DEN08LA090

According to the pilot, he was performing a fly-over with another airplane when the engine lost power. The pilot was able to restart the engine; however, it lost power shortly thereafter. The pilot performed a forced landing to the west in an open alfalfa field. The airplane impacted several ditches resulting in substantial damage to the airplane. A postimpact fire ensued, destroying the airplane. Due to the fire damage to the engine, the reason for power loss could not be determined.

On May 17, 2008, at 1155 mountain daylight time, a DeHavilland DH112 Venom, N21MJ, operated by an airline transport pilot, was destroyed when it impacted an irrigation ditch during a forced landing 1.5 miles northwest of the Platte Valley Airpark (18V), Hudson, Colorado. A postimpact fire ensued. Visual meteorological conditions prevailed at the time of the accident. The flight was being operated under the provisions of Title 14 Code of Federal Regulations Part 91 without a flight plan. The pilot was not injured. The round-robin flight departed Rocky Mountain Metropolitan Airport (BJC), Denver, Colorado, approximately 1130. According to the pilot, he was performing a fly-over with another airplane at the Platte Valley Airpark Fly-In. The pilot stated that as he pitched up to climb the engine lost power. The pilot was able to restart the engine; however, it lost power "about five seconds" later. The pilot performed a forced landing to the west in an open alfalfa field. The airplane traveled over two irrigation ditches, and impacted a third ditch. The right main landing gear collapsed. The airplane came to rest 2,630 feet west of the initial landing point. The belly of the fuselage and cabin area was torn and fragmented. Both main landing gear crushed up into the wing, the right auxiliary fuel tank separated partially, and both wing spars were bent. The post impact fire consumed a large portion of the fuselage, engine, and cabin area. The wreckage was recovered and relocated to a hangar in Greeley, Colorado. Examination of the engine revealed that the accessory housing, compressor, housing, and several burner cans were charred, melted, and partially consumed by fire. The driveshaft, turbine, and aft portion of the housing were continuous and unremarkable. The engine accessories, to include both fuel pumps, were charred, melted, and partially consumed by fire. Due to the fire damage, engine continuity or engine accessory functionality could not be confirmed.