In this paper, we present a variable structure based sliding mode controller for recovery of an aircraft from spin. The spin recovery problem is formulated as a two point boundary value problem where the two points, different steady states of the aircraft, are obtained from a bifurcation analysis of the aircraft model. Using the bifurcation analysis results of the aircraft, the spin states of aircraft are identified. Once the aircraft enters into spin, the controller is activated to bring it back to a desired state which is a level flight trim solution also found from a bifurcation map of the aircraft model.