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AIL
ELEV
AIL
Flight Control Primary Page
TRIM DISPLAYS:
AILERON
RUDDER
STABILIZER
Invalid data
CONTROL SURFACE
DISPLAYS:
FLAPS
SLATS
SPOILERS
GF1010_031
ND
STAB
NU
NL RUDDER
LWD RWD
NR
TRIMS
AIL
− −
− −
FLIGHT CONTROLS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−26
PRIMARY/SECONDARY FLIGHT CONTROL EICAS MESSAGES
CONFIG RUD TRIM
Displayed during
takeoff,
if rudder trim is
out of certified range
(green band).
CONFIG AIL TRIM
Displayed during
takeoff,
if rudder trim is
out of certified range
(green band).
CONFIG STAB TRIM
Displayed during
takeoff,
if stabilizer
trim is out of certified
range (green band).
MACH TRIM FAIL
Indicates the mach trim
function has failed due
to loss of mach data
information.
RUD LIMITER FAIL
Indicates that the
rudder limiter switching
capability is lost. It may
be accompanied by an
additional rudder
authority caution
message.
LOW
Indicates that the rudder
authority available is low
(rudder limiter failed in
low authority position).
RUD AUTHORITY
RUD AUTHORITY SAFE
Indicates that rudder
authority is safe in current
configuration and speed.
RUD LIMITER FAULT
Indicates that one
channel of the rudder
limiter is inoperative.
ELEVATOR SPLIT
Displayed anytime elevator
split is:
At or greater than 4 degrees
above 250 knots, or
6 degrees below 250 knots.
STAB TRIM
Indicates both pitch trim
channels are inoperative.
Failure
Both STAB switches
May be result of:
MASTER DISC switch
selected OFF, or
pressed for more than 5
seconds.
"NO TAKEOFF"
"NO TAKEOFF"
"NO TAKEOFF"
CONFIG AIL TRIM
CONFIG RUD TRIM
CONFIG STAB TRIM
MACH TRIM FAIL
STAB TRIM
RUD LIMITER FAIL
RUD AUTHORITY HIGH
RUD AUTHORITY LOW
ELEVATOR SPLIT
RUD AUTHORITY SAFE
RUD LIMITER FAULT
GF1010_032
FLIGHT CONTROLS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−27
PRIMARY/SECONDARY FLIGHT CONTROL EICAS MESSAGES (CONT'D)
SPLRS/STAB BIT
Indicates that a fault
has been recognized
by the flight control
unit (maintenance
action before the next
scheduled check). This
message appears only
on the ground.
STAB CH 12
FAIL
Indicates that channel 1
or 2 failed.
STAB CH 12
OFF
Indicates that the affected
pitch trim off switch
(centre pedestal) has
been selected to the OFF
position.
PITCH FEEL FAULT
Indicates that either
pitch feel is inoperative
or degraded (force
gradient not nominal) on
one or both channels.
STAB CH 12
FAIL
PITCH FEEL FAULT
SPLRS/STAB BIT
STAB CH 12
OFF
FLIGHT CONTROLS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−28
SLAT/FLAP CONTROL SYSTEM
The slat and flap control system is an integrated electromechanical
system which operates both
slats and flaps from a single flight compartment control lever. The flap and slat control systems are
mechanically independent. Each system is comprised of actuators, linked through a rigid driveline, to
a central Power Drive Unit (PDU). Each PDU incorporates dual electric motor/brake assemblies. The
slats and flaps will continue to operate at half speed with a single motor operating.
Asymmetry brakes for both flaps and slats are installed to provided driveline braking in the event of
shaft failures. Dual sensors are located at the outboardmost
ends of the driveline. They are used by
the control units for system positioning and fault monitoring. Position sensors are located next to
each flap actuator to provide position feedback to the control units.
The slats are extended first if both slat and flap extension is required. The flaps are retracted first if
both slat and flap retraction is required.
Two Slat/Flap Control Units (SFCUs) control the operation of the slats and flaps. Electrically there
are two independent channels for slats and two independent channels for flaps. Each SFCU controls
and monitors the flaps and slats independently of the other unit. Each SFCU controls one slat PDU
　
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