This paper reviews some of the advances that have been made in stress analyses of the mounting brackets of aircraft component. Finite Element Analysis is implemented to calculate stress-intensity factors precisely for finding pits instructures. Observations of small-crack behavior at open and rivet-loaded holes and the development of small-crack theory have leads to the prediction of stress-life performance for components with stress concentrations under aircraft spectrum loading. By using the technique called crack-closure concept crack growth can be easily monitored in the aircraft structures. These advances are helping to assure continued safety of aircraft structures the main motivation is that to increasing the life of the material used for mounting brackets for structural application. i.e. increases the No. of cycles to failure (Nf) of the material.

Mounting Bracket, glass fibre, epoxy resin, rivet-loaded holes, crack growth, fatigue life.