HARDEEVILLE, SC, USA
N5191B
BELL 47G-2
THE PLT STATED THAT HE NOTICED A PECULIAR PEDAL REACTION DURING A TURN-AROUND; HOWEVER, HE REPORTED THAT THIS MAY HAVE BEEN CAUSED BY THE WIND WHICH WAS GUSTING TO 15 KTS. SHORTLY AFTER COMPLETING THE TURN-AROUND, HE EXPERIENCED A COMPLETE LOSS OF TAIL ROTOR CONTROL. THE FAILURE WAS REALIZED BY A REDUCTION OF NOISE, AN RPM INCREASE & AYAW TO THE RIGHT. THIS OCCURRED AT AN ALTITUDE OF APRX 300 FT AGL. THE PLT WAS UNABLE TO MAINTAIN DIRECTIONAL CONTROL IN FLT, SO HE AUTOROTATED TO A NARROW LOGGING ROAD. WHILE DESCENDING TO LAND, THE MAIN ROTOR STRUCK TREES ON BOTH SIDES OF THE ROAD. DURING TOUCHDOWN. THE MAIN ROTOR STRUCK & SVERED THE TAIL BOOM. AN EXAM REVEALED THE TEETH ON THE FORWARD (SHORT) TAIL ROTOR DRIVE SHAFT, PN 47-644-180-9, WERE WORN & OVERHEATED. ALSO, THE MATCHING SPLINES ON THE FRONT COUPLING, PN 47-620-494-3, WERE OVERHEATED & STRIPPED. ONLY A MINIMAL AMOUNT OF LUBRICATION WAS FOUND IN THE FRONT COUPLING. THE BELL MAINTENANCE & OVERHAUL INSTRUCTIONS RECOMMENDED DAILY INSPECTIONS & LUBE EVERY 50 HRS.
Source: NTSB Aviation Accident Database
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