20010824024629A

(-23) This aircraft struck the ground at over 200 mph, upright and slightly nose low. Evidence indicates that the engine was running and the propeller was spinning. A witness saw the airplane with very bright landing lights but turned the corner and did not witness crash. The witness also said that thunderstorms were approaching from the south with a lot of lightning. The accident occured about 30 minutes after sunset. The area would be dark with few lights on the ground for visual reference. Radar recording showed an aircraft sqwaking VFR (1200) about a mile away from the crash site at 20:20:19, level at 3,500 feet (MSL). The radar was showing a hit about every 12 seconds but no further hits were recorded. The ground elevation is about 840 feet (MSL) at the crash site. All major parts of the airplane were found at the crash site. (.19) on August 24, 2001, at about 2030 central daylight time, a Piper PA-28-235, N16405, piloted by a private pilot, was destroyed when it impacted terrain near crestline, Kansas. The 14 CFR part 91 personal flight was not on a flight plan. Visual meteorological conditions were reported at the jopl in regional airport, Joplin, Missouri, about 9 miles east of the accident site. The pilot, who was the sole occupant, was fatally injured. The local flight originated from jln at about 1845. An on-scene examination of the aircraft was conducted on August 25, 2001. The aircraft came to rest in a prepared farm field. The initial impact point was determined using a global positioning system (GPS) receiver as 37 degrees 08.766 minutes north latitude, 94 degrees 41.293 minutes west longitude. The left and right wings, ailerons, and flaps were destroyed and had impact damage. The wings were separated at the wing root. The outboard fuel tanks were separated and had fire damage. The outboard fuel caps were in-place and intact. Both main landing gear were destroyed and separated from their attachment points. The left aileron was attached at the inboard hinge. The bellcrank was destroyed and separated from its attachment points. One cable was separated at the bell crank. The separated cable exhibited signatures consistent with tension overload. Both aileron cables were cut at the wing root area for aircraft examination. The aileron control chain was broken and separated into pieces. The aileron control cable was attached to the broken control chain end. The aileron cables were cut near the cabin area for wreckage examination. The left flap was attached all attachment points. The flap torque tube was destroyed. The right aileron was attached to both hinges. The bellcrank was destroyed and separated from its attachment points. The aileron control cable was attached to the broken control chain end. The balance cable was cut for wreckage examination. The right flap was attached to the inboard and middle hinge. The empennage was destroyed and separated from the fuselage. The rudder was attached to the top attachment point. The rudder horn was destroyed and had impact damage. The rudder cables were attached to the rudder horn. The rudder cables were cut at the tail area for wreckage examination. The rudder cables were attached at the rudder pedals. The rudder stops were in-place and intact. The stabilator had leading edge impact damage. The stabilator cables were attached at the balance weight and at the control 't' bar. The stabilator cables were cut at the tail area for wreckage examination. The stabilator trim tab mechanism measured .5 inches, approximately 3 threads, corresponding to a neutral to nose down trim condition. The stabilator stops were in-place and intact. The fuselage was destroyed and fragmented into several pieces. The flap handle was separated and destroyed. Impact deformation was displayed at the flap down notch area and the 40Πnotch area. The fuel selector valve was separated and consumed in the post impact fire. The fuel selector was found in the off position. A vacuum gyro was disassembled, and the gyro had rotational scoring on the gyro drum and housing. The airspeed indicator was separated from the instrument panel. A white colored radial mark was found on the instrument face. The mark was located outside of the airspeed markings of the instrument. The engine was removed from the wreckage and supported for examination. The lower engine case was destroyed. The crankshaft was broken just aft of the propellor flange and exhibited a break consistent with torsional overload. The crankcase was broken in the area of the forward left cylinder, and the cylinder was pushed rearward. The crankshaft could not be rotated. The accessory case was fractured. The accessory gears were found intact. The magneto mounts were fractured. Both magneto's produced spark on all leads when rotated by hand. The carburetor was found separated and the fuel bowl was compromised. The propeller blades exhibited chordwise scratches and leading edge nicks. One of the blades was separated from the hub. No anomalies were detected with respect to the airframe or engine or their respective systems that could be associated with a preexisting condition.