N4505ZPiper PA-22-108 · 1960

On January 3, 2014, at 1949 central standard time, a Piper model PA-22-108 airplane, N4505Z, was substantially damaged during a forced landing near Forsyth, Missouri. The pilot and passenger were not injured. The airplane was registered to and operated by the pilot, under the provisions of 14 Code of Federal Regulations Part 91, without a flight plan. Night visual meteorological conditions prevailed for the cross-country flight, which departed Sullivan Regional Airport (UUV), Sullivan, Missouri, at 1700 and was en route to M. Graham Clark Downtown Airport (PLK), Branson, Missouri.

The pilot reported that the mixture control cable had fractured during a previous flight, and to continue on his cross-country trip he safety-wired the carburetor mixture control arm in the full-rich position. Fueling records, obtained from the airport management at UUV, indicated that the airplane had been fueled with 11.49 gallons of Avgas at 1630. The pilot stated that he flew at a cruise altitude between 2,500 and 3,000 feet mean sea level (msl) to the intended destination. However, while en route, he decided to make an unplanned stop at Ava Bill Martin Memorial Airport (AVO) to use the restroom facility. The pilot estimated that the duration of the ground stop was 15-30 minutes before the flight had departed again for PLK.

The pilot reported that while in cruise flight about 8 miles northeast of PLK, between 2,500 and 3,000 feet msl, the airplane suddenly experienced a total loss of engine power and the propeller began to windmill. The engine did not restart after he verified that the magneto switch and fuel selector were both on. He stated that his attention was then focused on finding a suitable area to perform a forced landing. The nearby roads contained curves and the surrounding terrain was hilly, so he decided to ditch the airplane in Bull Shoals Lake, located near Forsyth, Missouri. After landing in the lake, he and his passenger were able to swim to the shoreline where they were treated by first responders for symptoms of hypothermia. The pilot and his passenger were not physically injured during the accident. The airplane sunk following the ditching and remained submerged for nearly one week before it was recovered. Upon recovery from the lake, the airplane exhibited substantial damage to the engine firewall.

A postaccident examination of the wreckage established that there were no mechanical discontinuities within the engine drivetrain, valve train, or the accessory section. All four cylinders produced compression/suction while the engine crankshaft was rotated. The mixture control cable was found broken, and the carburetor mixture control arm was found safety-wired in the full-rich position. Both magneto assemblies exhibited water contamination and were allowed to air dry over a period of two days. After being air dried, both magnetos provided spark through each ignition lead wire to its respective spark plug. No fuel was located in the airplane fuel system; however, the airplane had been submerged in water for nearly one week.

A direct flight from UUV to PLK is 158.6 statute miles on a 226 degree true course. The pilot reported that the airplane typically achieved a cruise speed between 105-115 miles per hour (mph) while at a cruise altitude of 2,500-3,000 feet msl. Without any wind considerations, the non-stop direct flight between UUV and PLK would have taken between 1 hour 23 minutes and 1 hour 31 minutes, at 115 mph and 105 mph respectively. However, upper atmosphere wind modeling suggested that the wind aloft averaged 45 mph from 195 degrees at the cruise altitudes used during the accident flight.

According to the Piper PA-22-108 Owner's Handbook performance charts, at 3,000 feet msl and 75-percent engine power, the fuel consumption rate would be 7.8 gallons per hour (full-rich mixture) at a true airspeed of 112 mph. At 3,000 feet and 65-percent engine power, the fuel consumption rate would be 7.2 gallons per hour (full-rich mixture) at a true airspeed of 104 mph.

Performance calculations established that with the expected wind aloft, the non-stop direct flight, at 75-percent engine power, would have taken 2 hours and 14 minutes at a ground speed of 71 mph and used 17.4 gallons of fuel. That same flight, completed at 65-percent engine power, would have taken 2 hours and 31 minutes at a ground speed of 63 mph and used 18.125 gallons of fuel.

The accident airplane was equipped with a single 18 gallon fuel tank, of which 16.875 gallons were considered usable. The airplane landing gear configuration had been modified from a tricycle assembly into a conventional tail wheel; however, there was no available flight data to indicate how the lack of a nose gear would affect the airplane's overall cruise performance.

The pilot reported that he had completed flight planning calculations before departing on the accident flight; however, the actual paperwork that he used was lost and/or destroyed during accident. The pilot stated that the upper wind models that he was provided during the accident investigation were significantly higher than what he remembered planning for. Additionally, the pilot reported that he completed the accident flight at an engine speed of 2,250 rpm, which according to available performance charts was less than 65-percent engine power. Furthermore, the available cruise performance charts lacked true airspeed and engine speed data below 65-percent engine power.