Wing Anti-ice Switch #
DESCRIPTION – In flight, the three outboard slats on each wing are anti-iced with pneumatic bleed air. A single WING ANTI ICE switch controls a pneumatic shutoff valve in each wing. The valves are inhibited from opening on the ground, except for testing. They close automatically when a leak is detected and upon touchdown. When either wing anti-ice valve is open: EPR limit is automatically reduced and minimum idle RPM is increased. The valves close with a loss of electrical power.
OFF – When selected to OFF the ON light extinguishes and the wing anti-ice valves close.
ON – The WING ANTI ICE Switch controls the wing anti-ice system simultaneously on both wings. When selected ON:
- The ON light illuminates blue
- WING A. ICE message appears on ECAM MEMO display
- Wing anti-ice valves open if pneumatic supply is available
- On the ground, the valves open for 30 seconds only (test sequence)
FAULT – The WING ANTI ICE FAULT Light illuminates amber if the wing anti-ice valve position disagrees with selected position or if low pressure is detected. The FAULT light also illuminates momentarily when valves are in transit.
Engine Anti-ice Switch #
DESCRIPTION – Each engine nacelle is anti-iced by pneumatic bleed air. The engine anti-ice ducting is independent of the pneumatic system ducting. Each engine anti-ice valve is electrically controlled by the respective ENG ANTI ICE switch and is pneumatically operated. The engine must be running for the valve to open. When either engine anti-ice valve is open:
- Maximum N1 is limited
- Continuous ignition is provided
- Minimum idle RPM is increased.
The valves open with a loss of electrical power.
ON – The ENG ANTI ICE Switch controls the engine anti-ice system. When selected ON:
- The ON light illuminates blue
- ENG A. ICE message appears on ECAM MEMO display
- Engine anti-ice valves open if pneumatic supply is available
OFF – When selected to OFF the ON light extinguishes and the respective engine anti-ice valve closes.
FAULT – The ENG ANTI ICE FAULT Light illuminates amber if the engine anti-ice valve position disagrees with selected position. The FAULT light also illuminates momentarily when valves are in transit.
Probe/Window Heat Switch #
DESCRIPTION – The pitot probes, static ports, angle of attack probes, and total air temperature probes are electrically heated. Three independent probe heat computers automatically control the ground/flight modes and provide overheat protection and fault indications. The probes are automatically heated in flight, and on the ground when at least one engine is running. They can be operated manually prior to engine start by placing the PROBE/WINDOW HEAT switch ON. The TAT probes are not heated on the ground. Probe heat operates at low power on the ground, and automatically switches to normal power in flight.
AUTO – The AUTO selection (no lights) provides automatic heating of probes and windows in flight. On the ground if one engine is running windows and probes are automatically heated except for TAT probes.
ON – When the probe/window heat switch is selected to ON all probes and windows are electrically heated. The ON light also illuminates blue.
Engine Anti-Ice #
DESCRIPTION – Each engine nacelle is anti-iced by pneumatic bleed air. The engine anti-ice ducting is independent of the pneumatic system ducting. Each engine anti-ice valve is electrically controlled by the respective ENG ANTI ICE switch and is pneumatically operated. The engine must be running for the valve to open.
When either engine anti-ice valve is open:
- Maximum N1 is limited.
- Continuous ignition is provided
- Minimum idle RPM is increased
- The valves open with a loss of electrical power
