20070819021749A

(-23) At approximately 0930 on August 19, 2007, aircraft N6GN, sn: 342, a thorp T-18, departed FD38 on a 14 CFR 91 flight. There were two occupants onboard, one pilot and a passenger. At this time this office cannot positively determine which runway the aircraft departed from. The aircraft owner was a resident of the fly-in community FD38. This strongly suggests the aircraft departed FD38 the day of the accident. Witnesses stated that at about 300 feet above ground in a level attitude over greenbriar park traveling in a southeasterly direction, the engine quit producing power. The aircraft was then observed executing a left turn in an attempt to return to the airport. During the left turn the aircraft began to descend at a rapid rate impacting the ground in a flat attitude, according to witness. Investigation of the accident site and debris field suggests that the aircraft impacted the ground slightly nose and right wing low. The aircraft appeared to bounce, sliding for approximately 129 feet before coming to rest. The aircraft crash signature suggests the propeller was not producing power at the time of impact due to the horizontal position and lack of any damage to it. The engine was broken from its mounts and angled towards the right. The right wing was broken in two just outboard of the flap. Also, the fuselage was bowed towards the right. These signatures suggest that the aircraft did stall and begin to spin into the ground. There might not have been sufficient altitude for a full spin to develop. The passenger was ejected from the aircraft. There is no evidence to suggest the passenger was wearing the restraint system at the time of the accident. The restraint assembly was found to be disconnected. Post accident investigation of the restraint system found no defects and there was no damage noted to the assembly itself. The passenger restraint system was disconnected and undamaged upon arrival at the accident site. The medical examiner stated they would be able to determine if the passenger was secured at the time of impact. The pilot was secured in the aircraft, although the right shoulder harness failed at the metal mount. A post accident assessment of the powerplant was conducted. The powerplant did not show any signs of a catastrophic failure. The engine rotated freely and had continuity. Water was observed in various portions of the fuel system. The most significant amounts were noted in the electric fuel pump. The gasolator filter bowl was dislodged during impact. Corrosion was noted in the bottom of the gasolator bowl. Surface corrosion was also noted on the filter screen of the servo fuel injector unit. Upon disassembly a droplet of water was noted within the fuel manifold. While inspecting the fuel tank a round stain approximately three inches in diameter could be seen around the main feed port of the fuel tank as viewed from the fuel filler port. A visual inspection was conducted of the servo fuel injector assembly. The foam air filter element was found lodged in the inlet of the throttle body. Normally the filter element is positioned at the opening of the induction system intake. The father of the pilot stated that, according to his son, the aircraft was extremely difficult to restart when the engine was at operating temperature.