Denison, TX, USA
N108RA
Westland Wasp
During initial climb-out on a southwesterly direction, while at an estimated altitude of 90 feet above the ground, and an estimated airspeed of 25 knots, the helicopter experienced an un-commanded reduction of engine power to flight idle. The 358-hour student pilot turned the helicopter 180 degrees, put the collective down, and applied right anti-torque pedal. The helicopter landed hard on a street, impacting on all four landing gear before bouncing back into the air. During the second ground impact, the left rear landing gear collapsed and the main rotor blades and tail rotor made contact with the ground. The winds at the time of the mishap were reported from 040 degrees at 8 knots. The reason for the reported loss of engine power could not be determined.
On May 30, 2005, about 1205 central daylight time, a Westland Wasp turboshaft powered helicopter, N108RA, was substantially damaged following a partial loss of engine power during takeoff from private property near Denison, Texas. The student pilot and his passenger were not injured. The helicopter, for which an airworthiness certificate had not been issued, was registered to and operated by the pilot. Visual meteorological conditions prevailed and a flight plan was not filed for the 14 Code of Federal Regulations Part 91 personal flight. According to the 358-hour student pilot, during the initial climb-out in a southwesterly heading, at an altitude of approximately 90 feet above the ground, while at an estimated airspeed of 25 knots, the helicopter experienced an un-commanded reduction of engine power to flight idle. The pilot added that he turned the helicopter 180 degrees, placed the collective down, and applied right anti-torque pedal. The helicopter settled hard into a street, impacting on all four landing gear before bouncing back into the air. During the second ground impact, the left rear landing gear collapsed and the main rotor blades and tail rotor made contact with the ground. The pilot, who reports that he was operating the helicopter as a "public use" aircraft, reported to have accumulated all of his flight time in rotorcraft, with a total of 16.2 hours in the accident helicopter. The helicopter was manufactured in the United Kingdom by Westland Helicopter in 1965. The design consisted of an all-metal monocoque fuselage supported by four separate gear legs, each with a single wheel. Powering the four blade main rotor was a single 1,050 shaft horse power Rolls-Royce Nimbus 103 turboshaft engine. The helicopter was designed to carry one pilot and four passengers. N108RA was imported into the United States at an unknown date. A Federal Aviation Administration (FAA) inspector examined the wreckage. The inspector reported that the helicopter sustained structural damage to the fuselage. The reason for the reported uncommanded loss of engine power could not be determined. At 1145, the weather observation facility at Grayson County Airport (GYI), near Denison, Texas, located approximately 8 nautical miles southwest from the accident site, reported winds from 040 degrees at 8 knots, visibility 10 statute miles, scattered clouds at 2,200 feet and 3,100 feet, clouds broken at 3,800 feet, temperature 77 degrees Fahrenheit, dew point 66 degrees Fahrenheit, and barometric pressure setting of 29.88 inches of Mercury.
The partial loss of engine power for undetermined reasons. A contributing factor was the lack of suitable terrain for the forced landing.
Source: NTSB Aviation Accident Database
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