Accident Sequence
The airplane sustained damage when it nosed over after striking a road embankment during a forced landing. The forced landing was necessitated by a complete loss of engine power.
According to the pilot, the flight had been conducted at a cruise power setting of 22 inches of manifold pressure and 2,350 RPM. He reported that he had not yet initiated a fuel transfer from the auxiliary fuel tanks to the main tanks. The aircraft's fuel system is designed such that auxiliary tank fuel is first transferred to the main tanks, which then supply the engine.
The airplane was equipped with a Supplemental Type Certificate (STC) engine conversion. A representative of the company holding the STC stated that at power settings between 22 and 23 inches of manifold pressure and 2,300 RPM, the engine typically consumes approximately 13 gallons of fuel per hour. The main fuel tanks have a combined capacity of 60 gallons, of which 55 gallons are useable.
Post-Accident Fuel Quantities
After the accident, the main fuel tanks were found to contain a combined total of only 1/2 gallon of fuel. In contrast, the auxiliary fuel tanks held a combined total of 14 gallons. The pilot stated that at the moment the engine ceased producing power, both fuel quantity gauges indicated a reading of one-quarter full.