The Air Force Research Laboratory developed monopropellant, AF-M315E, has been selected for demonstration under the NASA sponsored Green Propellant Infusion Mission (GPIM) program. As the propulsion system developed by Aerojet-Rocketdyne for this propellant advances in maturity, studies have been undertaken to address the knowledge gaps in the adiabatic compression sensitivity of the propellant as it relates to the system parameters for this mission. Of particular interest is the sensitivity of the propellant at elevated temperatures and the resulting system peak pressures and dynamic response characteristics. For this study, an adiabatic compression U-tube apparatus was used to determine the driving pressure threshold levels of the propellant at elevated temperatures. These tests simulate the worst-case scenario resulting from a rapid closure or opening of valves in a propellant feed line in situ. The results of these tests are presented as a preliminary assessment on the margin of safety for the propellant.