The Shuttle version of the NAVSTAR Block II Global Positioning System (GPS) Space Vehicle (SV) will be injected into the transfer orbit with a Perigee Kick Motor (PKM) contained in an attached PAM-DII stage. Mission “drift” orbit injection will occur near the 4th apogee of the transfer orbit with an Apogee Kick Motor (AKM) burn. Final mission orbit will be attained following any necessary corrections by the Reaction Control System (RCS) which will also be used throughout the SV lifetime for orbit maintenance. A primary concern in the transfer procedure is GPS/PAM-DII separation following PKM burnout because of the possibility of SV and PAM-DII recontact if large coning angles have developed during the burn. Hence, initial flights will need substantial instrumentation to monitor PKM burn and separation data. The most desirable method of instrumentation readout is by telemetry transmission to an Air Force Remote Tracking station (RTS). This paper shows that the PKM burn can be planned to occur within the field of view of an RTS within the desired look angle constraints. A detailed example and an extensive series of mission planning charts are also provided.