There is increased motivation to extend the service life of high-value components within the aeroengine industry. Repair strategies are being developed to repair previously unrepairable components, removing the need for replacement. Laser deposition is being increasingly used to repair components that have been damaged in-service. The process allows complex deposition strategies to be used leading to flexibility in the repair strategy. This work will form part of a project to develop a validated FE model of the deposition process that can be applied to the repair of aeroengine components, allowing parametric studies to be carried out and optimum repair strategies to be selected. The objective of this proposal is to validate the model by measuring the residual stresses in two IN718 laser deposition samples on thick IN718 plates that have utilised two common deposition strategies.