Test of separable warhead. Range achieved 200 km. Ballistic launch. Expected range 210 km. Launched at 0612 local time. The launches were first made public by Tass on March 27, 1958: 'In May 1949 a single-stage Russian rocket attained an altitude of 109 km with an instrument payload of 120 to 130 kg'. References: 283 , 344 .
Check power plant, controls, performance, and skill temperatures; upper-air pressure, density, winds, ionisation; cosmic rays; photography research. Launched at 1000 local time. Reached 219 km.
Albert C. Hall of The Martin Company proposed to Robert C. Seamans, Jr., NASA's Associate Administrator, that the Titan II be considered as a launch vehicle in the lunar landing program. Although skeptical, Seamans arranged for a more formal presentation the next day. Abe Silverstein, NASA's Director of Space Flight Programs, was sufficiently impressed to ask Director Robert R. Gilruth and STG to study the possible uses of Titan II. Silverstein shortly informed Seamans of the possibility of using the Titan II to launch a scaled-up Mercury spacecraft. References: 16 .
In initial study contracts, Martin proposed vehicle similar to the Apollo configuration that would eventually fly and closest to STG concepts. GE proposed design that would lead directly to Soyuz. Convair proposed a lifting body concept. All bidders were influenced by STG mid-term review that complained that they were not paying enough attention to conical blunt-body CM as envisioned by STG. References: 26 , 27 .
NASA announced that the Mercury-Atlas 7 (MA-7) manned orbital flight would be delayed several days due to checkout problems with the Atlas launch vehicle. References: 483 .
Launch escape system (LES) installation for CSM 009 was completed, marking the first LES completion. References: 16 .
A September 1968 flight test was planned. However the first stage LOX tank developed hairline cracks during ground tests. 4L was removed from the pad in June 1968. The first stage was cannibalized; the upper stages were incorporated into the 1M1 mockup for further training of the launch crews. References: 96 .
Retrieved Intelsat 6 and attached new SRM. First active dual rendezvous of two orbiting spacecraft (Endeavour and Intelsat-Vl) First deployment of a drag chute on the orbiter fleet. Payloads: Intelsat-Vl reboost mission hardware, Assembly of Station by EVA Methods (ASEM), Commercial Protein Crystal Growth (CPCG), Air Force Maui Optical Site (AMOS) Calibration Test, Ultraviolet Plume Instrument (UVPl). Additional Details: STS-49. References: 1 , 2 , 5 , 6 , 7 .
Geostationary at 148.0 degrees W.