YAKIMA, WA, USA
N9726Q
BEECH A24R
WITNESSES REPORTED OBSERVING THE AIRPLANE PERFORMING AEROBATIC MANEUVERS WHICH INCLUDED LOW-LEVEL FLIGHT, STEEP TURNS, INVERTED FLIGHT, AND WINGOVERS. THE AIRPLANE MADE A STEEP RIGHT TURN OVER A NEIGHBOR'S HOUSE, AND WHEN THE WINGS LEVELED THE NOSE DROPPED AND THE AIRPLANE STRUCK AN 80-FOOT TALL PINE TREE WITH ITS RIGHT WING TIP. THE AIRPLANE CONTINUED FOR 91 FEET BEFORE COLLIDING WITH THE TERRAIN IN AN INVERTED POSITION.
HISTORY OF FLIGHT On September 2, 1995, approximately 1825 Pacific daylight time, a Beech A24R, N9726Q, collided with a tree during low-level maneuvering about 16 miles southwest of Yakima, Washington. The private pilot, who was the sole occupant, received fatal injuries, and the aircraft was destroyed. The local personal pleasure flight, which departed Yakima Air Terminal about 1800, was being operated in visual meteorological conditions at the time of the accident. No flight plan had been filed, and there was no report of an ELT activation. According to witnesses in the area, the pilot had been performing "aerobatic type" maneuvers and making low passes at numerous locations near the accident site. During the pullout from one of the maneuvers, the aircraft impacted a coniferous tree. Witnesses reported that the airplane had been observed performing aerobatic maneuvers over the pilot's neighbors as they worked on a bulldozer in front of their house. The maneuvers included steep turns, inverted flight, and wing-overs. The airplane was observed to make a steep right-hand turn to a heading which resulted in it heading almost directly toward the group of individuals gathered around the bulldozer. As the airplane rolled wings level, the nose was lowered or dropped, and the aircraft struck an 80-foot tall pine tree with its right wing tip, severing five feet of the outer wing panel. The aircraft immediately rolled to the right and crashed inverted into a creek bed. Four witnesses who were standing about 50 feet from the impact site were interviewed, and all reported that the aircraft's engine sounded like it was at full power until it impacted the ground. PERSONNEL INFORMATION The pilot held a private pilot certificate for single-engine land operations and an instrument rating. The pilot's flight logbook has not been located, however, the Federal Aviation Administration Medical Records, indicate that the pilot had listed a total flight time of 785 hours at the time of his last medical on July 22, 1995. The pilot had purchased the airplane on June 27, 1995, and it was reported that the pilot had accumulated a total flight time of 30 hours in this make and model airplane. WRECKAGE AND IMPACT INFORMATION The wreckage was found positioned inverted on the edge of a creek bed. A tree which had been separated at the 50 foot level was found 91 feet away from the wreckage. A magnetic heading of 300 degrees was taken from the tree to the wreckage. The aircraft's nose was pointed 215 degrees. All three landing gear were found in the retracted position. The left flap was extended beyond the down position; its actuator push rod had been sheared. The inboard panel of the left wing remained attached to the aircraft, with the outer eight and-a-half feet partially separated. Leading edge damage on the outboard panel exhibited accordion crushing. The aileron bellcrank remained in the outer wing panel, and the aileron control rod was separated. The left aileron was separated from the wing. The inboard portion of the right wing remained attached to the aircraft. The separated outer wing panel was found near the tree which had been topped. The right main landing gear mounting trunnion had separated from the bulkhead. The stabilator was free and the anti-servo tab followed with appropriate travel. The rudder was sheared off at the top and middle hinges. The rudder horn remained connected by its shackles. The stabilator, rudder, and trim cables had continuity up to the aft cabin area. Continuity was established on all controls. The propeller remained attached to the crankshaft. The leading edge of one propeller blade, on the inboard half, showed leading edge indentations; the blade was separated about 18 inches out from the hub. The other blade displayed an "S" bend and massive leading edge indentations on the inboard one-third of its span. The engine displayed impact damage, however, the crankshaft rotated easily and compression was developed in all four cylinders. Accessory gear and valve train continuity were established. The magnetos were broken from their mounts and displayed impact damage, however, a spark was produced with hand rotation at all four towers for each magneto. The fuel injection servo was sheared from its flange; fuel was found in the fuel injection fuel distribution valve. No contaminants or obstructions were found in the fuel system. The vacuum pump had broken from its mount. The rotor was broken, however, all vanes were intact. MEDICAL AND PATHOLOGICAL INFORMATION An autopsy on the pilot was performed by Dr. Daniel M. Selove, Yakima County. The pilot's cause of death was attributed to injuries sustained during the impact with the terrain. Toxicological samples were sent to the Federal Aviation Administration Civil Aeromedical Institute, Oklahoma City, Oklahoma, for analysis. The result of the analysis was negative. ADDITIONAL INFORMATION The wreckage was moved to a secured hangar at the Yakima Airport. The wreckage was released to the owner's representative on September 4, 1995.
THE PILOT'S FAILURE TO MAINTAIN CLEARANCE FROM A TREE. FACTORS RELATED TO THE ACCIDENT WERE: THE PILOT'S POOR JUDGMENT AND OSTENTATIOUS DISPLAY TO BUZZ.
Source: NTSB Aviation Accident Database
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