Hughes 369 Safety Record

loss of engine power for undetermined reasons, the pilot operating the helicopter outside of the height-velocity curve, and the pilot's failure to maintain control of the helicopter during the emergency landing. Factors relating to the accident were the pilot's attempted run-on landing and his improper in-flight decision to not land immediately after experiencing the engine problem.

the loss of engine power for undetermined reasons. A factor was the operation within the cross "hatched area" of the helicopter's height/velocity curve by the company.

The complete loss of power, due to a failure of the compressor impeller disk. Factors include the low altitude of the helicopter at the time of the power loss, and the need to autorotate in a confined area.

The removal of the tail rotor blade abrasion strips by the use of an unapproved method by the maintenance personnel which resulted in the imbalance of the tail rotor blade assembly and subsequent separation of the 90-degree gear box; the pilot/mechanic's unapproved repair to the tail rotor blade tip caps; and, his continued operation of the helicopter with known deficiencies.

Turbine wheel failure as the result of a low-cycle fatigue crack that initiated in a beyond-limits grinding gouge. Factors include improper maintenance by unknown parties and tree stumps that prohibited a successful emergency landing.

The pilot's failure to maintain control of the aircraft and his improper autorotation technique that induced the roll and subsequent ground collision. A factor was his lack of recurrent training.

improper maintenance (replacement) and inspection of the engine fuel governor by company maintenance personnel, the pilot's inadequate preflight inspection, and a subsequent disconnect of the adjustable governor lever control rod, which disabled the engine speed governor and resulted in a partial loss of engine power. Factors relating to the accident were: trees and soft terrain in the emergency landing area, and a tailwind during the forced landing touchdown.

failure of the pilot to maintain control of the helicopter, while maneuvering close to the ground. The unfavorable wind condition was a related factor.

improper planning/decision by the pilot, by failing to ensure there was adequate fuel on board, which resulted in fuel exhaustion and a subsequent roll-over during a forced landing on hilly terrain. A factor relating to the accident was: downsloping terrain in the emergency landing area.

the loss of engine power due to inadequate maintenance inspection of the fuel system which permitted air to enter the engine fuel supply. A factor in the accident was the pilot's improper execution of the autorotation landing.

THE PILOT/OPERATOR'S OPERATION OF THE HELICOPTER WITH A DISCONNECTED THROTTLE ON THE RIGHT COLLECTIVE; THE FAA INSPECTOR'S INADEQUATE PREFLIGHT/PRETAKEOFF CHECKS OF THE FLIGHT CONTROL/THROTTLE SYSTEMS; AND THE PILOT/OPERATOR'S FAILURE TO ADEQUATELY INFORM THE INSPECTOR OF THE DISCONNECTED RIGHT THROTTLE, WHICH RESULTED IN AN INADEQUATE POWER RECOVERY FROM AN INSPECTOR INITIATED AUTOROTATION.

FUEL EXHAUSTION, THE PILOT IN COMMAND'S FAILURE TO REFUEL THE AIRCRAFT, AND THE INABILITY TO SUCCESSFULLY EXECUTE AN AUTO- ROTATION LANDING BECAUSE OF THE LOW ALTITUDE.

the pilot's in-flight decision to maneuver the helicopter close to an active volcano steam vent which resulted in a whiteout condition from the steam, and the pilot's subsequent loss of visual contact with the ground.

the observer's failure to properly secure stowed items in the rear compartment prior to takeoff and the resultant foreign object damage to the tail rotor system which precluded the pilot from maintaining directional control.

UNSUITABLE TERRAIN ENCOUNTERED DURING THE AUTOROTATIVE FORCED LANDING. CONTRIBUTING TO THE ACCIDENT WAS TOTAL LOSS OF ENGINE POWER DUE TO SEIZURE OF THE COMPRESSOR IMPELLER FOLLOWING FAILURE OF THE NO.2 BEARING FOR UNDETERMINED REASONS.

LOSS OF ENGINE POWER DUE TO UNDETECTED FOREIGN MATTER CONTAMINATION OF THE ENGINE FUEL CONTROL. THE LACK OF A SUITABLE LANDING AREA WAS A FACOTR IN THE ACCIDENT.