N821SC

Part: GPS — MALFUNCTIONED (NR 1) · airframe 55,500 hrs · 22,812 cycles

NR 1 GPS MESSAGE "HEADING REQUIRED" RENDERING, GPS AND NR 1 AUTOPILOT INOPERATIVE. VECTORED SO ACFT STAYED ON HEADING MODE. AUTOPILOT NR 2 SELECTED BUT DID NOT ENGAGE. NOT SUCCESSFUL AFTER SEVERAL ATTEMPTS. RETURN TO AIRPORT. LANDED NORMAL. MX CHECKED WIRING FROM NR 2 NPU TO SWITCH BOX 81VU21, FOUND NORMAL. RESET NR 2 NPU, ACCOMPLISHED CHECK OF F/O HSI, OP'S CHECKED GOOD IAW 34-53-01. NR 2 GPS SENSOR READ OUT FOUND NORMAL IAW 34-53-01. ACFT RETURNED TO SERVICE.

Part: PITOT LINE — CLOGGED · airframe 55,381 hrs · 22,762 cycles

ON TAKEOFF ROLL, DEPARTING FROM SJU, CREW NOTICED THAT THERE WAS NO AIRSPEED INDICATION FROM F/O INDICATOR. CAPTAIN INDICATOR SHOWING BETWEEN 75-80 KTS AND FLUCTUATING. ABORTED T/O PROCEDURES FOLLOWED. RETURNED TO GATE. MAINT FOUND PITOT LINES CLOGGED WITH VOLCANIC ASH. LINES BACK FLUSHED IAW 34-11-10/302 ALL LINES RECONNECTED WITH LOW RANGE LEAK TEST ACCOMPLISHED IAW 34-11-10/501-515 SYSTEM TEST NORMAL, NO LEAKS IN SYSTEM. AIRCRAFT RETURNED TO SERVICE.

Part: PIN — DISCONNECTED (CABIN) · airframe 52,873 hrs · 21,986 cycles

DURING DAILY CHECK, MAINTENANCE FOUND R1 EMERGENCY EXIT LIGHTS INOP. FOUND PIN NR 3 DISCONNECTED FROM LIGHT ASSY, RECONNECTED, OPS CHECKED GOOD. AIRCRAFT RELEASED FOR SERVICE.

Part: GIRT BAR — CORRODED (L1 DOOR) · airframe 52,128 hrs · 21,674 cycles

DURING REPLACEMENT OF SLIDE, FOUND L1 DOOR SLIDE GIRT BAR ASSEMBLY CORRODED BEYOND LIMITS. REPLACED GIRT BAR ASSEMBLY IAW MM 25-61-15 PG 401.

Part: TIRE — SEPARATED (MLG) · airframe 52,121 hrs · 21,670 cycles

NR 6 TIRE RUBBER SEPARATION ON TAKEOFF FROM SJU, FLIGHT CONTINUED TO MIA AND MADE A SAFE LANDING. ON INSPECTION OF AIRCRAFT, FOUND LEFT INBOARD FOREFLAP, AFT FLAP AND CENTER HINGE FAIRINGS DAMAGED. REPLACED TIRE AND WHEEL ASSY, FLAP ASSY AND FLAP TAB ASSY. AIRCRAFT RELEASED TO SERVICE.

Part: WARNING MESSAGE — FALSE ACTIVATION · airframe 82,695 hrs · 21,912 cycles

DURING TAKEOFF, RECEIVED A CONFIGURATION DEVIATION WARNING, TAKEOFF ABORTED. UNABLE TO DUPLICATE CONFIGURATION DEVIATION WARNING. PREPARED A/C FOR TEST FLIGHT, TEST FLIGHT COMPLETED SATISFACTORY 11-26-07. AIRCRAFT RELEASED FOR SERVICE.

Part: CADC — DIRTY · airframe 51,659 hrs · 21,439 cycles

AT START OF TAKEOFF, F/O AIR SPEED INDICATION RAPIDLY WENT TO 90 KNOTS, CAPT MOVED NORMALLY. TAKEOFF WAS ABORTED, RETURNED TO GATE. CLEANED AND RE-RACKED NR 2 CADC. OPS CHECKED OK IAW AMM 34-12-34, AIRCRAFT RETURNED TO SERVICE.

Part: SLIDE — WILL NOT ARM (R1 DOOR) · airframe 51,156 hrs · 21,087 cycles

R1 EVACUATION SLIDE ARMING LEVER DOES NOT ENGAGE EVACUATION SLIDE. LEVER IS STUCK IN DISENGAGED POSITION. PLACED ON MEL 52-61-01-2 CAT-C. LUBRICATED R1 EVACUATION SLICE ARMING LEVER MECHANISM. OPS CHECKED OK IAW A300 AMM 52-22-22. CLEARED MEL AND RELEASED AIRCRAFT FOR SERVICE.

Part: CLAMP — BROKEN (NR 2 ENGINE) · airframe 51,153 hrs · 21,086 cycles

AFTER TAKEOFF NR 2 ENGINE FIRE LIGHT AND BELL CAME ON, REDUCED POWER, LIGHT WENT OUT. RETURNED TO FIELD AND MADE A SAFE LANDING. REPLACED BROKEN CLAMP ON 14TH STAGE BLEED MANIFOLD IAW 36-00-00 PAGE 425, LEAK CHECKED OK IAW AMM 71-00-00 PAGE 501. OPS CHECK, AIRCRAFT RELEASED TO SERVICE.

Part: RIB — DAMAGED (L/E SLAT) · airframe 50,653 hrs · 20,839 cycles

DURING INSPECTION, DAMAGE WAS FOUND ON RT WING NR 3 SLAT INBOARD END AT RIB 3 LEADING EDGE. REPAIRED PER AVBORNE REPAIR REFERENCE 25599-8-01-06, (AIRBUS TECHNICAL DISPOSITION #FOK/036/2006) CUT OUT DAMAGED AREA, MODIFIED NOSE RIB 3, MANUFACTURED AND INSTALLED REPAIR PARTS (SKIN INSERT, BUTT PLATES, NOSE RIB REPAIR ANGLE AND SHIM) AND INSTALLED MODIFIED NOSE RIB. APPLIED TOP COAT AND RESTORED ORIGINAL PAINT SCHEME.

Part: DOUBLER — DEBONDED (T/E FLAP) · airframe 50,653 hrs · 20,839 cycles

DURING INSPECTION, TWO DIS-BONDED DOUBLERS WERE FOUND ON LEFT WING OUTBOARD FLAP SKIN UPPER SURFACE ON RIB 4 AND 15 TRAILING EDGE AREA. AFTER DOUBLERS WERE REMOVED, CORROSION WAS FOUND. REPAIRED PER AVBORNE REPAIR REFERENCE 25599-9-01-24-06 (AIRBUS TECHNICAL DISPOSITION NR FOK/027/2006) CUT OUT DAMAGE AND INSTALLED REPAIR SHIM AND DOUBLER, APPLIED TOP COAT AND RESTORE ORIGINAL PAINT SCHEME.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 50,653 hrs · 20,839 cycles

DURING INSPECTION, CORROSION WAS FOUND ON THE FORWARD SIDE OF THE FORWARD PRESSURE BULKHEAD AT -Z180 AND +Y1000. REPAIR WAS ACCOMPLISHED PER AVBORNE REPAIR REF: 25599-10-01-25-06, (AIRBUS TECHNICAL DISPOSITION 942.042586/004/2006) SMOOTH REWORK OF CORRODED AREA, VERIFY CORROSION REMOVAL PER NTM 51-30-11, PERFORMED HFEC PER NTM 51-31-05 TO ENSURE HOLE AND SKIN ARE DAMAGE FREE. MANUFACTURED AND INSTALLED SHIM AND DOUBLER PER PAGE 4 - 5 OF REPAIR REFERENCE 25599-10-01-15-06.

Part: SKIN — CORRODED (FUSELAGE) · airframe 50,653 hrs · 20,839 cycles

DURING INSPECTION, FOUND 3 AREAS OF CORROSION ON FUSELAGE SKIN BETWEEN S26R AND S27R FRAME 58 - 60. REPAIRED PER AVBORNE REPAIR REF 25599-3-01-18-06, (AIRBUS REPAIR DESIGN APPROVAL SHEET RAS/DAHM/40204/2006) REMOVE FASTENERS, SMOOTH BLEND CORROSION, HFEC AND ROTO-TEST TO CONFIRM AREA IS DAMAGE FREE, FLAP PEEN PER SRM 51-40-19 REINSTALL FASTENERS AND RESTORE SURFACE PROTECTION PER SRM 51-40-12.

Part: SKIN — CORRODED (RT WING) · airframe 50,653 hrs · 20,839 cycles

DURING INSPECTION, CORROSION WAS FOUND AT RIGHT HAND WING SKIN UPPER SURFACE PANEL NR 2 AT THREE FASTENER LOCATION JUST INBOARD OF RIB NR 5, APPROXIMATELY 17 INCHES AFT OF REAR SPAR. REPAIRED PER AVBORNE REPAIR REFERENCE 25599-6-10-18-06. REMOVED FASTENERS AND BLENDED OUT CORROSION, VERIFIED NO FURTHER DEFECTS BY HFEC, RE-CUT COUNTER SINKS OF REMOVED FASTENERS, FLAP PEENED AREA PER SRM 51-40-19 REINSTALLED FASTENERS AND RESTORED FINISH PER SRM 52-40-10.

Part: SKIN — CORRODED (FUSELAGE) · airframe 50,653 hrs · 20,839 cycles

DURING INSPECTION, CORROSION WAS FOUND ON FUSELAGE SKIN ABOVE THE RT FORWARD PASSENGER DOOR, TWO AREAS, AT S9L BETWEEN FR 14C AND FR 14B AND 1 AREA AT S11L BETWEEN FR13 AND FR13A. ACCOMPLISHED REPAIR PER AVBORNE REPAIR REFERENCE 25599-7-02-02-2006, (AIRBUS REPAIR DESIGN APPROVAL SHEET RAS/AS/028/2006) PERFORMED SMOOTH REWORK OF CORRODED AREAS, PERFORMED INSPECTIONS, ROTOTEST AND DVI OF HOLES IN CORRODED AREAS, HFEC AND DVI OF CORRODED AREAS, INSTALLED OVERSIZE FASTENERS IN CORRODED AREAS AND RE-PROTECT PER SRM.

Part: WIRE HARNESS — SPARKS (CABIN) · airframe 50,388 hrs · 20,672 cycles

FLIGHT ENGINEER SEAT HAD SPARKS COMING OUT OF ELECT CONNECTOR ON RIGHT SIDE OF SEAT, THEN C/B POPPED. FOUND WIRES FUSED TOGETHER AT SEAT CANNON PLUG. SEAT DEACTIVATED AND PLACED ON MEL 25-11-01.

Part: COMPRESSOR — STALLED (NR 1 ENGINE) · airframe 50,175 hrs · 20,532 cycles

NR 1 ENGINE COMPRESSOR STALLED 4 TIMES CLIMBING THROUGH 15,500 FT. AFTER COMPRESSOR STALL, WITH SAME THROTTLE ANGLE, NR 1 ENG N1 WAS 98.4 PERCENT WHILE NR 2 WAS 104 PERCENT. ALL OTHER PRIMARY ENGINE PARAMETERS WERE FLUCTUATING. WHEN THE NR 1 THRUST LEVER WAS RETARDED TO FLT IDLE THE COMPRESSOR STALL CEASED AND NORMAL FLIGHT IDLE PARAMETERS WERE NOTED. AIRCRAFT LANDED WITHOUT INCIDENT.

Part: VALVE — UNSERVICEABLE (MLG) · airframe 50,136 hrs · 20,500 cycles

UNABLE TO LOWER GEAR, LANDING GEAR EXT C/B POPPED, PERFORMED ALTERNATE GEAR EXTENSION. LANDING NORMAL. REMOVED AND REPLACED LANDING GEAR ELECTRO VALVE IAW 32-31-12. OP'S CHECK AND LEAK CHECK SATISFACTORY IAW 32-30-00. AIRCRAFT RETURNED TO SERVICE.

Part: SOLENOID VALVE — LEAKING (NR 1 ENGINE) · airframe 50,119 hrs · 20,488 cycles

WHILE IN FLT, CLIMB, LOSS OF GREEN HYDRAULIC SYSTEM FLUID. AIRCRAFT RETURNED TO AIRFIELD, LANDING NORMAL. FOUND GREEN SYSTEM EDP SOLENOID VALVE LEAKING. REMOVED AND REPLACED EDP SOLENOID, OP'S CHECK SATISFACTORY IAW 29-11-32. AIRCRAFT LANDED OVERWEIGHT. INSPECTION PERFORMED PER 5-51-11, ALL SATISFACTORY. AIRCRAFT RETURNED TO SERVICE.

Part: DAMPENER — LEAKING (MLG)

AIRCRAFT TOOK OFF, MLG WOULD NOT RETRACT. RETURNED TO BASE. LANDING NORMAL. FOUND LT PITCH DAMPNER LEAKING FLUID. REMOVED AND REPLACED PITCH DAMPNER IAW 32-11-05. FUNCTIONAL CHECK SATISFACTORY, AIRCRAFT RETURNED TO SERVICE.

Part: WARNING LIGHT — ILLUMINATED (MLG) · airframe 48,135 hrs · 19,820 cycles

AFTER TAKE OFF, GEAR HANDLE UP, LT GEAR DOOR AMBER AND LT GEAR UNLOCK RED LIGHT STAYED ON, ON BOTH FWD AND F/E'S PANEL. AIRPLANE START TO VIBRATE ABOVE 230 KTS. FUEL JETTISON PROCEDURE WAS ACCOMPLISHED TO MAX. LANDING WEIGHT. AIRCRAFT LANDED NORMAL.

Part: LANDING LIGHT — FAILED · airframe 46,707 hrs · 18,654 cycles

RT LANDING LIGHT INOP, POPS CONTROL CIRCUIT BREAKER R&R LANDING LIGHT ASSY IAW 33-42-11. OPS CK SATISFACTORY

Part: DOOR · airframe 46,635 hrs · 18,610 cycles

After Departure bulk cargo door illuminated in flight. A/C returned to field, landing normal, no fuel was dumped.Corrective Action: Cycled aft bulk door I/A/W MM 52-34-00. Door indication op's checked normal. Door was verified to be closed and locked. Aircraft returned to service.

Part: FUEL CONTROL — OUT OF ADJUST (NR 2 ENGINE)

DURING CLIMB NR 2 ENGINE BLEED VALVE REG FAULT LIGHT CAME ON. TEMP INCREASE TO 230 DEGREES AND TEMP HI LIGHT CAME ON FOLLOWED BY A/C PACK FAULT LIGHT. UNABLE TO CONTROL PRESSURIZATION DUE TO NR 1 BLEED VALVE CURRENTLY ON MEL (LOCKED OUT) NR 2 HP BLEED FAULT LIGHT CAME ON. AIRCRAFT RETURNED TO AIRPORT. FUEL DUMP PROCEDURES USED FOR LANDING WEIGHT AND AIRCRAFT RETURNED WITH NORMAL LANDING. CLEARED BY ADJUSTING SPECIFIC GRAVITY PER 73-21-02. RUN UP CHECKS COMPLIED WITH, AIRCRAFT RETURNED TO SERVICE.

Part: SENSOR — FAILED (SENSOR)

AFTER DEPARTING BQN, SLATS WOULD NOT RETRACT, STALL WARNING AND STICK SHAKER ACTIVATED AT 175 KNOTS. DUMPED APPROXIMATELY 38,000 LBS OF FUEL AND RETURNED TO BQN. AIRCRAFT LANDED NORMAL. CHECKED AND FOUND CODE 71 AND NR 1 PITCH TRIM AND NR 1 AOA SENSOR FAILED. REMOVED AND REPLACED NR 1 AOA SENSOR IAW MM 27-36-15. OPS CHECK GOOD. AIRCRAFT RETURNED TO SERVICE. (M)