In this work we investigate end-of-life trajectories for spacecraft in orbit about the Sun-Earth L 1 and L 2 libration points. A plan for decommission is often re- quired during the mission design process. We study the spacecraft's natural dynamics in both a high- delity model and the circular restricted three-body problem. In particular, we consider the role of the unstable manifold and forbidden regions in determin- ing disposal outcomes. A simple maneuver scheme to prevent returns to the Earth vicinity is also an- alyzed. We include discussion on potential collision orbit schemes.