BOMBARDIER Primus 2000XP Einrichtungshandbuch

For Training Purposes Only

Sept 04

2-i

PILOT TRAINING GUIDE

AUTOMATIC FLIGHT CONTROL SYSTEM

Chapter 2: Automatic Flight Con trol System

TABLE OF CONTENTS

Page

Introduction ......................................................................................................................... 2-1

Description .......................................................................................................................... 2-1

Guidance Panel............................................................................................................. 2-1

AFCS Schematic........................................................................................................... 2-3

Autopilot ........................................................................................................................ 2-4

Autopilot Engagement................................................................................................... 2-6

Autopilot Disengagement .............................................................................................. 2-7

Yaw Damper ................................................................................................................. 2-8

PFD Annunciation ......................................................................................................... 2-9

Flight Director (FD)...................................................................................................... 2-10

Guidance Panel........................................................................................................... 2-12

Flight Director Modes .................................................................................................. 2-14

Lateral Modes ............................................................................................................. 2-15

Bearing (BRG) Source ................................................................................................ 2-27

VOR/LOC Nav Source ................................................................................................2-28

FMS Nav Source.........................................................................................................2-29

Vertical Modes ............................................................................................................ 2-30

Multi-Axis Modes......................................................................................................... 2-35

Takeoff (TO) Mode...................................................................................................... 2-38

Go Around (GA) Mode ................................................................................................2-38

Windshear Guidance (WSHR) Mode ..........................................................................2-39

Automatic Emergency Descent Mode................................................................... 2-41

Autopilot – Flight Director EICAS Messages...............................................................2-42

EMS Circuit Protection ................................................................................................ 2-44

PILOT TRAINING GUIDE

AUTOMATIC FLIGHT CONTROL SYSTEM

2-ii For Training Purposes Only

Sept 04

PAGE INTENTIONALLY LEFT BLANK

For Training Purposes Only

Sept 04

2-1

PILOT TRAINING GUIDE

AUTOMATIC FLIGHT CONTROL SYSTEM

INTRODUCTION

The Primus 2000XP includes an Automatic Flight Control System (AFCS) that

provides dual channel autopilots, dual yaw dampers, dual flight directors and

automatic pitch trim. The autopilot and yaw damper functions operate in an active

standby mode, with only one channel active at a time. All computations are performed

by two Flight Guidance Computers (FGC), located in the Integrated Avionics

Computer (IAC). The FGC receives inputs from the Electronic Flight Instrument

System (EFIS), the Air Data Computers (ADC), the Inertial Reference System (IRS),

the Flight Management System (FMS), the Fault Warning Computer (FWC) and the

Data Acquisition Unit (DAU).

DESCRIPTION

All computations are performed by the FGCs which are located in IAC1 and IAC2.

The FGCs receive inputs from the following through the Avionics Standard

Communications Bus:

• Flight Management System

• Electronic Flight Instrument System

• Inertial Reference System

• Fault Warning Computer

• Data Acquisition Units

• Micro Air Data Computers

GUIDANCE PANEL

The AFCS functions controlled by the FGC include:

• Flight director modes

• Pitch wheel references

• Engagement of the autopilot and yaw damper functions

• Selection of left or right Primary Flight Display (PFD) data to be used by FGC

PILOT TRAINING GUIDE

AUTOMATIC FLIGHT CONTROL SYSTEM

2-2 For Training Purposes Only

Sept 04

Through the flight computer, the AFCS will provide flight guidance outputs for

display on the Primary Flight Display (PFD). The flight director functions are as

follows:

• Mode selection

• Computation of guidance

• Data management and source selection

• Command bar output for display

If an autopilot or flight director mode is armed or active, the annunciator on the

appropriate button is illuminated.

SPD

MAN

FMS

CRS 1 CRS 2

PUSH DCT PUSH DCT

ALTHDG

Honeywell

FD FDAP

CPL

FLC NAV BANKHDG VNAV ALT

APR VS

PUSH CHG PUSH SYNC

GX_02_001

Indicates FLC mode

is active

Indicates HDG mode

is active

(The PFD control panels are located on each

side of the guidance panel)

Indicates NAV mode

is armed or active.

MINIMUMS

BARO Hpa

RAD IN

BARO SETNAV SRC

BRG V/L BRGFMS

HSI

Honeywell PUSH STD

For Training Purposes Only

Sept 04

2-3

PILOT TRAINING GUIDE

AUTOMATIC FLIGHT CONTROL SYSTEM

AFCS SCHEMATIC

SPD MAN

FMS

CRS 1 CRS 2

PUSH DCT PUSH DCT

ALTHDG

Honeywell

FD FDAP

CPL

FLC NAV BANKHDG VNAV ALT

APR VS

PUSH CHG PUSH SYNC

MAX

THRUST

IDLE

REV

MAX REV

ENG

RUN

OFF OFF

RUDDER

CONTROL SURFACE POSITION

CH 1 CH 2

TRIM SYSTEM

IAC 1 IAC 2

FGC 2

DUAL

ELEVATOR

SERVO

DUAL

AILERON

SERVO

YAW

DAMPER

ACTUATOR 1

YAW

DAMPER

ACTUATOR 2

FGC 1

DAU

MADC

FWC

IRS

EFIS

FMS

TOGA

BUTTONS

TRIM SWITCHES

CONTROL WHEEL

GUIDANCE PANEL

AP DISC

BUTTON

TOUCH

CONTROL

STEERING

(TCS)

GX_02_002

ASCB

AILERON ELEVATOR

R/T

PILOT TRAINING GUIDE

AUTOMATIC FLIGHT CONTROL SYSTEM

2-4 For Training Purposes Only

Sept 04

Manual selection of the master AFCS channel is accomplished via the pop-up menu

on either multifunctional display (MFD), in conjunction with the MFD control panel

located on the pedestal.

AUTOPILOT

The autopilot (AP) system automatically controls the airplane in pitch and roll attitude

via servo control of ailerons, elevator and aircraft pitch trim system. The two autopilot

computer channels operate in a high priority/low priority (active/standby)

configuration.

Assignment of priority channel is alternated on power-up. The high priority channel

provides control functions, while the low priority channel operates in a back-up mode.

The autopilot/yaw damper actuators and pitch trim interface can only be driven by the

priority channel.

In the event of a channel failure, the priority will automatically switch to the other

channel.

Each FGC shall determine which symbol generator is driving the selected PFD, as

selected on the reversion control panel located on the pedestal. The following

guidance data is received via the Avionics Standard Communications Bus (ASCB), for

use in the FGC:

GX_02_003

FGC 12

FGC 21

MFD CONTROL PANEL

MFD

Honeywell

AUTOTHROTTLE

SYSTEM 2/2

SAT

GSPD

-56

TAT

TAS

-40

234

345

HDG

315

ETE0+02

2.5

DVT

FMS1

000

-02

+12

-04

KLAX

KPHX

TOC

SRP

LUF

DVT +09

T5.0

FGC 1 2

TCAS MENU

EMER

TERR

MAP

PLAN

NAV

APT

NORM ABN

SKP

RCL

PAG

ENT

For Training Purposes Only

Sept 04

2-5

PILOT TRAINING GUIDE

AUTOMATIC FLIGHT CONTROL SYSTEM

Air data source identification Lateral and vertical path deviations

Attitude source identification Distance to station

NAV source identification Tuned-to-NAV and To/From status

Course error Inner, middle and outer marker data

Heading error Radio altitude and flags

The source of other guidance information is selected via the source identifier received

from selected PFD symbol generator. The data received includes:

IRS:

Roll angle Normal acceleration

Pitch angle Ground speed

Roll rate True track angle

Pitch rate Flight path angle

Yaw rate Magnetic heading

Longitudinal acceleration True heading

Lateral acceleration Inertial vertical speed

ADC:

Baro-corrected altitude True airspeed

Pressure altitude Dynamic pressure

Vertical speed VMO

Mach MMO

Calibrated airspeed

FMS:

Lateral steering command and flags VNAV submode selection flags

VNAV targets

FWC:

Preselected altitude

Display Controller (DC):

Speed references

PILOT TRAINING GUIDE

AUTOMATIC FLIGHT CONTROL SYSTEM

2-6 For Training Purposes Only

Sept 04

AUTOPILOT ENGAGEMENT

Autopilot is engaged via the AP button on the guidance panel. When there are no

vertical or lateral mode active, the autopilot will engage in (PIT) and (ROL) FD

modes.

Autopilot control authority:

• Roll rate is limited to ± 7.5°/sec.

• Pitch rate

• ± 0.3 g’s in straight and level flight

• maximum 0.7 g’s pitch up in a turn

The autopilot can engage throughout the range:

• Pitch = ± 50°

• Roll = ± 75°

• Once engaged, the autopilot will reduce the pitch and roll angles below control

limits

Autopilot control limits:

• Roll = ± 35° except in Approach (APP) mode. When in APP mode, the roll limits

are reduced linearly from ± 25°, above 200 feet radio altitude, to ± 5° at zero feet

radio altitude

• Pitch = ± 20°. In APP mode, the nose-down pitch limit is reduced below 300 feet,

programmed by vertical rate and radio altitude

CRS 2

PUSH DCT

Honeywell

FDAP

CPL

CRS 2

PUSH DCT

Honeywell

FDAP

CPL

GX_02_004

AP1

AP2

When selected, or will flash for

approximately 5 seconds, then steady.

AP1 AP2

20 20

10 10

ROL PITAP1

0.88 30000

23500

220

200

For Training Purposes Only

Sept 04

2-7

PILOT TRAINING GUIDE

AUTOMATIC FLIGHT CONTROL SYSTEM

AUTOPILOT DISENGAGEMENT

Autopilot disengagement is accomplished by activating any of the following:

• AP button on guidance panel

• Autopilot quick-disconnect (DISC) button on either control wheel

• Manual stabilizer trim when touch control steering (TCS) not active

• YD button on FGC panel

• TCS button on either control wheel (while depressed).When the TCS button on

either control wheel is activated, the aileron and elevator servo clutches are

released, the autopilot is disengaged and the flight director is resynchronized.

Releasing the TCS button reengages the servo clutches and autopilot is engaged, if

within normal pitch and roll limits. Where applicable, the flight director modes

will react as if the autopilot had just been engaged

• Takeoff/Go Around (TOGA) buttons on thrust levers

• Motor trip/failure or AFCS failure

• Stick shaker acuation

The AP1 or AP2 annunciator will flash red continually and an aural “cavalry charge”

will sound repeatedly. The annunciation and aural can only be canceled by depressing

DISC on either control wheel.

GX_02_005

Stabilizer

Trim

Autopilot Quick

Disconnect Button

(DISC)

Touch Control

Steering (TCS)

PILOT’S CONTROL WHEEL

R/T

GX_02_006

Takeoff/Go Around

(TOGA) Buttons

PILOT TRAINING GUIDE

AUTOMATIC FLIGHT CONTROL SYSTEM

2-8 For Training Purposes Only

Sept 04

YAW DAMPER

The yaw damper provides stability augmentation and turn coordination for the

airplane yaw axis via two linear actuators, in series with the rudder control system.

The yaw damper function will automatically engage on the ground, within 3 seconds

after successful completion of AFCS power-up test. As with the autopilot, the yaw

damper operates in an active/standby configuration. When engaged, the active yaw

damper will center both linear actuators.

The YD will not automatically engage once the airplane is airborne. The YD button,

located on the guidance panel, may be used to reengage the YD. When YD is engaged,

the associated arrow on the guidance panel is illuminated.

One yaw damper must be engaged for autopilot operation. Autopilot engagement

without YD will occur only when both YDs have failed in flight.

For more information on yaw damper, please refer to Chapter 10, FLIGHT

CONTROLS.

GX_02_007

CRS 2

PUSH DCT

Honeywell

FDAP

CPL

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