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 | 69
FOR SIMULATION USE ONLY – NOT A TRAINING AID
The canopy seal/anti-G electrical shutoff valve is controlled by the BLEED AIR
INFLOW switch. Power for this valve is provided through a circuit breaker,
placarded INFLOW SYS, on the battery bus circuit breaker panel in the front cockpit.
Absence of power leaves the valve closed.
After flowing through the shutoff valve, air proceeds to the heat exchanger for
cooling. A water separator is incorporated into the system to protect the anti-G
valves from contamination.
A safety valve automatically provides pressure relief if the pressure exceeds 7 psi.
A quick disconnect coupling for the anti-G suit hose connection and a test button
are provided on a control panel located on the left side console in each cockpit.
When the test button is pressed, the weighted rod is depressed allowing bleed air
to flow into the suit.
HEATING AND DEFOGGING SYSTEM
Engine bleed air for heating and defogging is tapped off the right side P3 port and
routed to the cockpit through the inflow and/or defog valves. Bleed air continues
through or bypasses the heat exchanger, then passes through the ECS portion of
the firewall shutoff valve and enters the cockpit through the defog outlets or the
foot warmers.
The routing of air in the two cockpits is based on the position of the vent control
lever, placarded AIR, located on the centre console in the front cockpit only. When
the vent control lever is set to CANOPY, air is routed to the windshield defog outlets
in the front cockpit and the canopy defog outlets in both cockpits.
Defog air is provided to the canopy from the mid-lever position and above. When
the vent control lever is set to FOOT, air is routed to foot warmer outlets in both
cockpits. The vent control lever mechanically positions a butterfly valve in the air
ducts in both cockpits to direct the air to the selected location.
The temperature of the air entering the cockpit is normally controlled automatically
between 60 and 90 °F as selected by the front cockpit pilot using the temperature
control switch placarded TEMP CONTROL.
This switch is a combination potentiometer and a three-position rotary switch. The
potentiometer portion of the switch, placarded AUTO, is used for automatic
temperature control. To increase cockpit temperature, rotate the switch toward
HOT, to decrease cockpit temperature, rotate the switch toward COLD.
Rotating the switch knob to the 6- o’clock position changes control to the manual
mode. In the manual mode, the rotary switch is spring loaded to off or null at the
manual position. Rotating the switch clockwise or counter clockwise toward COLD
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