N812FD

Part: CONTROLLER — FAILED (CABIN PRESSURE) · airframe 56,181 hrs · 13,436 cycles

ON DESCENT TO KMDT RECEIVED CAD REG 2 FAULT, RESET NO HELP. ON LANDING, ACFT SHOWED 3300 CAB ALT, WENT TO MANUAL, TURNED OFF BLEEDS & PACKS. CABIN OUTFLOW VLVS FWD & AFT STAYED CLOSED. OVERBOARD VENT PARTIALLY OPENED, ACFT STILL PRESSURIZED. SAFETY VLV STARTED TO OPEN, FRONT WINDOWS CRACKED, OPENED TO HELP DEPRESSURIZE. WINDOWS ALLOWED TO OPEN & RAPID DE-PRESSURIZED. MEL 10DEC13 14:50 MDT U RELEASED FOR SERVICE IAW MEL 21-31-02-A. CABIN PRESS CONTROL SYS, IDENTIFY 1 OR 2. 2 INOPERATIVE. 2 REG DEACTIVATED & CB OPEN & COLLARED. ENSURE CAB DIF PRESS IS ZERO PRIOR TO OPENING ANY DOORS. PERFORMED CABIN PRESS CONTROL ADJUSTMENT TEST IAW A310 300 AMM 21-31-00-05, NR 2 CONTROLLER FAILED. R&R NR 1 & NR 2 PRESS CONTROLLERS, TESTED GOOD IAW MM21-31-00-05. R&R IAW MM 21-31-11-04. OK FOR CONTINUED SERVICE.

Part: JACKSCREW — CONTAMINATED (SLAT SYSTEM) · airframe 55,892 hrs · 13,250 cycles

NR 1 & 2 SLAT SYSTEMS FAULTED ON APPROACH. COMPLIED WITH PHASE 1, NO HELP. COMPLIED WITH ECAM AND QRH. ON CONFIGURING FOR LANDING IAW QRH SLAT EXTENDED NORMALLY. SFCC 1 & 2 FAULT INDICATES SLAT 01111 SLAT BINDING IAW TSM 27-80-02, FIG 101. FOUND LT L/E TORQUE LIMITER TRIPPED. FOUND TORQUE LIMITERS ACTIVATED ON JACKSCREWS 1, 3 AND 6 LT WING IAW AMM 12-12-27-00 AND 12-13-27-00. DRAIN FLUID AND LUBED BALL NUT ON JACKSCREWS 1, 3, 6. FOUND EVIDENCE OF WATER DURING BALL NUT LUBE ON JACKSCREW NR 1, AND FLUID CONTAMINATION ON JACKSCREW NR 3. LUBE REMAINING JACKSCREWS AS A PRECAUTION. NO DEFECTS NOTED ON JACKSCREW CLAW STOPS. RESET SFCC 1 & 2 WITH ENGINES RUNNING. CYCLED SLAT/FLAP THROUGH FULL RANGE SEVERAL TIMES ALL INDICATONS NORMAL.

Part: CONNECTOR — FAILED (TRANSMIT ANTENNA) · airframe 55,419 hrs · 12,942 cycles

CAPTAIN'S RA DOES NOT PROPERLY AGREE WITH FO'S RA. DURING TROUBLESHOOTING NR 1 R/A WOULD FLUCTUATE BETWEEN 150FT AND 450FT, THEN GO ABOVE 2500FT. DISCONNECTED BOTH TRANSMIT AND RECEIVING ANTENNAS AND METERED BOTH COAX CABLES FROM NR 1 R/A RACK CONNECTOR (1SA1) NR 1, RECEIVING ANTENNA (5SA1) READ OPEN, NR 1 TRANSMITTER ANTENNA (4SA1) READ HIGH RESISTANCE TO GROUND. SUSPECT NR 1 TRANSMIT ANTENNA COAX CONNECTOR BAD.

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 55,383 hrs · 12,924 cycles

LEFT WING OTBD FLAP T/E LOWER SURFACE FOUND DELAMINATED, FROM INBD TO OTBD 2000 MM, DIM:16" X 7". REMOVED DELAMINATED LOWER SKIN IAW SRM 57-53-12/201. MADE NEW SKIN DOUBLER IAW SRM 57-53-12/201. FILLED THE HONEYCOMB CORE WITH COMPOUND IAW SRM 57-53-12/201. SMOOTHED HONEYCOMB CORE IAW SRM 57-53-12/201. WET LAYUP WITH ADHESIVE & FIBERGLASS IAW SRM 57-53-12/201. APPLIED ADHESIVE PRIMER IAW SRM 57-53-12/201. BONDED DOUBLER WITH ADHESIVE IAW SRM 57-53-12/201. DRILLED THE HOLES & DEBURR IAW SRM 51-40-44. INSTALLED RELEVANT FASTENERS IAW SRM 51-40-21. SEALED THE EDGE WITH SEALANT IAW SRM 57-53-12/201. RESTORED THE FINISH IAW SRM 51-75-10.

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 55,383 hrs · 12,924 cycles

RIGHT WING INBD LOWER FLAP T/E MID SECTION FOUND DELAMINATED. REMOVED DELAMINATED DOUBLER & DAMAGED HONEYCOMB CORE IAW SRM 57-52-12/201. MADE NEW SKIN DOUBLER IAW SRM 57-52-12/201. MADE HONEYCOMB CORE PLUG SRM 57-52-12/201. INSTALLED HONEYCOMB CORE PLUG AND EDGE PROFILE IAW SRM 57-52-12/201. SMOOTHED HONEYCOMB CORE IAW SRM 57-52-12/201. BONDED DOUBLER WITH ADHESIVE IAW SRM 57-52-12/201. SEALED THE EDGE WITH SEALANT SRM 57-52-12/201. RESTORED THE FINISH IAW SRM 51-75-10.

Part: FITTING — CORRODED (LT MLG LUG) · airframe 55,383 hrs · 12,924 cycles

LEFT WING-MLG FITTING-INSPECTION OF RIB 5 FORWARD LUG CORROSION EXCEED LIMITS. REMOVED CORROSION IAW REPAIR DWG R57249389, ISSUE B, STEP 1B. IAW EA6-5710-163164. PENETRANT INSPECT THE LUG BORE IAW NTM 51-90-00 TO CONFIRM ALL DAMAGED COMPLETELY REMOVED. IAW EA6-5710-163164. COMPLETED REPAIR IAW R572- 49389 ISSUE B, SECTION B, STEP 2 ON WARDS. IAW EA6-5710-163164.

Part: SPAR — CRACKED (CENTER WING) · airframe 55,383 hrs · 12,924 cycles

CENTER WING RT REAR SPAR NR 61 HOLE FOUND CRACKED. REAMED HOLE AT 0.4MM THROUGH ALL LAYERS PER EA6-5710-163167. INSPECTED PER NTM51-10-01,NO CRACK FOUND. REAMED UP THE HOLE ON ALL LAYERS TO 15.836-15.875MM IN TRANSITION FIT PER EA6-5710-163167. WET INSTALLED A NEW FASTENERS PER SRM51-40-44. PROTECTED AS PER SRM RULES.

Part: PLATE — CRACKED (FUELAGE) · airframe 55,383 hrs · 12,924 cycles

FOUND A CRACK ABOUT 5MM IN LENGTH, 1MM IN DEPTH INITIATED FROM THE NR 2 FASTENER HOLE OF THE RT WING UPPER CORNER ANGLE AT FR40. REAMED NR 2 HOLE AT 0.4MM THROUGH ALL LAYERS PER EA6-5710-163166. INSPECTED PER NTM51-10-01,NO CRACK FOUND. REAMED HOLE ON ALL LAYERS TO 11.476 - 11.515MM. IN TRANSITION FIT PER EA6-5710- 163166. PERFORM ROTOTEST INSPECTION AS PER NTM51-10-01 .NO DAMAGE FOUND.(PER EA6-5710- 163166) 5,WET INSTALLED A NEW FASTENER PER SRM51-40-44.(PER EA6-5710-163166) 5,RE-PROTECTED AS PER SRM RULES.

Part: SOLENOID VALVE — LEAKING (HYD RESEVOIR) · airframe 53,765 hrs · 12,208 cycles

GREEN HYD SYS LO RSVR INDICATION INFLIGHT FOLLOWED QRH, AFTER LANDING GREEN SYS REVR INDICATION RETURNED TO NORMAL. RESTORED FREE FALL EXTENSION SYSTEM TO NORMAL CONDITION AS PER AMM 32-33-00-2. PRESSURED GREEN HYD SYS AS PER AMM29-00-00-06, FOUND KRUEGER SELECTOR SOLENOID VALVE (50CV) HAD SIGNS OF EXTERNAL LEAK. REMOVED AND REPLACED SOLENOID VALVE (50CV) AS PER AMM 27-88-12-04-0. SERVICED GREEN HYD RESERVOIR AS PER AMM12-12-29-00. CLEANED AND SECURED PLUG OF GREEN HYD RESERVOIR QTY TRANSMITER 25GQ. PERFORMED ENG RUN AS PER JRH AND PERFORMED OPS TEST OF SLAT/FLAP AS PER AMM27-84-00-05, NO HYD LEAK NOTED. A/C OK FOR SERVICE.

Part: SKIN — CORRODED (ZONE 100) · airframe 52,428 hrs · 11,629 cycles

FUSELAGE SKIN EXTERIOR SURFACE FOUND CORROSION UNDER BULK CARGO DOOR SCUFF PLATE (FWD LWR CORNER). REMOVE THE CORROSION IAW SRM 51-74-10. APPLY ALODINE IAW SRM 51-21-10. MEASURE REMAIN THICKNESS OF THE REWORKED AREA IAW NTM51-10-04 (REMAINING THICKNESS WAS 0.148 INCH). DO AN HFEC INSP OF THE REWORKED AREA IAW NTM51-10-08 (NO CRACK FOUND) THE ORIGINAL THICKNESS IS 0.158 INCH, SO THE REMAINING THICKNESS IT IS WITHIN THE LIMIT PER SRM53-17-12/FIG104 6.RESTORE FINISH TOTHE REWORKED AREA IAW SRM51-75-10 7.THE ALLOWABLE REWORK MUST BE INSPECTED AT DEFINED INTERVALS IAW SRI53-17-12-1- 002-00

Part: COMPUTER — MALFUNCTIONED (FUEL QTY) · airframe 52,403 hrs · 11,618 cycles

ON TAKEOFF ROLL, MASTER WARNING REPETITIVE CHIME, AT APPROX 130 KTS RTO. ECAM SHOWED PITCH TRIM 2 YD 2 OFF. PITCH TRIM 2 YD 2 BOTH RESET OK. BRAKE 3 670 DEGREES. WHILE WAITING FOR HOT BRAKES TO COOL, FUEL WENT BELOW RQR FOR FOR TO. SO RETURN TO GATE, ON TAXI CAPT FELT LIKE THERE WAS A FLAT TIRE. ON RETURN TO GATE, MX INFORMS OF TIRE 3 FLAT. R & R FQC REF AMM 28-42-38-04 AND CARRIED OUT TEST FUEL QUANTITY SATISFACTORY. PERFORMED THE T/O CONFIG TEST IAW AMM31-51-00-05, AND TEST SATISFACTORY. ACFT OK FOR SERVICE.

Part: B-NUT — LEAKING (HYD SYSTEM) · airframe 51,824 hrs · 11,354 cycles

HYD GREEN SYS SERVICED WITHIN LIMITS, 10 MINUTES AFTER DEPARTURE, QTY IN AMBER BAN D. TURNED OFF NR 1 ENG HYD PUMP PRIOR TO TO RED DOT IN AMBER BAND AT FLT LEVEL 20. 15 MINUTES LATER RESERVOIR EMPTY. COMPLIED WITH QRH. SAFE LANDING. FOUND FLUID LEAKING OUT THE LT ENG HYD SHUTOFF VALVE. TROUBLE SHOT GREEN HYDRAULIC SYSTEM, FOUND LOOSE B-NUT AT THE FIRE SHUTOFF VALVE OF NR 1 ENGINE IS LEAKING. TIGHTENED THE B-NUT. RAN HYDRAULIC SYSTEMS. NO LEAK FOUND. REPLENISHED GREEN SYS HYDRAULIC FLUID TO TOP HAT LEVEL IAW AMM 12-12-00-0. A/C OK FOR SERVICE.

Part: JACKSCREW — FAILED (SLATS) · airframe 51,778 hrs · 11,332 cycles

RECEIVED SLAT SYS 1 AND SYS 2 FAULT. SLAT STUCK AT APPROX 2 DEG, LANDED SLATS 2 DEG AND FLAPS 40 DEG, REPEAT WRITE UP. CYCLED ON THE GROUND PRIOR TO DEPARTURE AND THEY WORKED OK. CYCLED AIRBORN AND THEY STUCK. APPEAR TO BE AIRLOAD RELATED, CYCLED AT 210 KTS. PERFORMED BITE CHECK OF SFCC-1/2 FOUND FAULT CODE 0-0-0-1-0 (LT KRUGER FLAP RETRACT SW) NOTED IN BOTH SF CC. DETAILED INSP OF LT SYS TORQUE LIMITER AND RT SYS TORQUE LIMITER FOUND LT SYS TORQUE LIMITER POPPED OUT. R & R LT NR 2 JACKSCREW IAW AMM 27-84-22-4. THEN ADJ/TEST IAW AMM 27-84-00-5/6, OPS CHECKED 10 TIMES WORKS GOOD WITH ENG RUN IAW JRH CHAP 3/5. ACFT, OK FOR SERVICE.

Part: ANTI-ICE VALVE — WARNING MESSAGE (NR 1 NACELLE) · airframe 51,457 hrs · 11,165 cycles

DURING TAKEOFF ROLL WITH ANTI-ICE ON, RECEIVED ECAM MESSAGE "ENG NR1 ANTI-ICE NAC VALVE". ACCOMPLISHED RTO AT 70 KTS. (RTO 1 OF 2) SEE WRI 30-20/3659 FOR DEFERRAL OF NR1 ENG NAC A/I VALVE. FAULT CLEARED WHEN REDUCING POWER, NO FURTHER FAULTS. CREW TAXIED BACK TO T/O AGAIN. RTO 2ND TIME FOR SAME PROBLEM, FAULT DID NOT CLEAR. SEE WRI 30-20/3659 FOR DEFERRAL OF NR 1 ENG NAC. A/I VALVE. MEL'D AND DEACTIVATED AGAIN.

Part: ANTI-ICE SYSTEM — FAULTED (NR 1 ENGINE) · airframe 51,457 hrs · 11,165 cycles

DURING T/O POWER APPLICATION, WHEN TOGA PWR WAS SELECTED THE GREEN A/THR LIGHT ILLUMINATED HOWEVER THE THROTTLES WOULD NOT MOVE. ACCOMPLISHED RTO AT 25 KTS. VERIFIED AT BLOCK IN NR1 ENGINE ANTI ICE WAS FAULTING IN ECAM. RELEASED FOR SERVICE IAW MEL: 22-30-01-A CATEGORY: C EXPIRATION: 30NOV09 "MEL 22-30-01-A: ATS - INOP, ALL THRUST SETTINGS MUST BE MANUALLY SET. NO OPS WITHIN METRIC AIRSPACE. A/C CATII" CHECKED HISTORY WITH NONE FOUND FOR 25 DAYS. RAN A COMPLETE AUTO THROTTLE CHECK IAW MM 22-30-00-5 AND ALL SYS TEST NORMAL. A/T SYS IS GOOD TO GO. ACFT IS STILL CAT-2 DUE AUTO BRAKING.

Part: ANTI-ICE VALVE — FAULTED (NR 1 NACELLE) · airframe 51,457 hrs · 11,165 cycles

DURING TAKEOFF ROLL AT 85KTS ECAM WARNING "ENG NAC ANTI ICE VALVE". ACCOMPLISHED RTO (ENG NR1) ENG ANTI ICE WAS ON DURING TAKE OFF. VERIFIED AT BLOCK IN NR 1 ENG ANTI ICE WAS FAULTING IN ECAM. VERIFIED AT BLOCK IN NR 1 ENG ANTI ICE WAS FAULTING IN ECAM. "MEL 30-21-01-E: ENGINE (IDENTIFY 1 AND/OR 2) 1 ANTI-ICE VALVE - INOP. ENGINE NACELLE VALVE(S) SECURED OPEN." R & R NR1 ENGINE NACELLE ANTI-ICE VALVE IN REF TO AMM 30-21-11-4. OPS CHECK GOOD. OK FOR SERVICE. AWAITING TDR RESULTS.

Part: BRAKE SYS — MALFUNCTIONED (MLG) · airframe 51,457 hrs · 11,165 cycles

DURING TRO WITH MAX BRAKES SELECTED, ONLY WHEEL BRAKES ON NR1,2,5,6 (LT SIDE) OPERATED NORMALLY. ACFT STARTED ABRUPT PULL TO LT DESELECTED AUTO BRAKES AND STOPPED USING MANUAL BRAKES. MEL 20NOV09 14:24 GRR RELEASED FOR SERVICE IAW MEL: 32-42-05 CATEGORY: C, EXPIRATION: 30NOV09 "MEL 32-42-05: AUTOBRAKE SYS - INOP. COMPLETED BITE TEST OF BRAKE SYS CONTROLLER AND ANTI SKID NO FAULTS LOGGED ALL TESTS PASS IN REF TO TSM32-42-00. UNABLE TO PERFORM HIGH SPEED TAXI TO DUPLICATE PROBLEM. NO HISTORY FOR 99 DAYS.

Part: CONTROL UNIT — BINDING (RUDDER) · airframe 50,646 hrs · 10,615 cycles

SECOND REJECTED T/O DUE TO BLUE RUDDER SERVO CONTROL JAM, ECAM WARNING CAME ON AT 40-50 PERCENT N1. NO FAULT FOUND ON 1ST RTO. RAN ENGINE & CHECKED ALL FLT CONTROL OPERATIONS (WRI 27-20/2731). REPLACED JAMMING DETECTION CONTROL UNIT IAW AMM 27-14-17-4 PRECAUTIONARY. R & R BLUE SYS RUDDER SERVO JAM DETECTION SWITCH, 22CB, IAW AMM 27-24-12-4. OPS CHECKED GOOD. R & R BLUE SYS RUDDER ACTUATOR IAW AMM 27-24-11-4.

Part: CONTROL UNIT — INOPERATIVE (RUDDER) · airframe 50,646 hrs · 10,615 cycles

2ND REJECTED TAKEOFF DUE TO BLUE RUDDER SERVO CTL JAM, ECAM WARNING CAME ON AT 40-50 PERCENT N1. NO FAULT FOUND ON 1ST RTO, RAN ENG AND CHECKED ALL FLT CONTROL OPERATION (WRI 27-20/2731). REPLACED JAMMING DETECTION CONTROL UNIT PER AMM 27-14-17-4 PRE CAUTIONARY REMOVED AND REPLACED BLUE SYSTEM RUDDER SERVO JAM DETECTION SWITCH, 22CB, PER AMM 27-24-12-4. OPS CHECKS GOOD. REMOVED & REPLACED BLUE SYSTEM RUDDER ACTUATOR IAW AMM 27-24-11-4.

Part: SKIN — DAMAGED (RUDDER) · airframe 50,486 hrs · 10,479 cycles

UPON INSPECTION OF RUDDER BY THERMOGRAPHY IAW EO 6-5530-7-5004 PT 2 PARA 8 STEP C AND D THE FOLLOWING DEFECTS WERE NOTED IN ADDITION TO ORIGINAL FINDINGS REF EA 6-5740-118399 THE UPPER RT PORTION OF THE RUDDER HAS 1 ADDITIONAL AREA OF MOISTURE MEASURING .960 WIDE BY .600 TALL APPROX 1.5 INCHES AFT OF 37MM NOTED AREA. REMOVED DAMAGE AND REPAIRED RUDDER IAW EA 6-5540-121333, RELEASE DATE 24 JUL, 2008.

Part: SKIN — DENTED (NR 1 SLAT) · airframe 50,486 hrs · 10,479 cycles

DENT IN RT NR 1 LEADING EDGE SLAT, DENT MEASURES 4 INCH LONG BETWEEN RIBS 7 AND 8, 35 INCHES FROM INBD EDGE, 5 1/2 INCHES BELOW PAINTED SURFACE, AND 5/32 INCH DEEP. REMOVED DAMAGE AND REPAIRED DENT ON RT NR 1 LEADING EDGE SLAT BETWEEN RIBS 7 AND 8, 35 INCH FROM INBD EDGE, 5 1/2 INCHES BELOW PAINTED SURFACE IAW A310-300 SRM 57-40-00-FIG 206.

Part: SKIN — DENTED (ZONE 100) · airframe 50,486 hrs · 10,479 cycles

EXTERNAL LT FUSELAGE SKIN HAS 2 DENTS. NR 1 AT FRAME 60 BETWEEN STRINGER 43 AND 44L 4 INCHES ABOVE BOTTOM SKIN LAP MEASURES 6 INCHES LONG BY .800 INCHES WIDE BY .037 INCHES DEEP. NR 2 DENT AT FRAME 61 BETWEEN STRINGER 43 AND 44L 3 INCHES ABOVE SKIN LAP MEASURES 2 INCHES LONG BY .600 INCHES WIDE BY .017 INCHES DEEP. MEASURED ON PAINTED SURFACE. DISTANCE OF DENTS FROM FRAMES OUT OF LIMITS IAW SRM 53-10-12 DIAGRAM 109. REPAIRED DENTS, NR 1 AT FRAME 60 BETWEEN STRINGER 43 AND 44L 4 INCHES ABOVE BOTTOM SKIN LAP, NR 2 DENT AT FRAME 61 BETWEEN STRINGER 43 AND 44L 3 INCHES ABOVE SKIN LAP, IAW SRM 53-10-12 FIG 216.

Part: BRACKET — CRACKED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

CRACKED BRACKET AT FRAME 19, STRG 46 LT. REPLACEMENT OF BRACKET IAW SRM 51-72-10.

Part: DOOR FRAME — DAMAGED (ZONE 200) · airframe 49,597 hrs · 9,932 cycles

TOOLING IMPACTS FOUND ON DOOR FRAME 14 UNDER DOOR STOP 8 LH, PAX DOOR 1. REPAIR PERFORMED BY SMOOTH BLEND OUT, DVI INSPECTING OF FASTENER HOLES AND HFEC INSPECTION OF BLENDED AREAS FOR CRACK FREE CONDITION IAW EA 6-5312-95486 AND RAS 041687/013/2005 ISSUE A.

Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

HEAVY CORROSION UNDER ANTI-CHAFING PLATE ON SKIN PANEL BETWEEN FRAME 92-94, STRG 9-13 LT AND RT, OUT OF LIMIT. REPLACEMENT OF BOTH SKIN-PANELS (FABRICATED BY EFW-DRS) IAW SRM 51-72-10.

Part: PLATE — CRACKED (ZONE 200) · airframe 49,597 hrs · 9,932 cycles

CRACKED SHEAR PLATES BETWEEN FRAME 79-80/82, STRG 26 LT AND RT. REPLACEMENT OF BOTH SHEAR PLATES IAW SRM 51-72-10.

Part: FITTING — CRACKED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

CRACKED ATTACHMENT HOLES IN CORNER PROFILE AT FRAME 25A BETWEEN STRG 28-34 RT. REPLACEMENT OF CORNER PROFILE IAW SRM 51-72-10 AND PTOF DRW, R255B0061.

Part: FITTING — CRACKED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

CRACKED ATTACHMENT HOLES IN CORNER PROFILE AT FRAME 25A BETWEEN STRG. 28-34 RT. REPLACEMENT OF CORNER PROFILE IAW SRM 51-72-10 AND PTOF DRW, R255B0061.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

HEAVY CORROSION ON FLOOR SUPPORT BETWEEN FRAME 14-17, STRINGER 26, Y-1959 RT. REPAIR PERFORMED BY REINFORCING WITH ANGLE IAW SRM 53-12-15/FIG 207.

Part: BRACKET — CRACKED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

CRACKED BRACKET AT FRAME 19, STRG 50 LT. REPLACEMENT OF BRACKET IAW SRM 51-72-10.

Part: ANGLE — MISMANUFACTURED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

LESS EDGE MARGIN (5-6 MM) AT ANGLES STRG 26 RT AT FRAME 69 AND STRG 26 LT FRAME 63 AND 65. IT'S IMPOSSIBLE TO INSTALL DAN5-6X OR DAN5-8 FASTENER DURING PTOF. REPAIR PERFORMED BY INSTALLING REPAIR ANGLES FABRICATED IN EFW-DRS (RE0074-201/RE0074-200) IAW SRM 51-72-10.

Part: FITTING — DAMAGED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

MISDRILLED HOLE IN CORNER FITTING FRAME 54.1 RT DUE TO FAILED INSTALLED ROLLERTRACK ON CARGO FLOOR STRUCTURE. REPLACEMENT OF CORNERFITTING IAW SRM 51-72-10.

Part: SKIN PANEL — CHAFED (ZONE 600) · airframe 49,597 hrs · 9,932 cycles

CHAFING MARKS FOUND AROUND MANHOLE 9 APERTURE ON THE UPPER SURFACE OF THE BOTTOM WING SKIN PANEL NR 2 BETWEEN RIB 14-15, BOTH WINGS. REPAIR PERFORMED BY SMOOTH BLEND OUT, NDT INSPECTION FOR CRACK FREE AND FILLING BLEND LEVEL RESIN IAW EA 6-5720-92205 AND RAS/BAE/1001697/2005 ISSUE A.

Part: ANGLE — FAILED (ZONE 200) · airframe 49,597 hrs · 9,932 cycles

LESS MARGIN AT ONE HOLE AT FRAME 59, STRG 26 LT. NEW SUPPORT CAN'T BE INSTALLED BETWEEN FRAME 59 AND SEAT TRACK AS PER DRW, R539H0112. REPAIR PERFORMED BY INSTALLING REINFORCING PLATE WHICH IS FIXED WITH HI-LOK'S DAN5-5 IAW, SRM 51-72-10 AND EFW DD-0467024 ISSUE AA.

Part: SKIN — DENTED (LT ELEVATOR) · airframe 49,597 hrs · 9,932 cycles

DENT IN BOTTOM SKIN OF LT ELEVATOR TRAILING EDGE (30X30X1,5). REPAIR PERFORMED IAW SRM 55-21-11/CONFIG 1/PARA 5D/FIG 204.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

HEAVY CORROSION FOUND ON THE T-SECTION AT FRAME 92, BETWEEN STRG 19-23 LT (TAILCONE). REPAIR PERFORMED BY CUT OUT THE T-SECTION AND INSTALLING NEW PORTION AND REPAIR ANGLES IAW EA 6-5319-92229 AND RAS/DAHAM/4020157/2005 ISSUE B.

Part: FITTING — DAMAGED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

FOUND MISDRILLED HOLE IN CORNER FITTING ADJACENT AND LESS MARGIN TO ROLLER TRACK HOLE, FRAME 60, CARGO FLOOR STRUCTURE, Y1460 LT. REPAIR PERFORMED BY CREATING AN OBLONG HOLE AND INSTALLING FASTENER WITH STRENGTHENING PLATE IAW 6-5317-95859 AND RAS/DAHAM/4020259/2005 ISSUE A.

Part: STRINGER — DAMAGED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

SEVERAL MISDRILLED HOLES ON STRINGER 33 RT BETWEEN FRAME 69-70. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201 / SEC "C-C".

Part: FRAME — DENTED (ZONE 200) · airframe 49,597 hrs · 9,932 cycles

TOOL IMPACT CAUSES DENT IN FRAME 71, STRG 15 RHS. SPLICE REPAIR PERFORMED IAW SRM 53-10-13 / PG 210, 213 / FIG 203.

Part: BRACKET — CRACKED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

CRACKED BRACKET AT FRAME 19, STRG 49 LT . REPLACEMENT OF BRACKET IAW SRM 51-72-10.

Part: FRAME — DENTED (ZONE 200) · airframe 49,597 hrs · 9,932 cycles

TOOL IMPACT CAUSES DENT IN FRAME 70, STRG 15 RHS. SPLICE REPAIR PERFORMED IAW SRM 53-10-13 / PG 210, 213/FIG 203.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

HEAVY CORROSION ON STRINGER 53 LT BETWEEN FRAME 55/58-59, OUT OF LIMIT. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14 / FIG 201.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

HEAVY CORROSION AT LONGITUDINAL PROFILE IN BULK CARGO COMP BETWEEN FRAME 67-69 RHS OUTBOARD, STRG 44. REPLACEMENT OF LONGITUDINAL IAW SRM 51-72-10.

Part: FLOORBEAM — DAMAGED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

FOUND MISDRILLED HOLES AT CROSSBEAM FRAME 54.1 AND 54.2, Y-805. CROSSBEAM SPLICE REPAIR ON BOTH CROSSBEAMS PERFORMED IAW SRM 53-10-15/FIG 207.

Part: WEB — DAMAGED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

FOUND DAMAGED WEB PLATE BETWEEN FRAME 86-87, STRG 39 RT. REPLACEMENT OF WEB PLATE IAW SRM 51-72-10 AND SRM 53-19-18 / PG 76 / ITEM 10.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

HEAVY CORROSION ON LONGITUDINAL PROFIL IN BULK CARGO COMPARTMENT BETWEEN FRAME 65-66, AD. REPLACEMENT OF LONGITUDINAL IAW SRM 51-72-10.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

HEAVY CORROSION AT SEAT TRACK BETWEEN FRAME 15A-19, STRG 26 RHS, OUT OF LIMIT. REPLACEMENT OF SEAT TRACK IAW SRM 51-72-10.

Part: LONGERON — CORRODED (ZONE 200) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

HEAVY CORROSION AT LONGITUDINAL BEAM BETWEEN FRAME 73A-75, STRG 26 RHS. REPLACEMENT OF LONGITUDINAL BEAM IAW SRM 51-72-10.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 49,597 hrs · 9,932 cycles

FOUND DELAMINATION AT OLD REPAIRS OF LT INBOARD FLAP BETWEEN RIB 4-RIB 5 AND RIB 9-RIB 10. REPAIR DAMAGED AREAS OF INBOARD FLAP BETWEEN RIB 4 AND RIB 5 IAW SRM 57-53-12 FIGURE 208. REPAIR DAMAGED AREAS OF INBOARD FLAP BETWEEN RIB 9 AND RIB 10 IAW SRM 57-53-12 PARAGRAPH 13, FIGURE 209 VERSION 3 EA 6-5752-92202, RAS/DABRE/7005881/2005 ISSUE C.

Part: PLATE — CHAFED (ZONE 200) · airframe 49,597 hrs · 9,932 cycles

DEEP CHAFING MARKS ON LT AND RT ANTI CHAFING PLATE, FRAME 92-93, STRG 9-14. REPLACMENT OF ANTI-CHAFING PLATES LT AND RT IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

HEAVY CORROSION ON STRINGER 52 BETWEEN FRAME 55/58-60 LHS. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14 / FIG 201.

Part: FLOORBEAM — MISREPAIRED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

OLD REPAIR AT CROSSBEAM FRAME 63 BETWEEN Y500 AND Y1160 IN AFT CARGO COMPARTMENT FLOOR STRUCTURE, NOT CONFORM TO SRM 53-10-15 / 207. SPLICE REPAIR RENEWED IAW SRM 53-10-15/FIG 207.

Part: SKIN — DENTED (ZONE 300) · airframe 49,597 hrs · 9,932 cycles

DENT IN RT ELEVATOR BOTTOM SKIN TRAILING EDGE. REPAIR PERFORMED BY FILLING AND LAMINATING IAW SRM 55-21-11/FIG 204.

Part: LONGERON — MISREPAIRED (ZONE 200) · airframe 49,597 hrs · 9,932 cycles

FOUND TWO SPLICE REPAIRS ON EXTRUSION BETWEEN FRAME 15A-17, Y1959 LT, MATERIAL NOT CONFORM TO SRM 53-12-15/FIG 207. SPLICE REPAIRS ON EXTRUSION RENEWED IAW SRM 53-12-15/FIG 207.

Part: TUBE — CRACKED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

DAMAGED (CRACKED) TUBE ASSY BETWEEN FRAME 24-25, STRG 52 RT. REPLACEMENT OF TUBE ASSY IAW SRM 51-72-10.

Part: WEB — DAMAGED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

FOUND DAMAGED WEB PLATES BETWEEN FRAME 86-87, STRG 33 LT AND RT. REPLACEMENT OF WEB PLATES IAW SRM 51-72-10 AND SRM 53-19-18/PG 53.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

CORRODED STRINGER BETWEEN FRAME 67-69, STRG 57 AD, OUT OF LIMIT. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14 / FIG. 201.

Part: WEB — DAMAGED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

FOUND DAMAGED WEB PLATE BETWEEN FRAME 86-87, STRG 36 LT. REPLACEMENT OF WEB PLATE IAW SRM 51-72-10 AND SRM 53-19-18/PG 76/ ITEM 40.

Part: BRACKET — CRACKED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

CRACKED BRACKETS (TWO) BETWEEN CROSSBEAM 32/33 AND 33/34 RHS, STRG 26-27, Y-2462. REPLACEMENT OF BOTH BRACKETS IAW SRM 51-72-10.

Part: BEAM — DAMAGED (ZONE 800) · airframe 49,597 hrs · 9,932 cycles

SCRATCHED AND DENTED BEAM 5 FWD CARGO DOOR BETWEEN FRAME 20B-21. REPLACEMENT OF BEAM IAW SRM 51-72-10.

Part: SKIN PANEL — FAILED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

OLD REPAIR DOUBLER ON FUSELAGE SKIN BULK CARGO DOOR CUTOUT AT FRAME 69, STRG 43-45. DOUBLER MATERIAL NOT CONFORM TO RAS/DAHAM/12953/2000 ISSUE B AND SOGERMA CARD 6007 (B24279). DOUBLER REPLACED IAW RAS/DAHAM/12953/2000 ISSUE B AND SOGERMA DR B24279 NR 6007.

Part: SKIN PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

CORROSION SPOT BELOW STRG 57 ON LONGITUDINAL LAP JOINT AT INNER SKIN SURFACE IS OUT OF LIMIT, FRAME 65-66, STRG 57 AD. BLEND OUT REPAIR APPROVED EA 6-5317-92204 AND RAS/DAHAM/4020031/2005 ISSUE A.

Part: FITTING — CRACKED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

FOUND CRACKED FITTING AT FRAME 66, STRG 50 LHS. REPLACEMENT OF FITTING IAW SRM 51-72-10.

Part: LONGERON — MISREPAIRED (ZONE 200) · airframe 49,597 hrs · 9,932 cycles

FOUND SPLICE REPAIR ON EXTRUSION BETWEEN FRAME 12A-14, Y-953 RT, MATERIAL NOT CONFORM TO SRM 53-12-15/FIG 207. SPLICE REPAIR ON EXTRUSION RENEWED IAW SRM 53-12-15/FIG 207.

Part: SKIN — CORRODED (ZONE 600) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

FOUND SKIN BULGE (CORROSION) ON LEADING EDGE OF RT WING INBOARD FLAP, NEAR TO TRACK 1. REPLACEMENT OF L/E SKIN AT FLAP IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

CORROSION ON STRINGER 53, 54 AND 55 LHS BETWEEN FRAME 70-71. STRINGER SPLICE REPAIRS PERFORMED IAW SRM 53-10-14/FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

CORROSION ON STRINGER 57 BETWEEN FRAME 65-67 AD, OUT OF LIMIT. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: SUPPORT — DAMAGED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

DAMAGED SECTION-SUPPORT AT AFT FIRE WALL, FRAME 101 LOWER AREA. REPAIR PERFORMED BY REPLACEMENT OF SECTION-SUPPORT IAW SRM 51-72-10.

Part: SKIN — DELAMINATED (ELEVATOR) · airframe 49,597 hrs · 9,932 cycles

FOUND DELAMINATION ON UPPER SKIN ON TRAILING EDGE OF RT ELEVATOR BETWEEN RIB 6-8. REPAIR OF CORE AND INSTALLING EXTERNAL REPAIR STRAP, PERFORMED BY EA 6-5521-92209 AND RAS/CASA/4419/2005 ISSUE A.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

CORROSION ON FITTING AT FRAME 63, STR 41-45 LT, OUT OF LIMIT. REPLACEMENT OF FITTING IAW SRM 51-72-10.

Part: STRINGER CLIP — CORRODED (ZONE 100) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

HEAVY CORROSION ON STRINGER CLIP BETWEEN STRINGER 52-53, FRAME 59 LT. REPLACEMENT OF STRINGER CLIP IAW SRM 51-72-10.

Part: PLATE — MISREPAIRED (ZONE 800) · airframe 49,597 hrs · 9,932 cycles

FOUND OLD DOUBLER REPAIR ON LOWER INNER SKIN OF AFT CARGO DOOR, FRAME 62-62A. REPAIR IS NOT PERFORMED IAW. SRM, NOT ALLOWED THAT DOUBLER ENDS AT FRAME. INNER DOUBLER REPAIR RENEWED IAW. TD/KO/S1/01693/2004 ISSUE A AND RAS/DATLS/0001693/2004 ISSUE A.

Part: PLATE — DAMAGED (ZONE 800) · airframe 49,597 hrs · 9,932 cycles

SCRATCHED AND DENTED CORNER PLATE AT BEAM 5 FWD CARGO DOOR AT FRAME 25A. REPLACEMENT OF CORNER PLATE IAW SRM 51-72-10.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 49,597 hrs · 9,932 cycles

HEAVY CORROSION AT SEAT TRACK BETWEEN FRAME 14-19, STRG 26 RHS, OUT OF LIMIT. REPLACEMENT OF SEAT TRACK IAW SRM 51-72-10.

Part: SKIN PANEL — MISREPAIRED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

FOUND OLD REPAIR DOUBLER BETWEEN FRAME 75A-76, STRG 29-30 RT. DOUBLER ENDS ON THE LONGITUDINAL JOINT, NOT ALLOWED IAW SRM 53-10-12/FIG 203. REPAIR PERFORMED BY INSTALLING NEW EXTERNAL DOUBLER IAW EA 6-5318-92197 AND RAS/DAHAM/4019986/2005 ISSUE B.

Part: SKIN PANEL — MISREPAIRED (ZONE 100) · airframe 49,597 hrs · 9,932 cycles

FOUND OLD DOUBLER REPAIR ON FUSELAGE SKIN BETWEEN FRAME 71-72, STRG 26-27 RT CLOSE TO CIRCUMFERENTIAL JOINT FRAME 72. THERE MUST BE A MINIMUM DISTANCE OF THREE FASTENER SPACING BETWEEN THE OUTER ROW OF THE DOUBLER TO THE FIRST FASTENER ROW OF A LONGITUDINAL CIRCUMFERENTIAL JOINT (REF. SRM 53-10-12 / FIG. 201A). REPAIR PERFORMED BY INSTALLING NEW EXTERNAL DOUBLER IAW SRM 53-10-12/FIG 233. APPROVED BY EA 6-5318-92198 AND RAS/DAHAM/4019984/2005 ISSUE B.

Part: SKIN PANEL — WORN (ZONE 500) · airframe 49,590 hrs · 9,930 cycles

ELONGATED HYDRAULIC FITTING HOLES AT PYLON SUPPORT BRACKET AND BOTTOM OF LT WING, RIB 8. REPAIR PERFORMED BY OVERSIZING HOLES AND INSTALLING BUSHES IAW R572-49184 ISSUE C, APPROVED BY EA 6-5720-92194 AND RAS/BAE/1001639/2005 ISSUE A.

Part: SKIN — CHAFED (ZONE 600) · airframe 49,590 hrs · 9,930 cycles

FOUND SEVERAL CHAFING MARKS ON LEADING EDGE D-NOSE SKIN RT BETWEEN TRACK 5 AND 6. REPLACEMENT OF D-NOSE SKIN IAW SRM 51-72-10.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 49,593 hrs · 9,931 cycles

FOUND DELAMINATION AT UPPER SKIN TRAILING EDGE BETWEEN RIB 16-17 OF LT INBOARD FLAP. METAL-SKINNED CORE REPAIR AT T/E PERFORMED AS PER SRM 57-53-12/PARA 13 / FIG 208, APPROVED BY EA 6-5752-92199 AND RAS/DABRE/7005884/2005 ISSUE A.

Part: SKIN — CHAFED (ZONE 600) · airframe 49,590 hrs · 9,930 cycles

FOUND SEVERAL CHAFING MARKS ON LEADING EDGE D-NOSE SKIN RT BETWEEN SLAT TRACK 2 AND JACK 2. REPLACEMENT OF D-NOSE SKIN IAW SRM 51-72-10.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 49,593 hrs · 9,931 cycles

OLD DOUBLER REPAIR ON T/E OF RT INBOARD FLAP, RIB 8-10, NOT CONFORM TO SRM 57-12-52, ONE RIVET ROW IS MISSING. REPAIR PERFORMED AS PER SRM 57-53-12/FIG 208, APPROVED BY EA 6-5752-92201 AND RAS/DABRE/7005882/2005 ISSUE C.

Part: SKIN PANEL — WORN (ZONE 600) · airframe 49,590 hrs · 9,930 cycles

ELONGATED HYDRAULIC FITTING HOLES AT PYLON SUPPORT BRACKET AND BOTTOM OF RT WING, RIB 8. REPAIR PERFORMED BY OVERSIZING AND INSTALLING BUSHES IAW R572-49184 ISSUE C, APPROVED BY EA 6-5720-92194 AND RAS/BAE/1001639/2005 ISSUE A.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 49,590 hrs · 9,930 cycles

FOUND DELAMINATION ON OLD REPAIR AT TRAILING EDGE OF RT INBOARD FLAP, UPPER AND LOWER SIDE BETWEEN RIB 11-13 AND RIB 8-9. REPAIR PERFORMED AS PER SRM 57-53-12 / PARA 13 / FIG 209 AND 208, APPROVED BY EA 6-5752-92201A AND RAS/DABRE/7005882/2005 ISSUE A.

Part: SKIN — CHAFED (ZONE 600) · airframe 49,590 hrs · 9,930 cycles

FOUND THREE CHAFING MARKS ON LEADING EDGE D-NOSE SKIN BETWEEN SLAT TRACK 6 AND JACK 4 RT WING. NOSE SKIN REPAIR PERFORMED IAW SRM 57-41-12/ FIG 204 WITH ALTERNATIVE MATERIAL, APPROVED BY EA 6-5741-92200 AND RAS/BAE/1001636/2005 ISSUE B.