F2000EX EASY 02-27-00
ATA 27 – FLIGHT CONTROLS
CODDE 1 PAGE 1 / 2
TABLE OF CONTENTS
DGT94085 ISSUE 3
02-27 ATA 27 – FLIGHT CONTROLS
02-27-00 TABLE OF CONTENTS
02-27-05 GENERAL
Introduction
Flight control sources
Primary and secondary flight controls
02-27-10 DESCRIPTION
Introduction
Primary flight controls
Ailerons
Pitch control
Rudder
Secondary flight controls
02-27-15 CONTROL AND INDICATION
Control
Indication
02-27-20 SYSTEM PROTECTION
Introduction
Circuit breakers
Placard markings
02-27-25 NORMAL OPERATION
Introduction
ON GROUND
IN FLIGHT
02-27-30 ABNORMAL OPERATION
Introduction
SLAT abnormal operation
No 1 hydraulic system failure
No 2 hydraulic system failure
No 1 and 2 hydraulic system failure
Jamming
CAS messages
DASSAULT AVIATION Proprietary Data
02-27-00 F2000EX EASY
ATA 27 – FLIGHT CONTROLS
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TABLE OF CONTENTS
ISSUE 3 DGT94085
INTENTIONALLY LEFT BLANK
DASSAULT AVIATION Proprietary Data
F2000EX EASY 02-27-05
ATA 27 – FLIGHT CONTROLS
CODDE 1 PAGE 1 / 4
GENERAL
DGT94085 ISSUE 3
INTRODUCTION
The primary flight controls of the Falcon 2000EX EASy airplane are hydraulically and
actuated.
The primary flight controls include two ailerons, two mechanically-linked elevators, one
horizontal stabilizer and one rudder.
Secondary flight controls include leading edge slats, trailing edge double slotted flaps and
airbrakes. All secondary flight controls are hydraulically actuated and either controlled by
control handles located in the flight deck center pedestal or automatically controlled when
specific flight conditions are met for slats or airbrakes operation.
DASSAULT AVIATION Proprietary Data
02-27-05 F2000EX EASY
ATA 27 – FLIGHT CONTROLS
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GENERAL
ISSUE 3 DGT94085
FLT CONTROL
circuit breakers
ENG-TRM-BRK window Airbrakes
indicating auto extension
trim configuration disarm pushbutton
HSI window indicating
slats, flaps, airbrakes
SPEED LIMITATIONS
and pitch trim
placard marking
configurations
Pitch trim
on yoke
Aileron and rudder
normal trim controls, Slats / Flaps
pitch and aileron control and
emergency controls, emergency slats
and airbrakes controls switch
FIGURE 02-27-05-00 FLIGHT DECK OVERVIEW
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F2000EX EASY 02-27-05
ATA 27 – FLIGHT CONTROLS
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GENERAL
DGT94085 ISSUE 3
FLIGHT CONTROL SOURCES
PRIMARY FLIGHT CONTROLS
AILERON CONTROL RUDDER CONTROL ELEVATOR CONTROL
SYSTEM SYSTEM SYSTEM
- Hydraulic No 1 - Hydraulic No 1 - Hydraulic No 1
- Hydraulic No 2 - Hydraulic No 2 - Hydraulic No 2
- A1 bus for aileron trim - ESS bus for rudder trim - B1 bus for normal pitch trim
- B2 bus for emergency - Autopilot for yaw damper - ESS bus for emergency trim
aileron trim
- ESS bus for pitch Arthur
- B1 bus for aileron Arthur variable unit
variable unit
- Position of stabilizer and
- ADS2 data via ARINC bus slats control for pitch Arthur
for aileron Arthur variable variable unit
unit
SECONDARY FLIGHT CONTROLS
LEADING EDGE SLATS FLAPS AIRBRAKES
- Hydraulic No 1 for normal - Hydraulic No 2 - Hydraulic No 2
slat operation
- ESS bus for flap control - ESS bus for A/B control
- Hydraulic No 2 for
emergency slat extension
- A2 and BAT buses for
normal slat operation
- BAT bus for emergency
extension
- Angle of attack sensors for
automatic extension and
retraction
DASSAULT AVIATION Proprietary Data
02-27-05 F2000EX EASY
ATA 27 – FLIGHT CONTROLS
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GENERAL
ISSUE 3 DGT94085
PRIMARY AND SECONDARY FLIGHT CONTROLS
Rudder
Flaps Elevator
Slat
Horizontal
stabilizer
Airbrakes
Aileron
FIGURE 02-27-05-01 PRIMARY AND SECONDARY FLIGHT CONTROLS
DASSAULT AVIATION Proprietary Data
F2000EX EASY 02-27-10
ATA 27 – FLIGHT CONTROLS
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DESCRIPTION
DGT94085 ISSUE 3
INTRODUCTION
The primary flight control system is hydraulically and actuated. Control inputs from the flight
deck are transferred from the dual control yoke and column through a system of push-pull
rods and bellcranks, which provide manual inputs to dual hydraulic servo-actuators connected
to the appropriate primary flight control surface.
In the case of total hydraulic failure, all primary flight controls can be operated manually. In
this abnormal condition, airspeed should be limited to 260 KIAS or less.
Horizontal stabilizer, aileron and rudder trims are electrically actuated. The horizontal
stabilizer trim has a second emergency electrical motor. The ailerons have a normal and an
emergency electrical trim.
PRIMARY FLIGHT CONTROLS
Between the pilot or copilot column and yoke and a flight control surface, the control channel
is composed of:
- a series of push-pull rods acting as the mechanical link between the control column and
yoke and the servo-actuator,
- a main Artificial Feel Unit (AFU),
- a variable bellcrank, or Arthur, for roll and pitch feel control,
- a trim unit,
- a servo-actuator,
- an auxiliary artificial feel unit connected to the servo-actuator.
DASSAULT AVIATION Proprietary Data
02-27-10 F2000EX EASY
ATA 27 – FLIGHT CONTROLS
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DESCRIPTION
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SERVO-ACTUATOR
Each primary flight control surface is actuated by its associated hydraulic servo-actuator.
The servo-actuators consist of two independent barrel and piston assemblies operating in
unison. Each of No1 and 2 hydraulic systems independently supplies a barrel and piston
assembly.
FIGURE 02-27-10-00 SERVO-ACTUATOR SCHEMATIC (ONE BARREL REPRESENTED)
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ATA 27 – FLIGHT CONTROLS
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DESCRIPTION
DGT94085 ISSUE 3
The servo-actuator unit is attached to the control surface and connected to the airframe by
its rods.
Movement of a control-input linkage (push-
pull rod) controls the servo-actuators by
directing hydraulic fluid to displace the dual
barrel and piston.
Movement of the servo-actuator assembly
provides force to deflect the control surface
through a connecting rod.
Should one hydraulic system fail, a bypass
valve within the corresponding barrel
interconnects the two chambers and
depressurizes the barrel of the affected
hydraulic system. This keeps possible the
movement of the inert barrel actuated by the
active one.
Should both hydraulic systems should fail,
pilot inputs can mechanically move the
entire servo-actuator assembly and deflect
the control surface by bringing the control
input lever to abutment. The by-pass valve
is restricted in order to avoid flutter.
An accumulator keeps pressure to
compensate possible hydraulic fluid leakage
and thermal retraction.
FIGURE 02-27-10-01 SERVO-ACTUATOR OPERATION
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ATA 27 – FLIGHT CONTROLS
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DESCRIPTION
ISSUE 3 DGT94085
ARTIFICIAL FEEL UNIT
Each primary flight control incorporates a main spring-loaded Artificial Feel Unit (AFU)
upstream from its servo-actuator. The main AFU provides an aerodynamic artificial load feel
to pilot’s controls directly proportional to the input movement and to the resultant spring
compression of the AFU.
The elevator main AFU is electrically heated for high altitude flight.
FIGURE 02-27-10-02 FLIGHT CONTROL SCHEMATIC (TYPICAL)
An auxiliary spring-loaded AFU is connected to the airframe and to the auxiliary arm of each
servo-actuator. In case of control linkage disconnection, the auxiliary AFU forces the slide
valves to position the servo-actuator into the neutral position.
DASSAULT AVIATION Proprietary Data
