This paper introduces the concepts utilized for the integration of a cryogenic capillary pumped loop into a flight experiment. The Cryogenic Capillary Pumped Loop (CCPL) version V, which was recently manufactured (9/97), is to be integrated into the Cryogenic Thermal Storage Unit (CRYOTSU) flight experiment as a secondary experiment. CRYOTSU, a Get-Away-Special (GAS) Can experiment, is currently manifested on STS-95 with an anticipated launch date of October 1998. The CCPL uses nitrogen as the working fluid with a 70-120 K operating temperature. The primary benefit of the CCPL is as a heat transport device in cryogenic bus systems. The primary issue of structurally supporting the CCPL while reducing parasitic heat loads will be detailed.