N824SHHoffius Stowe CHALLENGER II

On May 10, 2014, about 1342 eastern daylight time, an amateur-built Challenger II airplane, N824SH, impacted the ground following a loss of control near Attica, Indiana. The pilot was fatally injured and the airplane was destroyed. The aircraft was registered to and operated by the pilot under the provisions of 14 Code of Federal Regulations Part 91 as a personal flight. Visual meteorological conditions prevailed for the flight, which was not on a flight plan. The flight originated from a private airstrip near Covington, Indiana at an unconfirmed time. It was reported that the airplane was maneuvering at low altitude prior to the accident. The airplane then descended and impacted the ground.

The pilot, age 72, held a private pilot certificate with a single-engine land airplane rating. His most recent medical examination was on November 23, 1992. At the time of that examination, the pilot reported having 235 hours total flight time.

The accident airplane met the definition of a "Light Sport Airplane", and as such did not require the pilot to hold a valid medical certificate. Regulations permitted the pilot to fly as a Light-Sport pilot as long as he had a valid driver's license and was in compliance with 14 CFR 61.53 "Prohibition on operations during medical deficiency".

The accident airplane was an amateur-built airplane constructed from a kit. The airplane was a high-wing monoplane with tricycle landing gear. It could seat two occupants in a tandem seating arrangement and was constructed primarily of aluminum with a fabric covering. The airplane was powered by a Hirth model 2703 engine. The engine was a 2-cylinder 2-cycle engine rated to produce 55 horsepower. According to Federal Aviation Administration records, the pilot was not the original builder of the airplane and had purchased the airplane in 1992.

At 1254, the recorded weather conditions at the Purdue University Airport, Lafayette, Indiana, about 15 miles northeast of the accident site were: Wind variable at 3 knots; visibility 10 statute miles; clear skies; temperature 21 degrees Celsius; dew point 5 degrees Celsius; Altimeter setting 29.96 inches of mercury.

The aft fuselage and tail surfaces of the airplane remained intact. The forward fuselage was crushed and the tip of the right wing also had crush damage. The left wing was intact and remained attached to the fuselage. The damage to the right wing and fuselage were consistent with a right wing low, nose low impact. Postaccident examination of the airplane confirmed flight control system continuity from the cockpit to all control surfaces. The airplane's engine could not be rotated by hand. A subsequent teardown examination of the engine confirmed that impact damage had prevented the engine from rotating. No preimpact anomalies were detected in regard to the engine examination. The airplane had several electronic engine instruments installed; however, the instrument manufacturer confirmed that the units installed had no recording capability. No pre-impact anomalies were discovered during examination of the airplane.

Investigators noted that the airspeed indicator installed in the amateur-built airplane was marked for speeds from 40 to 340 miles per hour. According to the airworthiness documentation, the airplane had a stall speed of 32 miles per hour, and a maximum speed of 105 miles per hour.

An autopsy of the pilot listed the cause of death as spinal cord disruption due to the accident.

Toxicology testing was performed by the FAA Civil Aerospace Medical Institute. Testing results were negative for all substances in the screening profile.