On April 16, 2026, about 1030 eastern standard time, a Rajchl Vladimir Airplane Swing 06, N613SA, was substantially damaged when it was involved in an accident near O’Brien, Florida. The private pilot was fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. According to a family member, the pilot departed from O’Brien Airpark (FD71), O’Brien, Florida about 1015. She stated that the pilot intended to fly a traffic pattern and return to pick her before departing on a sightseeing flight. She observed the airplane depart to the south and recalled that the engine sounded normal. About 18 minutes after departure, she received a phone call from a neighbor advising that an airplane had crashed near the airport. According to a witness, who was also the property owner where the accident occurred, the airplane was flying northwest about 300 ft above ground level (agl). He observed the airplane briefly but did not continue to watch it because it sounded normal. Shortly thereafter, he heard a popping or flapping noise, which caused him to look back at the airplane. He observed the airplane pitched nose down at about a 45° angle, followed by full nose down attitude, before rotating about 180° and impacting terrain. Following the accident, the witness approached the airplane and could smell fuel, but observed no fire. He further stated that he did not see any parts separate from the airplane before it impacted the ground. The airplane came to rest in an open field on a 304° magnetic heading. All three blades of the composite propeller were liberated from the propeller hub assembly. One blade was found in the impact hole adjacent to the engine and was fractured mid span. A second blade was found 100 ft to the right of the main wreckage and was undamaged. The third blade was found 90 ft to the left of the main wreckage; the tip of the aft blade face was missing, while the back blade tip remained. The blade was split from the face and back surfaces. All three blades exhibited minor rotational scoring signatures. The engine was buried 3 ft in soft soil and was not visible. It remained partially attached to the engine mount and firewall. Fuel consistent with automotive gasoline, was observed dripping from the engine as it was removed from the impact crater. The engine was rotated 720° degrees when force was applied to the crankshaft. Thumb compressions were observed on cylinders 1 and 3. Cylinders 2 and 4 retained air pressure when 5 psi of shop air was applied. Valve train movement was observed on all cylinders, and continuity between the crankshaft and camshaft was confirmed. A borescope examination of the combustion chambers revealed no abnormalities of the intake and exhaust valves, piston domes, or cylinder walls. Fuel was present in the fuel pump and tested negative for water using water detecting paste. The cockpit instrumentation was destroyed by impact forces. The fuselage was crushed and fractured in several locations. The fuel tank was breached, and fuel blighting of the surrounding vegetation was observed. The empennage was located on the right side of the fuselage behind the right wing structure and remained connected to the main wreckage by flight control cables. The horizontal stabilizer was separated from the empennage structure but remained attached by the control cables. Flight control cable continuity of the elevator and the rudder was established from the empennage to the rudder pedals and control yoke. The right wing was partially separated from the fuselage structure, and its leading edge exhibited uniform crush damage. The left wing was separated from the fuselage and was located about 30 ft forward of the main wreckage. The wreckage was retained for further examination.