Development of a Procedure for Re-engineering of the Central Wing Component of a Commercial Aircraft

In this research, an investigation has been made to find out the reasons of failure occurred in the wing box connection of a commercial aircraft. The investigation consists of mechanical, metallurgical and fractographical tests. A procedure based on MIL-1530-C standard has then been developed for the purpose of re-engineering of the failed component to achieve a design with a higher performance. The results of this research emphasis that to get rid of the deficiencies in aeronautical structural components, an appropriate re-engineering procedure must be derived based on the original used design philosophy in conjunction with appropriate numerical and experimental tests. It is concluded that practical use of this standard can be a complicated task and therefore a refined methodology has to be derived instead based on the considered standard rules and judgments.