Cessna T210M Safety Record

The deterioration and subsequent leakage of a hydraulic line which resulted in the total loss of hydraulic fluid and the inability of the pilot to extend the landing gear into the locked position.

The pilot-in-command's failure to confirm, the landing gear was down and locked. Factors were the check pilot's failure to confirm the landing gear was down and locked, and the sun glare.

The company mechanic's failure to correctly install one or more of the crankshaft counterweight pin retaining plate snap rings, specifically ensuring that the snap rings were fully seated in their grooves. This led to the complete separation of the No. 2 leading counterweight and the partial separation of the No. 3 trailing weight from the crankshaft and a resulting internal catastrophic engine failure. A factor in the accident was the lack of definitive procedural guidance in any of the engine manufacturer's reference material, available at the time, on the correct installation of these components.

The pilot's failure to maintain clearance from the terrain while descending in an area of deteriorating weather. Factors include mountainous terrain, clouds, low ceilings, the pilot's inadequate preflight weather analysis, and his improper decision to attempt to continue on to his planned destination after encountering deteriorating weather.

The pilot's failure to maintain sufficient airspeed during final approach to landing, resulting in an inadvertent stall. A factor was the high density altitude.

The pilot's failure to follow alternate landing gear extension procedures. Factors were the main landing gear failure to extend and a loss of electrical power.

Installation of improper connecting hardware by maintenance personnel, and, the inadequate inspection of the installed hardware by inspection personnel resulting in separation of the engine throttle linkage.

The disintegration of the #1 cylinder piston resulting from a detonation/pre-ignition condition due to an unknown reason. A factor was the lack of suitable terrain for the forced landing.

failure of #5 exhaust valve and/or #5 exhaust valve guide, which resulted in a progressive engine failure (debris puncturing the #5 piston crown, exhaust gasses entering the crankcase, loss of oil through the breather system, oil exhaustion, and subsequent damage to the engine bearings and connecting rods). Darkness and obstructions (vehicles) in the emergency landing area were related factors.

The pilot's miscalculation of fuel consumption and his inadequate in-flight decision making, which resulted in fuel exhaustion and the loss of engine power.

the pilot's improper planning/decision, which resulted in fuel exhaustion and loss of engine power. Factors relating to the accident were: the inaccurate fuel quantity gage, and the light condition at dusk.

The pilot's impairment of judgment and performance due to the recent excessive use of potent prescription drugs, the pilot's descent below the published decision height, and the pilot's failure to execute a missed approach. Factors contributing to the accident were the adverse meteorological conditions which were below the published required visibility, runway visual range, and ceiling minima due to fog.

failure of the #2 cylinder connecting rod bolt due to oil starvation as a result of the shifting of the main bearing. A factor was the unsuitable terrain for the forced landing.

loss of engine power for undetermined reason(s). Factors relating to the accident were: the weather conditions (restricted visibility with snow falling), reduced light condition at dusk, and the lack of suitable terrain for an emergency landing.