POWERPLANT
AIRPLANE
O
PERATIONS
MANUAL
2-10-50
Page
16
Code
01
REVISION 41
Copyright © by Embraer. Refer to cover page for details.
f) In case of disagreement between the REF A-ICE condition selected
by the pilot and the actual Anti-Ice system condition, a caution
message (ENG REF A/I DISAG) is displayed on the EICAS,
provided the Parking Brake is released (OFF) or with any Thrust
Lever Angle above 45°.
g) If any thrust lever is set to an angle above 45° before takeoff data
successfully entered, a caution message (ENG NO TO DATA) is
presented on the EICAS.
ENGINE START
Engine start, commanded through the Start/Stop Knob, is automatically
managed by the FADEC as follows:
− The FADECs A and B alternate as FADEC in control on every
subsequent ground start. If the Ignition Selector Knob is set to
AUTO position, a single ignition system, corresponding to the
FADEC in control, will be used.
− The FADEC activates the ignition system when N2 is at
approximately 14% and commands the fuel solenoid valve to
open when N2 is at approximately 31.5% (28.5% for airplanes
equipped with FADEC B7.4 and on) or 12 seconds after ignition
is activated, if the Ignition Selector Knob is set to AUTO or ON
position.
− Whenever the start cycle is completed, the FADEC deactivates
the ignition system and provides a discrete signal to command
the Starting Control Valve (SCV) to close.
− If
the Ignition Selector Knob is set to OFF position, the FADEC
neither activates the ignition system nor actuates the fuel valve
from closed to open position, in order to enable ground/flight
dry motoring.
NOTE: If the engine is already running with TLA above IDLE
thrust, the fuel valve is not closed, even if the Ignition
Selector Knob is set to OFF position.
− When the engine is started on ground, only the FADEC in
control commands ignition, if the Ignition Selector Knob is set to
AUTO position. During an in flight start, both FADECs
command ignition.
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