Rationale in detail was:
Two tests to simulate an abort on the pad. The purpose of these tests was to qualify the launch escape system and its associated sequencing.
Suborbital (Little Joe II test launch vehicle):
Three suborbital tests with the objective of development and qualification of the launch escape system and qualification of the command module structure. Test conditions would include maximum dynamic pressure for the launch escape system and module structure testing and high atmospheric altitudes for launch escape system testing. The latter test requirement was being reviewed.
Current Apollo requirements for the Saturn developmental flights were to determine launch exit environment on SA-6 with SA-8 as backup. Requirements on launch vehicles SA-7, SA-9, and SA-10 were to flight- test components of or the complete emergency detection system.
Four launch vehicle development flights prior to the manned flight. Flight test objectives for the unmanned flights were one launch environment flight with a spare and two launch vehicle emergency detection system flights.
Six unmanned Saturn C-5 launch vehicle development flights. Flight test objectives were two launch vehicle emergency detection system flights, one spacecraft launch environment flight, and three reentry qualification flights. Preliminary objectives of manned flights were completion of the lunar excursion module qualification, lunar reconnaissance, and lunar exploration. Although the first C-5 manned flight was scheduled as the seventh C-5, a spacecraft suitable for manned flight would be available for use on the sixth C-5 to take advantage of possible earlier development success.