This specification established the requirements for a 5 second duration, 4500 pound thrust (when determined at 60°F) solid propellant rocket engine hereinafter specified as 5 S-4500.
This specification covers pressure boundary layer control systems of turbo-jet and turbo-prop aircraft for increasing the aerodynamic lift of the wings and flaps during approach, landing, and takeoff.
This specification covers the design requirements and configuration of letters, numerals, and identification for aircrew station displays and control panels.