When in-service related damage is discovered how do we determine the critical crack size or the remaining service life of the component.
BEASY’s fracture modeling tools were used to create a model of the actual rotor hub and a crack growth analysis was performed using realistic fatigue spectrum loading. An initial flaw located on the inside bore of the lug hole was propagated fully automatically including the transition from a part-through to through thickness crack.
BEASY provided the capability to obtain accurate (and realistic) fracture mechanics solutions. As a result inspection intervals were improved and better management decisions made with regard to the use of the aircraft.