Cessna T210M Safety Record

the pilot's failure to verify the current local wind condition that resulted in his selection of the wrong runway and an inadvertent downwind landing, a runway overrun and a ground collision with objects. A factor in the accident was the short runway and its dirt surface, which reduced brake effectiveness.

Maintenance personnel's improper installation and servicing of a retaining ring, which resulted in the failure of the landing gear door actuator and failure of the landing gear extension system during landing.

Spinning of the crankshaft No. 2 main bearing for undetermined reasons resulting in damage to the aft cheek of the No. 2 main bearing journal, fatigue failure of the crankshaft cheek, failure of the engine in cruise flight, and damage to the airplane during the subsequent forced landing on unsuitable terrain..

the failure of the landing gear actuator switch. Factors relating to the accident were the false landing gear indication, the precautionary landing, and the improper maintenance adjustment performed on the landing gear switch prior to the accident flight.

The pilot's inadequate preflight and in-flight planning/decision resulting in miscalculation of fuel consumption, fuel exhaustion and loss of engine power. Factors were rough terrain in a vineyard, power lines in the landing area, and night time.

the loss of engine power while on final approach due to fuel starvation as a result of the pilot's improper use of the fuel selector. A contributing factor was the elevated runway edge.

The failure of the pilot to comply with emergency procedures contained in the Pilot's Operating Handbook, which resulted in an excessively rich mixture and loss of engine power.

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 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.

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.