Accident Details
On June 6, 2025, about 1830 central daylight time, an Air Tractor AT-502 airplane, registration N9185F, was substantially damaged when it crashed near Grady, Arkansas. The pilot was fatally injured. The aircraft was being operated as a Title 14 Code of Federal Regulations Part 137 agricultural application flight.
Departure and Ground Marks
The aircraft was departing from a 2,300-foot-long paved airstrip oriented approximately 015°. A track in the grass off the right side of the runway began about 300 feet from the end of the pavement and appeared consistent with being made by the airplane tailwheel. The track was oriented about 025°. After about 200 feet, the single track transitioned to three tracks consistent with all three landing gear wheels being on the ground. These tracks were about 200 feet long and ended about 100 feet beyond the end of the runway pavement, continuing along the approximate 025° heading into an adjacent soybean field. The center track was offset to the right relative to the outer two tracks, consistent with the tail of the airplane being offset as it traveled through the field. An additional set of tracks began again about 50 feet from an irrigation ditch, which was located about 450 feet from the end of the runway pavement.
Airplane Damage and Position
The airplane came to rest inverted on the north side of an irrigation ditch. The outboard left wing was fragmented, and the aft fuselage was partially separated. The engine mount was deformed; however, the engine remained securely attached and appeared undamaged. Engine control continuity was confirmed.
Flight Control Continuity
Aileron control continuity was confirmed from the cockpit control stick to the left-wing pushrod and to the right aileron. The left aileron was separated and fragmented, consistent with the outboard wing damage. Elevator control continuity was confirmed from the cockpit control stick to the elevators; however, the aft elevator pushrod was bent consistent with the fuselage damage. The left rudder cable was separated immediately forward of the rudder control horn, with the separation frayed consistent with an overstress failure. The right rudder cable was continuous from the cockpit rudder pedal to the control horn at the aft fuselage.
Planned Examinations
Further examination of the engine and airframe fuel system is planned. Additionally, a Satloc GPS position tracking unit was retained for examination and data download.