COLLINSVILLE, OK, USA
N113BW
WALTON SKYBOLT
THE AIRPLANE ROTATED AT THE MIDPOINT OF A 2,400 FOOT RUNWAY AND ACCELERATED WHILE ABOUT 20 FEET ABOVE THE RUNWAY. AS THE AIRPLANE APPROACHED THE DEPARTURE END OF THE RUNWAY THE AIRPLANE ENTERED A RAPID PULL UP TO VERTICAL. FROM AN ALTITUDE OF 200 FEET TO 300 FEET ABOVE THE GROUND THE AIRPLANE ENTERED A LEFT TURN AND THE BANK INCREASED TO EXCEED 90 DEGREES. THE AIRPLANE THEN PITCHED DOWN FROM 30 DEGREES TO NEAR VERTICAL WITH LEFT WING LOW. WITNESSES REPORTED THAT THE ENGINE WAS AT FULL POWER. A POST IMPACT FIRE DESTROYED THE AIRPLANE. THERE WERE NO AIRFRAME DISCREPANCIES NOTED. CONTROL RODS AND A RUDDER CABLE WERE FOUND SEPARATED AND EXAMINATION BY THE NTSB METALLURGIST REVEALED THE CONTROL RODS EXHIBITED FRACTURE FEATURES AND ASSOCIATED DEFORMATION CONSISTENT WITH OVERSTRESS SEPARATIONS.
On August 27, 1994, at 1125 central daylight time, a homebuilt Walton Skybolt, N113BW, was destroyed following a loss of control during takeoff near Collinsville, Oklahoma. The airline transport rated pilot and one passenger received fatal injuries. Visual meteorological conditions prevailed for the planned cross country flight. Witnesses reported the flight was planned from Sand Ridge Airport, Collinsville, Oklahoma, to Joplin, Missouri. A preflight and runup was conducted by the pilot. The airplane rotated from the midpoint of the south runway and accelerated as the airplane flew about 20 feet above the ground. As the airplane approached the departure end of the runway, they observed the airplane in a "rapid pullup" to "vertical." Subsequently from an altitude of 200 feet to 300 feet a left turn was initiated and the bank increased to exceed 90 degrees. One witness observed the "nose was pitched down approximately 30 degrees below the horizon, left wing low, engine full power, airplane pointed north." Another witness reported the airplane continued to "pitch down to near vertical and rotate left." Witnesses stated that the engine was developing power until the impact and there were no inflight airframe discrepancies observed. The post crash fire erupted at impact. A witness stated that on all previous takeoffs he observed the airplane climb to about 200 feet AGL. The pilot would then initiate a left climbing turn, with a 45 degree bank and nose high attitude, to crosswind. The Federal Aviation Administration (FAA) inspector examined the airplane, which came to rest at the southeast corner of the field approximately 200 feet east of the runway. He observed ground scars that approximated those of the left wing leading edge. Portions of the airplane were located in a ground scar which exhibited circular striations. Control rods and a rudder cable were found separated and these components were forwarded to the NTSB for metallurgical examination. The airplane battery was an electrical source in the vicinity of the rudder cable. The Office of the Chief Medical Examiner of Oklahoma City, Oklahoma, performed the autopsy. Toxicological results were negative. Metallurgical examination (report enclosed) revealed the control rods exhibited fracture features and associated deformation consistent with overstress separations. The mating ends of the cable separation contained what appeared to be melted and resolidified material, typical of an arc strike. The airplane was released to the estate.
THE PILOT'S FAILURE TO MAINTAIN AIRSPEED RESULTING IN AN INADVERTENT STALL.
Source: NTSB Aviation Accident Database
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