A5-21. 10 psi
A5-22. As high-g conditions occur, the anti-g valves activating weight is forced down to
close the exhaust valve and open the demand valve. This allows cooled engine
bleed air from the refrigeration system service heat exchanger to flow through
the anti-g valve, where it is regulated, to inflate the g-suit. Pressure to the g-suit
is varied in proportion to the g-force acting upon the aircraft and crewmembers,
to a maximum of 10 psi. As g-forces decrease, the activating weight is forced
upward by spring tension. This reduces the pressure of the airflow to the g-suit
and exhausts excess suit pressure into the cabin. As this occurs, the demand
valve closes, blocking air from the g-suit.
A5-23. Provides a measure of personal comfort, offsetting the discomfort caused by the
wearing of the anti-exposure suit or heat created by cockpit equipment and
resulting high-temperature ambient air
A5-24. In a manifold downstream of the vent suit temperature valve
A5-25. Vent suit temperature valve, over-temperature sensor, pressure regulating valve,
pressure relief valve, and air hose assembly
A5-26. Automatic and manual
A5-27. Circulates liquid coolant to remove heat from the radar transmitter high-voltage
RF energy modules
A5-28. Ground cooling fan
A5-29. Cooling liquid-to-air heat exchanger, liquid coolant pump, airflow valve, ground
cooling fan, coolant system filter, low-pressure sensor, high-temperature sensor,
and coolant temperature sensor
A5-30. The ground cooling fan is electrically powered and supplies a flow of ambient air
for heat transfer from the liquid cooling heat exchanger during aircraft ground
operations.
A5-31. It is a more efficient extinguishing system than CO2, and under normal
atmospheric pressure and temperature, it is odorless and tasteless.
A5-32. Two
A5-33. Two inlet ports and one outlet port, and a poppet that shuts off one inlet port
A5-34. 400 (+20, -15) cubic inches
A5-35. If a fire is indicated in no. 3 engine nacelle, pull no. 3 engine emergency handle
aft and press the no. 3 engine fire-extinguishing discharge button. If the fire
persists and it becomes necessary to discharge the second container of the same
fire-extinguishing system into no. 3 engine nacelle, the transfer switch, which is
guarded and shear-wired in the DIRECT TO ENGINES position, must be set to
TRANSFER TO ADJACENT ENGINES, and the no. 3 engine fire-extinguishing
discharge button must be pressed again. This action electrically ignites
the cartridge in the transfer container valve assembly of the second
fire-extinguishing container in that system.
A5-36. Provides detection and extinguishing for the APU compartment on the ground
and in flight
A5-37. A horn sounds and a warning light illuminates
A5-38. To contain and transport the regulated, filtered, dry air to the radar and
electronic countermeasures (ECM) waveguide cavities
5-31
