Five firings of the Rocketdyne J-2 rocket engine (S/N J-2047) were conducted in Test Cell J-4 of the Large Rocket Facility. These firings were accomplished during test period J4-1801-16 at pressure altitudes of approximately 100,000 ft at engine start to investigate S-II/S-V (1) fuel pump operation during the start transient at lower than minimum model specification inlet pressure, (2) thrust chamber pressure buildup rate with low starting energy, and (3) gas generator and augmented spark igniter temperature transients with warmest and coldest expected thrust chamber temperatures as predicted from the AS-501 countdown demonstration. Engine operation was satisfactory for all firings. The accumulated firing duration was 46.2 sec. (Author)


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