N7893RBeech V35A · 1969

On October 22, 2022, about 1817 eastern daylight time, a Beech V35A airplane, N7893R, was substantially damaged when it was involved in an accident near Sunbury, Georgia. The pilot was not injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.

According to the pilot, before the flight, he had about 35 gallons of fuel in the left wing’s fuel tank, and an estimated 15 to 20 gallons of fuel in the right wing’s fuel tank. Subsequently, the pilot departed Eagle Neck Airpark (1GA0), Shellman Bluff, Georgia, about 1720 and flew to Brunswick Golden Isles Airport (BQK), Brunswick, Georgia, to practice instrument approaches. After completing two approaches at BQK, he flew back to 1GA0.

After arriving at 1GA0 and entering the traffic pattern, he extended the left downwind leg about 10 miles north of the airport before turning on to a left base leg. The engine then suddenly lost power. The pilot immediately switched fuel tanks with no result. At this point, the airplane’s airspeed was about 120 mph, and it was at 1,500 ft above mean sea level. Having switched tanks and still with no engine power, he moved the throttle, propeller, and mixture controls full forward without result. He then “called mayday” over the radio and had a choice between a forced landing to the Medway River and a marsh. He chose to perform a forced landing to the river, close to the marsh.

He kept the landing gear retracted, and when the airplane touched down on the water, it came to a stop very quickly. After the landing, the pilot stepped out onto the wing and called 911. The airplane was in about six feet of water, and as it settled, the pilot stood on the top of the fuselage with water up to his knees and awaited rescue. About 1 hour later, he was rescued by the United States Coast Guard.

The airplane was recovered from the water two days after the accident and Federal Aviation Administration (FAA) inspectors observed the airplane’s recovery. The right lower wing root displayed crush and compression damage, and the right outboard wing panel was twisted. The left ruddervator was missing a portion of its outboard section; its balance weight had separated from the control surface and was not recovered. The nose landing gear doors, lower engine cowling, and lower fuselage displayed crush and compression damage, and was missing an access panel on the lower fuselage below the passenger cabin. The inspectors did not note the presence of fuel or oil leaking from the airplane. About 1 gallon of fuel was recovered from each of the airplane’s left- and right-wing fuel tanks.

The airplane was subsequently transported to an aircraft recovery facility and examined in detail. The fuel selector was found selected to the left fuel tank, the throttle control was fully open, the mixture control was set to fully rich, and the propeller control was in the high rpm position. The propeller displayed visible aft bending. The fuel tanks remained intact. A trace amount of fuel was recovered from the fuel strainer, and the fuel distribution valve was absent of fuel. The fuel distribution valve screen and fuel injectors were absent of debris or other obstructions. The magnetos were water-damaged and could not be tested.

An engine data monitoring device was recovered from the airplane and its data were downloaded by the NTSB Vehicle Recorders Laboratory. The recovered data included a dataset that correlated to the accident flight, though the unit’s internal clock had not been set accurately; therefore, a correlation of the data to actual time could not be made. The data included cylinder head (CHT) and exhaust gas temperatures (EGT) for each of the engine’s six cylinders, with data for each parameter captured every six seconds. The dataset correlated to the accident flight was 1 hour and 7 minutes long. Rises in CHT and EGT consistent with the application of takeoff power began about 8 minutes into the recording session. About 1 hour and 4 minutes after the beginning of the recording, a sudden increase in EGT of about 100°F for all the engine’s cylinders was observed that persisted over a duration of about 30 seconds. The sudden EGT increase was followed by a rapid decrease in EGT and gradual decrease in CHT that continued for the remaining 3 minutes of the recording, consistent with a loss of engine power.

According to the airplane’s FAA-Approved Airplane Flight Manual, “Maximum usable fuel of each 39 or 40 gal. main tank is 37 gallons.” The fuel selector in the accident airplane had placards for each fuel tank that indicated a capacity of 37 gallons.