CEN14FA453

The pilot's failure to maintain control of the airplane while returning to the airport immediately after takeoff, which resulted in the airplane exceeding its critical angle of attack and entering an aerodynamic stall during the turn. Contributing to the accident was the pilot's inadequate preflight planning, which resulted in the airplane being over maximum gross weight and its subsequent decrease in takeoff climb performance.

The pilot and three passengers boarded the airplane for a local flight at night. The controller cleared the flight for takeoff and observed the airplane lift off about 2,000 feet down the runway. Shortly after liftoff, the pilot contacted the controller and reported that the airplane was not "climbing fast" and that he wanted to make a left turn to return to the airport. The controller approved the left turn and observed the airplane begin a left turn and descend to impact with the terrain. A postimpact fire ensued. Examination of the accident site indicated that the airplane impacted in a steep descent. The witness observations and the impact geometry are consistent with the pilot failing to maintain adequate airspeed while turning to return to the airport, resulting in the airplane exceeding its critical angle of attack and experiencing an aerodynamic stall. A postaccident examination of the airplane and engine did not reveal any anomalies that would have prevented normal operation of the aircraft. Weight and balance calculations showed that the airplane was between 93.6 and 165.6 pounds over maximum gross weight at the time of the accident. The decreased takeoff climb performance reported by the pilot was likely due to the airplane's over gross weight condition.

Weight and Balance Two sets of weight and balance calculations, using different variables, were performed for the airplane. The airplane's weight and balance paperwork showed the maximum gross weight for the airplane was 2,457 pounds, the maximum useful load was 787.4 pounds, and the maximum aft moment was 116,000 pound-inches. The occupant weights provided by the medical examiner were: pilot - 130 pounds; right front passenger - 200 pounds; left rear passenger - 172 pounds; and right rear passenger - 166 pounds. The first calculation used the occupant weights that were provided by the medical examiner's office, 10 pounds of baggage, and 35 gallons of fuel. These calculations showed the airplane had a takeoff weight of 2,550.6 pounds with a moment of 112,957 pound-inches. The second calculation increased the occupant's body weights by 10% to account for the weight lost by the thermal injuries and increased the baggage to 15 pounds. These calculations resulted in the airplane at a gross weight of 2,622.6 pounds, which is 165.6 pounds over gross weight and with a moment of 117,127 pound-inches. Witnesses who were with the pilot and passengers before the flight stated the pilot asked two of the passengers how much they weighed. One witness recalled that the passenger who would become the right front seat passenger stated he weighed 200 pounds. The witness stated the pilot performed some calculations in his head and indicated that he believed they would be below the weight limit for the airplane. Personal Electronic Device Two iPhones were located in the wreckage. One of the iPhones was able to be accessed and it was sent to the NTSB Vehicle Recorder Division for examination. The iPhone was owned by one of the passengers. At 20:33:01, a text message first referenced the flight. Text messages continued with the same recipient until 21:37. The messages discussed a destination of Kelley's Island; a half hour flight each way for a total flight time of one hour; and the possibility of further communication about the flight using Snapchat. At 21:49, a 10-second video was taken from the back right passenger seat while the aircraft was taxiing. The video panned from the right exterior of the airplane to the forward interior. Persons were in both the left and right front seats. The person in the right front seat was not touching the flight controls. The person in the left front seat had both hands on the yoke. The flap handle was visible in the full up position. An autopsy was performed on the pilot at the Cuyahoga County Medical Examiner's Office on August 28, 2014. The death of the pilot was attributed to blunt trauma and thermal injuries sustained in the accident. The FAA's Civil Aerospace Medical Institute performed forensic toxicology testing on specimens from the pilot with negative results for drugs and alcohol. The airplane impacted the ground, a chain link fence, a guy wire, and a telephone pole before coming to rest about 1,000 feet from the departure end of runway 6 on a bearing of 20 degrees. This location is just north of the intersection of Bishop Road and Curtiss Wright Parkway. The wreckage path was along a 210 degree heading. The left wing tip, including the position light, was embedded in the ground at the first impact mark east of the chain link fence. The airplane then traveled through the fence, with the left wing contacting one of the fence posts. The main impact ground scar was on the west side of the fence. Adjacent to the main impact mark were two slash marks in the soft ground. Both marks were about 12 inches long. One of the slash marks was about 7 inches deep and the other was about 4 inches deep. The airplane came to rest on a heading of about 160 degrees with the left wing against the telephone pole. A postimpact fire ensued. The left wing tip was the first part of the airplane to impact the terrain. The wing tip light assembly was embedded in the ground. A concave impact mark along with paint and rust transfers on the left wing aileron indicate that it contacted a metal fence post. The inboard six feet of the aileron was accordioned and crushed toward the outboard section of the aileron which remained attached to the wing. A three foot section long outboard section of the flap remained attached to the wing. The inboard section of the wing and flap were burned. The wing was separated from the fuselage. The wing strut remained attached to the wing. The leading edge of the wing was crushed aft. The outboard section of the right wing was bent upward about 30 degrees starting near the strut attach point. The right wing was separated from the fuselage. The strut remained attached to the wing. The flap and aileron remained attached to the wing. The inboard section of the wing sustained fire damage. The outboard section of the wing was crushed aft. The flap actuator showed the flaps were in the retracted position. The empennage remained intact with the rudder and elevator attached to their respective stabilizers. The outboard section of the right horizontal stabilizer and elevator were crushed. The elevator trim was measured and the measurement equated to a 9 to 10 degree nose-up trim setting. The cabin area and instrument panel were destroyed by the post impact fire. The fuel selector was on the "Both" position and the fuel shutoff valve was in the open position. Flight control continuity was established from all of the flight controls to their respective cockpit controls. Engine The engine was located with the main wreckage. The engine mounts were separated from the firewall due to thermal damage. The propeller remained attached to the engine. The exhaust system sustained impact damage. The rear accessory case and the accessories sustained thermal damage. The accessories and cylinder valve covers were removed. Thumb compression and engine continuity from the propeller to the accessory section was established when the propeller was rotated by hand. The cylinders and pistons were examined using a lighted borescope and no anomalies were noted. The left magneto could not be turned by hand. The magneto cap was removed and the internal components of the magneto were melted. The right magneto turned by hand, but no spark was visible on the ignition leads. The ignition cap was removed and the inside of the magneto was found melted. The engine was equipped with two vacuum pumps. The pump with the longer shaft was mounted lower on the accessory case. The pump frangible shaft couplings were melted on both pumps and therefore they could not be turned by hand. Both pumps were opened. The vanes and rotor inside both pumps were intact. All fuel lines from the flow divider to fuel nozzles were intact. The fuel nozzles were removed. Nozzle No. 1 was not obstructed, nozzle No 2. was inadvertently dropped in oil during removal, nozzle No 3. was separated in two pieces neither of which were obstructed, and nozzle No. 4 was 80% obstructed with the insert not obstructed. The fuel flow divider was opened and examined. The rubber diaphragm was intact. The engine driven diaphragm fuel pump housing was burned; however, the pump plunger was intact. The throttle arm on the fuel servo was connected and moved the throttle plate. The mixture control arm was separated from impact. The finger screen was clean. The ignition leads sustained thermal damage, but they remained attached to all of the spark plugs. The spark plugs were slightly worn and showed normal operating signatures. The No. 1 bottom plug was wet with oil. Propeller The propeller spinner was fractured and separated from the propeller. Both propeller blades were straight. One propeller blade contained a ¾ to 1-inch deep gouge near the tip of the blade. Chordwise scratches and leading edge polishing were visible on this blade. The other blade contained light chordwise scratches. There were no anomalies identified with