Recent work on bonded crack retarders for aerospace structures has demonstrated how they offer advantages in improvement in fatigue life. We have previously studied the residual stresses in aluminium plates with a bonded strap attached only by an adhesive layer. Residual stress is generated because of the misfit in coefficient of thermal expansion between the strap and the substrate. However, in application the straps are likely to require additional bolt or rivet fixtures in order to ensure integrity in the case of adhesive disbond. In this experiment we will investigate the stresses generated in a crack retarder structure with a cold worked fastener hole.