On October 17, 2003, at approximately 1530 central daylight time, a Beech 65-A90 twin-engine airplane, N511BF, was destroyed during a forced landing following a loss of engine power near Fentress, Texas. The commercial pilot, sole occupant of the airplane, sustained minor injuries. The airplane was registered to American Aircraft Sales International, of Venice, Florida; and operated by Sky Dive San Marcos, of San Marcos, Texas. Visual metrological conditions prevailed, and a flight plan was not filed for the 14 Code of Federal Regulations Part 91 sky diving flight. The flight originated from Fentress Airpark (XS90), near Fentress, Texas, about 30 minutes prior to the accident. The 1,127-hour pilot reported to the FAA inspector, who responded to the site, that all systems appeared to be running normally throughout the flight from takeoff until releasing jumpers from 14,000 feet and throughout most of the descent. After the jumpers were out of the airplane, he set the torque levers to idle, retracted flaps, and then set the propeller to 1,800 RPM. He began his descent towards Fentress Airpark. As the flight approached the airport, the pilot set the flaps to approach setting, and extended the landing gear, then verified "three green" on the pedestal. After looking up from the pedestal, he noticed the annunciator panel flashing and indicating a malfunction of the right engine generator. No other annunciator lights were observed to be illuminated. The engine did not appear to be producing any torque. He then began the emergency engine out procedures, and began looking for a field to land in. The pilot attempted to restart the engine, turning the starter-generator on and advancing the condition lever. White smoke began to come out from the cowling, and at that time he shut-off the fuel and turned the starter-generator off. The airplane impacted the ground on a northerly heading with the flaps and landing gear retracted. The airplane swung around facing a southeast direction, and struck a tree. After the pilot ran from the accident site, he observed the right engine nacelle engulfed in flames, which then spread to the fuselage. Review of the engine logbook revealed the engine was being operated in excess of 1,000 hours beyond the manufacturer's recommended time between overhauls of 3,600 hours. Examination of the engine was conducted with assistance from a representative from the engine manufacturer. The engine displayed severe fire damage, including partial fire consumption of the accessory gearbox. All of the external housings displayed fire and heat damage. Control continuity was verified. There were no indications of operational distress in the compressor, combustion, and turbine sections. Fire and heat damage to the recovered controls and accessories precluded further evaluation. The engine fuel control was consumed by fire; therefore, precluding any assessment of the area. No anomalies were found on the engine that would have prevented normal operations.