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Atlas MA-3
Part of Atlas MA engine series Family
LOx/Kerosene propellant rocket stage. .

Status: Retired 1995. Thrust: 1,644.96 kN (369,802 lbf). Gross mass: 3,174 kg (6,997 lb). Unfuelled mass: 3,174 kg (6,997 lb). Specific impulse: 290 s. Specific impulse sea level: 256 s. Burn time: 120 s. Diameter: 4.90 m (16.00 ft). Span: 4.90 m (16.00 ft).

No Engines: 2.



Country: USA. Engines: LR89-5. Launch Vehicles: Atlas Centaur LV-3C, Atlas E, Atlas E CGM-16E, Atlas F HGM-16F, Atlas SLV-3 Agena B, Atlas Agena B, Atlas F, Atlas SLV-3 Agena D, Atlas SLV-3, Atlas F/Trident, Atlas E/Trident, Atlas F/PTS, Atlas F/MSD, Atlas F/SVS, Atlas F/Agena D, Atlas F/OIS, Atlas E/MSD, Atlas E/SVS, Atlas E/SGS-2, Atlas E/OIS, Atlas E Altair. Propellants: Lox/Kerosene.

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