This paper is focused on determining the initial conditions that are to be used for proximity operation maneuvers for orbital transfers in three-body periodic orbits, including lunar halo orbits and Mars-Phobos Distant Retrograde Orbits (DROs). In order to generate such initial conditions, orbital transfers from Earth to the aforementioned orbits are briefly presented here with an emphasis on the arrival uncertainty. The uncertainty in ∆V generated by propulsion systems of spacecraft is propagated up to the nominal orbit insertion location. This gives an idea on what the initial conditions for the proximity operations phase would be and what maneuvers the spacecraft is expected to perform for proximity operations upon final approach. Here, Time-of-Flight, TOF, is an independent variable and can be seen as a design parameter subject to the constraints provided by the aforementioned initial conditions of the chaser vehicle with respect to the target vehicle. Examples of ∆V-optimal solutions are also shown along with pork chop-like plots for proximity operations, called prosciutto plots. These plots allow mission designers to consider proximity operation maneuvers for the planned operations for various potential departure and arrival windows, giving flexibility and risk management in case the nominal maneuvers are compromised.