N93725Wolseley Motors SE5-A · 2008

The accident occurred during a test flight after the airplane had been repaired from a previous accident. The experimental amateur-built airplane was a reproduction of a WWI British bi-wing fighter that was in production from 1916-1918. The pilot noted that the purpose of the flight was to obtain airborne fuel burn data and to further calibrate the airplane's electric fuel quantity gauge. The airplane's fuel tanks had been filled and drained several times during his previous attempts to calibrate the fuel quantity gauge. The piloted noted that the last time the airplane had been serviced with fuel was 5 days before the accident. He stated that while on initial climb from runway 14 (5,502 by 100 feet, asphalt), about 60 feet above the ground, the airplane experienced a total loss of engine power. The pilot reported that the airplane stalled as he attempted to restart the engine. The airplane impacted terrain about 60 feet west of the runway, approximately 2/3 down the length of the runway. The right upper and lower wings, the left lower wing, and the forward fuselage primary structure were substantially damaged. A postaccident inspection found no evidence of any useable fuel in the airplane's four fuel tanks. Additionally, there was no evidence of a fuel spill at the accident site. The pilot reported that there were no preimpact mechanical malfunctions or failures that would have precluded normal operation of the airplane or its engine. He also stated that the accident could have been prevented if he had focused on landing the airplane on the remaining runway, instead of attempting to restart the engine.

The accident occurred during the second flight since manufacture/certification. The experimental amateur built airplane was a reproduction of a WWI British fighter that was in production 1916-1918. On the first flight, the pilot noted that forward stick pressure was needed to maintain level flight. The pilot/builder subsequently adjusted the horizontal stabilizer to increase the nose-down flight characteristics. On the second flight, the pilot stated that the takeoff was normal but the airplane had a lower rate-of-climb and airspeed than the first flight. Upon reaching 2,000 feet, the pilot reduced engine power and noted having normal stick pressure to maintain a level flight attitude, but a 10 mph drop in airspeed and 100 feet per minute descent rate. The airspeed and altitude continued to decrease as he turned to the left. An increase in engine power did not result in an increase in airspeed or reduction of the descent rate. The pilot stated that the airplane continued to loose airspeed and altitude until about 30-40 feet about ground level when the right wing dropped and the airplane impacted terrain. The original airplane design incorporated an engine installation with a zero degree engine thrust angle. The accident airplane incorporated a different engine that resulted in a -12 degree engine thrust angle. The pilot/builder was unaware of the thrust angle differences until after the accident flight.