In the design of advanced two-phase capillary pumped loop heat transport systems for Space Station elements, evaporator plates able to accommodate a wide variety of instruments/payloads are becoming critical items. An evaporator plate configuration consisting of six parallel capillary evaporator pumps bonded into a common aluminum cold plate has been selected under a NASA Goddard Space Flight Center (GSFC) Focussed Technology program.* Predicted performance characteristics include a power density capability greater than 10 W/cm2, a transport capacity of over 5 kW (per 900 cm2 plate), turndown capability of over 16:1, and load-sharing capability (within a closed system). Following proof-of-performance tests, these plates will form part of a thermal test bed at NASA/GSFC. This paper details the design and analysis of the prototype capillary cold plates along with the proposed fabrication and test plans. Although the first prototype capillary cold plate (PCCP) unit is under construction, it seems that the present PCCP baseline design will meet the specified requirements. A section is also devoted to the evaluation of payload accommodation aspects and future design evolution of capillary pumped loop two-phase evaporator plates.