FTW04LA164

The pilot reported that he was starting the 4th load (of 12 loads) when he topped-off the hopper with 1,500 pounds of 46% UREA fertilizer prior to his departure from the 4,000 feet long by 100 feet wide dirt airstrip. During the takeoff roll, as the airplane approached lift-off, the right main landing gear axle and wheel separated from the landing gear strut. The strut "dug" into the runway and separated from the airplane. The pilot further reported that the engine and propeller "dug" into the runway and caused the airplane to nose-over. The airplane came to rest in the inverted position. Examination by the FAA inspector revealed that 2 bolts from the left main landing gear (part number AN 509-616-35 and MS 20008H-22) were fractured. The fractures showed evidence of fatigue. The aircraft was reported having accumulated a total of 11,006 hours since new; however, the time since the installation of the failed bolts could not be established.

On June 17, 2004, approximately 1400 central daylight time, a Grumman G-164A single-engine agricultural airplane, N6567, was substantially damaged following a loss of control during takeoff from an airstrip near Garwood, Texas. The commercial pilot, sole occupant of the aircraft, was not injured. Visual meteorological conditions prevailed, and a flight plan was not filed for the 14 Code of Federal Regulations Part 137 aerial application flight. The flight originated from the operator's private dirt airstrip, near Garwood, Texas.

The pilot reported that he was starting the 4th load (of 12 loads) when he topped-off the hopper with 1,500 pounds of 46% UREA fertilizer prior to his departure from the 4,000 feet long by 100 feet wide dirt airstrip. During the takeoff roll, as the airplane approached lift-off, the right main landing gear axle and wheel separated from the landing gear strut. The strut "dug" into the runway and separated from the airplane. The pilot further reported that the engine and propeller "dug" into the runway and caused the airplane to nose-over. The airplane came to rest in the inverted position.

Examination of the airplane by a Federal Aviation Administration (FAA) inspector, who responded to the accident site, revealed that the upper wings, rudder, and horizontal stabilizer were structurally damaged, the fuselage was wrinkled, the propeller was bent, and the firewall was bent.

Further examination by the FAA inspector revealed that 2 bolts from the left main landing gear (part number AN 509-616-35 and MS 20008H-22) were fractured. The fractures showed evidence of fatigue. The aircraft was reported having accumulated a total of 11,006 hours since new; however, the time since the installation of the failed bolts could not be established.