Venice

The pilot was not familiar with the mountain airport. The airplane was high during the first visual approach to the runway. The pilot performed a go-around and the airplane was again high for the second approach. During the second approach, the approach angle steepened, and the airplane pitched nose-down toward the runway. The nosegear touched down about halfway down the runway followed by main gear touchdown. The airplane then bounced and the sound of engine noise increased as the airplane banked right and the right wing contacted the ground. The airplane subsequently flipped over and off the right side of the runway, and a postcrash fire ensued. Examination of the airframe and engines did not reveal any preimpact mechanical malfunctions. The examination also revealed that the right engine thrust reverser was deployed during the impact sequence, and the left engine thrust reverser was stowed. Although manufacturer data revealed single-engine reversing has been demonstrated during normal landings and is easily controllable, the airplane had already porpoised and bounced during the landing. The pilot’s subsequent activation of only the right engine’s thrust reverser would have created an asymmetrical thrust and most likely exacerbated an already uncontrolled touchdown. Had the touchdown been controlled, the airplane could have stopped on the remaining runway or the pilot could have performed a go-around uneventfully.

The airplane departed and was climbing to an assigned altitude when the pilot informed an air traffic controller of a loss of engine power on the left engine. The pilot received radar vectors back to the departure airport and reported the airport in sight. There was no further communication with the controller. Review of radar data revealed that the airplane was about 825 feet from and 200 feet above the landing runway threshold. Seventeen seconds later, the airplane was at 100 feet above ground level and left of the intended landing runway. The last radar return was 5 seconds later, and the airplane was at 200 feet above ground level. A witness observed the airplane in the vicinity of landing runway. The airplane pitched straight up, stalled, spun to the left three times before it collided with the ground and caught fire. Postcrash examination of the airframe and flight controls revealed no anomalies. The left engine was disassembled and all connecting rods were intact except for the No.2 connecting rod. Metallugical examination of the connecting rod revealed that the bearing failed, most likely due to a progressive delamination of the bearing. Review of the airplane flight manual revealed a minimum of 300 feet of altitude is required to recover from power-off stalls with 7500 pounds at both forward and aft center of gravity. The stall speed with the landing gear and flaps up with 0 degree angle of bank is 83 miles per hour or 72 knots. The stall speed with the landing gear extended and the flaps down is 73 miles per hours or 63 knots.

The flight was climbing from 5,000 to 10,000 feet and the pilot obtained a maximum altitude of 6,300 feet. The airplane then began to lose altitude and deviate off course. The pilot declared a mayday and reported the airplane was in a spin. Several witnesses near the accident site reported hearing airplane engine noises and seeing the airplane descend from the clouds in a nose-down spiral to the ground. Two AIRMETs were valid at the time of the accident and included the accident location: "AIRMET TANGO update 3 for turbulence ... . Occasional moderate turbulence below a flight level of 18,000 feet due to wind shear ... ." "AIRMET ZULU update 2 for ice and freezing level ... . Occasional moderate rime and/or mixed icing in clouds and precipitation below 8,000 feet." Two pilots who departed in separate Beech 200 airplanes about the time of the accident airplane stated they encountered "moderate rime" icing between 5,000 and 6,000 feet, and one pilot reported instrument meteorological conditions and light turbulence between 1,800 to 6,000 feet. Examination of the airplane revealed no evidence of airframe or engine malfunction. The de-ice ejector flow control valves for the left wing, right wing, and empennage pneumatic boots were removed for examination, and all valves functioned when power was supplied.

An airplane impacted the runway shortly after takeoff. According to the pilot, the airplane rolled sharply to the left immediately after liftoff from the runway. The passenger in the back seat stated the airplane banked sharply to the left after takeoff. The pilot then applied right rudder and aileron to stop the roll. Unable to level the airplane with the horizon, the pilot elected to reduce power to idle on both engines and land on the remaining runway. The airplane impacted the runway, slid into the grass and erupted into flames.

Witnesses watching N900CE's approach for landing to runway 17 at Marco Island Executive Airport stated the pilot appeared to have difficulty aligning the Machen modified Aerostar with the runway centerline. They stated the aircraft appeared unstable about the yaw and roll axes, and appeared too fast. Winds were from the southwest at about 15 knots, gusting to about 20 knots. One pilot/witness close to the touchdown area saw the right wheel touch down instantly, and climb back up to about 50 feet, agl without the full addition of engine power. Most witnesses thought he was either performing a go-around or an extended touch down further down the runway. The airplane continued, "..more and more wobbly" until it entered a climbing attitude and sharp left bank and turn. About half way down the runway the left wing dropped until it contacted the terrain left of the runway, and the aircraft slid into mangrove trees and burned. During postcrash examination, flight control continuity from surface to cockpit floorboards was confirmed. No condition was found with either engine or propeller that would have precluded proper operation, precrash. A witness listening to the pilot's initial radio call up for approach and landing stated that no abnormality was reported by the pilot. Postmortem toxicology testing on specimens obtained from the pilot by the FAA Toxicology and Accident Research Laboratory and the Dade County Medical Examiner revealed quinine found in the blood and urine. The side effects of quinine can include disturbances of vision, hearing, and balance.

Witnesses stated that the aircraft was climbing and just after takeoff, the left wing dropped, the aircraft then leveled off, climbed approximately 75 more feet. The aircraft then abruptly turned hard left and went straight in, striking a wall surrounding a swimming pool, burst into flames and was consumed by post crash fire. Examination of the left engine revealed evidence that suggests that water was ingested into the cylinders prior to impact. The pilot, sole on board, was killed.