In this paper, Fracture Mechanics is used to predict debonding propagation in adhesive joint between aluminum and composite plates. Three types of loadings (lambda=0, lambda=0.5, and lambda=1 when lambda is the ratio of lateral to in-plane loading) and two types of glass-epoxy composite sequences: [0/90](2s) and [0/45/-45/90](s) are considered for the composite plate and their results are compared. It was seen that generally the cases with stacking sequence of [0/45/-45/90](s) have much shorter lives than cases with [0/90](2s). It was also seen that in cases with lambda=0, the ends of the debonding front propagates forward more than its middle, while in cases with lambda=0.5 or lambda=1 it is vice versa. Moreover, regardless of value of lambda, the difference between the debonding propagations of the ends and the middle of the debonding front is very close in cases lambda=0.5 and lambda=1. Another main conclusion was that the non-dimensionalized debonding front profile is almost independent of sequence type or the applied load value.