User:JustinTime55/sandbox/Apollo CSM infobox
 Apollo 15 Command and Service Module in lunar orbit | |||
| Manufacturer | North American Aviation North American Rockwell | ||
|---|---|---|---|
| Designer | Maxime Faget | ||
| Country of origin | United States | ||
| Operator | NASA | ||
| Applications | Manned lunar landing Skylab crew shuttle Apollo-Soyuz Test Project | ||
| Specifications | |||
| Launch mass | 32,390 pounds (14,690 kg) Earth orbit 63,500 pounds (28,800 kg) Lunar | ||
| Dry mass | 26,300 pounds (11,900 kg) | ||
| Payload capacity | 2,320 pounds (1,050 kg) | ||
| Crew capacity | 3 | ||
| Dimensions | 36.2 feet (11.0 m) high 12.8 feet (3.9 m) diameter | ||
| Volume | 218 cubic feet (6.2 m3) | ||
| Power | Fuel cells | ||
| Regime | Low Earth orbit Cislunar space Lunar orbit | ||
| Design life | 14 days | ||
| Production | |||
| Status | Retired | ||
| Built | 35 | ||
| Launched | 19 | ||
| Operational | 19 | ||
| Failed | 2 | ||
| Lost | 1 | ||
| Maiden launch | February 26, 1966 | ||
| Last launch | July 15, 1975 | ||
| Last retirement | July 24, 1975 | ||
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| Configuration | |||
 Apollo Block II CSM diagram
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