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ENGAGE
Used to engage respective
yaw damper channel.
DISC
Used to disengage
yaw dampers
Yaw Damper Panel
Center Pedestal
YD (amber)
Indicates that both yaw dampers
have been disengaged.
YAW DAMPER
DISC ENGAGE
YD 1 YD 2
10
AP
10
YD
Vol. 1 11--30--8
FLIGHT CONTROLS
Rudder REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Yaw Damper --- EICAS Indications <1001>
Figure 11---30---7
YD 1 or 2 INOP status (white)
Indicates that respective yaw damper
has failed or is off.
YAW DAMPER caution (amber)
Indicates both yaw dampers are
off or failed.
YD 1 INOP
YD 2 INOP
YAW DAMPER
Status Page
Primary Page
Vol. 1 11--30--9
FLIGHT CONTROLS
Rudder REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
A. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Trim RUDDER
TRIM DC BUS 2
2
F2
Rudder Trim Limiter PFEEL 2 RTL DC
ESSENTIAL
R5
Trim Indication AIL/RUD TRIM
IND
BATTERY
BUS 1 L7
Vol. 1 11--30--10
FLIGHT CONTROLS
Rudder REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 11--40--1
FLIGHT CONTROLS
Elevators REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. ELEVATORS
Longitudinal (pitch) control is provided by the elevators, assisted by a moveable horizontal
stabilizer.
Two separate elevator control systems are provided. The left elevator system is controlled
by the pilot and the right system is controlled by the copilot. Under normal conditions, the
two systems are interconnected through a pitch disconnect mechanism. Forward and aft
movement of either control column inputs simultaneous movement of both elevator surfaces.
Both systems are similar, with the exceptions that the autopilot is connected to the left
elevator system and the stall protection system is connected to the right elevator system.
Each elevator is hydraulically powered by three power control units (PCUs) which receive
mechanical inputs the control columns. Each hydraulic system powers one of the three
PCUs of each elevator. Elevator flutter damping is incorporated in the PCUs.
Control column centering and artificial feel is provided by electro--mechanical pitch feel units.
The spoiler and stabilizer control units (SSCUs) automatically vary the control column
artificial feel force as a function of the horizontal stabilizer position, flap extension and
aircraft acceleration.
In the event of an elevator control jam, the left and right elevator systems can be
mechanically separated by pulling a PITCH DISC handle and turning it 90_ to lock the
handle in place. The operable side can then be used to maintain pitch control.
Vol. 1 11--40--2
FLIGHT CONTROLS
Elevators REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Elevator System
Figure 11---40---1
ELEVATOR
PCUs
AFT
QUADRANT
PITCH FEEL
SIMULATOR
UNIT
PITCH
DISCONNECT
HANDLE
STICK
PUSHER
ELEVATOR
AUTO PILOT
CONTROL SERVO
COLUMN
& STICK
SHAKER
FORWARD QUADRANT /
TENSION REGULATOR
LOAD
LIMITER
Vol. 1 11--40--3
FLIGHT CONTROLS
Elevators REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Elevator Emer Controls and Flight Control --- Synoptic Page
Figure 11---40---2
Elevator Position Scale (white)
Upper mark represents --23.6
Center mark represents neutral (0 )
Lower mark represents +18.4
PULL &
TURN
Pitch Disconnect Handle
Center Pedestal
Elevator Position Indicator (white)
Indicates relative position of respective
elevator.
ELEV
Flight Controls Page
BRT
PITCH DISC
Used to disconnect the
control columns in case
of a jam in one of the
elevator systems.
To disconnect, pull
handle up, and rotate
90 to lock in position.
Vol. 1 11--40--4
FLIGHT CONTROLS
Elevators REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Elevator --- EICAS Indications <1001>
Figure 11---40---3
ELEVATOR SPLIT
PITCH FEEL
ELEVATOR SPLIT caution (amber)
Indicates that left and right elevator surface
mismatch exceeds 6 (below 250 knots) or
3 (above 250 knots).
PITCH FEEL FAULT status (white)
Indicates loss of redundancy in the pitch
　
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