Accident Sequence
While maneuvering at approximately 12,500 feet mean sea level during a search mission, the pilot of a news helicopter observed a group of individuals exiting a tree-covered area and a National Guard UH-60 helicopter staged on the ground in an open area. After a radio conversation with the National Guard pilot, the news helicopter pilot attempted to land in the open area to obtain video footage of a rescue operation.
The pilot circled the open area three times at an airspeed of 40 to 50 knots before attempting to land about 300 feet from the National Guard helicopter. Approximately 30 feet above ground level, the pilot applied forward cyclic to increase airspeed for a run-on landing. Shortly thereafter, the helicopter began a yaw to the right. The pilot then applied full left anti-torque pedal input, but the right yaw continued. At about 10 feet above ground level, the pilot reduced throttle and applied forward cyclic. The helicopter subsequently impacted the terrain nose first, rolled to the left, and came to rest on its left side.
Background
The flight's purpose was to assist in an air search for a missing individual and provide aerial photo footage. The accident site was located in mountainous open terrain at an elevation of approximately 12,400 feet mean sea level.
Environmental Conditions
The pilot reported that the wind was calm and the temperature was approximately 70 degrees Fahrenheit at the time of the accident.
Pilot Actions
The pilot stated that he did not complete any performance calculations prior to the flight.
Helicopter Condition
No preaccident anomalies were noted with the helicopter.
Loss of Tail Rotor Effectiveness Information
The FAA has published information about loss of tail rotor effectiveness. At higher altitudes, where the air is thinner, tail rotor thrust and efficiency are reduced. When operating at high altitudes and high gross weight, especially while hovering, the tail rotor thrust may not be sufficient to maintain directional control, and loss of tail rotor effectiveness can occur. In this case, the hovering ceiling is limited by tail rotor thrust and not necessarily by power available. Under these conditions, gross weights need to be reduced and/or operations need to be limited to lower density altitudes.