CEN24LA107

Shortly after takeoff, when the airplane was about 200 to 400 ft above the runway, the engine started popping and misfiring and then lost power. The pilot performed a forced landing to wet grass with standing water, during which the airplane flipped over and came to rest upright. The airplane sustained substantial damage to the left wing and empennage. Postaccident examination revealed 15 gallons of fuel in the fuselage fuel tank and continuity of the fuel system. Impact damage precluded an engine run. The examination of the fuel-injected engine and fuel system did not reveal any preimpact mechanical malfunctions or failures that would have resulted in a misfire or loss of engine power. The reason for the loss of engine power could not be determined.

On February 3, 2024, about 1430 central standard time, an Edge 540 airplane, N321JA, sustained substantial damage when it was involved in an accident near La Porte, Texas. The pilot was not injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. The pilot reported that after a normal runup, she took off from unway 30 at La Porte Municipal Airport (T41), La Porte, Texas. Engine power was normal during the takeoff roll and liftoff. About midfield and 200 to 400 ft above the runway, the engine started to make loud popping noises and lost power. Multiple witnesses at the airport reported hearing the engine popping and misfiring. One witness reported that the engine lost power. The pilot maneuvered the airplane toward a grassy area . Upon touchdown, the airplane flipped over and came to rest upright. The airplane sustained substantial damage to the left wing, horizontal stabilizer, vertical stabilizer, rudder, and elevator. Postaccident examination revealed that there was about 15 gallons of fuel inside the fuselage tank; however, both main wing fuel tanks were empty. The fuel selector valve was selected to the fuselage tank. The pilot reported that she often operated with the two main wing tanks empty to help with airplane center of gravity while performing aerobatic maneuvers. The fuel tanks were not compromised. Impact damage to the engine and propeller precluded an engine run. Continuity of the fuel lines was confirmed from the fuselage fuel tank to the flow divider on the engine. Both the electric pump and engine-driven fuel pump moved fuel through the system as designed. Engine continuity was confirmed when the engine crankshaft was rotated through at the propeller. The right magneto produced a spark through each ignition harness lead. The left magneto was impact separated but produced a spark through each lead when tested by hand. The examination of the engine and fuel system revealed no preimpact mechanical malfunctions or failures that would have precluded normal operation.