On July 14, 2026, sometime between 1252 and 1356 CDT, a Luscombe 8A, N1164K, was substantially damaged when it crashed in a field near Canton, Texas. The pilot, who was the sole occupant, was fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. The flight had originated from the pilot’s private airstrip where the airplane was hangared, which was oriented north to south. A farmer discovered the airplane wreckage about 800 ft northwest of the private airstrip, at about 1356. There were no eyewitnesses to the accident. The pilot sent a text message to a friend at about 1252, which was his last known communication. Additionally, a nearby resident reported hearing what sounded like an engine “winding up” for a few seconds, followed by less than a second of silence, then a “boom” sound. He stated that he heard the sound within the general timeframe of the accident, but he was unable to identify the specific time. The accident pilot purchased the airplane in December 2025. His wife told investigators that the pilot flew the airplane frequently and that they felt it did not produce sufficient take-off performance for them to fly together. She said he usually flew it in the morning or evening and had not flown the airplane much in high-temperature conditions. When she returned home from an appointment at around 1400, she observed the windsock located at the north end of the runway, which indicated the wind was from the north. She noted that the wind had been coming from the south earlier in the day. She said that the pilot typically took off to the south because the prevailing winds were generally from that direction, but on the day of the accident she believed he must have taken off to the north. Figure 1: Overhead map view of accident location The airplane impacted a field in a steep, nose-down attitude about 800 feet northwest of the northern end of the private airstrip. The longitudinal axis of the fuselage was oriented on a heading of about 349° magnetic and exhibited fore-aft crushing. All major structures and components of the airplane were located within the immediate wreckage area. Pieces of windscreen plexiglass were scattered forward and left of the primary wreckage, within about a 30-ft diameter. Disturbance of the surface soil was limited to the area located immediately under the wreckage. Figure 2: Photo of airplane wreckage at accident scene The right wing was displaced aft and the left wing was displaced forward. Compression wrinkling was observed along the top skin of the left wing along with forward bending at the wing root leading edge. The right wing was damaged at the outboard leading edge and the aft spar had separated at the fuselage. Both the left and right ailerons remained attached to their respective wings. The empennage remained intact and attached to the aft fuselage. Both elevators and the rudder also remained attached. The elevator trim tab was connected to the left elevator and articulated freely by hand. The upper fuselage had collapsed into the cabin. The propeller remained attached to the engine crank flange. One blade was intact and exhibited no chordwise scratches or damage. The second blade was fractured and splintered near the blade root with aft bending.