CAMERON, MO, USA
N6711C
Beech C23
The pilot said that while inbound to the airport, she received a weather advisory over the airport's unicom frequency of winds at 270 degrees magnetic at 7 knots. The pilot performed a visual straight-in approach to runway 17. She said that when she entered the flare, the airplane was still over the runway centerline. The pilot said that the airplane 'was blown off [of the] runway to the east.' The pilot said that she attempted to get back to the runway, but the attempt failed. The pilot said, she then added power for a possible go-around, but the airplane went into a ravine. Examination of the wreckage revealed no anomalies.
On November 14, 1997, at 1700 central standard time (cst), a Beech C-23, N6711C, operated by a private pilot, sustained substantial damage when on landing, the airplane drifted off of the runway and impacted into a ravine along side the runway. Visual meteorological conditions prevailed at the time of the accident. The personal flight was being conducted under 14 CFR Part 91. No flight plan was on file. The pilot and three passengers on board reported no injuries. The local flight originated at Cameron, Missouri, at 1600 cst. In her written statement, the pilot said that while inbound to Cameron Memorial Airport, Missouri, she received a weather advisory over the airport's unicom frequency of winds at 270 degrees magnetic at 7 knots. The pilot performed a visual straight-in approach to runway 17. She said that when she entered the flare, the airplane was still over the runway centerline. The pilot said that the airplane "was blown off [of the] runway to the east." The pilot said that she attempted to get back to the runway, but the attempt failed. The pilot said, she then added power for a possible go-around, but the airplane went into the ravine. A Federal Aviation Administration (FAA) inspector examined the airplane at the accident site. The airplane was resting upright in a ravine along the left side of the runway. The airplane's left wing was bent up and aft at the inboard leading edge, and separated at the wingroot. The fuselage was crushed and buckled inward at the bottom left forward side of the cabin, and at the trailing edge of the left wing. The nose gear was bent to the right and aft, and was embedded in the bottom of the fuselage. Both propeller blades were bent aft. Flight control continuity was confirmed. Examination of the engine, engine controls and other airplane systems revealed no anomalies.
the pilot's failure to maintain directional control of the airplane in the landing flare. A factor relating to this accident was the crosswind.
Source: NTSB Aviation Accident Database
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