ATL95LA048

The aircraft was being flown on the first flight after being painted. The pilot reported that during cruise flight, the engine quit. He was unable to glide to the nearest airport, and the airplane was force landed in a field. Post-accident examination of the fuel system revealed about 3 ounces of water in the fuel gascolator, and the fuel line from the fuel tank selector to the gascolator was filled with water. After the accident, the engine ran normally in a test cell; no evidence of mechanical failure or malfunction was observed.

On February 9, 1995, at 1224 central standard time, a Cessna T210G, N6854R, collided with terrain during a forced landing near Covington, Tennessee. The airline transport pilot had minor injuries, and the aircraft was substantially damaged. The aircraft was operated under the provisions of 14 CFR Part 91 by the pilot. Visual meteorological conditions existed at the time, and no flight plan was filed for the personal flight. The flight originated in Covington, Tennessee at an undetermined time.

The pilot was flying the aircraft immediately after the aircraft exterior had been painted. During cruise flight, the engine lost power. Unable to make the airport, the aircraft was landed in a field, about 7 miles southwest of the Covington Municipal Airport. During the forced landing, the aircraft sustained structural damage.

The wreckage was examined following the accident by an inspector from the Federal Aviation Administration. He reported that the wing fuel tanks were ruptured during the ground impact, which prevented the determination of fuel tank quantity and contamination. The fuel gascolator was opened, and contained about 3 ounces of water. The fuel line to the gascolator was completely filled with water, with no evidence of fuel present.

The engine was crated and shipped to the manufacturer's facility for an inspection. The engine was installed in a test cell, and prepared for a test run. Due to impact damage, the turbocharger was not installed for the test run. A fuel pressure line fitting was replaced due to impact damage. The engine started on the first attempt, with about one revolution of the propeller. The engine was run at a peak rpm of about 2,700, with a corresponding fuel flow of 167 pounds per hour. The engine driven fuel pump and magnetos functioned normally. The engine ran smoothly at idle rpm, and transitioned smoothly to full throttle rpm. After several minutes of operation, the test run was concluded.