Hughes 369 Safety Record

The pilot's misinterpretation of the wind direction (in-flight planning) and subsequent improper descent rate to the ground during a landing attempt. A factor was the tailwind conditions.

The failure of the collective bungee support bracket due to non-compliance with a service information notice, which resulted in the pilot executing a precautionary autorotative landing. A contributing factor was the lack of suitable terrain for the landing.

The pilot's failure to maintain rotor rpm while performing a simulated autorotation, which resulted in a hard landing. A contributing factor was the pilot's incorrect interpretation of the examiner's instruction to add power.

the pilot's failure to maintain an adequate visual lookout and obstacle clearance altitude, which resulted in a collision with power lines. Factors in the accident were the position of the sun relative to the helicopter's flight path, which lessoned the visual acuity of the pilot, and, the pilot's intentional low altitude flight.

The fatigue cracking and failure of the tail rotor control rod during cruise flight, which resulted in a hard landing during the precautionary landing.

The pilot's failure to maintain clearance of a tree during a landing attempt due to loss of visibility from a self induced brown-out condition. Contributing factors were the pilot's failure to identify a hazardous landing site, and the tree.

the bullet(s), which severed the helicopter's left tail rotor pedal. Contributing factors were the severed anti-torque pedal and the unsuitable terrain for landing.

The pilot's failure to maintain aircraft control due to delayed remedial action during the encounter with the loss of tail rotor effectiveness. Contributing factors were the pilot's inadequate preflight performance planning, and the inadequate supervision by the US Forest Service personnel.

the partial loss of engine power due to fuel contamination. The fuel contamination was due to the failure of the maintenance personnel to ensure that the helicopter's fuel system had been thoroughly cleaned after a known previous contamination event, and the failure of company line personnel to follow the daily quality assurance checks on the company's remote based fuel supply.

The flight crew's failure to maintain adequate altitude/clearance from a building, which resulted in contact with the building, dynamic rollover, and collision with terrain.

the pilot's improper in-flight planning and decision making, his failure to maintain terrain clearance, and the total failure of the tail rotor drive shaft as a result of the tail rotor strike.

The loss of engine power as a result of fatigue cracking of the compressor adaptor coupling initiated by fretting on the pilot diameter and subsequent disconnection of the compressor from the turbine assembly. A contributing factor was the low operating altitude of the helicopter, which made a successful autorotation by the pilot imposible.

The pilot's inadequate compensation for wind conditions while the helicopter was standing, which resulted in the coasting main rotor blade contacting the tail boom. A factor associated with the accident was the gusty wind condition.

The pilot's misjudgment of clearance from the surface of the lake during the aerial application pass. The low altitude operation, glassy water, and his visual perception were contributing factors.

The improper installation of a bolt in the gas generator governor linkage by company maintenance personnel, which resulted in a loss of the bolt, a loss of engine power while maneuvering, and subsequent forced landing and collision with trees. Factors contributing to the accident were an inadequate preflight inspection by the pilot, and an uncommanded surge in engine power.