Hughes 369 Safety Record

the total loss of engine power resulting from a fatigue failure of the 3rd stage turbine wheel airfoils. The reason for the airfoil's fatigue failure could not be determined.

The entanglement of the fuel quantity sender float in the start pump wiring within the fuel tank as a result of the wiring not being properly secured. This rendered the fuel gauge inaccurate and the low fuel warning light inoperative which led to fuel exhaustion. The improper securing of the wiring was a result of unspecified maintenance personnel not identifying the unsecured condition. Contributing factors were the lack of adequate guidance in the maintenance manuals on inspection of the wiring and the low rotor RPM during the autorotation resulting in a hard landing.

the failure of the pilot-in-command to maintain clearance from terrain. Factors include the high density altitude and the pilot-in-command's improper in-flight planning.

The pilot's inadequate visual lookout while lifting into a hover to ensure the helicopter was clear of all objects, which resulted in separation of an external mirror that then struck and damaged a main rotor blade. Factors in the accident were the presence of a seismic cable, and high vegetation around the helicopter's takeoff spot.

The pilot's failure to maintain altitude/clearance from terrain. A factor contributing to the accident was the pilot's attention being diverted inside the cockpit to look at the global positioning system.

The failure of the operator's maintenance personnel to properly rig the left/right seat twistgrip throttles to the engine fuel control, the pilot in command's failure to adhere to the rotorcraft flight manual, and the check pilot's premature flare during the autorotation resulting in a hard landing.

The loss of engine power due to the failure of the generator input drive-end bearing, which resulted in excessive vibrations that induced a fatigue fracture of the Pc line leading to the engine fuel control unit. A contributing factor was the lack of suitable terrain for the forced landing.

Dynamic rollover during an attempted takeoff, due to the combined effects of the soft sloping terrain and the pilot's failure to redistribute the passengers to a more favorable lateral CG condition.

A loss of engine power due to turbine blade separation as a result of hot corrosion damage to the turbine blades. Contributing to the accident was the pilot misjudging the flare at the completion of the autorotation resulting in a hard landing. The dark night was a factor.

Overload failure of the tail rotor transmission housing (gearbox) for undetermined reasons, which resulted in an inability to adequately control the aircraft.

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.

Inadequate visual surveillance by the pilot before takeoff resulting in liftoff with a deplaning passenger still partially aboard the helicopter. A factor in the accident was the operator's inadequate procedures.

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.