De Havilland Dhc Safety Record

the mechanical separation of the left engine beta control linkage during landing rollout, which resulted in asymmetrical decelerative action and the pilot's subsequent inability to maintain directional control. The separation of the linkage was due to the airline's inadequate inspection and quality assurance procedures. An inoperative windsock pivot point, which resulted in faulty wind direction information to the flight crew was a factor in this accident.

The pilot's failure to secure the engine oil filler cap during the preflight inspection that resulted the subsequent loss of engine power, and his in-flight decision to attempt a single engine go-around with full wing flaps extended.

The pilot's inadequate preflight which failed to detect water contamination in the fuel system. A factor was the unsuitable terrain in the emergency landing area.

The pilot's inadequate compensation for the gusty wind conditions, and his attempted flight into adverse weather. Factors associated with the accident are high and gusty winds.

The pilot's failure to maintain adequate airspeed which resulted in an inadvertent stall. Factors associated with this accident were the pilot's unfamiliarity with the geographic area, the low clouds, his becoming disoriented, and the blind canyon into which he flew. An additional factor was the intentionally disabled stall warning system.

The pilot's inadequate procedures/directives when he allowed a passenger to exit the cabin area while the propeller was still turning, and the passenger's failure to follow the pilot's instructions to stay away from the propeller. A factor associated with the accident is the passenger's unfamiliarity with aircraft.

The pilot's excessive climb and turning maneuver at low altitude, the pilot's inadvertent stall, and the intentional operation of the airplane with the required stall warning system disabled. Factors associated with this accident were the pilot's overconfidence in the modified airplane's ability, the uninstalled ventral fin, inadequate compliance with the STC by the company, unclear information by the manufacturer, and inadequate surveillance by the FAA.

The failure of maintenance personnel to correctly diagnose and correct a reoccurring nose gear steering problem, and the improperly tensioned nose wheel steering actuator cables which provided the pilot with an erroneous cockpit indication that the nose gear was centered when it was cocked.

a loss of engine power due to the fatigue failure of the no.1 exhaust push rod. Factors contributing to the accident were: insufficient information on pushrod inspection and overhaul from the manufacturer, unsuitable terrain available for landing, and the pilot's failure to maintain airspeed during the approach which led to an inadvertent stall.

The pilot's misjudged touchdown which resulted in dragging the right wingtip and rupturing the fuel tank. A factor associated with the accident is the rough water conditions.

the pilot's inadequate en route fuel consumption calculations, which led to his failure to recognize a deteriorating fuel duration versus time-to-go situation in a more timely way.

failure of the ground marshaller to marshal the airplane into a correct parking place on the ramp, her failure to verify clearance between the right wing of the airplane and the ground de-ice cart, and failure of the flight crew to ensure clearance of the right wing as the airplane was being taxied into the parking place. Factors relating to the accident include: a congested ramp facility, and inadequate ramp markings.

a missing 'C' clip, which resulted in the master link coming apart, allowing the electric elevator trim chain and cable to become entangled in the elevator trim cables.

a fractured fusion weld in the piston of the roll spoiler servoactuator, which allowed the plug at the base of the piston to separate and jam the piston. A factor relating to the incident was: the inadequate design of the airplane's roll spoiler servoactuator piston.

loss of the right engine propeller control oil, which led to an overspeed of the right engine and propeller, and necessitated a shut-down of the right engine; and failure of the pilot to maintain adequate altitude/distance from terrain during visual approach for a precautionary landing at an alternate airport. Factors relating to the accident were: fluctuation of the left engine power, premature lowering of the airplane flaps, and an encounter with adverse weather conditions (including high winds, severe turbulence, and white-out conditions) during the approach.

a fractured fusion weld in the piston of the roll spoiler servoactuator, which allowed the plug at the base of the piston to separate and jam the piston. A factor relating to the incident was: the inadequate design of the airplane's roll spoiler servoactuator piston.

A failure of the normal landing gear extension system due to a hydraulic leak, and the failure of the airplane's emergency landing gear extension system due to inadequate servicing by company maintenance personnel. Factors were the emergency landing gear extension systems dirty and binding condition, a worn emergency landing gear extension cable, and the training simulator's lack of fidelity concerning the force required to operate the emergency gear extension T-handle.

the pilot's inadequate compensation for wind conditions, and failure to maintain adequate airspeed, which resulted in an inadvertent stall and collision with terrain (water). A factor associated with the accident was the gusty wind condition.

continued flight by the pilot into adverse weather condition, and his failure to maintain adequate altitude/clearance from mountainous terrain. Factors related to the accident were the high/mountainous terrain, and weather conditions that included low ceilings.