Bell 206 Safety Record

A HARD LANDING CAUSED BY THE PILOT NOT BEING ABLE TO JUDGE HIS ALTITUDE ABOVE OR HIS CLOSURE RATE TO TERRAIN BECAUSE OF HIGH VEGETATION IN THE AREA AVAILABLE FOR A FORCED LANDING. AN ENGINE FAULURE CAUSED BY MATERIAL FAILURE OF THE COMPRESSOR SECTION IS A CONTRIBUTING CAUSE OF THE ACCIDENT.

A PARTIAL LOSS OF ENGINE POWER DUE TO CONTAMINATES IN THE FUEL CONTROL UNIT. THE ORIGIN OF THE CONTAMINATES WAS NOT DETERMINED. CONTRIBUTING FACTOR(S) WAS: THE HELICOPTER WAS NOT EQUIPPED WITH FLOATS.

THE PILOT MISJUDGED THE CLEARANCE BETWEEN THE HELICOPTER AND THE POWER LINE. THE POWER LINE (TRANSMISSION WIRE) WAS CONSIDERED TO BE A CONTRIBUTING FACTOR.

PILOT'S IMPROPER EMERGENCY PROCEDURES AND FLARE THAT LED TO A HARD LANDING AND ROLL OVER. FACTORS IN THE ACCIDENT WERE THE PILOT'S DECISION TO INITIATE AN AUTOROTATION FOLLOWING AN UNDETERMINED EVENT AND FAILURE TO MAINTAIN DIRECTIONAL CONTROL DURING THE LANDING SEQUENCE.

PILOT'S FAILURE TO MAINTAIN MAIN ROTOR RPM WHILE EXECUTING AN AUTOROTATION WHICH RESULTED IN A HARD LANDING. CONTRIBUTING TO THE ACCIDENT WAS THE PILOT'S FAILURE TO FOLLOW AUTOROTATION PROCEDURES AFTER THE REPORTED ENGINE FAILURE.

PILOT DISPLAYED POOR INFLIGHT PLANNING WHILE MANEUVERING. THE PILOT DID NOT IDENTIFY THE WIND CONDITIONS RESULTING IN A LOSS OF DIRECTIONAL CONTROL. THE PILOT'S CORRECTIVE ACTION WAS INADEQUATE AND AS RESULT, THE HELICOPTER COLLIDED WITH THE TERRAIN.

THE PILOT INADVERTENTLY TURNING OFF THE ENGINE FUEL SUPPLY INSTEAD OF THE EXTERNAL LOAD FUEL SUPPLY. CONTRIBUTING TO THE ACCIDENT WAS THE PILOT'S FAILURE TO JETTISON THE EXTERNAL LOAD DURING THE AUTOROTATION.

PARTIAL LOSS OF ENGINE POWER FOR AN UNDETERMINED REASON. FACTORS RELATED TO THE ACCIDENT WERE: PERSON(S) IN THE INTENDED EMERGENCY LANDING AREA AND SOFT TERRAIN WHERE THE HELICOPTER TOUCHED DOWN.

THE PILOT'S FAILURE TO CONTROL THE RATE OF DESCENT WHICH RESULTED IN A HARD LANDING. CONTRIBUTING TO THE ACCIDENT WAS A POWER LOSS DUE TO A COMPRESSOR FAILURE.

INADEQUATE MAINTENANCE/INSPECTION OF THE AIRCRAFT FUEL SYSTEM BY COMPANY MAINTENANCE PERSONNEL AND FUEL CONTAMINATION, WHICH RESULTED IN A PARTIAL LOSS OF ENGINE POWER. RELATED FACTORS WERE: A BINDING (STUCK) FUEL FILTER CAP BYPASS VALVE AND PARTIAL FAILURE (INTERMITTENT OPERATION) OF THE RESPECTIVE ANNUNCIATOR LIGHT SYSTEM.

AN ENCOUNTER WITH STRONG DOWN-SLOPE WINDS AND GUSTS DURING A CRITIACAL PHASE OF FLIGHT WHICH CAUSED POWER REQUIRED TO EXCEED POWER AVAILABLE. CONTRIBUTING FACTORS TO THE ACCIDENT WAS THE DOWNHILL TERRAIN AND THE DOWNDRAFT CONDITIONS.

IMPROPER OPERATION OF THE CYCLIC BY THE STUDENT PILOT, FAILURE OF THE STUDENT TO RELINQUISH CONTROL AND INADEQUATE SUPERVISION BY THE FLIGHT INSTRUCTOR.

THE PILOTS ATTEMPT TO CONDUCT THE FLIGHT WITH LESS THAN REQUIRED FUEL RESULTING IN LOSS OF ENGINE POWER AND SUBSEQUENT DAMAGE TO THE HELICOPTER WHILE PERFORMING AN AUTOROTATIVE LANDING.

THE RATED PILOT'S INADEQUATE TAKEOFF TECHNIQUE THE THE INSTRUCTOR PILOT'S MOMENTARY LACK OF JUDGEMENT IN HAVING THE PILOT ATTEMPT A HYDRAULICS OFF TAKEOFF.

FAILURE OF THE #1 TURBINE WHEEL. CONTRIBUTING TO THIS ACCIDENT WAS THE UNREPORTED OVER TEMPERATURE CYCLES OF THE ENGINE. ALSO CONTRIBUTING WAS THE UNSUITABILITY OF THE LANDING SURFACE FROM THE PRESENCE OF THE 1/4 INCH STEEL SHEETING.