In addition, the astronauts will try to photograph the fine texture of the undisturbed lunar material. For this purpose, a closeup stereo camera is under development and may be ready for the first lunar landing mission.

The lunar samples, together with the astronauts and their spacecraft, will be brought back to the Lunar Receiving Laboratory (Houston) for a period of precautionary quarantine and other processing. Then the samples will be distributed to more than 135 investigators throughout the world. The data from their analyses and from the surface experiments will provide the first direct knowledge of the moon and its interaction with its environment.

Launch Vehicles.-One Saturn V was launched (Apollo 8), and prelaunch preparations were underway on two others, which were delivered to KSC during this period. Saturn V launch vehicle ground test activities continued to concentrate on the

problems identified by the flight of Apollo 6 in April 1968. The effort consisted of space vehicle vibration studies to determine allowable POGO induced oscillation; static and dynamic tests of the coupling effect on spacecraft/spacecraft LM adapter (SLA) resulting from such oscillations; and the resulting corrective action and modifications. Additionally, the structural qualification tests of the S-II stage lightweight structure were completed. The modifications to resolve the three technical problems experienced by Apollo 6 were flown on Apollo 8. They consisted of the pogo fix (injecting helium gas into a cavity in an existing prevalve at the lower end of the LOX feedline of the four outboard F-1 engines of the S-IC stage); redesigned fuel lines for the J-2 engine augmented spark igniter; and SLA structural corrections. (The last two modifications were also flown on Apollo 7.) Apollo 8 experienced no pogo during launch. While one flight without pogo is not absolute proof that it will not recur, it does provide added assurance that the F-1 engine fix is effective. The solutions to the J-2 Engine and SLA problems proved satisfactory on Apollo 7 and 8.

The first Saturn V launch vehicle with the lightweight S-II structure design is scheduled for launch in early 1969. The dry weight of this S-II stage and of subsequent S-II's is approximately 2200 pounds less than previous ones.

The S-IC-6 first stage completed acceptance tests in August, was shipped to Michoud, completed post static checkout in December, and is scheduled to arrive at KSC in February 1969. S-IC-7 was delivered to Mississippi Test Facility (MTF) where acceptance tests were completed in November. It was subjected to a long duration static firing to test the accumulator fix for the pogo problem. The stage was returned to Michoud for post static checkout and preparation for delivery to KSC. S-IC-8 was removed from storage, given a factory checkout, and sent to MTF for acceptance test. S-IC-9 completed factory assembly and checkout and was being readied for acceptance test. Stages S-IC-10 through 15 were being assembled at the factory.

Modifications, cryogenic proof pressure tests, and static firing were completed for the S-II-5 stage at MTF, and the stage was delivered to KSC in November. S-II-6 completed the same final acceptance tests and was in post static checkout for delivery to KSC at period's end. S-II-7 was delivered to MTF in November for the required acceptance testing. The remaining S-II stages-S-II-8 through 15-were in various stages of assembly and checkout.

The S-IVB-506 and 507 stages underwent acceptance tests and were placed in storage awaiting delivery to KSC. S-IVB508 remained in storage. S-IVB-509 was assembled, subjected to factory checkout, and placed in storage. The remaining three stages were in various stages of assembly.

Instrument Unit S-IU-505 completed retrofit and retest and was delivered to KSC in December. S-IU-506 and 507 were being retrofitted and retested, with delivery scheduled for early 1969, and 508 was in component assembly. Structural fabrication of units 509 and 510 was begun.

Quality and Reliability Assurance

The Apollo Quality and Reliability Assurance (Q&RA) effort concentrated on the readiness of hardware for the Apollo 7 and 8 missions. Q&RA teams reviewed more than 7000 nonconformances and corrective actions on Apollo hardware. They analyzed the criticality of 924 space vehicle single failure points and evaluated equipment certifications. Critical hardware items, which required verification prior to launch, were identified and reported to the Apollo Program Director and to the manned space flight centers. Each of the identified items was effectively cleared prior to launch. As a result, the assessed levels of quality and reliability were confirmed by the successful performance of the prescribed missions.

Apollo Q&RA also performed risk analyses for alternate Apollo 8 mission plans. These analyses concentrated on evaluating the life science aspects of extending the usage of hardware with a demonstrated earth orbit capability to the requirements of a lunar mission. Program Management used the results of these analyses in selecting the Lunar Orbit mission and in developing and refining mission operation improvements. These improvements included, among others, providing for on-board emergency manual navigational aids; additional planning for crew safety; and testing the S-Band communications and other selected systems.

APOLLO APPLICATIONS

The Apollo Applications Program (AAP) efforts progressed into the phase of final hardware and software development. The AAP objectives remain essentially those described in the 18th Semiannual Report (p. 29), except that the specific objective of extended lunar exploration, using Saturn V launch vehicles, was

transferred from AAP to the newly formed Apollo Lunar Explora tion Office. The Apollo Applications Program is designed to capitalize on the Apollo-developed capabilities and resources to accomplish additional scientific, technical, and medical investigations.

Missions

Because of financial limitations, NASA developed a "core program" with a limited number of Saturn IB launches planned and dropped the Saturn V Workshop from the list of planned missions. However, the flexibility remains to expand technical efforts beyond the "core program" at a later time.

The AAP missions are the Saturn I Workshop (launch of two Saturn IB vehicles); the Workshop revisit (single launch); the solar astronomy mission (launch of two Saturn IB vehicles); and the backup Saturn I Workshop or backup solar astronomy mission. These missions are described in detail in the 19th Semiannual Report (p. 22), and therefore only summarized here. (Fig. 1-12)

The Saturn I Workshop mission calls for the launch first of an unmanned Saturn IB with an S-IVB stage modified for use as living and working quarters, an airlock module, and a docking adapter. Then the manned Apollo CSM will be launched and will rendezvous and dock with the S-IVB stage. This mission is open-ended with consumables on board sufficient for 28 days. In the Workshop revisit mission, a single Saturn IB launches a three-man CSM to rendezvous and dock with the Saturn I Workshop remaining in orbit from the previous mission. Planned to last up to 56 days, the flight will test the ability of men and equipment to function for long periods in space.

The solar astronomy mission consists of two flights: the first, a Saturn IB launch of a three-man CSM with consumables for a 56-day stay; the second, a Saturn IB launch of the unmanned Apollo Telescope Mount (ATM) with its payload of solar instruments. Both will rendezvous and dock with the Workshop in orbit from the first mission. (Fig. 1-13)

Hardware is planned to be available to permit backup missions in the event of the failure of any of the flights that support the Saturn I Workshop mission or the solar astronomy mission. Backup hardware includes a Saturn I Workshop, including the associated airlock module and multiple docking adapter; a lunar module and Apollo Telescope Mount; one additional CSM; and two additional Saturn IB launch vehicles.

The schedule for the AAP missions has changed since the last report. The Saturn I Workshop mission slipped from a launch readiness in late 1970 to the last half of 1971; the solar astronomy mission slipped from 1971 to 1972.

AAP Management

The Apollo Applications hardware responsibility was realigned between Manned Spacecraft Center and Marshall Space Flight Center (MSFC) in order to make best use of available facilities and manpower. MSFC was assigned responsibility for modifying the lunar module ascent stage and for developing the airlock. Thus, MSFC has been assigned the following flight hardware: Saturn IB; lunar module ascent stage modification; workshop, airlock, and Multiple Docking Adapter (MDA); payload enclosure for workshop and Apollo Telescope Mount launches; Apollo Telescope Mount; and assigned experiments. MSC is responsible for the CSM and its required modification; for SLA; for manned launches; for crew systems; for medical equipment; for food; and for assigned experiments.