Bell 206 Safety Record

The pilot misjudging the distance of the intended touchdown point resulting in his intentional decrease in the main rotor rpm to clear obstacles below. Contributing to the accident was the total loss of engine power due to undetermined reasons.

the pilot's continued VFR flight into instrument meteorological conditions (IMC). The terrain conditions, low ceiling, fog, and whiteout conditions were related factors.

fuel contamination, due to improper servicing of the helicopter, which resulted in an intermittent loss of engine power. A factor relating to the accident was: the pilot's inadequate control of the helicopter, during autorotation with intermittent engine power.

fatigue failure of the engine PC line, induced by damage from improper installation, which resulted in a loss of engine power and an autorotative landing to unsuitable terrain.

The inadvertent deployment of the passenger's parachute as a result of his failure to follow proper procedures and deactivate the automatic opening device on the parachute.

The pilot's improper in-flight planing/decision and inadequate supervision of the passenger, which allowed the helicopter's lateral center-of-gravity to be exceeded. Factors relating to the accident were: pressure (compelling influence) on the pilot and passenger that was induced by the need to rescue the stranded pilot from a life threatening situation, high winds, and large waves.

THE PILOT'S FAILURE TO CROSS-CHECK A FAULTY ENGINE SPEED INDICATION WITH OTHER ENGINE PERFORMANCE INDICATIONS TO VERIFY WHETHER AN ENGINE MALFUNCTION HAD ACTUALLY OCCURRED, AND HIS FAILURE TO MAINTAIN ADEQUATE ROTOR RPM DURING AN EMERGENCY LANDING. THE PILOT'S REACTION TO THE PERCEIVED ENGINE MALFUNCTION LED TO AN UNNECESSARY REDUCTION OF ENGINE POWER AND SUBSEQUENT EMERGENCY LANDING.

the pilot's misjudgment of the landing flare altitude during a night autorotation while preoccupied with maintaining proper main rotor rpm. A factor in the accident was the pilot's visual perception which was affected by the outside ambient lighting conditions.

FAILURE OF THE PILOT OF N444CR TO MAINTAIN ADEQUATE MAIN ROTOR CLEARANCE FROM N38903, AND THE OPERATOR'S FAILURE TO PROVIDE ADEQUATE OR RECOMMENDED SAFE HELIPAD DIMENSIONS. A FACTOR IN THE ACCIDENT WAS THE LACK OF VISUAL REFERENCE TO THE ROTATING BLADES OF THE PARKED HELICOPTER, N38903.

THE PILOT'S IMPROPER COMPENSATION FOR WIND CONDITIONS DURING THE APPROACH AND LANDING. FACTORS WERE THE GUSTS, TURBULENCE, AND TAILWIND CONDITIONS AT THE LANDING SITE.

1) THE PILOT NOT OBTAINING FORECAST WEATHER FOR HIS ROUTE OF FLIGHT NOR HIS DESTINATION 2) THE PILOT'S INFLIGHT DECISION TO FLY INTO SNOW WITH THE HELICOPTER'S ENGINE AIR INDUCTION PARTICLE SEPARATOR KIT NOT INSTALLED, AS REQUIRED BY THE BELL 206B PILOT'S OPERATING HANDBOOK, AND 3) THE PILOT'S IN FLIGHT DECISION TO TURN THE ENGINE ANTI ICE TO THE OFF POSITION. A FACTOR IN THIS ACCIDENT WAS THE UNSUITABLE TERRAIN THE PILOT WAS FLYING OVER WHEN THE ENGINE LOST POWER. THIS UNSUITABLE TERRAIN CAUSED THE PILOT TO USE COLLECTIVE PITCH TO CLEAR TREES RESULTING IN INSUFFICIENT ROTOR RPM TO CUSHION THE LANDING TOUCHDOWN.

FAILURE OF THE PILOT-IN-COMMAND TO PROPERLY USE THE HELICOPTER'S PERFORMANCE DATA. FACTORS WHICH CONTRIBUTED TO THE ACCIDENT WERE: THE ADVERSE TERRAIN AND HIGH DENSITY ALTITUDE.