N262KTS D Martin STALLION · 2019

On March 13, 2022, at 1500 eastern daylight time, an experimental, amateur-built Aircraft Designs Inc. Stallion airplane, N262KT, was substantially damaged when it was involved in an accident in Ridgeland, South Carolina. The pilot was not injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 flight test flight.

The pilot reported that the accident flight was the airplane’s 5th flight during phase 1 flight testing for the experimental amateur-built airworthiness certificate. During the takeoff roll on runway 18 at the Ridgeland Claude Dean Airport (3J1), Ridgeland, South Carolina, he noticed an amber caution message for high voltage on the electronic flight instrumentation system. He elected to continue the takeoff and at an altitude of about 50 ft above ground level, when he raised the landing gear, the engine immediately lost all power. He moved the landing gear handle back to the “down” position, deployed the flaps, and performed a forced landing straight ahead into an open field. After a landing roll of about 100 yards, the airplane yawed to the right about 90°.

Examination of the wreckage by a Federal Aviation Administration inspector revealed that the airplane sustained substantial damage to the lower fuselage structure.

The pilot further reported that after the accident, he found the primary alternator field circuit breaker in the open position. Both batteries (one on the airframe electrical bus, the other on the engine electrical bus) retained some power. The engine electrical bus had power when activated by its independent switch; however, neither of the electric fuel pumps would operate, though they appeared to draw some current.

According to the pilot, the engine was equipped with a Simple Digital System electronic fuel injection and ignition system. The system was powered by a dedicated 12 volt engine electrical bus, which included a backup battery and dual redundant electric fuel pumps. The system required an estimated 24 amps to operate.

The engine electrical bus received its power from the 28 volt airframe bus, through a DC-DC converter. The engine was equipped with a primary 60-amp alternator and a backup 20-amp alternator, both of which were connected to the airframe electrical bus.

The airplane was also equipped with an electric/hydraulic power pack that provided hydraulic pressure to operate the retractable landing gear. The electric motor required about 40-42 amps at startup and about 20-22 amps when running.