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Engine Anti-Ice System
Normally activated automatically via the ice detection system. Air is taken from the 9th stage, upstream of the bleed air valve. Air flow into the nacelle is controlled by the engine anti-ice valve, which fails open without electrical power. Duct pressure and temperature are monitored. A T2 sensor supplies inlet temperature to the FADEC. With the engine ice protection buttons pushed out, the engine anti-ice valves are closed regardless of the mode selector position.
The FADEC must be configured through the MCDU for takeoff in icing conditions (the engine anti-ice need not be manually switched on). At temperatures below 10°C, the REF A/I should be set to ENG, and for temperatures below 5°C, the REF A/I should be set to ALL. Default control logic is used 1,700' afe, or 2 minutes after takeoff, whichever occurs first.