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Aileron/Rudder Trim Panel................................................................................................10-7
Aileron/Rudder Trim Indications........................................................................................10-8
Flap Schematic .................................................................................................................10-9
Flight and Ground Spoilers - Schematic ......................................................................... 10-10
Ground Spoilers Arming Logic ........................................................................................ 10-11
Stall Protection System - Schematic............................................................................... 10-12
Pitch, Roll and Yaw Controls .......................................................................................... 10-13
TRIM Controls.................................................................................................................10-14
Flap and Spoiler Controls ............................................................................................... 10-15
Stall Protection System................................................................................................... 10-16
EICAS Flight Controls Indications (Ground Spoilers) ..................................................... 10-17
EICAS Flight Controls Indications (Flight Spoilers)......................................................... 10-18
EICAS Flight Controls Indications (Flaps)....................................................................... 10-19
EICAS Flight Controls Indications (Trim) ........................................................................ 10-20
EICAS Flight Controls Indications (Aileron, Elevator, Rudder) ....................................... 10-21
10-iv 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
FLIGHT CONTROLS
For Training Purposes Only
Sept 04
10-1
P I LOT T R A I N I N G GU I D E
CHAPTER 10: FLIGHT CONTROLS Introduction
The Challenger 604 has conventional flight controls organized on an advanced
technology airfoil and a T-tail configuration empennage. The flight control surfaces
are actuated by crew or autopilot inputs via mechanical connections to hydraulic
Power Control Units (PCUs). Artificial control loading is provided at the individual
control columns, control wheels and rudder pedals.
The flight controls may be divided functionally into two categories: Primary and
Secondary Flight Controls.
Primary Flight Controls
The primary flight controls are the ailerons, elevators and rudder. Each aileron and
elevator is powered by two hydraulic systems. The rudder is powered by all three
hydraulic systems.
In the unlikely case of total electrical failure or double-engine failure, ACMP 3B can
be electrically energized directly from the Air-Driven Generator (ADG). This ensures
hydraulic power is available to the flight controls.
Secondary Flight Controls
The secondary flight controls include the trim systems, (aileron, rudder and horizontal
stabilizer), flaps, flight spoilers and ground spoilers. The stall protection system (SPS)
is also considered a function of the secondary flight control system.
Flight Control Surfaces
Figure 10-1
Rudder
Elevators
Aileron
Flaps
Ground Spoiler
Flight Spoiler
P604_10_001
FLIGHT CONTROLS
10-2 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Primary Flight Controls
Description
The primary flight controls are arranged conventionally with rudder pedals and a
control wheel and column for both the pilot and copilot. Movement of the cockpit
controls is transmitted mechanically via cable and/or pushrods to the aileron, elevator
and rudder power control units (PCUs) which hydraulically move the control surfaces.
Artificial control loading provides tactile feedback to the pilots at the individual
control columns, control wheels and rudder pedals.
Position indicators are located on the EICAS Flight Controls Synoptic Page. White
triangles and position scales indicate relative deflection of the ailerons, elevators and
rudder.
Aileron and elevator flight control surfaces are each powered by two hydraulic
systems, and the rudder is powered by all three systems. Flight control system design
ensures that the loss of one hydraulic system will not prevent the operation of any
control surface. Furthermore, should two hydraulic systems be lost, the remaining
hydraulic system is sufficient to maintain safe aircraft control. Protection against cable
jam/failure or PCU jam/failure is also provided for each axis.
　
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