NEW WORLD AVIATION, INC.

BEGAN TAKEOFF ROLL, AT APPROXIMATELY 50 KNOTS, A TRIPLE CHIME MASTER WARNING WAS HEARD ACCOMPANIED BY A RED EICAS SPOILERS EXTENDED MESSAGE. NOTICED SPOILERS WERE EXTENDED ON FLT MFD PAGE AND PHYSICALLY FELT THE LIFT DUMPING. ABORTED TAKEOFF. THE SPOILERS STOWED ON THEIR OWN DURING THE TAXI BACK.

DURING FLIGHT, A PASSENGER NOTICED A WISP OF SMOKE COMING FROM THE CONVECTION OVEN CONTROL PANEL. THE PIC PULLED THE CIRCUIT BREAKER FOR THE OVEN AND NOTICED A SLIGHT BURNT ELECTRICAL ODOR. THERE WERE NO FURTHER ISSUES AND THE FLIGHT CONTINUED ON. ON ARRIVAL, MAINTENANCE WAW ABLE TO REMOVE THE OVEN CONTROL PANEL AND WITHIN THE PANEL FOUND WIRES BEHIND THE TEMPERATURE CONTROL KNOB THAT SHOWED SIGNS OF ARCING. STOWED THE CONNECTOR PLUGS AND PULLED AND COLLARED THE OVEN CIRCUIT BREAKER FOR FURTHER FLIGHT. THE OVEN CONTROL PANEL IS BEING REPLACED WITH A REPAIRED UNIT.

THE PILOT REPORTED INTERMITTENT NR 1 FLAP MOTOR CIRCUIT BREAKER TRIPPING IN FLIGHT. AFTER FURTHER INVESTIGATION, FOUND A CAM LOCK FASTENER BEHIND PILOTS LT ARM THAT HOLDS THE TRIM PANEL ON AT FUSELAGE BS 280, HOOKED THE WIRING AND CAUSED THE WIRE TO SHORT OUT AND TRIP THE BREAKER. THE SHORT MELTED THE TIP OF THE FASTENER. REPLACED FASTENER AND REPAIRED WIRING, REPOSITIONED WIRING AS REQUIRED.

AT START OF DECENT, THE WINDSCREEN CRACKED AND A SMALL PEACE OF THE OUTHER LAYER OF WINDSHELD DEPARTED THE ACFT. THE ACFT CONTINUED DECENT AND LANDED AT ITS INTENDED AIRPORT WITH NO OTHER INCIDENT. THE WINDSCREEN WAS REPLACED AND THE FLIGHT CONTINUED.

DURING CLIMB, LT ENGINE FIRE T-HANDLE ILLUMINATED. ALL ENGINE GAUGES INDICATED NORMAL. REDUCED POWER ON LT ENGINE. LIGHT EXTINGUISHED IN ABOUT 3 SECONDS AND FIRE LOOP TESTED NORMALLY. RAN THE APPROPRIATE CHECK LIST AND CONTINUED WITHOUT FURTHER ISSUE. WROTE UP THE DISCREPANCY, ADVISED MX AND DISPATCH. MX FOUND THE FIRE LOOP TOO CLOSE TO THE REAR FLANGE. THE FIRE LOOP WAS RESET TO THE CORRECT DISTANCE FROM FLANGE.

AT PREFLIGHT, THE PILOT NOTICED THAT THE SPEED BRAKES DID NOT CLOSE COMPLETELY. MAINT WAS CALLED AND AFTER SOME OPERATIONAL CHECKS AND A VISUAL INSPECTION OF THE CONTROL SYS AT THE LT MAIN GEAR WHEEL WELL A STONE WAS FOUND AT A CONTROL CABLE PULLEY AND THE STONE WOULD NOT ALLOW THE CABLE TO CLOSE THE SPEED BRAKES ALL THE WAY. STONE LOGED IN PULLEY. (K)

AT START UP OF THE RT ENGINE, THE PILOT NOTICED A VIBRATION AND THE ENGINE WAS SHUT DOWN, TROUBLESHOT PROBLEM. IT WAS DETERMINED THAT A HIGH PRESSURE TURBINE BEARING HAD FAILED. (K)

ON AIRCRAFT POST FLIGHT INSPECTION, FOUND GROUND SPOILER ACTUATOR SEEPING HYDRAULIC FLUID. CLEANED AFFECTED AREA, GROUND RUN AIRCRAFT TO ACTUATE SPOILERS, AND FOUND ACTUATOR SEEPING BETWEEN VALVE BODY AND ACTUATOR HOUSING. REMOVED AND REPLACED ACTUATOR. LEAK CHECKED, OK. (K)

NR 1 ENGINE FORWARD THROTTLE CABLE DISCOVERED TO HAVE A VERY ROUGH GRINDING FEEL. REPLACED FORWARD AND AFT NR 1 ENGINE THROTTLE CABLE ASSEMBLIES AND RIGGED IAW MM, OPERATION CHECKED NORMAL. DURING RESOLUTION OF THIS CONDITION. IT WAS DISCOVERED THAT BOTH CABLE ASSEMBLIES MUST BE CHANGED AS A SET CONTRARY TO WHAT MFG AND MM STATES. (K)

GEAR LIGHT NOSE GEAR FAILED TO ILLUMINATE WITH GEAR EXTENSION UNTIL 150 KTS. PINNED LANDING GEAR , ISSUED SPECIAL FLIGHT PERMIT FOR AC RETURN. JACKED AC AND INSPECTED NOSE GEAR, DISCOVERED LOCKING CLIP ON NOSE GEAR DOWN/LOCKED SWITCH POPPED OUT OF DETENT-SECURED AND SAFTIED DOWN/LOCKED SWITCH. CYCLED LANDING GEAR TEN TIMES WITH NO FURTHER DISCREPANCIES. (K)

IAW MM, TO COMPLY WITH THE 24 MONTH NDT REQUIREMENTS UNDER THE ULTRASONIC, CORROSION WAS FOUND UNDER THE LT FWD WING ATTACHMENT FITTING AT FUSELAGE STA 345, BUTT LINE 40. (K)

UPON LANDING, RT THRUST REVERSER ONLY DEPLOYED AN INCH AND WOULD NOT STOW. FOUND T/R ACTUATOR JAMMED. REMOVED AND REPLACED RT T/R ACTUATOR. OPS AND LEAK CHECKED GOOD.

UPON LANDING AT KIAD, RIGHT THRUST REVERSER ONLY DEPLOYED AN INCH AND WOULD NOT STOW. FOUND T/R ACTUATOR JAMMED. REMOVED AND REPLACED RIGHT T/R ACTUATOR. OP AND LEAK CHECK GOOD IAW GIV AMM (REV 51) 78-00-00 PAGE 401-421 PARA 2A, B AND C.

AT 5000 LANDING INSPECTION THE FS 793 AFT BULKHEAD CAP ANGLE NDT INSPECTION WAS PERFORMED AND A CRACK WAS FOUND ON THE RT SIDE ABOUT .3750 INCH LONG. A NEW CAP ANGLE WAS INSTALLED.

MAINTENANCE WAS INVESTIGATING THE STABILIZER WORKING LOOSE IN LESS THAN 10 HOURS SINCE LAST MAKING ADJUSTMENTS. THERE WAS A CONCERN ABOUT A SNAPPING NOISE DURING VERTICAL SHAKING OF THE AIRFOIL AT THE OB POSITIONS. THIS LED MAINTENANCE TO REMOVE THE ASSEMBLY FOR INSPECTION; WHICH RESULTED IN FINDING A 9.5 INCH CRACK IN THE FORWARD SPAR KEVLAR WRAP. (K)

ON TAKEOFF WITH GEAR UP, THE GEAR HANDLE LIGHT WAS ON. PRELIMINARY TROUBLESHOOTING DETERMINED THAT THE LT MAIN GEAR DOOR UP SWITCH WAS AT FAULT. WHEN REPLACING SWITCH, FOUND A LOOSE WIRE AT A BUTT SPLICE. (K)

LT ENGINE WILL NOT START; NO START VALVE OR IGNITION LIGHT WHEN STARTER BUTTON PRESSED. A REPLACEMENT STARTER WAS INSTALLED AND THE AIRCRAFT WAS FLOWN BACK TO ITS HOME BASE. (K)

UPON AIRCRAFT TEST FLIGHT FOR COMPLETION OF TAWS INSTALLATION. AIRCRAFT EXPERIENCED SMOKE IN THE CABIN AND COCKPIT. CREW DECLARED AND EMERGENCY LANDING AND PERFORMED AN UNEVENTFUL LANDING, USING NORMAL PUBLISHED EMERGENCY PROCEDURE. TROUBLESHOOTING FOUND THE APU GCU BURNED OUT (4) DIODE BOARD GCU REPLACED WITH AN OVERHAULED UNIT AND OPS CHECKED OK. (K)

LT ENGINE FIRE T-HANDLE WAS FLASHING. NO OTHER INDICATIONS OF FIRE. PERFORMED RESISTANCE CHECK OF LT ENGINE FIRE LOOPS AND FOUND CENTER CONDUCTOR RESISTANCE OF ACCESSORY GB LOOP READING HIGH. REPLACED LT ENGINE ACCESSORY GB LOOP. FUNCTIONAL CHECK AND GROUND RUN OK. (K)

WHILE ARRIVING, NOTICED LOW HYDRAULIC QUANTITY. CREW DIVERTED, DUE TO INCREASED RUNWAY LENGTH. (EA25200504599)

LEFT WINDSHIELD FAILED IN FLIGHT, OUTER PANE CRACKED AND SEPARATED. CREW FOLLOWED CHECKLIST PROCEDRUES AND LANDED AT A SUITABLE AIRFIELD. (M)

CREW REPORTED NO CABIN AIR AFTER TAKE-OFF FROM TEB. AIRCRAFT RETURNED TO ABE BELOW 10,000 FOR SWAP OUT WITH ANOTHER. AIRCRAFT GROUND RUN BY MAINTENANCE PERSONNEL AND OPERATED THROUGH NORMAL AND EMERGENCY MODES. IT WAS DETERMINED THAT FLOW CONTROL VALVE WAS INTERMITTENT. FLOW CONTROL VALVE IS TO BE CHANGED.

LT ENGINE FIRE LIGHT CAME ON FOR A FEW SECONDS. AFTER REDUCTION OF POWER, LIGHT EXTINGUISHED. NO OTHER INDICATIONS OF A FIRE. INSPECTED FIRE HARNESS LOOPS WITH NO DEFECTS NOTED. COMPLIED WITH FIRE LOOP RESISTANCE CHECKS IAW MFG MM AND FOUND WITHIN LIMITS. FIRE LOOP TEST, OK. AIRCRAFT GROUND RUN AND COULD NOT DUPLICATE. REPLACED HP SECTION OF MOD VALVE CRUSH GASKET DUE TO MINOR AIR LEAK. THIS WAS NOT BELIEVED TO CAUSE THE PROBLEM.

AT APPROXIMATELY 0650 PACIFIC TIME, WHILE ON CLIMB OUT AND CLIMBING THROUGH 5500 FT MSL THE AIRCRAFT EXPERIENCED AN UNCOMMANDED SHUTDOWN OF THE LEFT ENGINE. ALL CHECKLISTS AND PROCEDURES WERE FOLLOWED. AN EMERGENCY WAS DECLARED, AND AN UNEVENTFUL LANDING WAS MADE. MAINTENANCE WAS CONTRACTED AND ALL PROCEDURES VIA OPS AND MAINTENANCE WERE ACCOMPLISHED. REPRESENTATIVES WERE DISPATCHED TO AIRCRAFT. A/C WAS GROUND RUN AFTER INCIDENT WITH NO ABNORMAL EFFECTS. ENGINE FUEL CONTROL UNIT WAS REPLACED AT ENGINE MFG RECOMMENDATION.

AUTOPILOT SYSTEM, WHEN AUTOPILOT SELECTED TO ALTITUDE PRESET, A/C DID NOT CAPTURE SELECTED ALTITUDE. FMS HEADING IN ONE DIRECTION AC DID NOT CAPTURE HEADING AS SELECTED. ON APPROACH TO RDG, PILOT WAS UNABLE TO SELECT APP NR ON AUTOPILOT CONTROLLER. REMOVED AND REPLACED A/P PITCH COMPUTER. AC TEST FLOWN SATISFACTORY AND RETURNED TO SERVICE.

LEAKING ACTUATOR OR LINE CAUSED EXCESSIVE LESS OF COMBINED HYDRAULIC FLUID. FOUND THE END CAP CRACKED APPROXIMATELY .3333 OF THE CAP CIRCUMFERENCE.

LEFT WING REAR BEAM HAD CORROSION UNDERNEATH AILERON. (X)

CREW REPORTED SMOKE IN CABIN DURING FLIGHT. REMOVED AND REPLACED TEMPERATURE CONTROLLER AND H VALVE. OPS CHECKED OK

RIGHT HAND MAIN GEARBOX COWLING CAME OFF OF AIRCRAFT DURING FLIGHT. NO DAMAGE TO AIRCRAFT OTHER THAN MGB COWL ITSELF. NO PERSONAL OR PROPERY DAMAGE OCCURRED. (X)