N426KSShell John SUPER SIX · 2010

On February 6, 2017, at 1615 eastern standard time, an experimental, amateur-built Super Six, N426KS, was substantially damaged when it was involved in an accident near Morganton, North Carolina. The private pilot was seriously injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.

The pilot, who was the owner of the airplane, stated that he would occasionally run the airplane and would not fly it, but on the day of the accident, he decided to take the airplane around the airport traffic pattern one time. He conducted a preflight inspection, which included measuring the fuel contained in the tanks. The pilot remembered conducting a normal engine run-up and a portion of the takeoff, but did not remember anything further until he woke up in the ambulance following the accident. He did not recall if he had retracted the landing gear or if the engine was operating.

Witnesses reported that they saw the airplane descend through the trees, followed immediately by a postimpact fire. One witness heard the engine “sputtering” before impact.

The pilot, who was the owner of the airplane, had about 5,500 hours total flight experience, of which 7 hours were in the accident airplane. He accrued about 50 total hours flight experience in the previous year, of which none were in the accident airplane.

The two-seat, single-engine, tailwheel-equipped airplane was powered by a Pratt and Whitney, R1830-92, 1,200 horsepower engine. The airplane's airworthiness certificate was issued in March 2011; the airplane had accumulated approximately 85 hours of total flight time. The most recent condition inspection was completed on April 6, 2016, at 77.6 hours total aircraft time. The pilot’s son, who had about 75 hours of flight experience in the accident airplane, stated that the engine consumed about 50 gallons per hour (gph) in cruise flight and 120 gph at a takeoff power setting.

Post-accident examination of the airplane by a Federal Aviation Administration (FAA) inspector revealed that the airplane impacted trees and terrain about 3,500 ft west of the departure end of the runway in a wooded area, about 250 ft from residential buildings. The cockpit, left inboard wing, and right wing were consumed by fire. The outboard portion of the left wing was suspended about 25 ft above the ground in a tree aft of the main wreckage. The empennage exhibited impact and postimpact fire damage. The engine remained attached to the airframe and displayed impact and thermal damage. The reduction gear box and propeller separated from the airframe and was located about 50 ft from the wreckage in a clearing. The propeller exhibited little rotational damage, and one of the three blades was bent slightly aft in a near-feathered position. The propeller dome was crushed on one side. The metal fuel tank was breached during impact, but the fuel sump contained a small amount of liquid consistent with the odor and color of aviation fuel.

The airplane checklist stated that the fuel selector should be selected to the fullest tank for takeoff and that the auxiliary fuel tank should not be used during takeoff or landing. Due to impact and thermal damage, neither the position of the fuel selector valve nor whether the fuel boost pump was on at the time of the accident could be determined.