Airbus A320 Cockpit Tour: #23 - Anti Ice Panel: What do all those buttons do?!

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In this video we will cover the anti icing section of the overhead panel. Sorry guys I forgot to talk about the fault lights in the segment! Here are the details on what they mean for each button:

(1) WING ANTI ICE pb sw
This switch controls the wing anti ice system on the left and right sides simultaneously.
Off : ON light goes off.
Wing anti-icing control valves close.
FAULT : Light comes on amber, and caution appears on ECAM, if:
‐ The position of the anti-icing control valve is not the required position, or
‐ Low pressure is detected.
Note: The amber FAULT light comes on briefly as the valves transit.
ON : Light comes on blue.
WING A. ICE appears on the ECAM MEMO page.
Wing anti ice control valves open if a pneumatic supply is available.
On the ground the wing anti-icing control valves open for 30 s only (test sequence).

(1) ENG 1 (2) ANTI ICE pb-sw
Off : ON light goes off.
Engine anti-ice valve closes.
FAULT : Light comes on amber, and caution message appears on ECAM, if the position of
the anti-ice valve disagrees with the ENG 1 (2) pushbutton selection.
Note: The amber FAULT light comes on briefly as valve transits.
ON : Light comes on blue.
ECAM MEMO displays “ENG A. ICE”.
Engine anti-icing valve opens if bleed air is available from the engine.


The ice and rain protection system allows unrestricted operation of the aircraft in icing conditions and
heavy rain. In flight, hot air from the pneumatic system heats the three outboard slats (3-4-5) of each wing.
Air is supplied through one valve in each wing.
The WING pushbutton on the ANTI ICE panel controls the valves.
When the aircraft is on ground, the flight crew can initiate a 30 s test sequence by turning the system
ON.
If the system detects a leak during normal operation, the affected side’s wing anti-ice valve
automatically closes (Refer to DSC-36-10-50 Leak Detection).
When wing anti-ice is selected, the N1 or EPR limit is automatically reduced, and the idle N1 or EPR
is automatically increased.
If the electrical power supply fails, the valves close.

An independent air bleed from the high pressure compressor protects each engine nacelle from ice.
Air is supplied through a two-position (open and closed) valve that the flight crew controls with two
pushbuttons, one for each engine.
The valve automatically closes, if air is unavailable (engine not running).
When an engine anti-ice valve is open, the N1 or EPR limit is automatically reduced and, if
necessary, the idle N1 or EPR is automatically increased for both engines in order to provide the
required pressure.
If electrical power fails, the valves open.