A case study is presented for the use of Relative Operation Sequence (ROS) command buffers to quickly execute a propulsive maneuver to avoid a collision with space debris. In this process, a ROS is custom-built with a burn time and magnitude, uplinked to the spacecraft, and executed in 15 percent of the time of the previous method. This new process provides three primary benefits. First, the planning cycle can be delayed until it is certain a burn must be performed, reducing team workload. Second, changes can be made to the burn parameters almost up to the point of execution while still allowing the normal uplink product review process, reducing the risk of leaving the operational orbit because of outdated burn parameters, and minimizing the chance of accidents from human error, such as missed commands, in a high-stress situation. Third, the science impacts can be customized and minimized around the burn, and in the event of an abort can be eliminated entirely in some circumstances. The result is a compact burn process that can be executed in as few as four hours and can be aborted seconds before execution. Operational, engineering, planning, and flight dynamics perspectives are presented, as well as a functional overview of the code and workflow required to implement the process. Future expansions and capabilities are also discussed.