On February 17, 2005, approximately 0720 mountain standard time, a Cessna P210N single-engine airplane, N4912K, sustained substantial damage during a forced landing following a loss of engine power during initial takeoff climb from Hunt Field Airport, near Lander, Wyoming. The private pilot, who was the sole occupant, was not injured. The airplane was registered to Avtrans Leasing, L.L.C., Lander, Wyoming, and operated by the pilot. Visual meteorological conditions prevailed, and an instrument flight rules (IFR) flight plan was filed for the Title 14 Code of Federal Regulations Part 91 personal flight. The flight was originating from Hunt Field Airport at the time of the accident and was destined for Worland, Wyoming. According to the pilot, prior to takeoff, the fuel tanks were topped off with fuel. The pilot completed a "normal" preflight and engine run-up prior to departure from runway 3. During the initial takeoff climb approximately 500 feet agl, the engine lost power. The pilot executed a left turn and attempted a forced landing to the airport. Subsequently, the airplane impacted terrain and came to rest upright on a municipal golf course. Examination of the airplane by a Federal Aviation Administration inspector who responded to the accident site revealed the right wing was buckled, the left wing tip was buckled, the main landing gear was collapsed, and the propeller blades were bent aft. The fuel selector was observed in the RIGHT fuel tank position. The airplane was recovered to a secure hangar at Hunt Field Airport for further examination. A review of the engine maintenance records revealed the number 4 cylinder was removed and replaced due to a leaking exhaust valve on February 2, 2004, at 433.7 hours since major overhaul. On November 1, 2004, the engine underwent its most recent 100 hour inspection at a 393.7 hours since major overhaul. On March 21, 2005, under the supervision of a FAA inspector, the airframe and engine were examined in a hangar at Hunt Field Airport. According to the inspector, engine continuity was established from the crankshaft to the valve train and accessory gears when the crankshaft was rotated by hand. Thumb compression was noted on all cylinders. Fuel was found in the fuel lines from the tank to the engine. The gasculator and filter screen were clear of contaminants and the fuel system vent lines were found open. No anomalies were noted with the engine or airframe that would have precluded normal operation. The reason for the loss of engine power was not determined.