Cessna T210M Safety Record

A loss of engine power during the final landing approach for reasons that could not be determined because postaccident examination did not reveal any malfunctions or failures that would have precluded normal operation.

The total loss of engine power due to fuel starvation for reasons that could not be determined because postaccident testing of the engine did not reveal any malfunctions or failures that would preclude normal operation. Contributing to the accident was the pilot’s improper in-flight fuel management following the loss of engine power.

Latent dimensional discrepancies related to the engine crankcase main bearing saddle bores, which precipitated the fatigue failure of the crankshaft and a complete loss of engine power. Contributing to the accident was the engine manufacturer's failure to properly identify and address the crankcase discrepancies when the engine was rebuilt.

The pilot's improper in-flight planning, which resulted in a loss of engine power due to fuel exhaustion. A factor was the lack of suitable terrain available for the forced landing.

The failure of the right main landing gear wheel, which resulted in the pilot's inability to maintain directional control during landing rollout. A factor in the accident was the failure of maintenance personnel to inspect the wheel in accordance with maintenance manual instructions.

the pilot's inadequate compensation for the wind conditions which resulted in a loss of control during landing. A contributing factor was the gusty crosswind.

The pilot's failure to use all the available runway and his failure to follow the prescribed short field takeoff procedure resulting in a loss of control during the takeoff roll. Factors were the short, rough, and rising runway, and the soft dirt surrounding the runway.

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.

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.

ENGINE FAILURE DUE TO INADEQUATE VAPOR RECOVERY SYSTEM (INADEQUATE AIRCRAFT MAINTENANCE/SERVICE) AND INCORRECT FUEL GRADE. A FACTOR IN THE ACCIDENT WAS UNSUITABLE TERRAIN.

THE IMPROPER CALIBRATION OF THE FUEL QUANTITY GAUGES BY MAINTENANCE PERSONNEL, WHICH RESULTED IN ERRONEOUS FUEL QUANTITY INDICATIONS AND LED TO FUEL STARVATION. CONTRIBUTING TO THE ACCIDENT WERE THE UNSUITABLE TERRAIN CONDITIONS THAT EXISTED AT THE FORCED-LANDING SITE.