N830FT

Part: TIRES — FAILED (LT MLG)

DURING TAKEOFF ROLL, AIRCRAFT SWUNG VIOLENTLY TO THE LEFT, CAUSING LEFT WING AND BODY GEAR TRUCKS TO DEPART LEFT SIDE OF RUNWAY. ABORTED TAKEOFF. INCIDENT CAUSED DAMAGE TO LT WING GEAR BRAKE EQUALIZATION RODS, BRAKE SYSTEM HYDRAULIC LINES, 2 DEFLATED TIRES. COMPONENTS TO BE REPLACED IAW MM 32. AIRCRAFT INSPECTED PER MM 05-51-37 AND MM 05-51-05; NO ADDITIONAL DISCREPANCIES FOUND. BASED ON PILOT REPORT, BELIEVE CAUSE TO BE FLAT TIRES ON LEFT WING GEAR DUE TO A LONG TAXI.

Part: TRANSMITTER MNT — OUT OF RIG (LT TE FLAPS)

DURING CLIMBOUT, OUTBOARD FLAPS WOULD NOT RETRACT HYDRAULICALLY PAST APPROX 7 DEGREES. FOUND LEFT OUTBOARD TRANSMITTER MOUNT ASSY OUT OF RIG. RE-RIGGED AND REPLACED TRANSMITTER ASSY PER BOEING MAINTENANCE MANUAL 27-58-01, OPERATIONAL CHECK OK. REPLACED FLAP INDICATOR FOR OUTBOARD FLAPS PRECAUTIONARY PER M/M 27-51-00 AND 27-58-01.

Part: MOTOR CLUTCH — SLIPS (TE FLAPS)

DURING AIR TURN BACK FOR SPLIT FLAP, INBOARD FLAPS DID NOT WORK IN ALTERNATE WORK, OK IN NORMAL. FOUND THAT THE INBOARD FLAP ELECTRIC MOTOR CLUTCH SLIPPING REPLACED ALTERNATE FLAP MOTOR ASSY PER BOEING M/M 27-51-17. OPERATIONAL CHECK OK PER M/M 27-51-00.

Part: TRANSMITTER — FAILED (RT LE FLAP)

DURING TAXI OUT, FLAPS SELECTED 10 DEGREES, THE OUTBOARD STOP AT 5 DEGREES, RECYCLED NO HELP. FOUND RIGHT OUTBOARD FLAP TRANSMITTER AT FAULT REPLACED TRANSMITTER AND CANNON PLUG PER MAINTENANCE MANUAL 27-58-01.

Part: AILERON — LOCKED OUT (RIGHT)

RETURNED TO BLOCKS DUE TO RIGHT HAND OUTBOARD AILERON LOCKED OUT WITH FLAPS AT 20 UNITS. INSPECTED RIGHT HAND OUTBOARD AILERON LOCKOUT ACTUATOR INSTRUMENTS AND WIRING. REMOVED, CLEANED, INSPECTED ELECTRICAL CONNECTIONS AND FOUND NO OBVIOUS DEFECTS, SYSTEM CHECKS SATISFACTORY.

Part: RESERVOIR — RUPTURED (CARGO DOOR)

UPON ARRIVAL VCP, UNABLE TO OPEN SIDE CARGO DOOR. WHILE ATTEMPTING TO TROUBLESHOOT DOOR HYDRAULIC PROBLEM, DOOR HYDRAULIC RESERVOIR RUPTURED. FOUND BENT LINE CAPPED WHICH CAUSED RUPTURE. REPLACED RESERVOIR IAW MM 52-35-00.

Part: TURBINE — FAILED (NR 4 ENGINE)

JFK - ON CLIMBOUT, NR 4 ENGINE EXPERIENCED A COMPRESSOR STALL AT CONSTANT SPEED, ALTITUDE 17,000 MAX EGT 856, ENGINE SHUTDOWN. SECOND STAGE TURBINE FAILURE, FOUND METAL IN TAIL PIPE. ENGINE CHANGED.

Part: ENGINE VANE CONT — MALFUNCTIONED (NR 4 ENGINE)

AT TAKEOFF, UNABLE TO REACH TARGET BEFORE HITTING STOPS. REPLACED ENGINE VANE CONTROL.

Part: FUEL CONTROL — MALFUNCTIONED (NR 4 ENGINE)

DURING CLIMBOUT EXPERIENCED SLUGGISH ENGINE RESPONSE NR 4 ENGINE AT FL 210. CLIMBING THROUGH FL 290 HEARD AUDIBLE STALL AND OBSERVED SUBSEQUENT TOTAL LOSS OF ENGINE POWER. ALL PARAMETERS DROPPED OFF INCLUDING EGT. RELIGHT OF ENGINE WAS NORMAL AND ENGINE PERFORMANCE REMAINED NORMAL DURING RETURN TO JFK. INSPECTED INLET/EXHAUST AND BLEEDS, BORESCOPED ENGINE 8TH, 9TH, 14TH, AND 15TH STAGE COMPRESSORS, BORESCOPED 1ST AND 2ND STAGE TURBINES, NO DAMAGE. REMOVED AND REPLACED FUEL CONTROL UNIT AND TT2 SENSOR.

Part: STRINGER — ELONGATED HOLE (BS 1852)

S34L ELONGATED HOLE AT BS 1852. STRINGER REPLACED.

Part: TE SKIN — SEPARATING (RT AILERON)

RIGHT OUTBOARD AILERON TRAILING EDGE SEPARATING INBOARD APROXIMATELY 6 TO 10 INCHES. REPAIRED PER BOEING SRM 51-40-09.

Part: LE SKIN — GOUGED (RT TE FOREFLAP)

RIGHT OUTBOARD FLAP, FOREFLAP OUTBOARD END LEADING EDGE IS GOUGED IN 3 PLACES. REPAIRED PER BOEING SRM 51-40-09.

Part: TE SKIN — SEPARATED (RT AILERON)

RIGHT OUTBOARD AILERON TRAILING EDGE SEPERATED OUTBOARD OF NR 2 STATIC WICK. REPAIRED PER BOEING SRM 51-40-09.

Part: RADOME — DELAMINATED (FWD FUS)

RADOME HAS AREAS OF ERROSION AND APPROXIMATELY 2 BY 2 AREA OF DELAMINATION. REPAIRED PER BOEING SRM 51-40-09.

Part: FAIRING — CRACKED (NR 3 PYLON)

NR 3 PYLON LOWER AFT FAIRING CRACKED ON RIGHT SIDE AND HAS LOOSE AND MISSING FASTENERS ON BOTH SIDES. REPAIRED PER BOEING SRM 51-40-02.

Part: SKIN — CRACKED (LT ELEVATOR)

LEFT INBOARD ELEVATOR TRAILING EDGE CRACKED, UPPER AND LOWER SURFACE APPROXIMATLY 36 TO 40 INCHES FROM INBOARD END. REPAIRED PER BOEING SRM 51-40-14.

Part: STRINGER — MISDRILLED (BS 1820-1850)

FOUND AT BS 1820 TO BS 1850, S34L UPPER SIDE OF HAT CHANNEL HAS 32 HOLES .5 INCH APART AND 11 HOLES UPPER SIDE OF HAT CHANNEL IN SPLICE AREA AT BS 1890. REPLACED STRINGER PER EA 5310-0-01.

Part: STRINGER — CORRODED (BS 1740-1890)

S34L FROM BS 1740 TO SPLICE ARE AT BS 1890 HAS LIGHT CORROSION ON LOWER UPPER SECTION OF HAT CHANNEL, NO PROTECTIVE COATING ON STRINGER. STRINGER REPLACED FOR OTHER DAMAGE.

Part: SKIN — MISDRILLED (BS 1740-1960)

DURING STRUCTURAL INSPECTION REQUIRED BY AD 95-01-04, MISDRILLED AND PLUGGED FUSELAGE SKIN WAS FOUND BETWEEN BS 1740 AND 1960 AT STRINGER 4. REPAIR ACCOMPLISHED PER FAA APPROVED DRAWING POLAR 747 53-830-1. AIRCRAFT RELEASE FOR SERVICE.