N410FE

Part: WIRE — BROKEN (R1 DOOR) · airframe 42,176 hrs · 22,981 cycles

R1 DOOR SLIDE ARMING LIGHT ASSEMBLY HAS BROKEN WIRES. TERMINATED WIRES TO 8WN FWD RT DOOR ESCAPE SLIDE WARNING LIGHT ASSEMBLY IAW A310-200 AWM 52-73-01. TESTED GOOD IAW A310-200 AMM 52-73-11-04.

Part: CONTROL UNIT — FAULTY (VHF COMM) · airframe 42,114 hrs · 22,941 cycles

COMPLETE LOSS OF COMM ON VHF 1, 2 & 3 AT 1:15 INTO 2 HR FLIGHT. WE CHECKED QRH, NO HELP. CHECK 02 MASK DOORS & RESET. UNPLUGGED & PLUGGED IN AUXILIARY HEADSETS. TRIED COMM WITH CTR USING MASKS, AUXILIARY, NO HELP. RESET VHF 1, 2 & 3 BREAKERS & AFTER 12 - 15 MIN OF LOST COMM WE REGAINED INTERMITTENT USE OF COMM 1 & 2. COMM 1 ON CAPTAIN SIDE IS WEAK, LOW VOLUME, LOT OF STATIC ON OVERHEAD. R & R 1 RN AUDIO INTEGRATION UNIT, OPERATIONS CHECKED OK A310MM 23-51-18-04.

Part: ENGINE — POWER LOSS (NR 1) · airframe 41,940 hrs · 22,833 cycles

THROTTLE KNOBS STAYED WITH A HALF A KNOB. ON TAXI OUT ENG 1 LAGGED ENG NR 2 N1 UP TO 30 PERCENT ACCELARATION. FOR TAKEOFF, TRIED TO SET 40 PERCENT N1 AND ENG NR 1 N1 LAGGED ENG 2 N1 BY INITALLY 10 TO 20 PERCENT. WHEN TO GAD FOR TAKEOFF THE N 1 INITIALLY WERE WITHIN 7 TO 10 PERCENT NIS THEN ENG NR 1 N1 ACCELERATION LAGGED. ENG NR 2 N1 UP TO 20 PERCENT FINALLY N1'S STABILIZED AT ENG NR 1 N1 93 PERCENT ENG 2 N1 100.8 PERCENT ABORTED TAKEOFF AT 80 KIAS ADHERED TO QRH. COMPLETED INSTALLATION OF FUEL PUMP STEP 3 PARGRAPH H-11 PER AMM 73-12-01-02 AND COMPLETED INSTALLATION OF MEC PER AMM 73-21-01-04 FROM STEP 4 PAR C-3. RAN ENGINE AND LEAK CHECK AND POWER ASSURANCE PER ENGINE RUN FORM AND JRH 4-20. OPS CHECKED GOOD. OK TO CONTINUE.

Part: LONGERON — CRACKED (ZONE 100) · airframe 41,444 hrs · 22,512 cycles

WHILE PERFORMING ROTO PROBE ON FWD LOWER HOLE OF INSPECTION AREA THREE IAW WIC E6-5310-7-3328 A PT4, FOUND CRACK IN LONGERON. REPAIRED IAW 6-5310-T0300114, PS P1.

Part: FRAME — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

DURING ACCOMPLISHMENT OF EO 6-5310-7-5020, PART 1, FOUND EDGE DISTANCE FOR HOLES H23 AT FR 46 LT TO BE BELOW .472". FRAME 46 LT HOLE H23 COMPLIED WITH MOD TYPE T MOD NR 6-5315-T0300100, REV NO PS P1 STEPS 29 AND 30.

Part: FITTING — CRACKED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

DURING ACCOMPLISHMENT OF EO 6-5310-7-5020 PT 2, FRAME 45, HOLE H22 RT SIDE SHOWS CRACK INDICATION. FRAME 47 RT HOLE 22 COMPLIED WITH MOD TYPE T MOD NR 6-5315 T0300100 REV NR PS P1, STEPS 1, THRU 13.

Part: ANGLE — CRACKED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FRAME 46, HOLE H27 SHOWS CRACK INDICATION IN ANGLE FITTING AT 6 O'CLOCK. RT FRAME 46, HOLE H27 COMPLIED WITH MOD TYPE T MOD NR 6-5315-T0300100, REV NO PS P1 STEPS 14 THRU 28.

Part: FERRULE — CRACKED (NR 2 NACELLE) · airframe 41,444 hrs · 22,512 cycles

NR 2 PYLON FERRULE CRACKED AT FWD ATTACH POINT OF PNUEMATIC DUCT. CRACK IS 0.50 LONG. COMPLIED WITH EA 6-5450-T0300088 AND SB 54-2028. R & R FERRULE HALVES AND SPLICES.

Part: FITTING — CRACKED (ZONE 400) · airframe 41,444 hrs · 22,512 cycles

NR 2 PYLON FERRULE CRACKED AT FWD OTBD UPPER CORNER AND AT FWD ATTACH POINT OF PNUEMATIC DUCT. CRACK A IS 1' LONG AND CRACK B IS 0.50 LONG. COMPLIED WITH EA 6-5450-T0300088 AD SB 54-2028. R & R FERRULE HALVES AND SPLICES.

Part: SKIN — DAMAGED (ZONE 300) · airframe 41,444 hrs · 22,512 cycles

LEFT ELEVATOR UPPER SURFACE IS PUNCTURED AND DENTED. PUNCTURE (APPROX. 1.5" X .75"X .75") DENT (APPROX. .5" X .4" X .030") DAMAGE IS 8" FWD OF T/E AND 100" INBD OF ELEVATOR TIP REF SNRM N01030. REPAIRED LT ELEVATOR UPPER SURFACE IAW SRM 55-21-11, CONFIG 1, PARA 5(I), FIG 209, SRM 51-73-10, PARA 3 AND EA 6-5520-T0300152 (WRI 55-20 3586) ALL WORK PERFORMED ON SNRM N01030 AND EA 6-5520-T0300152.

Part: SHEAR TIE — MISINSTALLED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

DURING ACCOMPLISHMENT OF EO 6-5310-7-5020 APT2. FOUND EDGE DISTANCE FOR HOLES H1 AND H2 AT FR 43 RT TO BE BELOW MINUM OF .472. R & R FRAME FOOT AT FR43 RT IAW SRM 51-72-10.

Part: SUPPORT ANGLE — CRACKED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

WHILE WORKING WC E6-5310-7-5020PT2, FOUND ONE BRACKET CRACKED AT MDCC FR43 BELOW STR 26R. R & R SUPPORT ANGLE IAW SRM 51-72-10. FABRICATED NEW SUPPORT ANGLE ON N00941.

Part: SUPPORT ANGLE — MISMANUFACTURED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

DURING ACCOMPLISHMENT OF E0 6-5310-7-5020 APT1, FOUND EDGE DISTANCE FOR HOLES H1 AND H 2 AT FR 43 LT TO BE BELOW MINIMUM OF .472". R & R SUPPORT ANGLE AT FR 43 LT IAW SRM 51-72-10. R & R FRAME FOOT AT FR 43 LT IAW SRM 51-72-10.

Part: SKIN — DENTED (TAILCONE) · airframe 41,444 hrs · 22,512 cycles

DENT ON TAILCONE JUST AFT OF RIB 92 AND 93 BETWEEN STR 2L AND 3L APPROX. 1" X 1". REPAIRED DENT ON TAILCONE AFT OF FR 92 (RIB) BETWEEN STR 2 AND 3L IAW EA 6-5310-T0300131 REF WRI 53103597.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,444 hrs · 22,512 cycles

FOUND 1" SQ OF CORROSION ON FRAME 14A LT AT STR 30L AREA FOUND TO BE OUT OF LIMITS AFTER CORROSION REMOVAL IAW SRM 51-74-10. REPAIRED FRAME 14A LT AT STR 30-32L IAW SRM 53-12-13.

Part: SKIN — CRACKED (ZONE 500) · airframe 41,444 hrs · 22,512 cycles

LT WING UPPER FIXED T/E AT AILERON ACTUATOR CUTOUT PANEL LANDING FOR PANEL 575 BT IS CRACKED .4 IN LENGTH. REMOVED LANDING AT LT WING UPPER FIXED T/E AT AILERON ACTUATOR CUT-OUT IAW SRM 51-40-21, PARA 5, 7, AND 16. LOCATED AND DRILLED NEW LANDING IAW SRM 51-40-40 AND DWG A57242821, REV H. INSTALLED NEW PANEL LANDING ON LT WING AT AILERON CUT-OUT IAW SRM 51-40-21. APPLIED TOP COAT PROTECTION IAW SRM 51-75-10.

Part: WEB — CORRODED (ZONE 100) · airframe 41,444 hrs · 22,512 cycles

AVIONICS COMPARTMENT LT SIDE WALL CORRODED AT WEB BETWEEN FR 14 AND 15 UNDER AIR CONDITION DUCT IN 3 PLACES. AFTER REMOVAL OF LEVEL 1 CORROSION, FOUND TO BE OUT LIMITS IAW SRM 51-74-10. FABRICATED 2 EA WEBS IAW DWG A21214044 AND 2 EA ANGLES IAW DWG A21214044. R & R 2 EA WEBS AND ANGLES AT FR 14-15L IAW SRM 51-40-21.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOOR PANEL 231NH CRUSHED IN TWO LOCATIONS AT CLEVIS ADAPTER CUTOUT. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ 25-005, REV J.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOOR PANEL 231AH CRUSHED, TWO LOCATIONS, AT CLEVIS ADAPTER CUTOUTS.

Part: SKIN — DAMAGED (RT ELEVATOR) · airframe 41,444 hrs · 22,512 cycles

RT ELEVATOR HAS TWO SMALL HOLES APPROX .2500" LONG X .1250" WIDE ON LOWER SIDE OF COMPOSITE. REPAIRED RT ELEVATOR LOWER SIDE BY CUTTING OUT DAMAGED SKIN, FILLING AND APPLYING REPAIR DOUBLER AND REPROTECTED COATING IAW SRM 55-21-11, PARA 5, I AND EA 6-5520-T0300120.

Part: WEB — CORRODED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOOR LT SHEAR WEB UPPER SURFACE CORRODED AT 2 PLACES AND AT FOUR BOLTS AROUND PLUGGED DUCT BETWEEN FR 11 AND FR 12. AFTER LEVEL 1 CORROSION REMOVAL ON WEB FOUND TO BE OUT OF MFG DWG TOLERANCE. MFG NEW WEB AND REPLACED IAW SRM 51-40-20, PAR 6, PAR 7 AND SRM 51-72-10, P1. REPLACED FOUR CORRODED BOLTS IAW SRM 51-40-21.

Part: ADAPTER — DAMAGED (FUSELAGE) · airframe 41,444 hrs · 22,512 cycles

IMPACT DAMAGE AT SCALLOP REMOVED CLEVIS ADAPTER BETWEEN SEAT TRACK 2R & 3R AT FR 54.2 IAW SRM 51-72-10 MATCH DRILLED REAMED NEW CLEVIS ADAPTER IAW SRM 51-40-44. INSTALLED NEW CLEVIS ADAPTER BETWEEN SEAT TRACK 2R & 3R AT FR 54.2 IAW A310-200 SRM 51-72-10. TOP COATED FASTENERS IAW SRM 51-75-10. APPLIED CPC TO REPAIR AREA IAW SRM 51-23-00.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · airframe 41,444 hrs · 22,512 cycles

AFT CARGO BAY LONGITUDINAL BEAM BETWEEN FR 63-64 HAS A 1" SQ AREA OF CORROSION AT LWR SURFACE LT SIDE. AFTER REMOVAL OF LEVEL 1 CORROSION FOUND AFT CARGO COMPT LONGITUDINAL BEAM BETWEEN FR 63-64, LT SIDE TO BE OUT OF LIMITS IAW DWG 17, A255-71979. R & R LONGITUDINAL BEAM BETWEEN FR 63-64, LT SIDE IAW 51-72-10, PGS 1- 3.

Part: SKIN — DENTED (FUSELAGE) · airframe 41,444 hrs · 22,512 cycles

FUSELAGE FRAMES 77-78, STRINGERS 27-28L, THREE DENTS MEASURED. DENTS NR 1 AND 3 OUT OF LIMITS IAW SRM 53-10-12, DIA 109, DENT NR 2 WITHIN LIMITS IAW SRM 53-10-12, DIA 109, FIG 110. NDT CONFIRMS NO CRACK CONDITION EXISTS INTERNAL AND EXTERNAL IAW NTM 51-10-07 ON ALL THREE CRACKS. REPAIRED TOW DENTS IAW SRM 53-10-12, FIG 225, REPROTECTED REPAIR AREA IAW SRM 51-75-10.

Part: TEE FITTING — CORRODED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

AVIONICS COMPARTMENT CEILING TEE FITTING AT SEAT TRACK 5L CORRODED AT FR 14 AROUND CLIPNUT. R & R TEE FITTING DUE TO BEYOND REPAIR IAW SRM 51-72-10, PAGE 2, PARA. 5. REPROTECTED FASTENERS IAW SRM 51-75-10.

Part: STRUCTURE — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

ON REMOVAL OF SEAT TRACK 5R FR 15A, FOUND THREE ELONGATED HOLES ON EXISTING MATING STRUCTURE (EXTRUSION) EXTRUSION BEYOND ECONOMICAL REPAIR. R & R EXTRUSION IAW SRM 51-72-10. REPROTECTED IAW SRM 51-75-10.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 41,444 hrs · 22,512 cycles

SEAT TRACK 5R CORRODED AT THE FLANGES AT FR 15A, CORROSION OUT OF LIMITS. MATERIAL LOSS IS .063". R & R SEAT TRACK 5R AT FR 15A.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOOR PANEL 262MF CRACKED ACROSS MID SECTION AT CLEVIS ADAPTER CUTOUT. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ 25-005, REV J.

Part: CARGO TRACK — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

MAIN DECK CARGO TRACK 3R HAS 2 INCH LONG DAMAGED AREA AT FR 74. FABRICATED, LOCATED, DRILLED, AND INSTALLED NEW SEAT TRACK SECTION 3R WITH SPLICES FROM FR73.5 TO 74.5 IN MDCC IAW SRM 51-72-10 PARA 6, SRM 51-40-21 PARA 6 & 8, AND SRM 53-10-16 PG 247-248. PROTECTED REPAIR IAW SRM 51-72-10 PARA 6 ITEM J.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FR 79-80 SEAT TRACK 4L HAS 2EA AREAS OF CORROSION AT UPPER SURFACE. REMOVED CORROSION & FOUND OUT OF LIIMITS IAW SRM 53-10-16, FIG 101. FABRICATED, DRILLED, LOCATED, AND INSTALLED NEW SEAT TRACK IAW SRM 53-10-16.

Part: FLOORBOARD — CRACKED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOORBOARD 231YH HAS AN 11 INCH CRACK AT CLEVIS CUT OUT. FABRICATED FLOORBOARD IAW DWG, SRZ 25-005, REV J.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOORBOARD 252WH UPPER SURFACE HAS 10 SQUARE INCHES CRUSHED & DAMAGED AT MID CLEVIS AND THREE WORN INSERTS. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-005, REV J.

Part: FLOORBOARD — DAMAGED · airframe 41,444 hrs · 22,512 cycles

FLOORBOARD 252RT UPPER SURFACE HAS THREE 1 SQUARE INCH PUNCTURE AND THREE WORN INSERTS. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-005, REV J.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

MAIN DECK CARGO FLOORBOARD 242EK BETWEEN SEAT TRACK 2R AND 3R, FR 50 AND FR 54, HAS TWO INSERTS PULLED OUT AND TWO AREAS OF IMPACT DAMAGE. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-005, REV J.

Part: FLOORBOARD — CRACKED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOORBOARD BETWEEN SEATS TRACKS 2R & 3R FR34 THRU FR 36 TOP SKIN CRACKED IN TWO PLACES. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-005, REV J.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOOR PANEL BETWEEN SEAT TRACKS 2R & 3R, FR33 & FR37 TOP SKIN CRACKED IN TWO PLACES. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ 25-005, REV J.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOOR PANEL BETWEEN TRACKS 2L AND 3L AND FR 51 AND FR 59 HAS TWO AREAS OF IMPACT DAMAGE. REMOVED AND REINSTALLED NEW FLOOR PANEL IAW AMM 53-10-25-04 FABRICATED NEW FLOOR PANEL IAW DWG 5RZ-25-005

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOOR PANEL BETWEEN TRACKS 2R & 3R AND FR 59 AND FR61 HAS THREE AREAS OF IMPACT DAMAGE. REMOVED AND REINSTALLED NEW FLOOR PANEL IAW 310 53-10-25-04 FABRICATED NEW FLOOR PANEL IAW DWG 5RZ -25-005

Part: FLOORBOARD — CRACKED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOORBOARD 252GF CRACKED AROUND CLEVIS ADAPTER, FABRICATED FLOORBOARD IAW DWG, SRZ 25-005, REV J.

Part: FLOORBOARD — DAMAGED · airframe 41,444 hrs · 22,512 cycles

FLOORBOARD 143DF HAS BROKEN OUT EDGE FILLER, 60". FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-005, REV J.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOORBOARD 242BF CRUSHED AT UPPER SIDE. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-005, REV J.

Part: FLOORBOARD — CRACKED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOORBOARD 221CF CRACKED AT TWO PLACES. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-005, REV J.

Part: FLOOR PANEL — CRACKED · airframe 41,444 hrs · 22,512 cycles

FLOOR PANEL 251NG TOP SKIN CRACKED. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ 25-005, REV J.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOOR PANEL 241MK TOP SKIN CRACKED. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ 25-005, REV J.

Part: ADAPTER — DAMAGED (FUSELAGE) · airframe 41,444 hrs · 22,512 cycles

MAIN DECK CARGO CLEVIS ADAPTER AT FR 36 BETWEEN SEAT TRACKS 4L AND 5L HAS IMPACT DAMAGE AT SCALLOP ONE SQUARE INCH. AFTER BLEND OUT OF DAMAGED AREA IAW SRM 51-73-10, FOUND TO BE OUT OF LIMITS IAW SRM 53-10-15, FIG 101. R & R CLEVIS ADAPTER IAW SRM 51-75-10.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOOR PANEL 242QJ HAS THREE PLACES WITH CRACKS IN TOP SKIN AND ONE MISSING INSERT. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ 25-005, REV J.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOORBOARD 242ZJ, CRUSHED AT UPPER SIDE. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ -25-005, REV J.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 41,444 hrs · 22,512 cycles

FLOORBOARD 242UJ CRUSHED AT UPPER SIDE. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ-25-005, REV J.

Part: OUTFLOW VALVE — INOPERATIVE (CABIN PRESSURE) · airframe 41,143 hrs · 22,307 cycles

RT NR 1 PRESSURE REGULATOR FAULT DURING CLIMB, FWD NR 1 OUTFLOW VALVE STUCK FULL OPEN. QRH NO HELP. CABIN WOULD NOT PRESSURIZE. TROUBLESHOT TO NR 1 FWD OUTFLOW VALVE STUCK OPEN. REPLACED OUTFLOW VALVE IAW AMM CH 21-31-12-04-01. OPS CKS GOOD. ACFT OK FOR SERVICE.

Part: CONTROLLER — FAULTED (CABIN PRESSURE) · airframe 41,065 hrs · 22,263 cycles

PASSING THROUGH 10,000 FT, RECEIVED CABIN ALT ALERT. DESCENDED TO 10,000. ACFT WOULD NOT PRESSURIZE IN AUTO WITH REGULATORS NR 1, NR 2 OR IN MANUAL POSITION. ALL DOORS & OUTFLOW VALVES INDICATED, SHOWED CLOSED. FOUND NR 2 CABIN PRESSURE CONTROLLER FAULTING AT WARN CKT STEP. REPLACED NR 2 CABIN PRESSURE CONTROLLER PER AMM 21-31-11-04 OPS WAS NORMAL PER MOCC.

Part: CONNECTOR — DIRTY (SELECTOR VALVE) · airframe 39,871 hrs · 21,461 cycles

AFTER TAKEOFF KRUGER FLAPS DID NOT RETRACT. CYCLED TO NO AVAIL. AFFECTED SURFACE DEACTIVATED IN RETRACTED POSITION. OBSERVE AFM PERFORMANCE LIMITATIONS FOR INOPERATIVE KRUGER FLAPS." REACTIVATED KRUEGER FLAPS IAW MM 27-87-00-09-0. FOUND CONNECTOR ON KRUEGER SELECTOR SOLENOID VALVE VERY DIRTY. CLEANED CONNECTOR IAW SMP. KRUEGER FLAPS OP'S AND LEAKED CHECKED GOOD 20TIMES IAW MM 27-87-00-05. OK FOR SERVICE.

Part: ANGLE — DAMAGED (ZONE 500) · airframe 39,485 hrs · 21,215 cycles

REFER TO EO 6-5710-3322 A3 PT3 & 4, FOUND THE FASTENER HOLES IN THE INTERNAL ANGLES ON THE CENTER WING BOX HAVE BEEN SECOND OVERSIZED AT PREVIOUS MAINTAINANCE CHECK PERFORMED ROTO-TEST INSPECTION REQUIREMENTS OF EO 6-5710-7-3322 A3 PT3 & 4, FOR THE HOLES WITH CRACK, REAMED THE HOLES TO CRACK FREE AND TO THE NEXT NOMINAL SIZE. FOR THE HOLES WITHOUT CRACK, REAMED THE HOLES TO THE NEXT NOMINAL SIZE . COLD WORKING FOR ALL THE FASTENER HOLES. INSTALLED RELATED FASTENERS. COMPLIED WITH EA 6-5710-141614.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

FWD CARGO - FUSELAGE SKIN INTERIOR SURFACE FOUND CORROSION BETWEEN FR38 12" TO FR38.1 , STGR50R-54L REMOVED CORROSION IAW SRM 51-74-10. REMAINING THICKNESS IS 0.035" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-08 COMPLIED WITH EA NR6-5310-141622.

Part: FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

LT WING RIB 5 MLG FWD LUG CORROSION EXCEED LIMIT COMPLIED WITH EA 6-5710-141613.

Part: BRACKET — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

2 EA REINFORCE BRACKETS FOUND CORROSION AT FR12A , STGR 40L-44L. REMOVED CORROSION IAW SRM 51-74-10. REMAINING THICKNESS IS 0.045" IAW NTM 51-10-04. NO CRACK FOUND IAW NTM 51-10-08 AND NTM 51-10-18 WITHIN ALLOWABLE DAMAGE IAW EA 6-5310-141616. RESTORED FINISH IAW SRM 51-75-10.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

FWD CARGO COMPT- 136AR ACCESS DOOR SURROUNDING CUTOUT SKIN INTERIOR SURFACE FOUND CORROSION (FR38.1-38.2 , STGR49R-54L) REMOVED CORROSION IAW SRM 51-74-10 THE REMAINING THICKNESS IS 0.040" PER NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-08 AND NTM 51-10-18 MADE THE REPAIR PARTS AND DOUBLERS IAW EA NR6-5310-141622. INSTALLED THE REPAIR PARTS AND DOUBLERS IAW EA NR 6-5310-141622. RESTORED FINISH IAW SRM 51-75-10.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

FWD TOILET SERVICE CUTOUT SKIN INTERNAL DOUBLER FOUND CORROSION AT FR12-12A , S37-44LT REMOVED CORROSION PER SRM 51-74-10 AND EA 6-5310-141616 THE REMAINING THICKNESS IS 0.060" PER NTM 51-10-04 NO CRACK FOUND PER NTM 51-10-08 AND NTM 51-10-18 WITHIN ALOWABLE DAMAGE PER EA 6-5310-141616 RESTORED FINISH PER SRM 51-75-10

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

FWD CARGO COMPT. - 134AR ACCESS DOOR SURROUNDING CUTOUT SKIN INTERIOR SURFACE FOUND CORROSION (FR23-FR24, STGR49R-52R) REMOVED CORROSION IAW SRM 51-74-10 REMAINING THINKNESS IS 0.033" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-08 MADE THE REPAIR PARTS IAW SRM 53-13-12-201 REPAIR NR 4 AND NR 6 INSTALLED THE REPAIR PARTS IAW SRM 51-40-21, RESTORED FINISH IAW SRM 51-75-10. THIS REPAIR MUST BE INSPECTED IAW IIR53-13-12-2-004-00/SRI.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT. - STRINGER 44L, FOUND CORRODED AT FR16A-18 BLENDED OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.110" IAW NTM 51-10-04. NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA6-5310-141616 RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

FWD CARGO COMPT. - FRAME WEB FOUND CORROSION AT STR49R-50R , FR37 BLENDED OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.055" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA6-5310-141626 FLAP PEENING IAW SRM 51-29-00 RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT - FRAME 13A, STRINGER 45L-44L, FRAME LWR FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.107" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616, RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT - FRAME 16A, STRINGER 45L-44L FRAME LWR FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10 REMAINING THINKNESS IS 0.089" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616, RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT - FRAME 14A, STRINGER 45L-44L FRAME LWR FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10 REMAINING THINKNESS IS 0.092" IAW NTM 51-10-04. NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616. RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT - FRAME 15A STRINGER 45L-44L FRAME LWR FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.107" IAW NTM 51-10-04. NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616. RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT - FR12A, S45-44L FRAME LOWER FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.112" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616. RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT - FRAME 16, STRINGER 45L-44L FRAME LWR FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10, REMAINING THINKNESS IS 0.085" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616, RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT - FRAME 15, S44L-37L FRAME BOTTOM FLANGE FOUND CORROSION BLENDED OUT, CORROSION IAW SRM 51-74-10 REMAINING THINKNESS IS 0.048" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616 RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT - FRAME 13, STINGER 44L-45L FRAME LOWER FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.048" IAW NTM 51-10-04. NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616, RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AV COMPT - FRAME 14, STRINGER 45L-44L FRAME LWR FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10 REMAINING THINKNESS IS 0.065" IAW NTM 51-10-04. NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616. RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT- FRAME 17, STRINGER 45L-44L FRAME LOWER FLANGE FOUND CORROSION BLENDED OUT, CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.195" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616, RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT-FRAME 14, S41-37L FRAME BOTTOM FLANGE FOUND CORROSION BLENDED OUT, CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.046" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA6-5310-141616 RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT- FRAME 15 STRINGER 45L-44L FRAME LWR FLANGE FOUND CORROSION BLENDED OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.078" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA6-5310-141616 RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT- FRAME 14, STRINGER 44L-42L FRAME BOTTOM FLANGE FOUND CORROSION BLENT OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.113" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 WITHIN ALLOWABLE DAMAGE IAW EA 6-5310-141616 RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT- FRAME 14A, STRINGER R41L-37L FRAME BOTTOM FLANGE FOUND CORROSION. REMOVED CORROSION IAW 51-74-10 REMAINING THINKNESS IS 0.046" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA NR 6-5310-141616. RESTORED FINISH IAW SRM 51-75-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,485 hrs · 21,215 cycles

AVIONICS COMPT- FRAME 14A, STRINGER 42L-44L FRAME BOTTOM FLANGE FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-74-10. REMAINING THINKNESS IS 0.048" IAW NTM 51-10-04 NO CRACK FOUND IAW NTM 51-10-18 AND NTM 51-10-08 WITHIN ALLOWABLE DAMAGE LIMIT IAW EA 6-5310-141616. RESTORED FINISH IAW SRM 51-75-10.

Part: NOSE COWL — DENTED (NR 2 ENGINE) · airframe 39,334 hrs · 21,117 cycles

DURING TAXI IN, ACFT SLID OF TAXITRACK ON TURN. ACFT HIT SNOWBANK WITH NOSE GEAR AND ENGINE NR 2. ENGINE NR 2 NOSE COWL HEAVILY DAMAGED. REQUIRES PYLON, NOSE LANDING GEAR AND ENGINE INSPECTION PERFORMED INSPECTION PER AMM 72-22-00-6 FOR RUBSTRIP DAMAGE. DAMAGE AT MAX MEASURED 1/8 INCH IN DEPTH. ALL WITHIN LIMITS PER INSPECTION ITEM E. PERFORMED INSPECTION PER AMM 05-51-27-0 FOR SIDE LOADS FROM IMPACT. PERFORMED PHASE 1 FROM INSPECTION, NO DAMAGE FOUND. PERFORMED INSPECTION PER AMM 05-51-11-0, ENGINE AND NOSE GEAR RELATED PART FOR DAMAGE FROM IMPACT. REPLACED DAMAGED NOSECOWL PER AMM 71-11-00-4. OK FOR SERVICE.

Part: CLAMP — DELAMINATED (RUDDER DUPLEX) · airframe 37,662 hrs · 20,106 cycles

RUDDER CHECK ON FLIGHT CONTROL TEST UNSAT, RUDDER TRAVEL RESTRICTED ON ECAM, RUDDER PEDALS STUCK IN HALF DOWN POSITION, BOTH LEFT AND RIGHT SIDE, WOULD NOT RETURN TO CENTER POSITION FOUND DUPLEX ROD LWR SEPARATION CLAMP (P/N A2727024500200) RUBBER DISBONDED ALLOWING CLAMP TO FALL INTO LWR RUDDER QUADRANT. REMOVED AND REPLACED CLAMP IAW A310-200 AMM 27-21-17-4 01.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 37,658 hrs · 20,102 cycles

AVIONICS COMPARTMENT FR 16A- FR17, OUTBOARD SIDE STR 44 LT 4 SQ IN CORROSION REMOVED 9 FASTENERS FOR FOM PER A310-200 SRM 51-40-21. REMOVED CORROSION PER A310-200 SRM 51-74-10. MATERIAL BEFORE .063 AFTER .041 LOSS OF .021 FOUND TO BE OUT OF LIMITS PER A310-SRM 53-10-00. COMPLIED WITH EA 6-5310-110480. REINSTALLED FASTENERS PER A310 SRM 51-40-21.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 37,658 hrs · 20,102 cycles

MDCC SEAT TRACK R3 FRAME 33- FR 45 7EA AREAS CORROSION 10 SQ IN. REMOVED CORROSION (7EACH AREAS) IAW A310-200 SRM 51-74-10. FAB`D 1 SEATTRACK FROM FRAME 36- 38.2; FAB`D 2 REPAIR ANGLES IAW A310-200 SRM 53-10-16; ALODINED, PRIMED, TOP COATED PER A310-200 SRM 51-75-10.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

A 2.0 SQ INCH AREA OF CORROSION EXIST AT MDCC SEAT TRACK L-6 FRAME 34, 1 SEAT TRACK AND 4 REPAIR ANGLES IAW A310 SRM 53-10-16. ALODINED PRIMED AND TOP COATED IAW SRM 51-75-10. INSTALLED SEAT TRACK AND 4 REPAIR ANGLES IAW A310 SRM 53-10-16.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

AFT CARGO PIT/CABIN FLOORBEAM 58 CRACKED JUST BELOW PREVIOUSLY REPAIR RBL6 FEET APPROX TOTAL CRACK LENGTH 1.0 INCH PREVIOUSLY INSTALLED REPAIR NO IAW A310 SRM 53-10-15 FIG 206. REMOVED EXISTING, REPAIR AND REPAIRED IAW FEDEX EA6-5310-110482.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN FLOORBEAM FRAME 36 BETWEEN SEAT TRACKS 2 AND 3 RT FWD SIDE UPPER FLANGE HAS 1 REPAIR ANGLE MEASURING 8.6" BY 2.4" AND TWO .250 STOP DRILLED HOLES, THE INBOARD STOP DRILL HOLE HAS A CRACK CONTINUING PAST THE DRILL STOP (0.5 INCH CRACK) PREVIOUSLY INSTALLED REPAIR FOUND NOT TO BE IAW FEDEX EA 6-5321-45448. REMOVED EXISTING PREVIOUS REPAIR AND REPAIRED PER FEDEX EA6-5310-110483. REMOVED AND REINSTALLED FLOOR PANEL 232XH IAW A310/200 AMM SUPPLEMENT 53-10-23.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

FLOORBEAM 36, LT BETWEEN SEAT TRACKS NR 2 LT NR 3 LT - FWD SIDE OF FLOORBEAM, VERTICAL STIFFENER AT UPPER END HAS A .500 INCH HORIZONTAL CRACK. REMOVED FLOOR BOARD (2EA) IAW A310/200 SRM 51-40-21. FABRICATED REPAIR ANGLES AND REPAIRED FLOORBEAM 36 IAW A310/200 SRM 53-10-15. INSTALLED FLOORBOARDS IAW A310/200 SRM 51-40-21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

A 1.5 SQ INCH AREA OF CORROSION EXIST AT MDCC SEAT TRACK L-5 FRAME 34 FAVED 1 SEAT TRACK AND 4 REPAIR ANGLES PER SRM 53-10-16, ALODINED PRIMED TOP COATED PER SRM 51-75-10. INSTALLED SEAT TRACK AND 4 REPAIR ANGLES IAW SRM 53-10-16.

Part: WINDOW FRAME — CHAFED (COCKPIT) · airframe 37,658 hrs · 20,102 cycles

1ST OFFICER SLIDING WINDOW ASSY FRAME HAS CHAFED AREA FWD END 2 PLACES COMPLIED WITH FEDEX EA6-5610-110455 PART 1.

Part: RIB — DAMAGED (VERTICAL STAB) · airframe 37,658 hrs · 20,102 cycles

VERTICAL STAB RT SIDE AT INTERSECTION OF ACCESS PANELS 323AL AND 323BR APPROX 2.5 INCHES FROM VERTICAL LOWER RIB EDGE 2 EACH WEAR MARKS APPROX .200 IN DIAMETER AND .050 DEEP BLENDED CHAF MARKS IAW A310 SRM 51-73-10 CHECKED LIMITS IAW A310 SRM 55-30-00 (OUT OF LIMITS). CUT OUT DAMAGE IAW A310 SRM 55-31-12 PB201 VERIFIED MATERIAL ID IAW A310 SRM 55-31-12. FABRICATED DOUBLER IAW A310 SRM 55-31-12. ALODINED DOUBLER IAW A310 SRM 55-31-*12 PRIMED DOUBLER IAW A310 SRM 55-31-12. INSTALLED DOUBLER IAW A310 SRM 55-31-12, HEAT TREATED RIVETS IAW A310 SRM 51-25-00 TOP COATED TO MATCH IAW A310 SRM 51-75-10.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

AFT CARGO PIT/CABIN FLOORBEAM 54.2 CRACKED RLL 2.5 FEET APPROX TOTAL CRACKED LENGTH .25 REPAIRED FLOORBEAM 54.2 PER FEDEX EA6-5310-110456 AND AIRBUS REPAIR DRAWING R53706311.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

FWD CARGO COMP MDCC FLOORBEAM C23 HAS A CRACK BETWEEN SEAT TRACKS 2R AND 3R, CRACK LENGTH .125. FAB`D 2 REPAIR ANGLES PER A310/200 SRM SUPPLEMENT 53-10-15 ALODINED; PRIMED, TOP COATED PER SRM51-75-10; INSTALLED 2 REPAIR ANGLES PER SRM SUPPLEMENT 53-10-15.

Part: RIB — DAMAGED (VERTICAL STAB) · airframe 37,658 hrs · 20,102 cycles

VERTICAL STAB RT SIDE AT INTERSECTION OF ACCESS PANELS 323AL AND 323BR APPROX 2.5 INCHES FROM VERTICAL LOWER RIB EDGE 2 EACH WEAR MARKS APPROX .200 IN DIAMETER AND .050 DEEP BLENDED CHAF MARKS IAW A310 SRM 51-73-10 CHECKED LIMITS IA W A310 SRM 55-30-00 (OUT OF LIMITS). CUT OUT DAMAGE IAW A310 SRM 55-31-12 PB201 VERIFIED MATERIAL ID IAW A310 SRM 55-31-12. FABRICATED DOUBLER IAW A310 SRM 55-31-12. ALODINED DOUBLER IAW A310 SRM 55-31-*12 PRIMED DOUBLER IAW A310 SRM 55-31-12. INSTALLED DOUBLER IAW A310 SRM 55-31-12. HEAT TREATED RIVETS IAW A310 SRM 51-25-00. TOPCOATED TO MATCH IAW A310 SRM 51-75-10.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

AFT CARGO PIT/CABIN FLOORBEAM 61 CRACKED AT APPROX 6 FEET RLL TOTAL CRACK LENGTH .30 APPROX COMPLIED WITH FEDEX EA6-5310-11460.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

DUMMY TRACK IN FWD PIT FR 38.2 TO FR 40 TH NR 5 WORN .040 REMOVED AND REPLACED 2 FLOOR BOARDS IAW A310/200 AMM53-10-25-4. REMOVED AND REINSTALLED 1 DUMMY TRACK SECTION AND ATTACHING PARTS IAW A310 SRM 51-40-21. REPAIRED HOLE IN DUMMY SEAT TRACK IAW A310/200 SRM53-15-16.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

6 AREAS OF CORROSION EXIST AT MDCC SEAT TRACK L-3 BETWEEN FRAMES 74 THRU 79 EACH DEFECTED AREA MEASURE 1.5 SQ INCHES CORROSION REMOVED IAW A310/200 SRM 51-74-10 ONE SPOT FOUND OUT OF LIMITS IAW A310/200 SRM 53-10-16 DAMAGED AREA TRIMMED OUT IAW SRM 53-10-16. REPLACED PARTS, FABED IAW SRM 53-10-16, NEW PARTS ALODINED IAW A310/200 SRM 51-21-10 PARTS, PROTECTED IAW A310/200 SRM53-10-16 SEAT TRACK CUT AND SPLICED AT FR 77 10" -80/82.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

3 AREAS OF CORROSION EXIST AT MDCC SEAT TRACK NR 1 DEFECTED AREA MEASURES 7.5 SQ IN FROM FRAMES 76 THRU 79. REMOVED CORROSION 3 AREAS A, B, C, IAW A310/200 SRM51-74-10 MEASURED MATERIAL LOSS .075 AT AREA A FR-76 MATERIAL LOSS .009 AT AREA B FR77-78 MATERIAL LOSS .003 AERA C FR79 AND CHECKED ALLOWABLE LIMITS IAW A310/200 SRM53-10-16 FIG 101 AREA A AT FR76. FOUND TO BE OUT OF LIMITS AND AREAS B AND C FR 77-78-79 FOUND TO BE WITHIN LIMITS IAW A310/200 SRM 53-10-16 FIG 101. RESTORED SURFACE PROTECTION TO AREA B/C IAW A310/200 SRM 51-23-10 AND SRM51-75-10, REPAIRED AREA A IAW A310 SRM53-10-16.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 37,658 hrs · 20,102 cycles

FWD CARGO COMP FLOORBEAM C38 HAS A CRACK BETWEEN SEAT TRACKS 4L AND 5L REMOVED FLOOR PNL 231VF TO BETWEEN FR 37-40 TO FOM REPAIR PER A310/200 SRM 51-40-12 REWORKED THE MILLED MERTRIAL STIFFENER TO REMOVE CRACK PER A310/200 SRM SUPPLEMENT 53-10-15 FIG 201 NDT PER NTM51-10-08 SHOWS NO CRACK INDICATION AFTER REWORK, ALODINE PRIMED AND TOPCOATED MATING SURFACE AND 2 EACH ANGLES PER A310/200 SRM 51-21-10 AND SRM 51-75-10. INSTALLED 2 EACH ANGLES PER A310/200 SRM 53-10-15 AND SRM51-40-21. TOPCOATED REPAIR AREA PER A310/200 SRM 51-75-10. INSTALLED FLOOR PNL 231VF PER A310/200 SRM 51-40-21.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 37,658 hrs · 20,102 cycles

6 AREAS OF CORROSION EXIST AT MDCC SEAT TRACK NR 1 BETWEEN FRAMES 61 THRU 71/72 EACH AREA MEASURES 1.25 SQ INCHES. REMOVED CORROSION ON SEAT TRACK IAW A310-200 SRM 51-74-10 3 AREAS FOUND TO BE OUT OF LIMITS IAW A310-200 SRM 53-10-16 PB 101. ALODINED, PRIMED, AND TOPCOATED, 3 AREAS IAW A310-200 SRM 51-21-10 AND 51-75-10. REPLACED TRACK SECTION FOUND TO BE OUT OF LIMITS IAW A310-200 SRM SUP 53-10-16 FIG 202.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 37,658 hrs · 20,102 cycles

FWD CARGO COMP MDCC FLOORBEAM C33 HAS A CRACK BETWEEN SEAT TRACKS 4L AND 5L, CRACK LENGTH .125. REMOVED CRACK FROM FLOORBEAM PER SRM 53-10-15; FABBED 2 REPAIR ANGLES PER SRM 50-40-21; ALODINED, PRIMED, TOPCOATED PER SRM 51-75-10; INSTALLED REPAIR PARTS PER SRM 53-10-15 FIG 20, SH 2A.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 37,658 hrs · 20,102 cycles

6 AREAS OF CORROSION EXIST AT MDCC SEAT TRACK L-2 BETWEEN FRAMES 63 AND 64 THRU FRAME 70, DEFECTED AREA MEASURES 10 SQ INCHES DUE TO AREA OF CORROSION FOUND TO BE OUT OF LIMITS. REPAIRED SEAT TRACK BY SPLICING IN NEW TRACK SECTION IAW A310-200 SRM 53-10-16.

Part: WARNING LIGHT — ILLUMINATED (FUEL FILTER) · airframe 34,726 hrs · 18,546 cycles

FUEL FILTER CLOG LIGHT ON T/O AT 60KTS. REJECTED T/O. ALL INDICATIONS NORMAL ON 60 PERCENT RUNUP FOR ENG ANTI-ICE. ECAM WARNING STOPPED STOPPED AS SOON AS POWER WAS REDUCED. I THINK IT WAS NR 1 ENG, BUT AM NO T POSITIVE. ENT BY: 001941 RPT BY: 119121 FACT 24OCT04 15:12 RNO R GRD RUN TO 65 PERCENT WITH NO PROBLEM. REMOVED AND REPLACED 1 ENG. FUEL FILTER ASSY FOR T/S. LEAK AND OPS CKS, OK ON GRD RUN. MM 73-12-03. ENT BY: 001941 RPT BY: 001941

Part: FRAME — DENTED (FUSELAGE) · airframe 34,693 hrs · 18,523 cycles

N00197, INCOMING CONDITION, JUST FORWARD OF FR 10 LT SIDE IS A DENT (2 INCH X 2 INCH X .090 INCH) WHICH IS OUT OF LIMITS IAW SRM TABLE 53-10-00 TABLE 102. INSTALLED REPAIR DOUBLER, FILLER IAW EA 6-5330-55382 AND SRM 51-71-70, EO-356-09-04-007-2/-4, DWG R536 11016, AND RAS AS/285/2004.

Part: FRAME — DENTED (FUSELAGE) · airframe 34,693 hrs · 18,523 cycles

N00196 INCOMING CONDITION, JUST FORWARD OF FRAME 10 RT SIDE IS A DENT 1 INCH X .5 INCH X .050 INCH WHICH IS OUT OF LIMITS IAW SRM 53-10-00 TABLE 102. INSTALLED REPAIR DOUBLER AND FILLER C/W EA 6-5330-55381 AND SRM 51- 71-70, TECHNICAL REQUEST OE-356-09-04-007-2/-4 AND MFG DWG R536 11020.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 34,693 hrs · 18,523 cycles

MDCC 67 INCHES TO RIGHT OF CTR FR 54.3 FLOORBEAM CRACKED .4 INCH ON FWD AND AFT SIDE. REPAIRED AREA IAW A310/200 SRM 53-10-15, FIG 201.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 34,693 hrs · 18,523 cycles

MDCC 62 INCHES TO LEFT OF CTR FR 16A IS CORROSION ON TRACK 5R. REMOVED AND REPLACED SEAT TRACK IAW A310/200 SRM 53-10-16.

Part: THRESHOLD — CORRODED (ZONE 100) · corrosion level 2 · airframe 34,693 hrs · 18,523 cycles

AFT PIT AREA (BULK) THRESHOLD BETWEEN FS 67 AND FS 69 FOR BULK DOOR CUTOUT HAS CORROSION ON FITTINGS UNDER AND AROUND NUT PLATES AND FASTENERS. REMOVED CORROSION MATERIAL LOSS IN AREA MINUS LONGITUDINAL SECTION IS .008 INCH AND FOUND TO BE IN LIMITS IAW SRM 51-74-10 AND 53-17-13. REMOVED LONGITUDINAL SECTION DUE TO OUT OF LIMITS MATERIAL LOSS NOTED .019, AND REPLACED AND TREATED AREAS AND SECTION ALL IAW SRM 51-74-10, 53-17-13, AND 51-40-20.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 34,693 hrs · 18,523 cycles

MAIN CABIN FR52 SEAT DUMMY TRACK (CLS ADAPTOR) AT TRACK 2R, 24 INCHES TO RT OF CTRIS, CRACKED UNDERNEATH AT BEND RADIUS APPROX 4 IN LONG. REMOVED AND REPLACED CLS ADAPTOR FR52 2R IN MAIN CABIN IAW SRM A310/200 51-40-21.

Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 34,362 hrs · 18,318 cycles

ON DEPARTURE ECAM ALERT FLAPS SYS 2 FAULT. RECYCLED TO NO AVAIL. CATEGORY: C EXPIRATION: 01JUN04 "MEL 27-51-01-01: NR 2 SLATS / FLAPS CONTROL COMPUTER INOP. C/W PROCEDURES IN MEL 27-51-01-01, SYSTEM TESTS ARE OK. REMOVED & REPLACED NR 2 SFCC IAW A310 MM 27-51-18-4. OPS CHECKED GOOD.

Part: IRU — FAILED (NR 1) · airframe 34,209 hrs · 18,237 cycles

AFTER T/O 1 IRU FAILED, 2 IRU WAS ALREADY MEL'D INOP. RETURN TO DFW. REMOVED AND REPLACED THE 1 IRU PER MM 34-25-00 -05-1, PERFORMED IRS SYS ADJ/TEST IN CONJUNCTION WITH WRI 34-43-6941 (IRU 3) AND WRI 34-43-6937 (IRU 2). ALL IRU'S TESTED NORMAL. PERFORMED AFS/LAND TEST, TEST PASSED. A/C CAT STATUS PLACED INTO A/C CAT II; AP1 & 2 CK CAT III.

Part: SEAT TRACK — DAMAGED (CARGO BAY) · airframe 32,989 hrs · 17,622 cycles

FLOOR DAMAGED ON UPPER DECK AT POSITION 6R.DAMAGE CAUSED BY BALLAST PALLET HITTING LOCK DAMAGING FLOOR. NO RESTRICTION FLOOR DAMAGE ON UPPER DECK..REF E.A 6-5321-71244, OK FOR SCV TEMPORARY REPAIR ACCOMPLISHED PER E.A. 6-5321-71244. 0FACT 02JUN03 18:06 CWF U REPAIRED DAMAGED FLOOR STRUCTURE BY REPLACING THE BROKEN SEAT TRACK ADAPTER AND THE BROKEN FLOOR PANEL IAW EA 6-5321-71244 PART 2

Part: FITTING — CORRODED · airframe 31,766 hrs · 16,886 cycles

#1 RUDDER HINGE FITTING HAS CORROSION AT LWR HINGE PIN ATTACH. R&R FITTING.

Part: HYDRAULIC SYSTEM — FAILED (YELLOW SYS) · airframe 31,095 hrs · 16,478 cycles

ON CLIMB LOST YELLOW SYS HYD QTY WENT TO RED DOT. PERF EMERGENCY CHECKLIST PER ECAM AND RED TABS.

Part: PITOT — CLOGGED (LEFT)

99-161 - REJ T/O AT 90KTS DUE TO NO AIRSPEED IND ON CAPT PFD (SPD TAPE). CLEARED PITOT SYS TUBE WITH AIR AND FOUND BUGS. AIRSPD IND NORM PER A310 MM 34-10-00. AC OK FOR SERVICE.

Part: WASHER — OUT OF POSITION (GEARBOX)

98-0133, NR 1 OIL QTY WAS 16 QTS ON GRND AT LEVEL OFF FL 310 12 QTY. STARTED TIMING THE DROP AT 7 QTS, LOST 1 QT PER 7 MIN. PRECAUTIONARY LANDING IN DEN. WHEN WE LANDED ANALOG AND ECAM SHOWED 4 QTS. REMOVED WASHER LODGED BETWEEN SEAL AND AFT CASE OF TOWER SHAFT GEAR BOX. LEAK CHECKS OK. SERVICED WITH 11 QTS OIL.