Drew, MS, USA
N51037
AIR TRACTOR INC AT-602
The pilot stated that the airplane had just been loaded with fertilizer for an aerial application flight and that the fuel tanks were about ¾ full. The last memory he had of the event was the start of the takeoff roll. There were no witnesses to the accident. A ground scar was present along the runway with the left navigation light embedded in the scar. The airplane sustained substantial damage to wings, ailerons, and rudder. Flight control continuity was established from the control stick to the aileron and elevator control surfaces and from the rudder pedals to the rudder. The tailwheel lock was found engaged and a functional test revealed no anomalies. Engine control continuity was established from the power quadrant to the engine and allowed for unrestricted movement of the power lever, propeller control lever, and condition lever. No anomalies or malfunctions were found that would have precluded normal operation. The reason for the loss of control during takeoff could not be determined based on the available information.
On June 4, 2021, about 1625 eastern daylight time, an Air Tractor AT602, N51037, was substantially damaged when it was involved in an accident near Drew, Mississippi. The pilot sustained minor injuries. The airplane was operated as a Title 14 Code of Federal Regulations (CFR) Part 137 aerial application flight. The pilot stated that the airplane had just been loaded with about 4,000 lbs of dry fertilizer for the application flight and that the fuel tanks were about ¾ full (150 gal). The last memory he had of the flight was the start of the takeoff roll. There were no witnesses to the accident. A ground scar was present along the runway with the left navigation light embedded in the scar. The airplane sustained substantial damage to wings, ailerons, and rudder. Flight control continuity was established from the control stick to the aileron and elevator control surfaces and from the rudder pedals to the rudder. The tailwheel lock was found engaged and a functional test revealed no anomalies. Engine control continuity was established from the power quadrant to the engine and allowed for unrestricted movement of the power lever, propeller control lever, and condition lever. The N1 section of the engine was inspected using a borescope and no anomalies were noted. All 5 blades of the propeller were bent aft and the pitch links for the #2 and #3 blades were fractured, consistent with the engine producing power at the time of impact.
A loss of control during takeoff for reasons that could not be determined.
Source: NTSB Aviation Accident Database
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