Bar talk I fear dagenham. From the flight manual.
The cockpit is normally pressurised to either 10,000 or 26,000 feet with air bled from the engines ninth stage compressor. 26,000 is preferred as it allows greater airflow through the cockpit and enhances cooling. Cockpit temperature can be controlled by rheostat between 40 and 100°F. A duct high temperature limit sensor operates with AUTO TEMP selected to limit cockpit air to a maximum of 126°F. A high limit switch is also provided which limits cockpit air to 155°F in auto or manual control.
The aircraft has 600 cc (enough for 16 injections) of Triethylborane (TEB) carried in a tank on each engine. TEB will burn spontaneously with exposure to air above –5°C and is injected into the combustion chamber to light the JP-7 fuel on engine start and also whenever afterburner is selected. Catalytic igniters attached to the afterburner flame holders tend to maintain afterburner operation after initial ignition.
At sea level static conditions, military thrust is approximately 70% of maximum thrust. At high altitude military thrust is approximately 28% of the maximum thrust available.
Minimum afterburner thrust is approximately 85% of maximum afterburner thrust at sea level and approximately 55% at high altitude.
Aircraft carries 262 liters of liquid nitrogen for fuel tank pressurisation and inerting (to prevent autogenous ignition). Each hydraulic reservoir (4 off) is pressurised by separate gaseous nitrogen bottles.