Accident Overview
On August 24, 2025, at approximately 1926 central daylight time, a Rans S-12 Airaile airplane, registration N2757A, was substantially damaged in an accident near Concordia, Kansas. The pilot, the sole occupant, was fatally injured. The flight was conducted under Title 14 Code of Federal Regulations Part 91 as a personal flight.
Witness and Video Evidence
A witness reported that the airplane appeared to have trouble gaining altitude and alternated between slight climbs and descents while flying east. The airplane then turned south and entered a nose-down spiral descent to the ground. The same witness captured a cellphone video of the airplane’s final moments. Preliminary review of the video revealed audio evidence of the engine operating as the airplane entered a progressively steeper left turn toward the east. As the left bank angle increased, the airplane adopted a steep nose-down pitch attitude and continued in a spiraling descent. An abrupt reduction in engine noise occurred after the airplane entered the steep spiraling descent from low altitude.
Aircraft and Inspection History
According to FAA documentation, the experimental light sport airplane was issued a special airworthiness certificate on November 9, 2007, with the application noting original manufacture in 1995. At the time of the accident, the hour meter indicated 767.2 hours. Maintenance logbooks were not located at the accident site or in the pilot’s two hangars at Blosser Municipal Airport in Concordia, Kansas.
Wreckage and Impact
The wreckage came to rest at the edge of a soybean field and a residential backyard, under power lines that were undamaged. The nose was oriented east. All major structural components and flight controls were identified. The fuselage and both wings exhibited substantial impact damage; the forward fuselage and nose cone fragmented upon terrain impact. The steel-tube fuselage showed multiple fractures and bends consistent with impact. The instrument panel was fractured with several instruments separated. Both seats sustained impact damage. The empennage remained attached to the tubular tailboom, and the vertical and horizontal stabilizers appeared undamaged. The elevator, rudder, and pitch trim tab remained attached to their hinges; similarly, ailerons and flaps remained attached.
Flight Control and Engine Examination
Postaccident examination revealed no evidence of flight control system component failure. Rudder control cable continuity was confirmed from pedals to rudder horn. Elevator control push/pull tube continuity was confirmed, with a 90° upward bend and fractured rod end consistent with impact. Aileron and flap cable continuity were confirmed; flaps were fully retracted. Each wing had a 5-gallon fuel tank with ample fuel. The fuel odor was consistent with auto-fuel, and a light blue coloration indicated 2-cycle engine oil premix. Fuel was present in lines to the carburetors.
The engine remained attached to its mounts with no crankcase or cylinder fractures, and no evidence of coolant, fuel, or oil leaks. Exhaust was attached. Both carburetors remained attached and contained residual fuel with no contamination. Throttle and choke cables were continuous. Examination found no mechanical failure in the carburetors. Internal engine drivetrain continuity was confirmed; the crankshaft rotated freely and via starter. Cylinder compression and suction were confirmed. The rotating valve was undamaged and functioned normally with no evidence of oil starvation or seizure. Cylinder walls, piston domes, and skirts showed normal operation features. A foreign object debris damage mark on the power-takeoff side of the cylinder head was consistent with a previous piston failure event, as evidenced by carbon deposits, but the PTO piston and cylinder were undamaged. The magneto-side was undamaged. Residual coolant was present around cylinders, and the coolant expansion container contained coolant. The injection oiler contained a light gray fluid consistent with water-contaminated oil, but no thermal distress or seizure was observed in oil-lubricated components. Four sparkplugs exhibited normal operation features with no mechanical damage. The dual-ignition system was not functionally tested.
The propeller hub remained attached to the reduction gearbox. Carbon-composite propeller blades fractured about 12 inches from the blade grips, consistent with engine operation at impact. Three fractured blades were located 24 ft at 095°, 81 ft at 030°, and 86 ft at 360° true from the main wreckage.
Conclusion
The examination of the airplane, engine, and propeller revealed no evidence of a preimpact mechanical malfunction or failure that would have prevented normal operation.