N425FE

Part: COMPUTER — MALFUNCTIONED (NR 1 ENGINE) · airframe 38,910 hrs · 26,279 cycles

REJECTED TAKEOFF AT APPROX 78 KTS. NR1 ENGINE EXCEEDED THE SELECTED FLEX POWER SETTING N1(101.4). THE NR2 ENGINE ENGINE MOMENTARITLY STABLIZED AT 101.4 N1 THEN INCRESED UNSYMETERICALLY TO THRUST LIMIT OFF 107.1. CLEARED RUNWAY AND CHECKED ALL GUAGES FOR EXCEDENANCE, ALL WERE OK. AFTER CONFERENCE WITH MX ANOTHER ATTEMP WAS MADE WITH AUTO THROTTLES ENGAGED, ATS SYS WORKED NORMAL. AFTER CREW DEBRIEF CHECKED MTP AND NR1 PMC SHOWING FAILED. N1 WITHIN LIMITS AND NO ACTION REQUIRED REF 72-00-00-06. NR1 RESET AND WORKING ENTIRE FLIGHT. RELEASED FOR SERVICE IAW MEL: 22-30-01-C. R & R NR 1 TCC IAW MM 22-36-34-04-01. OPS CHECKED GOOD.

Part: SWITCH — INOPERATIVE (CARGO DOOR) · airframe 38,498 hrs · 25,983 cycles

ECAM, FWD CARGO DOOR NOT CLOSED CAME ON AT FL 220 ON DEPARTURE, RAN QRH, CABIN ALT OK, RETURNED TO DEPARTURE, FWD CARGO SWITCH FAULT ECAM CAME ON LATER. R & R FWD CARGO DOOR SWITCH (16WS) IAW MM 52-71-11-04.

Part: SKIN — DAMAGED (ZONE 500) · airframe 38,229 hrs · 25,797 cycles

LEFT WING OTBD FLAP LOWER SKIN DISBONDED 7.5 IN LENGTH X 1.5 IN WIDE AT T/E,48 IN INBD FROM OTBD EDGE. REPAIRED LT WING T/E SKIN IAW EA 6-5750-135278 - WINGS - LT OTBD FLAP T/E -REPAIR TRACKING EA.

Part: SEAT TRACK — BENT (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

SEAT TRACK SCALLOP 9 INCHES AFT OF FRAME 60 THE LOCKING TABS ARE CUT OUT AND 6 INCHES AFT OF FR60 THE LOCKING TABS ARE BENT UP. DAMAGED SEAT TRACK SCALLOPS WERE REPAIRED BY CUTTING SEAT TRACK AND REPAIRED SEAT TRACK IAW SRM 53-10-16, FIG 201, PAGE 206 .

Part: SKIN — MISREPAIRED (LT WING TE FLAP) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LT WING INBD FLAP UPPER SKIN AT RIB 10 TO 11 AND BETWEEEN THE REAR SPAR AND AUXILIARY SPAR ON STRINGERS 6 AND 7 MEASURES 5.4 IN X 6.6 IN. PREVIOUSLY INSTALLED REPAIR LOCATED AT LT WING INBD FLAP UPPER MAIN SKIN AT RIB 10 TO 11 AND BETWEEN THE REAR SPAR AND AUXILIARY SPAR ON STRINGER 6 AND 7 WAS DETERMINED NOT TO BE A VALID. REPAIR IAW ANY SRM BASED ON VISUAL EVALUATION. REMOVED EXISTING REPAIR AND INSTALLED A NEW REPAIR IAW EA 6-5750-135270.

Part: FRAME — FAILED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS FRAME REPAIR LOCATED IN BULK CARGO COMPARTMENT UNDEFLOOR ON FRAME 67 BETWEEN STRINGERS 43 TO 46 RT HAS A REPAIR AGLE ON AFT SIDE OUTER FLANGE MEASURING 9-8 IN LONG. PREVIOUSLY INSTALLED REPAIR LOCATED IN BULK CARGO ON FRAME 67 BETWEEN STRINGERS 43 TO 46 RT OUTER FLANGE WAS DETERMINED NOT TO BE IAW SRM 53-10- 13, FIG 202, PG 209 DUE TO NOT A VALID REPAIR BASED ON A VISUAL EVALUATION WITH THE REPAIR INSTALLED. REMOVED EXISTING REPAIR AND ATTACHING PARTS AND INSTALLED NEW REPAIR AND FABRICATED PARTS IAW EA 6-5310-135266.

Part: CARGO TRACK — CRACKED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

MAIN CARGO DECK FLOOR SUPPORT STRUCTURE FR 54.2 RT SIDE NR 5 SEAT TRACK HAS 3.5 INCH CRACK ON LOWER PART OF SEAT TRACK. REMOVED DAMAGED TRACK SECTION BETWEEN FR 54.2 AND FR 55/58 AND INSTALLED NEW REPLACEMENT TRACK SECTION AT TRACK NR5 RT IAW SRM 51-75-10,53-16-16 AND DWG 16R532H1413.

Part: SKIN — DENTED (ZONE 800) · airframe 38,229 hrs · 25,797 cycles

L 2 DOOR EXTERIOR SKIN 20.5 INCHES FROM AFT END OF DOOR SKIN,12.5 INCHES FROM BOTTOM OF DOOR SKIN HAS SM DENT,10 MM W X .014 IN DEEP CUT OUT DAMAGED SECTION OF EXTERIOR DOOR SKIN AT FR 75 BETWEEN STR 24 LT AND STR 25 LT AND INSTALLED REPAIR EXTERNAL DOUBLER IAW SRM 52-10-00,FIG 206, PAGES 224-226.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 38,229 hrs · 25,797 cycles

IN FWD CARGO AT FRONT FACE OF PRESSURE BULKHEAD FR 39 ALL THE WAY TO BOTTOM AND 24 " LT OF BOTTOM CTR THERE IS CORROSION APPROX 8 SQ INCHES AT STRINGER 50L. REMOVED CORROSION AND DAMAGED AREA IAW SRM 53-15-17 PG 215-216 . REPAIRED AREA BY INSTALLING 1 EA DOUBLER, 4 EA SHIMS, 3EA T-SECTIONS, 1 EA FITTING AND 2 EA STR T-SECTIONS IAW SRM 53-15-17, PAGE 215.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

IN FWD CARGO MAIN DECK FLOORBEAM (FR 37) AT 27 INCHES RT OF CTR LINE. FWD FACE IS A CRACK IN THE UPPER SIDE OF THE BEAM APPROX .7500 INCH LONG REMOVED DAMAGE SECTION , INSTALLED NEW BEAM SECTION IAW SRM 53-10-15, FIG 201.

Part: BEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 38,229 hrs · 25,797 cycles

LONGITUDENAL BEAM Y953 BETWEEN FR 12A AND FR 14 HAS EXFOLIATION CORROSION IN THE MAIN DECK. REMOVED CORROSION IAW SRM 51-74-10, CHECKED, FOUND OUT OF LIMIT. FABRICATED NEW TEE CAP AND REPAIRED IAW SRM 53-12-15 AND DWG 12A536-10797.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

MAIN DECK CARGO COMPT 10 IN AFT OF FR 14 , 57 IN. LT OF CTR LINE FLOOR SUPPORT CHANNEL HAS 4 SQ IN OF LEVEL 1 CORROSION ON UPPER SURFACE OF CHANNEL. REMOVED LEVEL 1 CORROSION. DURING CORROSION REMOVAL FOUND FLOOR SUPPORT CHANNEL OUT OF LIMITS. R & R FLOOR SUPPORT CHANNEL IAW SRM 51-40-21 AND SRM 51-40-44.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

MAIN FLOOR SUPPORT FLANGE UPPER SURFACE OF SEAT TRACK GOUGED .5 SQ IN. LOCATED 4 IN FWD OF FR 17 AND 37IN RT OF CTR LINE. BLENDED GOUGE IN MAIN FLOOR SUPPORT FLANGE 4IN FWD OF FR17 AND37IN RT OF CTR LINE IAW SRM 51-74-10. CHECK LIMITS FOUND OUT OF LIMIT IAW SRM 51-23-10. REPAIRED SEAT TRACK IAW SRM 53-12-16.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

MAIN DECK CARGO COMPARTMENT 5 IN AFT OF FR 14, 31 IN LT OF C/L FLOOR SUPPORT UPPER SURFACE HAS 3 SQ IN OF CORROSION. REMOVED LEVEL 1 CORROSION REMOVED DAMAGED FLOOR SUPPORT, FABRICATED REPLACEMENT PART AND INSTALLED NEW PART BETWEEN FR11 AND FR 15, AT Y770 IAW SRM 53-12-15, FIG 19 AND SRM 51-40-21.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

MAIN DECK CARGO COMPARTMENT 10 IN AFT OF FR 14, 53 IN LT OF C/L FLOOR CHANNEL SUPPORT FOR COURIER SEAT HAS 3 SQ IN OF CORROSION AROUND ANCHOR NUTPLATES TOP SURFACE. REMOVED LEVEL 1 CORROSION. REMOVED DAMAGED FLOOR SUPPORT (WEB) AND REPLACED WITH NEW PART BETWEEN FR 14 AND FR 15A AT Y1359 IAW SRM 53-12-15,FIG 16 AND SRM 51-40-21.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

MAIN CARGO DECK FLOOR STRUCTURE FRAME 54.2 SEAT TRACK STRUCTURE 3R HAS 1 EA .1875" DRILL START (MISDRILL). R & R SEAT TRACK 3R IAW SRM 51-72-10 ON MAIN DECK FLOOR STRUCTURE FR54 TO FR 54.2

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

UPPER DECK FLOOR STRUCTURE BETWEEN FR 18 AND FR19 AT SEATTRACK 2L (Y450) HAS LEVEL 1 CORROSION ON FLANGE UPPER SURFACE APPROX 6 SQ. INCHES, TOTAL CORROSION WAS REMOVED IAW SRM 51-74 10. CHECKED LIMITS AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16. R & R SEAT TRACK 2L BETWEEN FR 18 AND FR 19 IAW SRM 53-12-16.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

MAIN CARGO DECK FLOOR STRUCTURE FR 54.3 BETWEEN SEAT TRACKS 2R AND 3R HAS 1 EA, .25 " CRACK IN STRUCTURE CROSSBEAM. CUT OUT DAMAGED AREA OF CROSSBEAM IAW SRM 53-10-15, FIG 204. NDT VERIFIED CRACKED AREA. REMOVED IAW NTM 51-10-08. FABBED REPAIR PART AND INSTALLED IAW SRM 53-10-15, FIG 204.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CABIN UNDER FLOOR BEHIND BULK CARGO ON STRINGER 39 LT BETWEEN FRAMES 73 TO 74, HAS 1 EACH REPAIR ANGLE SPLICE 12.6" LONG WITH A STRINGER CUTOUT OF 4.4" LONG. PREVIOUSLY INSTALLED REPAIR LOCATED AT AFT CABIN UNDERFLOOR BEHIND BULK CARGO ON STRINGER 39 LT BETWEEN FRAMES 73 TO 74 WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206. DUE TO INCORRECT MATERIAL THICKNESS OF REPAIR ANGLE BASED ON A VISUAL EVALUATION WITH REPAIR INSTALLED. REMOVED EXISTING REPAIR SPLICE AND REPAIRED A NEW REPAIR AND INSTALLED IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206.

Part: FLOOR SUPPORT — MISREPAIRED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN COURIER AREA FLOOR SUPPORT "T" CAP LONGERON RT SIDE BETWEEN FRAMES 12A TO 14, NR5 RT LONGERON FROM CTR- Y1959, HAS 2 EA REPAIR ANGLES MEASURING 11.4" LONG EACH AND 1 EA REPAIR SECTION MEASURING 35" LONG FROM FRAME 12A TO FR15A PREVIOUSLY INSTALLED REPAIR LOCATED AT MAIN CABIN COURIER AREA FLOOR SUPPORT "T" CAP LONGERON RT SIDE BETWEEN FRAMES 12A TO 15A NR 5 RT FROM CTR -Y1959 WAS DETERMINED NOT TO BE IAW SRM 53-12-15, FIG 207, PAGES 230A TO 230B, DUE TO INCORRECT FASTENERS, MATERIAL THICKNESS AND PEELING PAINT WITH NO ALODINE BASED ON A VISUAL EVALUATION WITH REPAIR INSTALLED. R & R COMPLETE ASSY WITH NEW PART ASSY IAW SRM 51-72-10, PAGES 1 TO 3.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS EXTERNAL LAP SEAM REPAIR LOCATED AT LT SIDE FUSELAGE SKIN AT FRAME 38 AND BETWEEN STRINGERS 42 TO 45 LT. THE REPAIR FILLER MEASURES 8.6" X 23.5" AND THE REPAIR DOUBLER MEASURES 21.9" X 10.5". PREVIOUSLY INSTALLED REPAIR LOCATED AT LT SIDE FUSELAGE SKIN LAP SEAM AT FRAME 38 AND BETWEEN STRINGERS 42 TO 45 LT WAS DETERMINED NOT TO BE IAW SRM 53-10-12, FIG 217 SHEETS 1 TO 3, PAGES 262 TO 280. DUE TO INCORRECT MATERIAL THICKNESS, LOCATION AND SKIN CUTOUT, BASED ON A VISUAL EVALUATION WITH REPAIR INSTALLED. REMOVED EXISTING REPAIR AND REPAIRED SKIN IAW SRM 53-10-12, FIG 217, SHEETS 1 TO 3, PAGES 262 TO 280. FOLLOW UP TRACKING IAW SRI 53-10-12-2-002- 00, PARA 3B, PAGES 209 TO 214. INITIAL AT 44,500 FC, REINSPECT 13,700 FC. METHOD IS ULTRASONIC AND EDDY CURRENT.

Part: SKIN — DENTED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

EXTERIOR SKIN JUST AFT OF AFT CARGO DOOR BETWEEN FRAMES 64 AND 65 AND STR 39R AND 44R HAS MULTIPLE DENTS. DEEPEST DENT MEASURED APROX .7500 IN WIDE,1IN LONG AND .027IN DEEP. NDT CHECK C/W NO CRACKS FOUND IAW NTM 51-10-08. REPAIRED EXTERIOR SKIN BY FABRICATING DOUBLER AND TRIPLER IAW SRM 53-17-12, FG 205, PG 225-226 INSTALLED REPAIR DOUBLER AND TRIPLER IAW SRM 53-17-12, FG 205.

Part: SKIN — MISREPAIRED (NR 2 SLAT) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS FLUSH REPAIR LOCATED ON LT WING NR 2 SLAT NOSE SKIN BETWEEN RIB 13 AND 15 JUST BELOW UPPER GIRDER MEASURES 5.4 X 5.8 INCH PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 57-43-11, FIG 202, SHEET 3, PAGES 209 TO 213 AND PAGE 216 DUE TO 64 EA BLIND FASTENERS MISSING LOCK RING WASHERS ON HEADS ONLY. REMOVED 64 EA FASTENERS AND INSTALLED 64EA FASTNERS AND REPAIRED IAW SRM 57-43-11, FIG 202, SHEET 3, PAGE 209 TO 213 AND PAGE 216.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STR REPAIR LOCATED IN AFT CARGO ON STRINGER 52 LT BETWEEN FRAMES 62 TO 63 HAS 1 EACH STRINGER REPAIR SECTION FROM FR 60 TO 63 MEASURING 43IN LONG AND 1EA REPAIR SPLICE 7.6 IN LONG. PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206 DUE TO INCORRECT FASTENER SIZE INSTALLED. REMOVED 6 EA RIVETS, REAMED HOLES UP TO .1875 AND INSTALLED HILOCK IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 47 LT BETWEEN FR 59 AND FR 60 HAS 1EA STRINGER REPAIR SECTION FROM FR 55/58 TO 60 MEASURING 29.4IN LONG AND 1EA REPAIR SPLICE 7.9 INCH LONG. PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201, PAGE 203 TO 206 DUE TO INCORRECT FASTENER SIZE INSTALLED. REMOVED 6 EA, .1562 RIVETS, REAMED HOLES UP TO .1875 AND INSTALLED 6EA HI LOCK IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 45 LT BETWEEN FR 60 AND FR 61 HAS 1 EA STRINGER REPAIR SECTION FROM FR 55/58 TO 62 MEASURING 51IN LONG AND 1EA REPAIR SPLICE 8IN LONG. PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206 DUE TO INCORRECT FASTENER SIZE INSTALLED. REMOVED 6EA 5/32 RIVETS , REAMED HOLES UP TO .0937 AND INSTALLED HILOCK 6EA IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STRINGER REPAIR LOCATED IN FWD CARGO ON STR 47 RT BOTTOM FRAMES 38 AND FR 38.1 HAS 1 EACH REPAIR SPLICE 6.9 INCH LONG AND THE STRINGER SECTION WAS CUT ONLY TO REMOVE FOR ACCESS , ORIGINAL STRINGER INSTALLED. PREVIOUS REPAIR DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206 ONLY DUE TO REPAIR SPLICE NOT HAVING ALODINE PREVIOUSLY AND HAVING PEELING PAINT. REMOVED EXISTING REPAIR SPLICE , CLEANED OFF ALL COATING , APPLIED TREATMENT AND PAINT, AND REINSTALLED EXISTING SPLICE IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STRINGER REPAIR LOCATED IN FWD CARGO ON STR 46 RT BETWEEN FRAME 38 AND FR 38.1 HAS 1 EACH REPAIR SPLICE 6.8 INCH LONG AND THE STRINGER SECTION WAS CUT ONLY FOR ACCESS ORIGINAL STRINGER INSTALLED PREVIOUSLY INSTALLED REPAIR DETERMINED TO NOT IAW SRM 53-10-14 FIG 201 PAGES 203 TO206, ONLY DUE TO REPAIR SPLICE NOT HAVING BEEN PREVIOUSLY ALODINED AND PEELING PAINT. REMOVED EXISTING REPAIR SPLICE, CLEANED OFF ALL COATINGS , APPLIED TREATMENT AND PAINT AND REINSTALLED EXISTING SPLICE IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 56 LT BETWEEN FRAMES 66 TO 67 HAS 1 EA STRINGER REPAIR SECTION FROM FR 65 TO 67 MEASURING 33.5 INCH LONG AND 1 EACH REPAIR SPLICE 8.2 INCH LONG PREVIOUSLY INSTALLED REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206, DUE TO INCORRECT REPAIR SPLICE THICKNESS. REMOVED EXISTING REPAIR SPLICE AND REPAIRED STRINGER IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206 .

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STRINGER REPAIR IN FWD CARGO ON STR 45 RT BETWEEN FR 38 AND FR 38.1 HAS 1 EACH REPAIR SPLICE 6.8 INCH LONG AND THE STR SECTION WAS CUT ONLY TO REMOVE FOR ACCESS ORIGINAL STR INSTALLED PREVIOUS REPAIR DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201 ONLY DUE TO REPAIR SPLICE NOT HAVING ALODINE PREVIOUSLY AND HAVING PEELING PAINT. REMOVED EXISTING REPAIR SPLICE , CLEANED OFF ALL COATINGS , APPLIED TREATMENT AND PAINT AND REINSTALLED EXISTING SPLICE IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STR REPAIR LOCATED IN BULK CARGO ON STR 54 R BETWEEN FR 66 AND FR67 HAS 1 EA STR REPAIR SECTION FROM FR 65 TO FR 67 MEASURING 32 IN LONG AND 1EA REPAIR SPLICE 8.1 INCH LONG PREVIOUS INSTALLED REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201. PAGES 203 TO 206 DUE TO INCORRECT FASTENERS SIZE AND TYPE AND SHAPE OF SPLICE. REMOVED EXISTING REPAIR SPLICE TRIMMED ENDS TO COLLECT SHAPE, REAMED HOLES UP AND REINSTALLED EXISTING REPAIR SPLICE IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STR REPAIR LOCATED IN AFT CARGO ON STR 46 LT BETWEEN FRAMES 61 TO 62 HAS 1EA STR SECTION FROM FR 55/58 TO 62 MEASURING 71.7 INCH LONG AND 1EA REPAIR SPLICE 7.9 INCH LONG. PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206 DUE TO INCORRECT FASTENERS SIZE INSTALLED. REMOVED 6 EA 5/32 RIVETS , REAMED HOLES UP TO .1875 AND INSTALLED 6 EA HILOCKS IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206.

Part: SEAT TRACK — MISREPAIRED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN SEAT TRACK NR1 Y0 BETWEEN FRAMES 61 TO 62, HAS 1 EA REPAIR ANGLE ON LT SIDE UPPER FLANGE MEASURING 9.3 INCHES LONG X 1.7 IN TALL AND 1 EA UPPER FLANGE REPAIR FILLER FOR CUT MEASURING 3.1 INCHX 0.900 IN PREVIOUSLY INSTALLED REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-16, FIG 206, PAGES 206 PAGES 233 TO 236 DUE TO INCORRECT REPAIR ANGLE THICKNESS INSTALLED. REMOVED EXISTING REPAIR ANGLE AND REPAIRED SECTION TRACK IAW SRM 53-10-16, FIG 206, PAGES 233 TO 236.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 55 R/H BETWEEN FR66 AND FR67 HAS 1 EACH STRINGER REPAIR SECTION FROM FR 65 TO 67 MEASURING 32 INCH LONG AND 1 EACH REPAIR SPLICE 8.1 INCH LONG. PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14 FIG 201, PAGES 203 TO 206 , DUE TO INCORRECT FASTENER SIZE AND TYPE AND SHAPE. REMOVED EXISTING REPAIR SPLICE, TRIMMED ENDS TO COLLECT SHAPE REAMED UP HOLES AND REINSTALLED EXISTING REPAIR SPLICE IAW SRM 53-10-14, FIG 201, PAGES 203 TO 206.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 51 RT BETWEEN FRAMES 60 TO 62 HAS 1 EA, STRINGER REPAIR SECTION MEASURING 15.1 INCH LONG AND 2 EA. REPAIRS SPLICES 8.1 INCH LONG PREVIOUSLY REPAIRS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201, DUE TO INCORRECT REPAIR SPLICES MATERIAL THICKNESS. REMOVED 2 EA EXISTING REPAIR SPLICES, FABRICATED 2 EACH NEW SPLICES, TREATED, PRIMED, TOP COATED AND INSTALLED NEW REPAIR IAW SRM 53-10-14, FIG 201, PAGE 203 TO 206.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 38,229 hrs · 25,797 cycles

PREVIOUS EXTERNAL LAP SEAM REPAIR LOCATED AT LOWER FUSELAGE SKIN AT FRAME 66 AND BETWEEN STRINGERS 54 LT TO 56 RT. THE REPAIR FILLER MEASURES 19.3 IN X 11 IN AND THE REPAIR DOUBLER MEASURES 17.5 IN X 12.9 IN. AGING ACFT. PREVIOUSLY INSTALLED REPAIR LOCATED AT LOWER FUSELAGE SKIN LAP SEAM AT FRAME 66 AND BETWEEN STRINGERS 54 LT TO 56 RT WAS DETERMINED NOT TO BE IAW SRM 53-10-12, FIG 217 DUE TO LOCATION OF DOUBLER ENDAT LAP SEAM. REMOVED EXISTING REPAIR AND REPAIRED IAW SRM 53-10-12, FIG 217, PAGES 262 TO 280. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100. FOLLOW UP TRACKING IAW EA 6-5310- 99460. INITIAL AT 44,500 FC, REPEAT EVERY 13,700 FC .

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

MDCC SEAT TRACK 4L HAS 2 LOCK TABS GOUGED AT FRAMES 54.3-55. BLENDED GOUGES ON SEAT TRACK IAW SRM 51-74-10. CHECKED LIMITS IAW SRM 53-10-16, FIG 101 AND FOUND OUT OF LIMITS. R & R SEAT TRACK 4L BETWEEN FRAMES 54.3 AND 55 IAW SRM 51-40-21.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 38,229 hrs · 25,797 cycles

MAIN DECK CARGO COMPARTMENT SEAT TRACK 4 LT HAS 3 EA AREAS OF CORROSION ON SCALLOPS AND FLANGE, ABOUT 30 SQ IN BETWEEN FR 74 AND FR 76. REMOVED LEVEL 1 CORROSION. REMOVED DAMAGED SECTION OF TRACK, FABRICATED REPLACEMENT SECTION OF SEAT TRACK, 4 LT BETWEEN FR 74 AND FR 77 AND INSTALLED. ALL WORK ACCOMPLISHED IAW SRM 53-10-16, FIG 208, PAGES 249/250.

Part: UNKNOWN — UNKNOWN · airframe 36,923 hrs · 24,850 cycles

LO TANK READ 1200 LBS LESS AFTER 1 HR T/O. GAUGE HAD DASH IN LAST DIGIT. DASH WENT AWAY. FQI CONTINUED TO DECREASE TO 1200 TOTAL. ON DESCENT FUEL INCREASED, AT LDG FQI READ OK. RELEASE FOR SVC/MEL 28-42-01-01 CAT: C EXP: 21OCT08 ALL LO TANK IND INOP. FUEL TO KNWN QTY/VERIFY TANK QTY WITH MAG STICKS. VERIFIED LO TANK STICK PER 12-11-28 6273LBS AT BLOCK IN. NO LEAKS ON LEFT WING EXT SURFACES. FQ ONBD FUEL USED = 55880LBS. PREV FUEL SLIP FUEL WAS 56.9KLBS. NO FAULTS FLT 1463 REPORTED FQID GOOD ON THIS LEG. FQIS NOTED, 322, 703, 704. PER TSM 28-42-00 CODE SHOULD NOT BE T/S, INTERMITTENT ON BITE, AND SHOULD BE LOGGED, CHK AFTER NEXT FLIGHT. FQI CK OK ;

Part: CONNECTOR — INOPERATIVE (FIRE DETECTION) · airframe 36,716 hrs · 24,707 cycles

AFTER T/O FROM KIND, NR 2 ENG SHOWED ADVISORY FRO "NAC HEAT" OF 90. LEVELED OFF AT 15,000 FEET AND SLOWED TO 200 K. NAC HEAT DID NOT REDUCE. CONSULTED GOC AND RETURNED TO KIND AS EMERGENCY A/C. FIRE DEPT FOUND NO HOTSPOTS. SINGLE-ENG TAXIED TO PARKING. CREW DEBRIEFED REVEALED NO LEFT ECAM SCREEN ADVISORY OR INSTRUCTIONS. ENGINE PAGE CAME UP ON RIGHT ECAM. NO FIRE WARNING ASSOCIATED WITH ENGINE. WENT TO DISCONNECT CONNECTOR DH6 AND FOUND WIRE PULLED OUT OF CONNECTOR. REPLACED CONNECTOR DH6 PER ESPM AND PERFORMED ADJUSTMENT TEST OF FIRE AND OVERHEAT DETECTION SYSTEM. TESTS OK.

Part: SKIN — DAMAGED (ZONE 200) · airframe 36,499 hrs · 24,558 cycles

FOUND 5 HOLES AT FRAME 16A TO HAVE PRE EXISTING TOOLING DAMAGE IN HOLES, FASTENERS MARKED AS A, B, C, D,AND E. COMPLIED WITH EA NR 6-5310-118477 TITLE: " FUSELAGE, AD 2007-11-12 5653-2037-SKIN AT FRAME 16A, OVERSIZED FASTENERS HOLES ".

Part: SKIN — DAMAGED (ZONE 300) · airframe 36,499 hrs · 24,558 cycles

RIGHT ELEVATOR UPPER SURFACE TRAILING EDGE; INBD SECTION HAD 2 DENTS AND A PUNCTURE ON THE INBD T/E WEDGE. REPAIRED DAMAGE TO RT ELEVATOR UPPER SURFACE BY, REMOVING DAMAGED AREAS AND FABBED AND BONDING CORE, AND APPLYING FIBERGLASS LAYUPS IAW A310SRM 55-21-11. RESTORED FINISH IAW A310 SRM 51-75-10.

Part: ATTACH ANGLE — CRACKED (ZONE 500) · airframe 36,499 hrs · 24,558 cycles

LEFT WING ATTACHING ANGLE FOR L/E PANEL 523 HB IS CRACKED. FABRICATED A NEW REINFORCING PLATE IAW AIRBUS DWG 23-A-572-43292 ISSUE F. PRIMED IAW A310 SRM 51-21-10 AND 51-23-10. REPLACED REINFORCING PLATE IAW A310 SRM 51-40-21.

Part: DOOR FRAME — GOUGED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

AFT PIT DOOR, LWR FWD CORNER, GOUGED. FOUND GOUGE TO BE OUT OF LIMITS IAW SRM 51-10-00. REMOVED AND REPLACED EDGE SECTION IAW SRM 51-40-21. FOR ADJUSTMENT AND CHECK SEE WC 41X5114ALI.

Part: STRUCTURE — GOUGED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

AFT PIT DOOR, NEAR AFT HOOK, STRUCTURE DENTED. NO DENTS ALLOWED IAW SRM 51-10-00. REMOVED AND REPLACED EDGE SECTION IAW SRM 51-40-21. FOR ADJUSTMENT AND CHECK SEE WC 41X5114ALI.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

BULK PIT FLOOR SUPPORT AT FRAME 65 - 66 LBL 36 IS CORRODED. REPLACED IAW SRM 51-40-21.

Part: STRINGER — CRACKED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

THE AVOINICS COMPARTMENT FLOOR STRUCTURE FROM FRAME 16 TO 17; STRINGER 44 L IS CRACKED. FORMED EDGING IAW DWG A53612025. HEAT TREATED IAW TPS 1003; REV A. TREATED IAW SRM 51-21-10 & 51-23-10. PART MARKED IAW GMM 7-0-1000; STEP 7-B.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

BULK PIT STR 46 RT FR 67-68 IS CORRODED. REMOVED CORROSION IAW A310-200 SRM 51-22-00. CHECKED LIMITS; MATERIAL REMOVED 100%. FOUND TO BE OUT OF LIMITS IAW SRM 51-10-00. REMOVED STRINGER IAW SRM 51-40-21. RECEIVED NEW STRINGER. DRILLED & LOCATED IAW SRM 51-40-40 & DWG A53973214. INSTALLED IAW SRM 51-40-21.

Part: FITTING — CRACKED (ZONE 200) · airframe 36,499 hrs · 24,558 cycles

RT UPPER CIRCUMFERINTIAL FITTING LOWER FASTENER INDICATES EDDY CURRENT CRACK INDICATION PER NTM 57-10-54. REMOVED AND REINSTALLED FLOOR TRIM AND AIRDUCT, AND FLOOR FITTING IAW A310 SRM 51-40-21 PARA 5, EDDY CURRENT INSP, INDICATION OF CRACK IN FITTING IAW A310NTM 57-10-54 PT 6, MAT ID AND FAB NEW FITTING IAW AIRBUS DWG A53870037 REV G, LOCATED FITTING IAW A310 SRM 51-40-44 TABLE 1, ALODINED, PRIMED, AND PAINTED FITTING IAW A310 AMM 51-75-10-8.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

FOUND SIX EDDY CURRENT INDICATIONS ON INNER SKIN LIP BETWEEN STA - 3620 TO 3726 (FR67 - 69 ) BULK CARGO DOOR. REWORKED IAW SRM 53-17-12. NDT AREA IAW. NTM53-30-52 PT 6 AND 51-10-08. FOUND 1 CORROSION INDICATION NO CRACKS IN SUB STRUCTURE. REMOVE CORROSION IAW SRM 53-17-12 ORIG MAT .238 OF .228 WITHIN LIMITS IAW SRM 53-17-12, REMOVED SECTION, LATERAL WEB, FLOOR SUPPORT AND CORNERS TO FOM IAW SRM 51-40-21 ALODINED IAW SRM 51-21-10, PRIMED AND PAINTED IAW SRM 51-23-10. INSTALLED NEW SECTION P/N A5397305720000, PO NR 614306.5, LATERAL WEB, FLOOR SUPPORT, AFT CORNER P/N A5397326420251, PO 614306.1 AND FWD CORNER P/N A5397325850251, PO 614306.3 IAW 1-40-21.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 36,499 hrs · 24,558 cycles

CENTER ARTICULATING SEAT TRACK FITTING AT FRAME 38.2 IS CRACKED. REMOVED FITTING IAW FEDEX A310 SRM 51-40-21; PARA 7. MATERIAL ID FOR BRACKET 7075-T7351 IAW AIRBUS DWG A53781977 AND A310 SRM 51-31-00. MACHINED A FITTING IAW AIRBUS DWG A53781977. ALODINED AND PRIMED FITTING IAW FEDEX A310 SRM 51-21-10. PAINTED FITTING IAW A310 SRM 51-23-10. LOCATED AND DRILLED NEW FITTING IAW A310 51-40-44. PART MARKED NEW FITTING IAW FEDEX GMM 7-0-1000; PARA 7-B. INSTALLED NEW FITTING IAW A310 SRM 51-40-21; PARA 7.

Part: WEB — DENTED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

FWD CARGO DOOR CUTOUT, LWR FWD WEB DENTED. FABRICATED, POTTED EDGES, COMPLETED CURE AND SANDED EDGE POTTNG. INSTALLED INSERTS & APPLIED NON-SKID IAW DWG 25-005 REV F.

Part: SKIN — DENTED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

EXTERNAL FUSELAGE, FRAME 38, 4 INCHES ABOVE STRINGER 43 RIGHT, SMALL DENT ON RIVET. FOUND DENT TO BE OUT OF LIMITS IAW SRM 53-10-12, FABBED REPAIR DOUBLER AND FILLER IAW SRM 53-10-12. REMOVED DAMAGE IAW SRM 53-10-12. ALODINED IAW SRM 51-21-10. PRIMED & PAINTED IAW SRM 51-23-10. INSTALLED REPAIR IAW SRM 53-10-12 & 51-40-21. NDT ACCOMPLISHED PER NTM 51-10-08. NO FUTHER DAMAGE NOTED.

Part: SKIN — DENTED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

EXTERNAL FUSELAGE, FRAME 38, 4 INCHES ABOVE STRINGER 43 RIGHT, SMALL DENT ON RIVET. FOUND DENT TO BE OUT OF LIMITS IAW SRM 53-10-12, FABBED DOUBLER AND FILLER IAW SRM 53-10-12. REMOVED DAMAGE IAW SRM 53-10-12. ALODINED IAW SRM 51-21-10. PRIMED & PAINTED IAW SRM 51-23-10. INSTALLED REPAIR IAW SRM 53-10-12 & 51-40-21. NDT ACCOMPLISHED PER NTM 51-10-08. NO FURTHER DAMAGE NOTED.

Part: SKIN — DENTED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

EXTERNAL FUSELAGE, FRAME 38, 9 INCHES ABOVE STRINGER 43 RIGHT, SMALL DENT ON RIVET. FOUND DENT TO BE OUT OF LIMITS IAW SRM 53-10-12, REMOVED DAMAGE IAW SRM 53-10-12. FABBED REPAIR PARTS IAW SRM 53-10-12. ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED IAW SRM 51-23-10. INSTALLED REPAIR IAW SRM 53-10-12 & 51-40-21. NDT ACCOMPLISHED PER NTM 51-10-08. NO FUTHER DAMAGE NOTED.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

FWD LOWER CARGO COMPARTMENT/CORROSION ON FWD FACE OF FRAME 35 BETWEEN STRINGER 43 AND 44. FRAME 35 BETWEEN STR 43 AND 44 R CORRODED OUT OF LIMITS IAW A310 SRM 53-10-00. FRAME REPAIRED IAW A310 SRM 53-10-13 FIG 203. MATERIAL ID 2024-0, .063 PO NR 597274.1: HEAT TREATED IAW TIMCO TPS 1003 REV A FRAME (PO NR 612789.5).

Part: PANEL — DAMAGED (ZONE 500) · airframe 36,499 hrs · 24,558 cycles

LEFT WING LOWER SURFACE L/E DROP PANEL (RIB 28) INTERIOR SKIN IS MISSING FOIL. REPAIRED LOWER SURFACE L/E DROP PANEL BY REMOVING DAMAGED FOIL, APPLYING NEW FOIL REPAIR, ALODINED FOIL REPAIR, AND APPLING FR PRIMER IAW SRM 57-41-12, 51-21-00, AND 51-75-10.

Part: SHEAR TIE — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

FOUND BULK PIT, FWD SIDE FR 67 S54L , HAS SURFACE CORROSION. REMOVED CORROSION IAW SRM 51-74-10; REMOVED CLIP IAW SRM 51-40-21 CHECKED LIMITS IAW SRM 51-31-20 AND FOUND TO BE WITHIN LIMITS IAW SRM 53-10-00; ALODINED IAW SRM 51-21-10 AND PRIMED AND PAINTED IAW SRM 51-23-10; RECIEVED NEW CLIP AND INSTALLED IAW SRM 51-40-21.

Part: FAIRING — DELAMINATED (ZONE 600) · airframe 36,499 hrs · 24,558 cycles

NR 5 RIGHT WING FLAP FAIRING OUTER SKIN IS DELAMINATED 5 INCHES AFT OF THE FWD ATTACH POINT. REPAIRED THE DELAMINATION BY REMOVING DAMAGE & APPLYING A WET PAY UP IAW SRM 57-20-35. PAINTED IAW AMM 51-75-10-08.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 36,499 hrs · 24,558 cycles

FWD CARGO DOOR EXTERNAL SURFACE AFT LWR CORNER GOUGED. DEPTH OF GOUGE WAS .048 FOUND TO BE OUT OF LIMITS IAW SRM 52-30-00. REMOVED EDGE MEMBER IAW SRM 51-40-21. REMOVED SEAL RETAINER IAW SRM 51-40-21. RECIEVED NEW EDGE MEMBER IAW SRM 52-31-00. FABBED DOUBLER AND FILLER IAW SRM 52-30-00, INSTALLED DOUBLER & FILLER IAW SRM 51-40-21, INSTALLED EDGE MEMBER & SEAL RETAINER IAW SRM 51-40-21.

Part: SHIELD — CHAFED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

BULK PIT DOORWAY NET SHIELD CHAFED REF EA 6-2550-90213. COMPLIED WITH EA 6-2550-90213.

Part: BULKHEAD — DENTED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

EMPENNAGE AFT PRESSURE BULKHEAD IS DENTED AT THE 9 O'CLOCK POSITION APPROX 32 INCH FROM THE CENTER LINE. DENT IS SHALLOW AND SMOOTH. REPAIRED AREA IAW EA NR 6-5310-118458 "FUSELAGE AFT PRESSURE BULKHEAD WEB DENT".

Part: SKIN — DAMAGED (ZONE 500) · airframe 36,499 hrs · 24,558 cycles

LT FLAP VANE L/E SKIN CHAFED AT NR 3 TRACK ATTACH POINT. GENERATED RFTS N425FE-25-33028. RECEIVED EA NR 6-5750-118464. REMOVED FASTENER FROM BLENDED AREA. HFEC INSPECTED THE HOLE PER NTM 51-10-01 PART 6. NO FINDINGS. INSPECTED BLENDED AREA PER NTM 51-10-08 PART 6. NO FINDINGS. FINISHED BLENDED AREA WITH CORROSION PROTECTION PER SRM 51-23-10. INSTALLED FASTENER IAW SRM 51-40-21 PARA 6. PRIMED AND PAINTED TO MATCH IAW SRM 51-23-10. RECORDED PART NR AND SERIAL NR PER EA 6-5750-118464.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

LEFT MLG WHEEL WELL CUTOUT; INTERNAL LOWER INBD CORNER HAS CORROSION AND BARE METAL. COMPLIED WITH EA 6-5310-118456; FUSELAGE LT MLG DOOR OPENING CORNER FITTING REPAIR.

Part: PANEL — CHAFED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING PANEL NR 612 AT IS CHAFED ON THE MATING SURFACES. COMPLIED WITH EA 6-5720-118459 PT 1.

Part: PANEL — CHAFED (ZONE 500) · airframe 36,499 hrs · 24,558 cycles

LEFT WING PANEL 512 AT IS CHAFED IN SEVERAL AREAS ON THE BACK SIDE. COMPLIED WITH EA 6-5720-118459 PT1.

Part: STRINGER — CORRODED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

BULK PIT; FRAME 68; STRINGER 53R AND STRINGER 54R HAS SURFACE CORROSION. REMVOED CORROSION IAW AMM 51-74-10-8. FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00, DRILLED UP SPLICES AND STRINGERS IAW SRM 51-72-10, ALODINED & PRIMED AREAS AND PARTS IAW 51-21-10, 51-23-10, INSTALLED PARTS STRINGERS AND SPLICES IAW SRM 51-40-21.

Part: WEB — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

MAIN CARGO FLOOR STRUCTURE HAS CORROSION ON THE UPPER SURFACE OF THE FLOOR WEBBING AT APPROX LBL 88 BETWEEN FRAMES 32 AND 33. BLENDED CORROSION IAW SRM 51-74-10, PARA 5. ORIGINAL MATERIAL THICKNESS OF .094 AND .065 AFTER BLEND OUT FOR A TOTAL LOSS OF .029. FOUND TO BE OUT OF LIMITS IAW SRM SUPP 53-74-15; FIG 1. REMOVED WEB IAW SRM 51-40-21 PGS 6-7. LOCATED AND DRILLED NEW WEB IAW SRM 51-40-21 PGS 6-7. ALODINED AND PRIMED WEB IAW SRM 51-21-10. INSTALLED WEB IAW SRM 51-40-21 PGS 6-7. APPLIED CIC ON WEB IAW AMM 51-22-00-0.

Part: FLOOR SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

MAIN DECK FLOOR STRUCTURE, CORROSION ON UPPER SURFACE OF FLOOR WEBBING AT APPROX LBL 88 BETWEEN FRAMES 32 AND 33. BLENDED CORROSION REF SRM 51-74-10 PAR 5. ORIGINAL MATERIAL THICKNESS OF .094 AND .065 AFTER BLEND OUT FOR TOTAL MATERIAL LOSS OF .029 FOUND TO BE OUT OF LIMITS REF SRM SUPP 53-74-15 FIG 1. REMOVED FLOOR WEBBING REF SRM 51-40-21 P 6-7. LOCATED AND DRILLED NEW FLOOR WEBBING REF SRM 51-40-21 P 6-7. ALODINED AND PRIMED FLOOR WEBBING REF SRM51-21-10. INSTALLED FLOOR WEBBING REF SRM 51-40-21 P 6-7 APPLIED C.I.C ON FLOOR WEBBING REF MM 51-22-00-0.

Part: SEAT TRACK — WORN (COCKPIT) · airframe 36,499 hrs · 24,558 cycles

COCKPIT SEAT TRACK INBD SIDE IS WORN WITH 2 GOUGES. BLENDED AREAS IAW A310-200 SRM 51-74-01. FOUND TO BE OUT OF LIMITS IAW A310-200 CMM SOGERMA-SOCEA 25-13-00; PG 602; PARA 3. ORDERED AND RECEIVED NEW SEAT TRACK FROM STORES P/N 2510114050-21, PO 613319.1.

Part: RETAINER — CRACKED (NR 4 SPOILER) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING NR 4 SPOILER OUTBD END HINGE RIB SEAL RETAINED IS CRACKED AND THE SEALS TORN. REMOVED CHANNEL IAW A310-200 SRM 51-40-21. MATERIAL ID IS 2024-0, 0.050; PO 583365.1 IAW A310-200 BRITISH AEROSPACE DWG A-572-46948; SRM 51-31-00; TABLE 3 AND SRM 57-51-11; FIG 7. FABRICATED CHANNEL IAW A310-200 BRITISH AEROSPACE DWG A 572-46948. HEAT TREATED 2024-0 TO 2024-T42 IAW TP 51003; REV A; HRD 57/58 LOAD NR HTO 31908-6. ALODINED; PRIMER AND PAINTED IAW A310-200 SRM 51-23-10. ASSEMBLED SEAL AND RETAINER TO CHANNEL IAW A310-200 BRITISH AEROSPACE DWG A 572-46948. INSTALLED CHANNEL IAW A310-200 SRM 51-40-21; PARA 6 AND 57-51-11; PG 56.

Part: HOUSING — CORRODED (RADIO ALTIMETER) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

NR 1 RADIO ALTIMETER TRANSMISSION ANTENNA MOUNT RING HOUSING CAVITY AND DOME NUTS ARE CORRODED. REMOVED AND REPLACED HOUSING IAW A310-200 SRM 51-40-21.

Part: FLOOR PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

MAIN DECK FLOOR STRUCTURE HAS CORROSION ON THE UPPER SURFACE OF THE FLOOR WEBBING AT APPROX LBL 87 BETWEEN FRAMES 34 AND 35. BLENDED OUT THE CORROSION REF A310-200 SRM 51-74-10; PARA 5. ORIGINAL THICKNESS 0.094 AND 0.087 REMAINING. MATERIAL REMOVED 0.007. FOUND TO BE OUT OF LIMITS IAW A310-200 SRM ; SUPP 53-14-15; FIG 1. UT GAUGE T82750 USED. REMOVED FLOOR WEB IAW A310- 200 SRM 51-40-21; PGS 6-7. DRILLED HOLES IN NEW WEB P/N A5378198422200, PO 612403.1 IAW A310-200 SRM 51-40-44; PGS 1-7. ALODINED HOLES IAW A310-200 SRM 51-21-10 AND PRIMED HOLES IAW A310-200 SRM 51-23-10. INSTALLED FLOOR WEB P/N A5378198422200, PO 612403.1 IAW A310-200 SRM 51-40-21. APPLIED CIC REF A310-200 AMM 51-22-00-0.

Part: SKIN — CHAFED (ZONE 600) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING NR 4 SPOILER T/E IS CHAFED. REMOVED DAMAGED SEALS AND REPLACED THEM WITH NEW SEALS P/N A5771006820851, PO 612443.6 BOTH IAW FEDEX A310-200 SRM 51-40-21; PGS 11-26. PRIMED AND TOP COAT PAINT BOTH IAW FEDEX A310-200 SRM 51-23-10.

Part: SKIN — CHAFED (ZONE 600) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING NR 6 SPOILER TRAILING EDGE IS KNIFE EDGED. REMOVED DAMAGED TRAILING EDGE IAW A310 SRM 51-40-21. LOCATED; DRILLED; AND INSTALLED NEW TRAILING EDGE IAW A310-200 SRM 51-40-21.

Part: PANEL — CHAFED (ZONE 600) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING ROOT HYD SHELF GROUND CONNECTION ACCESS PANEL MATING SURFACE IS WORN. CLEANED CUTOUT AREA REF A310-200 SRM 51-73-10. (NO MATERIAL LOSS); FOUND ONLY PAINT MISSING. ALODINED REF A310-200 SRM 51-21-10; PG 4. PRIMED AND PAINTED REF A310-200 SRM 51-23-10; PG 1.

Part: FLOOR PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

MAIN DECK FLOOR STRUCTURE HAS CORROSION ON THE UPPER SURFACE OF THE FLOOR WEBBING AT FRAME 35; APPROX LBL 87. BLENDED OUT CORROSION REF A310-200 SRM 51-74-10; PARA 5. ORIGINAL MATERIAL THICKNESS OF 0.094 AND 0.065 AFTER BLEND OUT FOR A TOTAL MATERIAL LOSS OF 0.029. FOUND TO BE OUT OF LIMITS REF A310-200 SRM 53-14-13; FIG 1. UT GAUGE 82750 USED. REMOVED WEBBING REF A310-200 SRM 51-40-21; PGS 6-7. LOCATED AND DRILLED WEBBING P/N A5378198422200, PO 612403.1 REF A310-200 SRM 51-40-44; PGS 6-7. ALODINED AND PRIMED WEBBING REF A310-200 SRM 51-21-10. INSTALLED WEBBING REF A310-200 SRM 51-40-21; PGS 6-7. APPLIED CIC REF A310-200 AMM 51-22-00-0.

Part: HOUSING — CORRODED (RADIO ALTIMETER) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

NR 2 RADIO ALTIMETER TRANSMISSION ANTENNA MOUNT RING HOUSING CAVITY AND DOME NUTS ARE CORRODED. REMOVED ANTENNA HOUSING IAW A310-200 AMM 34-43-11-4. REMOVED CORROSION IAW FEDEX A310-200 SRM 51-74-10. 100 PERCENT MATERIAL LOSS; FOUND TO BE OUT OF LIMITS IAW FEDEX A310-200 SRM 53-10-00. RECEIVED NEW HOUSING A539735540040096; PO 613251.1. INSTALLED HOUSING IAW FEDEX A310-200 AMM 34-42-11-4.

Part: RUB STRIP — CHAFED (ZONE 500) · airframe 36,499 hrs · 24,558 cycles

LEFT WING SPOILER T/E RUB STRIP IS CHAFED. REMOVED T/E RUB STRIP IAW AIRBUS CMM 57-73-11. RECEIVED NEW RUB STRIP P/N A5777020920400, PO 612493.2. LOCATED AND DRILLED IAW AIRBUS CMM 57-73-11. INSTALLED RUB STRIP IAW AIRBUS CMM 57-73-11. PRIMED AND TOP COATED IAW A310-200 SRM 51-23-10.

Part: DOOR FRAME — GOUGED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

LOWER FUSELAGE FWD CARGO DOOR CUTOUT AT FRAME 25; STA 1711 LOWER VERTICAL SECTION HAS A GOUGE ON THE EDGE. REMOVED GOUGES IAW A310-200 SRM 51-74-10. ORIGINAL THICKNESS 0.236; REMAINING MATERIAL 0.230; MATERIAL REMOVED 0.006. FOUND TO BE WITHIN LIMITS IAW A310-200 SRM 53-13-12. ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED IAW SRM 51-23-10.

Part: PANEL — CORRODED (ZONE 400) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

NR 2 PYLON PANEL NR 424 ER IS CORRODED ON THE INNER AND OUTER SURFACES. REMOVED CORROSION & CHECKED LIMITS IAW SRM 54-52-21 PG 104. FOUND TO BE OUT OF LIMITS IAW SRM 54-52-51 PG 104. INSTALLED REPAIR IAW SRM 51-52-51 PGS 219-220. ALODINED PARTS IAW SRM 51-21-10. PRIMED & PAINTED PARTS IAW SRM 51-32-10 PG 1. MINOR REPAIR.

Part: PANEL — CHAFED (LT WING) · airframe 36,499 hrs · 24,558 cycles

LEFT WING FUEL TANK PLATE NR 540 FB HAS FRETTING FROM THE MESH GASKET. EVALUATED AND FOUND TO BE OUT OF LIMITS FOR PANEL 540 FB DUE TO NO DAMAGE ALLOWED IN AREA PER FEDEX A310 SRM 57-20-16; PG 109. ORDERED AND RECEIVED A NEW CLAMP PLATE FOR PANEL 540 FB P/N A5735005700000, PO 613410.1. PANEL TO BE INSTALLED ON FEDEX WORK CARD 45C0529.

Part: SPOILER — CHAFED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING SPOILER NR 5 TRAILING EDGE IS KNIFE EDGES. REMOVED DAMAGED TRAILING EDGE IAW A310 SRM 51-40-02. LOCATED; DRILLED; DEBURRED AND INSTALLED NEW TRAILING EDGE P/N A5777020920400 IAW A310 SRM 51-40-02.

Part: SPOILER — CHAFED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING NR 7 SPOILER TRAILING EDGE IS KNIFED EDGED. REMOVED DAMAGED RIGHT WING SPOILER TRAILING EDGE SEAL AND REPLACED WITH A NEW SEAL P/N A5777020920400, PO 612493-3 BOTH IAW FEDEX A310-200 SRM 51-40-21; PG 11-24. PRIMED AND TOP COAT PAINTED BOTH IAW FEDEX A310-200; SRM 51-23-10.

Part: PANEL — CORRODED (LT WING) · airframe 36,499 hrs · 24,558 cycles

LEFT WING FUEL PANEL 550 HB HAS FRETTING CORROSION AROUND THE ATTACHMENT HOLES. PANEL FOUND TO BE OUT OF LIMITS REF A310-200 SRM 57-20-16, FOR INSTALLATION OF THE NEW PANEL SEE FEDEX WIC 45X5052ALI.

Part: PANEL — GOUGED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING FUEL PANEL 650KB HAS GOUGING ON THE UNDERSIDE. PANEL FOUND TO BE OUT OF LIMITS REF A310-200 SRM 57-20-16. FOR THE INSTALLATION OF THE PANEL SEE FEDEX WIC 46X5042ALI.

Part: PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

RIGHT WING FUEL PANEL 650 HB HAS FRETTING CORROSION AROUND THE ATTACHMENT HOLES. PANEL FOUND TO BE OUT OF LIMITS REF A310-200 SRM 57-50-16. FOR INSTALLATION SEE FEDEX WIC 46X5042 ALI.

Part: PANEL — CORRODED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING FUEL PANEL 650LB HAS FITTING CORROSION ON THE INNER BOLT HOLES. FUEL PANEL WAS FOUND TO BE OUT OF LIMITS REF A310-200 SRM 57-20-16; FIG 103; SHEET 4, TO BE INSTALLED ON FEDEX WIC 46X5042ALI.

Part: PANEL — CORRODED (ZONE 600) · airframe 36,499 hrs · 24,558 cycles

RIGHT FUEL TANK PANEL 640 FB HAS FRETTING CORROSION ON OUTER PANEL MATING SURFACES. FUEL PANEL IS OUT OF LIMITS REF A310-200 SRM 57-20-16; FIG 103; SHEET 4. REPLACED FUEL PANEL TO BE INSTALLED ON FEDEX WIC 46X5052ALI.

Part: WEB — CORRODED (CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

FWD LOWER CARGO COMPARTMENT/CORROSION ON WEB BETWEEN FRAMES 34 AND 35 RT UNDER ROLLER TRACK AT RBL 56 ABOVE STRINGER 44. REPLACED IAW SRM 51-72-10.

Part: WEB — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

FWD LOWER CARGO COMPARTMENT/CORROSION ON WEB BETWEEN FRAMES 34 AND 35 RT UNDER ROLLER TRACK AT RBL 56 ABOVE STRINGER 44. WEB AT FRAME 34-35 RT REPLACED IAW SRM 51-72-10. DWG. 14A53778329 ISSUE N & SRM 53-14-18.

Part: FAIRING — DELAMINATED (ZONE 300) · airframe 36,499 hrs · 24,558 cycles

LT HORIZONTAL STABILIZER FWD APRON IS TORN. REPLACED NEW APRON FAIRING ON N00181.

Part: PANEL — CHAFED (LT WING) · airframe 36,499 hrs · 24,558 cycles

LT WING T/E NR 572 BB HAS CHAFING; BARE METAL AND PEELING PAINT ON THE INNER SURFACE. REMOVED DAMAGED AREA, FABRICATED FILLER PLATE & DOUBLER. LAID UP REPAIR,CURED, PLACED A BEAD OF SEALANT AROUND DOUBLER. INSTALLED NEW GROMMET, PRIMED PANEL & APPLIED FINISH COAT. IAW SRM 51-77-12,51-77-10, 51-35-00, & 51-75-10.

Part: PANEL — CRACKED (ZONE 500) · airframe 36,499 hrs · 24,558 cycles

LT WING PANEL 524 AB IS CRACKED. REMOVED PANEL. REPAIRED BY REMOVING THE PREVIOUS REPAIR. APPLYING A FIBERGLASS WET LAY UP APPLYING NEW ALUMINUM FOIL & REFINISHING IAW SRM 51-40-21 PARA 5.

Part: PANEL — CORRODED (NR 2 PYLON) · airframe 36,499 hrs · 24,558 cycles

NR 2 PYLON PANEL NR 423 EL IS CORRODED ON THE MATING SURFACES. RECEIVED NEW PANEL. INSTALLED NEW EDGE STRIPS TO THE PANEL REF SRM 51-40-21 PARA 6.

Part: PANEL — ERODED (LT WING) · airframe 36,499 hrs · 24,558 cycles

LEFT WING LOWER SURFACE L/E DROP PANEL (RIB 28) EXTERNAL SURFACE HAS AN ERODED AREA. REPAIRED LT WING LOWER SURFACE L/E DROP PANEL BY REMOVING DAMAGE, APPLING FOIL REPAIR, ALODINING FOIL REPAIR, APPLING FR PRIMER, AND APPLING FINISH COAT IAW SRM 57-41-12,51-21-00, & 51-75-10.

Part: SKIN — GOUGED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

BULK PIT DOOR CUTOUT, FWD LWR AREA, GOUGED. COMPLIED WITH EA 6-5310-118471 PT 1

Part: FITTING — CORRODED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

AVIONICS COMPARTMENT STRINGER 44L END FITTING IS CORRODED FWD OF FR 17. FITTING REMOVED IAW SRM 51-40-21. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL MAT 0.067. MAT REMOVED 0.014. MAT REMAINING 0.053. OUT OF LIMITS IAW SRM 53-10-00 & DWG A53610607. REMOVED FITTING, RECEIVED NEW FITTING, LOCATED, DRILLED & INSTALLED NEW FITTING IAW SRM 51-40-21, 51-40-44 & TORQUED BOLTS TO 150 IN LBS IAW SRM 51-49-00. INSTALLED EDGING IAW SRM 51-40-21. APPLIED CIC IAW AMM 51-22-00-0.

Part: SKIN — CORRODED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

AVIONICS COMPARTMENT FUSELAGE INTERIOR SKIN IS CORRODED FWD OF FRAME 17; OUTBD OF STRINGER 44L. REMOVED CORROSION IAW SRM 51-74-10. MEASURED MATERIAL THICKNESS. REMAINING MATERIAL THICKNESS 0.197. SHOWED TO BE 0.1968 / - 1MM IAW DWG A53610567. FOUND TO BE WITHIN LIMITS. RFTS GENERATED; NO. N425FE-26-32-569. ALODINED AREA IAW SRM 51-21-10. PRIMED & PAINTED AREA IAW SRM 51-23-10. RESTORED CIC COATING IAW AMM 51-23-20-0.

Part: PANEL — TORN (ZONE 600) · airframe 36,499 hrs · 24,558 cycles

RT WING L/E LOWER SURFACE PANEL 623 LB SPEED TAPE IS PEELING OFF AND TORN. REMOVED DAMAGED FOIL IAW SRM 57-41-12. APPLIED NEW FOIL IAW SRM 51-75-12. PRIMED IAW SRM 57-41-12.

Part: ACCESS PANEL — CHAFED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RT WING L/E LOWER SURFACE ACCESS PANEL 623 GB EDGES IS CHAFED AND HAS 3 WEAK SPOTS. BLENDED CHAFED AREA IAW SRM 51-73-10. ORIGINAL THICKNESS 0.056. REMAINING THICKNESS 0.054 IAW A57243224 DWG. FOUND TO BE WITHIN LIMITS. ALODINED IAW SRM 51-21-01. PRIMED IAW SRM 51-23-01. RESTORED CIC IAW AMM 51-22-00.

Part: PANEL — DAMAGED (ZONE 600) · airframe 36,499 hrs · 24,558 cycles

RT WING L/E LOWER SURFACE ACCESS PANEL 623 JB UPPER SURFACE SPEED TAPE IS PEELING OFF AND TORN. REMOVED DAMAGED IAW SRM 57-41-12. APPLIED NEW FOIL IAW SRM 57-41-12. APPLIED SURFACE FINISH IAW SRM 57-41-12 PG 227.

Part: PANEL — TORN (ZONE 600) · airframe 36,499 hrs · 24,558 cycles

RT WING L/E LOWER SURFACE PANEL 623 EB SPEED TAPE IS PEELING OFF AND TORN. REMOVED DAMAGED FOIL IAW SRM 57-41-12. APPLIED NEW FOIL IAW SRM 57-41-12. PRIMED IAW SRM 51-23-10.

Part: PANEL — CORRODED (LT WING) · airframe 36,499 hrs · 24,558 cycles

LT WING T/E PANEL NR 572 DB IS CHAFED AND CORRODED WITH PAINT PEELING ON THE MATING SURFACES. REPAIRED PANEL BY REMOVING DAMAGE, FABRICATING FILLER PLATE AND DOUBLER, LAYING UP REPAIR DOUBLER AND FILLER PLATE & COMPLETING CURE & REMOVING EXCESS ADHESIVE FLASH, APPLING SEALANT TO REPAIR DOUBLER EDGES & CURING, APPLING FE PRIMER AND APPLING FINISH COAT IAW SRM 51-77-12, 51-77-10, 51- 35-00, AND 51-75-10.

Part: PANEL — TORN (ZONE 600) · airframe 36,499 hrs · 24,558 cycles

RT WING L/E LOWER SURFACE PANEL 623 FB SPEED TAPE IS PEELING OFF AND TORN. REMOVED DAMAGED FOIL IAW SRM 51-75-10. APPLIED NEW FOIL IAW SRM 57-41-12. PRIMED IAW SRM 57-41-12.

Part: PANEL — TORN (ZONE 600) · airframe 36,499 hrs · 24,558 cycles

RT WING L/E LOWER SURFACE PANEL 623 MB SPEED TAPE IS PEELING OFF AND TORN. REMOVED DAMAGED FOIL IAW SRM 57-41-12. APPLIED NEW FOIL IAW SRM 57-41-12. APPLIED SURFACE FINISH IAW SRM 51-75-10.

Part: SHEAR PLATE — CRACKED (ZONE 200) · airframe 36,499 hrs · 24,558 cycles

MAIN CABIN INTERCOSTAL WEB IS CRACKED AT FRAME 79 AND STRINGER 26R. REMOVED FLOOR PANEL 262 AH IAW SRM 51-40-21 PARA 5. REMOVED SHEAR PLATE IAW SRM 51-40-21 PARA 7. LOCATED & DRILL NEW SHEAR PLATE IAW SRM 51-40-40. INSTALLED SHEAR PLATE REF SRM 51-40-21 PARA 7. INSTALLED FLOOR PANEL 262 AH REF SRM 51-40-21 PARA 5. RESTORED CIC TO NEW SHEAR PLATE REF AMM 51-22-00-0.

Part: FLAP TRACK — WORN (TE FLAPS) · airframe 36,499 hrs · 24,558 cycles

RIGHT FLAP VANE TRACK NR 2 IS WORN. REPAIRED RIGHT WING NR 2 FLAP VANE TRACK IAW AIRBUS CMM 57-25-15.

Part: FRAME — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT FRAME 69 HAS CORROSION ON THE UP RIGHT DAM ABOVE STR 55 LEFT. REMOVED CORROSION IAW SRM 51-74-10; CHECKED LIMITS IAW SRM 51-74-10. FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. REMOVED DAMAGED PARTS IAW SRM 51-40-21. RECIEVED NEW PART (WEB). LOCATED AND DRILLED NEW PART IAW SRM 51-40-44; INSTALLED IAW SRM 51-40-21.

Part: MOUNT — CORRODED (NR 2 ENGINE) · airframe 36,499 hrs · 24,558 cycles

NR 2 ENGINE UPPER INBD FWD MOUNT BEAM IS GOUGED IN AREAS. BLENDED DAMAGED AREA REF A310 SRM 51-72-10. ORIGINAL THICKNESS WAS .320. REMOVED .010; REMAINING THICKNESS .310. WITHIN LIMITS REF A310 SRM 54-51-81. CAD PLATED REF A310 SRM 51-21-10. PRIMED REF A310 SRM 54-51-81. MINOR REPAIR.

Part: FITTING — DAMAGED (RUDDER) · airframe 36,499 hrs · 24,558 cycles

RUDDER; LEFT SIDE LEADING EDGE; BR 4 UPPER HINGE BLOCK REPAIR AREA HAS 1 EACH MISSED DRILLED HOLE. COMPLIED WITH EA 65540-118461.

Part: FLAP TRACK — WORN (TE FLAPS) · airframe 36,499 hrs · 24,558 cycles

LT FLAP VANE NR5 TRACK HAS WORN AREAS MARKED. REPAIRED NR 5 L/W FLAP VANE TRACK IAW AIRBUS CMM 57-52-15.

Part: ACOUSTIC PANEL — DELAMINATED (THRUST REVERSER) · airframe 36,499 hrs · 24,558 cycles

DELAMINATION ON THE NR 2 ENGINE LEFT LOWER ACOUSTIC PANEL. REMOVED DAMAGE, APPLIED & CURED REPAIR. RESTORED FINISH IAW ENGINE MANUAL 78-32-02.

Part: FLAP TRACK — WORN (TE FLAPS) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING INBD FLAP VANE MID TRACK INBD SIDE HAS WORN AREA. REPAIRED NR 3 R/W FLAP VANE TRACK IAW AIRBUS CMM 57-52-15.

Part: FLAP TRACK — WORN (TE FLAPS) · airframe 36,499 hrs · 24,558 cycles

RIGHT FLAP VANE TRACK IS WORN, NR 5 TRACK. REPAIRED RIGHT WING NR 5 FLAP VANE TRACK IAW AIRBUS CMM 57-52-15.

Part: PANEL — CORRODED (LT ELEVATOR) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

LT ELEVATOR PANEL NR 335 CT IS CORRODED. REMOVED CORROSION IAW A310 SRM 51-74-10. ORIGINAL MATERIAL THICKNESS 0.080 IAW AIRBUS DWG 38; A55276950. REMOVED 0.001; REMAINING MATERIAL 0.079. FOUND TO BE WITHIN LIMITS IAW A310 SRM 55-22-00; TABLE 101. UT GAUGE NR T8225Q; CAL DATE 21/20/07. ALODINED IAW A310 SRM 51-21-10. PRIMED AND TOP COATED IAW A310 SRM 51-23-10.

Part: FLAP TRACK — WORN (NR 1 FLAP) · airframe 36,499 hrs · 24,558 cycles

LT FLAP VANE NR 1 TRACK HAS WORN AREAS MARKED. REPAIRED NR 1 FLAP VANE TRACK IAW AIRBUS CMM 57-52-15.

Part: FLAP TRACK — WORN (TE FLAP) · airframe 36,499 hrs · 24,558 cycles

LT FLAP VANE NR 4 TRACK HAS WORN AREAS MARKED. REPAIRED L/W NR 4 FLAP VANE TRACK IAW AIRBUS CMM 57-52-15.

Part: FLAP TRACK — WORN (TE FLAPS) · airframe 36,499 hrs · 24,558 cycles

LT FLAP VANE NR 2 TRACK HAS WORN AREAS MARKED REPAIRED NR 2 FLAP VANE TRACK IAW AIRBUS CMM 57-52-15.

Part: MOUNT — CORRODED (NR 2 ENGINE) · airframe 36,499 hrs · 24,558 cycles

NR 2 PYLON FWD ENGINE MOUNT HOLES HAVE CORROSION. REMOVED CORROSION REF SRM 51-74-10. AFT INBD HOLE SIZE IS 0.825. ALL REMAINING HOLES ARE 0.809. WITHIN LIMITS REF SRM 54-51-81; CADMIUM PLATED REF A310 SRM 51-21-10. PRIMED AREA REF SRM 54-51-81. MINOR REPAIR

Part: FLAP TRACK — WORN (TE FLAP) · airframe 36,499 hrs · 24,558 cycles

LEFT FLAP VANE NR 3 TRACK HAS WORN AREAS (MARKED). REPAIRED LEFT FLAP VANE NR 3 TRACK IAW AIRBUS CMM 57-52-15.

Part: FLAP TRACK — WORN (TE FLAP) · airframe 36,499 hrs · 24,558 cycles

RIGHT FLAP VANE TRACK NR 1 IS WORN. RECEIVED NEW TRACK FOR INSTALLATION; SEE FEDEX JOB CARD 46S5181CP. OLD TRACK IS OUT OF LIMITS. MAX LIMIT 0.0315; MEASURED 0.065.

Part: SKIN — DELAMINATED (NR 2 COWLING) · airframe 36,499 hrs · 24,558 cycles

NR 2 ENGINE OUTBD FAN COWL IS DELAMINATED AT THE EXTERIOR CENTER SECTION, 18 INCHES FROM THE T/E. ABRADED SURFACE & REPAIRED IAW SRM 54-10-00 FIG 1 & RDN 54-20-00 REPAIR 1 & 2.

Part: FLAP TRACK — WORN (TE FLAPS) · airframe 36,499 hrs · 24,558 cycles

RIGHT FLAP VANE TRACK NR 4 IS WORN REPAIRED R/W NR 4 FLAP VANE TRACK IAW AIRBUS CMM 57-52-15.

Part: FAIRING — ERODED (TE FLAP) · airframe 36,499 hrs · 24,558 cycles

FWD FLAP FAIRING 634 AB/BB; FWD END IS ERODED. REPAIRED ERROSION BY REMOVING THE DAMAGE AND APPLIED A WET LAY UP IAW A310 SRM 57-20-35.

Part: FAIRING — DENTED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RT WING FAIRING 634 AT IS DENTED AND DELAMINATED. REPAIRED IAW SRM 57-20-35.

Part: PANEL — DELAMINATED (INTERIOR) · airframe 36,499 hrs · 24,558 cycles

AFT PIT CEILING PANEL 162 AB OUTER SURFACE IS DELAMINATED AND CRACKED; THE INNER SURFACE HAS PUNCTURED AREAS. REPAIRED CEILING PANEL 162 AB FOR THE AFT PIT IAW DWG SRZ 25-013 AND PAINTED (WHITE).

Part: PANEL — CHAFED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING PANEL NR 672 CB UPPER SKIN IS CHAFED. REPAIRED IAW SRM 51-77-10 & BONDED IT IAW SRM 51-77-12. REFINISHED AREA IAW SRM 51-75-10.

Part: FAIRING — PUNCTURED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

PUNCTURE ON THE INTERIOR SURFACE OF PANEL NR 144FR. REPAIRED INTEROR SURFACE OF PANEL 144 FR BY REMOVING THE DAMAGE. CLEANED & PREPPED FOR APPLICATION OF THE WET LAY UP. APPLIED, CURED & SANDED THE WET LAY UP. CLEANED & PREPPED FOR THE APPLICATION OF THE REFINISH. APPLIED THE REFINISH IAW SRM 51-77-10 & SRM 51-75-10.

Part: PANEL — DELAMINATED (LT WING) · airframe 36,499 hrs · 24,558 cycles

LEFT WING PANEL 577 BT IS DELAMINATED IN NUMEROUS PLACES. REMOVED DAMAGED; PREPED FOR BOND, LAYED UP, VAC BAGGED & CURED REPAIR IAW SRM 51-77-12 & 51-77-10. RESTORED PROTECTIVE FINISH IAW SRM 51-75-10.

Part: STRUCTURE — DEBONDED (NR 1 SPOILER) · airframe 36,499 hrs · 24,558 cycles

LT WING NR 1 SPOILER INBD FWD CORNER IS DISBONDED. REPAIRED NR 1 SPOILER AT THE INBD FWD CORNER BY APPLYING REPAIR PLIES IAW SRM 51-77-11 PARA 3E; FIGURE 208.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

FWD PIT HAS CORROSION ON THE BOTTOM OF THE FLOORBEAM AT FRAME 37; LBL 103CM (40.5). REMOVED CORROSION FROM THE BOTTOM OF FLOORBEAM 37; Y 1000 TO 1030 IAW SRM 51-74-10; PG 210. ORIGINAL THICKNESS .126 IAW SRM 53-14-15; PG 9 AND DRAWING A53779635. MATERIAL REMOVED .054. OUT OF LIMITS IAW SRM 53-10-15. INSTALLED REQUIRED REPAIR IAW SRM 53-10-15; FIG 206.

Part: PANEL — CHAFED (NR 2 NACELLE) · airframe 36,499 hrs · 24,558 cycles

NR 2 PYLON PANEL NR 423 BL IS CHAFED ON THE MATING SURFACES. BLENDED CHAFED AREAS IAW SRM 54-52-51; ITEM 4; PG 102. ORIGINAL MATERIAL THICKNESS IS .079 IAW SRM 54-52-51; FIG 4; SHEET 2. REMOVED .031; REMAINING MATERIAL THICKNESS IS .048. FOUND TO BE OUT OF LIMITS IAW SRM 54-52-51; DIAGRAM 101. FABBED DOUBLER IAW SRM 54-52-51; FIG 202. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-23-10. INSTALLED DOUBLER IAW SRM 54-52-51; FIG 202. TOP COATED IAW SRM 51-23-10.

Part: PANEL — DAMAGED (ZONE 500) · airframe 36,499 hrs · 24,558 cycles

LEFT WING PANEL (WS 66-151) FOIL ON THE BACK OF THE PANEL IS PEELING OFF AND THE PANEL IS PUNCTURED. REPAIRED LT WING PANEL WS 66-151, BY APPLYING REPAIR PLIES IAW SRM 51-77-10 & 51-77-12. REMOVED DAMAGED FOIL IAW SRM 57-42-12. APPLIED NEW FOIL IAW SRM 57-41-12. APPLIED SURFACE FINISH IAW SRM 51-75-10, PRIMED IAW SRM 57-41-12.

Part: SKIN — DELAMINATED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

DELAMINATION ON PANEL NR 143 FL; INTERIOR SKIN. REPAIRED IAW SRM 51-77-10 & 51-75-10.

Part: FAIRING — ERODED (TE FLAP) · airframe 36,499 hrs · 24,558 cycles

NR 5 RT WING FLAP FAIRING HAS NUMEROUS SPOTS OF EROSION AND CHIPPED PAINT. PAINTED IAW AMM 51-75-10-8.

Part: ATTACH FITTING — GOUGED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING SKIN ABOVE THE PYLON OUTBD ATTACH FITTING IS GOUGED. REPAIRED AREA IAW EA 6-5730-118443.

Part: RAIL — BENT (CARGO TRAY) · airframe 36,499 hrs · 24,558 cycles

FWD CARGO COMPARTMENT; ROLLER TRAY SIDE RAIL IS BENT; BY CARGO DOOR OPENING JUST ABOVE DOOR SPOOL NR 3. ROLLER TRAY FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00 REMOVED AND REPLACED IAW AMM 25-52-21-4 PARA 2B & 2D. FABBED IAW DWG. A25771256. ALODINED IAW SRM 51-21-10. PRIMED & PAINTED IAW SRM 51-23-10.

Part: FAIRING — DENTED (TE FLAPS) · airframe 36,499 hrs · 24,558 cycles

FWD FLAP FAIRING 634 AB/BB LOWER AFT END IS DENTED. REPAIRED DENT BY REMOVING THE DAMAGE AND APPLYING A WET LAY UP.

Part: PANEL — DAMAGED (INTERIOR) · airframe 36,499 hrs · 24,558 cycles

AFT PIT CEILING PANEL 162 DC HAS EXPOSED COMPOSITE CORE AND IS CRUSHED. REPAIRED AFT PIT CEILING BY APPLYING A FIBERGLASS OVERALL IAW SRZ 25-013 & RESTORED THE FINISH IAW SRZ 25-013.

Part: STRUCTURE — CHAFED (NR 4 SPOILER) · airframe 36,499 hrs · 24,558 cycles

RT WING NR 4 SPOILER; OUTBD EDGE IS CHAFED AND WORN. NO DAMAGE NOTED TO INDER LYING CFRP STRUCTURE AT THE OUTBOARD END OF THE RT WING NR 4 SPOILER IAW SRM 57-70-00 & 51-10-10. APPLIED SURFACE PROTECTION IAW SRM 51-75-10. MINOR REPAIR.

Part: BEARING — CORRODED (RUDDER HINGE) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

RUDDER HINGE ARM; NR 5 BEARINGS ARE CORRODED. REMOVED 2 BEARING ASSEMBLIES. CLEANED AND INSPECTED HINGE ARM. REPLACED BEARING ASSEMBLIES IAW FEDEX A310-200 AM 53-36-11-08 P/N FOR ALL OF THE BEARING THAT WERE REPLACED ARE AS FOLLOWS; NSA 5100-006C; NSA 8130-08.

Part: SKIN — DEBONDED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RT WING UPPER L/E SKIN PANEL AT STA WQFS 66-151 LINER FOIL IS DISBONDED AND TORN. REMOVED & REPLACED DAMAGED FOIL IAW SRM 57-41-12.

Part: SKIN — CHAFED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING INBD SLAT; INBD OF NR 1 TRACK; INNER SURFACE FASTENERS ARE CHAFING ON THE WING L/E SKIN. BLENDED AREA SMOOTH & REMOVED DAMAGE IAW SRM 51-73-10. FOUND TO BE OUT OF LMITS IAW SRM 57-40-00. DAMAGED SECTION OF THE L/E SKIN IAW SRM 57-41-12. HEAT TREATED NEW FORMED L/E SKIN. FABBED, LOCATED & DRILLED NEW SKIN & 1 REPAIR BUTT STRAP IAW SRM 57-41-12 FIG 203 & 51-40-44. ALODINED REPAIR PARTS IAW SRM 51-21-10. PRIMED & TOP COAT PAINTED IAW SRM 5-23-10. INSTALLED NEW SKIN SECTION & REPAIR BUTT STRAP IAW SRM 51-41-12.

Part: BEARING — CORRODED (RUDDER HINGE) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

RUDDER HINGE ARM NR 6; RUDDER BEARINGS ARE CORRODED. REMOVED 3 BEARING ASSEMBLIES. CLEANED AND INSPECTED HINGE ARM. REPLACED BEARING ASSEMBLIES IAW A310 200 AMM 53-36-11-08, P/N OF THE BEARING ASSEMBLIES ARE AS FOLLOWS, NSA5100-006C; NSA 8130-08 AND A5537014020000.

Part: PANEL — DAMAGED (ZONE 600) · airframe 36,499 hrs · 24,558 cycles

RIGHT WING L/E PANEL UPPER SURFACE; APPROX RIB 14 HAS THE PROTECTIVE METAL TAPE LOOSE AND PAINT PEELING. REMOVED DAMAGED FOIL IAW SRM 57-41-12. APPLIED NEW FOIL IAW SRM 57-41-12. APPLIED PROTECTIVE FINISH IAW A310 SRM 51-75-10. PRIMED IAW SRM 57-41-12.

Part: PANEL — CORRODED (NR 1 NACELLE) · airframe 36,499 hrs · 24,558 cycles

NR 1 PYLON PANEL NR 414 GR IS CORRODED AROUND THE SCREW HOLES. REMOVED THE CORROSION IAW SRM 51-74-10. ORIGINAL MAT THICKNESS .079 IAW SRM 54-52-51; PG 12. REMOVED .059; .020 MAT REMAINING. OUT OF LIMITS IAW SRM 54-52-51; FIG 101. FABBED FILLER/DOUBLER AND REMOVED DAMAGE IAW SRM 54-52-51; FIG 203. ALODINED FILLER/DOUBLER IAW SRM 51-21-10. PRIMED FILLER/DOUBLER IAW SRM 51-23-10. PAINTED FILLER/DOUBLER IAW SRM 51-23-10. INSTALLED FILLER/DOUBLER IAW SRM 54-52-51;FIG 203.

Part: DOUBLER — CORRODED · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

FWD LOWER CARGO PIT BILGE DOUBLER IS CORRODED BETWEEN STR 51L AND STR 52 L.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT IF THE BULK PIT FROM FRAME 78 TO FRAME 79; STRINGER 50R TO STRINGER 51R INTERIOR SURFACE HAS CORROSION. R&R DOUBLER LAV SERVICE DOOR; S50R & DRAIN MAST IAW 51-40-21 & AMM 30-71-11-4. REMOVED & REINSTALLED S45R; 47R; 48R FROM FRAMES 75-82& PAN IAW SRM 51-40-21. REMOVED CORROSION FROM DOUBLER & FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. ORIG MAT 0.098; REMAINING MAT 0.054; REMAINING MAT 0.044. REMOVED CORROSION FROM S50R & FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. ORIG MAT .039; REMAINING MAT 0.000; REMOVED MAT 0.039. FABBED DOUBLER S50R IAW DWG A5398067 & A53980908. TREATED IAW SRM 51-21-10 & 51-23-10.

Part: PANEL — CHAFED (NR 1 NACELLE) · airframe 36,499 hrs · 24,558 cycles

NR 1 PYLON PANEL NR 414BR HAS 2 CORNERS CHAFED. BLENDED CHAFED AREA IAW SRM 54-52-51; FIG 101. FOUND TO BE OUT OF LIMITS IAW SRM 54-52-51; FIG 101. FABBED DOUBLER IAW SRM 54-52-51; FIG 202. ALODINED IAW SRM 51-21-10 AND PRIMED IAW 54-52-51; FIG 51-23-10. INSTALLED DOUBLER IAW SRM 54-52-51; FIG 202. TOP COATED AREA IAW SRM. MINOR REPAIR.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

LT SIDE FUSELAGE SKIN IS CORRODED AROUND THE WING TO FUSELAGE FAIRING NUT PLATES AT 3 PLACES BETWEEN FRAMES 45 AND 46. REMOVED DOME NUTS AND REPLACED DOME NUTS PER FEDEX A310-200 SRM 51-40-21; PARAGRAPH 6. REMOVED CORROSION PER FEDEX A310-200 SRM 51-73-12. CHECKED LIMITS AND FOUND TO BE IN LIMITS PER FEDEX A310-200 SRM 53-15-12; FIG 1; SHEET 4 AND DIAGRAM 101. ORIGINAL MATERIAL .236, MATERIAL REMAINING .205 AT THE FWD SPOT; CENTER SPOT .224 AND THE AFT SPOT .217. MATERIAL LOSS AT THE FWD SPOT .031; THE CENTER SPOT .012 AND THE AFT SPOT .019. UT GAUGE USED T8225Q. ALODINED; PRIMED AND PAINTED PER FEDEX A310-200 AMM 51-23-10.

Part: SEAT TRACK — UNKNOWN (ZONE 200) · airframe 36,499 hrs · 24,558 cycles

CENTER ARTICULATING SEAT TRACK BETWEEN FRAME 38.2 AND FRAME 40. REMOVED DAMAGED SEAT TRACK IAW SRM 51-40-21 PARA. 6. INSTALLED NEW SEAT TRACK IAW EO E-6-5310-7-3322 PT 2.

Part: LONGERON — CHAFED (NR 2 PYLON) · airframe 36,499 hrs · 24,558 cycles

NR 2 ENGINE PYLON AFT FAIRING; OUTBD UPPER LONGERON IS CHAFFED AT SEVERAL SCREW HOLES. REMOVED DAMAGED LONGERON IAW A310-300 SRM 61-40-21; PG 7, RECEIVED LONGERON P/N 221-0081-328, PO 610555.3 AND LOCATED HOLES IAW A310-300 SRM 51-40-40. INSTALLED LONGERON IAW A310-300 SRM 51-40-21; PARAGRAPH 6.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

FOUND FLOOR PANEL P/N 35039003 HAS EDGE DAMAGE. REPAIRED FLOOR PANEL 132 YF I.A.W. FEDEX DWG. SRZ-25-00 REV. E.

Part: FLOOR PANEL — DAMAGED (AFT CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

AFT CARGO PIT FLOOR PANEL 151FF HAS CORNER DAMAGE. FABRICATED NEW FLOOR PANEL. POTTED EDGES. COMPLETED CURE & SANDED EDGE POTTING. INSTALLED INSERTS & APPLIED NON-SKID IAW DWG SRZ 25-005; REV F.

Part: WEDGE — CRACKED (RT AILERON) · airframe 36,499 hrs · 24,558 cycles

RT OUTBD AILERON T/E WEDGE IS CRACKED AND THE AFT EDGE IS SEPARATED. THIS SDR WAS OPENED FOR AIRCRAFT N425FE INSTEAD OF AIRCRAFT N365FE IN ERROR. SDR 08-0895 HAS BEEN INITIATED TO ADDRESS THE DISCREPANCY DOCUMENTED ON NON-ROUTINE N00026 THAT WAS WRITTEN AGAINST AIRCRAFT N365FE.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

FLOOR PANEL 152YF HAS EDGE DAMAGE AND IS DENTED. FABRICATED NEW FLOOR PANEL. POTTED EDGES, COMPLETED CURE & SANDED EDGE POTTING. INSTALLED INSERTS & APPLIED NON-SKID IAW DWG SRZ 25-005; REV F.

Part: FRAME — CRACKED (NACELLE) · airframe 36,499 hrs · 24,558 cycles

NR 2 STRINGER PANEL 485AL HAS A CRACKED FRAME ON THE LT SIDE AT FWD MID SKIN. REMOVED CRACKED FRAME; RECEIVED NEW FRAME P/N 221-0081-181; PO 611742.3. LOCATED HOLES IAW SRM 51-40-40 AND INSTALLED IAW SRM 51-40-31 PARA 6. MINOR REPAIR.

Part: FAIRING — DELAMINATED (HORIZ STAB) · airframe 36,499 hrs · 24,558 cycles

RT HORIZONTAL STABILIZER LOWER APRON FAIRING IS DELAMINATED. REAPPLIED ADHESIVE PER SRM 55-15-11; PARAGRAPHS (H) & (I) TO DISBONDED SILICONE MATERIAL.

Part: LONGERON — CHAFED (NR 2 PYLON) · airframe 36,499 hrs · 24,558 cycles

NR 2 ENGINE PYLON AFT FAIRING; OUTBD UPPER LONGERON IS CHAFED AT SEVERAL SCREW HOLES. REMOVED DAMAGED LONGERON IAW A310-300 SRM 61-40-21; PG 7. RECEIVED LONGERON P/N 221-0081-328, PO 610555.3 AND LOCATED HOLES IAW A310-300 SRM 51-40-40. INSTALLED LONGERON IAW A310-300 SRM 51-40-21; PARAGRAPH 6.

Part: FLOOR PANEL — DELAMINATED (FWD CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

FWD CARGO PIT FLOOR PANEL 132GF HAS EDGE DAMAGE AND IS DELAMINATED. FABRICATED NEW FLOOR PANEL. LOCATED HOLES, POTTED EDGES, CURED EDGE POTTING. INSTALLED INSERTS & APPLIED NON-SKID IAW DWG SRZ 25-005; REV F.

Part: PANEL — DAMAGED (FWD CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

FWD CARGO PIT CEILING PANEL 132GC HAS EXPOSED CORE ON BOTH SIDES OF THE PANEL. REPAIRED PANEL & APPLIED PAINT (WHITE) ON FWD PIT CEILING IAW DRAWING SRZ 25-013.

Part: FLOOR PANEL — DELAMINATED (FWD CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

FWD CARGO PIT FLOOR PANEL 131RF IS DELAMINATED IN 5 AREAS. FABBED NEW FLOOR PANEL. LOCATED HOLES, POTTED EDGES, CURED EDGE POTTING; INSTALLED INSERTS & APPLIED NON-SKID IAW DWG SRZ 25-005; REV F.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT LOWER SKIN HAS CORROSION AT STR 57; FRAMES 54 THRU 54.1. REMOVED FASTENERS IAW SRM 51-40-21. REMOVED CORROSION IAW SRM 51-74-10. CHECKED LIMITS IAW SRM 53-16-12. ORIG. MAT THICKNESS IS .177 REMAINING MAT. THICKNESS .174. REMOVED .003. FOUND TO BE WITHIN LIMITS IAW SRM 53-10-12 PG. 139. ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED IAW SRM 51-23-10. INSTALLED RIVETS IAW SRM 51-40-21.

Part: PANEL — DAMAGED (CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

BULK CARGO PIT PANEL NR 161JW IS PUNCTURED AND DELAMINATED. REPAIRED BULK CARGO PIT IAW DWG SRZ 25-013. PAINTED PANEL IAW DWG SRZ 25-013.

Part: FRAME — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT FUSELAGE FRAME HAS CORROSION ON THE WEB AT FRAME 64 BETWEEN STR 49L AND 50L. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL MATERIAL 0.045; MATERIAL REMOVED 0.017, MATERIAL REMAINING 0.028. FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. FORMED ANGLE, HEAT TREATED ANGLE IAW TPS 1003; REV A. DRILLED UP PARTS, ALODINED, PRIMED & TOP COATED PARTS IAW SRM 51-40-44, 51-21-10, & 51-23-10. INSTALLED PARTS IAW SRM 53-10-13. ALSO APPLIED TOP COAT ON PARTS IAW SRM 51-23-10.

Part: PANEL — PUNCTURED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

PUNCTURE ON THE INTERIOR SURFACE OF PANEL NR 144FR. REPAIRED INTERIOR SURFACE BY REMOVING THE DAMAGE. APPLIED, CURED & SANDED THE WET LAY UP. APPLIED REFINISH IAW SRM 51-77-10 & SRM 51-75-10.

Part: FRAME — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT FUSELAGE FRAME WEB HAD CORROSION AT FRAME 66 BETWEEN STR 49L AND STR 50L. REPAIRED FUSELAGE FRAME 66 BETWEEN STRINGER 49L & STRINGER 50L IAW SRM 53-10-10; PARA 4.

Part: SKIN — CORRODED (BS 3355) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

AFT PIT LOWER FUSELAGE SKIN IS CORRODED AT FRAME 62; S56R. REMOVED CORROSION IAW SRM 51-74-10; CHECKED LIMITS IAW SRM 53-17-12. FOUND TO BE WITHIN LIMITS IAW SRM 53-10-12. ALODINED IAW A310 SRM 51-21-10. PRIMED AND PAINTED BOTH IAW A310 SRM 51-23-10. MINOR REPAIR

Part: RUB STRIP — DEBONDED (T/E FLAP) · airframe 36,499 hrs · 24,558 cycles

LT OUTBD FLAP UPPER EXTERNAL SKIN HAS THE METAL CHAFE STRIP DISBONDED. REMOVED & REPLACED CHAFE STRIP IAW SRM 57-53-12 FIG 201.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT STR 56R HAS CORROSION ON THE LOWER ANGLE AT FRAME 69. REMOVED FASTENERS IAW SRM 51-40-21. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS 0.079. REMAININGMATERIAL 0.073. WITHIN LIMITS IAW SRM 53-10-00. ALODINED IAW SRM 51-21-00. PRIMED IAW SRM 51-23-00. INSTALLED FASTENERS IAW SRM 51-40-21.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT CARGO PIT; FWD BULKHEAD AT FRAME 54; THE CEILING ATTACH ANGLE IS CORRODED FROM 131 TO 139 CM (51.5" TO 54.5 "). REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL MATERIAL THICKNESS .098. REMAINING LATERIAL .050. MATERIAL REMOVED .048. OUT OF LIMITS IAW SRM 53-10-00. REMOVED ANGLE IAW SRM 51-40-21. FABBED NEW ANGLE IAW DWG A53410767. ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED IAW SRM 51-23-10. PART MARKED IAW GMM 7-0-1001. INSTALLED ANGLE IAW SRM 51-40-21. MINOR REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

FLOOR PANEL 147BF UPPER LAYERS ARE DETERIORATED IN NUMEROUS PLACES. FABRICATED NEW FLOOR PANEL 147 BF; POTTED EDGES; COMPLETED CURE & SANDED EDGE POTTING. INSTALLED INSERTS & APPLIED NON-SKID IAW SRZ 25-005; REV F.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

FLOOR PANEL PANEL 147 AF IS DELAMINATED AND OIL SATURATED. FABRICATED NEW FLOOR PANEL. LOCATED HOLES, POTTED EDGES. CURED EDGE POTTING. INSTALLED INSERTS AND APPLIED NON-SKID IAW SRZ 25-005; REV F.

Part: PANEL — PUNCTURED (AFT CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

AFT CARGO PIT PANEL NR 152LW IS PUNCTURED. REPAIRED AFT PIT PANEL & TOP COATED (WHITE) IAW DWG SRZ 25-031.

Part: FLOOR PANEL — PEELING (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

MLG WHEEL WELL FLOOR PANEL 148BF UPPER LAYER IS PEELING. FABRICATED NEW FLOOR PANEL. LOCATED HOLES, POTTED EDGES. CURED EDGE POTTING. INSTALLED INSERTS AND APPLIED NON-SKID IAW SRZ 25-005; REV F.

Part: PANEL — DEBONDED (AFT CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

AFT CARGO PIT PANEL NR 151PW IS DISBONDED. REPAIRED PANEL & APPLIED TOP COAT WHITE IAW DRAWING SRZ 25-013.

Part: PANEL — DAMAGED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

AFT PIT CEILING PANEL 162AB OUTER SURFACE IS DELAMINATED AND CRACKED; THE INNER SURFACE HAS PUNCTURED AREAS. REPAIRED IAW DWG SRZ 25-013 & PAINTED.

Part: PANEL — CRACKED (RT WING) · airframe 36,499 hrs · 24,558 cycles

RT WING LOWER SKIN IS CRACKED IN THE TRAILING EDGE AREA AT WING STA 653, JUST INBD OF RIB 11. COMPLIED WITH EA 6-5730-118457 REV A.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT STRINGER 45R IS CORRODED BETWEEN FRAMES 54.2 AND 54.3. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS WAS 0.110. REMAINING MATERIAL 0.105. WITHIN LIMITS IAW SRM 53-10-00. ALODINED IAW SRM 51-21-00. PRIMED & PAINTED IAW SRM 51-23-00.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT LOWER FUSELAGE SKIN IS CORRODED AROUND THE DRAIN HOLE AREA AT STR 57 BETWEEN FRAMES 54.1 AND 54.2. REMOVED CORROSION IAW SRM 51-74-10. ORIG. MAT. THICKNESS IS .196 IAW DWG. A53970182. REMOVED .023. REMAINING MAT. OF .173 IS WITHIN LIMITS IAW SRM 53-10-00. ALODINED IAW SRM 51-21-10. PRIMED & PAINTED IAW SRM 51-23-10.

Part: FLOORBEAM — CORRODED (CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

CORROSION IS ON THE BOTTOM OF THE FLOORBEAM AT FRAME 47; LBL 103CM IN FWD PIT. FOUND TO BE OUT OF LIMITS IAW SRM 52-30-00. REMOVED EDGE MEMBER IAW SRM 51-40-21. REMOVED SEAL RETAINER IAW SRM 51-40-21. RECEIVED NEW EDGE MEMBER IAW SRM 52-31-00. FABBED DOUBLER AND FILLER IAW SRM 52-30-00. INSTALLED DOUBLER & FILLER IAW SRM 51-40-21. INSTALLED EDGE MEMBER & SEAL RETAINER IAW SRM 51-40-21.

Part: RUB STRIP — DAMAGED (T/E FLAP) · airframe 36,499 hrs · 24,558 cycles

LT OUTBD FLAP UPPER SURFACE CENTER CHAFE STRIP IS WRINKLED AND BULGING. REMOVED & REPLACED THE CHAFE STRIP IAW SRM 57-53-12; FIG 201.

Part: PANEL — DAMAGED (AFT CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

AFT CARGO PIT CEILING PANEL NR 152 DC IS DELAMINATED AND DENTED. RECEIVED NEW PANEL. TO BE INSTALLED ON CARD 41C0071.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT CARGO PIT; FWD BULKHEAD AT FRAME 54; THE CEILING PANEL ATTACH ANGLE IS CORRODED AT RBL 166 CM 65. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL MATERIAL THICKNESS .098. REMAINING MATERIAL .043. REMOVED .055, OUT OF LIMITS IAW SRM 53-10-00. REMOVED ANGLE IAW SRM 51-40-21. FABBED NEW ANGLE IAW DWG A53410767. ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED IAW SRM 51-23-10. PART MARKED IAW GMM 7-0-1001. INSTALLED ANGLE IAW SRM 51-40-21. MINOR REPAIR.

Part: SKIN — DELAMINATED (T/E FLAP) · airframe 36,499 hrs · 24,558 cycles

LT OUTBD FLAP AFT EDGE OF THE FLAP IS DELAMINATED ON THE UPPER SURFACE. PREPARED & RESEALED IAW SRM 57-53-12 FIG 209.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

AFT PIT FUSELAGE FRAME HAS CORROSION ON THE WEB AT FRAME 65 BETWEEN STR 49L AND 50L. REMOVED CORROSION IAW SRM 51-74-10. CHECKED LIMITS IAW SRM 53-17-12. FOUND TO BE WITHIN LIMITS. ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED BOTH IAW SRM 51-23-10. MINOR REPAIR.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT LOWER FUSELAGE STRINGER 51R HAS CORROSION IN THE AREA ON THE STRINGER BETWEEN FRAMES 60 AND 61. REMOVED CORROSION FROM STRINGER IAW SRM 51-74-10. ORIGINAL MATERIAL THICKNESS 0.110. MATERIAL REMOVED 0.013. REMAINING MATERIAL 0.097. FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. REMOVED STRINGER IAW SRM 53-10-10. FABBED REPAIR STRINGER & COUPLINGS IAW SRM 51-21-10. ALODINED REPAIR STRINGER & COUPLINGS IAW SRM 51-21-10. PRIMED & PAINTED REPAIR STRINGER & COUPLINGS IAW SRM 53-23-10. INSTALLED REPAIR STRINGER & COUPLINGS IAW SRM 53-10-14.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT STR 49R HAS CORROSION ON THE LOWER RADIUS 6" AFT OF FRAME 65. REMOVED CORROSION IAW SRM 51-74-10. REMOVED FASTENERS TO F.O.M. ORIGINAL MATERIAL THICKNESS 0.092. MATERIAL REMOVED 0.004. MATERIAL REMAINING 0.088. FOUND TO BE WITHIN LIMITS IAW SRM 53-10-00. ALODINED IAW SRM 51-21-10. PRIMED & PAINTED IAW SRM 51-23-10. INSTALLED FASTENERS IAW SRM 51-40-21.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 36,499 hrs · 24,558 cycles

AFT PIT FUSELAGE FRAME HAS CORROSION ON THE WEB AT FRAME 67 ABOVE S49L. REMOVED CORROSION IAW SRM 51-74-10. CHECKED LIMITS IAW SRM 53-17-13. FOUND TO BE WITHIN LIMITS; ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED BOTH IAW SRM 51-23-10. MINOR REPAIR

Part: PANEL — DAMAGED (AFT CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

AFT CARGO PIT PANEL NR 161MW IS DELAMINATED AND PUNCTURED. REPAIRED PANEL & APPLIED TOP COAT (WHITE) ON AFT CARGO PIT IAW DWG SRZ 25-013.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT CARGO PIT; FWD BULKHEAD AT FRAME 54; THE CEILING PANEL ATTACH ANGLE IS CORRODED FROM RBL 37 TO 48 CM (14" TO 18.5"). REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL MATERIAL THICKNESS .098. REMAINING MATERIAL .043. MATERIAL REMOVED .055. OUT OF LIMITS IAW SRM 53-10-00. REMOVED ANGLE IAW SRM 51-40-21. FABBED NEW ANGLE IAW DWG A53410767. ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED IAW SRM 51-23-10. PART MARKED ANGLE IAW GMM 7-0-1001. INSTALLED ANGLE IAW SRM 51-40-21. MINOR REPAIR.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT STRINGER 45R IS CORRODED WHERE IT PASSES UNDER FRAME 54.2. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS WAS 0.110. REMAINING MATERIAL 0.105. WITHIN LIMITS IAW SRM 53-10-00. ALODINED IAW SRM 51-21-10. PRIMED & PAINTED AREA IAE SRM 51-23-10.

Part: FRAME — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT FUSELAGE FRAME HAS CORROSION ON THE WEB BETWEEN STR 49L AND STR 50L, FRAME 65. REMOVED CORROSION IAW SRM 51-74-10. CHECKED LIMITS IAW SRM 53-17-13 & FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. FORMED IAW SRM 51-26-00. REPAIR PARTS HEAT TREATED. REPAIR PARTS LOCATED & DRILLED IAW SRM 51-40-44. ALODINED IAW SRM 51-21-10. PRIMED & TOPCOAT PAINT IAW SRM 51-23-10. INSTALLED IAW SRM 53-10-13 PAGE 205. MAJOR REPAIR.

Part: FRAME — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

AFT PIT FUSELAGE FRAME HAS CORROSION ON THE WEB AT FRAME 64 BETWEEN STR 49L AND 50L. REMOVED CORROSION IAW SRM 51-74-10. FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. FORMED ANGLE, HEAT TREATED ANGLE IAW TPS 1003; REV A. DRILLED UP PARTS; ALODINED, PRIMED & TOP CAOTED PARTS IAW SRM 51-40-44; 51-21-10 & 51-23-10. INSTALLED PARTS IAW SRM 53-10-13. ALSO APPLIED TOP COAT PN PARTS IAW SRM 51-23-10.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

RT SIDE FUSELAGE SKIN HAS CORROSION AROUND THE WING TO BODY FAIRING MOUNT AREA BETWEEN FRAME 45 AND FRAME 46. REMOVED CORROSION IAW SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM 53-10-12; PAGE 139. ALODINED AREA IAW SRM 51-21-10. PRIMED & TOP COAT PAINTED BOTH IAW SRM 51-23-10. MINOR REPAIR

Part: PANEL — DELAMINATED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

FOUND DELAMINATION ON PANEL NR 143FL, INTERIOR SKIN. REPAIRED BY REMOVING DAMAGE. APPLIED, CURED & SANDED WET LAY UP. APPLIED REFINISH IAW SRM 51-77-10 & SRM 51-75-10.

Part: PANEL — PUNCTURED (AFT CARGO BAY) · airframe 36,499 hrs · 24,558 cycles

AFT CARGO PIT PANEL NR 162 OW IS PUNCTURED. REPAIRED AFT CARGO PIT PANEL AND TOP COATED ( WHITE ) IAW DRAWING SRZ -75-013.

Part: TIP CAP — DAMAGED (HORIZONTAL STAB) · airframe 36,499 hrs · 24,558 cycles

RT HORIZONTAL STABILIZER TIP LOWER L/E IS ERODING BEHIND THE ANTI-EROSION STRIP. REMOVED DAMAGE, VERIFIED MAT I.D. APPLIED LAYUP & CURED, RESTORED FINISH IAW 55-14-11.

Part: SKIN — DELAMINATED (LT MLG DOOR) · airframe 36,499 hrs · 24,558 cycles

LT MAIN LANDING GEAR DOOR EXTERNAL SKIN HAS DELAMINATION 36" FROM THE FWD END. REMOVED THE DAMAGE. CLEANED & PREPPED FOR THE REPAIR. POTTED AREA; CURED; SANDED & APPLIED REPAIR PLYS & VAC BAGGED. CURED, SANDED PERFORMED A RESIN SWEEP. CURED & SANDED SMOOTH IAW SRM 51-77-12 FIG 202. RESTORED FINISH IAW SRM 51-75-10.

Part: SEALANT — CRACKED (THRUST REVERSER) · airframe 36,499 hrs · 24,558 cycles

NR 2 ENGINE OUTBD THRUST REVERSER TRANSLATOR SLEEVE LOWER CORNER IS CRACKED. EVALUATED DAMAGE AND FOUND CRACKED SEALANT ONLY, REMOVED DAMAGED SEALANT AND RESEALED IAW SRM 51-24-00 AND 51-76-10. PERFORMED PAINT TOUCH-UP OF REPAIR AREA IAW SRM 51-75-10

Part: SEAT TRACK — GOUGED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

MAIN CABIN SEAT TRACK AT Y 450 IS GOUGED FROM FRAMES 50 TO 51. REMOVED GOUGE IAW SRM 51-73-10. ORIGINAL DIAMETER OF THE SCALLOPS IS .790 IAW DWG A5381922. MATERAL REMOVED IS .020. DIAMETER DIAMETER REMAINING FOR SCALLOP IS .810. FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16. ALODINED, PRIMED, AND PAINTED AREA IAW AND AMM 51-23-10-0.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

MAIN CABIN SEAT TRACK AT Y 953 SCALLOPS ARE GOUGED AND CRACKED AT FRAMES 42 TO 43. FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16. REMOVED ORIGINAL SEAT TRACK IAW SRM 51-40-21. IAW SRM 53-15-16. LOCATED & DRILLED NEW SEAT TRACK SECTION IAW DWG A53874204. ALODINED & PRIMED IAW 51-75-10. INSTALLED IAW SRM 51-40-21. CIC AREA IAW AMM 51-20-00-0. MAJOR REPAIR.

Part: CARGO TRACK — CRACKED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

MAIN CARGO COMPARTMENT AT FRAME 46 BETWEEN SEAT TRACK -Y 450 AND -Y 953 TIE DOWN TRACK IS CRACKED. REMOVED AND REPLACED TIE DOWN TRACK IAW SRM 51-40-21.

Part: TIP CAP — ERODED (HORIZONTAL STAB) · airframe 36,499 hrs · 24,558 cycles

LT HORIZONTAL STABILIZER TIP IS ERODED AT THE LOWER L/E. REPAIRED LT HORIZONTAL STAB TIP BY REMOVING PREVIOUS REPAIR AND APPLING A WET LAY-UP FIBERGLASS REPAIR AND REFINISHING AREA IAW SRM 55-14-11.

Part: PANEL — PUNCTURED (VERTICAL STAB) · airframe 36,499 hrs · 24,558 cycles

VERTICAL STABILIZER PANEL NR 325 FL IS PUNCTURED. REPAIRED DAMAGED AREA BY APPLYING FIBERGLASS OVERLAYS IAW SRM 53-33-13 FIG 201 SECTION C-C. PAINTED REPAIR AREA ON THE PANEL IAW 51-75-10-08.

Part: TIP CAP — CRACKED (VERTICAL STAB) · airframe 36,499 hrs · 24,558 cycles

VERTICAL STABILIZER TIP IS CRACKED AND DELAMINATED AT THE FWD HOIST POINT HOLE. REPAIRED VERTICAL STAB TIP ERROSION DAMAGE BY REMOVING DAMAGE SKIN PLYS, APPLING A WET LAYUP FIBERGLASS REPAIR AND REFINISHING IAW SRM 55-34-11.

Part: SLEEVE — CRACKED (THRUST REVERSER) · airframe 36,499 hrs · 24,558 cycles

NR 2 ENGINE OUTBD T/R TRANSLATOR SLEEVE, UPPER CORNER PANELS ARE CRACKED. CLEANED FWD TRANSLATOR SLEEVE PANEL REF AMM 12-21-11. HFEC PANEL EF NDT MANUAL 51-10-08. NO CRACKS FOUND. REMOVED AFT TRANSLATOR SLEEVE PANEL REF SRM 51-40-21 PARA 13. CLEANED AFT PANEL REF AMM 12-21-11. HFEC PANEL REF NDT MANUAL 51-10-08. NO CRACKS NOTED. ALODINED FWD & AFT PANEL REF SRM 51-21-10. PRIMED REF SRM 51-23-10. REINSTALLED AFT PANEL REF SRM 51-40-10 PARA 13. PAINTED REF SRM 51-23-10.

Part: PANEL — DAMAGED (RT MLG DOOR) · airframe 36,499 hrs · 24,558 cycles

RT MLG ZONE 742 STRUT DOOR LOWER AFT SECTION HAS A DEEP NICK AND THE EDGE IS CHIPPED AWAY. REMOVED DAMAGE AND REPAIRED IAW SRM 52-81-11 PB 201 & 51-77-11 CHAP 4D.

Part: RUB STRIP — DELAMINATED (LT WING) · airframe 36,499 hrs · 24,558 cycles

LT WING PANEL NR 587FT IS DELAMINATING. REPAIRED LEFT WING PANEL 587FT BY REMOVING RUB STRIP, FABRICATING A NEW RUB STRIP & BONDING THE NEW ONE ON IAW SRM 57-52-12.

Part: PANEL — BROKEN (VERTICAL STAB) · airframe 36,499 hrs · 24,558 cycles

VERTICAL STABILIZER PANEL NR 325 CR IS BROKEN. REMOVED DAMAGE, VERIFIED MAT I.D. APPLIED REPAIR PLYS, CURED. RESTORED FINISH IAW SRM 55-33-13 & 51-77-00.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 36,499 hrs · 24,558 cycles

MAIN CABIN SEAT TRACK IS BROKEN BETWEEN STA 60 AND 61, RBL 77. FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16 FIG 101. REMOVED SEAT TRACK SECTION IAW SRM 51-40-21 PARA 7. FABRICATED NEW SEAT TRACK SECTION REF SRM 53-51-16 FIG 203. LOCATED & DRILLED NEW SEAT TRACK SECTION IAW SRM 51-40-44 PARA 2. ALODINED SEAT TRACK IAW SRM 51-21-10 PARA 2. PRIMED & PAINTED SEAT TRACK IAW SRM 51-23-10 PARA 1. INSTALLED SEAT TRACK SECTION IAW SRM 51-40-21 PARA 7. MAJOR REPAIR.

Part: SKIN — DELAMINATED (RT MLG DOOR) · airframe 36,499 hrs · 24,558 cycles

RT MAIN LANDING GEAR DOOR EXTERNAL SKIN HAS DELAMINATION 34" FROM THE FWD END. REMOVED DAMAGE AT THE TWO EACH AREAS. PERPARED AREA FOR REPAIR PLY LAY UP. LAYED UP, BAGGED & CURED REPAIR PLYS. APPLIED & CURED ROSIN COAT, RESTORED FINISH IAW SRM 52-81-10 & 51-77-10 PG 209; WET LAY UP REPAIR.

Part: FAIRING — CRACKED (NR 2 NACELLE) · airframe 36,499 hrs · 24,558 cycles

NR 2 PYLON SKIN ABOVE THE INBD T/R IS CRACKED AT APPROX STA 704 RIB 7. CLEANED AREA & REMOVED SCRATCHES IAW SRM 51-73-10 PG 203. NO CRACKS NOTED. REPLACED SEAL SECTION IAW SRM 51-40-21. ORIGINAL MATERIAL THICKNESS 0.024. MATERIAL REMAINING 0.021. WITHIN LIMITS IAW SRM 54-50-00.

Part: RUB STRIP — CHAFED (R1 DOOR) · airframe 36,499 hrs · 24,558 cycles

R-1 UPPER FWD CORNER IS CHAFED. REMOVED CHAFED RUB STRIP IAW SRM 51-40-21; PARA 6. ALODINED AND PRIMED AREA SRM 51-21-10. INSTALLED NEW RUB STRIP REF A310-200 SRM 51-40-21 PARA 6. MINOR REPAIR.

Part: BRIDGE — CORRODED (HORIZONTAL STAB) · airframe 36,499 hrs · 24,558 cycles

LT HORZIONTAL STABILIZER TIP BRIDGING STRIP CORRODED UNDER THE NUTPLATES. REMOVED THE CORROSION REF SRM 51-74-10; PARA 5. FOUND TO BE WITHIN LIMITS IAW SRM 55-10-00 TABLE 101. ALODINED REF SRM 51-21-10, PARA 5. PRIMED REF SRM 51-23-10; PG 1. INSTALLED NUTPLATES REF SRM 51-40-21 PARA 6. MINOR REPAIR.

Part: PANEL — CHAFED (NR 2 NACELLE) · airframe 36,499 hrs · 24,558 cycles

NR 2 PYLON PANEL NR 424 BR; CHAFED ON THE MATING SURFACES. CUT OUT DAMAGED AREA OF PANEL 424BR IAW SRM 54-52-51 FIG 203.; SHEETS 1-3. FABBED REPAIR DOUBLER & SHIM. INSTALLED BOTH IAW SRM 54-51-51; FIG 203; SHEETS 1-3. MINOR REPAIR.

Part: RUB STRIP — CHAFED (R1 DOOR) · airframe 36,499 hrs · 24,558 cycles

R-1 DOOR UPPER AFT CORNER IS CHAFED. REMOVED CHAFED RUB STRIP REF SRM 51-40-21 PARA 6. ALODINED AND PRIMED AREA REF SRM 51-21-10. INSTALLED NEW RUB STRIP REF SRM 51-40-21 PARA 6. MINOR REPAIR.

Part: NOSE COWL — CORRODED (NR 1 ENGINE) · airframe 36,499 hrs · 24,558 cycles

NR 1 ENGINE NOSE SECTION HAS CORROSION ON THE INNER SKIN OF THE INTAKE AT THE 4:00 O'CLOCK POSITION; ACCESS 434BR. REMOVED AND REPLACED NR 1 ENGINE NOSE COWL IAW MM 71-11-00-4.

Part: STRAP — CORRODED (RUDDER) · airframe 36,499 hrs · 24,558 cycles

RUDDER L/E PANEL NR 326 LL; BRIDGING STRAP IS CORRODED UNDER THE NUT PLATES. REMOVED AND REPLACED BRIDGING STRAP REFERENCE A310-200 SRM 51-40-21; PARA 5.

Part: STRAP — CORRODED (RUDDER) · airframe 36,499 hrs · 24,558 cycles

RUDDER L/E PANEL NR 326GL BRIDGING STRAPS ARE CORRODED UNDER THE NUT PLATES. REMOVED AND REPLACED THE BRIDGING STRAPS REFERENCE FEDEX A310-200 SRM 51-40- 21.

Part: SUPPORT BRACKET — CRACKED (NR 2 NACELLE) · airframe 36,499 hrs · 24,558 cycles

NR 2 PYLON FIRE EXTINGUISHER NR 2 SUPPORT BRACKET IS CRACKED. CLEANED MARKED AREA PER AMM 12-21-11-0. ACCOMPLISHED HFEC IAW NTM 51-10-01 PT 6 USING T8257A. NO CRACKS NOTED. PRIMED CLEANED AREA PER SRM 51-23-10.

Part: LATCH — CHAFED (THRUST REVERSER) · airframe 36,499 hrs · 24,558 cycles

NR 1 ENGINE INBD T/R, LOWER FWD LATCH DOOR IS CHAFED TO A KNIFE EDGE AND CRACKED OUT IN THE UPPER CORNER. REMOVED DAMAGED DOOR AND INSTALLED NEW DOOR P/N 9071M77G11; PO 610928.2. IAW SRM 51-40-21; PARA 5. MINOR REPAIR

Part: SPAR — CRACKED (NR 2 PYLON) · airframe 36,499 hrs · 24,558 cycles

NR 2 PYLON AFT LOWER SPAR ANGLE IS CRACKED AT STA 999/RIB 19. REMOVED A54515241500 STAMPING TO ACCESS THE CRACKED ANGLE PER SRM 51-40- 21 PARA 5. REMOVED CRACKED A54515063204 ANGLE PER SRM 51-40-21; PARA 5 & 6. ORDERED AND RECEIVED NEW A54515063204 NAGLE. LOCATED, DRILLED AND DEBURRED FASTENER HOLES ON THE NEW ANGLE PER SRM 51-40-40. INSTALLED THE NEW ANGLE & REINSTALLED STAMPING PER SRM 51-40-21; PARA 5, 6 AND 7. MINOR REPAIR.

Part: FRAME — CRACKED (NR 2 PYLON) · airframe 36,499 hrs · 24,558 cycles

NR 2 PYLON A-FRAME IS CRACKED AT STA 1115/RIB 21. REMOVED A5451675001 FLODED SHEET METAL SECTION & CRACKED A54521550100 TEE PER SRM 51-40-21 PARA 5. ORDERED & RECEIVED NEW A54521550100 TEE. LOCATED, DRILLED & DEBURRED FASTENER HOLES ON NEW TEE IAW SRM 51-40-40. INSTALLED NEW TEE & FOLDED SHEET METAL SECTION PER SRM 51-40-21; PARA 5. MINOR REPAIR

Part: STRAP — CORRODED (RUDDER) · airframe 36,499 hrs · 24,558 cycles

RUDDER L/E PANEL NR 326 JL BRIDGING STRAP IS CORRODED UNDER THE NUTPLATES. REMOVED AND REPLACED STRAPS IAW SRM 51-40-21 PARA 5. MINOR REPAIR.

Part: BULKHEAD — DAMAGED (MLG WW) · airframe 36,499 hrs · 24,558 cycles

MAIN WHEEL WELL FWD BULKHEAD PANEL NR 147 CZ HAS SEVERAL RETAINER BRACKETS THAT HAVE WORN PIP PIN HOLES.

Part: PANEL — DENTED (NR 2 PYLON) · airframe 36,499 hrs · 24,558 cycles

NR 2 PYLON PANEL NR 423 DL IS DENTED. DRESSED OUT DENT REF SRM 51-73-10 PAGE 214. ACCOMPLISHED HFEC INSPECTION IF THE DENT AREA IAW NTM 51-10-20. NO DEFECTS NOTED. MINOR REPAIR.

Part: STRAP — CORRODED (RUDDER) · airframe 36,499 hrs · 24,558 cycles

RUDDER L/E PANEL NR 326 EL BRIDGING STRAPS ARE CORRODED UNDER THE NUT PLATES. REMOVED AND REPLACED THE BRIDGING STRAPS REFERENCE A310-200 SRM 51-40-21; PARA 5.

Part: STRAP — CORRODED (RUDDER) · airframe 36,499 hrs · 24,558 cycles

RUDDER L/E PANEL NR 326 CL BRIDGING STRAPS ARE CORRODED UNDER THE NUT PLATES.

Part: SLEEVE — CRACKED (THRUST REVERSER) · airframe 36,499 hrs · 24,558 cycles

NR 2 ENGINE OUTBD T/R TRANSLATOR SLEEVE IS CRACKED IN THE UPPER CORNER. REMOVED OLD SEALANT AND RESEALED IAW SRM 51-76-10 AND 51-10-30. PAINTED IAW SRM 51-23-10.

Part: FAIRING — CRACKED (HORIZONTAL STAB) · airframe 36,499 hrs · 24,558 cycles

RT HORIZONTAL STABILIZER UPPER APRON FAIRING IS CRACKED AND DELAMINATED IN SEVERAL PLACES. FABRICATED DOUBLER IAW SRM 55-15-11. REMOVED DAMAGED SECTION IAW SRM 55-15-11 FIG 201. INSTALLED DOUBLER IAW SRM 55-15-11 PGS 219/220. INSTALL SILICONE DOUBLER AND REPAIRED DAMAGED AREAS IAW SRM 55-15-11 PARAGRAPH 5 (4).

Part: FAIRING — MISALIGNED (LT WING TE FLAP) · airframe 36,499 hrs · 24,558 cycles

LEFT WING FLAP FAIRING 533CB IS DELAMINATED IN TWO SPOTS. REPAIRED LEFT WING FLAP FAIRING BY REMOVING THE DAMAGE. CLEANED & PREPED FOR THE APPLICATION OF A WET LAY UP. APPLIED, CURED & SANDED THE WET LAY UP. CLEANED & PREPPED FOR REFINISH. APPLIED REFINISH IAW SRM 57-20-35, SRM 51-40-13, SRM 51-23-10 & SRM 51-40-10.

Part: FAIRING — DEBONDED (HORIZONTAL STAB) · airframe 36,499 hrs · 24,558 cycles

LT HORIZONTAL STABILIZER LOWER APRON FAIRING IS DISBONDED. RE-APPLIED ADHESIVE PER SRM 55-15-11 PARAGRAPH 5 SECTIONS H & I TO DISBONDED SILICONE MATERIAL.

Part: PANEL — DELAMINATED (VERTICAL STAB) · airframe 36,499 hrs · 24,558 cycles

VERTICAL STABILIZER PANEL 325CR IS DELAMINATED. REMOVED DAMAGE, VERIFIED MAT. I D APPLIED PLYS, CURED, RESTORED FINISH IAW 55-33-13 & 51-77-00.

Part: FAIRING — DELAMINATED (LT WING TE FLAP) · airframe 36,499 hrs · 24,558 cycles

LT WING FLAP FAIRING 535CB IS DELAMINATED. REPAIRED LT WING FLAP FAIRING 535CB BY REMOVING DELAMINATED SKIN AND CORE SECTION AND APPLYING NEW CORE SECTION AND FIBERGLASS OVERLAY REPAIR IAW SRM 57-20-35. RESTORED FINISH IAW SRM 51-75-10.

Part: FAIRING — CRACKED (HORIZONTAL STAB) · airframe 36,499 hrs · 24,558 cycles

RT HORIZONTAL STABILIZER FWD APRON FAIRING BLADES ARE CRACKED. REMOVED THE DAMAGED SECTION IAW SRM 15-15-11 PGS 219 & 220. FABRICATED DOUBLER PLATE IAW SRM 15-15-11 PG 225. INSTALLED DOUBLER IAW SRM 15-15-11 PARA 5-B (4).

Part: FAIRING — ERODED (LT WING TE FLAP) · airframe 36,499 hrs · 24,558 cycles

LEFT WING FLAP FAIRING 533CB L/E IS ERODED BY THE TEFLON SEAL. REPAIRED LEFT WING FLAP FAIRING L/E BY REMOVING THE TEFLON SEAL TO AND REMOVED THE DAMAGE. CLEANED & PREPPED FOR A WET LAY UP. APPLIED, CURED & SANDED THE WET LAY UP. CLEANED & PREPPED FOR REFINISH. APPLIED REFINISH & REINSTALLED SEAL IAW SRM 57-20-35, SRM 51-40-13, SRM 51-40-00, SRM 51-23-10 & 51-40-10.

Part: FAIRING — DELAMINATED (LT WING TE FLAP) · airframe 36,499 hrs · 24,558 cycles

LEFT WING FLAP FAIRING 532CB IS DELAMINATED IN TWO SPOTS. REMOVED DAMAGE, POTTED CORE, CURED, SANDED & PREPPED FOR WET LAY UP. LAYED UP REPAIR PLYS CURED & SANDED REPAIR PLYS; APPLIED SEALER RESIN, CURED & SANDED, REAPPLIED ANTI-STATIC PRIMER & FINISH TOP COAT IAW SRM 57-20-35.

Part: FILLET — PUNCTURED (ZONE 100) · airframe 36,499 hrs · 24,558 cycles

LT FILLET PANEL NR 577BL IS PUNCTURED. REPAIRED PUNCTURES IAW SRM 51-77-12.

Part: PANEL — DELAMINATED (VERTICAL STAB) · airframe 36,499 hrs · 24,558 cycles

VERTICAL STABILIZER PANEL 325DL (ACTUATOR ACCESS PNL), FWD SECTION IS DELAMINATED. RESTORED FINISH PER SRM 51-75-10. REPAIRED BY REMOVING DAMAGE AND APPLYING A 250 DEGREE PREPREG LAYUP IAW SRM55-33-13.

Part: FAIRING — DELAMINATED (HORIZONTAL STAB) · airframe 36,499 hrs · 24,558 cycles

LT HORIZONTAL STABILIZER FWD APRON FAIRING IS DELAMINATED. INSTALLED NEW APRON FAIRING. MINOR REPAIR.

Part: SKIN — DELAMINATED (LT ELEVATOR) · airframe 36,499 hrs · 24,558 cycles

THE LT ELEVATOR LOWER SURFACE TE APPROXIMATELY 4" FROM THE TE TO APPROXIMATELY 18 INCHES FROM THE TE; STA 276 ER 8 TO STA 291 ER 9 IS DELAMINATED. UPON FURTHER INVESTIGATION FOUND THE AREA TO BE PREVIOUSLY REPAIRED PER EA 6-5520-118195 PT 1. NO DELAMINATION NOTED.

Part: MUFFLER — CRACKED (APU) · airframe 36,499 hrs · 24,558 cycles

APU TAIL CONE EXHAUST PIPE IS CRACKED AND TORN APPROXIMATELY 6 FT INSIDE THE TAILCONE AT THE 6 O'CLOCK POSITION. REPLACED APU EXHAUST MUFFLER WITH A NEW EXHAUST MUFFLER IAW REF 49-81-15-4.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,033 hrs · 24,285 cycles

CORROSION ON FRAME 19 LOWER FLANGE BETWEEN STRINGER 52-53 LT. REPAIR PERFORMED BY CUT OUT FRAME FLANGE AND INSTALLING FABRICATED REPAIR ANGLE ON FRAME IAW TD 038083/004/2005 ISSUE A AND EA 6-5312-82892.

Part: FLAP SYSTEM — MALFUNCTIONED (TE FLAPS) · airframe 35,667 hrs · 24,078 cycles

FLAP FAULT BOTH LIGHT SY1/SY2 WHEN FLAPS SET TO 15-15. RECYCLED FLAPS AND WORKED OK, BUT A BIT SLOW. NEED SAFETY WIRE ON FLAP OVERRIDE SWITCH. SYSTEM NR 1 AND NR 2 FAULTS CLEARED AT THIS TIME. MTP SHOWED NR 2 SFCC FAULT. PERFORMED BITE TEST OF SFCC THAT SHOWED 'JAM'. RESET SFCC. CYCLED FLAPS SEVERAL TIMES THROUGH FULL RANGE WITH NO FAULTS NOTED, USING ENGINES. FLAPS OPS CHECK NORMAL PER A310 AMM 27-50-00. INSPECTED FLAPS, NO DEFECTS NOTED. SAFETY FLAP OVERRIDE SWITCH.

Part: BOOT — LOOSE (HEAT EXCHANGER) · airframe 35,073 hrs · 23,748 cycles

WHILE EN ROUTE AT FL 280, HAD MID NR 2 "A" LOOP ILLUMINATE THEN 5 SECONDS LATER "B" LOOP NR 2 MID LIGHT ILLUM. SMOKE LIGHT ILLUMINATE. PUT SMOKE MASK ON DECLARED EMERGENCY, PERFORMED MCD COMPARTMENT SMOKE DETECTION ADJUSTMENT AND TESTED RAN PACKS WITH A/C CLOSED UP ON APU AND ENGS WITH NO FAULTS. DURING REMOVAL AND REPLACEMENT OF COALESCER BAGS FOUND BOOTS ON HEAT EXCHANGERS LT AND RT PACKS LOOSE REF WRI 21-50/8103 FOR INFO. SUSPECT THIS MAY HAVE CAUSED CARGO SMOKE FAULT. FOUND EXCESSIVE LEAKS IN A/C BAY ON RT AND LT PACK HEAT EXCHANGER COUPLINGS. FOUND RT AND LT COALESCER BAGS DIRTY WITHOUT ODOR. RESECURED RT, LT COUPLING CLAMPS PER SMP. REMOVED AND REPLACED RT AND LT BAGS PRECAUTIONARY, RT AND LT PACK

Part: DAMPER — DAMAGED (MLG) · airframe 34,454 hrs · 23,399 cycles

AFTER T/O FROM MEM, LDG GEAR LEVER WOULD NOT MOVE FROM CENTER DETENT. PUT GEAR IN DOWN POSITION, RETURNED TO MEM FOR LDG. FOUND INDICATOR POPPED ON LT MLG PITCH DAMPER UPON ARRIVAL TO A/C. REPLACED LT MLG PITCH DAMPER PER A310-200 M/M 32-11-15-4-01. A/C WILL BE BACK IN SERVICE.

Part: FILLER — MISSING (FUSELAGE SKIN) · airframe 33,927 hrs · 23,079 cycles

EXTERNAL DOUBLER AT FWD LOWER FUSELAGE NOSE SECTION AT FS 4 MISSING FILLER.

Part: SKIN — CORRODED (FS 66) · corrosion level 2 · airframe 33,927 hrs · 23,079 cycles

FS 66 BL 0 HAS SURFACE CORROSION ON SKIN AND FRAME. REMOVED DAMAGED SKIN AND STRINGER FABED NEW PARTS INSTALLED PARTS IAW SRM 53-10-12, 53-10-14, 53- 17-14, AND MM 51-75-10-8.

Part: SKIN — CORRODED (FR 60) · airframe 33,927 hrs · 23,079 cycles

EXTERNAL FUSELAGE SKIN BULGING AT FR 60 S52 LT AND HAS SEVERAL SHEARED RIVETS.

Part: FLOOR PANEL — CRACKED (CARGO BAY) · airframe 33,927 hrs · 23,079 cycles

MCD FLOOR PNL 232AH CRACKED ON BACK.

Part: PANEL — DELAMINATED (VERTICAL STAB) · airframe 33,927 hrs · 23,079 cycles

VERTICAL STAB PNL 325DL DELAMINATED AT LOWER END SCREW HOLE.

Part: FLOOR PANEL — CRACKED (CARGO BAY) · airframe 33,927 hrs · 23,079 cycles

MCD FLOOR PNL 231XG CRACKED AND DELAMINATED ON BACK SIDE.

Part: PANEL — CRACKED (HORIZONTAL STAB) · airframe 33,927 hrs · 23,079 cycles

LT IB HORIZONTAL STAB L/E HAS MULTIPLE CRACKS WHERE RIBS ATTACH TO SKIN.

Part: RADOME — DELAMINATED (FUSELAGE) · airframe 33,927 hrs · 23,079 cycles

RADOME HAS DAMAGE AREA AT 1 O`CLOCK POSITION, DELAM AREA.

Part: FILLER — MISSING (FS 3) · airframe 33,927 hrs · 23,079 cycles

EXTERNAL DOUBLER AT FWD RT LOWER FUSELAGE NOSE SECTION AT FS 3 IS MISSING FILLER. REMOVED FLOOR ACCOMPLISHED REPAIR WITH MINOR DEVIATION BY EA 6-5330-92339. INSTALLED FLOOR AND PAINTED.

Part: SPAR CAP — CORRODED (HORIZONTAL STAB) · airframe 33,927 hrs · 23,079 cycles

LEFT HORIZONTAL STAB FWD UPPER SPAR CAP IS CORRODED AT NR 10 NUTPLATE COUNTING IB-OUT.

Part: SPAR CAP — CORRODED (HORIZONTAL STAB) · airframe 33,927 hrs · 23,079 cycles

LEFT HORIZONTAL STAB UPPER SPAR CAP IS CORRODED AT NR 23 NUTPLATE COUNTING IB-OUT.

Part: FRAME — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 33,927 hrs · 23,079 cycles

LT HORIZ STAB T/E FORMER/WEB CORRODED AROUND NUTPLATES AND WEB FROM REAR SPAR TO 10" AFT OF REAR SPAR AND 54" FROM FUSELAGE. REMOVED CORROSION FOUND OUT OF LIMITS IAW SRM 55-10-00 FIG 101. REMOVED FORMER WEB RIB IAW SRM 51-40-21. RIB FABRICATED ON PCT NR T5/546620 LOCATED AND DRILLING IAW SRM 51-40. INSTALLED NEW RIB IAW SRM 51-40-21 PG 27.

Part: FLOOR SUPPORT — CRACKED (FR 11-12A) · airframe 33,927 hrs · 23,079 cycles

FWD MDCC UNDERFLOOR FLOOR PANEL SUPPORT FROM FRAME 11-12A, LBL 30 IS CORRODED AND CRACKED AT LOWER SURFACE. REMOVED AND REPLACED PANEL SUPPORT IAW SRM 51-40-00, PART FABRICATED ON PCT NR T5/546112.

Part: FLOOR SUPPORT — CORRODED (FR 13-15) · corrosion level 2 · airframe 33,927 hrs · 23,079 cycles

FWD MDCC UNDERFLOOR AREA FLOOR PANEL SUPPORT BETWEEN FRAMES 13-15 LBL 58 IS CORRODED. REMOVED CORROSION IAW SRM 51-22-00 ORIG MAT=.079 AFTER =.042 OUT OF LIMITS IAW SRM 53-12-15. REMOVED DAMAGED SUPPORT IAW SRM 51-40-21. LOCATED AND DRILLED NEW SUPPORT IAW SRM 51-40-44. INSTALLED NEW FLOOR SUPPORT IAW SRM 51-40-21.

Part: SEAT TRACK — DAMAGED (FS 62-36) · airframe 33,927 hrs · 23,079 cycles

MDC - SEAT TRACK AT RBL 58 BETWEEN FS 62-63 HAS SEVERAL DAMAGED LUGS.

Part: SEAT TRACK — CORRODED (FR 75-77) · airframe 33,927 hrs · 23,079 cycles

MDCC - SEAT TRACK BETWEEN FS 75-77 LBL HAS SPOTS OF CORROSION.

Part: FLOOR PANEL — CRACKED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 231VG-2 IS CRACKED. FABED NEW FLOOR PANEL.

Part: FLOOR PANEL — CRACKED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 231JH CRACKED. FABED NEW FLOOR PANEL.

Part: FLOOR PANEL — CRACKED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 231JG IS CRACKED. FABED NEW FLOOR PANEL.

Part: FLOOR PANEL — CRACKED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 231TG CRACKED. FABED NEW FLOOR PANEL.

Part: FLOOR PANEL — DELAMINATED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 242EK IS DELAMINATED. FABED NEW FLOOR PANEL.

Part: FLOOR PANEL — CRACKED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 232TG IS CRACKED. FABED NEW FLOOR PANEL.

Part: FLOOR PANEL — DELAMINATED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 232NG DELAMINATED. FABED NEW FLOOR PANEL.

Part: FLOOR PANEL — CRACKED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 241WH IS CRACKED. FABED NEW FLOOR PANEL.

Part: FLOOR PANEL — CRACKED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC - FLOOR PANEL 231NH IS CRACKED. FAB`D NEW PANEL.

Part: SPAR — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 33,927 hrs · 23,079 cycles

LT HORIZ STAB UPPER REAR SPAR T-CAP LOWER SIDE CORRODED AT NUTPLATES 51 TO 57 IN FROM FUSELAGE. REMOVED NUTPLATES, REMOVED CORROSION, MODIFIED RIB SUPPORT FABED REPAIRS, AND INSTALLED REPAIRS IAW SRM 51-40-21, 55-11-21, AND 51-74-10.

Part: FLOOR PANEL — DELAMINATED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 242UJ DELAMINATED. FABED NEW PANEL.

Part: FLOOR PANEL — CRACKED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 231KH IS CRACKED. FABED NEW FLOOR PANEL.

Part: FLOOR PANEL — DELAMINATED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 232EG IS DELAMINATED. FABED NEW FLOOR PANEL.

Part: SEAT TRACK — CORRODED (CARGO DECK) · corrosion level 2 · airframe 33,927 hrs · 23,079 cycles

MDCC SEAT TRACK BETWEEN FR. 51 ,52 LBL 56 HAS CORROSION . REMOVED AND REPLACED SEAT TRACK DUE TO OUT OF LIMITS CORROSION IAW SRM 53-10-16 AND 51-40-21.

Part: SEAT TRACK — CRACKED (FR 61-62) · airframe 33,927 hrs · 23,079 cycles

MCD SEAT TRACK BET FR 61 AND FR 62 BL 0 HAS CRACK. REPAIRED SEAT TRACK IAW SRM 53-10-16.

Part: SEAT TRACK — CORRODED (FR 58-72) · corrosion level 2 · airframe 33,927 hrs · 23,079 cycles

MAIN DECK SEAT TRACK FR 58 TO 72 CORRODED. REMOVED CORROSION, REMOVED TRACKS, FAB REPAIR PARTS INSTALLED REPAIR PARTS IAW SRM 51-23-10, 51-40-21, AND 53-10-16.

Part: SEAT TRACK — CORRODED (FR 79) · airframe 33,927 hrs · 23,079 cycles

MDCC - SEAT TRACK FR 79 LBL 56 CORRODED. REMOVED CORROSION, REMOVED SEAT TRACK, DRILLED NEW TRACK, INSTALLED TRACK IAW SRM 53-10-16, 51-40-21, 51-40-44, AND 51-40-21.

Part: FLOOR PANEL — PUNCTURED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC FLOOR PANEL 231VG IS PUNCTURED. FABED NEW FLOOR PANEL.

Part: SEAT TRACK — DAMAGED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC SEAT TRACK HAS DAMAGED LUGS. REMOVED DAMAGED TRACK AND INSTALLED NEW TRACK IAW SRM 51-40-21, 51-21-10, AND 53-10-16.

Part: SEAT TRACK — CORRODED (CARGO DECK) · corrosion level 2 · airframe 33,927 hrs · 23,079 cycles

MDCC SEAT TRACK IS CORRODED. REMOVED CORRODED TRACK AND INSTALLED NEW TRACK IAW SRM53-10-16, 51-40-21, AND51- 23-10.

Part: SEAT TRACK — NICKED (CARGO DECK) · airframe 33,927 hrs · 23,079 cycles

MDCC SEAT TRACK HAS NICKS. REMOVED NICKED SEAT TRACK AND INSTALLED NEW TRACK IAW SRM 53-10-16, 51-27-00,51-40- 40,AND 51-21-00.

Part: RIB — CRACKED (ZONE 300) · airframe 33,927 hrs · 23,079 cycles

LEFT HORIZONTAL L/E PANEL 331BB RIB NR 1 IS CRACKED AT UPPER AFT CORNER.

Part: SEAT TRACK — CORRODED (FR 69-70) · corrosion level 2 · airframe 33,927 hrs · 23,079 cycles

SEAT TRACK BETWEEN FS 69-70, LBL 37" HAS CORROSION. REMOVED LIGHT SURFACE CORROSION IAW SRM 51-74-10 PG 204 MAT LOSS .001, FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16 PG 103. TREATED AND PRIMED IAW SRM 51-21-10 PG 1 AND TOPCOATED IAW SRM 51-23-00 PG 1.

Part: SEAT TRACK — CORRODED (FR 71-73) · corrosion level 2 · airframe 33,927 hrs · 23,079 cycles

SEAT TRACK BETWEEN FS 71-73, LBL 32" HAS SEVERAL SPOTS OF CORROSION. REMOVED LIGHT SURFACE CORROSION IAW SRM 51-74-10 PG 204 .002 MAT LOSS FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16 PG 103. TREATED AND PRIMED IAW SRM 51-21-10 PG 1 AND TOP COATED IAW SRM 51-23-00 PG 1.

Part: HOSE — LEAKING (HYD SYSTEM) · airframe 33,824 hrs · 23,011 cycles

AT APPROXIMATELY 1000 FT ON CLIMB-OUT RECEIVED ECAM WARNING FOR GREEN HYD SYSTEM RESERVOIR LOW. THIS CONFIRMED ON OVERHEAD PANEL ACCOMPLISHED ECAM ITEMS AND RED TABS. GEAR EXTENDED BY GRAVITY EXTENSION METHOD SYSTEM QTY DID NOT GO TO ZERO. FOUND RUPTURED LINE ON LEFT MAIN GEAR SIDE STRUT LOCK ACTUATOR. ROBBED LINE OFF ACFT 402 TO RETURN 425 TO SERVICE. ALSO, RESTORED GEAR SYSTEM TO NORM AFTER EMERGENCY EXTENSION PER MM REF 32-33-00-2 AND SERVICED HYD FLUID PER MM REF CHPTR 12 ACFT GOOD FOR CONTINUE SERVICE.

Part: PLATE — BROKEN (ZONE 100) · airframe 33,434 hrs · 22,743 cycles

PLATE AND SEC-L BENT AND BROKEN BETWEEN FR86 AND FR87. REMOVED PLATE AND FABRICATED NEW SEC-L. INSTALLED NEW SEC-L AND PLATE IN A/C.

Part: PLATE — BENT (ZONE 100) · airframe 33,434 hrs · 22,743 cycles

PLATE AND SEC-L BENT AND BROKEN BETWEEN FR86 AND FR87. REMOVED PLATE AND FABRICATED NEW SEC-L. INSTALLED NEW SEC-L AND PLATE IN A/C.

Part: CONTROL HANDLE — OBSTRUCTED (COCKPIT) · airframe 33,299 hrs · 22,662 cycles

SLATS WOULD NOT RETRACT AFTER TAKEOFF. SLAT/FLAP HANDLE WOULD ONLY OPERATE BETWEEN 15/0 AND 20/20 POSITIONS. RETURNED TO MEM AND MADE 20/20 LANDING. NO OTHER INDICATIONS OF MALFUNCTION ON SFPI OR FLAPS/SLATS SYS 1/2 INDICATIONS. FOUND DEBRIS IN FLAP HANDLE. REMOVED AND OPERATED. OPS CHECKS AS PER AIRBUS M/M 27-50-00.

Part: SCREW — BROKEN (FLAP HANDLE) · airframe 33,232 hrs · 22,629 cycles

AFTER TAKEOFF, THE FLAP HANDLE COULD NOT BE MOVED PAST THE FLAPS 0 DEGREES, NOR COULD MOVE IT PAST THE FLAPS 20 DEGREE POSTION. THE FLAPS DID MOVE FROM THE 20 DEGEES TO 15 AND BACK. FOUND SPECIAL-SCREW ITEM 161 REF A310-200 IPC 53-11-31-13 BROKEN. PARTS NEEDED. ADDED MPN A2791261920000, CPN 5310684 QTY 1 SCREW MSN 908160. INSTALLED FLAP HANDLE AND DETENT SCREW PER AMM 27-51-11-4. OPS CK NORMAL. RII:292460 ENT BY: 014582 RPT BY: 014582.

Part: SKIN — DAMAGED (ZONE 200) · airframe 31,560 hrs · 21,573 cycles

RT FUSELAGE, AFT, BETWEEN VERTICAL ATTACHMENT BOLTS CENTER AND AFT OB SIDE HAS CORROSION ON SKIN 1 INCH X 4 INCHES. REMOVED FASTENERS FROM AFFECTED AREA. REMOVED CORROSION IAW A310 SRM 51-22-00 C/W UT THICKNESS INSPECTION IAW NTM 51-10-01/401. FOUND TO BE OUT OF LIMITS IAW A310 SRM 53-19-12. EC INSPECTION REVEALED NO CRACKS. FLAP PEENED THE REWORKED AREA IAW SRM 51-29-00. INSTALLED NEW FASTENERS IAW A310 SRM 51-40-00. RE-PROTECTED AREA IAW A310 SRM 51-23-00. ALL WORK COMPLETED IAW EA 6-5319-68248 DATED 02-13-03

Part: DAMPENER — INOPERATIVE (LEFT MLG)

LAND GEAR LEVER UPON RETRACTION IND RETRACT FAULT. TRIED TO RECYCLE GEAR DOWN TO UP & SAME IND. *S/D* REMOVED AND REPLACED LT MLG PITCH DAMPENER IAW 32-11-15. RECHARGED NITROGEN PRESSURE MM 12-12-32. TEST OK.

Part: RETRACT MECH — MALFUNCTIONED (LANDING GEAR)

98-0187 STA-ATL - LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF SYSTEM 1 OR SYSTEM 2, INTERLOCK ENGAGED.

Part: PUMP — INOPERATIVE (NR 1 ENGINE)

ENG NR 1 GREEN HYD PUMP INOP. FAILURE OCCURRED IMMEDIATELY AFTER TAKEOFF. REMOVED AND REPLACED NR 1 GREEN SYSTEM PUMP, SHAFT AND CASE RETURN FILTER, OPS CHECK GOOD.