Cessna 210 Safety Record

the aircraft control not maintained by the pilot and the pilot exceeded the design limits of the aircraft. The clouds and night conditions were contributing factors.

The pilot's failure to verify landing gear extension. Factors were the unreliable retraction/extension assembly, and the flying club's continued operation of the airplane with known deficiencies in the equipment.

The failure of the flex hydraulic line and the chaffing of an electrical line under the pilot seat that resulted in an inflight fire. The pilot's inflight decision to continue flight with a known airplane deficiencies.

Inadequate quality control by the manufacturer of the throttle control cable, which resulted in failure of the cable due to fatigue. A factor was the lack of suitable terrain for the forced landing.

The pilot's failure to maintain proper altitude during the final approach segment of the visual approach. A factor was the diminishing light conditions of a deepening dusk.

The pilot's failure to monitor his altitude and maintain an adequate terrain clearance during the approach. The dark night lighting conditions and the visual illusion created by the lack of ground reference lights were factors in the accident.

The cause of the right main gear collapse was undetermined. A factor was the failure of the gear 'down & locked' switch resulting in a false 'down & locked' indication in the cockpit.

The failure of the pilot to follow procedures and directives established by the operator for his failure to fuel the airplane after landing following the first leg. Contributing to the accident was the total loss of engine power due to fuel exhaustion. Findings in the investigation were 1) the failure of company maintenance personnel to comply with all instructions of Airworthiness Directive (AD) 94-12-08, and 2) the pilot flew a total of 1.8 hours in a multi-engine airplane after the first leg landing; 1.5 hours of which were as a flight instructor.

The failure of maintenance personnel to detect cracked main landing gear saddles during required inspection, and subsequent fatigue fracture of the left main landing gear saddle resulting in separation of the saddle and disabling of the left main gear.

The pilot's continued VFR flight into instrument meteorological conditions and his failure to maintain aircraft control. A related factor was the fog.

The pilot's failure to secure the oil cap after adding oil; the flight instructor's failure to insure the preflight was completed properly; and oil on the windshield obstructing forward vision.

The pilot's failure to maintain control during the landing flare/touchdown. Factors were the pilot's delay in aborting the landing and the fence post.

The pilot's inadequate management of fuel and his failure to follow the pre-landing checklist resulting in the loss of engine power as a result of fuel starvation. Factors were the pilot's physiological condition and the lack of suitable terrain for the forced landing.

A loss of engine power due to a disconnected throttle/power lever, cable. Also causal was the failure of the mechanic to install a cotter pin in the throttle control cable attach hardware at the throttle control arm, and failure of the company quality control inspector to verify after the job was completed that a cotter pin was installed, which resulted in disconnection of the throttle control cable from the throttle control arm after takeoff allowing the throttle control to move from the full open position. A related factor was the unsuitable terrain encountered by the pilot during the forced landing.

The pilot's inadequate preflight planning and his failure to verify fuel consumption during flight that resulted in fuel exhaustion and subsequent collision with obstacles and the ground.

A loss of engine power due to the fatigue failure of the mixture control cable, which was due to the improper installation and adjustment of the cable 99 hours prior to the accident.

a total loss of engine power due to an in-flight separation of the crankshaft, caused by a fatigue crack that originated from the aft fillet radius of the No. 2 main journal, resulting in a forced landing in a field and impact with a tree.