CREW
AWARENESS
AIRPLANE
OPERATIONS
MANUAL
2-04-25
Page
2
Code
01
REVISION 39
AOM-145/1114
A bug in the airspeed scale on the PFD indicates the stall speed for
the associated condition and a pitch limit indicator is presented on
EADI to indicate the current margin to the stick shaker angle. When
the airplane reaches 0.5 g, the stick pusher is inhibited, stopping its
actuation over the control column. A quick disconnect button is
provided in the control wheel to permit pilots to cut the system if the
need arises. To disconnect the system in case of failure, the SPS
panel provides one cutout button for each channel. An EICAS
message is presented to indicate that the system has failed or is
cutout.
EICAS displays the SPS/ICE SPEEDS message to indicate that the
Ice Detection/SPS interface logic (Ice Compensation) is active, and
consequently the SPS will actuate at reduced angle of attack values
for flaps 9°, 18° and 22°.
NOTE: The first in-flight ice detection, by any ice detector, activates
the ice compensation.
− The ice compensation is inhibited during 5 minutes after
takeoff.
− The ice compensation is reset only on the ground, by pressing
the SPS Test Button.
SYSTEM INHIBITION
The stick pusher does not actuate in the following conditions:
− On the ground (except during test).
− Below 0.5 g.
− If the quick disconnect button is pressed (except for JAA certification).
− Below 200 ft AGL. If radio altimeter has failed, this condition reverts
to a 10-second delay after takeoff.
− If any cutout buttons are released.
− Above 200 KIAS.
− If at least one channel is inoperative.
SYSTEM TEST
A test button is provided to test the system on the ground. The system
operates normally if not tested. Test button remains illuminated if the
system has not been tested or after unsuccessful tests. It is not possible
to test the system in flight. This inhibition is valid for 30 seconds after
landing, above 70 KIAS or with landing gear not downlocked.
NOTE: Test button remains illuminated if quick disconnect button is
pressed during test.
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