Cessna 208 Safety Record

The pilot’s inability to maintain control of the airplane when it encountered a microburst during a landing attempt and a go-around near known thunderstorm activity. Contributing to the accident was an inadequate amount of wind sensors and wind shear detection equipment used by the ATC tower to detect microburst activity at the airport.

The pilot's delayed response to initiate a go-around during a night visual approach over water after the airplane entered instrument meteorological conditions, which resulted in a loss of forward visibility and subsequent impact with the water.

The pilot’s failure to maintain adequate airspeed while maneuvering during an attempted go-around, which resulted in an exceedance of the airplane's critical angle of attack and an aerodynamic stall at low altitude. Contributing to the accident, was the pilot’s decision to perform an approach to a short runway at an excessive airspeed and his late decision to perform a go-around, which resulted in a slow climb at a reduced safe margin above stall airspeed.

The pilot's loss of consciousness while taxiing due to an accumulation of toxic levels of carbon dioxide gas inside the airplane as a result of dry ice sublimation. Also causal was the pilot's decision to fly the airplane in an unventilated configuration, the operator's policy that allowed this configuration, and the shipping company's inadvertent loading of excess dry ice, which exacerbated the concentration of carbon dioxide.

The pilot's decision to continue a visual flight rules flight into an area of instrument meteorological conditions and his subsequent failure to level the airplane after the autopilot disconnected, which resulted in a collision with terrain.

Fracture of a compressor turbine (CT) blade due to operational overtemperatures and the failure of a maintenance technician to detect an existing crack in the CT blade during the last engine inspection.

The pilot's attempted aborted landing late in the landing sequence because she saw another airplane on the runway facing her with its propeller turning, which resulted in a hard landing, a subsequent loss of directional control, and ground loop.

A total loss of engine power due to a fatigue fracture of the fuel pressure line that connected the fuel control unit and the fuel flow transducer due to vibration as the result of a fatigue fracture of an associated support clamp. Contributing to the accident was the mechanic’s inadequate inspection of the fuel line support clamp during the previous replacement of the fuel line.

An encounter with a wind gust during ground maneuvering and the captain’s improper flight control positioning to account for wind conditions, which resulted in the airplane being blown onto its left wing.

The fuel pump gear manufacturer’s allowance of set-up gears made from a nonconforming material to be put in the production inventory system, the installation of a nonconforming gear in the accident airplane’s production fuel pump, and the gear’s failure, which resulted in a loss of fuel flow to the engine and the subsequent loss of engine power.

The total loss of engine power as a result of a fractured first-stage compressor blade due to fatigue cracking. The source of the fatigue crack could not be determined due to secondary damage sustained to the fracture surface.

The inadvertent deployment of the reserve parachute, resulting in the skydiver being prematurely pulled from the airplane and striking the horizontal stabilizer.

The failure of both pilots to maintain adequate clearance/distance from each other at the taxiway intersection to avoid a collision. Contributing to the accident was a lack of clear and concise instruction to either airplane by the ground controller to preclude them from entering the taxiway intersection at the same time.

The pilot's selection of unsuitable terrain for landing. Contributing to the accident were snow-covered terrain, blowing snow and flat lighting conditions.