DESCRIPTION
General 10−10−1
Primary Flight Controls 10−10−1
Secondary Flight Controls 10−10−1
Primary Flight Controls 10−10−1
Description 10−10−1
Components and Operation 10−10−2
Secondary Flight Controls 10−10−7
Description 10−10−7
Components and Operation 10−10−8
Stall Protection System 10−10−17
Stall Protection System Computer 10−10−17
Stick Pusher Disconnect 10−10−17
Controls and Indicators 10−10−19
Primary Flight Controls 10−10−20
Stab Trim, Aileron Trim, Rudder Trim 10−10−21
Flaps, Spoilers 10−10−22
Stall Protection System 10−10−23
EICAS Messages 10−10−29
SUMMARY
Power Supply and Circuit Breaker Summary 10−20−1
LIST OF ILLUSTRATIONS
DESCRIPTION
Figure 10−10−1 Flight Control Surfaces 10−10−1
Figure 10−10−2 Roll Control − Schematic 10−10−3
Figure 10−10−3 Pitch Control − Schematic 10−10−5
Figure 10−10−4 Yaw Control − Schematic 10−10−7
Figure 10−10−5 Stab Trim Panel 10−10−9
Figure 10−10−6 Stab Trim Indications 10−10−9
Figure 10−10−7 Aileron/Rudder Trim Panel 10−10−10
Figure 10−10−8 Aileron/Rudder Trim Indications 10−10−10
FLIGHT CONTROLS
Table of Contents
Vol. 2 10−00−1
Oct 05/06
CHAPTER 10 - FLIGHT CONTROLS
10−00−1
CL−605 Flight Crew Operating Manual
PSP 605−6
TABLE OF CONTENTS
Page
TABLE OF CONTENTS
LIST OF ILLUSTRATIONS
DESCRIPTION
Figure 10−10−9 Flap Schematic 10−10−12
Figure 10−10−10 Flight and Ground Spoilers − Schematic 10−10−14
Figure 10−10−11 Ground Spoilers Arming Logic 10−10−16
Figure 10−10−12 Stall Protection System − Schematic 10−10−18
Figure 10−10−13 Pitch, Roll and Yaw Controls 10−10−20
Figure 10−10−14 Trim Controls 10−10−21
Figure 10−10−15 Flap and Spoiler Controls 10−10−22
Figure 10−10−16 Stall Protection System 10−10−23
Figure 10−10−17 EICAS Flight Controls Indications (Ground Spoilers) 10−10−24
Figure 10−10−18 EICAS Flight Controls Indications (Flight Spoilers) 10−10−25
Figure 10−10−19 EICAS Flight Controls Indications (Flaps) 10−10−26
Figure 10−10−20 EICAS Flight Controls Indications (Trim) 10−10−27
Figure 10−10−21 EICAS Flight Controls Indications (Aileron, Elevator,
Rudder) 10−10−28
FLIGHT CONTROLS
Table of Contents
Vol. 2 10−00−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
Page
GENERAL
The Challenger 605 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 10−10−1
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
　
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