separated from the S-IVB stage about three hours and fifteen minutes ground elapsed time (GET).

The alternate mission selected used the service propulsion engine to transfer the spacecraft from the initial S-IVB insertion orbit into a highly eliptical orbit. The earth intersecting eliptical orbit achieved, following the 445-second firing of the service propulsion engine, had an apogee of 12,020 nm and a potential perigee of 18 nm. Engineers had hoped to fire the service propulsion engine a second time. However, the first firing consumed too much fuel. As a consequence, the desired reentry velocity could not be obtained. At 400,000 feet, the reentry conditions were a velocity of 32,819 ft/sec and a flightpath angle of 5.84 compared to the planned conditions of 38,243 ft/sec and 5.8°.

The spacecraft landed within 50 miles of the onboard targeted landing point, was recovered by the U.S.S. Okinawa, and was found to be

in good condition (including the crew hatch). Charring of the Command Module thermal protection appeared similar to that on the Apollo 4 spacecraft. Overall performance of the Command and Serv ice Module was excellent.

As to the operational support for the launch, the countdown was completed without an unscheduled hold. Ground system performance was highly satisfactory. The relatively few problems encountered in countdown were overcome so that vehicle launch readiness was not compromised.

Launch damage to the complex and support equipment was minor. Modifications to the ground systems after launch of AS 501 were effective in reducing the amount of blast damage to a level below that sustained during the AS 501 launch.

Tracking and data network performance was satisfactory during the mission. Only minor problems were encountered, and none affected mission operations.

Apollo 7 Mission

Apollo 7 is to be the first manned Apollo mission. This will be a Command and Service Module operations mission and will use a Saturn IB vehicle. The primary objectives are to demonstrate CSM/ crew performance, to demonstrate crew/space vehicle/mission support facilities performance during a manned CSM mission, and to demonstrate CSM rendezvous capability.

The launch vehicle is to place the manned CSM in an elliptic orbit. The CSM will separate from the S-IVB on the second orbit, using the SM Reaction Control System. After separation, the CSM is to perform a transposition maneuver, followed by a simulated docking with the S-IVB stage. Primary emphasis during the orbital operations period will be on demonstrations of subsystems operations.

The SM propulsion system is to perform the nominal de-orbit burn. Touchdown is planned to occur in the Atlantic, near Bermuda.

The Saturn IB 205 launch vehicle stages and components will be the final design configuration, except that engine thrust will not be at the uprated level. The Block II Command and Service Modules will contain R&D instrumentation, and will have the unitized crew couch. The modified Block I Adapter will contain acquisition lights and a docking target. A tiebar will replace the Lunar Module in the Adapter. The Launch Escape System will be the final configuration. A TV camera will be carried in the Command Module.

Experiments.-Experiments in synoptic terrain and weather photography, bone demineralization, cytogenetic blood studies, and lower body negative pressure will be performed.

Operations.-Factory checkout in preparation for delivery of the S-IB-5 stage to KSC started on January 2, following block modifications. The Apollo 7 space vehicle stages, instrument unit, service module, and Command module were received at KSC between March 28 and May 30. The launch vehicle was erected on launch complex 34 on April 18.

When the CSM arrived at KSC, it was placed in the vacuum chamber for simulated altitude tests and combined systems testing before being mated with the launch vehicle. Several problems were encountered in these pre-launch checks of this first Block II command and service module. An oxidizer spill during reaction control system (RCS) hypergolic fuel hot flow tests contaminated some antennas, cables, and connectors in the instrument unit, and replacement was necessary. Several RCS leaks in the spacecraft caused some delays. At the end of this reporting period, the spacecraft was in the vacuum chamber, and preparations for the manned altitude tests were underway. Launch vehicle pre-launch checks were progressing satisfactorily. Apollo 8 Mission

The Apollo 8 (AS-503) mission was being planned as the first in the CSM-LM Operation phase. While plans called for it to be the first manned Saturn V space vehicle, NASA would retain the alternative to revert to an unmanned mission if necessary. The mission's primary objectives would be to demonstrate crew/space vehicle/mission support facilities performance during a manned Saturn V mission with a CSM and LM; to demonstrate LM/crew performance; and to demonstrate performance of planned and backup lunar orbit rendezvous mission activities. These activities would include pre-translunar injection procedures, transposition, docking, LM withdrawal, intravehicular and extravehicular crew transfer, docked service and descent propulsion systems burns, and LM active rendezvous and docking.

The launch vehicle would place the manned spacecraft in a circular orbit. The CSM would then separate from the launch vehicle, turn around, dock, and perform LM withdrawal. Several tasks would be performed while in orbit. These include unmanned S-IVB restart, extravehicular crew transfer, docked DPS and SPS burns, staging with the LM manned and separated from the CSM, LM active rendezvous, and an APS burn with the ascent stage unmanned and separated from the CSM. CSM and LM orbits throughout the mission would not exceed 300 nm altitude. Activity subsequent to the fifth day would involve the CSM only.

The AS-503 launch vehicle would be equipped with R&D instrumentation. The S-II stage structure would be of the heavyweight design, and engine thrust would not be at the uprated level. The spacecraft, adapter, and launch escape system would be in the final configuration but with R&D instrumentation added to the spacecraft.

The launch vehicle stages and a Boilerplate spacecraft, BP-30, for an unmanned mission were in pre-launch checkout at KSC on January 1. The launch vehicle stages were mated in the Vertical Assembly Building and the boilerplate spacecraft was added. Pre-launch preparations for an unmanned mission were proceeding satisfactorily.

However, following assessment of the Apollo 6 mission, NASA decided to plan and prepare for a manned mission on Apollo 8, though still retaining the capability to fly unmanned. Subsequently, the launch vehicle was demated, and the second stage (S-II-3) was shipped to the Mississippi Test Facility for cryogenic proof pressure testing, a test constraining manned flight.

All planning was revised to prepare for the possible manned flight. The S-II-3 cryogenic proof pressure test was successfully completed. To reduce spacecraft loads during S-IC F-1 engine shutdown, a decision was made to cant the outboard or control engine 2° at T+15 seconds through S-IC cutoff (for SA 503 and subsequent launch vehicles). An F-1 engine had to be replaced because of a fuel leak in the turbopump main fuel seal.

Meanwhile Lunar Module No. 3 arrived at KSC in mid-June and was placed in work stands for initial pre-launch checks. During leak checks, leaks were experienced around some flanges. Steps were being taken to solve this problem.

Development and Test

The Apollo space vehicle design was rapidly approaching maturity as modifications resulting from the Apollo 204 accident review and from the initial flight of the Saturn V launch vehicle were being incorporated and confirmed through test. Significant test and required modification activity was underway on spacecraft structure and launch vehicle first stage propulsion. This work was primarily aimed at controlling longitudinal oscillations of the vehicle.

Command and Service Module.-The extensive design and test procedure changes resulting from the Apollo 204 accident continued to be implemented. The additional changes and related retesting further delayed the Apollo Program; the Spacecraft continued to be the pacing item in the program.

The command and service module design was verified by therrial/ vacuum testing with no major changes required prior to manned flight. The command and service module inflammability tests, initiated following the AS-204 accident, were completed. From these tests, the Agency decided that a safe spacecraft atmosphere could be 95 percent oxygen at 6.2 psia or 60 percent oxygen/40 percent nitrogen at 16.2 psia. Spacecraft launch atmosphere will be 60/40 at 16.2 psia. After lift-off the environment would gradually change to almost 100 percent oxygen at 5.0 psia at or near orbit insertion.

Acoustic and vibration tests were conducted to evaluate the ability of a crewman to perform tasks in a Saturn V simulated launch environment. Test vehicle CSM-105/AV was used for these tests. A successful manned low-frequency vibration test with Astronaut Gordon Cooper completed the series of tests.

Qualification of the two drogue/three main parachute configured Earth Landing System (ELS) was nearing completion. Water impact testing designed to demonstrate the ability of the command module to land in water, even though landing velocities were increased slightly because of weight increases, were progressing satisfactorily. And the CSM structural test program was nearing completion.

To validate the Block II Service Module propulsion system, three static firings were conducted using SM 102. One 10-second and two 60-second firings were successfully accomplished. Based on the satisfactory results of these firings, NASA concluded that a static firing of SM-101, to be used in Apollo 7, would not be required.

Manufacturing of Command and Service Modules 103 and 104 was completed. Both spacecraft were well into factory checkout by the end of June. CSM-103 was to be delivered to Kennedy Space Center in August for the second manned Block II mission. CSM 106 should be undergoing factory checkout in mid-July. The remaining flight vehicles were in various stages of manufacture. Command and Service Modules 104 and 106 should be delivered to Kennedy Space Center in the second half of 1968. Manufacturing completion rates were averaging one CSM every two months. (Fig. 1–5.)

Lunar Module-During the first half of 1968 several major milestones were accomplished in the lunar module (LM) program. At the beginning of the year Lunar Test Article 8 was in vacuum chamber B at MSC undergoing thermal/vacuum tests constraining the LM-3 mission (the first manned LM flight). The structural test article, LTA-3, successfully completed man-rating drop tests at the contractor's facility. Subsequently, it was transported to MSC for use in the