DASSAULT AVIATION Falcon 2000EX EASy Manuale utente
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TABLE OF CONTENTS
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02-22 ATA 22 – AUTO FLIGHT
02-22-00 TABLE OF CONTENTS
02-22-05 GENERAL
Introduction
02-22-10 DESCRIPTION
Automatic flight control system interface
Automatic flight control system operation
Automatic flight control system modes
Autopilot CAT II approach
02-22-15 SPEED PROTECTION MODE
Introduction
Definitions
General rules for speed protections
Speed protection modes with autopilot on
Speed protection modes with autopilot off
Speed protection modes without mode on the FMA
02-22-20 CAS MESSAGES
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INTRODUCTION
The Falcon 2000EX EASy Automatic Flight Control System (AFCS) is composed of:
- 2 Flight Director (FD) and 2 AutoPilot (AP) systems,
- 1 Thrust Director (TD) and 1 Auto-Throttle (AT) systems, 2 Yaw Damper (YD) and 2 Mach
Trim (MT) systems.
The AFCS elaborates orders in path and roll axis. These orders are displayed on the Attitude
Director Indicator (ADI), on the Head-up Guidance System (HGS, optional), and identified as
Flight Director (FD) orders.
The AFCS elaborates also a thrust order, displayed on the ADI, on the HGS (optional), and
identified as Thrust Director order.
When AP and AT are engaged, electric servo-motors are connected to:
- the flight controls via a clutch, so that the airplane will follow the FD orders,
- the power levers cables so that the engines will follow the TD orders.
Flight Director (FD) and AutoPilot (AP) can operate in:
- basic mode (ROLL and PATH),
- superior modes:
o Lateral NAVigation (LNAV),
o Heading / Track (HDG / TRK),
o APProach (APP),
o ALTitude (ALT),
o Altitude SELection (ASEL),
o CLimB (CLB),
o Vertical Speed (VS),
o Vertical NAVigation (VALT, VCLB, VPTH, VASEL, VGP),
o Glide Slope (GS).
Thrust Director (TD) and Auto-Throttle (AT) can operate in:
- speed / Mach mode,
- thrust mode.
The FD can also operate in the following specific modes:
- Go-Around (GA),
- windshear (not available).
The Automatic Flight Control System (AFCS) also automatically trims the airplane in pitch and
compensates for pitch variation during deployment of slats, flaps and airbrakes.
Whatever vertical modes selected, when AP is engaged, pitch is automatically limited to +/-
20°.
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FIGURE 02-22-05-00 FLIGHT DECK OVERVIEW
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FIGURE 02-22-05-01 THRUST DIRECTOR - FLIGHT DIRECTOR
When engaged, the AT generate the appropriate synchronized power settings on the two
engines, with respect of engine and airplane flight envelope limitations (max / min N1, VMO /
MMO) or specific speed references.
The TD is associated to the speed bug set through the GP in MAN mode or by the FMS in
FMS mode.
FD and TD can be selected to be displayed or not on ADI by pressing on the relevant FD/TD
pushbuttons on the Guidance Panel (GP). When they are selected, a green ON symbol is lit
on the pushbutton. When the FD and/or TD commands are invalid, a red flag is displayed on
both ADI and FD and TD are dropped from displays.
FIGURE 02-22-05-02 FMA AREA
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AP and AT modes status (armed, engaged) and their references are displayed on the Flight
Mode Annunciator (FMA) on each ADI, according to the EASy color code. Only one vertical
AP mode and one lateral AP mode may be active at the same time. However, one vertical
armed and one lateral armed modes can be simultaneously selected, for example when APP
(approach mode) is armed, LOC and GS are armed.
Activation of the Touch Control Steering (TCS) function allows the crew to manually set a new
reference attitude and path without disengaging the AP. When the TCS pushbutton (on the
yoke) is depressed, the AP servomotors are disengaged allowing the pilot to fly the airplane.
Release of the TCS button will re-engage the AP servomotors. The FD will synchronize on the
new reference values or return to its previous target, depending on previous active modes.
When AP is not engaged, an automatic Mach trim increases manual longitudinal stability of
the airplane at high Mach numbers (above 0.77) by adjusting the horizontal stabilizer position
as Mach number is changing.
Mach trim is automatically engaged at airplane power up and cannot be manually
disengaged.
With the Mach trim system engaged, the normal trim can be used at any time to adjust the
stabilizer position. Once the normal pitch trim switch is released, the Mach trim system will
resume its operation.
When AP is engaged, an auto-trim is provided by the AFCS.
A Yaw Damper (YD) independent from the AP provides automatic stabilization in yaw during
manual handling of the airplane, and turn coordination during AP operation.
NOTE
FD and/or TD orders can also be flown manually (AP and/or AT disengaged, lateral and vertical
modes remain active).
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AUTOMATIC FLIGHT CONTROL SYSTEM INTERFACE
AFCS (Autopilot and Auto-Throttle) is managed:
- on the instrument panel,
o the Guidance Panel (A) gathering all AFCS mode controls and indications,
o the Flight Mode Annunciator (B) providing status of AFCS mode operation (B and C).
- on the yoke (D),
o the AutoPilot (AP) quick disconnect pad,
o the Take-Off Go Around (TOGA) pushbutton,
o the Touch Control Steering (TCS) pushbutton.
- on the throttles of engines No 1 and 2,
o the AT (E) quick disconnect pushbuttons.
FIGURE 02-22-10-00 AFCS CONTROLS
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FIGURE 02-22-10-01 GUIDANCE PANEL
The AFCS functions are hosted in the Modular Avionics Unit (MAU). The EASy installation
contains two AFCS. The standard dual configuration can provide both manual and automatic
reversion and interface capabilities sufficient to maintain full AFCS functionality, despite the
absence of the other AFCS (due to failure). The fail operational design of the AFCS provides
automatic reversion following in-flight failure of an MAU, except for the servo-motor failures:
after a servo-motor failure, there is a transfer in priority AFCS, but the engagement of the 2nd
AFCS is inhibited. The reversion is annunciated to the crew, but will result in no changes to
the mode selection or engage status except for servo-motor failures.
AUTOMATIC FLIGHT CONTROL SYSTEM OPERATION
PILOT FLYING (PF) SIDE SELECTION
FIGURE 02-22-10-02 AP / YD / PF AREA
PILOT SIDE (PF) pushbutton (on the GP). The selected side is indicated by a green light on
the left or right side of the pushbutton (LH by default), and by an horizontal arrow in the
middle of each Flight Mode Annunciator (FMA) of each ADI.
NOTE
At power on, LH side is selected by default.
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The following sensors and equipment selected on the PF side are used by the AFCS for
computations:
- Air Data System (ADS),
- Inertial Reference System (IRS),
- Flight Management System (FMS).
During the PILOT SIDE selection change, AP/FD modes are automatically de-selected and
they must be selected again.
NOTE
We can observe that after a PILOT SIDE change, non-engaging of LNAV,VNAV modes.
In this case, it is recommended to respect a waiting period (about 30 sec) before a new
selection of these modes.
AP ENGAGEMENT
FIGURE 02-22-10-03 AP PUSHBUTTON
Engagement of the AP is achieved through depression of the AP pushbutton on the GP.
When engaged, ON is illuminated in green on the AP pushbutton and a green AP symbol is
displayed at the top center of each FMA.
When AP is engaged, the horizontal and vertical modes are displayed in reverse video on
the FMA. With this symbology, pilots are immediately warned about the status of the
AutoPilot.
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AP DISENGAGEMENT
Normal AP disconnect
-Quick disconnect pad on the yoke (one push),
-AP pushbutton on the GP,
-Go-Around pushbutton (one push).
FIGURE 02-22-10-04 AUTOPILOT DISENGAGEMENT (RH)
AP disconnect
-Normal or emergency stabilizer trim command,
-Overriding action on the yoke (force disconnection),
-AP 1 and 2 failure,
-Stall warning.
NOTE
When triggered, continuous aural AutoPilot warning and AP red symbol flashing on the FMA
remains active as long as there is no push on the quick disconnect pad.
TCS pushbutton (push and maintain): when the TCS pushbutton (on the yoke) is
depressed, the AP servomotors are disengaged but the AP is not properly speaking
disconnected.
YD ENGAGEMENT / DISENGAGEMENT
The Yaw Damper is automatically engaged on the ground after successful completion of the
AFCS power up test or in-flight upon AP engagement, or by pressing the YD pushbutton
(the ON caption on the pushbutton illuminates in green).
YD disengagement will disengage AP, but AP disengagement will not disengage the YD.
YD failure will not disengage the AP.
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