Engine Model: Dual Mode-Liquid Apogee Engine. Designer: TRW. Propellants: MON/Hydrazine. Thrust(vac): 454 N (102 lbf). Isp: 315 sec. Burn time: 3,600 sec. Mass Engine: 4.80 kg (10.50 lb). Diameter: 0.30 m (0.99 ft). Length: 0.56 m (1.84 ft). Chambers: 1. Chamber Pressure: 7.00 bar. Area Ratio: 204.00. Thrust to Weight Ratio: 9.58. Country: USA. Status: In Production. First Flight: 1991. First Flight: April 1991. Mounting: fixed. Engine Cycle: pressure-fed at 15 atm. Oxidizer: MON 3-flow rate at 0.076 kg/sec. Fuel: high purity hydrazine-flow rate at 0.071 kg/sec. O/F Ratio: 1.070:1. Cooling Method: radiation. Ignition: hypergolic with initiation at 28 V electrical to an on/off bi-propellant torque motor valve. Burn Time: 24,000 sec total, with a 3600 sec maximum single burn.