Bell 206 Safety Record

The hard landing due to the pilot's failure to maintain proper main rotor rpm. Contributing factors were the loss of engine power for undetermined reasons, and the pilot's failure to deploy the emergency floats.

fuel contamination due to the combination of DIEGME, water, and bacterial growth, which resulted in formation of an apple-jelly type material that blocked the fuel nozzle screen and led to a loss of engine power.

the loss of a bolt in a Thomas coupling on the tail rotor drive shaft, for undetermined reasons, during climb, while operating over unsuitable terrain.

The pilot's inadvertent VFR flight into instrument meteorological conditions, which resulted in his failure to maintain control of the helicopter. Factors were the fog and the pilot's lack of instrument flight experience.

the pilot encountered a loss of tail rotor effectiveness which led to an uncontrolled rotation and subsequent hard landing. Factors were unfavorable wind conditions, density altitude, and uneven terrain.

A snow ingestion caused loss of engine power due to the pilot's inadequate preflight inspection and failure to remove the accumulated snow from the engine inlet area. Also causal was the pilot's failure to maintain main rotor rpm while maneuvering to avoid power lines directly in his path during the autorotation necessitated by the loss of power. While the failure to maintain proper rotor rpm is listed as causal, the Safety Board acknowledges that the pilot's successful avoidance of the power lines, which required expenditure of rotor energy, likely precluded a more severe accident.

**This report was modified on 2/23/2016. Please refer to the public docket for this accident for additional information.** The pilot-in-command's excessive rate of descent and improper use of the collective control, which resulted in a low rotor rpm condition.

The failure of the platform worker to maintain clearance with the turning tail rotor blades. A factor was the inadequate coordination between the pilot and the passengers pertaining to procedures for disembarking from the helicopter.

The failure of maintenance personnel to properly assemble the engine's accessory gearbox, which resulted in a total loss of engine power due to partial blockage of the main oil passage by an o-ring. The blockage reduced oil flow to the turbine shafting, which led to the total failure of the gas producer turbine shaft and the power (free) turbine shaft. A factor was the lack of suitable terrain for the forced landing.

the pilot's inability to maintain control of the helicopter after encountering a dynamic rollover due to entanglement of the external load cable with the left landing gear skid.

the passenger's failure to recognize and avoid the hazard associated with the rotating tail rotor. The operator/event organizer's lack of ground facilities or support personnel to assist/control passenger access to the helipad was a related factor.

the pilot's improper in-flight planning/decision. A related factor was his failure to follow the company procedure of maintaining visual contact with the external long-line cable, while hovering with it attached.

The pilots improper in-flight planning/decision to conduct an out of ground effect hover with a tailwind resulting in an in-flight loss of directional control due to loss of tailrotor effectiveness/unanticipated right yaw, and subsequent in-flight collision with a tree and terrain. Contributing to the accident was the manufactures inadequate written procedures in the flight manual, and the pilot's inadequate training pertaining to the loss of tailrotor effectiveness/unanticipated right yaw.