Abstract
The failure investigation of an aircraft rear wheel gear hub at hood position was conducted to find the cause of fracture. The stereographs represented river pattern at crack initiation site originating from the preexisting cracks at the inner surface of hood. The metallurgical study showed the overaging of wheel hub material. Stress analysis by finite elemental analysis identified the stress concentration regions nearly at the same positions of wheel hub from where it was failed in reality. The SEM analysis of fracture surface represented that crack propagated by cleavage mode with microvoid coalescence at the eutectic and alpha-Mg interface. The overloading was a cause of final failure with visible features of chevron marks pointing back in the direction of crack originating site. (C) 2012 Elsevier Ltd. All rights reserved.