Five firings of the J-2 rocket engine were conducted in Test Cell J-4 of the Large Rocket Facility. The firings were accomplished at pressure altitudes ranging from 104,000 to 112,000 ft at engine start to evaluate engine starting characteristics at the minimum main oxidizer valve sequence ramp limit and reduced fuel pump net positive suction head. These firings were in support of the S-2 vehicle application for Saturn flights. Engine components were thermally conditioned to predicted values for the S-2 interstage/engine environment. Satisfactory engine operation was obtained. The accumulated firing duration was 56.22 sec.


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