Mitsubishi MU-2B Safety Record

The inadequate inspection and rigging of the nose landing gear downlock mechanism by maintenance personnel, which resulted in the failure of a bolt and the subsequent collapse of the nose gear during the landing roll.

Complete loss of No. 2 engine power due to a partial rim failure of the 2nd stage turbine wheel, resulting in No. 2 engine shutdown and turbine debris exiting the side of the engine. The wheel failure mechanism could not be determined due to missing turbine components that were not recovered despite two ground search attempts.

the pilot's failure to lower the landing gear prior to landing. A factor to the accident was the pilot's diverted attention due to the flap system anomaly.

The failure of the ground controller to coordinate the runway crossing of a maintenance tug, with the local controller, which resulted in a ground collision with an MU-2 airplane during it's takeoff roll.

The pilot's misjudgment of the landing flare which resulted in a hard landing. Contributing factors were the subsequent overload and collapse of the nose landing gear.

the pilot's failure to adequately compensate for an asymmetrical thrust condition and to maintain directional control during the landing flare. The owner/pilot's failure to comply with the applicable service bulletin concerning propeller/power control rigging was a factor.

the pilot improperly aligning the airplane on the runway for takeoff. Contributing factors were the reduced visibility due to rain, and the dark night.

The autopilot's computer connections arcing and reported disconnection during the localizer approach and the pilot not performing a go around prior to the hard landing. A factor was the pilots lack of total experience in the accident airplane's make and model.

failure of the pilot to follow the published emergency procedures after loss of power in the left engine. Factors relating to the accident were: fatigue failure of the left torque sensor and gear assembly, which resulted in the loss of engine power, failure of the manufacturer to comply with the respective service bulletin, and the pilot's improper use of the flaps and reverse (single-engine) thrust.

an uncontained failure of the second stage turbine wheel due to fatigue. Factors were: obstructions in the forced landing area and the inability of the airplane to climb after the turbine wheel failure.

an anomaly in the fuel system that allowed a pressure differential to occur between the center and outer portions of the main integral fuel tank, which in turn resulted in fuel starvation of both engines. A factor relating to the accident was: failure of company maintenance personnel to remove fuel system vent check valves as recommended by Mitsubishi MU-2 Service Bulletin 130A.

FUEL STARVATION DUE TO IMPROPER REFUELING PROCEDURES BY THE FBO PERSONNEL, INADEQUATE PREFLIGHT BY THE PILOT, AND RESULTANT ICE IN THE FUEL, WHICH BLOCKED FUEL FLOW TO THE ENGINES. A FACTOR WAS THE LACK OF SUITABLE TERRAIN FOR A FORCED LANDING.

A PROPELLER BLADE FATIGUE FAILURE DUE TO IMPROPER OVERHAUL BY OTHER MAINTENANCE PERSONNEL NOT PERFORMING OVERHAUL IN ACCORDANCE WITH FACTORY SERVICE BULLETINS.

LOSS OF DIRECTIONAL CONTROL BY THE PILOT, DURING TAKEOFF GROUND RUN. CONTRIBUTING TO THIS ACCIDENT WERE A LOSS OF POWER ON THE LEFT ENGINE DUE TO SNOW INGESTION, HEAVY SNOW SHOWERS IN PROGRESS AND AN ICY, SNOW COVERED RUNWAY.

FAILURE OF THE OWNER/OPERATOR TO OBTAIN PROPER MAINTENANCE AND INSPECTION OF THE AIRCRAFT. FACTORS RELATED TO THE ACCIDENT WERE: OPERATION OF THE AIRCRAFT BY THE PILOT WITHOUT A CURRENT ANNUAL INSPECTION (KNOWN DEFICIENCY), AN OIL LEAK IN THE LEFT ENGINE WHICH RESULTED IN OIL EXHAUSTION, AND AN UNDETERMINED PROPELLER CONTROL LINKAGE PROBLEM WITH THE RIGHT ENGINE.