Agusta A109 Safety Record

The loss of tail rotor control due to the separation of the tail rotor duplex bearing ring nut from the thrust sleeve, which resulted in the loss of helicopter control.

Fatigue fracture of the main rotor blade tip cap leading edge and subsequent partial separation of the tip cap, resulting in increased vibrations in the main rotor.

The flight nurse’s inadvertent application of left anti-torque pedal during cruise flight, which resulted in a rapid yaw and pitch movement that caused the tail rotor blades to contact the tailboom.

The pilot's spatial disorientation during an instrument approach in dark night instrument meteorological conditions, which resulted in a loss of control and subsequent impact with terrain.

The non-instrument-rated pilot’s decision to initiate the flight into marginal visual flight rules and instrument meteorological conditions, which resulted in spatial disorientation and a subsequent loss of control.

The pilot's excessive cyclic input during a missed approach maneuver in night instrument meteorological conditions, which resulted in a loss of control and spiraling descent into terrain.

A total loss of engine power due to fuel exhaustion as a result of the pilot's inadequate in-flight planning and his decision to continue flight with a known low fuel level state.

The lack of available engine power and subsequent loss of rotor rpm due to the pilot’s departing with one engine at idle. Contributing to the incident was a corroded engine control wiring harness.

The pilot's improper positioning of the number 2 Power Flight Control switch and his inability to obtain the proper climb rate to clear a concrete wall barrier. Contributing factors included the checklist not being followed and the limit override switch not being activated.

The pilot's improper in-flight planning and decision to continue flight under visual flight rules into deteriorating weather conditions, which resulted in an inadvertent in-flight encounter with instrument meteorological conditions and a collision with rising terrain while attempting to reverse course.

The reported loss of engine power for undetermined reasons. A contributing factor was the failure to maintain clearance with the safety fence during the aborted takeoff, which resulted in a dynamic rollover of the helicopter.

Fatigue of the tail rotor trunnion resulting in complete trunnion failure and subsequent tail rotor separation from the helicopter. Factors contributing to the accident were the low altitude, low airspeed, excessive tail rotor loading, and the worn tail-rotor blade grip bushings.

The pilot's improper preflight inspection, during which he failed to remove a flashlight from the tailboom strake. A factor was the pilot's attention be diverted by a mechanic during the preflight inspection.

The pilot's failure to maintain control of the helicopter while maneuvering, resulting in the excessive descent rate and impact with terrain. Factors to the accident included the dark night, low ceiling and reduced visibility at the time of the accident.