Embraer EMB145 Operation Manual page 2131

ICE AND RAIN
AIRPLANE
PROTECTION
OPERATIONS
MANUAL
Engine ice protection is provided by heating the engine air inlet lip,
through the use of non-temperature-controlled hot air tapped directly
upstream of each high stage valve. As the engine air inlet has enough
airflow surrounding the lip when the engine is running, the engine air
inlet lip anti-icing system can be operated on the ground normally and
with no limitations. Each engine has its own protection system
independent of the airplane's pneumatic system.
The left hand Pneumatic System supplies the horizontal stabilizer anti-
icing subsystem. Each half-wing anti-icing subsystem is supplied by its
respective side of the Pneumatic System.
The bleed air thermal anti-icing system may be deactivated by buttons,
located on the overhead panel.
On the ground, the FADEC incorporates an automatic logic to reduce
the maximum available thrust to avoid a sudden engine thrust loss
during lift-off, even with the thrust lever set at MAX position.
In flight, the FADEC allows the engines to deliver the maximum rated
thrust to compensate for the effect of the high bleed air consumption
by the wing and horizontal stabilizer thermal anti-icing subsystems.
Moreover, the FADEC provides an automatic logic to ensure a
minimum available thrust during icing conditions, even during low
thrust setting conditions. This logic is automatically inhibited when the
landing gear is extended, in order to improve the airplane's rate of
descent and glide slope path adjusting capability.
The APU bleed air is not hot enough to perform anti-icing functions.
Therefore it must not be used for such applications.
A caution message is presented on the EICAS if the thermal anti-icing
system is turned on during non-icing conditions.
Page Code
2-15-10 2 01 REVISION 39