On December 14, 1996, at 1133 central standard time (cst), a Cessna 170B, N2506C, operated by a solo student pilot, sustained substantial damage when on landing roll, the airplane departed the runway and subsequently nosed over. Visual meteorological conditions prevailed at the time of the accident. The personal flight was being conducted under 14 CFR Part 91. No flight plan was on file. The student pilot reported no injuries. The cross-country flight originated at Mount Comfort, Indiana. In his written statement, the student pilot said the ATIS information at Willard Airport, Savoy, Illinois, called the wind 130 degrees magnetic at 15 knots. On initial contact with the Willard Airport Air Traffic Control Tower, the student pilot informed the tower controller that he was a student pilot and that he was inbound for a full stop landing. The tower controller cleared the student pilot to land on runway 04. On final approach, the student pilot said that he had to use "the wing low with opposite rudder method to a greater degree than I ever used before." On touchdown "the right wing rose to an unacceptable angle. I attempted to lower the wing and stay on the runway, but I lost control of the aircraft." The airplane departed the left side of the runway, "the tires sank causing the aircraft to pitch forward, stopping the engine. The aircraft stood vertical, stopping momentarily, then the wind seemed to blow the airplane over." The Federal Aviation Administration (FAA) inspector who examined the wreckage at the scene found the left wing rear spar bent downward. The inboard bottom surface of the left wing was bent back and buckled outward near the left fuel tank. The bottom wing skin was opened up along the lateral rivet line. The left wing strut was kinked downward in the middle. The right wing was bent aft and downward. The right rear spar was bent slightly downward. There were skin wrinkles in the bottom inboard surface of the right wing near the right fuel tank. The upper forward cabin frame was bent slightly around the cabin door. The vertical stabilizer was crushed downward and buckled outward. The top portion of the rudder was bent over to the left. The rudder counter weight was located on the right side of the vertical stabilizer. Both propeller blades were bent slightly forward. The spinner was crushed to one side. Flight control continuity was confirmed. No anomalies were found with the engine, engine controls, brakes or other airplane systems.