Accident Sequence
During a hover taxi on a company 14 CFR Part 135 pilot checkride, the helicopter experienced a series of fore and aft skid collisions with the taxiway. The tail rotor subsequently separated from the helicopter.
The purpose of the flight was for one of the company pilots to complete an initial instrument checkride. As the examinee taxied the helicopter for departure, the check pilot retarded the number 1 engine to a partial power setting. The examinee then lowered the collective.
The helicopter's skids contacted the ground, causing it to bounce into the air in a nose-low attitude. This was followed by a ground contact on the toes of the skids and an additional bounce. During the second bounce, aft cyclic was applied, and the tail rotor contacted the ground and broke from the helicopter.
After the tail rotor separated, the helicopter bounced and began turning to the right. The check pilot applied power to the number 1 engine, and the forward portion of the skids contacted the ground while the helicopter turned. The helicopter spun approximately 270 degrees about 10 feet above ground level.
After 1 to 1½ turns, the check pilot assumed control of the helicopter. He leveled the helicopter and applied full left pedal. The spin continued until he closed both throttles and performed a hovering autorotation.
Pilot Actions and Post-Accident Information
Neither the check pilot nor the examinee reported any mechanical malfunctions with the helicopter prior to the accident. The chief pilot stated that the check airman responded in accordance with current company policy and procedures.