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Flap/Slat/Gear Extension Speed Bugs................................................................ 10-39
Spoiler System .................................................................................................... 10-40
Stall Protection.......................................................................................................... 10-55
Stall Protection Components..................................................................................... 10-55
Angle-of-Attack (AOA) Vane ............................................................................... 10-55
Mach Transducer ................................................................................................ 10-56
Stick Shaker Actuator.......................................................................................... 10-56
Stall Pusher......................................................................................................... 10-57
Stall Protection Disconnect Buttons ....................................................................10-57
Stall Pusher On/Off Switches.............................................................................. 10-58
Stall Protection Computer ................................................................................... 10-59
Stall Protection Computer Schematic ................................................................. 10-60
Stall Protection Operation ................................................................................... 10-61
Stall Warning Advance........................................................................................ 10-62
Stall System Pilot-Activated Test ........................................................................ 10-63
System Integration .......................................................................................................... 10-64
Primary Flight Controls.............................................................................................. 10-64
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-ii For Training Purposes Only
Sept 04
Secondary Flight Controls......................................................................................... 10-64
Stall Protection System....................................................................................... 10-64
Primary/Secondary Flight Control EICAS Messages .......................................... 10-65
Slat/Flap EICAS Messages................................................................................. 10-67
Stall Protection EICAS Messages....................................................................... 10-70
EMS Circuit Protection.............................................................................................. 10-71
For Training Purposes Only
Sept 04
10-1
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
INTRODUCTION
The Global Flight Controls System includes primary flight controls, secondary flight
controls and stall protection systems. Primary flight controls are responsible for the
roll, pitch, and yaw attitudes of the aircraft. Roll control is achieved through the use of
ailerons, pitch control through elevators and a pitch trim system while yaw is
controlled by the rudder. Aileron and elevator PCUs are designed so they will provide
adequate dynamic stiffness for flutter protection in the event of a supply hydraulic
system failure. Flutter dampers, therefore, are not required on the aircraft.
Secondary flight controls include all lift altering devices. Multifunction spoilers
provide automatic roll assistance and manual lift dumping in flight. Automatic ground
lift dumping on landing is provided by the multifunction spoilers in conjunction with
the ground spoilers. Leading edge slats and trailing edge flaps alter the wing profile in
response to pilot inputs to provide increased lift at low airspeeds.
Stall protection is provided to alert the flight crew if the aircraft nears the stall angle.
Various warnings are provided to the crew and, if corrective action is not taken, a stick
pusher will activate before the stall angle is reached.
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-2 For Training Purposes Only
Sept 04
DESCRIPTION
PRIMARY FLIGHT CONTROL
The primary flight controls consist of two separate elevators and ailerons, and a single
rudder. The primary flight surfaces are actuated by Power Control Units (PCUs) that
are hydraulically powered and mechanically controlled. Artificial control loading
(tactile feedback) is provided to the control wheels and rudder pedals. Surface
positioning is shown on the FLIGHT CONTROL synoptic page and on the EICAS
display. Trim position is displayed on the EICAS display.
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