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Five firings of the J-2S rocket engine were conducted in Rocket Development Test Cell (J-4) on July 17, and 29, 1969. These firings were accomplished at pressure altitudes ranging from 85,000 to 101,000 ft at engine start. The primary objectives of these test periods were to (1) determine if main-stage conditions which existed during sea-level testing of engine S/N J-113 would result in similar abnormal oxidizer dome vibrations in the 4400- to 4700- Hz frequency range during altitude testing of engine J-112-E, (2) evaluate high thrust idle-mode operation with a simulated full-face oxidizer flow injector configuration, and (3) document effects of closing the thrust chamber bypass valve during high thrust idle-mode operation. Altitude testing did not result in abnormal (greater than 100 grams) oxidizer dome vibration in the 4400- to 4700- Hz range during test period 04. The thrust chamber bypass valve closing resulted in a 65 F increase in fuel injection temperature; however, stabilized high thrust idle-mode operation was not attained during test period 05.