N6036UBeech A36 · 1979

On June 13, 2010, about 1800 central daylight time, a Beech A36, N6036U, was destroyed when it impacted terrain near Lidderdale, Iowa. The airplane was registered to OK Flying LLC., and was being operated by a private pilot under the provisions of 14 Code of Federal Regulations Part 91 as a personal flight. Visual meteorological conditions existed at the surface with instrument conditions at 1,100 feet above ground level (agl). No flight plan was filed. The private pilot and his passenger were fatally injured. The flight departed from the Algona Municipal Airport (AXA), Algona, Iowa, at an unconfirmed time, and was destined for the Lamar Municipal Airport (LLU), Lamar, Missouri.

At 0556 on the day of the accident, the pilot contacted the Fort Worth Automated Flight Service Station (AFSS) and obtained a weather briefing for a proposed visual flight rules (VFR) flight from AXA to LLU. The briefer informed the pilot of widespread areas of instrument conditions along the route of flight. He provided forecast information for the route including convective activity and that an airmen's meteorological information bulletin (AIRMET) for instrument flight rules (IFR) conditions existed for portions of the proposed flight. At the conclusion of the call, the pilot stated that he would call back at a later time for updated weather information.

At 1403, the pilot contacted the Washington AFSS and again obtained weather information for a VFR flight from AXA to LLU. The pilot was informed of an AIRMET for instrument conditions at the departure airport and an area encompassing the western half of the state of Iowa. The AIRMET was valid until 2200. The briefer also informed the pilot of convective activity along the route of flight. At the conclusion of the call the pilot again stated that he would call back at a later time for updated weather information.

At 1634, the pilot contacted the Fort Worth AFSS and again obtained weather information for a VFR flight from AXA to LLU. The pilot stated to the briefer that he could see gaps in the clouds at AXA. The briefer advised the pilot that marginal VFR conditions existed for most of the proposed route of flight but there were still areas with instrument flight rules (IFR) conditions along the route. The briefer informed the pilot that VFR flight was not recommended.

The airplane impacted the ground about 62 nautical miles (nm) south-southwest of the departure airport. The destination airport was about 280 nm south of the accident site.

The pilot held a private pilot certificate, issued in August, 2003, with an airplane single engine land rating. He did not have an instrument rating. His most recent third class airman medical certificate was issued on January 26, 2010. The medical certificate listed a limitation that the pilot wear corrective lenses. The pilot's flight logbook was not recovered during the investigation. The pilot reported having 900 hours of flight experience on his most recent airman medical certificate application.

The airplane was a 1979 Beechcraft model A36, serial number E-1422. It was a single-engine, low-wing monoplane configured to seat 6 occupants including the pilot. The airplane had a retractable tricycle landing gear and was constructed predominately of aluminum. The airplane was powered by a Continental IO-550-B engine, serial number 296794-P. The engine was rated to produce 300 horsepower. The airplane logbooks were not recovered during the investigation.

At 1800, the weather conditions at the Arthur N Neu Airport, Carroll, Iowa, located about 4 nm south of the accident site were recorded as: Wind 20 degrees at 8 knots; 10 miles visibility; overcast ceiling at 1,100 feet agl; temperature 68 degrees Fahrenheit; dew point 62 degrees Fahrenheit; altimeter setting 29.99 inches of mercury.

The airplane wreckage was distributed along a path from the initial impact point in a corn field continuing across a road into another farm field. Fuel blight was evident on the crops two days after the accident. Portions of all major components of the airplane were identified within the wreckage path. The airplane was severely fragmented with various pieces and components distributed over a wide area fanning from the initial impact point. The overall length of the wreckage path was about 1,000 feet in length from the initial impact point to the engine which had separated from the airframe. There was a T-shaped ground scar/depression at the initial impact point with dimensions similar to the overall airplane dimensions. Green fragments of glass consistent with the right navigation light lens was found near the right side of the T-shaped impact scar, consistent with an upright orientation at impact.

The fuselage was fragmented and the cabin section was crushed. The aft fuselage and empennage came to rest adjacent to the remains of the cabin. The vertical stabilizer and the left horizontal stabilizer remained attached to the aft fuselage. The rudder remained attached to the vertical stabilizer. The inboard half of the left elevator, including the trim tab remained attached to the left horizontal stabilizer. The right horizontal stabilizer and elevator were separated. The right elevator remained attached to the right horizontal stabilizer. Both wings were fragmented. The outboard portion of the left wing from the tip to the inboard end of the aileron was separated from the remainder of the left wing. The left aileron remained attached. The left flap was separated from the left wing. The right wing was separated from the rest of the airplane. The wing was crushed and the wing skins were torn open exposing the internal wing structure. The right flap and aileron were separated from the wing

The propeller flange was separated from the crankshaft and remained attached to the propeller hub. All three propeller blade shanks remained attached to the hub. One blade was separated from its shank just outside of the hub. The other two blades exhibited bending and twisting.

The engine was separated from the airplane. Both magnetos were separated from the engine. One magneto was located and produced spark on all leads when rotated by hand. All six cylinders remained attached to the engine. The lower portion of the crankcase, including the oil pan was separated from the remainder of the engine. Valve train continuity was established by visual inspection of the exposed gears.

Examination of the airplane did not reveal any anomalies with regard to the airplane, engine, or systems.

An autopsy was performed on the pilot at the Iowa Office of the State Medical Examiner in Ankeny, Iowa. The cause of death was attributed to multiple blunt force injuries.

A Final Forensic Toxicology Fatal accident report was prepared by the Federal Aviation Administration Civil Aerospace Medical Institute. The reported findings were:

27 (mg/dL, mg/hg) ETHANOL detected in Muscle