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Ten firings of the Rocketdyne J-2 rocket engine (S/N J-2036-1) were conducted during two test periods (J4-1901-07 and J4-1901-08) on August 21 and 27, 1968, in Test Cell J-4 of the Large Rocket Facility. This testing was in support of the Saturn V vehicle. The firings were accomplished at pressure altitudes between 93,000 and 102,000 ft at engine start. The primary objective of these firings was to evaluate transient gas generator temperatures under simulated engine first burn and restart conditions. Transient gas generator temperatures, particularly on engine restarts were significantly reduced by utilizing a gas generator oxidizer supply line assembly which incorporated a geometrically different bellows section. The supply line assembly utilized on this series of firings had a 1.7 percent greater pressure drop at a flow of 3.5 lbm/sec. The total accumulated firing duration for these tests was 163 sec.