Accident Overview
On 4 September 2016, at approximately 17:07 local time, a Van's RV-6A aircraft, registration SP-YUT, crashed in Wrocanka near Krosno, Poland. The aircraft was operated by a private owner and was on a training flight in the vicinity of Krosno Airport (EPKR). Both occupants—the pilot and a passenger—sustained fatal injuries. The aircraft was destroyed by fire.
Flight and Conditions
The flight was conducted under visual flight rules (VFR) in daylight. Weather conditions at the time included a southerly wind with an average speed of 4.4 m/s (max gust 9.5 m/s) and turbulence. The Polish State Commission for Aircraft Accident Investigation noted that weather could have had an influence on the accident.
Sequence of Events
The pilot arrived at the airport at about 16:50, spoke with an instructor, and announced his intention to perform several flights. After preparing the aircraft, the pilot and passenger took off from runway 16 around 17:00 and flew south of the airport. About two minutes into the flight, the pilot reported being south of the airport at an altitude of approximately 200 meters. The aircraft then executed a steep left bank, reaching about 80° and then 90°. The commission determined that the aircraft entered a rotor, was dynamically stalled, and entered the first phase of a left spin (possibly flat). The aircraft struck the ground at an angle of about 37° with no ground roll. Fuel tanks ruptured, and a fire ensued.
Aircraft and Pilot Information
The Van's RV-6A is a two-seat, single-engine, low-wing aircraft with metal semi-monocoque construction. It was registered in the Special category. The aircraft's documentation showed a valid registration and permit to fly. The pilot held a private pilot license (PPL(A)) and a glider pilot license, with an estimated total flight time of about 400 hours, including 55.5 hours on the RV-6. Recent flying time was low (13.5 hours in the period from July 2015 to May 2016). The pilot was described by other pilots as preferring very gentle flying and avoiding simulated emergency maneuvers during instruction.
Damage and Injuries
The aircraft was totally destroyed by impact and fire. Both occupants died at the scene. Autopsy found no alcohol in the pilot's blood.
Analysis Findings
The commission established that the aircraft's maximum takeoff weight of 748 kg was exceeded by 62 kg, but this did not directly influence the accident. Control continuity was verified until impact. The control stick was found deflected to the right, and the engine was running at impact. The aircraft's stall characteristics are abrupt, with rapid autorotation. The steep turn at low altitude and in turbulent conditions likely led to a stall and subsequent spin from which recovery was not possible.