Bell 47 Safety Record

The disengagement of the oil jet fitting from its threaded receptacle at the forward end of the engine crankshaft. This resulted in excessive oil within the clutch assembly, the subsequent slipping of the clutch, and ultimately the disengagement of the rotor drive system from the engine. Contributing factors were the pilot's not maintaining clearance from the electric fences which were also hidden objects against the grass landing surface.

The pilot's failure to use carburetor heat, which resulted in a loss of engine power. Factors included the ambient carburetor icing conditions and the lack of suitable terrain for the forced landing.

the pilot's failure to verify that ground personnel had disconnected the loading hose from the hopper before takeoff, resulting in restricted directional control and a hard landing.

The pilot's failure to maintain rotor rpm while attempting a precautionary autorotation landing. A factor was the loss of engine power for undetermined reasons.

A loss of power for undetermined reasons and the failure of the pilot to maintain adequate rotor RPM following the power loss. Contributing factors were the pilot's lack of certification and total experience.

The pilot's failure to maintain the proper touchdown point during landing causing the landing skid to become entangled with the edge of the helipad platform and the resultant rollover and main rotor blade strike of the tow vehicle.

The pilot's failure to adequately preflight the helicopter's fuel system resulting in the total loss of engine power as a result of water contamination. Factors were the incorrect filter installed on the fueling truck and the pilot's improper touchdown technique.

The loss of engine power for an undetermined reason. Factors associated with the accident were the low altitude of the helicopter, which precluded an emergency autorotation, and the crop field.

A fouled external load cable, and the pilot's operation of the helicopter with a non-approved external bucket installation, resulting in misrouted hydraulic lines and consequent malfunction of the external load release system.

An in-flight loss of control caused by the main rotor severing the tail rotor drive shaft as a result of the pilot's cyclic pull-up into a tailwind for his second approach and landing. The loss of the tail rotor caused an uncontrollable descent and tree strike with the main rotor and in-flight collision with terrain. Contributing to the accident was the pilot's improper decision to make a downwind approach and landing.

the pilot's improper entry into the autorotation, which resulted in the loss of power and a low rotor rpm condition. Also causal was the pilot's improper execution of the autorotation which resulted in the hard landing. Factors in the accident were the performance of the autorotation at dusk over rough terrain.

The pilot's failure to maintain directional control due to vibration from the main rotor blade for undetermined reasons. A related finding was the improper repair of a crack in the laminant of the blue main rotor blade by other maintenance personnel.

The pilot's selection of unsuitable terrain for landing resulting in debris being blown up during landing resulting in damage to the tail rotor and loss of control.

The pilots failure to follow written instructions in the flight manual for an engine failure, and the improper use of flight controls (cyclic/collective) during an autorotation resulting in a hard landing, and collision of the main rotor blades with the tailboom assembly. Contributing to the accident was the improper installation of circlips on the counterweight assembly during an engine overhaul. This resulted in a subsequent total failure of the number 5 connecting rod.