NTSB Narrative Summary Released at Completion of Accident
On July 1, 2014, about 1730 central daylight time, an Air Tractor AT-602, N91331, operated by Shannon Agricultural Flying, Inc., was destroyed when it impacted a bean field in Clarksburg, Mississippi. The commercial pilot was fatally injured. Visual meteorological conditions prevailed, and the airplane, which departed Shannon Field (02CD), Clarksdale, Mississippi, was not operating on a flight plan. The local aerial application flight was conducted under the provisions of 14 Code of Federal Regulations Part 137.
According to company personnel and GPS data, the airplane was applying fertilizer in both directions in an east-west race track pattern. After completing each leg, the airplane would make a 20- to 30-degree left turn, followed by a right turn to reverse course and fly the next track. The GPS data ended prior to the final turn.
A witness on his lawn mower noted the airplane when it flew over his property about 150 feet above the ground. He heard the airplane's engine running over the sound of the mower, and saw the airplane turn right, to the north, and the wings become vertical. The airplane then impacted the ground, and when it did, the witness saw smoke and fertilizer being ejected up into air. The witness then went to the wreckage and found the pilot unresponsive.
The initial impact occurred on flat terrain in the vicinity of 34 degrees north, 06.34 minutes north latitude, 090 degrees, 34.26 minutes west longitude, at an elevation of about 160 feet. The wreckage path, which began with green lens material, headed about 360 degrees magnetic. Approximately 75 feet beyond the initial impact point, there was a 3-foot-deep, 10-foot-long crater with the propeller hub and four of the five propeller blades partially embedded at its right edge. Beginning about 20 feet beyond the crater, was the fifth propeller blade and the rest of the airplane.
The airplane was fractured into multiple sections and pieces, with all flight control surfaces located at the scene. Flight control continuity was confirmed via the control cables from the cockpit to the rudder and elevator, and through push rod and bellcrank fractures to the ailerons.
After the airplane's removal to a storage facility, the engine was partially disassembled. Soil was found in the gas generator case and throughout the combustion section, the compressor turbine blade tips exhibited smearing and the turbine shroud exhibited corresponding circumferential rubbing, and the compressor disc outer rim and blade platforms exhibited circumferential rubbing with frictional heat discoloration and material in the vicinity of the 1st stage power turbine vane ring and baffle, all of which was consistent with the engine being under power at impact.
One of the five propeller blades exhibited torsional bending, and two blades remaining in the hub left witness marks consistent with propeller pitch being in "the normal operating range" and not feathered.