N689FE

Part: SKIN — DENTED (ZONE 800) · airframe 22,596 hrs · 12,968 cycles

FABRICATE NEW LOWER INNER SKIN PER EA NO:T6-5230-T0382227 AT MDCD FR21~26,LONGN 8 ~ STGR 30L FABRICATED AND INSTALLED NEW LOWER INNER SKIN AT MDCD FR21-26, LONGN 8 - STGR30L POSITION. I.A.W FEDEX EA : T6-5230-T0382227AP2, SEQ NO:966 TITLE:DOORS - MAIN CARGO DOOR - REPAIR OF INNER SKIN IMPACT DAMAGE, C20-C21.THIS REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. AND THE REPAIR IS APPROVED PER RDAF FOR 6 MONTHS PENDING DTA.

Part: SKIN — DENTED (ZONE 800) · airframe 22,596 hrs · 12,968 cycles

PER EA NO:T6-5230-T0382227 PERFORM SPLICE REPAIR ON MDCD INNER SKIN AT FR21,LONGN 4~5 FABRICATED AND INSTALLED NEW REPAIR SPLICE AND CONNECTING CLIP AT MDCD FR21, LONGN 4 - 5 POSITION. I.A.W FEDEX EA : T6-5230-T0382227AP2, SEQ NO:966 MAIN CARGO DOOR - REPAIR OF INNER SKIN IMPACT DAMAGE, C20-C21.THIS REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. AND THE REPAIR IS APPROVED PER RDAF FOR 6 MONTHS PENDING DTA.

Part: FORK — DAMAGED (ZONE 800) · airframe 22,596 hrs · 12,968 cycles

FABRICATE NEW REAR FORK FRAME 21 PER EA NO:T6-5230-T0382227 AT MDCD FR21,LONGN 6~STGR 30L FABRICATED AND INSTALLED NEW REAR FORK FRAME 21 AT MDCD FR21, LONGN 6 - STGR30L POSITION. I.A.W FEDEX EA : T6-5230-T0382227AP2, SEQ NO:966 TITLE:DOORS - MAIN CARGO DOOR - REPAIR OF INNER SKIN IMPACT DAMAGE, C20-C21.THIS REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. AND THE REPAIR IS APPROVED PER RDAF FOR 6 MONTHS PENDING DTA.

Part: SKIN — DENTED (ZONE 800) · airframe 22,596 hrs · 12,968 cycles

AIRCRAFT REPAIR ASSESSMENT: EXISTING REPAIR SPLICE FOUND ON MAIN CARGO DOOR INNER SKIN BTW FR20~21, BEAM 3~4 COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: STRUCTURES - REPAIR CATALOG - A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707, INSPECTION OF EXISTING REPAIR SPLICE ON MAIN CARGO DOOR INNER SKIN BTW FR20~21, BEAM 3~4 WAS EVALUATED. THE EXISTING REPAIR NEED TO BE REDONE AS PER EA:6-5230- T0382227 A, MAIN CARGO DOOR - REPAIR OF INNER SKIN IMPACT DAMAGE, C20- C21. THE REPAIR IS APPROVED PER RDAF FOR 6 MONTHS PENDING DTA AND CLASSIFIED AS MAJOR PER GMM 6-2-100. "MAJOR REPAIR."

Part: FLOOR SUPPORT — CRACKED (ZONE 200) · airframe 22,596 hrs · 12,968 cycles

M/D FLOOR SUPPORT FOUND CRACK AT FR37~FR38, -Y2462. REMOVED CRACK SUPPORT AT M/D FLOOR FR37~38,-Y2462,THEN INSTALLED NEW ONE WITH FASTENERS I.A.W A300-600F SRM 51-72-10-001 ,PAGE 2 & 51-40-21-001,PARA.7,PAGE 24~25,THE REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SKIN — GOUGED (ZONE 500 SPOLER) · airframe 22,596 hrs · 12,968 cycles

A GOUGE WAS FOUND ON OUTBD EDGE LOWER SIDE OF L2 SPLR. ACCOMPLISHED DOUBLER REPAIR WITH FASTENERS AT OUTBD EDGE OF L2 SPLR RIB 18 POSITION I.A.W FEDEX EA NO:T6-5750-T0383884P1, SEQ NO: XXX , TITLE: WING - FLIGHT SURFACES - LH #2 SPOILER - WEAR DAMAGE AT OUTBOARD FACE OF FRONT SPAR AT RIB 18 - REINFORCEMENT REPAIR.THIS REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SKIN — DENTED (ZONE 600 FLAP) · airframe 22,596 hrs · 12,968 cycles

RH WING OUTER FLAP D-NOSE SKIN GOT DENT BETWEEN RIB15~17 ,S-1.1~1.2 ACCOMPLISHED THE NOSE SKIN FLUSH REPAIR AT RH WING OUTER FLAP RIB15~17, S-1.1~1.2 I.A.W A300-600F SRM 57-50-00-201, PARA.4H, PAGE.231~236, FIG.208 & SRI:57-50-00-201, IIR:57-50- 00-2-002-00, PARA.3B, TABLE.203, PAGE.207/208. THE REPAIR CLASSIFIED AS CAT.B MAJOR PER GMM 06-2-100.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 22,596 hrs · 12,968 cycles

M/D SEAT TRACK FOUND CORROSION AT FR80-4", Y0 POS. ACCOMPLISHED THE SEAT TRACK SPLICE REPAIR AT MAIN DECK FLOOR SEAT TRACK AT FR80~FR78 PLUS 13" Y0 IAW A300-600F SRM 53-10-16-201 PARA.4 FIG201, PAGE203~208. THIS REPAIR CLASSIFIED AS MAJOR CAT A PER GMM6-2-100.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 22,596 hrs · 12,968 cycles

M/D SEAT TRACK FOUND CORROSION AT FR80-5", Y1221.2 POS. ACCOMPLISHED THE SEAT TRACK SPLICE REPAIR AT MAIN DECK FLOOR SEAT TRACK AT FR80~FR78 PLUS 13" Y1221.2 IAW A300-600F SRM 53-10-16-201 PARA.4 FIG201, PAGE203~208. THIS REPAIR CLASSIFIED AS MAJOR CAT A PER GMM6-2-100.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 22,596 hrs · 12,968 cycles

M/D FLOOR SUPPORT FOUND CRACK AT FR38.1~FR38.2, -Y2462 POS REMOVED CRACK SUPPORT AT M/D FLOOR FR38.1~38.2,-Y2462,THEN INSTALLED NEW ONE WITH FASTENERS I.A.W A300-600F SRM 51-72-10-001 ,PAGE 2 & 51-40-21-001,PARA.7,PAGE 24~25,THE REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100

Part: STRUT — CRACKED (ZONE 200) · airframe 22,596 hrs · 12,968 cycles

M/D FLOOR SUPPORT FOUND CRACK AT FR38.1~FR38.2, Y2462 POS. REPLACED THE CRACK STRUT WITH NEW PART ON M/D FLOOR SUPPORT AT FR38.1 ~FR38.2 Y2462 I.A.W A300-600F SRM 51-72-10-001,PAGE2 AND 51-40-21-001 PARA 7 PAGE24 - PAGE50. THIS REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SHEAR WEB — CRACKED (ZONE 200) · airframe 22,596 hrs · 12,968 cycles

M/D FLOOR STRUCTURE FOUND A SHEAR WEB CRACK AT FR77-1', S-26R. REPLACED THE CRACK SHEAR WEB WITH NEW PART ON M/D FLOOR STRUCTURE AT FR77-1", S- 26R I.A.W A300-600F SRM 51-72-10-001, PAGE 2 AND 51-40-21-001, PARA 7, PAGE 24~ PAGE 50.THIS REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: FITTING — NOT REPORTED (ZONE 800) · airframe 22,596 hrs · 12,968 cycles

REPLACE MAIN DECK CARGO DOOR ACTUATOR BEARING FITTING AT FRAME 23 PER EO NO:E6- 5230-E0378588 B P5 ACCOMPLISHED THE REPLACEMENT OF BEARING FITTING AT MAIN DECK CARGO DOOR FR23, LONGN1- LONGN3 I.A.W FEDEX EO NO:E6-5230-E0378588 B P5, SEQ NO:949, TITLE: DOORS-CARGO DOOR/HYD SYS - DETAILED VISUAL INSPECTION OF THE MAIN DECK CARGO DOOR (MDCD) ACTUATOR BEARING FITTINGS AT FRAME 23 AND 24 - AOT A52W016-24, THE REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SUPPORT — CRACKED (ZONE 500) · airframe 22,596 hrs · 12,968 cycles

LH WING TE CAVITY LOWER FACE OF UPPER FIXED PNL FOUND SUPPORT WEB CRACK NEAR L5 SPLR INBD. TRIMMED OUT AND INSTALLED REPAIR BRACKET REPAIR AT LH WING SKIN SUPPORT ABX144.2 I.A.W FEDEX EA NO : T6-5740-T0383807 P1, SEQ NO : 1013, TITLE : WING-ATTACH FITTINGS-LH WING ABX144.2 BOX RIB - OUTBOARD SKIN SUPPORT-CRACK AT FWD LOWER CORNER. THE REPAIR CLASSIFIED AS MINOR CAT.A PER GMM 6-2-100 NOTE: THIS REPAIR CHANGE THE CLASSIFICATION FROM MAJOR TO MINOR IN FINAL EA.

Part: FITTING — CRACKED (ZONE 800) · airframe 22,596 hrs · 12,968 cycles

THE MAIN DECK CARGO DOOR ACTUATOR BEARING FITTING WAS FOUND CRACK AT FRAME 24 ACCOMPLISHED THE REPLACEMENT OF BEARING FITTING AT MAIN DECK CARGO DOOR FR24, LONGN1- LONGN3 I.A.W FEDEX EO NO:E6-5230-E0378588 B P5, SEQ NO:949, TITLE: DOORS-CARGO DOOR/HYD SYS - DETAILED VISUAL INSPECTION OF THE MAIN DECK CARGO DOOR (MDCD) ACTUATOR BEARING FITTINGS AT FRAME 23 AND 24 - AOT A52W016-24, THE REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SUPPORT FITTING — CORRODED (ZONE 600) · airframe 22,266 hrs · 12,759 cycles

RH MLG FWD LUG RIB 5 CORROSION IN BORE. REMOVED CORROSION FROM RH MLG FWD LUG RIB 5 PER AIRBUS R57240425 AND EA # 6-5710-T0380814 P1.

Part: SUPPORT FITTING — CORRODED (ZONE 500) · airframe 22,266 hrs · 12,759 cycles

BUSH E HAS DAMAGE TO CHROME FACE. REMOVED AND REPLACED BUSHING D AND E PER AIRBUS R57240425.

Part: PROXIMITY SENSOR — FAILED (MLG) · airframe 22,198 hrs · 12,711 cycles

ON DEPARTURE LG WOULD NOT RETRACT ON SYS 2, SWITCHED TO SYS 1 & GEAR WOULD STILL NOT RETRACT. ALL GEAR REMAINED GREEN & DOORS SHOWED UNLOCK UNTIL HANDLE PLACED BACK DOWN. ON ARRIVAL, FOUND FAULT LIGHT ON PROX BOX 54GB. PERFORMED MEMORY RECALL ON 54GB & GOT A CODE 63 & A BOX FAULT LIGHT. NO OTHER ASSOCIATED FAULTS OR CODES. NO NEAR/FAR, NO TARGET, NO OTHER CODES. ACFT TO FLY MEL CONFIGURATION WITH GEAR DOWN. MEL MX PROCEDURE IS ACCOMPLISHED & SEPERATE OIL CREATED. ACFT IS OKAY TO CONTINUE. R & R PROX DETECT PROCESSING UNIT IAW MM. COMPLETED TEST WITH NO FAULTS. JACKED ACFT IAW MM & PERFORMED MULTIPLE GEAR SWINGS IN BOTH SYS 1 & 2 WITH NO FAULTS. RAN TEST AGAIN ONCE ACFT BACK ON GROUND WITH NO FAULTS.

Part: FIRE DETECTOR — FAILED (NR 1 ENGINE) · airframe 22,111 hrs · 12,649 cycles

ENG1 LOOP A FAULT DURING CLIMB OUT. APPEARED AND WENT AWAY AFTER A SHORT TIME ON FIRST FLIGHT, OCCURRED AGAIN TWICE DURING 2ND FLIGHT (ALSO DURING CLIMB OUT). RELEASED FOR SERVICE PER MEL: 26-XX-XXC CAT: C EXP: 14JUL24 ENG 1 LOOP A - INOP. FLIGHT CREW MUST PERFORM FUNCTIONAL TEST OF ENG FIRE WARNING SYSTEM PRIOR TO EACH DEPARTURE." AMM: 26-XX-XX-XX AMM: 26-12-XX-XX TEST #1 ENGINE FIRE DETECTOR FOUND NO FAULTS. REMOVED AND REPLACED 11WD FIRE DETECTOR UNIT AS PER M/M 26-12-XX-XX AND TESTED AS PER M/M 26-12-XX-XX ALL TEST PASSED, A/C OK FOR SERVICE. INSTALLED PART IS FROM THE CASH PROGRAM.

Part: CONTROLLER — FAILED (FLAP/SLATS) · airframe 21,118 hrs · 12,047 cycles

ON FINAL, CONFIGURED SLATS/FLAPS 15/15, WE SELECTED 15\20. AFTER SEVERAL SECONDS WE RECEIVED SLATS/FLAPS FAULT ECAM. IAW ECAM, WE CYCLED FLAP LEVER WITH NO CHANGE. WE THEN DISCONTINUED THE APPROACH AND WENT THROUGH THE QRH PROCEDURE. WE WERE PREPARED FOR A LESS THAN 20 FLAP LANDING, BUT WHEN WE FULLY CONFIGURED, SLATS/FLAPS EXTENDED NORMALLY TO 30/40. NORMAL LANDING ACCOMPLISHED AND EMERGENCY WAS TERMINATED. EMERGENCY DECLARED. REMOVED AND REPLACED SFCC 1 REF AMM 27-51-00. OPS CHECK GOOD.

Part: WEB — CRACKED (ZONE 100) · airframe 20,840 hrs · 11,898 cycles

MDCC UNDER FLOOR 1EA WEB CRACKED AT FR47, Y953-Y1456. REPAIRED MDCC UNDER FLOOR CRACKED WEB AT FR47, Y953-Y1456 PER A300-600F SRM53-15-15- 201 FIG.201.THIS IS CAT B REPAIR AND IT MUST BE INSPECTED AT DEFINED INTERVALS PER A300- 600F SRI53-15-15-2-002-00. INSPECTION THRESHOLD FROM REPAIR EMBODIMENT:24000FC, SUBSEQUENT INSPECTION AT INTERVAL OF 3000FC.INSPECTION METHOD: DETAILED VISUAL. MAJOR REPAIR IAW FEDEX GMM 6-2-100.

Part: WARNING MESSAGE — FALSE ACTIVATION · airframe 19,973 hrs · 11,340 cycles

DURING APPROACH AND SLAT EXTENSION, RECEIVED ECAM. SLAT SYS 1 FAULT. & FLAPS SYS 1 & 2 FAULT. CYCLE PER ECAM. FAULT DID NOT CLEAR. ALL 3 FAULTS RETURNED INCLUDING AMBER ECAM KRUGER NOT EXTENDED. COMPLIED WITH QRH DECLARED EMERGENCY & LANDED. LT FLAPS SLATS EXTENDED FOR INSPECTION AFTER LANDING. NO FAULTS NOTED DURING POST FLIGHT INSPECTION, PERFORMED BITE PROCEDTURE ON SFCC 1 AND 2 IAW TSM 27-50-00, NO FAULTS FOUND, PERFORMED FLAPS & SLATS OPS TEST MULTIPLE TIMES IAW AMM 27-54-00-05, OPS TEST GOOD, INSPECTED SLATS / KRUEGER FLAPS IAW AMM 27-80-00-00, NO DAMAGE NOTED. A/C OK FOR SERVICE.

Part: HINGE — DELAMINATED (LT WING SPOILER) · airframe 18,039 hrs · 10,135 cycles

LH WING - 4# SPOILER I/B HINGE LOWER SURFACE DELAMINATED (S=20MM X 15MM,D=2.18MM), I/B HINGE INBD SURFACE DELAMINATED (S=60MM X 60MM,D=1.90MM). LH WING - 4# SPOILER I/B HINGE DELAMINATED.COMPLIED WITH EA: 6-5750-T0356106. TITLE: WING - FLIGHT SURFACES - LH 4# SPOILER CENTER HINGE ARM LOWER AND OUTSIDE SURFACE DELAMINATION. THIS IS CAT A REPAIR. MAJOR REPAIR IAW FEDEX GMM 6-2-100.

Part: HINGE ARM — DELAMINATED (RT WING SPOILER) · airframe 18,039 hrs · 10,135 cycles

RH WING - #3 SPOILER O/B CTR HINGE ARM LWR SURFACE DELAMINATED (S=10MM X 15MM,D=2.0MM), I/B CTR HINGE ARM I/B SURFACE DELAMINATED (S=30MM X 40MM,D=1.5MM). RH WING - #3 SPOILER I/B & O/B CTR HINGE ARM DELAMINATED.COMPLIED WITH EA: 6-5750- T0356102. TITLE: WING - FLIGHT SURFACES - RH 3# SPOILER CENTER HINGE ARM LOWER AND OUTSIDE SURFACE DELAMINATION. THIS IS CAT A REPAIR. MAJOR REPAIR IAW FEDEX GMM 6-2- 100.

Part: SKIN — DELAMINATED (RT WING SPOILER) · airframe 18,039 hrs · 10,135 cycles

RT WING NR 5 SPOILER I/B CTR HINGE ARM I/B SURFACE DELAMINATED (S=30MM X 40MM, D=1.3MM), O/B CTR HINGE ARM O/B SURFACE DELAMINATED (S=30MM X 40MM, D=1.5MM), O/B CTR HINGE ARM LOWER SURFACE DELAMINATED (S=20MM X 20MM, D=2.1MM). RT WING NR 5 SPOILER I/B & O/B CTR HINGE ARM DELAMINATED. COMPLY WITH EA: 6-5750-T0356107. TITLE: WING-FLIGHT SURFACES-RT NR 5 SPOILER CENTER HINGE ARM LOWER AND OUTSIDE SURFACE DELAMINATION. THIS IS CAT A REPAIR. MAJOR REPAIR, IAW FEDEX GMM 6-2-100.

Part: HINGE ARM — DELAMINATED (RT WING SPOILER) · airframe 18,039 hrs · 10,135 cycles

RT WING, NR 4 SPOILER I/B CTR HINGE ARM I/B SURFACE DELAMINATED (S=30MM X 40MM,D=1.5MM), O/B CTR HINGE ARM O/B SURFACE DELAMINATED (S=30MM X 25MM,D=1.45MM). RT WING, NR 4 SPOILER I/B & O/B CTR HINGE ARM DELAMINATED. COMPLY WITH EA: 6-5750-T0356104; TITLE: WING-FLIGHT SURFACES-RT NR 4 SPOILER CENTER HINGE ARM OUTSIDE SURFACE DELAMINATION. THIS IS CAT A REPAIR, MAJOR REPAIR IAW FEDEX GMM 6-2-100.

Part: HINGE ARM — DELAMINATED (NR 4 SPOILER) · airframe 18,039 hrs · 10,135 cycles

RH WING - #4 SPOILER I/B CTR HINGE ARM I/B SURFACE DELAMINATED (S=30MM X 40MM,D=1.5MM), O/B CTR HINGE ARM O/B SURFACE DELAMINATED (S=30MM X 25MM,D=1.45MM).

Part: FRAME — CRACKED (FRM 40) · airframe 18,039 hrs · 10,135 cycles

NDT INSP RT CENTER WING JOINT AT FR40 UPPER HOLE FOUND CRACKED SIGNAL. NDT INSP RT CENTER WING JOINT AT FR40 UPPER HOLE FOUND CRACKED SIGNAL. COMPLIED WITH EA: 6-5710-T0356266 P1. TITLE: WINGS-BASIC WING STRUCTURE-CRACK IN THE UPPER HOLE AT FR40 RHS CENTER WING JOINT. THIS IS CAT B REPAIR. THRESHOLD: TH=IT=3260FC/7041FH, INTERVAL: TH=IT=3260FC/ 7041FH. METHOD OF INSPECTION: AFTER FASTENER AND BUSHER REMOVAL, DO A ROTOTEST INSPECTION(NTM51-10-01). MAJOR REPAIR, IAW FEDEX GMM 6-2-100.

Part: JOINT — CRACKED (FRAME 40) · airframe 18,039 hrs · 10,135 cycles

NDT INSPECTION, RT CENTER WING JOINT AT FR40 UPPER HOLE FOUND CRACKED SIGNAL.

Part: GCU — MALFUNCTIONED (NR 2) · airframe 17,769 hrs · 9,958 cycles

PDIS 689 24-20 1465 20MAY20 GENERATOR #2 FAULT @ CLIMB FROM FL 300 TO FL 330. TRIED RESET GENERATOR #2 WOULD NOT RESET .ATTEMPTED START OF APU @ FL 330 WOULD NOT START.DESCENDED TO FL250 TO ATTEMPT SECOND START OF APU . APU WOULD NOT START. DECLARED EMERGENCY AND RETURNED TO MEMPHIS THE NEAREST SUITABLE AIRPORT REMOVED AND REPLACED #2 GCU REF. A300-600 AMM 24-22-12-04. OPS CHECK GOOD. PERFORMED 2 ENGINE RUNS WITH #2 GEN AS ONLY POWER SOURCE. NO DEFECTS NOTED VOLTS AND FREQS WERE STEADY.

Part: SKIN — DENTED (CARGO DOOR) · airframe 15,088 hrs · 8,400 cycles

CARGO DOOR EXTERNAL SKIN HAS TWO DENTS. 5 INCHES FROM FWD LOWER CORNER, 1 INCH. AND 4 INCHES FROM FWD EDGE. FOUND TO BE OUT OF LIMITS IAW SRM 52-30-00, CUT OUT DAMAGED AREA, FABRICATED A REPAIR DOUBLER AND INSTALLED IAW SRM 52-34-00. MAJOR REPAIR.

Part: SEAT TRACK — DAMAGED (FRAMES 63-64) · airframe 15,088 hrs · 8,400 cycles

MAIN CABIN SEAT TRACK -Y1959 DAMAGED BETWEEN FRAMES 63 AND 64. REMOVED DAMAGED SECTION FROM THE SEAT TRACK IAW SRM 51-40-21. FABRICATED A REPAIR IAW SRM 53-10-16, PG 207, FIG 202. INSTALLED THE REPAIR IAW SRM 51-40-21. MAJOR REPAIR.

Part: SOLENOID VALVE — INOPERATIVE (SLAT / FLAP SYS) · airframe 14,356 hrs · 7,958 cycles

SLATS & FLAPS SYSTEM 1 AND 2 FAULTED WHEN THE HANDLE WAS SELECTED TO 15/20. FLAPS WOULD RETRACT TO 0 WHEN SELECTED, BUT ONLY EXTEND TO 15/15 WITHOUT A FAULT INDICATION. REPLACED A FAULTY SOLENOID MM 27-54-33-04. OPERATED FLAPS AND SLATS FOR 6 CYCLES WITH BOTH ENGINES RUNNING, NO FAULTS ON EITHER SFCC, OR ON OVERHEAD AND NO ASSYMETRY LOCKOUT. SYSTEM OPS CHECKED NORMAL.

Part: VALVE — CRACKED (HYD SYSTEM) · airframe 13,853 hrs · 7,659 cycles

AT TOP OF DESCENT, THE GREEN SYS HYD QTY LOW ECAM ILLUMINATED. ECAM AND OVERHEAD BOTH INDICATED QTY LOSS. NO AIR LIGHT WAS ASSOCIATED WITH THIS PROBLEM. MANUALLY EXTENDED GEAR IAW QRH. AFTER LANDING, THE GREEN SYS QTY REAPPEARED BOTH ECAM AND OVERHEAD. INDICATION RETURNED TO PREDISPATCH QTY LEVELS. REMOVED AND REPLACED THE LT ENGINE GREEN SYSTEM PYLON MANIFOLD RESTRICTOR VALVE IAW AMM 29-11-61-04.

Part: GAUGE — LEAKING (DOOR ASSIST) · airframe 13,848 hrs · 7,654 cycles

R1 ENTRY DOOR EMERGENCY CYLINDER PRESSURE GAUGE IS MISSING CENTER PLUG IN LENS AND IS LEAKING OIL FROM GAUGE. REMOVED AND REPLACED R1 DOOR DAMPER EMERGENCY OPERATION CYLINDER IAW MM 52-10-14-04-02.

Part: RELIEF VALVE — FAILED (HYD SYSTEM) · airframe 13,844 hrs · 7,652 cycles

RIGHT AFTER DEPARTING AT FL 340, DURING DESCENT, RECEIVED A GREEN HYD RESERVOIR LOW LEVEL WARNING. CONFIRMED ON OVERHEAD AND ECAM. FOLLOWED ECAM AND QRH PROCEDURES. MANUALLY EXTENDED LANDING GEAR AND SHUT DOWN APPROPRIATE EQUIPMENT. DECLARED EMERGENCY. ACCOMPLISHED LEAK CHECK IAW TSM FLOW CHART FOR LOW AIR IAW TSM 29-34. FOUND DEPRESSURIZATION VALVE LEAKING AIR. INSTALLED A NEW PRESSURE RELIEF VALVE ON GREEN SYSTEM IAW AMM 29-11-27-04. LEAK CHECKED, NO LEAKS NOTED.

Part: VALVE — STUCK (HYDRAULIC SYS) · airframe 13,840 hrs · 7,651 cycles

ON DESCENT TO KMEM, GOT GREEN HYD RESERVOIR LO LEVEL. CONFIRMED ON OVERHEAD & ECAM. FOLLOWED QRH PROCEDURE & MANUAL EXTENDED GEAR AND SHUT DOWN AFFECTED EQUIPMENT. DECLARED EMERGENCY & STOPPED ON RWY. GREEN RSVR AIR CAME ON THEN QUAN FLUCTUATED. NO PUMPS OR SYS RUN W/O FLUID. AFTER LANDING QUAN NORM. FOUND GRN DEPRESS VLV STUCK OPEN. R&R GRN RSVR DEPRESS VALVE, LK CK OK. CK'D GRN SYS HYD DPI'S. NONE TRIPPED. RAN ENG'S. GRN EDP'S OPS CK OK. GRN ACMP'S OPS CK OK. LK CK OK.

Part: FLUID — LOW (NR 2 IDG) · airframe 12,047 hrs · 6,580 cycles

ON TAKEOFF ROLL, JUST AFTER SETTING TAKEOFF POWER, ECAM FLASHED LOW OIL PRESS, THEN WENT AWAY, GEN NR 2 FAILED SHORTLY AFTER. REJECTED TAKEOFF PRIOR TO 70 KTS. DURING IDLE RUN NR 2 ENG WAS READING 16 QTS. CHECKED OIL SERVICING ON NR 2 ENG SERVICED WITH 1/2 QT, INDICATOR READS 20 QTS IAW 12-13-79. CHECKED NR 2 ENG IDG SERVICE FOUND NR 2 IDG LOW ON OIL. SERVICED IAW 12-13-24-00-02. NO FURTHER INDICATIONS OR FAULTS NOTED. ACFT OK TO CONTINUE.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MDCC FLOOR PANEL 231 JG PUNCTURED ON SEVERAL PLACES. FABRICATED NEW PANEL ON T15 1172142 IAW DWG SRZ 25-005 REV L. CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MAIN DECK FLOOR PANEL 251 CH IS DELAMINATED. FABRICATED NEW PANEL ON T15 1172111 IAW DWG SRZ 25-005 REV L. CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 119 hrs · 6,522 cycles

FLOORBOARD PANEL 241 LK HAS CRACKED. FABRICATED NEW PANEL ON T15 1172117 IAW DWG SRZ 25-005 REV L. CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — BROKEN (ZONE 200) · airframe 119 hrs · 6,522 cycles

MCD FLOOR PANEL 232 ZG HAS BROKEN BOTTOM COMPOSITE LAYER ON RT EDGE CORNER. FABRICATED NEW PANEL ON T15 1172044 IAW DWG SRZ 25-005 REV L. CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MAIN DECK CARGO COMPARTMENT, FLOOR PANEL 232 VH DAMAGED. FABRICATED NEW PANEL ON T15 1172146 IAW DWG SRZ 25-005 REV L. CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 119 hrs · 6,522 cycles

FLOORBOARD PANEL 242QJ HAS PUNCTURED HOLE. FABRICATED NEW PANEL ON T15 1172048 IAW DWG SRZ 25-005 REV L. THIS REPAIR IS CLASSIFIED AS A CATEGORY A MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MAIN CABIN DECK FLOOR PANEL 241 KJ HAS CRACKED. FABRICATED NEW PANEL ON T15 1172744 IAW DWG SRZ 25-005 REV L CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MAIN DECK FLOOR PANEL 231 BH DAMAGED. FABRICATED NEW PANEL ON T15 1172143 IAW DWG SRZ 25-005 REV L CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MAIN DECK CARGO FLOOR PANEL 242 PF HAS DELAMINATED ON LT FWD EDGE CORNER. FABRICATED NEW PANEL ON T15 1172149 IAW DWG SRZ 25-005 REV L, CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 119 hrs · 6,522 cycles

FLOORBOARD PANEL 241 LK HAS CRACKED. FABRICATED NEW PANEL ON T15 1172117 IAW DWG SRZ 25-005 REV L. CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MCD FLOOR PANEL 232 HG LOWER SURFACE DAMAGED AT FASTENER HOLE. FABRICATED NEW PANEL ON T15 1172057 IAW DWG SRZ 25-005 REV L CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 119 hrs · 6,522 cycles

FLOORBOARD PANEL 241 AJ HAS ELONGATED MOUNTING HOLE. FABRICATED NEW PANEL ON T15 1172144 IAW DWG SRZ 25-005 REV L CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MAIN DECK FLOOR PANEL 231 UG DAMAGED. FABRICATED NEW PANEL ON T15 1172121 IAW DWG SRZ 25-005 REV L CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MAIN DECK FLOOR PANEL 251GF DAMAGED. FABRICATED NEW PANEL ON T15 1172147 IAW DWG SRZ 25-005 REV L. THIS REPAIR IS CLASSIFIED AS A CATEGORY A MAJOR REPAIR.

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MCD FLOOR PANEL 232 BH HAS DELAMINATED ON RT FWD EDGE CORNER. FABRICATED NEW PANEL ON T15 1172035 IAW DWG SRZ 25-005 REV L. CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MCD FLOOR PANEL 232 QG HAS CRACK ON MID AFT AREA. FABRICATED NEW PANEL ON T15 1172120 IAW DWG SRZ 25-005 REV L. CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 119 hrs · 6,522 cycles

PANEL 242ZJ HAS A CUT, APPROX .5 INCHES. FABRICATED NEW PANEL ON T15 1172055 IAW DWG SRZ 25-005 REV L. REPAIR IS CLASSIFIED AS A CATEGORY A MAJOR REPAIR.

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MAIN DECK FLOOR PANEL 251 BH IS BROKEN. FABRICATED NEW PANEL ON T15 1172119 IAW DWG SRZ 25-05 REV L. CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MAIN DECK FLOOR PANEL 251 HH IS DELAMINATED. FABRICATED NEW PANEL ON T15 1172064 IAW DWG SRZ 25-05 REV L. CLASSIFIED AS MAJOR CAT A REPAIR.

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 119 hrs · 6,522 cycles

MAIN DECK FLOOR PANEL 252 BH, AFT, IS BROKEN DOT 135-5. FABRICATED NEW PANEL ON T15 1172116 IAW DWG SRZ 25-05 REV L. CLASSIFIED AS MAJOR CAT A REPAIR.

Part: INTERCOSTAL — BENT (FUSELAGE) · airframe 119 hrs · 6,522 cycles

MDC FRAME 49 FROM Y 0 TO - Y450 HAS BENT INTERCOSTAL FEATURE. REMOVED INTERCOSTAL AT FRAME 49, BETWEEN 0 - TO -Y450 IAW SRM 51-40-21. FABRICATED NEW INTERCOSTAL ON T15 1171519. INSTALLED NEW INTERCOSTAL AT FRAME 49, BETWEEN 0 TO -Y450 IAW SRM 51-40-21, MAJOR REPAIR.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 119 hrs · 6,522 cycles

MAIN DECK FLOOR SUPPORT BEAM, UPPER SURFACE HAS CORROSION AT FRAME 12, Y450. REMOVED DAMAGE IAW SRM 51-74-10 & CHECKED LIMITS, ORIGINAL MATERIAL = 0.079". REMOVED 0.20", NO ALLOWABLE DAMAGE LIMITS FOUND IN SRM TR 17450. REMOVED FLOOR SUPPORT AT FRAME 12, Y450 IAW SRM 51-40-21. FABRICATED NEW FLOOR SUPPORT ON T15 1172329. INSTALLED NEW FLOOR SUPPORT AT FRAME 12, Y450 IAW SRM 51-40-21, FROM FRAME 11 - 13, MAJOR REPAIR.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 119 hrs · 6,522 cycles

MDC FRAME 48, Y 0 TO -Y450, HAS CRACKED ON INTERCOSTAL. REMOVED INTERCOSTAL AT FRAME 48, BETWEEN 0 TO -Y450 IAW SRM 51-40-21. FABRICATED NEW INTERCOSTAL ON T15 1171512. INSTALLED NEW INTERCOSTAL AT FRAME 48, BETWEEN 0 TO -Y450 IAW SRM 51-40-21, MAJOR REPAIR.

Part: FITTING — CRACKED (FUSELAGE) · airframe 11,929 hrs · 6,522 cycles

MDC FRAME 48, -Y1456 HAS CRACKED UNDER FLOOR BRACE LOWER FITTING. R & R ONE EACH FITTING AT FRAME 48, -Y1456 UNDER FLOOR LOWER BRACE IAW SRM 51-40-21. PN A5381206720001.

Part: LUG — CORRODED (LT WING) · corrosion level 2 · airframe 10,848 hrs · 5,911 cycles

LEFT MLG FWD LUG HAS CORROSION IN BORE & ON FWD & AFT FACES COMPLIED WITH EA T 6- 5710 T0303688 P5. TERMINATING ACTION OF RIB 5 FWD LUG LT. WINGS BASIC WING STRUCTURE. MAJOR REPAIR.

Part: LUG — CORRODED (RT WING) · corrosion level 2 · airframe 10,848 hrs · 5,911 cycles

RIGHT MLG FWD LUG HAS CORROSION IN BORE & ON FWD & AFT FACES COMPLIED WITH EA T 6- 5710 T0303688 P6. TERMINATING ACTION OF RIB 5 FWD LUG RT. WINGS BASIC WING STRUCTURE. MAJOR REPAIR.

Part: TRANSMITTER — INOPERATIVE (HYD SYSTEM) · airframe 9,391 hrs · 5,114 cycles

ENROUTE AT FL370, WATCHED GREEN HYD RESERVOIR LEVEL DROP TO RED DOT. COMPLIED WITH QRH. LOSS OF GREEN SYS DID NOT REACH RED DOT IN YELLOW BAND. DURING LANDING, REPORTED THAT GREEN SYS RETURNED TO HAT BAND AREA. RAN GREEN HYD SYSTEM & OPERATED FLIGHT CONTROLS. GREEN SYS MAINTAINED 3000 PSI PRESSURE & DID NOT LOSE FLUID QTY. REMOVED AND REPLACED GREEN HYDRAULIC RESERVOIR QTY TRANSMITTER IAW MM 29-31-11-04. OPS AND LEAK CHECKED GOOD. RESTORED FREE FALL MECHANISM TO NORMAL OPERATING CONDITION. IAW MM 32-33-00-02.

Part: SPLICE — CRACKED (FRAME 47) · airframe 9,371 hrs · 5,109 cycles

FUSELAGE FRAME 47, STRINGER 24 - 26R SPLICE FITTING FOUND CRACKED, COMPLIED WITH EO 6-5310-7-5017 P6.

Part: SELECTOR VALVE — MALFUNCTIONED (HYD SYSTEM) · airframe 8,481 hrs · 4,602 cycles

AT LEVEL OFF RECEIVED YELLOW HYD LOW PRESS THEN LOW QUANTITY. FOLLOWED QRH SECURED YELLOW SYSTEM AND CONTINUED TO DESTINATION. REPLACED MCD SELECTOR VALVE IAW MM 52-33-53-04. OPS AND LEAKS CHECKS NORMAL ACFT OK FOR SERVICE.

Part: SKIN — GOUGED (RT WING TE FLAP) · airframe 6,019 hrs · 3,293 cycles

RT INBD FLAP UPPER SURFACE APPROX 18" AFT OF L/E AND 1.5" OTBD OF RIB 6A; THERE IS A GOUGE APPROX 6 IN LONG X 2.5 INCHES WIDE AND 0.070 IN DEEP AT DEEPEST AREA. BLENDED DAMAGED AREA IAW SRM 51-73-10, CHECKED LIMITS - ORIGINAL .031, REMAINING .013, MATERIAL LOSS .018. FOUND TO BE OUT OF LIMITS IAW SRM 57-50-00. NDT FOR CRACKS NO CRACKS NOTED. REMOVED DAMAGED AREA, FABRICATED AND INSTALLED REPAIR PATCH IAW TD FOK/279/2011 ISSUE B AND REPROTECTED AREA IAW SRM 51-75-10. OPS CHECK AND GAP CHECK OF INNER RT FLAP AND MOVABLE FAIRING GOOD IAW AMM 27-50-21-04.

Part: SKIN — DAMAGED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

FWD CARGO DOOR CUTOUT AT FR 20 APPROX 30" UP FROM SILL BEAM THERE IS A FIELD BLEND THAT MEASURES APPROX 1.5 IN L X .500 W X .100 IN D. REPAIRED IAW SRM 53-13-13, FIG 201-210.

Part: FLOORBEAM — BENT (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

AFT CARGO COMPARTMENT RT SIDE FR 63 BETWEEN SEAT TRACK 4R AND 5R, UPPER FLOORBEAM IS BENT. ACCOMPLISHED REPAIR TO AFT CARGO FR C-63 DAMAGE IAW E.A. 6-5310-152428.

Part: STIFFENER — BENT (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

AFT CARGO UPPER CEILING AT FR 62 AT SEAT TRACK NR4 RT SIDE HAS A STIFFENER BENT. REMOVED ANGLE STIFFENER PER SRM 51-40-21 PARA 7. FABRICATED 1EA ANGLE STIFFENER PER DWG A53275446. REPROTECTED ANGLE STIFFENER PER SRM 51-21-10 AND SRM 51-75-10. LOCATED AND DRILLED ANGLE STIFFENER PER SRM 51-40-44, AND INSTALLED PER SRM 51-40-21.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

FLOORBOARD 251JF HAS CORNER BROKEN OFF, FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRS 25-005, REV J.

Part: FLOOR PANEL — MISMANUFACTURED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

FLOOR PANEL 2426F FABRICATED INCORRECTLY, MISSING 1 X 1.5 LEG ON END. FABRICATED PANEL 2426F IAW DWG SRZ 25-005 REV. J.

Part: FLOORBOARD — DAMAGED (MAIN DECK) · airframe 6,019 hrs · 3,293 cycles

MDCC FLOORBOARD 252 GF, NR2 IS BROKEN, 1 EA SECTION. FABRICATED REPLACEMENT FLOORBOARD 252, GF 2 IAW DWG SR2 25-005.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

MAIN CABIN CARGO ZONE 240 FLOORBOARD, 242RJ BROKEN AT CLEVIS ATTACH POINT. FABRICATED REPLACEMENT FLOORBOARD 242RJ.

Part: FLOORBEAM — BENT (BS 4150) · airframe 6,019 hrs · 3,293 cycles

AFT CARGO FLOORBEAM AT FRAME 63 IS BENT, BS 4150. FABRICATED CHANNELS FOR FLOORBEAM REPAIR IAW SRM 53-10-15, FIG 207. REPAIR ACCOMPLISHED ON SNRM N00007 AND EA 6-5310-152428.

Part: FLOOR SUPPORT — BENT (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

MAIN CARGO CABIN FRAME 48 TO FRAME 50 RT SIDE BETWEEN SEAT TRACKS 1 & 2 FLOOR SUPPORT BENT. REMOVED FLOOR SUPPORT IAW SRM 51-72-10. FABRICATED FLOOR SUPPORT IAW SRM 53-15-15 FIG.9 AND DWG A53813946. LOCATED AND DRILLED FLOOR SUPPORT . INSTALLED FLOOR SUPPORT IAW SRM 51-72-10 AND DWG A53813911.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

MAIN DECK CARGO COMPARTMENT FLOOR PANEL 251BF IS BROKEN IN HALF ON BOTTOM SURFACE. FABRICATED REPLACEMENT FLOOR PANEL 251BF IAW DWG SRZ 25-005, REV J.

Part: SHEAR PLATE — CRACKED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

GUSSET ON RT SIDE OF ACFT FUSELAGE FLOOR LEVEL BEHIND LOWER SIDEWALL AT FR 79, CRACKED. REMOVED SHEAR PLATE RT SIDE FLOOR LEVEL AT FR 79 IAW SRM'S 51-40-21 AND 51-72-10. LOCATED AND DRILLED NEW SHEAR PLATE IAW SRM 51-72-10. INSTALLED NEW PLATE IAW SRM'S 51-72-10 AND 51-40-21.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

MAIN DECK CARGO COMPARTMENT FLOOR PANEL, 252GF CRACKED. FABRICATED REPLACEMENT PANEL 252GF IAW DWG SRZ 25-005, REV J.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

MAIN DECK CARGO COMPARTMENT FLOOR PANEL 252DF TIP BROKEN OFF. FABRICATED REPLACEMENT FLOOR PANEL 252DF IAW DWG SRZ 25-005, REV J.

Part: SHEAR PLATE — CRACKED (ZONE 500) · airframe 6,019 hrs · 3,293 cycles

GUSSET ON LT SIDE OF AFT FUSELAGE FLOOR LEVEL BEHIND LOWER SIDEWALL AT FR 79, CRACKED. REMOVED LT SIDE SHEAR PLATE AT FLOOR LEVEL AT FR 79 IAW SRM'S 51-40-21 AND 51-72-10. LOCATED AND DRILLED NEW SHEAR PLATE IAW SRM 51-72-10, INSTALLED NEW SHEAR PLATE IAW SRM 51-72-10 AND 51-40-21.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

MAIN DECK CARGO COMPARTMENT FLOOR PANEL 242UF IS BROKEN. FABRICATED REPLACEMENT FLOOR PANEL 242UF IAW DWG SRZ 25-005, REV J.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

FLOOR PANEL 242GF HAS 1EA 9" CRACK ON BOTTOM SURFACE. FABRICATED REPLACEMENT FLOOR PANEL 242GF IAW DWG SRZ 25-005, REV. J.

Part: FLOOR PANEL — BROKEN (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

FLOOR PANEL 242KF IS BROKEN IN HALF. FABRCATED REPLACEMENT PANEL 242KF IAW DWG SR2 25-005.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

FLOOR PANEL 242BF IS BROKEN IN HALF. FABRICATED REPLACEMENT FLOOR PANEL 242BF IAW DWG SRZ 25-005 REV. J.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 6,019 hrs · 3,293 cycles

FLOOR PANEL 143DF IS OIL SOAKED. FABRICATED REPLACEMENT PANEL 143DF IAW DWG SRZ-25-005, REV J. IDENTIFIED REPLACEMENT PANEL IAW GMM 7-0-1001.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 6,019 hrs · 3,293 cycles

FLOOR PANEL, 242SF, HAS 3 EA, 2" CRACKS ON BOTTOM SURFACE. FABRICATED REPLACEMENT PANEL 242SF IAW DWG SRZ-25-005, REV J AND IDENTIFIED REPLACEMENT PANEL 242SF IAW GMM 7-0-1001.

Part: SMOKE DETECTOR — INOPERATIVE (E/E BAY) · airframe 3,733 hrs · 2,001 cycles

WHEN LANDING GEAR WAS LOWERED AVIONICS SMOKE WARNING CAME ON - THERE WERE NO OTHER INDICATIONS OF SMOKE - WARNING WENT ON/OFF EVERY 5 SECONDS -AFTER LANDING AND TAXI - IN MECHANICS AND FIRE RESCUE FOUND NO EVIDENCE OF SMOKE - ALL WARINGS CEASED WHEN ENGINES WERE SHUTDOWN. TSM 26-16-00 AVIONICS SMOKE TEST NORMAL. CLEANED BACK OF MTP SMOKE TEST PANEL IAW SMP, INSP. CONNECTOR AT SMOKE DETECTOR 13WA, CK'S GOOD. REPLACING SMOKE DETECTOR, PRECAUTIONARY, IN WORK. REPLACED AVIONICS SMOKE DETECTOR 13WA IAW MM 26-15-12-4 TESTS OKAY. RAN APU WITH PACKS FOR 15 MIN, ALL INDICATIONS NORMAL, OKAY TO CONTINUE.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 2,771 hrs · 1,468 cycles

MDCC SEAT TRACK 5R 12 INCHES FWD OF FR 64 HAS A WORN SCALLOP REPAIRED SEAT TRACK IAW SRM 53-10-16 FIG 201.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 2,771 hrs · 1,468 cycles

MAIN DECK CARGO COMPARTMENT SEAT TRACK NR 2 RT, 6 INCHES FWD OF FR 64 HAS 1 WORN SCALLOPS. REMOVED DAMAGED SECTION OF NR 2 TRACK AND INSTALLED SEAT TRACK SPLICE REPAIR AT SEAT TRACK NR 2 RT BETWEEN FRAME 62 AND FRAME 64 IAW SRM 53-10-16, FIG 201, PAGE 207/208.

Part: ENGINE — FAILED (NR 1) · airframe 2,767 hrs · 1,465 cycles

ON TAKEOFF HEAVY VIBRATION WITH NOISE AND ECAM ADVISORY FOR NR 1 ENGINE N1. NR 1 ENGINE N1 SHOWED MAX OF 3.6. N2 VIB NR 1 ENG 0.6. ALL OTHER ENGINE PARAMETERS NORMAL. COMPLETED INSTALLATION OF FIRST STAGE FAN BLADES ACCORDING TO AMM 72-21-00-4. REINSTALLED SPINNER CONE ACCORDING TO AMM 72-21-00-8. READY FOR VIBRATION SURVEY. ACCOMPLISHED VIBRATION SURVEY PER JRH 7-14, PEAK N1 VIBE NOTED WAS 2.6 AT MAX POWER. ALL PARAMETERS WITHIN LIMITS AT THIS TIME.

Part: UNKNOWN — UNKNOWN (FUEL SYSTEM) · airframe 2,436 hrs · 1,299 cycles

DURING CRUISE, RT OUTER FUEL TANK DROPPED AS LOW AS 7.04 LBS, WHILE LT OUTER TANK REMAINED AT 8.04 LBS & 2 CB'S WITH NO CORRECTION. ARRIVED AT ACFT, FOUND FUEL QTYS ALL NORMAL, L/O AT 8.3, R/O AT 8.3, ECAM AND OVERHEAD TOTALS AGREE WITH TANKS. PRESSURIZED ALL PUMPS / SYSTEMS, INSPECTED ACFT FOR SIGNS OF LEAKS, NONE FOUND. FQIC "SYS MONITOR" SHOWS 'SOFT' CODES 331, 431, 022, 502, 631. CLEARED FQIC, TEST GOOD. SYSTEM IS NOW IN "LA" MODE. TRANSFERED FUEL FROM R/O TO INNERS, ACCOMPLISHED MX STEPS FOR MEL 28-42-01-01. RELEASED FOR SERVICE PER MEL/CDL. ALL RT OUTER TANK INDICATIONS INOP EITHER FUEL TO KNOWN QTY OR, AFTER REFUELING VERIFY TANK QTY WITH MAG MEASURING STICKS, & STICK READINGS, ARE RECORDED IN

Part: RELAY — SURGES (NR 1 ENGINE) · airframe 2,418 hrs · 1,289 cycles

DURING TAKEOFF ROLL NR 1 ENG N1 AND N2 SURGED AFTER TOGA, DROPPED 2 3 PERCENT TIMES. NOTED EGT AND FF GAGES MIRRORED N1 AND N2. REJECTED TAKEOFF AT 85 KTS. FOLLOWED QRH PROCEDURE. REMOVED AND REPLACE RELAY 33KS.

Part: RELAY — FAILED (ENGINE) · airframe 2,418 hrs · 1,289 cycles

DURING T.O. ROLL NR 1 ENG N1 AND N2 SURGED AFTER TOGA, DROPPED 2 % 3 TIMES. NOTED EGT AND F.F. GAGES MIRRORED N1 AND N2. REJECTED TO AT 85 KTS. FOLLOWED QRH PROCEDURE. RETRIEVED FAULT CODE 351-18, 28 VDC POWER DISCONNECT FAULT. PER TSM REMOVED AND REPLACED RELAY 33KS. PERFORMED POWER ASSURANCE RUN. RAN ENG'S AT T/O PWER FOR 5 MIN. NO FAULTS NOTED, NO FLUCTUATIONS NOTED FOR ANY OF THE PARAMETERS. IAW TSM 73-21-30 & JRH.