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Shortly after lift-off, both propeller blades separated from the aircraft, which then touched down and subsequently overturned. One of the propeller blades was located 80 metres to the left of the strip and the other, with hub and constant speed unit attached, was located 40 metres to the right of the strip. The propeller hub contained a fracture which was caused by the propagation of a fatigue crack originating at the root of the blade retention thread. The engine had been fitted with two fifth order crankshaft damper weights. This was contrary to the manufacturer's requirement, which was for one fifth order and one sixth order counterweight to be fitted. It is considered likely that fitment of the incorrect counterweights initiated and contributed to the propagation of the fatigue crack.

Download Final Report
[ Download PDF: 22KB]
General details
Date: 22 December 1986 Investigation status: Completed 
Time: 1245  
Location:Gilberland Mine, 105km South of Georgetown Investigation type: Occurrence Investigation 
State: Queensland Occurrence type: Propeller/rotor malfunction 
Release date: 08 June 1988 Occurrence class: Technical 
Report status: Final Occurrence category: Accident 
 Highest injury level: Minor 
Aircraft details
Aircraft manufacturer: Cessna Aircraft Company 
Aircraft model: 182 
Aircraft registration: VH-TWM 
Type of operation: Private 
Damage to aircraft: Substantial 
Departure point:Gilberland Mine QLD
Departure time:N/A
Destination:Mareeba QLD
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