N419FE

Part: OUTFLOW VALVE — STUCK (CABIN PRESSURE) · airframe 43,725 hrs · 21,216 cycles

NR 1 FWD OUTFLOW VALVE STUCK FULL OPEN COULD NOT MAINTAIN CABIN PRESSURIZATION. TURNING OFF NR 1, REGULATOR, NO HELP. R & R OUTFLOW VALVE.

Part: PRIORITY VALVE — CRACKED (HYD SYSTEM) · airframe 43,487 hrs · 21,030 cycles

YELLOW HYDRAULIC SYSTEM RSVR LO LEVEL. FOUND PRIORITY VALVE 27-3148 BROKEN. REPLACED PRIORITY VALVE 273179 IAW AMM 27-44-16-04. SYSTEM OP CHECKED NORMAL. SERVICED YELLOW SYSTEM HYDRAULICS IAW AMM 12-12-29-00-0.

Part: POWER UNIT — MALFUNCTIONED (TE FLAPS) · airframe 43,184 hrs · 20,808 cycles

FLAP SYSTEM 1&2 FAULTED AT FLAPS 0. CHECKED SFCC'S BOTH SHOW ASYMMETRY FAULTS. REMOVED FPPU AND NULLED R & R IAW MM 27-56-00-05. RESET FAULTS ON BOTH SFCC'S AND PERFORMED BITE TEST IAW MM 27-51-00-05-0, NO FAULTS OCCURED. RAN FLAPS FULL TRAVEL UP AND DOWN SEVERAL CYCLES. FLAPS CYCLED WITH NO FAULTS. ACFT OK FOR SERVICE.

Part: BRAKE — FAILED (NR 2 MLG) · airframe 43,024 hrs · 20,719 cycles

ON WALK AROUNG FOUND NR 2 MLG TIRE ABOUT TO COME OFF, BRAKE IS ALL BROKE UP AND HUB COVER IS CRACKED. REPLACED LT BOGIE, NR 1 AND NR 2 WHEEL ASSY, NR 2 BRAKE ASSY, AND NR 1 AND NR 2 WHEEL SPEED TRANSDUCERS. FINAL CLOSED.

Part: TRANSMITTER — FAILED (OIL PRESSURE) · airframe 43,016 hrs · 20,716 cycles

REJECTED TAKEOFF FOR ENGINE NR 2 HIGH OIL PRESSURE REPEAT WRITE UP REJECT APPROX 85KTS. REPLACED NR 2 ENG. OIL PRESSURE TRANSMITTER IAW MM 79-33-11-04. LEAK AND OPS CKS GOOD. RAN ENG IAW JRH AND OIL PSI WAS 56PSI AT IDLE. RAN AT 75%N2 AND PSI WAS 58PSI. OK FOR SERVICE.

Part: DOUBLER — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,835 hrs · 20,595 cycles

FOUND CORROSION ON LT FUSELAGE FWD LAV SERVICE DOOR CUTOUT AT LOWER EDGE (APPR. .5" SQ IN). REMOVED CORROSION FROM LAV SERVICE PANEL BOX AND FOUND IT TO BE OUT OF LIMIT IAW SRM 53-10-00 FIG 106. REMOVED SKIN REINFORCING DOUBLER ON INTERNAL CUTOUT AREA DUE TO CORROSION. REMOVED CORROSION AND TREATED METAL REF SRM 51-74-10, PAR 5 & SRM 51-72-10. REPLACED SKIN REINFORCING DOUBLER AND LAV SERVICE BOX IAW SRM 51-40-21, 51-72-10 AND DWG R53600013. REINSTALLED LAV DRAIN LINES AND LEAK CHECKED, FOUND TO BE SATISFACTORY IAW AMM 38-31-17-4. ALL WORK IS ON FILE AT CWF UNDER WO 00048350. THIS IS A MAJOR REPAIR IAW GMM6-2-100.

Part: DOUBLER — CORRODED (ZONE 500) · corrosion level 2 · airframe 42,835 hrs · 20,595 cycles

NR 1 PYLON SPIGOT FITTING -TO -WING DOUBLER HAS CORROSION ON OTBD SIDE (APPROX 2" SQ, VISIBLE) BETWEEN OTBD SPIGOT ATTACH BOLTS. ALSO THIS DOUBLER HAD A GOUGE ON L/E - REF.N01074. REMOVED NR1 PYLON FROM LT WING TO ACCESS SPIGOT FITTING IAW AMM 54-50-00-4, REMOVED SPIGOT FITTING FROM LT WING IAW SRM 51-72-10 AND AB DWG A57150751. REPAIRED REINFORCING WING DOUBLER BY REMOVING CORROSION AND BLENDING OUT THE GOUGE ON THE L/E (REF N01074) IAW EA 6-5710-135242, REF OE-345-06-10- 001& OE-345-06-10-001A AND REPAIR DESIGN APPROVAL SHEET-RAS/BAE/1013534/2010 ISSUE A. REINSTALLED SPIGOT FITTING ON LT WING AND NR 1 PYLON ON LT WING IAW AMM 54-50-00-4, SRM 51-72-10 AND AB DWG A57150751. THIS IS A MAJOR REPAIR IAW GMM 6-2-100. THIS WORK IS ON FILE AT CWF UNDER WO 00048350.

Part: RIB — CORRODED (ZONE 600) · corrosion level 2 · airframe 42,835 hrs · 20,595 cycles

REWORK OF RT MLG GEAR SUPPORT RIB 5 BUSHES (WRONG OD). FOUND CORROSION IN THE BORES AND ON THE SPOT FACES OF THE MLG GEAR SUPPORT RIB 5 , AFT PINTLE FWD LUG ON BOTH WINGS. REMOVED CORROSION IAW REF EO 6-5710-7-5010, C2, PT8, AND EA 6-5710-135239 AND THE W/C N01963 AND THE PRINCIPALS OF R57249121 AND THE OPERATORS DAMAGE REPORTS. MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME — DAMAGED (ZONE 200) · airframe 42,835 hrs · 20,595 cycles

MAIN DECK CARGO COMPT, FRAME 38.1 HAS 1 EA. DOUBLE DRILLED HOLE IN FRAME, ABOVE STRINGER 23, RT SIDE. REPAIRED RT FRAME 38.1 AT STRINGER 20R TO 21R IAW EA 6-5310-135249, EADS.

Part: BEAM — CHAFED (ZONE 400) · airframe 42,835 hrs · 20,595 cycles

FOUND A CHAFED AREA ON THE EDGE OF LIGHTING HOLE ON CANTILEVER BEAM ON NR 1 PYLON, 5" LT OF CTR LINE AT RIB J4. REPAIRED NR1 PYLON CANTILEVER BEAM AT RIB J4 BY REMOVING SHARP EDGES AND ADDING A DOUBLER IAW EA 6-5450-135245. ALL WORK WAS DOCUMENTED ON N00729 UNDER WO NR 00048350. REF DRW A54612175, A54610997 AND RAS70536549/004/2010 ISSUE A, DATED 23 JUL 2010.

Part: FLOOR SUPPORT — CORRODED (CABIN) · airframe 42,835 hrs · 20,595 cycles

FLOOR SUPPORT CHANNEL BETWEEN FR 14 AND FR 14C INBD OF FLOORBOARD 221EF HAS EXFOLIATION, CORROSION ABOUT 8 X 1 SQ INCH. REMOVED CORROSION IAW SRM 51-74-10 , CHECKED LIMITS IAW SRM 53-12-15, FOUND OUT OF LIMITS. REPAIRED SUPPORT IAW SRM 53-12-15, PAGE 230A/230B, FIG 207.

Part: SKIN — FAILED (ZONE 100) · corrosion level 2 · airframe 42,835 hrs · 20,595 cycles

REPAIR DOUBLER INSTALLED ON LOWER LT SKIN OF FUSELAGE AT FRAME 69 AND BETWEEN STRINGERS 54 RT TO 56 LT WAS EVALUATED AND IT WAS DETERMINED NOT TO BE INSTALLED IAW SRM 53-10-12, FIG 216, SHEETS 1 AND 2, PAGES 262 TO 272. EVALUATION REVEALED THAT THE DOUBLER INSTALLED DID NOT HAVE THE CORRECT AMOUNT OF FASTENER ROWS AND THE MATERIAL OF THE DOUBLER WAS THE INCORRECT THICKNESS. REMOVED DOUBLER REPAIR AND FILLER AT FRAME 69 AND BETWEEN STRINGERS 54 RT TO 56 LT LOCATION AND INSTALLED THE CORRECT REPAIR DOUBLER AND FILLER IAW SRM 53-10-12, FIG 216, SHEETS 1 AND 2, PAGES 262 TO 270. THIS REPAIR IS CLASSIFIED AS A MAJOR IAW GMM 6-2-100.

Part: SKIN — DAMAGED (ZONE 100) · airframe 42,835 hrs · 20,595 cycles

FOUND REPAIR DOUBLER ON LT FUSELAGE SKIN AT FRAME 11A, AFT OF THE CAPTAIN FIXED WINDOW TO BE THE INCORRECT THICKNESS AND LOCATION IAW EA 6-5330-113170. REMOVED EXISTING REPAIR DOUBLER, TRIMMED CUT OUT AS REQUIRED AND REPAIRED SKIN IAW SRM 53-12-12, FIG 202, SHEET 1 AND 3, PAGES 211 TO218. THIS REPAIR WAS CLASSIFIED AS A MAJOR IAW GMM 6-2-100.

Part: FLOOR SUPPORT — CRACKED (ZONE 100) · airframe 42,835 hrs · 20,595 cycles

FOUND .250" CRACK IN CROSSBEAM AT FRAME 55/58 BETWEEN SEAT TRACK 4R AND SEAT TRACK 5R ON AFT SIDE, 1.5" BELOW UPPER CAP. REMOVED DAMAGED AREA OF CROSSBEAM AT FRAME 55/58 BETWEEN SEAT TRACKS 4R AND 5R IAW SRM 53-10-15 PAGE 259, HAD NDT PERFORM INSPECTION IAW NTM 51-10-08, NO CRACK INDICATIONS FOUND. FABBED REPAIR ANGLE AND INSTALLED REPAIR IAW SRM 53-10-15, PAGE 253 THRU 259. FOUND REPAIR TO BE MAJOR IAW GMM 6-2-100.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 42,835 hrs · 20,595 cycles

FWD CARGO COMPT. MAIN DECK FLOORBEAM FR 36 , 0.25 INCH CRACK ON FRAME JUST BELOW UPPER T CAP, BETWEEN SEAT TRACKS 4L-5L CUT OUT CRACKAND BLENDED AREA IAW A310 SRM 51-27-11, NDT CHECKED IAW NTM FOR CRACKS NO CRACK NOTED. REPAIRED CROSS BEAM IAW A310 SRM 53-10-15FIG 203 PAGE 249/250

Part: ACTUATOR — LEAKING (KRUEGER FLAPS) · airframe 42,580 hrs · 20,478 cycles

GREEN SYS HYD FLUID DELETED TO RED DOT. FOLLOWED QRH. REMOVED LT KRUEGER FLAP ACTUATOR IAW MM 27-88-11-4. REPLACED LT KRUEGER FLAP ACTUATOR IAW MM 27-88-11-4.

Part: COMPUTER — MALFUNCTIONED (SLAT/FLAPS) · airframe 41,911 hrs · 20,165 cycles

ON CLIMB OUT, ECAM DISPLAY "KRUGER NOT RETRACTED" CLEARED ECAM. APPLIED QRH PROCEDURES RETURNED TO DEPARTURE DUE TO INSUFFICIENT FUEL TO DESTINATION. PERFORMED SFCC BITE TEST FOUND NR 1 SFCC AND POSITON SW 49CV (LT KRUEGER) DEFECTIVE. R & R NR 1 SFCC AND POSITON SWITCH 49CV IAW AMM 27-51-18-4 & 27-89-12-4. PERFORMED BITE TEST /OPS TESTED IAW AMM 27-51-00-5. NO FAULTS FOUND. ACFT OK FOR SERVICE.

Part: CROSSBEAM — CRACKED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

CROSS-BEAM CRACKED AT FRAME 54.3 BETWEEN Y-1450 AND Y-1950. THE CROSS-BEAM WAS REPAIRED IAW FEDEX EA 6-5310-113718.

Part: DOOR FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,758 hrs · 19,520 cycles

AFT CARGO COMPARTMENT DOOR FRAME, CORROSION AT FRAME 59A BETWEEN STRG29-30 RT. REPAIRED IAW SRM 53-17-13 FIG 210A.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,758 hrs · 19,520 cycles

CORROSION FOUND AT AFT CARGO COMPARTMENT DOOR FRAME - FR59A, BETWEEN STRG 26 RT AND 29 RT. AFT CARGO COMPARTMENT DOOR FRAME WAS REPAIRED BETWEEN STR 26-29 RT IAW FEDEX EA 6-5310-113171.

Part: DOOR FRAME — CRACKED (ZONE 800) · airframe 40,758 hrs · 19,520 cycles

BULK CARGO COMPARTMENT DOOR FWD FRAME WITH CRACK. DOOR FWD FRAME WAS REPLACED IAW SRM 51-72-10.

Part: ANGLE — CORRODED (ZONE 300) · corrosion level 2 · airframe 40,758 hrs · 19,520 cycles

RT THS, SPOT OF CORROSION AT UPPER ANGLE AT AREA OF RIB 18/19. IT WAS REPAIRED IAW SRM 55-11-21 FIG 221.

Part: ANGLE — CORRODED (ZONE 300) · corrosion level 2 · airframe 40,758 hrs · 19,520 cycles

RT THS, SPOT OF CORROSION AT UPPER ANGLE AT AREA OF RIB 14/15. IT WAS REPAIRED IAW SRM 55-11-21 FIG 215.

Part: DOOR FRAME — CRACKED (ZONE 800) · airframe 40,758 hrs · 19,520 cycles

BULK CARGO COMPARTMENT DOOR FWD LOWER CORNER WITH CRACK ON EDGE MEMBER. DOOR FWD LOWER CORNER EDGE MEMBER WAS REPLACED IAW SRM 51-72-10.

Part: SKIN — FAILED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON RT FUSELAGE FR78 STA 4241 STRG 24-27 RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO SONFORM TO AN SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 53-10-12 FIG 225 SHEET 1.

Part: DOOR FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,758 hrs · 19,520 cycles

AFT CARGO COMPARTMENT DOOR FRAME FOUND CORRODED, FR59A, BETWEEN STRG27 RT AND 36 RT. THE AFFECTED FRAME WAS REPAIRED BETWEEN STRG 27-36RT.

Part: PANEL — DELAMINATED (ZONE 600) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON RT WING LOWER SURFACE T/E, STA 1787/1835, RIB 29-30. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUS REPAIR EVALUATED AND FOUND DEBONDED. RT WING T/E LOWER SURFACE WAS REPAIRED IAW FEDEX EA 6-5710-113165.

Part: SKIN — MISREPAIRED (ZONE 800) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON FWD CARGO DOOR, ON INNER SKIN BETWEEN BEAM 4 AND 5, AT FR 20A-21. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR WAS EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. SKIN PANEL WAS REPLACED IAW SRM 51-72-10.

Part: BEAM — MISREPAIRED (ZONE 800) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON FWD CARGO DOOR, LOWER CORNER OF FR 20A BTW BEAM 4 AND BEAM 5. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. SECTION EDGE WAS REPLACED IAW SRM 51-72-10.

Part: SEAT TRACK — CRACKED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

DUMMY TRACK NR 5 RT AT Y-1959 BETWEEN FR 54 AND FR 54.2 CRACKED AT LOCKS. THE DUMMY TRACK WAS REPLACED IAW SRM 51-72-10.

Part: SKIN — FAILED (ZONE 600) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON RT FLAP INBD LOWER SKIN, NEAR TRACK NR 2. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 57-52-12 FIG 205.

Part: SEAT TRACK — CRACKED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

CABIN, DUMMY TRACK NR 3 RT (Y-953) CRACKED BETWEEN FR 54 AND FR 54.2. THE PART WAS REPLACED IAW SRM 51-72-10.

Part: SKIN — DAMAGED (TE FLAP) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON RT OUTBD FLAP, UPPER SKIN, MAIN SPAR RIB 3. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT CONFORM WITH SRM REPAIR. NEW REPAIR WAS ACCOMPLISHED IAW FEDEX EA 6-5710-113163.

Part: SKIN — FAILED (TE FLAP) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON LT OUTBOARD FLAP, UPPER SKIN, MAIN SPAR RIB 2. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR WAS EVALUATED AND FOUND NOT CONFORM TO SRM. A NEW REPAIR WAS ACCOMPLISHED IAW FEDEX EA-6-5710-113163.

Part: SEAT TRACK — CRACKED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

DUMMY TRACK NR 1 AT Y0 BETWEEN FR 54 AND FR 54.2 WITH CRACK AT LOCKS. THE PART WAS REPLACED PER SRM 51-72-10.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON LT INBD LOWER SKIN, T/E RIB 2-4. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND EXISTING REPAIR WAS FOUND DEBONDED AND WAS REMOVED. NEW REPAIR WAS INSTALLED PER EA 6-5710-113162.

Part: SEAT TRACK — WORN (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

CABIN DUMMY TRACK NR 5 LT AT Y1959 BETWEEN FR 54 AND FR 54.2 WITH WEAR OF 1.7MM AT AFT HOLE ATTACHMENT AND WITH CRACKS AT LOCKS. THE AFFECTED PART WAS REPLACED IAW SRM 51-72-10.

Part: SKIN — FAILED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON RT FUSELAGE AFT BULK DOOR STA 3726/3779, FR 69-70, STRG 41-43 RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 53-10-12 FIG 224 SHEET1.

Part: BEAM — MISREPAIRED (ZONE 800) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON RT SIDE OF BULK DOOR BETWEEN BEAM 4 AND BEAM 5, STA 3620, FR67. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR WAS ACCOMPLISHED PER SRM 52-30-00.

Part: SKIN — FAILED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON RT FUSELAGE BELOW AFT CARGO DOOR AT STA 3302/3355, BETWEEN STRG 45-48 RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. THE REPAIR WAS EVALUATED AND FOUND NOT TO CONFORM TO EXISTING FEDEX EA 6-5330-87763. NEW REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH FEDEX EA 6-5330-87763.

Part: SKIN — FAILED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON RT FUSELAGE, STA 1764/1817, BETWEEN STRG 31- 33RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR WAS ACCOMPLISHED IAW SRM 53-10-12 FIG 225 SHEET 1 AND FIG 217.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON FWD CARGO DOOR SKIN, FR 25-25A BETWEEN BEAM 3 AND BEAM 4. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. THE REPAIR WAS EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. A NEW REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH FEDEX ENGINEERING AUTHORIZATION 6-5230-113174.

Part: SKIN — FAILED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

PREVIOUS REPAIR FOUND LOCATED ON RT FUSELAGE STA 1764/1817, STRG 34-36 RT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION OR IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. NEW REPAIR WAS ACCOMPLISHED PER SRM 53-10-12 FIG 225 SHEET 1.

Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,758 hrs · 19,520 cycles

AFT SEAT TRACK AT Y 1390 WITH CORROSION OUT OF SRM ALLOWABLE VALUES NEXT TO FR68. SEAT TRACK REPAIRED IAW SRM 53-16-10, FIG 202.

Part: SKIN — DELAMINATED (ZONE 600) · airframe 40,758 hrs · 19,520 cycles

RT WING INBD FLAP T/E SKIN W/DEBONDS (UPPER SKIN RIB 14-15) REPAIRED IAW SRM 57-52-12.

Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,758 hrs · 19,520 cycles

AFT MDCC - SEAT TRACK Y0 WITH CORROSION OUT OF VALUES BETWEEN FR74 AND FR75. SEAT TRACK REPAIRED IN ACCORDANCE WITH SRM SUPP 53-10-16 FIG 202 BETWEEN FR 72 AND FR 73.

Part: SKIN — CORRODED (ZONE 600) · corrosion level 2 · airframe 40,764 hrs · 19,526 cycles

RT WING FRONT SPAR WITH CORROSION BETWEEN STA 482/RIB 8 AND STA 935/RIB 15. RT WING UPPER SKIN REPAIRED IAW FEDEX EA 6-5710-113179.

Part: DUMMY RAIL — WORN (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

DUMMY TRACK NR 6 RT BETWEEN FR 54 AND 54.2 WITH WEAR OF 1.1MM AT AFT ATTACHMENT HOLES. DUMMY TRACK REPAIRED IAW SRM 53-15-16, FIG 203.

Part: SKIN — DEBONDED (ZONE 600) · airframe 40,758 hrs · 19,520 cycles

RT WING, OUTBD FLAP RIB 10 T/E DEBONDING THE REPAIR WAS ACCOMPLISHED IAW FEDEX EA 6-5710-113163.

Part: SKIN — DENTED (ZONE 200) · airframe 40,758 hrs · 19,520 cycles

FUSELAGE DENT BETWEEN FR 10A AND FR 11 AT 300MM TO THE RIGHT OF CENTERLINE, AT Z 2120. IT WAS REPAIRED IN ACCORDANCE WITH SRM 53-12-12 FIG 201 SHEET 1.

Part: SKIN — DENTED (ZONE 200) · airframe 40,758 hrs · 19,520 cycles

FUSELAGE DENT BETWEEN FR10A AND FR11 AT 300MM TO THE RIGHT OF CENTERLINE, AT Z 2120. IT WAS REPAIRED IN ACCORDANCE WITH SRM 53-12-12 FIG 201 SHEET 1.

Part: SKIN — DAMAGED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

N00180 STATIC DISCHARGE PEAK SITUATED BETWEEN FR2 AND FR3 NEXT TO Z-1051. IT WAS REPAIRED IN ACCORDANCE WITH 53-10-12 FIG 221, SHEET 1.

Part: FLOORBEAM — CRACKED (ZONE 100) · airframe 40,758 hrs · 19,520 cycles

MDCC CROSSBEAM AT FR33 Y-690 FOUND CRACKED. A REPAIR IN ACCORDANCE WITH SRM SUPP 53-10-15 FIGURE 201 "SHEET A" WAS ACCOMPLISHED.

Part: HANDLE — UNSECURE (DOOR) · airframe 40,614 hrs · 19,421 cycles

AT APPROX 85KIAS, RIGHT FORWARD COMPT DOOR AMBER LIGHT CAME ON WITH SINGLE CHIME, ABORTED T/O. RETURNED TO RAMP. FOUND RT ACCESS DOOR BETWEEN AVIONICS COMP AND FWD LWR CARGO HOLD DOOR HANDLE NOT UP COMPLETELY AND SECURE. MOVED HANDLE UP INTO LOCKED SECURE POS. ALL IND BACK TO NML. NO HISTORY ON DOOR OR DOOR INDICATION.

Part: COMPENSATOR — MALFUNCTIONED (BRAKE TEMP) · airframe 39,489 hrs · 18,520 cycles

DURING L/G RETRACTION AT FLL, ALL 4 RT SIDE BRAKE TEMP INDICATORS SHOWED 700*ITH CORRESPONDING CAUTION. LOWERED GEAR FOR COOLING AFTER APPROX 1 MIN CAUTION WENT AWAY AND BRAKES TEMP INDICATED FROM 125 TO 150 (LEFT MAIN TEMPS 50- 65). ALL OTHER INDICATIONS NORMAL. ON TOUCHDOWN RT WHEEL TEMP INDICATIONS SHOWED 700 THEN RETURNED TO NORMAL INDICATIONS. DURING T/S FOUND 4GW TO BE BAD. 4GW NEEDS TO BE REPLACED PER A310- 200 AMM ATA 32-47-13-4. REMOVED AND REPLACED RT BRAKE TEMP COMPENSATOR IAW A310 AMM 32-47-13-4. OPS CHECK GOOD AT THIS TIME. OFF MFG 35-242-100 POS 2SRL 242002046 TAG 7A2184ON MFG 35-242-100SRL BB0091 TAG 152A69S.

Part: SKIN — DAMAGED (LT ELEVATOR) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. LT ELEVATOR UPPER SURFACE T/E 6' O/B FROM I/B END (ITEM 35 OF LIST). REPAIRED ELEVATOR IAW E NR #6-5520-87201. REPAIR IS CLASSIFIED AS MINOR AS PER EA6-5520-87201 AND FEDEX GMM 6-2-100.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. FLOORBEAM NR 35 C R OF CENTER LINE. COMPLIED WITH FEDEX EA NR 6-5310-87772 AND CLASSIFIED AS A MINOR REPAIR PER FEDEX EA NR 6-5310-87772 AND FEDEX GMM 6-2-100.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. FLOORBEAM NR 34 R L OF CENTER LINE. COMPLIED WITH FEDEX EA NR 6-5310-87772 AND CLASSIFIED AS A MINOR REPAIR PER FEDEX EA NR 6-5310-87772 AND FEDEX GMM 6-2-100.

Part: SKIN — DELAMINATED (LT ELEVATOR) · airframe 38,799 hrs · 18,108 cycles

LT ELEVATOR TOP SURFACE STA 473/ER19 HAS 3EA AREAS OF CORROSION. COMPLIED WITH FEDEX EA NR 6-5520-87163.

Part: SKIN — DELAMINATED (LT ELEVATOR) · airframe 38,799 hrs · 18,108 cycles

LT ELEVATOR TOP SURFACE BETWEEN STA468/ER16 AND STA474/ER20 IS DELAMINATION. COMPLIED WITH EA NR 6-5520-87163.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. ITEM NR 22 ON LIST FUSELAGE LOWER RT SIDE AT FR 58 THIS REPAIR WAS ACCOMPLISHED IAW FEDEX EA NR 6-5530-49627A REVISE DATE 04/25/00. THIS REPAIR IS CLASSED AS A MAJOR REPAIR AND HAS FOLLOW UP ACTION REQUIRED ALSO FRAME AND STRINGER LOCATIONS HAVE BEEN CORRECTED TO MATCH EXISTING DOUBLER INSTALLATION, REFERENCE EA6-5330-87763 PT1.

Part: LATCH — DAMAGED (THRUST REVERSER) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. NR 2 ENGINE NACELLE O/B T/R BELOW AFT UPPER LATCH. (ITEM NR 51 OF LIST) REMOVED EXISTING REPAIR DOUBLER PER A310 SRM 51-40-21 AND COMPLIED WITH FEDEX EA # 6-7830-87224, THIS REPAIR IS CLASSIFIED AS MINOR AS PER FEDEX GMM 6-2-100.

Part: RIB — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

VERTICAL STAB RT SIDE 6" BELOW RIB 21 TO RIB 1 HAS CORROSION ON REAR CHORD SPAR CHORD FLANGE IN FASTERNER HOLES, AROUND FASTERNER HOLE AREA EXTENDING TO STAB SKIN AS MARKED. REMOVED NUPLATES IAW A310-200 SRM 51-40-21. REMOVED CORROSION IAW A310-200 SRM 51-74-10. CHECKED LIMITS IAW A310-200 SRM 55-30-00 TABLE 101. ALL AREAS ARE IN LIMITS EXCEPT FOR HOLE NR 15,18, 25 IAW SRM 55-30-00. HOLES 15,18 25 ARE IN LIMITS IAW OE-345-03-05-023. TREATED, PRIMED TOP COATED IAW SRM 51-23-20 51-75-10. REINSTALLED NUT PLATES IAW A310-200 SRM 51-40-21. COMPLIED WITH EA6-5510-87215.

Part: DOOR — CORRODED (ZONE 400) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

NR 1 PYLON PANEL 416AR HAS AREA AROUND SCOOP AND EXTENDING UNDER SCOOP WITH CORROSION. REMOVED AND REPLACED DOOR ASSY PER A310-200 AMM 54-50-00-4, DUE TO CORROSION OUT OF LIMITS PER A310-200 SRM 54-50-00 TABLE 102, SHEET 2.

Part: WEDGE — DAMAGED (T/E FLAP) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION, LT WING COMPOSITE REPAIR LOWER SURFACE INBD T/E FLAP WEDGE 5 INCH FWD OF AFT EDGE AND 28 INCH O/B OF I/B EDGE. COMPLIED WITH EA6-5750-87746 PT1 NO ANOMALIES NOTED AS PER FEDEX GMM 6-2-100, FIG 1. THIS REPAIR IS CLASSIFIED AS MINOR.

Part: STRUCTURE — DAMAGED (T/E FLAP) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR AND MINOR CLASSIFICATION. RT WING RT I/B T/E LOWER SURFACE AFT OF NR 2 FLAP TRACK BEAM. COMPLIED WITH EA 6-5750-87747 PART 1. NO DEFECTS NOTED PER NTM 51-10-08. REPAIR IS CLASSIFIED AS A MINOR REPAIR PER FEDEX GMM 6-2-100.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MAIN DECK CARGO FR12 STA 1067 LONGERON 2ND FROM CENTER IS CORRODED. REMOVED CORROSION IAW A310 SRM 53-10-00. REMOVED & REPLACED DAMAGED SECTION IAW A310 SRM 51-72-10.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2

A/C COMPARTMENT FRAME 42, 5 O'CLOCK POSITION FRAME IS CORRODED. REMOVED CORROSION AND REPAIRED FR 42 AT 5 O'CLOCK POSITION IAW EA 6-5310-87135.

Part: SKIN — MISREPAIRED (RUDDER) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. FLUSH REPAIR LT SIDE RUDDER LOWER T/E. ITEM 36 OF LIST. FLUSH REPAIR IS FOUND TO BE NOT CONFORM WITH A310-200 SRM 55-41-0. REMOVED IMPROPER REPAIR AND INSTALL PROPER REPAIR IAW A310-200 SRM 55-41-12 REPAIR 7. REINSTALLED LIGHTING STRIP A310-200 SRM 55-41-12 FIG 207. RESTORED SURFACE PROTECTION AFTER COMPOSITE WORK IAW A310-200 SRM 51-75-10. REPAIR IS CLASSIFIED AS MINOR IAW FEDEX GMM 6-2-100.

Part: STRUCTURE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

BETWEEN FRAME 91 AND 95 (AFT OF THS BOX) BILGE AREA AND AROUND ACCESS THRESHOLD 300 SQ INCHES OF BARE METAL WITH LITE SURFACE CORROISION. REMOVED AND REPLACED CORRODED STRUCTURE AT FR91 TO 95 AND STR 16 LT IAW A310 SRM 51-40-21 AND DWG'S A53989325, A53989300, A53989559, A53989330, A53986001.

Part: SKIN — MISREPAIRED (FUSLEAGE) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. ITEM NR 24 ON LIST. FUSELAGE DOUBLER LOWER RT SIDE AT FR70. REMOVED UNAPPROVED REPAIR IAW A310-200 SRM 51-40-21, INSTALLED NEW REPAIR IAW A310-200 SRM 53-10-12 FIG 224, REPAIR IS DETERMINED TO BE MINOR IAW FEDEX GMM 6-2-100.

Part: PANEL — DAMAGED (NR 2 NACELLE)

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. NR 2 ENGINE NACELLE ENGINE EXHAUST TO NACELLE TRANSITION PANEL 30 INCHES FWD OF AFT. ITEM 46 OF LIST. REMOVED DOUBLER IAW A310-200 SRM 51-4-21 TO EVALUATE REPAIR FOR SRM CONFORMANCE AND DETERMINE MAJOR/MINOR REPAIR CLASSIFICATION, REINSTALLED DOUBLER IAW A310-200 SRM 51-40-21 AND EA 6-5480-87206.

Part: DOUBLER — DAMAGED (FUSLEAGE) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OF MINOR CLASSIFICATION. ITEM 12 ON LIST. FUSELAGE FLUSH ROUND DOUBLER LOWER LT SIDE FR35 INSTALLED NEW REPAIR IAW A310 SRM 53-10-12, AND A310 AMM 25-54-10-2, REPAIR IS CLASSIFIED AS MINOR AS PER FEDEX GMM 6-2-100.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

MAIN CABIN FRAME 34 TO 37 SEAT TRACK YB77 HAS 2EA AREAS OF CORROSION NR 4 SEAT TRACK RT. REMOVED CORROSION IAW A310 SRM 51-74-10, OUT OF LIMITS IAW A310 SRM 53-10-16 FIG 101. FABBED NEW REPAIR SECTION OF SEAT TRACK IAW A310 SRM 53-10-16 FIG 208. REMOVED AND REINSTALLED SPICES AND SUPPORT BRACKET IAW A310-200 SRM 51-72-10. REMOVE BAD SECTION OF TRACK FROM FR33.5 TO 36.5 AND INSTALLED NEW REPAIR SECTION IAW A310-200 SRM 51-72-10 AND 53-10-16 FIG 208.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

AFTER REMOVAL OF SEAT TRACK NR 3 RT BETWEEN FRAMES 45-54. FOUND BRACE FITTING AT FRAME 47/48 ATTACH POINT CRACKED 1.2 INCH LONG ON INBOARD SIDE OF TRACK. REPAIRED IAW EA 6-5310-79122.

Part: STRINGER — DAMAGED (FUSLEAGE) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. TAIL CONE DOUBLER LT SIDE AT FR 102. ITEM 34 OF LIST. REMOVED FABRICATED AND REPLACED STRINGER. REMOVED AND FABRICATED NEW SKIN DOUBLER. REPAIRED BUTT JOINT PER A310 SRM 51-40-21, SRM 53-19-12, SRM 51-71-40, ALODINED, PRIMED AND TOP COATED PER A310 SRM 51-75-10. REPAIR IS CLASSIFIED AS MINOR AS PER FEDEX GMM 6-2-100.

Part: SKIN PANEL — CRACKED (LT WING) · airframe 38,799 hrs · 18,108 cycles

LEFT WING, LEADING EDGE PANEL LAND, JUST FWD OF FLAP TRACK NR 5 PANEL LAND AND REPAIR CRACKED (MARKED). REMOVED LANDING PLATE IAW A310 SRM 51-40-2, FABBED NEW PLATE IAW DRAWING A572443982, TREATED, PRIMED AND TOPCOATED IAW A310 SRM 51-75-10. REINSTALLED LANDING PLATE IAW A310 SRM 51-75-10 AND 51-40-21 ON LT WING L/E UNDER PANEL 524EB.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

FR 38 MDCC FLOORBEAM LT OF CTR AT 38 INCHES, AFTER REMOVAL OF CLS ADAPTER TO FACILITATE FRAME REPAIR, FASTENER HOLES FOUND TO BE OUT OF ROUND, FWD INBOARD HOLE ON CLS ADAPTOR AFT OUTBD, AND ALSO 2 DRILL STARTS. BLENDED OUT DRILL STARTS PER A310 SRM 51-73-10, NDT FOR CRACKS NONE FOUND PER A310 NTM 51-10-08, MEASURED DEPTH FOUND A .019 LOSS AND WITHIN LIMITS PER A310 SRM 53-10-15 FIG 101 SHEET 2, DRILLED 2 EA HOLES TO 2ND OVER 1/4 INCH HILOCKS AND ALL OTHER HOLE DRILLED TO .247 NOMENIAL 1/4" HILOCK IN CONJUCTION WITH N00681 FLOORBEAM REPAIR AND CLS ADAPTER REMOVAL AND REPLACEMENT PER A310 SRM SUPPLEMENT 53-10-15 FIG 201 SHEET 6A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

REF. SNRM# N00525 MAIN CABIN FRAME 37 CLS ADAPTER -Y040 IS GOUGED AND CRACKED (BETWEEN SEAT TRACK 2 AND 3 LT). REMOVED AND REPLACED CLS ADAPTER PER A310 SRM 51-72-10 TREATED, PRIMED AND TOP COATED AREA AND FASTENERS PER A310-200 SRM 51-75-10.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MAIN DECK CARGO ZONE 240 LT NR4 SEAT TRACK, FR 54 AND FR 54.1 CORROSION PROPAGATED ON SEAT TRACK FLANGE SCREW HOLES 2-AREAS. BLENDED CORROSION IAW A310-200 SRM 51-74-10, 53-10-16, CHECKED LIMITS AND NOTED FOR MATERIAL LOSS, DUE TO CORROISION OUT OF LIMITS REMOVED AND REPLACED SEAT TRACK IN MAIN DECK CARGO ZONE 240 LT SEAT TRACK AT FR54 AND 54.1 IAW A310-200 SRM 51-72-10.

Part: SEAT TRACK — GOUGED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MDCC SONE 241, RT NR 2 SEATRACK, FR54.2 HAS 1-EA GOUGES AREA ON SCALOPE HOLE. REMOVED DAMAGED SEAT TRACK FITTING AT MDCC ZONE 241 RT NR 2 FR54.2 AND REPLACED WITH NEW SEAT TRACK FITTING P/N A5381114620000 IAW A310 SRM 51-40-21.

Part: LONGERON — CORRODED (ZONE 200) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MAIN DECK CARGO FR 14 LONGERON 4TH FROM CENTERLINE CORRODED OUT OF LIMITS. REMOVED AND REPLACED LONGERON A53610797234 WITH NEW PART IAW A310 SRM 51-72-10.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

FWD PIT BAY CEILING AREA FR 38, 38 INCHES TO LT OF CTR FLOORBEAM IS CRACKED. REWORKED AREA TO INSTALL 2EA ANGLE REPAIRS PER A310-200 SRM 53-10-15. CLEAN, TREATED AND PRIMED AREA PER A310-200 SRM 51-21-10, INSTALLED 2EA REPAIR ANGLES PER A310-200 SRM 53-10-15 FIG 201. TREATED, PRIMED AND TOP COATED PER A310-200 SRM 51-21-10.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MAIN DECK CARGO COMPT LEFT NR 3 SEAT TRACK, FR48, FR49.5, FR51.5, FR53.5, 4 EA AREAS OF CORROSION INSIDE SCALLOP HOLES AS MARKED. REMOVED AND REPLACED SEAT TRACK SECTION BETWEEN FRAME 50.5 TO 54 IAW A310-200 SRM 53-10-16.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MAIN DECK CARGO COMPT RT NR 2 SEAT TRACK, FR45.5, FR46, FR46.5, FR47, FR49, FR52.5, FR53, FR54 CORROSION INSIDE SCALOPE HOLES, 9 AREAS AS MARKED. REMOVED CORROSION IAW A310 SRM 51-74-10. TRACK IS OUT OF LIMITS IAW A310 SRM 53-10-16 FIG 101. FABRICATED NEW SEAT TRACK FROM FR45 TO 54 IAW A310 DWG A538-11922. REMOVED AND REINSTALLED CLS ADAPTERS AND REMOVED OLD TRACK AND INSTALLED NEW TRACK IAW A310 SRM 51-72-10.

Part: PANEL — DAMAGED (LT WING) · airframe 38,799 hrs · 18,108 cycles

LT WING TO FUSELAGE FILLET PANEL 3RD PANEL FWD OF T/E. REMOVED PANEL 577AL DUE TO NON CONFORMANCE IAW A310 AMM 53-10-63-4. REPAIRED PANEL IAW A310 SRM 51-77-10. TREATED PANEL IAW A310 SRM 51-75-10. INSTALLED PANEL 577AL IAW A310 AMM 53-10-63-4, COMPLETED REPAIR CONFORM TO ALL FAA APPROVED DATA.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

AFT CARGO COMPT AFT OF FR 601 ON RT STG 50 HAS AREA OF CORROSION. REMOVED 9EA RIVETS PER A310-200 SRM 51-40-21. REMOVED CORRSION PER A310-200 SRM 51-71-10, NDT FOR MAT LOSS FOUND TO BE OUT OF LIMITS PER A310-200 SRM 53-10-00. CUT OUT DAMAGED SECTION PER A310-200 SRM 53-10-14. TREATED AND PRIMED TOP COATED FILLER AND COUPULING PER A310-200 SRM 51-75-10. INSTALLED STG FILLER AND STG REPAIR COUPLING PER A310-200 SRM 51-40-21.

Part: PANEL — CRACKED (RT WING) · airframe 38,799 hrs · 18,108 cycles

RIGHT WING T/E PANEL LANDING FOR ACCESS PANEL 675CB HAS 1.0 INCH CRACK. REMOVED AND REPLACED LANDING PLATE IAW SRM 51-72-10.

Part: FITTING — CORRODED (TAIL CONE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

BILGE AREA FR91, 33 INCHES TO LEFT OF CTR STG 29L FITTING FOR TAIL CONE HAS CORROSION AROUND FASTENER HOLE EXTENDING UNDER FASTENER AND FASTENER IS CORRODED. REMOVED BOLT, CLEANED CORROSION AROUND FASTENER HOLE HAD NDT VERIFY THICKNESS AND FOUND IT TO BE WITHIN LIMITS IAW A310 SRM 53-10-00 PAGE 106 TABLE 102, TOP COATED AREA IAW A310 SRM 51-75-00 AND INSTALLED SERVICEABLE HARDWARE IAW A310 SRM 51-40-21.

Part: COVER — CORRODED (ZONE 100) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

CORROSION TWO PLACES AROUND RIVETS, FWD CARGO UNDER FLOOR AREA, FRAME 38.1 BETWEEN STRINGERS 44R AND 45R, FWD FLANGE OF WATER SERVICE PANEL. REMOVED AND REPLACED POTABLE WATER PAN AT FR38.1 IAW A310 SRM 51-72-10 AND SRM 51-40-21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MAIN DECK CARGO COMP'T LEFT NR 5 SEAT TRACK, FR49, FR51.5, FR54, CORROSION INSIDE SCALLOP HOLES, 3-AREAS. REMOVED AND REPLACED SEAT TRACK SECTION BETWEEN FRAMES 50.5 AND 54 IAW A310-200 SRM 53-10-16.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MAIN DECK CARGO COMPT RT NR 3 SEAT TRACK FR45.5, FR47, FR48, FR49, FR51.5, FR52.5, CORROSION INSIDE SCALLOP HOLES 8-AERAS. REMOVED CORROSION IAW A310-200 SRM 51-74-10. TRACK WAS OUT OF LIMITS IAW A310-20 SRM 53-10-16 FIG 101. REMOVED AND REINSTALLED COUPLERS AND ATTACH FITTING IAW A310-200 SRM 51-72-10. REMOVED AND REPLACED BAD TRACK WITH NEW TRACK IAW A310-200 SRM 51-72-10. REINSTALLED CLS ADAPTERS IAW A310-200 SRM 51-72-10.

Part: INTERCOSTAL — BENT (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

BETWEEN FR85 AND FR86 STG 35R (RT) 2EA CAPS ON INTERCOSTAL ARE BENT. INTERCOSTAL WEB & ANGLE FOUND TO BE CRACKED. REMOVED AND REPLACED WITH NEW WEB & ANGLE IAW A310 SRM 51-40-21.

Part: FRAME — CRACKED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

MAIN CABIN FRAME 37 CLS ADAPTER -YD40 IS GOUGED AND CRACKED (BETWEEN SEAT TRACK 2 AND 3 LT). REMOVED AND REPLACED CLS ADAPTER PER A310 SRM 51-72-10. TREATED, PRIMED AND TOP COATED AREA AND FASTENERS PER A310-200 SRM 51-75-10.

Part: WEDGE — DAMAGED (TE FLAP) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. LT WING REPAIR LOWER SURFACE I/B TRAILING EDGE FLAP FWD OF THE TRAILING EDGE WEDGE AND AFT OF NR 2 FLAP TRACK BEAM, ITEM 57 OF LIST. LT WING I/B FLAP LOWER SURFACE, AND AFT OF NR 2 TRACK BEAM REPAIR DOUBLER IS RIVETED ACCESS PANEL ON I/B FLAP ASSY DWG AND FOUND TO BE IN CONFORMANCE WITH AIRBUS DWG A579- 70100.

Part: SKIN — DAMAGED (TE FLAP) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. RT WING RT INBOARD TRAILING EDGE FLAP LOWER SURFACE AFT AND INBOARD OF NR 2 TRACK BEAM, ITEM 43 OF LIST. RT WING RT INBOARD TRAILING EDGE FLAP LOWER SUFACE AFT AND I/B OF NR 2 FLAP TRACK BEAM DOUBLER IS RIVETED ACCESS PANEL ON I/B FLAP ASSY AND FOUND TO BE IN CONFORMANCE WITH AIRBUS DWG A579-70100.

Part: SEAT TRACK — CORRODED (CARGO DECK) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

M-DECK CARGO COMP'T RT NR 4 SEAT TRACK FR46, FR47, FR48, FR49.5, FR50.5, FR51.3, FR52.5, FR53.4, CORROSION INSIDE SCALOPE HOLES, 9-AREAS. REMOVED CORROSION IAW A310-200 SRM 51-74-10, OUT OF LIMITS IAW SRM 53-10-16 FIG 101. FABBED NEW SEAT TRACK IAW DWG A538-11923. REMOVED AND REINSTALLED CLS ADAPTERS AT FR46 TO FR54 IAW A310-200 SRM 51-72-10. REMOVED BAD SECTION OF TRACK & INSTALL NEW SEAT TRACK FROM FR46 TO 54 IAW SRM A310-200 51-72-10.

Part: ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

FRAME 86 JUST ABOVE THS JACKSCREW 1 AREA OF CORROSION BETWEEN 2EA FASTENERS ON L-ANGLE. REMOVED CORROSION IAW A310 SRM 51-73-10. EVALUATED AREA AND FOUND IT TO BE OUT OF LIMITS IAW A310 SRM 53010-00. REMOVED AND REPLACED L-ANGLE IAW A310 SRM 51-40-21. TREATED BARE METAL IAW A310 SRM 51-75-10. (SEE JPF)

Part: SKIN — DAMAGED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. ITEM NR 27 OF LIST FUSELAGE DOUBLER TOP RT SIDE AT FR 78. FUSELAGE DOUBLER ON TOP RT SIDE AT FRAME 78 FOUND TO BE IN CONFORMANCE WITH A310-200 SRM 53-10-12 FIG 216 THIS REPAIR IS BOUND TO INSPECTIONS AT DEFINED INTERVALS IN SRI 53-10-12-2-001. (SEE JPF).

Part: DOOR — CRACKED (ZONE 100) · airframe 38,799 hrs · 18,108 cycles

AFTER REMOVAL OF PANEL 143GL ON SNRM N00035, FOUND RAM AIR EXHAUST DOOR SURROUND BOX TO HAVE A 10 INCH CRACK ON INBD SIDE UPPER RADIUS. REMOVED AND REPLACED LT RAM AIR EXHAUST.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

NR 1 SEAT TRACK, FR61.5, FR 62.5, FR64.5, FR65.5, FR66.5, FR70.5, HAS 9 AREAS CORROSION INSIDE SCALLOPED HOLES. REMOVED CORROSION IAW SRM 51-74-10, SEVERAL AREAS OUT OF LIMITS IAW SRM 53-10-16 FIG 601. CUT OUT 2EA SEAT TRACKS FROM 2EA SEAT TRACKS IAW SRM 51-10-16 FIG 208, INSTALLED 2EA TRACKS AND SPLICES IAW 51-10-16 FIG 208.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION ITEM NR 5 FUSELAGE, L-SHAPED DOUBLER RT SIDE ABOVE RT WING AT FR44 L-SHAPE DOUBLER, RT SIDE ABOVE WING AT FRAME A310-200 SRM 53-15-12 FIG 1 SHEET 9.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

RIGHT HORIZONTAL STAB L/E LWR CHORD FLANGE FROM STA 158 RIB 5 TO RIB 18 HAS CORROSION ON TOP AND BOTTOM SURFACE EXTENDING UNDER NUT PLATES. REMOVED CORROSION IAW A310-200 SRM 51-74-10 CHECKED LIMITS IAW A310-200 SRM 55-10-00. STRAPED & SHIMED AREA IAW A310-200 SRM 51-11-21. TREATED, PRIMED & TOPCOATED IAW A310-200 SRM 51-21-10 & 51-23-10. RIB 5 TO RIB 13 & RIB 14 TO RIB 18 IS WITHIN LIMITS IAW A310-200 SRM 55-10-00.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. ITEM NR 9 ON LIST FUSELAGE, REPAIR DOUBLER, LOWER RT SIDE, AT FR 26/32 REPAIR DOUBLER FOUND TO BE IN CONFORMANCE WITH A310-200 SRM 53-10-12 FIG 205. ACTUAL LOCATION OF DOUBLER FRAME 26/32 AT STR 31 RT SIDE.

Part: ACCESS PANEL — DAMAGED (CARGO DOOR) · airframe 38,799 hrs · 18,108 cycles

LOWER FUSELAGE FWD CARGO DOOR ACCESS PANEL NR 811BR HAS (2EA) CRACKS AT FASTENER HOLE. REPLACED WITH NEW ACCESS PANEL DUE TO EXCESSIVE REPAIRS AND PANEL DEFORMATION IAW A310-200 SRM 51-71-30. PAINTED IAW A310 SRM 51-75-10.

Part: SEAT TRACK — GOUGED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

RT NR 2 SEATRACK FR 54.2, HAS 1 GOUGED AREA ON SCALOPE HOLE. REMOVED DAMAGED SEAT TRACK FITTING AT MDCC SONE 241 RT NR 2 FR 54.2 AND REPLACED WITH NEWS SEAT TRACK FITTING P/N A5381114620000 IAW A310-200 SRM 51-40-21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

M DECK COMP'T NR 1 SEAT TRACK, FR45.5, FR48, FR49, FR52, FR52.5 FR53.5, 6-EA AREAS OF CORROSION INSIDE SCALOPE HOLES AS MARKED. REMOVED CORROSION IAW SRM 51-74-10, OUT OF LIMITS BETWEEN FR52 & 54 IAW 53-10-16 FIG 101. CUT OUT & FABBED NEW REPAIR SECTION OF SEAT TRACK AND SPLICES IAW SRM 53-10-16 FIG 205. TREATED, PRIMED & TOPCOATED IAW SRM 51-23-20 & 51-75-10. INSTALLED SEAT TRACK & SPLICES FROM FRAME 51.5 TO 54 IAW SRM 51-10-16 FIG 205.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. ITEM NR 20 OF LIST FUSELAGE DOUBLER LOWER LT SIDE AFT OF LT MLG DOOR OPENING. FUSELAGE DOUBLER FOUND TO BE IN CONFORMANCE WITH AIRBUS DWG A538-12568 LOWER LT SIDE AFT OF LT MLG DOOR.

Part: RIB — CORRODED (NR 2 PYLON) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

NR 2 PYLON OTBD SIDE RIB 16A UPPER AREA BRACKET LWR AREA HAS AN AREA OF CORROSION EXTENDING UNDER FASTENERS. REMOVED AND REPLACED BRACKET IAW A310-200 SRM 51-72-10. REINSTALLED 3 NUTPLATES IAW A310 SRM 51-40-21. (SEE JPF)

Part: PANEL — CORRODED (CARGO BAY) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

BULK CARGO CEILING PANEL SUPPORT CENTER BETWEEN FRAMES 65 AND 66 HAS SEVERE EXFOLIATED CORROSION FROM END, BACK 6 INCHES. REMOVED STRAP IAW A310-200 SRM 50-40-21. REPLACED STRAP FOR CEILING PANEL SUPPORT IAW A310-200 SRM 50-40-21.

Part: FAIRING — DAMAGED (HORIZONTAL STAB) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION, FLUSH REPAIR LT HORIZONTAL STAB L/E FAIRING 331CB L/E OUTBOARD END. THIS REPAIR ON THE LT HORIZONTAL STAB L/E FAIRING 331CB WAS FOUND TO BE IAW A310-200 SRM 55-12-12, FIG 201. CLASSED AS A MINOR REPAIR PER FEDEX GMM 6-2-100, AND IS NOT BOUND BY ANY REPETITIVE INSPECTION REQUIREMENTS. (OPEN)

Part: ADAPTER — CRACKED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

MDCC ZONE 241, BETWEEN RT SEAT TRACK 2-3 FR 43, 1-EA. CLS ADAPTER HAS CRACKED UNDERNEATH. REMOVED AND REPLACED CLS ADAPTER IAW A310 SRM 51-72-10.

Part: PANEL — CORRODED (ZONE 300) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

CORROSION AROUND FASTERNER HOLES, LEFT AND RIGHT SIDE TOP OF RUDDER, PANEL 326AT REMOVED TO REPAIR STATIC WICK BASE N00238.

Part: ADAPTER — CORRODED (ZONE 200) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MAIN CABIN AT FRAME 38 CLS ADAPTOR, -YE15 HAS 1EA AREA OF CORROSION (BETWEEN SEAT TRACK LAND 2 LT)

Part: SEAT TRACK — CORRODED (FUSLEAGE) · airframe 38,799 hrs · 18,108 cycles

M DECK CARGO COMPT LT NR 4 SEAT TRACK, FR 48, FR 49, FR 50, FR 52.5, FR 53.5 CORROSION INSIDE SCALOPE HOLES 5-AREAS AS MARKED. REMOVED CORROSION IAW SRM 51-74-10. OUT OF LIMITS IAW A310 SRM 53-10-16 FIG 101. CUT AND REMOVED BAD SECTION OF SEAT TRACK FROM FR 49.5 TO FR 45.5 LT NR 4 IAW A310 SRM 53-10-10 FIG 205. FABBED NEW REPAIR SPLICES IAW SRM 53-10-16 FIG 205.

Part: STRAP — CRACKED (ZONE 300) · airframe 38,799 hrs · 18,108 cycles

REF. SNRM NR N00844 BETWEEN FR 86 AND FR 87 STG 34L (LT) INTERCOSTAL IS BENT ANGLE STRAP FOUND TO BE CRACKED REMOVED AND REPLACED WITH NEW ANGLE IAW A310 SRM 51-40-21.

Part: SKIN — DENTED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

REPAIR NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION. ITEM NR 8 ON LIST FUSELAGE, LT SIDE FR77 AT 3 O'CLOCK POSITION. REPAIRED DENT AREA IAW A310 SRM 53-10-12 FIG 112 AND 51-73-10 PARA. 7 FIG 4. TREATED BARE METAL IAW A310 SRM 51-21-10.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MDCC ZONE 252 RT NR 4 SEAT TRACK HAS AREA OF CORROSION INSIDE SCALLOPED HOLE (1- AREA ONLY) AT FRAME 64.5. REMOVED CORROSION IAW A310-200 SRM 51-74-10 FOUND CRACK, FABBED REPAIR SECTION AND SPLICED IAW A310-200 SRM 51-10-16 FIG 208 AND SRM 51-40-40. REMOVED OLD SECTION OF SEAT TRACK IAW A310-200 SRM 51-72-0 TREATED PRIMED AND TOP COATED NEW SECTION IAW A310-200 SRM 51-21-10 HEAT TREATED RIVETS IAW A310-200 SRM 51-25-00. INSTALLED SEAT TRACK SECTION IAW A310-200 SRM 53-10-16 FIG 208 AND SRM 51-40-20.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MDCC ZONE 241, RT SEAT TRACK NR 5, FR39.5, HAS 1-AREA OF CORROSION INSIDE SCALLOPED HOLE. REMOVED DAMAGED SEAT TRACK AND REPLACED WITH NEW SEAT TRACK P/N A53810820000IAW A310-200 SRM 51-72-10.

Part: BRACKET — CORRODED (NR 1 PYLON) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

NR 1 PYLON OTBD SIDE UPPER AREA RIB 15A BRACKET ON LWR AREA HAS CORROSION EXTENDING UNDER FASTENERS FOR NUT PLATE. CORROSION REMOVED IAW A310 SRM 51-74-10, NDT MATERIAL THICKNESS AFTER THICKNESS IS OUT OF LIMITS. REMOVED AND REPLACED BRACKET AND 3EA NUTPLATES IAW A310 SRM 51-72-10 AND SRM 51-40-21.

Part: INTERCOSTAL — BENT (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

BETWEEN FR 84 AND FR 85 STG 34L INTERCOSTAL IS BENT. INTERCOSTAL ANGLE HAS BEEN REMOVED AND REPLACED IAW A310-200 SRM 51-40-21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MDCC SONE 252 RT NR 4 SEAT TRACK FS 68 FS 69.5 FS 70.5 HAS 3 AREAS OF CORROSION INSIDE SCALLOPED HOLES. REMOVED DAMAGED SEAT TRACK SECTION AND REPLACED WITH NEW SEAT TRACK SECTION FROM FRAME 69.5 TO FRAME 71.5 IAW A31-200 SRM 51-10-16 FIG 208 RT NR 4 RESTORED SURFACE PROTECTION IAW A310-200 SRM 51-23-00 AND SRM 51-21-10. APPLIED LUBRICANT RUST INHIBITOR TO REPAIR AREA IAW A3140-200 SRM 51-23-00.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

REF SNRM# N00536 MDCC ZONE 241 RT SEAT TRACK NR 5 FR 5.5 FR50 FR50.5 FR53 FR54 CORROSION INSIDE SCALLOPED HOLES 5-AREAS. REMOVED CORROSION IAW SRM 51-74-10 OUT OF LIMITS IAW SRM 53-10-16 FIG 101. REMOVED BAD SECTION OF TRACK FABBED REPAIR SPLICES AND TRACK INSTALLED NEW REPAIR SPLICES AND TRACK IAW SRM 53-10-16 FIG 205.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MDCC RT NR 5 SEATRACK, FS 78 FS 78.5 HAS 2 AREAS OF CORROSION INSIDE SCALLOPED HOLES. REPLACED SEAT TRACK IAW A310-200 SRM51-72-10, FABRICATED NEW SEAT TRACK IAW DRAWING A53279232, REMOVED REINSTALLED FLOORBOARDS IAW A310 AMM 53-10-21. REMOVED, REINSTALLED GILL LINERS IAW A310 AMM 25-58-22-4, APPLIED DINATROL ON SEAT TRACK IAW A310-200 SRM 51-75- 10.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 38,799 hrs · 18,108 cycles

M DECK ZONE 240, LEFT NR 2 SEAT TRACK, FR47, FR51, FR51.5, FR52.5, FR53 AND FR54, CORROSION INSIDE SCALLOPED HOLES, 6-AREAS. BLENDED CORROSION PER A310 SRM 51-74-10 MEASURED MATERIAL LOSS AND FOUND ALL AREAS WITHIN LIMITS EXCEPT FOR AREAS AT FRS 51.5 AND 52.5 WERE OUT OF LIMITS PER A310 SRM 53-10-16 FIG 101, CUT OUT AND REMOVED DAMAGED SEAT TRACK SECTION FROM FRAMES 50.5 TO PRODUCTION END AT FRAME 54, FABRICATED SEAT TRACK SECTION AND SPLICES, DRILLED AND INSTALLED PER A310 SRM 53-10-16 PARA 5.D FIG 205, TREATED, PRIMED AND TOPCOATED PER A310 SRM 51-75-10.

Part: BRACKET — LIGHTNING STRIKE (ZONE 300) · airframe 38,799 hrs · 18,108 cycles

LIGHTNING STRIKE TO BRACKET TOP OF RUDDER RIGHT SIDE FOUND AFTER REMOVAL OF PANEL 326AT FOR STATIC WICK REPAIR NOO238. REMOVED AND REPLACED COUPLING IAW A310-200 SRM 51-40-21, TOPCOATED COUPLING IAW A310-200 SRM 51-75-10.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 38,799 hrs · 18,108 cycles

MDCC ZONE 250, FS 54.2 LT SEAT TRACK NR 3 HAS GOUGES ON SCALLOP HOLE 1 - EA AREA. REMOVED AND REPLACED SEAT TRACK FITTING IAW A310-200 SRM 51-72-10.

Part: ADAPTER — CORRODED (ZONE 200) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MDCC ZONE 251 FS 60 BETWEEN RT SEAT TRACK NR 4 - 5, 1 - EA. CLS ADAPTER BROKEN. REMOVED AND REPLACED CLS ADAPTER IAW A310-200 SRM 51-72-10.

Part: ADAPTER — CRACKED (ZONE 200) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MDCC ZONE 250, FR 55/58 BETWEEN LT SEAT TRACK 2 - 3, 1 EA, CLS ADAPTER BROKEN. REMOVED AND REPLACED CLS ADAPTER IAW A310-200 SRM 51-72-10.

Part: CROSSBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MDCC ZONE 250, FS 54.2 BETWEEN LT SEAT TRACK 4 -5, LATERAL STUCTURE HAS CORROSION AT SCREW HOLES. REMOVED AND REPLACED CROSS BEAM IAW A310-200 SRM 51-72-10.

Part: ADAPTER — CORRODED (ZONE 200) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MDCC ZONE 241, FR 39, BETWEEN NR 2 - 3 RT SEAT TRACK LCS ADAPTER HAS 1 AREA OF CORROSION INSIDE SCALLOP HOLE. REMOVED AND REPLACED CLS ADAPTER IAW A310-200 SRM 51-72-10.

Part: PLATE — CRACKED (ZONE 500) · airframe 38,799 hrs · 18,108 cycles

LEFT WING LOWER AILERON ACCESS DOOR LANDING PLATE HAS CRACK IN IT. REMOVED CRACKED LANDING AND INSTALLED A NEW LANDING IAW A310-200 SRM 51-72-10.

Part: ADAPTER — GOUGED (ZONE 200) · corrosion level 2 · airframe 38,799 hrs · 18,108 cycles

MAIN CABIN FRAME 36, CLS ADAPTER -Y60 IS GOUGED, BETWEEN SEAT TRACK 3 - 4 LT. REMOVED AND REPLACED CLS ADAPTER IAW A310-200 SRM 51-72-10.

Part: SKIN — LIGHTNING STRIKE (FUSLEAGE) · airframe 38,799 hrs · 18,108 cycles

LT FUSELAGE FRAME 11A APPROX AT STR 18L HAS A LIGHTNING STRIKE. BLENDED OUT AREA IAW SRM 51-73-10 AND 53-10-12 FIG 220 SH 1. 34 PERCENT MATERIAL LOSS FOUND TO BE OUT OF LIMITS IAW SRM 53-12-12 DIA 104. REPAIRED SKIN WITH DOUBLER AND FILLER ONLY PER SRM 53-12-12 FIG 202 SH 1 FRAME WAS NOT DAMAGED.

Part: ENGINE — SMOKE · airframe 38,677 hrs · 18,058 cycles

AT 80 KTS A/C STARTED TO SHUDDER CONTINUOUSLY. A/C STARTED VEERING TO THE RIGHT REQUIRING CONTINUOUS LEFT RUDDER INPUT TO KEEP A/C ON RWY CENTERLINE. AIRPLANE BEHIND, WHO HAD TAXIED INTO POSITION & HOLD REPORTED SMOKE COMING OUT OF THE ENGINE AREA. ABORTED AT AROUND 95 KTS. NO ENGS PARAMETERS WERE EXCEEDED.

Part: ANGLE — CRACKED (WING ROOT) · airframe 38,163 hrs · 17,829 cycles

FOUND CRACK AROUND 1 OFF FASTENER ON LT WING ROOT TO FUSELAGE LOWER REINFORCEMENT PICK UP ANGLE PLATE AT FS 40/41. ISSUED AND COMPLIED WITH EO 6-5310-7-5003 REV 04 PT 1. CRACK STOP DRILLED, ROTOTEST PERFORMED. PAGE BLOCK 1 FAXED TO RECORDS AND INSPECTION REPORT SENT TO AIRBUS FIELD SERVICE SUPPORT. PERFORMED BY SIAEC AT B-CHK.

Part: CONTROL MODULE — INOPERATIVE (MLG) · airframe 38,080 hrs · 17,787 cycles

LANDING GEAR FAIL TO RETRACT ON TAKEOFF. QRH PROCEDURES FOLLOWED BUT GEAR HANDLE WOULD NOT RETRACT. OVER WEIGHT QRH PROCEDURES FOR LANDING COMPLETED. LANDED AT 290,000 LBS AT FPM SINK RATE, SMOOTH LANDING, NO CROSS WINDS FACT 26AUG04 05:03 PVG U T/S IAW TSM 32-30-00 FIG 109 DURING STEP 3 FOUND L/G CONTROL LEVER TO HAVE RATTLING INSIDE. REMOVED AND REPLACED LANDING CONTROL MODULE IAW 32-31-11-4 ACCOMPLISHED GEAR SWING IN THE NR 1 AND 2 POSITION BOTH OK. GEAR SWING AS IAW AMM 32-31-00 AIRCRAFT OK FOR SERVICE. BITE TEST OF 54GB NO FAULTS NOTED.

Part: WIRE — LOOSE (TERMINAL BLOCK) · airframe 36,103 hrs · 16,865 cycles

AFTER LEVEL OFF AT CRUISE AT FL350, CABIN RATE ECAM WARNING ILLUMINATED. FOLLOWED ECAM STEPS AND QRH PROCEDURES. WAS UNABLE TO CONTROL CABIN ALTITUDE. WHILE LEVEL AND IN MANUAL PRESSURIZATION, CABIN ALT STABILIZED AT 14,900 FT. WITH ALL OUTFLOW VALVES CLOSED. EQUIPMENT COOLING LOW FLOW ILLUMINATED. ECAM ASKED FOR EXTRACT OVERBOARD WHICH INCREASED CABIN ALTITUDE. RETURNED TO SUBIC. CHD GROUND AT PIN 13A AND 13B OF CABIN PRESSURE CTRL 105HM AND 106HM, FOUND BOTH 13A OF 105HM AND 106HM, BLOCK 158VT NR 10 PIN -J- AND NR 1 PIN -B- LOOSE. FIXED AND SECURED TERMINAL BLOCKS PER SMP FOR PRECAUTIONARY. REMOVED AND REPLACED 159GB AND 60GB RELAY SYS 1 AND 2.

Part: WIRE — CHAFED (EGT INDICATOR) · airframe 35,309 hrs · 16,473 cycles

ON TAKEOFF ROLL GREATER 80 KNOTS TO POWER NOT ACHIEVED. NR 2 EGT FLUCTUATION +- 200C FOLLOWED BY ROLLBACK TO ZERO. DASHED LINES RTD ON TAXI OUT/IN OK. REPAIRED CHAFED WIRING TO NR 2 EGT INDICATOR IAW EA. COMPLIED WITH PART 2 EA. OPS CHECK NORMAL.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 35,302 hrs · 16,470 cycles

CORROSION ON NOSE LAND GEAR WHEEL WELL BULKHEAD AT LEFT TOP CORNER NEAR FRAME 16. R&R SKIN PER EA 6-5340-66864.

Part: SPAR — CORRODED (HORIZ STAB) · airframe 35,302 hrs · 16,470 cycles

RIGHT HORIZ STAB REAR SPAR TOP T-CHORD CORRODED BETWEEN RIB 5 TO 9. R&R T CHORD PER EA 6-5100-66468.

Part: SPAR — CORRODED (HORIZ STAB) · airframe 35,302 hrs · 16,470 cycles

LEFT HORIZ STAB REAR SPAR TOP T-CHORD CORRODED APPROX 280 MM FROM RIB 3 TO 5. R&R T CHORD PER EA 6-5100-66468.

Part: SPAR — CORRODED (HORIZ STAB) · airframe 35,302 hrs · 16,470 cycles

RIGHT HORIZ STAB REAR SPAR TOP T-CHORD CORRODED BETWEEN RIB 3 TO 5. R&R T CHORD PER EA 6-5100-66468.

Part: SKIN — CORRODED (CARGO DOOR) · airframe 35,302 hrs · 16,470 cycles

FOUND CORROSION AT FWD CARGO DOOR INNER SKIN LWR SECTION AT FR 20. R&R SKIN PER EA 6-5230-66467.

Part: FITTING — CORRODED (LT PYLON) · airframe 35,302 hrs · 16,470 cycles

LT PYLON AFT THRUST AND SIDE LOAD FITTING CORRODED AT BEARING FACE. R&R FITTING PER EA 6-5450-66460.

Part: SKIN — CORRODED (LT WING) · airframe 35,302 hrs · 16,470 cycles

LT WING T/E SKIN CRACKED AT 581AB ACCESS CUTOUT AT RIB 11. R&R SKIN PER EA 6-5710-65463.

Part: FITTING — CORRODED (LT PYLON) · airframe 35,302 hrs · 16,470 cycles

SIGNS OF CORROSION AT L/PYLON THRUST & SIDE LOAD FITTING SLEEVE. R&R FITTING PER EA 6-5450-66458.

Part: FITTING — CORRODED (PYLON) · airframe 35,302 hrs · 16,470 cycles

R/SING PYLON FWD THRUST AND SIDE LOAD FITTING AREA, FOUND BEARING AREAS WITH BROWNISH STAINS AT TOP & BOTTOM OF FITTING. R&R FITTING PER EA 6-5450-66461.

Part: FITTING — CORRODED (RT PYLON) · airframe 35,302 hrs · 16,470 cycles

RT WING PYLON AFT MOUNT FITTING ATTACHMENTS CORRODED. R&R FITTING PER EA 6-5450-66459.

Part: SKIN — CORRODED (N/A) · airframe 34,742 hrs · 16,231 cycles

RT WING LOWER SKIN CORRODED ON LWR SURFACE ON NR 2 PANEL AT AFT EDGE AT RIB 9. STRUCTURAL REPAIR PER E.A. 6-5710-64296.

Part: WING — CORRODED (N/A) · airframe 34,742 hrs · 16,231 cycles

INBD LT WING UNDER SURFACE TRAILING EDGE AT ZONE 575 FND CORRODED. TEMPORARY REPAIR PER E.A. 6-5710-64295.

Part: COMPRESSOR — STALLED (NR 1 ENGINE) · airframe 34,515 hrs · 16,130 cycles

SEVERAL COMPRESSOR STALLS ON NR 1 ENGINE FL350. NO OTHER PARAMETERS NOTED. BLED ENG AND SLOWLY BROUGHT POWER BACK IN. REMOVED AND REPLACED NR 1 ENGINE AFTER NUMEROUS PARTS REPLACED.

Part: ENGINE — SURGES (NR 1) · airframe 33,900 hrs · 15,846 cycles

MULTIPLE ENGINE SURGE NR 1 ENGINE WITH ENG AND WING ANTI-ICE ON.

Part: COMPRESSOR — STALLED (NR 1 ENGINE) · airframe 33,896 hrs · 15,841 cycles

NR 1 ENG STALLED COMPRESSOR REPEATED EPR GAUGE ERRATIC UNABLE TO MAINTAIN.

Part: ADC — FAULTY · airframe 33,329 hrs · 15,592 cycles

01-228 AIRSPEEDS. R&R #2 ADC PER MM 34-11-34 & PURGED F/O PITOT LINE. OPS CK OK.

Part: CONTROLLER — INOPERATIVE (CABIN PRESSURE) · airframe 33,142 hrs · 15,510 cycles

CABIN PRESS INOP.

Part: OUTFLOW VALVE — FAILED (CABIN PRESSURE)

ON CLIMBOUT OF BOM AC WOULD NOT PRESSURIZE. COCKPIT IND SHOW NR 1 FWD OUTFLOW VLV OPEN. AC RELEASED PER MEL 21-47 OUTFLOW VLV FWD NR 1 DE-ACTIVATED IN THE CLOSE POS PER MXP 21-47B.

Part: PLATE — LOOSE (ACTUATOR) · airframe 32,293 hrs · 15,113 cycles

O00-336 ON T/O ROLL NR 2 ENGINE THRUST REVERSER UNLOCKED LIGHT ILLUMINATED. REVIEW NR 2 T/R DEACTIVATION PROC, FND LT LWR SLAVE ACTUATOR LOCKING PLATE LOOSE (BOLT BROKEN) CANIB BOLT FROM A/C 421 AND REINSTALLED SAME. AC OK FOR SERVICE.

Part: SKIN — CORRODED (FUSELAGE) · airframe 31,990 hrs · 14,969 cycles

CORROSION FOUND ALONG UPPER SKIN LAP JOINT STR 6 LT FROM FRAME 76 TO 80. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5330-52051.

Part: SKIN — CORRODED (FUSELAGE)

CORROSION FOUND ALONG UPPER SKIN BETWEEN STR 2 & STR 3 RT FROM FRAME 78 TO 79. REMOVED AND REPLACED PER FEDEX EA 6-5330-52051.

Part: WEDGE — CORRODED (LT ELEVATOR) · airframe 31,990 hrs · 14,969 cycles

LEFT ELEVATOR TRAILING EDGE WEDGE NR 3 FOUND CORRODED. CORROSION REMOVED. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5510-52046.

Part: WEDGE — CORRODED (RT ELEVATOR) · airframe 31,990 hrs · 14,969 cycles

RIGHT ELEVATOR MOST I/B TRAILING EDGE WEDGE FOUND CORRODED. CORROSION REMOVED. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-2210-52050.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 31,990 hrs · 14,969 cycles

AT FRAME 35 FOUND FLOORBEAM CRACKED AT RHS Y - 700, .5 INCH BELOW TOP FLANGE WITH CROSS BEAM CHORD. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52043 & A310 SUPL MANUAL 53-10-15, FIG 201.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 31,990 hrs · 14,969 cycles

AT FRAME 36 FOUND FLOORBEAM CRACKED AT RHS Y -900, .0625 INCH BELOW TOP FLANGE WITH CROSS BEAM CHORD. *S/D* REMOVED AND REPLACED PER EA 6-5100-52043 & A310 SRM SUPL MANUAL 53-10-15, FIG 201.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 31,990 hrs · 14,969 cycles

AT FRAME 34 FOUND FLOORBEAM CRACKED AT RHS Y - 700, .5 INCH BELOW TOP FLANGE WITH CROSS BEAM CHORD. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52043 & A310 SRM SUPL MANUAL 53-10-15, FIG 201.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 31,990 hrs · 14,969 cycles

AT FRAME 36 FOUND FLOORBEAM CRACKED AT RHS Y-700, .5 INCHES BELOW TOP FLANGE WITH CHORD. *S/D* REMOVED AND REPLACED PER FEDEX REF EA 6-5100-52043 & A310 SRM SUPL MANUAL 53-10-15, FIG 201.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 31,990 hrs · 14,969 cycles

AT FRAME 36 FOUND FLOORBEAM CRACKED AT LHS Y +700, .5 INCH BELOW TOP FLANGE WITH CROSS BEAM CHORD. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52043 & A310 SRM SUPL MANUAL 53-10-15, FIG 201.

Part: WARNING LIGHT — ILLUMINATED (NR 2 ENGINE) · airframe 31,579 hrs · 14,734 cycles

NR 2 ENGINE REV UNLK ILLUMINATE DURING TAKEOFF. PWR LOW SPD REF T/O.

Part: FRAME — CRACKED (FUSELAGE) · airframe 31,572 hrs · 14,720 cycles

INSPECTION FOUND CRACKS ON HOLES I & J IN AFT FLANGE OF FR 47, RT & LT SIDE BETWEEN STR 42 & 44.

Part: SKIN — DENTED (FUSELAGE) · airframe 31,572 hrs · 14,720 cycles

NR 49 & 50 2 DENTS FND ON FUSELAGE SKIN AT BETWEEN FR 61A & 3 AFT OF FR 61A & BETWEEN STR 46R TO 47R, LENGTH=3.5WIDTH=3 & DEPTH=0.050. R&R PERF IN ACCORD WITH EA 6-5330-49627.

Part: SKIN — CORRODED (RT WING) · airframe 31,572 hrs · 14,720 cycles

CORROSION FOUND AT RT WING BOTTOM SKIN BETWEEN WING ROOT PICKUP ANGLE AND EXTERNAL LWR SURFACE SPLICE AT WING RIB 1.

Part: STRAP — CORRODED (FUSELAGE) · airframe 31,396 hrs · 14,616 cycles

CORROSION ON CIRCUMFERENTIAL STRAP (P/N A53984667208). REPAIRED AFT PRESSURE BULKHEAD PER EA NR 6-5310-48160.

Part: BLEED VALVE — FAILED (NR 2)

99-144 - BLEED VALVE NR 2 FAULTED IN CRZ AT FL310, UNABLE TO RECOVER FAULTED BLD VALVE.

Part: RELAY — INOPERATIVE (LT & RT MLG)

RECEIVED NR 2 SYS OUTFLOW VALVE FAULT LIGHT. REGULATOR NR 2 OFF SYS NR 1 CK. PROBLEM COULD NOT DUP ON GROUND. PRECAUTIONARY REPLACED RT AND LT MLG RELAY 60GB AND 45GB, TERMINAL BLOCK 158VT NR 1. TEST PER MM 21-31-00 SAT.

Part: SWITCH — DIRTY (CARGO DOOR)

ON TAKEOFF, BULK CARGO DOOR SHOWED OPEN ON RIGHT AND LEFT ECAM OPEN. FOUND DOOR CLOSED. INSPECTED DOOR WARNING SWITCH, CONNECTOR WIRES OK. CLEANED WARNING SWITCH STRIKER DOOR, OPS AND IND CHECKED OK.

Part: SWITCN — LOOSE (NR 1 ENGINE)

NR 1 ENG REVERSER UNLOCK LIGHT AT T/O PWR. REJECTED T/O RETURN TO GATE. THRUST REVERSER NR 1 DEFER PER MEL 78-1 AND DEACTIVATED IN FWD THRUST POS. T/S FOUND UNLOCK SWITCH LOOSE AT LT SIDE. ADJUSTED AND RESECURED UNLOCK SWITCH. REACTIVATED PER MM 78-31-01. OPS CK NR 1 ENG T/REV USING APU AIR AND HOSE, FOUND T/REV OPER NORM AND ALL IND NORM.

Part: CONTROL — FAILURE (CABIN)

98-0143, STA-TPE, LOSS OF CABIN PRESS CLIMBING TO FL310. CABIN PRESS CONTINUED TO CLIMB PAST 10000 FT. AUTO PRESS WAS INEFFECTIVE A DESCENT WAS BEGUN AND MANUAL PRESS BROUGHT PRESS BELOW 10000 FT. UPON DESCENDING BELOW 18000 FT FLIGHT REMAINED IN MANUAL PRESS MODE. A/C RELEASED FOR SERVICE PER MEL/CDL 21-44. PERFORMED THE CPC 1 AND 2 TEST FOUND CPC NR 1 TEST FAILURE. TRIED TO REPLACE WITH NEW CONTROLLER, NO HELP. ITEM DEFERRED PER MEL 21-44. C/B PULLED. NR 1 CPC BITE TEST SHOWED TORQUE MOTOR CONTROL FAILED, THE ORIGINAL CPC WAS REINSTALLED.

Part: HOSE — LEAKING (NR 2 ENGINE)

FOUND LEAKING HYDRAULIC LINES ON NR 2 ENGINE THAT BURNT HOLE IN PAN. REPLACED ALL HYDRAULIC LINES, PAN AND BLANKETS.

Part: OUT FLOW VALVE — FAILED (CABIN)

DURING CLIMBOUT, CABIN PRESSURE EXCEEDED 10K FT SWITCH TO MANUAL CABIN CONTROL. BUT STILL UNABLE TO KEEP BELOW 10K FT, PERFORMED ECAM AND CHECKLIST ITEMS. NOTE ON ECAM PRESS PAGE NOTICED FWD AND AFT NUMBER TWO VALVE OPEN REGARDLESS OF MODE. CONFIRMED INOP DEFERRED MEL 21-44 CAT C C/N 0017036. *S/D* REMOVED NR 2 SYS AFT CABIN PRESSURE OUT FLOW VALVE 40HM AS PER M/M 21-31-12. REMOVED AND REPLACED NR 2 SYS FWD CABIN PRESSURE OUTFLOW VALVE PER M/M 21-31-12. OPERATIONAL TEST SATISFACTORY, CLEARED DMI.

Part: NAV DISPLAY — FAILED (LT COCKPIT)

SFS: WRI 36-61 2114 CAPT MAP DISPLAY INTERMITTENTLY LOSES COLOR DEPICTION AND HAS SPURIOUS LINES. REMOVED AND REPLACED CAPT'S NAVIGATIONAL DISPLAY UNIT PER M/M 31-57-22. OPS CHECK GOOD.

Part: WIRE — FAILED (LT GEN SYST)

SFS: WRI 24 20-2120 ON CLIMB-OUT PASSING FL200, ELECTRICAL JOLTS STARTED AGAIN, AFFECTING CAPTS ATT IND PFD NAV DISPLAY ECAM AND ENG INSTRUMENTS. ACARS LOCKED UP AND AUTO PILOT. PERFORMED BITE CHECK ON GPCU. LT GEN SYS, PMG/FIELD/WRNG/GCU. CHECKED WIRING AS PER AWM 24-22-01. FOUND WIRE NR11-4001-16RD CONNECTED FR D4958P PIN E TO IDG PLUG DG13B PIN NR2 OPEN. REPAIRED WIRE AS PER SP CHAP 20. RUN ENG PER JRH AND CKD ELECT SYS AW 24-00-00 OK.

Part: CONTROLLER — MALFUNCTIONED (CABIN)

CLIMBOUT APPROX 8,000 FT, RECEIVED RED ECAM WARNING LWR ACCESS DOOR NOT CLOSED, FOLLOWED BY EXCESSIVE CABIN RATE. ACCOMPLISHED ECAM. CABIN RATE CLIMBED AT SAME RATE AND ALTITUDE AS A/C DESCENDED TO 10,000 FT MADE PRECAUTIONARY LANDING KUL. LONG HISTORY OF PRESS PROBLEMS WITH A/C. CABIN PRESSURIZATION CONTROLLER NR 2 SELECTED OFF BY CREW. SELECTED NR 2 CPC ON AND ALL ECAM INDICATIONS NORMAL. PERFORMED BITE TEST ON BOTH CPCS WITH NO FAULTS. CHECKED BOTH LOWER ACCESS DOORS AND FOUND CLOSED. ADJUSTED INDICATION STRIKER ON FWD DOOR AND ECAM DOOR INDICATION NORMAL. PRESSURIZED CABIN TO 4 PSI DIFFERENTIAL.

Part: REGULATOR — MALFUNCTIONED (NR 2 ENGINE)

AFTER NR 2 ENG START CABIN AUTO PRESS NR 2 AND NR 2 REGULATOR FAIL, NR 1 SYS OK. AFTER TAKEOFF UNABLE TO PRESSURIZE CABIN IN AUTO OR MANUAL. THE OVERRIDE AND ECAM OUTFLOW VALVE POSITION INDICATED CLOSED. RESET NR 2 AUTO FLOW VALVE AND CONTROLLER C/B'S. ALSO, PERFORMED NR 2 CPC, BITE CHK NORMAL. ALL TESTS PASSED AND ALL FAULT LIGHTS RESET TO NORMAL POSITIONS.

Part: ACTUATOR ROD — SHEARED (CARGO DOOR)

REPORTED BY RAMP PERSONNEL. WHILE OPENING THE MDC DOOR. A LOUD SOUND WAS HEARD. MX DISCOVERED THAT THE MDC DOOR ACTUATOR ROD-END SHEARED. *S/D* REMOVED AND REPLACED MDC DOOR ACTUATOR PER M/M 52-36-27 AND TESTED PER M/M 52-36-00, CHECK OK.

Part: O-RING — FAILED (GREEN HYD SYST)

STA SFS - APPROX 1 HOUR INTO CRUISE, ECAM REPORTED GREEN HYD SYS RESERVOIR LOW OVERHEAD AND SYS PAGE AGREED. ACCOMPLISHED PROCEDURE, SHUT DOWN GREEN SYSTEM. MANUALLY EXTENDED GEAR. CHECKED AND FOUND HYD GREEN SYS GREEN ELECTRO HYD SELECTOR FITTING LEAKING. REMOVED AND REPLACED PACKING (O-RING), LEAK CHECKED OK. RESET OF SYSTEM NORMAL OPERATING CONDITION ON MANUAL EXTENSION PER MM 32-33-00, PG 18.