I A P 2 0 2 3 . 0 0 1 - A F M / I R I S T E X A N I I P A G E | 68
FOR SIMULATION USE ONLY – NOT A TRAINING AID
shutoff valve (inflow valve) and bi-level flow control bypass valve (defog valve),
respectively, and are located in the front cockpit only.
Power for both the defog valve and the inflow valve is provided through the INFLOW
SYS circuit breaker on the forward battery bus.
The BLEED AIR INFLOW switch is a three-position switch placarded HI, NORM, and
OFF. This switch controls the position of two solenoids on the inflow valve.
In the OFF position, both solenoids are de-energized and the valve is closed. In the
NORM position, one solenoid is energized allowing the inflow valve to partially
open. When the switch is set to HI, the second solenoid is energized and airflow
through the valve increases.
When the air conditioning compressor is operating and the aircraft is below 7500
feet MSL (pressurization no longer required) the inflow valve is automatically
closed regardless of the position of the BLEED AIR INFLOW switch. This improves
cooling performance by eliminating warm bleed air from the airflow into the cockpit
environment.
When the DEFOG switch is set to ON, the inflow valve is fully opened to maximize
the volume of bleed air entering the cockpit.
The ECS has two temperature sensing sources downstream of the heat exchanger
to alert the pilot of over temperature conditions in the ECS ducting. A 300 °F
temperature switch is located at the rear distribution valve aft of the front ejection
seat. Another 300 °F temperature sensor is located upstream of the defog selector
in the environmental system duct near the firewall. If the bleed air temperature at
either sensor location exceeds 300 °F, an amber DUCT TEMP caution will illuminate.
A manually actuated shutoff valve is located at the firewall. The valve is connected
by linkage to the hydraulic system shutoff valve and is actuated, along with the fuel
system shutoff valve, by pulling the FIREWALL SHUTOFF handle in the front cockpit
on the left console panel.
CANOPY SEAL AND ANTI-G SYSTEM
An anti-G system provides partial protection against the physiological effects of
high G manoeuvres. The system utilizes engine bleed air to supply pressure to each
pilot's anti- G suit. Each anti-G valve has a weighted rod with an orifice which is
displaced toward full open by gravity during positive G acceleration.
As the weighted rod moves further open with increasing G, the pressure in the anti-
G suit increases proportionally.
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