The command module (CM) would now be required to provide the crew with a one-day habitable environment and a survival environment for one week after touching down on land or water. In case of a landing at sea, the CM should be able to recover from any attitude and float upright with egress hatches free of water.
The service propulsion system would now provide all major velocity increments required for translunar midcourse velocity corrections, for placing the spacecraft into a lunar orbit, for rendezvous of the command and service modules CSM with the LEM on a backup mode, for transfer of the CSM from lunar orbit into the transearth trajectory, and for transearth midcourse velocity corrections for lunar missions.
Three FIST-type drogue parachutes would replace the original two called for in the earth landing system.
The CM camera system was revised to require one for monitoring the crew, displays, and spacecraft interior; the other for lunar photography and stellar studies. The latter camera could be used in conjunction with the telescope or independently at the crew's discretion.
A new communication concept was described in which all voice, telemetry, television, and ranging information for near-earth and lunar distances would be transmitted over a unified frequency system.
All references to the lunar landing module and space laboratory module were dropped. Among other deletions from the previous Statement of Work were:
- Parawing and other earth landing systems instead of parachutes
- The "skip" reentry technique
- HF beacon as recovery aid
- Radar altimeter from CSM communication system
- Crew recreational equipment
- Engineering and Development Test Plan