Analysis of crack length and life flight cycle in center wing lower surface skin access hole aircraft with DCRACK software

Abstract

One of the problems in the aviation world is that accidents are increasing. The increase in incidents and accidents can be caused by several factors including human error, weather conditions, and failure of the structure / component of the aircraft. Accidents that occur from failure factors, one of which is caused by cracks that occur in the structure due to continuous loading which does not become more attention until the failure. In this final project an analysis of damage tolerance is carried out at the Wing Centre, Lower Surface and Skin Access Hole locations. The choice of location is because aircraft wings are the most important component in aircraft control while operating. Damage tolerance analysis is carried out as an effort to minimize failures in aircraft structures due to cracks that arise. Damage tolerance analysis is done by giving load in the form of an aircraft wing, then an analysis of the growth of crack length that occurs due to loading. The result of damage tolerance analysis will be obtained crack length, aircraft flight life cycle, and critical crack value. And in this study will also bring up a recommendation that is the right time to do the inspection interval.