Hughes 369 Safety Record

The net gunner's improper decision to fire the net gun at an angle that allowed the net to become entangled in the main rotor system. A factor was foreign object damage to the main rotor blades.

A hard landing due to the dual student's failure to maintain main rotor speed, his improper landing flare, and the flight control interference by the flight instructor.

fuel exhaustion due to the pilot's failure to refuel the aircraft, which resulted in a loss of engine power. A contributing factor was the unsuitable steep terrain on which to make a forced landing.

The pilot's inadequate pre-flight planning which resulted in fuel exhaustion and the subsequent loss of engine power. A factor was rough and uneven terrain.

Fuel starvation as a result of a collapsed fuel nozzle filter screen. Contamination that blocked the fuel nozzle screen and water contamination were factors.

a loss of engine power while in cruise flight resulting from the failure and liberation of several turbine blades due to hot corrosion effects which weakened the blades. The hot corrosion damage was the result of multiple turbine over temperature events which occurred over several flights. Contributing factors were the lack of suitable terrain, and high vegetation.

the helicopter's encounter with loss of tail rotor effectiveness while hovering out-of-ground effect, and the pilot's failure to maintain control. A contributing factor was the soft terrain condition.

The turbine outlet temperature indicating system was out of calibration. Factors included improper maintenance calibration, which resulted in the over temperature of the turbine assembly.

improper maintenance inspection of the tail rotor by maintenance personnel and improper preflight inspection of the tail rotor by the pilot, which resulted in worn elastomeric bearings being continued in service, resulting in failure of the tail rotor assembly, and damage to the helicopter during a hard landing.

Fuel exhaustion and inaccurate fuel management. A false indication on the fuel quantity gage, and an erratic low level fuel warning system were factors.

The pilot's improper use of flight controls during an emergency landing. Factors were an encounter with a loss of tail rotor effectiveness (LTE) during an out-of-ground effect hover, the pilot's inadequate weather evaluation, and his failure to follow proper procedures for LTE.

an uncontrolled touchdown following entry into a "out-of-ground effect" hover. Factors were loss of tail rotor effectiveness, and the pilot's lack of recent experience in kind of aircraft and total experience in type of aircraft.

The pilot's failure to refuel the helicopter prior to fuel exhaustion. Factors associated with the accident were an inoperative low fuel warning system, and the pilot's improper autorotation.

The disintegration and failure of the oil pump drive spur gear aft bearing, which resulted in failure of the oil pump and subsequent oil starvation to the engine's turbine module. A factor in the accident was the failure of company maintenance personnel to comply with the manufacturer's service bulletin regarding replacement of the bearing.

A partial loss of engine power due to erosion in the compressor assembly module. Factors were a missing rotating labyrinth seal, the installation of which had not been performed by unknown maintenance personnel.