to move clear of the rocket and align itself. The CM would then separate from the Service Module (SM) and splash down. Mode III A Mode III type abort would be used when a Mode II type would risk the spacecraft coming down over land, or landing in the cold water of the North Atlantic. The CSM would separate from the rocket in the same manner as a Mode II abort, but would additionally use the SPS engine to make either a posigrade burn (Mode IIIA) or retrograde burn (Mode IIIB) to land in a specific area on the eastern side of the Atlantic. Mode III was only available as a primary abort mode for 10–15 seconds during a Saturn IB launch, and was only used as a backup abort mode for Saturn V launches, in case of an abort requiring the immediate landing of the spacecraft. Mode IV Was an abort mode that occurred during the S-IVB burn. Should the S-IVB fail the Service Module engine can place the CSM in Earth orbit to perform an Earth-orbit mission. Mode V A Mode V abort was only planned for use during the Apollo-Soyuz Test Project launch. In the event of an early S-IVB shutdown, the CSM RCS thrusters would be used to insert the entire stack (including the docking adapter) into orbit. The time window for a Mode V abort was only 1.5 seconds before nominal S-IVB cutoff. Saturn V Specific Abort Modes During orbital abort phases (S-IVB to COI, S-IVB to orbit and Mode IV), modes II and III were available as backup modes in the event of further problems. The EDS was enabled for the pad abort (beginning 5 minutes prior to launch) through abort mode IB phases. Beginning in mode IC, the EDS was switched off and aborts would have had to be commanded manually. S-IVB to COI ("Saturn IV-B (NASA's designation for the Saturn V's third stage burn) To Contingency Orbit Injection") In case of a failure of the S-II second stage, the stage would be jettisoned, and the rocket is high and fast enough that the S-IVB third stage, followed by the Service Module (SM) engine, has enough propellant to place the spacecraft in Earth orbit. There would not be enough propellant to perform trans-lunar injection, so only an Earth-orbit mission would be performed. S-IVB to Orbit The failing S-II would again be jettisoned, but