WPR24LA281 · Evektor-Aerotechnik A S HARMONY LSA

Shortly after takeoff, the airplane was about 200-300 ft above ground level, the engine lost power. The pilot landed the airplane back on the runway near the departure end and subsequently overran the end of the runway. Shortly thereafter, the right wing struck a shrub and the left main landing gear struck a large rock and sheared off, resulting in substantial damage. The airplane came to rest upright about 600 ft from the departure end of the runway. Postaccident examination revealed no evidence of failures or malfunctions that would have resulted in the loss of engine power. About 6 gallons of fuel were drained from the right tank and about 2 gallons of fuel were drained from the left tank. According to the airplane Pilot’s Operating Handbook, each fuel tank contained 0.25 gallons of unusable fuel. During the examination, with the left wing slightly lowered, fuel from the left tank was unable to be pumped to the engine, even though the level was above the unusable fuel amount. However, the pilot stated that he had the right fuel tank selected, and fuel continuity to the engine was established with it during postaccident examination; therefore, the low fuel level in the left tank should not have been a factor. According to the airframe manufacturer, the airplane’s unusable fuel was tested in accordance with Light Sport Aircraft (LSA) category and European Union Aviation Safety Agency (EASA) standards. Downloaded engine control unit data revealed that, shortly after takeoff, a rapid decrease in the fuel flow and fuel injection mass for each cylinder preceded the decrease of the other engine parameters until shutdown, consistent with fuel starvation. Furthermore, about 5 minutes after the accident, the pilot restarted the engine and ran it for about 30 seconds. Running the engine successfully after the accident likely compromised evidence of what caused the engine failure.

Verbatim NTSB analysis and probable cause from the NTSB dataset