OMNI AIR TRANSPORT, LLC

SWITCH GUARDS LOCATED ON THE CENTER PEDESTAL DO NOT FUNCTION WELL. A MAIN ENGINE START SWITCH GUARD WAS FOUND PUSHED TO THE SIDE AND PRESSED/JAMMED INTO THE SWITCH CAUSING UNCOMMANDED ACTIVATION WITHOUT LIFTING THE GUARD AND PRESSING THE SWITCH. ANOTHER AIRCRAFT, ALSO LEAR 45, A MAIN ENGINE FIRE EXTINGUISHER SWITCH GUARD WAS FOUND TO PRESS INTO THE SWITCH WHEN THE GUARD WAS NOT ALIGNED CAUSING INADVERTENT ACTIVATION WITHOUT LIFTING THE GUARD AND PRESSING THE SWITCH.

DURING DESCENT THROUGH ABOUT 10,000' A LOUD POP WAS HEARD AND RH WINDSHIELD WAS SEEN TO HAVE SHATTERED. NO PRESSURIZATION WAS LOST, CREW FOLLOWED QRH AND CONTINUED NORMAL PROCEDURES AND LANDED WITHOUT INCIDENT. UPON LANDING IT WAS DISCOVERED THAT THE OUTER PLY OF WINDSHIELD HAD SHATTERED. NO OTHER DAMAGE TO THE AIRCRAFT AND NO INJURIES NOTED.

DURING CLIMB AROUND FL290 LOUD POPPING SOUND WAS HEARD AND RH WINDSHIELD WAS OBSERVED TO BE CRACKED. CREW ANALYZED SITUATION, STOPPED CLIMB, FOLLOWED THE QRH AND DIVERTED BACK TO AIRPORT. UPON LANDING OUTER PLY OF WINDSHIELD WAS FOUND TO BE SHATTERED. NO OTHER DAMAGE NOTED AND NO INJURIES.

ON CLIMB-OUT, ENROUTE, CREW HEARD A POPPING SOUND FROM THE LEFT SIDE OF THE AIRCRAFT AS THE AIRCRAFT PASSED FL320. NO AIR WAS FELT COMMING FROM THE VENTS. CREW DONNED OXYGEN MASKS WHEN THEY NOTED CABIN ALTITUDE APPROACHING CLIMBING TOWARD 10,000 FT. EMERGENCY DESCENT WAS INITIATED AND EMERGENCY WAS DECLARED. AIRCRAFT DIVERTED.

AFTER LANDING, DISCOVERED A FUELING DOOR OPENED IN FLIGHT AND DAMAGED DOOR AND HINGE.

ON LANDING, DISCOVERED FUELING DOOR OPENED IN FLIGHT AND DAMAGED THE DOOR AND HINGE.

AFTER START UP OF ENGINES, ACFT BEGAN TO TAXI AND THE PILOT REPORTED RT THROTTLE LEVER BECAME UNRESPONSIVE DURING TAXI. THEY RETURNED AND AFTER TROUBLESHOOTING IT WAS DETERMINED THE CONTROL ASSY, PN 7-43489-2, FOR THE RT ENGINE HAD SHEARED IN HALF, 6" FROM THE END AT THE ENGINE SIDE CONNECTION.

DURING CRUISE AT 41,000 FEET, THE RIGHT WINDOW DELAMINATED RESULTING IN AN EMERGENCY DECENT AND LANDING AT THE CLOSEST AIRPORT.

DURING THE APPROACH THE LT ENGINE FLAMED OUT WHEN THE THROTTLE LEVER WAS RETARDED TOWARDS FLIGHT IDLE. THE PIC DECLARED AN EMERGENCY AND THE AIRCRAFT LANDED WITH NO INCIDENT. THE LT ENGINE WAS NEVER ATTEMPTED TO BE RESTARTED DURING THE APPROACH. ATTEMPTS WERE MADE AT STARTING THE ENGINE WITH NO SUCCESS AND THE FUEL FLOW WAS NOTICED TO BE READING ZERO. MAINTENANCE INSTALLED A PRESSURE GAUGE DIRECTLY TO THE LT ENGINE FUEL PUMP AND DURING A START ATTEMPT FOUND THE PUMP TO BE PRODUCING 0 PSI. THE PUMP WAS REMOVED AND THE IMPELLER WITHIN THE PUMP WAS FOUND TO BE NOT FUNCTIONING. A NEW PUMP WAS ORDERED AND IS BEING INSTALLED AS OF 1500 ON 2/8/12.

SHORTLY AFTER THROTTLING BACK TO FLIGHT IDLE TO DESCEND FROM 41,000 FT THE NR 2 ENGINE MOMENTARILY STAYED AT 80 PERCENT (APPROXIMATELY 15 SECONDS) AND THEN CONTINUED ROLLING DOWN AND FLAMED OUT. PILOT WINDMILL RESTARTED THE ENGINE AT APPROXIMATELY 26,000 FT AND HAD TO RESET THE FUEL COMPUTER TO TURN OFF THE COMPUTER LIGHT. SLIGHT ENGINE SURGE WHICH CREATED A SLIGHT YAW WAS NOTICED AT 6,000 FT. ONCE ON THE GROUND WITH THE ENGINES SHUT OFF THE NR 2 ENGINE FUEL COMPUTER LIGHT WAS REPORTED AS FLASHING. MAINTENANCE DISPATCHED TO THE AIRCRAFT WITH A LAPTOP AND UPON DOWNLOAD FOUND THE N2 MONOPOLE HAD CAUSED A FAULT WHICH WAS PICKED UP BY THE DEEC. A NEW N2 MONOPOLE WAS INSTALLED AND THE ENGINE WAS RAN WITH NO FURTHER PROBLEMS NOTED AND THE DEEC WAS CHECKED WITH NO FURTHER FAULT CODES FOUND.

DURING CLIMB TO ALTITUDE THE RT ENGINE FIRE LIGHT ILLUMINATED MOMENTARILY. THROTTLE LEVER WAS RETARDED MOMENTARILY BUT LIGHT WENT OUT WITH NO OTHER INDICATIONS OR WARNINGS. AIRCRAFT FIRE DETECTION SYSTEM CURRENTLY BEING INVESTIGATED FOR CAUSE OF MOMENTARY LIGHT.

AUTOPILOT FAILED AT CRUISE FOLLOWED BY PRIMARY PITCH TRIM FAIL, MACH TRIM FAIL, DURING DESCENT AC BUSS TIE C/B POPPED. AMMETERS INDICATED 50 AMP DIFFERENCE. DURING TROUBLESHOOTING OF THE AUTOPILOT, PITCH TRIM, MACH TRIM & AC BUSS SYSTEMS FOUND CONNECTOR P213 FOR AC PARALLELING BOX TO NOT BE FULLY SECURED. RESECURED P213 AND PERFORMED NUMEROUS OPS CHECKS OF AUTOPILOT, PITCH TRIM, MACH TRIM & AC SYSTEMS WITH NO DEFECTS NOTED AT THIS TIME. IAW AMM CH 22-10, 27-41, AND 24-20. PERFORMED ADJUSTMENT TO THE RT VOLTAGE REGULATOR FOR THE RT GEN AMP SPLIT IS WITHIN LIMITS DURING ALL VARIOUS LOADS IAW AMM 24-31-03.

FIRE BOTTLE GAUGE HAS INACCURATE INDICATION, FOUND TO INDICATE (0) ON PREFLIGHT. THE BOTTLE WAS REMOVED AND DETERMINED TO BE FULL OF AGENT AND NOTICED ROTATING THE BOTTLE MOVED THE PRESSURE GAUGE. BY HAND SHAKING THE BOTTLE THE PRESSURE INDICATION WOULD MOVE FROM A (0) INDICATION UP TO 800 PSI. THE BOTTLE WAS REPLACED WITH AN O/H UNIT.

LEFT HORIZONTAL STABLILIZER HEAT BLANKET SHEARED, BURNING A .6250 INCH HOLE IN THE LEADING EDGE OF THE HORIZONTAL STABILIZER 5 INCHES OUTBOARD FROM THE INBOARD EDGE. (X)