUMBER, REPAIR IDENTIFIED BY THE AGING AIRCRAFT INSPECTION PROGRAM.

Part: FLOORBEAM — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS CROSSBEAM REPAIR LOCATED IN AFT CARGO UNDER FLOOR AT FRAME 63 BETWEEN ROLLER TRACKS NR 3 LT Y1470 TO PRODUCTION SPLICE INBOARD OF NR 3 RT Y1470, HAS 3 EACH REPAIR SECTIONS PREVIOUSLY INSTALLED REPAIR LOCATED AT AFT CARGO UNDER FLOOR AT FRAME 63 BETWEEN ROLLER TRACKS NR 3 LT Y1470 TO PRODUCTION SPLICE INBOARD OF NR 3 RT Y1470 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-15 FIG 207, DUE TO INCORRECT REPAIRS INSTALLED, BASED ON A VISUAL EVALUATION WITH THE REPAIR INSTALLED. REMOVED CROSSBEAM AND REPLACED FROM PRODUCTION SPLICE TO EXISTING REPAIR ON LEFT SIDE I/B OF NR 3 LT Y1470 ROLLER TRACK PER A310 SRM 53-10-15 FIG 207 51-72-10. NO AIRBUS PART NUMBER, IDENTIFIED BY AGING AIRCRAFT INSPECTION.

Part: SEAT TRACK — MISREPAIRED (ZONE 100) · airframe 33,499 hrs · 28,336 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN SEAT TRACK NR 4 LT Y1456 BETWEEN FRAMES 50 TO 52, HAS 4 EACH REPAIR SPLICES MEASURING 7.4" LONG BY 3" TALL AND 1 EACH REPAIR SECTION 17" LONG. PREVIOUSLY INSTALLED REPAIR LOCATED AT MAIN CABIN SEAT TRACK NR 4 LT Y1456 BETWEEN FRAMES 50 TO 52 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-16 FIG 205, DUE TO INCORRECT REPAIR INSTALLED, BASED ON A VISUAL EVALUATION WITH THE REPAIR INSTALLED. REMOVED EXISTING REPAIR AND REPAIRED SEAT TRACK PER A310 SRM 53-10-16 FIG 205. THIS IS A REPAIR WITH NO AIRBUS ISSUED PART NUMBER, REPAIR IDENTIFIED BY THE AGING AIRCRAFT INSPECTION PROGRAM.

Part: YOKE — LOCKED (COCKPIT) · airframe 32,467 hrs · 27,658 cycles

RIC MISSED APPROACH A/P OFF, SELECTED FLAPS 20, GEAR UP, 3000' SET IN ALT WINDOW. AT 1600' REDC THROTTLES FOR SPD AT THIS POINT CLB STOPPED, PF KEPT BACK PRESS, YOKE SEEMED LOCKED IN PLACE. CAPT TOOK CTL, YOKE LOCKED, COULDN`T CLB. TRIED TO TURN ON A/P, NO LUCK. YOKE RELEASED WHEN TRIM SWITCH NOSE UP USED. ALL NORMAL CTLS, NML LNDG, FLAPS 20, A/P OFF WHEN YOKE LOCKED. C/W GEN INSP/CHK PER MM 27-00-00-6 2C2B. NO HARD SPOTS NOTED IN PITCH TVL. PERF GVI PER MM 27-30-00-6 FROM CNTL YOKES AFT TO AFT ACCY COMPT WHILE OPERATING ELEV NO PROBLEMS NOTED. AREA NOT YET INSP'D IS ON ELE AT HINGE LINE (334/344 PANELS) ON STAB PANELS IN LWR CARGO COMPT'S REMAIN OPEN. R/R FLC1 AND FLC2, NO OTHER DEFECTS FOUND.

Part: PUMP — FAILED (HYD SYSTEM) · airframe 32,231 hrs · 27,524 cycles

FLT LEVEL 350, LOST ALL GREEN HYD FLUID FOLLOWED BY GREEN PUMP LOW PRESSURE. ALL FLUID LEAKED OUT IN ABOUT 20 SECONDS. COMPLIED WITH ECAM. ENGINE 1 GREEN PUMP LOST PRESSURE AS QUANTITY WAS DECREASING BEFORE PUMP 2. GEAR WAS MANUALLY CRANKED DOWN AND HANDLE RETURNED TO NORMAL. REMOVED AND REPLACED LT GRN SYSTEM EDP PER AMM 29-13-32-4. OPS AND LEAK CHECKS NORMAL. REPLENISHED GREEN SYSTEM FLUID AND PRESSURIZED RESERVIOR. PERFORMED INSPECTION PER A310-200 AMM 29-00-00-3. ALL FILTER IND NORMAL. RAN 1/2 ENGINES PER A310 JRH. ALL PRESSURES NORMAL. OK FOR SERVICE.

Part: PRESSURE SWITCH — MALFUNCTIONED (FUEL FILTER) · airframe 31,967 hrs · 27,372 cycles

NR 1 FUEL FILTER CLOG CAME ON ON T/O ROLL. RELEASED FOR SERVICE PER MEL/CDL: 73-36-03-01. NR 1 FUEL CLOG LIGHT(S) INOP. VERIFY AND RECORD IN AML/EAML THAT FILTER HAS BEEN CHECKED FOR CONTAMINATION ONCE EACH FLIGHT DAY. CHECKED FILTER PER A310 AMM CH 73-12-03. UPDATED MPN 45D29, CPN 7310226 QTY 1. REMOVED AND REPLACED FUEL FILTER DIFFERENTIAL PRESSURE SWITCH IAW 73-34-11-4-04. RAN ENGINES IN REFERENCE TO JRH. FUEL PRESS DIFF, PRESSURE SWITCH OPS CHECKS AND LEAK CHECKS GOOD.

Part: SKIN — BENT (KRUEGER FLAP) · airframe 31,293 hrs · 26,899 cycles

WHILE INSPECTING AREA ON SNRM N00815, FOUND LEFT L/E TOP OUTBOARD AREA OF LT KRUEGER FLAP OUTBOARD HINGE CUTOUT HAS A 2 X 1 INCH AREA BENT OUT WITH A 0.4 INCH CRACK AND TWO GOUGES. COMPLIED WITH EA 6-5740-90157. OPS AND LEAK CHECK GOOD IAW A310-200 AMM 27-88-11-4. THIS IS A MAJOR REPAIR IAW FEDEX GMM 6-2-100.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,293 hrs · 26,899 cycles

CORROSION ON FRAME 20A AFT SIDE AT STRINGER 44R FORWARD CARGO. FR20A LOWER SECTION AT STR 44R CORROSION WAS FOUND TO BE OUT OF LIMITS IAW A310/200N SRM 53-10-00 FIG 102. REPAIRED BY CUTTING AND REMOVING FRAME SECTION 20A FROM STR 38R TO STR 45R. INSTALLED NEW FRAME SECTION AND SPLICE REPAIR ANGLES IAW FED EX DRAWING SR30-53-001.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,293 hrs · 26,899 cycles

CORROSION ON INSIDE OF FWD CARGO DOOR CUTOUT ON STRINGER 42R AT FRAME 20A AROUND RIVET BUCKTAIL. REMOVED CORROSION IAW A310/200 SRM 51-74-10 CHECKED BEFORE AND AFTER THICKNESS IAW A310/200 SRM 51-10-04. REPAIR IAW EA6-5313-89485, TREATED AREA IAW A310/200 SRM 51-21-10 AND 5123-10.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,293 hrs · 26,899 cycles

FS 20A STR 41R TO STR 45R HAS 1EA FITTING WITH CORROSION (OFF ACFT PART) PART NR A5377265020202. PART WAS REMOVED ON N00500 ITEM NR 22 ON JPF LOCATED AND DRILLED FITTING P/N A5377265020202 IAW A310/200 SRM 51-40-21. RESTORED PROTECTIVE COATING IAW A310/200 SRM 51-75-10. PART REMOVED AND WILL BE RE-INSTALLED ON NR N00500.

Part: STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,293 hrs · 26,899 cycles

CORROSION AROUND NUT PLATE HOLES ON PANEL SPLICE FOR 326EL. REMOVAL OF CORROSION OUT OF LIMIT PER SRM 55-40-00. REMOVED AND REPLACED STRAP IAW A310/200 SRM 51-72-10.

Part: SUPPORT BRACKET — CRACKED (NR 2 PYLON) · airframe 31,293 hrs · 26,899 cycles

FOUND ANGLE SUPPORT BRACKET FOR MAIN HYDRAULIC LINE CRACKED INBD SIDE OF PYLON AT RIB 20. REMOVED AND REPLACED ANGLE ON NR 2 PYLON IAW A310 SRM 51-40-21 AND 51-72-10.

Part: SKIN — GROOVED (RT FLAP) · airframe 31,293 hrs · 26,899 cycles

RT WING I/B FORE FLAP, CENTER LWR L/E HAS A 1.5 INCH GROOVE WORN INTO SKIN. REMOVED AND REINSTALLED , OPS TEST FLAP IAW A310-200 AMM 27-50-15-4 OPS TEST GOOD. REPAIRED FORE FLAP PER EA 6-5750-89216 AND A310-200 SRM 51-25-00. MAJOR REPAIR IAW FED-EX GMM 6-2-100.

Part: PANEL — CORRODED (NR 2 PYLON) · airframe 31,293 hrs · 26,899 cycles

NR 2 PYLON PNL 423EL HAS SEVERAL AREAS OF CORROSION AND WEAR MARKS ALONG FASTENER HOLES IN EDGE OF PANELS. REMOVED CORROSION AND WEAR MARKS FROM NR 2 PYLON PNL NR 423EL IAW A310-200 SRM 51-74-10. MATERIAL LOSS IS OUT OF LIMITS IAW A310-200 SRM 54-50-00. REPLACED DAMAGED PNL 423EL WITH NEW PNL IAW A310 SRM 51-72-10.

Part: BUTTSTRAP — CORRODED (FUSELAGE) · airframe 31,293 hrs · 26,899 cycles

CORROSION AT TWO NUT PLATE HOLES ON PANEL SPLICE FOR 326JL. REMOVED CORROSION ON PANEL 326JL BUTTSTRAP. MATERIAL LOSS FOUND TO BE OUT OF LIMITS PER A310 SRM 55-40-00. REMOVED AND REPLACED BUTTSTRAP PER A310 SRM 51-40-21.

Part: BUTTSTRAP — CORRODED (FUSELAGE) · airframe 31,293 hrs · 26,899 cycles

CORROSION AROUND NUTPLATE RIVETS ON PANEL SPLICE FOR 326GL, 1 AREA ON ONE END AND 4 AREAS ON OTHER END OF PANEL. REMOVED CORROSION ON PANEL 326GL BUTTSTRAP. MATERIAL LOSS FOUND TO BE OUT OF LIMITS PER A310 SRM 55-40-00. REMOVED AND REPLACED BUTTSTRAPS PER A310 SRM 51-40-21. MINOR REPAIR.

Part: SMOKE DETECTOR — MALFUNCTIONED (E/E BAY) · airframe 29,008 hrs · 25,414 cycles

AVIONICS SMOKE ECAM WARNING ON TAKEOFF. REJECTED AND PERFORMED ECAM AND AVIONICS SMOKE PROCEDURES, NO SNIFFER SMOKE DETECTED, DID RTO CHECKLIST AND RETURNED TO GATE AVIONICS SMOKE WARNING CAME ON 2 MORE TIMES BEFORE BLOCKING IN. REMOVED AND REPLACED E/E SMOKE DETECTOR IAW AMM. OPS CHECK REF, ALL NORMAL.

Part: ATTACH FITTING — BROKEN (NR 3 SPOILER) · airframe 28,939 hrs · 25,380 cycles

RT WING NR 3 SPOILER, OUTBOARD ACTUATOR LUG BROKEN OFF. COMPLETELY MISSING. FOUND DURING C-CHECK INSPECTION BY MX TASK CARD 46C0510. REMOVED AND REPLACED NR 3 RT SPOILER IAW MM 27-61-51-4 RIG AND OPS CHECKS GOOD GOOD IAW/MM 27-61-51-4. SERVICE TAG NO.717764 , MPN/A5771001300000, S/N ON 1040, S/N OFF 016, MPN OFF AJ7700133000. DATE CLOSED 03/12/03. .

Part: UPLOCK — MALFUNCTIONED (THRUST REVERSER)

DURING T/O ROLL AT APPROX 80 KTS, THE NR 1 THRUST REVERSER UNLOCK LIGHT CAME ON. REJECT T/O.

Part: CABLE — TWISTED (NR 1 ENG TR UNIT)

ON T/O ROLL (BELOW 80 KTS) AMBER NR 1 ENG REVERSER UNLOCK LIGHT ILLUM. REJECTED T/O AND RETURNED TO GATE FOR INSPECTION. PERFORMED REJECTION TAKEOFF CHECKLIST. FOUND RT LOWER FLEX CABLE HOUSING TWISTED AND BINDING. REMOVED AND REPLACED FLEX CABLE PER AMM 78-31-12 PG 201-203. T/R OPS CK GOOD ON ENG RUN.

Part: CPC — DEFECTIVE (NR 1/2)

ON DEPARTURE, A/C WOULD NOT PRESSURIZE. PERFORMED BITE CHECKS ON CPC 1 AND 2 NO DEFECTS NOTED. PREFORMED MANUAL CPC OPERATION, OPS CHECKS NORMAL. REMOVED AND REPLACED CPC NR 2 PRECAUTIONARY PER M/M 21-31-11. OPS CHECKS NORMAL PER M/M 21-31-00.

Part: COMPRESSOR — STALLED (NR 1 ENGINE)

NR 1 ENG CLIMBING THROUGH FL230 NR 1 ENGINE HAD VIBRATION AND COMPRESSOR STALLS. ANY POWER SETTINGS ABOVE IDLE WOULD CAUSE COMPRESSOR STALLS. EGT READING 720 DEG, LANDED WITH PWR AT IDLE.

Part: AUTO FEED SYST — INOPERATIVE (INNER TANK)

AT FL 370 CREW NOTICED LEFT FUEL FEED MSG ON ECAM. FUEL PAGE SHOWED NO FUEL WAS BURNING FROM THE INNER TANKS, X-FEED WAS OPENED. O/B FUEL WAS 3.2 + 3.0, LEFT INNER PUMPS WERE TURNED OFF, THEN BACK ON AFTER SEEING NO FUEL BURN. NO ECAM WARNINGS OCCURRED, INNER TANKS STARTED BURN ON GND. REMOVED AND REPLACED RELAY 133QA PER 28-21-00 PRECAUTIONARY, SYS OPS CK NORMAL IN MANUAL MODE PER MM 28-21-00. PRECAUTIONARY INOP AUTO FEED SYS. TRANSFERRED TO DDL PER MEL 28-11 CAT B, EXP 10-20-95 CTL NR 1018068.

Part: IRU — FAILED (NR 1)

THE NR 1 IRU FAILED, SHOWS IRS WARNING AND NR 1 F/D FAILED AT SAME TIME, REPEAT WRITE UP. SWAPPED NR 1 AND NR 3 IRS, NR 1 AND NR 3 IRS ALIGNED NORMAL. DEFER NR 3 IRS PER MEL 34-10 CAT C ITEM CONTROL 0919014, EXP 9-29-95. A/C DOWNGRADED TO CAT 2, MOCCC NOTIFIED, NEED (P/N 461600-0800-0801).