N448FE

Part: STRINGER — DAMAGED (ZONE 100) · airframe 39,640 hrs · 27,891 cycles

1 EA FASTENER HOLE AT FR 54, STRINGER 40 RT HAS DOUBLE DRILL AND DAMAGE IN COUNTERSINK REPAIRED DAMAGE HOLE IAW EA 6-5310-118123.

Part: SKIN — DAMAGED (ZONE 100) · airframe 39,640 hrs · 27,891 cycles

1 FASTENER HOLE AT FR 54, STRINGER 40 RT HAS DOUBLE DRILL AND DAMAGE IN COUNTERSINK REPAIRED DAMAGE HOLE IAW FED EX EA 6-5310-118123.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 39,640 hrs · 27,891 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN SEAT TRACK NR 2 LT Y450 BETWEEN FRAMES 51 TO 52 HAS 2 EA REPAIR SPLICES MEASURING 7 IN LONG BY 3 IN TALL AND 1 REPAIR SECTION 51.9 IN LONG FROM FR 54 TO BETWEEN FRAMES 51 AND 52 REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT SEAT TRACK REPAIR IAW A310 SRM 53-10-16, PAR 7 PAGES 227 - 232, FIG 20. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SEAT TRACK — MISREPAIRED (FUSELAGE) · airframe 39,640 hrs · 27,891 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN SEAT TRACK NR 4 RT - Y1456 BETWEEN FRAMES 62 TO 63, HAS 2. REPAIR ANGLES MEASURING 9.5" LONG BY 1.9" TALL AND 1. REPAIR PIECE 4 INCHES LONG. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED REPAIR AND INSTALLED CORRECT SEAT TRACK REPAIR IAW A310-200 SRM 53-10-16 FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — MISREPAIRED (FUSELAGE) · airframe 39,640 hrs · 27,891 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 55 RT BETWEEN FRAMES 65 TO 69 HAS 1 REPAIR SECTION MEASURING 80" LONG AND 1 REPAIR SPLICE MEASURING 8.2 INCHES LONG, REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER REPAIR SPLICE IAW A310-200 SRM 53-10-14 FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SEAL — MISSING (FLAP DOUBLER) · airframe 39,640 hrs · 27,891 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT WING OUTBOARD FLAP LOWER MAIN SKIN BETWEEN RIBS 4 AND 5 MEASURES 10.6 INCHES BY 9 INCHES. REPAIR NOT IAW SRM REQUIREMENTS DUE TO REPAIR MISSING FILLET SEAL AND PAINT. REPAIRED PROTECTIVE COATING AND RE-SEALED EDGES IAW A310-200 SRM 57-53-12 FIG 210. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — MISREPAIRED (FUSELAGE) · airframe 39,640 hrs · 27,891 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 54 RT BETWEEN FRAMES 65 TO 67 HAS 1 REPAIR SECTION MEASURING 40" LONG AND 1 REPAIR SPLICE MEASURING 8 INCHES LONG. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED 1 CORRECT REPAIR SPLICE IAW A310-200 SRM 53-10-14 FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: PAINT — MISSING (FLAP DOUBLER) · airframe 39,640 hrs · 27,891 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT WING OUTBOARD FLAP LOWER MAIN SKIN BETWEEN RIBS 3 AND 4 MEASURES 10.4" BY 9.9". REPAIR NOT IAW SRM REQUIREMENTS DUE TO REPAIR DOUBLER MISSING FILLET SEAL AND PAINT. REPAIRED PROTECTIVE COATING AND RESEALED EDGES IAW A310-200 SRM 57-53-12 FIG 210. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — MISREPAIRED (FUSELAGE) · airframe 39,640 hrs · 27,891 cycles

PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 56 RT BETWEEN FRAMES 67 TO 69, HAS REPAIR SECTION MEASURING 16" LONG AND 2 REPAIR SPLICES, THE FORWARD SPLICE IS 7.9 INCHES LONG AND THE AFT SPLICE IS 8.4 INCHES LONG. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER SPLICE REPAIR IAW A310-200 SRM 53-10-14 FIG 201. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 39,640 hrs · 27,891 cycles

MDCC NR 3 LT SEAT TRACK BETWEEN FRAMES 54.3 TO 54.2 HAS 2 AREAS OF DAMAGED SCALLOPS REMOVED AND REPLACED DAMAGED SEAT TRACK IN MDCC NR 3 LT AT FRAMES 54.2 TO 58 IAW A310-200 SRM 53-10-16 AND SRM 51-72-10.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 39,640 hrs · 27,891 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED AT LEFT SIDE UPPER FWD FUSELAGE SKIN BETWEEN FRAMES 0 TO 1 AND JUST FORWARD OF THE CAPTAINS WINDSHIELD MEASURES 9.5 INCHES BY 11.6 INCHES WITH A SKIN CUTOUT MEASURING 6.7 INCH BY 5.6 INCH REPAIR NOT IAW SRM REQUIREMENTS DUE TO LEVEL 1 SURFACE CORROSION FOUND ON REPAIR. REMOVED LEVEL 1 CORROSION BY HAND WITH NEGLIGIBLE MATERIAL LOSS AND RESTORED PROTECTIVE COATING IAW A310-200 SRM 53-12-12 FIG 201 SHEET 1, SRM 51-74-10, AND SRM 51-72-10. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SEAT TRACK — MISREPAIRED (CABIN) · airframe 39,640 hrs · 27,891 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN SEAT TRACK NR 3 LT Y953 BETWEEN FRAMES 61 TO 62 HAS 2. REPAIR SPLICES MEASURING 7.1" LONG BY 3" TALL AND 1. REPAIR SECTION 73" LONG FROM FRAME 55/58 TO BETWEEN FRAMES 61 AND 62 ALSO THE INBOARD AND OUTBOARD PRODUCTION SPLICES BETWEEN FRAMES 55/58 TO 59 ARE PREVIOUSLY MISLOCATED BY A .200" GAP BETWEEN SPLICES AND THE TOP FLANGES OF THE SEAT TRACK. REPAIR NOT IAW WITH SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT SEAT TRACK REPAIR SECTION IAW A310-200 SRM 53-10-16 FIG 208 SHEET 1. THIS IS AN AIRBUS REPAIR WITH NO ASSIGNED PART NUMBER AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: BLEED VALVE — CRACKED (NR 1 ENGINE) · airframe 39,477 hrs · 27,798 cycles

DURING CLIMB TO CRUISE ALTITUDE, ECAM PRESENTED AN ADVISORY PAGE FOR NR 1 ENG NAC TEMP AT 200. SELECTED NR 1 BLEED VALVE OFF AND REDUCED POWER ON NR 1 WITH NO CHANGE IN NR 1 NAC TEMP. AFTER THROTTLE WAS REDUCED TO ALMOST IDLE SETTING, NR 1 NAC TEMP FELL TO 190 DEGREES. THROTTLE REMAINED AT IDLE UNTIL SHORT FINAL APPROACH. DURING DESCENT WITH NR 1 AT IDLE, ADVISORY INDICATION WENT AWAY AFTER 10-15 MINUTES. FOUND A SMALL CRACK ON FAN AIR VALVE, FOUND A COUPLE OF SENSE LINES TO BE BAD. REMOVED AND REPLACED FAN AIR VALVE, REMOVED AND REPLACED SENSE LINES AND NACELLE TEMP SENSOR.

Part: VALVE — CRACKED (FAN AIR) · airframe 39,477 hrs · 27,798 cycles

DURING CLIMB TO CRUISE ALTITUDE, ECAM PRESENTED AN ADVISORY PAGE FOR NR 1 ENG NAC TEMP AT 200. SELECTED NR 1 BLEED VALVE OFF AND REDUCED POWER ON NR 1 WITH NO CHANGE IN NR 1 NAC TEMP. AFTER THROTTLE WAS REDUCED TO ALMOST IDLE SETTING, NR 1 NAC TEMP FELL TO 190 DEGREES. THROTTLE REMAINED AT IDLE UNTIL SHORT FINAL APPROACH. DURING DESCENT WITH NR 1 AT IDLE, ADVISORY INDICATION WENT AWAY AFTER 10-15 MINUTES OPEN ENGINE AND INSPECTED DUCTS, VALVES, CLAMPS ETC. FOUND A SMALL CRACK ON FAN AIR VALVE, FOUND A COUPLE OF SENSE LINES TO BE BAD. REMOVED AND REPLACED FAN AIR VALVE, REMOVED AND REPLACED SENSE LINES AND NACELLE TEMP SENSOR. OPS CHECK NORMAL A/C OK FOR SERVICE.

Part: ANTI-ICE VALVE — MALFUNCTIONED (NR 1 ENGINE) · airframe 39,476 hrs · 27,797 cycles

AFTER TAKEOFF RECEIVED NR 1 ENGINE ADVISORY NAC TEMP AT 200 DEGREES, AT CRUISE NR 1 ENG BLEED OFF, NO CHANGE. TEMP LOWERED TO 180 DEGREES IN CRUISE WHEN THROTTLES WERE REDUCED. REMAINED AT 180 DEGREES FOR THE DURATION OF THE FLIGHT. ALL OTHER ENGINE INDICATIONS WERE NORMAL. REPAIRED PRESSURE SENSOR TUBE PER MM 20-23-11-0. REMOVED AND REPLACED NACELLE ANTI ICE VALVE PER MM 30-21-11-4. OPS CHK NORMAL.

Part: SMOKE DETECTOR — MALFUNCTIONED (E/E BAY) · airframe 36,971 hrs · 26,321 cycles

JUST AFTER T/O HAD AVIONICS SMOKE WARNING ON ECAM AND OVERHEAD. NO ODOR OR SIGN OF SMOKE. DECLARED EMERGENCY. RETURNED TO KABQ LANDING WT APPROX 209,000 NR, BELOW MAX LANDING WEIGHT. CHECKED AVIONICS COMPT FOR EVIDENCE OF SMOKE. DUE TO NO EVIDENCE OF SMOKE IN COCKPIT OR AVIONICS COMPT SUSPECT INTERMITTENT DETECTOR 11WA. REPLACED 11WA , NOT TESTING AND 12WA PRECAUTIONARY.

Part: SKIN — CORRODED (FS 37-38) · airframe 36,925 hrs · 26,296 cycles

ACCOMPLISH MAINTENANCE "C" CHECK NR 004, FWD CARGO COMPARTMENT, FUSELAGE SKIN SURFACE PANEL FOUND WITH CORROSION AT INTERNAL PART OF COMPARTMENT BETWEEN FS 37 AND FS 38 BETWEEN STR 53 LT AND STR 53 RT. REPAIRED ACCOMPLISH PER FEDEX EA 6-5330-93193 (FOR DETAILS SEE JOB PROGRESS FORM). REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: ARM — CORRODED (PAX DOOR) · airframe 36,925 hrs · 26,296 cycles

RT FWD DOOR, LOWER ARM ASSY FOUND CORRODED. REPLACED BY A NEW ONE IAW AMM 52-11-21-4. FUNCTIONAL CHECK IAW AMM 52-10-11-501.

Part: SKIN — CORRODED (CENTER WING) · airframe 36,925 hrs · 26,296 cycles

CORROSION AT CENTRAL WING UPPER SKIN SURFACE FR 46 Y- 2126. REMOVED/INSTALLED ELEMENTS PER SRM 51-40-21 & 51-40-44. REMOVED CORROSION PER SRM 51-74-10 & 51-29-00 PG. 201. PERFORMED EDDY CURRENTS FOUND "OK". PAINTED PER SRM 51-75-10-08.

Part: ACTUATOR — MALFUNCTIONED (RUDDER) · airframe 36,305 hrs · 25,924 cycles

AFTER TAKEOFF AND FLAPS RETRACTED, BOTH NR 1 & 2 RUDDER FAULT. WOULD NOT RESET, EXTENDED THE FLAPS & THE RUDDER FAULT WENT AWAY. REMOVED AND REPLACED RUDDER VARIABLE STOP ACTUATOR PER A310-200 MM 27-23-23-4. TEST GOOD ON SYS 1 & 2 PER MM 27-23-00-5. PREMATURE REMOVAL/INSTALLATION, OFF MFG 8168-1.

Part: ACCESS PANEL — DAMAGED (ZONE 500) · airframe 34,636 hrs · 24,838 cycles

LT WING, LOWER ACCESS CUTOUT FOR PANEL 550GB. TWO SCREW HOLES FOR PANEL HAVE DAMAGED EDGES. REMOVED ANCHOR NUTS TO ACCESS DAMAGED HOLES. REMOVED DAMAGED AREA AND REAMED HOLES TO 0.495 AND 0.467. ENSURED CLEANED HOLES ARE CRACK FREE BY HFEC IAW NTM 51-10-01. FABRICATED 2 BUSHINGS FROM 2024T3 AND FREEZE INSTALLED. REAMED BOTH HOLES TO FINAL DIA. OF 0.312 AND PROTECTED AFFECTED AREA IAW SRM A310 SRM 51-23-00. REINSTALLED ANCHOR NUTS. ALL WORK COMPLETED IAW RAS 0288/2003 AND EA 6-5710-68295 DATED 02-13-2003.

Part: CONTROLLER (ZONE 300) · airframe 34,007 hrs · 24,493 cycles

CLIMBING OUT OF SEA, ECAM ALERT - "EXCESS CAB ALT". DONNED O2 MASKS AND TRIED TO TROUBLESHOOT PROBLEM. SWAPPED REGULATORS FOR PRESS. TRIED MANUALLY PRESS AIRPLANE. NO SUCCESS. RETURNED TO SEA FOR LANDING. UPON BLOCK-IN, COULD NOT TEST EITHER SYS 1 OR 2. FOUND #1 SYS BITE UNIT ROTARY SWITCH OUT OF "NORM FLT" POSITION. RESET TO NORMAL POSITION AND #1 UNIT TESTS OK PER A310 MM 21-31-00-5-01. OK FOR SERVICE.

Part: COALESCER BAG — CONTAMINATED (A/C BAY) · airframe 33,574 hrs · 22,424 cycles

ON FINAL ECAM WARN AVIONICS SMOKE AND M/DECK M/CARGO MID SMOKE DETECT. REMOVED AND REPLACED LT & RT COALESCER BAGS PER MM 21-51-16-3. OK FOR SERVICE.

Part: INDICATOR — FAULTY (COCKPIT) · airframe 33,542 hrs · 24,216 cycles

AFTER T/O OIL QTY ON NR 1 ENG SHOW 2 QT ON BOTH ANALOG AND ECAM IND. REINSTALLED C/P AND HEAT SHIELD. REMOVED AND REPLACED OIL QTY IND. TEST NORMAL PER 79-31-00-5-A.

Part: SMOKE WARNING — SMOKE

1-396 RECEIVED MAIN DECK CARGO SMOKE WARNING. BITE CHECK PER MM 26-19-00-5. NO FAULT FOUND. OK FOR SERVICE.

Part: ELEVATOR — MALFUNCTIONED (STAB) · airframe 32,432 hrs · 23,420 cycles

AFT 20 MIN OF FLT A/C HAD A AIR TURNBACK DUE TO TOO MUCH PRESS NEEDED TO OPERATE ELEVATOR. AC RETURN TO LAX.

Part: PITOT SYSTEM — DIRTY (RIGHT)

99-143 - NO AIRSPEED IND ON F/O SIDE PFD ON T/O. RTO AT 70 KNOTS. PERF ADC NR 2 OPS CK IAW MM 34-10-00 SYS CK GOOD. FLUSHED NR 2 PITOT SYS IAW 34-10-00, FOUND DEBRIS IN F/O PITOT TUBE, SYS OK FOR SERVICE.

Part: ADC — INOPERATIVE (E & E COMPT)

NO AIRSPEED IND ON TAKEOFF ROLL. ALL PFD SYMBOLS WERE PRESENT BUT CAPT AIRSPEED TRIANGLE NEVER INCREASED FROM 0. REMOVED AND REPLACED NR 1 ADC IAW M/M 34-11-34, SYSTEM OK FOR SERVICE.

Part: AIRSPEED IND — INOPERATIVE (LT COCKPIT)

CAPT HAD NO AIRSPEED INDICATION ON PFD DURING T/O. ABORTED AT 70 KNOTS. F/O AND STBY AIRSPEED INDICATE NORMAL.

Part: CONTROL HANDLE — FAILED (LANDING GEAR)

98-0188 STA-IND - AFTER T/O LANDING GEAR WOULD NOT RETRACT UNLOCK AND GREEN DIAMONDS ON ALL 6 INDICATORS. BOTH SYS 1 AND SYS 2 ON POSITION DETECTOR SWITCH TRIED MULTIPLE TIMES. REMOVED AND REPLACED LAND GEAR CONTROL HANDLE MODULE PER M/M 32-30. PERFORMED GEAR SWING 8 CYCLES, 4 ON SYS 1 AND 4 ON SYS 2. OPS CHECK GOOD RII REQUIRED RII NR 0859 16.

Part: PITOT LINE — CLOGGED (NR 1)

ON DEPARTURE CAPTS AIRSPEED TAPE WAS SHOWING ERRONEOUS SPD IND. SWIT TO ALT SPD TAPE RETURNED TO OPERATION BUT SPD WAS 300 KTS WHEN F/O WAS 160 KTS. SWITCHED TO ALT EFIS NO CHANGE. AFTER FLAP/SLAT RETRACT NR 1 YAW DAMPER FAILED AUTO THROTTLE SYS FAILED WOULD NOT RESET. NR 1 AND NR 2 EPR FAIL TO INDICATE AND WE HAD NO WAY OF SETTING CLIMB PWR. FOUND NR 1 PITOT LINE CLOGGED. FLUSHED OUT BOTH 1 AND 2 PER M/M 34-10-00. REMOVED AND REPLACED NR 1 ADC PER M/M 34-11-34. PERFORMED PITOT/STATIC CK ON NR 1 AND NR 2 CKS GOOD. FLUSHED BOTH ENGS NR 1 AND NR 2 PT2 LINES. RAN ENG'S EPRS OPS CK GOOD. PERFORMED AFS/LAND TESTS OK.

Part: FUEL CONTROL — OUT OF ADJUST (NR 1 ENGINE)

ON TAXI IN AT IDLE POWER, NR 1 ENG FLAMED OUT WITH CORRESPONDING ENG FAIL ECAM WARNINGS. FOR INFORMATION, 25-30 KT TAILWIND WAS PRESENT WHEN ENG FAILED. ENGINE RUN PERFORMED AND GROUND IDLE SPEED FOUND TO BE LOW. TEST NR 9 FUEL CONTROL TRIM PERFORMED IAW M/M 71-00-00, GROUND (MIN) IDLE ADJUSTMENT SCREW ADJUSTED TO INCREASE 8 CLICKS CLOCKWISE.

Part: TR COWL — DAMAGED (NR 2 ENGINE)

UPON ARRIVAL, DURING WALKAROUND FOUND APPROX 18 DIA HOLE ON AFT INBD EDGE OF NR 2 ENGINE FAN COWL. ALSO, NOTED SEVERE DISCOLORATION ON INBD REVERSER HALF WITH BURN STREAKS AND STRUCTURAL DAMAGE TO THE REVERSER. *S/D* REMOVED AND REPLACED GROUND THRUST REV CHECK VALVE AND LEAK CHECKED. REMOVED AND REPLACED INBD THRUST REV COWL AND INBD FAN COWL M/M PER 71-13-03. RIG CHECKED THRUST REV PER M/M 78-32-03. PERFORMED COWL LOAD SHARE ADJ/TEST PER M/M 71-13-03.