UTICA, NY, USA
CFFSS
MITSUBISHI MU-2B-60
DURING CLIMB, ONE OF THE FOUR PROPELLER BLADES ON THE NUMBER TWO ENGINE SEPARATED FROM THE PROPELLER HUB, DAMAGING ANOTHER PROPELLER BLADE AND THE FUSELAGE. SHORTLY THEREAFTER, THE ENGINE SHUT DOWN. THE ROTATIONAL UNBALANCE WAS ACCOMPANIED BY EXTREME VIBRATION AND RESULTED IN DISTORTION AND DAMAGE TO THE ENGINE/COWL ASSEMBLY AND THE WING. THE UPPER PORTION OF THE ENGINE COWL WAS DEFLECTED UPWARD OVER THE WING AT AN ANGLE OF ABOUT 30 DEG, RESULTING IN DISTORTION OF AIRFLOW, BUFFETING, AND DEGRADATION OF ROLL CONTROL. DUE TO EXCESSIVE DRAG, MAXIMUM POWER WAS REQUIRED ON THE NUMBER ONE ENGINE IN ORDER TO CONTROL THE RATE OF DESCENT AND LAND SUCCESSFULLY. A METALLURGICAL EXAMINATION DISCLOSED EVIDENCE OF FATIGUE CRACKING OF THE PROPELLER HUB ARM.
FATIGUE CRACKING OF THE PROPELLER HUB.
Source: NTSB Aviation Accident Database
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