Robinson R44 Safety Record

The pilot's attempt to move the helicopter from a sloped surface after an overspeed event, which resulted in a loss of helicopter control and impact with a car. The overspeed event resulted from misrouted and damaged wiring in the magneto, which subsequently resulted in errant and random signals to the governor.

Loss of oil in flight as a result of a loose oil filter adapter which resulted in the pilot initiating an immediate landing to an open field. Contributing to the accident was the pilot's manipulation of the throttle that led to a reduction in rotor rpm, which resulted in his inability to perform a normal landing.

Maintenance personnel's application of insufficient preload on the attachment hardware for the idler gear shaft during engine overhaul, which resulted in the dismounting of the idler gear shaft assembly due to wear and deformation and the subsequent total loss of engine power. Contributing to the accident was a mechanic's failure to identify metallic particles contained in the oil filter element at the most recent 100-hour inspection.

The pilot's improper collective application, which resulted in low rotor rpm during the takeoff climb and a subsequent ground collision. Contributing to the accident was the pilot’s self-induced pressure to complete the operation.

The pilot's improper preflight weight and balance calculation, which resulted in his operating the helicopter over its maximum gross takeoff weight and in its subsequent failure to climb.

A partial failure of the helicopter's engine tachometer due to the separation of one of the magnet assemblies and engine roughness, which precipitated the pilot’s initiation of an off-airport autorotation, during which he applied improper aft cyclic flight control input, which was contrary to the Pilot’s Operating Handbook. The reason for the reported engine roughness could not be determined during postaccident examination and engine test-runs.

An on-ground upset for reasons that could not be determined because postaccident examination of the helicopter revealed no evidence of mechanical malfunctions or failures that would have precluded normal operation.

The non-instrument rated pilot's inadvertent encounter with instrument meteorological conditions during initial climb and his improper decision to continue flight, which resulted in an in-flight impact with a tree and an emergency descent that resulted in a roll over on landing.

The pilot's failure to ensure that the helicopter was properly loaded, which resulted in the helicopter being in excess of its maximum allowable gross weight and led to a loss of main rotor rpm on takeoff. Contributing to the accident were the ground crewman's inadvertent overloading of the helicopter and the design of the spray tank's visual sight glass, which did not allow the pilot to visually verify the amount of the spray tank load without exiting the helicopter.

The certified flight instructor’s failure to maintain adequate main rotor blade rpm during a practice autorotation, resulting in a hard landing and rollover.

The pilot's failure to maintain adequate clearance from wires while maneuvering and his subsequent improper use of the collective control, which resulted in the main rotor contacting the tail boom.

The pilot's failure to see a wire cable prior to colliding with it. Factors contributing to the accident were the non-routine positioning of the wire cable, and the ground crew's failure to advise the pilot that the wire had been re-routed.