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The most highly loaded frames of the newly developed Airbus A400M transport aircraft have glass reinforced aluminium laminate (Glare) straps attached to them to increase their resistance to fatigue damage. These straps were designed using static strength requirements for the frame. Basic justification was done in two steps. Firstly, the frame load was divided between frame and flange on the basis of in-plane stiffness of these parts. Secondly, a fatigue analysis was performed on the strap using an empirical model for fatigue of Glare laminates under tension. This report contains a thorough explanation of the development of a code which can be used to analyse the fatigue crack initiation and propagation characteristics of the combination of frame flange and Glare strap at once under variable amplitude loading. The choice was made for a modular implementation of a combination of analytical models. This allows the programme to analyse a large variety of cases and allows it to be adapted easily in the case it is decided to continue its development. The fatigue crack initiation model works in three stages. First, it computes the highest stress cycle occurring in the metal sheets of the laminate, second, it corrects this cycle to match the available SN-data, and third, it finds the corresponding cycles to initiation using the nearest matching SN-curve. Fatigue crack growth calculations are based on an analytical model which applies displacement compatibility at the delamination boundary, to solve for the crack tip stress intensity and subsequently calculate crack- and delamination growth characteristics. These displacements originate from four phenomena …