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CSP A--013
MASTER
A. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Rudder Trim RUDDER
TRIM DC BUS 2 2 F6
REV 56, Jan 31/03
Vol. 1 11--30--10
FLIGHT CONTROLS
Rudder
Flight Crew Operating Manual MASTER
CSP A--013
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 11--40--1
REV 56, Jan 31/03
FLIGHT CONTROLS
Elevators
Flight Crew Operating Manual
CSP A--013
MASTER
1. ELEVATORS
Longitudinal (pitch) control is provided by the elevators and supplemented by a moveable
horizontal stabilizer (see section 50 of this chapter).
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 servo is connected to the left
elevator system and the stall protection stick pusher system is connected to the right
elevator system. A pitch feel simulator unit provides artificial feel to the control columns.
Each elevator system is hydraulically powered by three power control units (PCU’s) located
in the left and right horizontal stabilizers. The PCU’s receive mechanical inputs from the
control columns via cable runs and quadrants. Each hydraulic system powers one of the
three PCU’s of each elevator.
Two flutter dampers are installed outboard of the PCU’s on each elevator. The flutter
dampers are double acting shock absorbers which prevent elevator control surface flutter in
flight if all hydraulic pressure is lost to the PCU’s. On the ground, the flutter dampers provide
a gust lock function.
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.
Elevator position indications are displayed on the EICAS FLT CONTROL synoptic page.
NOTE
A difference of up to 3 degrees between the left and
right elevator indications on the FLT CONTROL
synoptic page is allowed. When the elevator is in the
neutral position (0_ ± 0.5_), a tolerance of ± 1.0_ in
the indication is allowed.
REV 56, Jan 31/03
Vol. 1 11--40--2
FLIGHT CONTROLS
Elevators
Flight Crew Operating Manual MASTER
CSP A--013
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
ELEVATORS
FLUTTER
DAMPERS
Vol. 1 11--40--3
REV 56, Jan 31/03
FLIGHT CONTROLS
Elevators
Flight Crew Operating Manual
CSP A--013
MASTER
Elevator System --- Synoptic Page Indications and Pitch Disconnect Handle <MST>
Figure 11---40---2
Elevator Position Scale (white)
Top tick mark represents 23.6 degrees,
center tick mark represents 0 degrees
and bottom tick mark represents --18.4
degrees.
PULL &
TURN
Pitch Disconnect Handle
Center Pedestal
Elevator Position Indicator (white)
Indicates relative position of respective
elevator.
Elevator Position Readout (white)
Numeric value represents position of
respective elevator in degrees.
Elevator Outlines (blue)
Elevator Flutter Damper Outlines (white)
Comes on to indicate that respective
elevator flutter damper has failed.
FLT Control Synoptic Page
<0039>
<0039>
0
<0039>
0
<0039>
14
<0039>
<0039>
REV 56, Jan 31/03
Vol. 1 11--40--4
FLIGHT CONTROLS
Elevators
Flight Crew Operating Manual MASTER
CSP A--013
Elevator System --- EICAS Messages <MST>
Figure 11---40---3
Status Page
<0039>
<0039>
<0039>
Vol. 1 11--50--1
REV 56, Jan 31/03
FLIGHT CONTROLS
Horizontal Stabilizer Trim
Flight Crew Operating Manual
CSP A--013
MASTER
1. HORIZONTAL STABILIZER TRIM
The horizontal stabilizer trim system supplements the elevators in providing pitch control.
The horizontal stabilizer trim system provides pitch trim by varying the angle of incidence of
　
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