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AIL AIL
ELEV ELEV
RUDDER
Indicates relative position of respective aileron
Top tick mark – 23.6°
Center tick mark – 0°
Bottom tick mark – -18.4°
Indicates relative position of rudder
Left tick mark – - 25°
Center tick mark – 0°
Right tick mark – 25°
FLIGHT CONTROLS
For Training Purposes Only
May 03
10-33
P I LOT T R A I N I N G GU I D E
EICAS Messages
MESSAGE MEANING AURAL WARNING
(IF ANY)
CONFIG FLAPS Flaps are not set at 20° with the aircraft in takeoff mode. “CONFIG FLAPS”
CONFIG SPOILERS Spoilers are not stowed with the aircraft in takeoff mode. “CONFIG
SPOILERS”
CONFIG STAB Pitch trim is not set in the green band with the aircraft in takeoff
mode. “CONFIG TRIM”
AILERON PCU One or both ailerons have a jammed power control unit.
ALT COMP FAIL The left or right altitude compensation circuit of the stall protection computer has failed.
ELEVATOR SPLIT Indicates > 5 degrees difference between left and right elevator surface position.
FLAPS FAIL Either both flap motors are overheated or the flaps have failed.
FLT SPLR DEPLOY Flight spoilers are deployed with either the radio altitude between 10’ - 300’ or engine
N1 > 79% or, with the radio altimeter inoperative, the gear is extended.
FLT SPLRS Left and/or right detent mechanism has failed (displays on ground only, unless there is
a loss of system 1 and 2 hydraulic pressure).
GND SPLRS Ground spoilers are inoperative.
GND SPLRS DEPLOY Ground spoilers are not stowed and the radio altitude is greater than 10’.
GND SPLRS NOT ARMED The ground spoilers are not armed with the aircraft in either takeoff mode or in the
landing mode.
MACH TRIM Mach trim is disengaged or failed.
STAB TRIM Both pitch trim channels are off or failed.
STALL FAIL One or both channels of the stall protection system have failed, resulting in the stick
pusher system becoming inoperative.
AILERON MON OK All four aileron PCU failure detection sensors are functioning properly.
T/0 CONFIG OK With engines running, and on ground, the aircraft is in takeoff configuration.
FLAPS MOTOR OVHT One of the flap motors is hot and has shut down.
STAB CH 1 INOP The respective pitch trim channel is off or failed, and the other channel is engaged and
STAB CH 2 INOP not failed.
EICAS Messages
Table 10-1
10-34 For Training Purposes Only
May 03
FLIGHT CONTROLS P I LOT T R A I N I N G GU I D E
Page Intentionally Left Blank
Table of Contents
For Training Purposes Only
May 03
11-i
P I LOT T R A I N I N G GU I D E FLIGHT INSTRUMENTS
Introduction .......................................................................................................................11-1
Electronic Flight Instrument System (EFIS) ................................................................11-1
Components and Operations ......................................................................................11-2
Primary Flight Display ...........................................................................................11-2
Multifunction Display .............................................................................................11-4
EFIS Comparator Monitor ...........................................................................................11-6
Full-Time Comparator ...........................................................................................11-6
Pitch ......................................................................................................................11-6
Roll ........................................................................................................................11-6
Heading.................................................................................................................11-6
Altitude ..................................................................................................................11-7
Indicated Airspeed ................................................................................................11-7
Category II Comparator.........................................................................................11-8
LOC Deviation.......................................................................................................11-8
G/S Deviation ........................................................................................................11-8
RA Deviation .........................................................................................................11-9
Comparator Indications and EFIS Failure Displays ............................................ 11-10
　
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