Apollo Service Module Question!?

I want to find out the chamber pressure of the Service Propulsion System or the main engine of the service module. I have found out the propellants used for the engine that are: Dinitrogen tetroxide and Aerozine 50 are hypergolic propellants. I would like to know it in atmospheres, if possible. For example, the SSME has a chamber pressure of 186.922 atm and the F-1 engine has a chamber pressure of 69.085 atm. This are just approximations not exact measurements. Thank you for your time.