1. INTRODUCTION - · PDF file1. INTRODUCTION The automatic flight control system (AFCS)...

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1. INTRODUCTION The automatic flight control system (AFCS) provides integration of the autopilot and flight director systems. The AFCS system consists of two interlinked flight control computers (FCC 1 and FCC 2), a two axis autopilot, two yaw dampers, automatic elevator trim control and assorted servos and actuators. The flight director commands the flight crew to follow cues on the primary flight displays (PFD’s). The flight control computer receives mode selections from the flight control panel and sensor information from the air data system, navigation systems, attitude and heading reference system, radio altimeter and surface position sensors. The flight control computer receives mode selections from the flight control panel and sensor information from the air data system, navigation systems, inertial reference system, radio altimeter and surface position sensors.<0025> The FCC’s provide flight guidance commands to the autopilot which provides the control signals to drive the aileron and elevator servos as well as the horizontal stabilizer trim. The flight director provides computed steering commands using a command bar on the attitude director indicator portion of the PFD’s. The steering commands provide visual guidance for the pilot to manually steer the aircraft as defined by the selected modes of operation. Canadair Regional Jet 100/200 - Automatic Flight Control System Page 1

Transcript of 1. INTRODUCTION - · PDF file1. INTRODUCTION The automatic flight control system (AFCS)...

Page 1: 1. INTRODUCTION - · PDF file1. INTRODUCTION The automatic flight control system (AFCS) provides integration of the autopilot and flight director systems. The AFCS system consists

1. INTRODUCTION

The automatic flight control system (AFCS) provides integration of the autopilot and flightdirector systems. The AFCS system consists of two interlinked flight control computers(FCC 1 and FCC 2), a two axis autopilot, two yaw dampers, automatic elevator trim controland assorted servos and actuators. The flight director commands the flight crew to followcues on the primary flight displays (PFD’s).

The flight control computer receives mode selections from the flight control panel and sensorinformation from the air data system, navigation systems, attitude and heading referencesystem, radio altimeter and surface position sensors.

The flight control computer receives mode selections from the flight control panel and sensorinformation from the air data system, navigation systems, inertial reference system, radioaltimeter and surface position sensors.<0025>

The FCC’s provide flight guidance commands to the autopilot which provides the controlsignals to drive the aileron and elevator servos as well as the horizontal stabilizer trim. Theflight director provides computed steering commands using a command bar on the attitudedirector indicator portion of the PFD’s. The steering commands provide visual guidance forthe pilot to manually steer the aircraft as defined by the selected modes of operation.

Canadair Regional Jet 100/200 - Automatic Flight Control System

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Page 2: 1. INTRODUCTION - · PDF file1. INTRODUCTION The automatic flight control system (AFCS) provides integration of the autopilot and flight director systems. The AFCS system consists

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AUTOFLIGHT

AUTOPILOTFLIGHT DIRECTOR YAW DAMPER

AUTO TRIM

INTEGRATEDAVIONICS

PROCESSINGSYSTEM (IAPS)

AUTOMATICFLIGHT CONTROLSYSTEM (AFCS)

FLIGHT CONTROLCOMPUTER

(FCC) DIAGNOSTICS

Canadair Regional Jet 100/200 - Automatic Flight Control System

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ALT SELALT HOLD

CRUISE MODESROLL PITCHHDGVORFMS

PITCHVSSPD

DESCENT MODESROLL PITCH

HDGVORLOCFMS

10 DEGREESNOSE UP

GO--AROUND MODESROLL PITCH

HDGROLL HOLD

VSSPDPITCH

CLIMB MODES

ROLL PITCH

HDGVORFMS

15 DEGREESNOSE UP

TAKEOFF MODEROLL PITCH

WINGSLEVELHDGHOLD

GS

APPROACH MODESROLL PITCH

LOCVORFMS

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1. FLIGHT CONTROL AND GUIDANCE

Integration among the various avionics systems is provided by the integrated avionicsprocessing system (IAPS) which is a computer card cage located in the avionicscompartment. Two flight control computers (FCC’s), mounted inside the IAPS, are the maincomputers for the automatic flight control system (AFCS). Control logic for the dual flightdirectors, the two axes autopilot with automatic pitch trim and the dual yaw dampers iscontained within the two FCCs.

The FCC’s use altitude and heading reference system (AHRS) and air data computer (ADC)system information to calculate flight path and control parameters for the AFCS. Otherinputs to the flight control computers include selections made on the flight control panel,flight management computer outputs and radio system outputs.

The FCC’s use the inertial reference system (IRS) and air data computer (ADC) systeminformation to calculate flight path and control parameters for the AFCS. Other inputs to theflight control computers include selections made on the flight control panel, flightmanagement computer outputs and radio system outputs. <0025>

The flight control panel is the mode selection panel for selecting and controlling the flightdirector and autopilot functions.

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Flight Director andCourse Selector PanelsContains switches toselect basic pitch and rollmodes (when not coupled)and set course on primaryflight display.

Mode IndicatorsWhen a mode switch is pressed,a mode request is sent to theon--side flight control computer.If conditions are within limits, thecomputer acknowledges byilluminating the green lightsadjacent to the mode switch.The primary flight displayindicates the selected mode.

Flight Control PanelCenter Glareshield

Autopilot PanelContains switchesto couple, uncouple,transfer control andreduce gains on theautopilot.

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The PFD’s indicate the following AFCS information:

� Flight director modes and status

� Autopilot modes and status

� Elevator, stabilizer, and aileron trim failures

� Yaw damper disengagement

� Alternate and common source selections (attitude reference, air data reference anddisplay control panel selection)

� Flight director system monitor status.

Using the flight control panel, the crew can select the following functions:

� Remove flight director cues from the primary flight display and revert to basic pitch and rolldisplays

� Set course and fly to the active navigation source

� Engage, disengage and transfer control of the autopilot

� Reduce autopilot gains

� Set and maintain airspeed, vertical speed, and altitude

� Set navigation, heading selection and approach modes.

A. Flight Director

The flight director provides visual guidance, by means of command bars on the attitudedirector indicator (ADI), to fly the aircraft manually or to visually monitor autopilotresponse to the guidance commands. The visual guidance commands (pitch and rollcontrol) are integrated with the AFCS modes, selected on the flight control panel, forautopilot operation. AFCS operating modes can be selected to the flight directors withthe autopilot disengaged. Pitch (including speed control) and roll guidance cues fromthe AFCS are displayed on the ADI portion of the PFD’s.

The flight director system provides commands to perform the following:

� Hold a desired attitude

� Maintain a pressure altitude

� Hold a vertical speed

� Hold a Mach number or indicated airspeed

� Capture and maintain a preselected barometric-corrected altitude

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� Capture and track a preselected heading

� Capture and track a preselected radio course (VOR, LOC,GS)

� Capture and track a localizer and glideslope to establish Category 2

� Maintain a wings-level, fixed pitch-up attitude for go-around

� Provide windshear escape guidance.

NOTE

When the autopilot is in IAS or vertical speed modewith the flight director engaged, the flight director maycommand excursions beyond VMO/MMO.

Flight directors are simultaneously turned on by either selecting a vertical mode,selecting a lateral mode, or by engaging the autopilot. Flight director selection activatesall flight control mode annunciations and presents steering commands for the selectedmode(s). When both flight directors are turned on, by engaging the autopilot, basicmodes (pitch and roll) are automatically selected. When both flight directors are turnedon, by selecting a vertical or lateral mode, basic modes are automatically selected forthe other axis.

Transfer mode controls the routing of flight guidance commands to the autopilot andflight directors. When transfer mode is selected, the copilot’s flight guidance commanddrives both flight directors. When not transferred, the pilot’s flight guidance commanddrives both flight directors.

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Flight Director(magenta)

Primary Flight DisplayPilot’s and Copilot’s Instrument Panels

Flight Control PanelCenter Glareshield

FD Flag (red)Indicates that either thepitch or roll data is invalid.

FD

<0015>

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Flight Control PanelCenter Glareshield

Course PointerIndicates position on compass rosethat corresponds to selected course.Color matches navigation source.

To / From IndicatorIndicates direction to or from thetuned station or waypoint. Colormatches navigation source.

Multifunction Display -- HSI ModePilot’s and Copilot’s Instrument Panels

Cross--Side Course Pointer (cyan)Indicates position on compass rose thatcorresponds to cross--side selected course.Displayed when activated by navigationsource knob on display control panel.

Selected Course ReadoutIndicates selected course as set usingcourse knob on flight control panel.Color matches navigation source.

Primary Flight DisplayPilot’s and Copilot’s Instrument Panels

<0015>

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B. Synchronization

Flight director synchronization is selected by pushing the AP/FD SYNC switch on theinboard side of each control wheel when in the following modes:

� Speed

� VS

� Altitude hold

� Pitch and roll.

Selecting synchronization has no effect if the autopilot is engaged.

Synchronization is annunciated with a yellow SYNC on the primary flight display. Themessage will remain for 3 seconds, or until the AP/FD sync switch is released,whichever is longer.

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Control WheelRear View

Flight DirectorSynchronizationSwitch (black)Used when autopilot isnot coupled, tosynchronize verticaland lateral referencesto those currentlyflown.

Primary Flight DisplayPilot’s and Copilot’s Instrument Panels

SYNC (yellow)Displayed when flightdirector synchronizationis selected.

<0015>

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C. Flight Mode Annunciator

Located above the blue (sky) portion of the attitude director Indicator. The flight modeannunciator presents flight mode information in two fields separated by a vertical cyanline. To the left of the line is the active or captured field (green) and to the right of theline is the armed field (white). The bottom line of the fields contains vertical modeinformation and the upper line is lateral information.

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Primary Flight DisplayPilot’s and Copilot’s Instrument Panels

IAS 400

HDG

GSALTS

LOC11/2 BNK

1/2 BANKANNUNCIATION

VERTICAL ARMEDFIELD

LATERAL ARMEDFIELD

LATERAL CAPTUREOR ACTIVE FIELD

VERTICAL CAPTUREOR ACTIVE FIELD

<0015>

D. Lateral Modes of Operation

(1) Roll Mode

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(2) Lateral Take-Off Mode

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(3) Heading Select Mode

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(4) Navigation Mode

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Page 13: 1. INTRODUCTION - · PDF file1. INTRODUCTION The automatic flight control system (AFCS) provides integration of the autopilot and flight director systems. The AFCS system consists

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(5) Approach Mode

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Canadair Regional Jet 100/200 - Automatic Flight Control System

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Page 14: 1. INTRODUCTION - · PDF file1. INTRODUCTION The automatic flight control system (AFCS) provides integration of the autopilot and flight director systems. The AFCS system consists

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(6) Back Course Mode

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NOTE

In FD mode with B/C selected, the localizer deviationis in the correct direction either on the front or on theback course. <0026>

=��3 ���� � ���� ����� � ����������� &�� �&� �� �� �� �� (������.��� �� (���' � ���� 4�� �� �� �� �� ������� ��(���� .����' ��� � &�����)������ ����� ������.��� *=6� �6�+ �� �� ������� ��� .����, =��3 ���� � ������(����6����3�� � ����������� &�� � ���� �� �� �� �� ������� ��(���� .������ �� (������ .��� �� (��� &�� ������.�� �� ��)������ ����� *=6� �6�+,

=��3 ���� � ��(���� ��� �������' ���6�� (��)�����' �� �� ��� &�� �� .����������� �� �� ��� �. �� ������.� � ���)�� 1� .��� ������� ������� .��� ������ ���,

=��3 ���� � ������ ��.�������� � ��)�������� &�� �� ��)������ ����� � ���� ������!��,

(7) Half Bank Mode

4��. 1��3 ���� ������ �� ��%���� ��������� 1��3 ���� �� �# ����� ,-� ��������� ���� ���� ����� &��� ����� �� ��'5�� .���, 4��. 1��3 ���� � ���..��� �� ���� ���� �(�������,

Canadair Regional Jet 100/200 - Automatic Flight Control System

Page 14

Page 15: 1. INTRODUCTION - · PDF file1. INTRODUCTION The automatic flight control system (AFCS) provides integration of the autopilot and flight director systems. The AFCS system consists

4��. 1��3 ���� � ������� 1� (� �� �� �6� =�0> &��� �� �� ���, 4��.1��3 ���� � ������������� ������� &�� ����1�� ���� ��'5�� .��� *(�� �����������+ �� �. �� ������.� � �1�)� �� ��. 1��3 ���� ����� �������� &�� �� .����������� � ������ ��, ��������� � ���1���� &�� �� �� ��3���.. ����' ������������' ��� ��� �((���� ���� ��(����' �� ��� ��� ��� ������!�� ��(����,

4��. 1��3 ���� � �������� ������� 1� (� �� �� �6� =�0> &��� ����' ���� ������������� ������� &�� �� ������ ���� �� ��. 1��3 ���� �������������,

4��. 1��3 � ����������� &�� � &��� �6� =0> �� �� �� �� (������ .����� (���,

(8) Lateral Go-Around Mode

������� �������� ���� ������� � ����� ��� �������' &�� � # �����1��3 �����, ��������� �. ������� �������� ���� ���� �� 1�� .��� �������� '�� ���� �� ����(����' ��� ����� ��� ���� ������� ���� , ������� ��� )��������������� ���� �������� ��� ����������, 9�� ������� �������� ��� � ������(���� �� ����' �� �� ������ ����(���� �� ���� &����� ��� 1� ���������1� ������ (� �. � -2�� &���' �� 1� (� �� �� �� �� ������� &���,

������� �������� ���� � ������� 1� (� �� ��� �. �� ��� � ��)����������-2�� &���� &��� ���1����, ������� �������� ���� � ������� 1� �������� �.�� �/0� �� ������ ������� ����,

������� �������� � ����������� &�� � ���� �� �� �� �� �� ������� ��(����.���� �� �� (������ .��� �� (���,

E. Vertical Mode of Operation

(1) Pitch Mode

9�� (��� ���� � �������' �� (��� ��.������ *(��� ������� �� �� (������.��� �� (���+ � �� �� �� ������� (��� ����, ���� ���� ������� ������� �� �������� �� (��� ��.������ )����,

-� (��� ��.������ )���� ��� 1� ����� � �� �� 7� (��� &���, $������� �.�� 7� (��� &��� &��� ���� �� (��� ��.������ 1� �6� ����� (�� ����3, -�(��� ��.������ � �� �� �� �� ������� (��� �������� �(�� ����� ����(������������' ���� .����� �� (��� ����' �� �������!�����,

9�� �� (�� ������� �������� � ��(�����' ������� �� 7� (��� &��� �� ������ �� �������� (�� ����� ����,

9�� ��(����� �� ����3�� � (�� ������� ��������' � ��& (�� ������� ���������� � 1� �� �� (���� �� �� �������� �. (��� ����' �� �)��� �� �������������(���� �. �� �%� ��� (�� ������� ��������,

Canadair Regional Jet 100/200 - Automatic Flight Control System

Page 15

Page 16: 1. INTRODUCTION - · PDF file1. INTRODUCTION The automatic flight control system (AFCS) provides integration of the autopilot and flight director systems. The AFCS system consists

���� ���� � ������������� ������� &�� �� ���� )������� ���� � ����)�' ����� .��� �������� � ��, $������ �� 7� (��� &��� �� �� .��� ������� (���� &����������� ����� (��� ���� &�� �� .��� �������� � ��' ���� �� ���� ��(���(���� �� 7� ����, ���� ���� � ������� 1� �� �������� �. � )������� �������' �� 1� � )������� ���� ��(����,

���� ���� � ����������� &�� � ���� �-�4 �� �� �� �� )������� ��(����.���� �� �� (������ .��� �� (���,

(2) Vertical Take-Off Mode

7������� ��3���.. ���� ������� � �# ����� (�����( �������, �� �. ������� ���� �� (�����( ������� �� �� ����� ,

�������� )������� ���� ���� �� 1�� .��� �������� ' �� ���� �� ����(����'����� ��� ���� )������� ���� ��� &���� �� .��� ������� ������� �� ����� ����(������ ���.��������, ������� ��� )������� ��3���.. ���� �������� �������������,

9�� ��3���.. ��� � �� ����(���� �� ��������' �� �� ������ &����� ��� 1���������� 1� ������ (� �. � -2�� &���' �� 1� (� �� �� �� �� ������� &���,

7������� ��3���.. ���� � ������� 1� (� �� ��� �. �� ��� � ��)����������-2�� &���� &��� �� �� �����, 7������� ��3���.. ���� � ������� 1������ �� ����(����' 1� ������� ' �� 1� �� �������� �� ��(���� �. ����������)� ����,

7������� ��3���.. ���� � ����������� &�� � ���� -2 �� �� �� �� )���������(���� .���� �� �� (������ .��� �� (���,

(3) Altitude Preselect Mode

�������� (�� ����� ���� ������� ������� �� ��(���� ��� ����3 (�� ���������������, -� 1��������� (�� ������� �������� � �� (����� �� �� (������ .����� (���' ��� ���������� )�� �� ��- 3��1 �� �� .��� ������� (����,

�������� (�� ����� ���� � ����� �(�� ��������, -� ��(���� (���� � � .��������. ��� ��� ����' &�� �� ��(���� (���� ��)�� �&�� .��� �� (�� ������� ��������.�� � ��� ��� ���� ,

��(���� &��� ��� ����� �. �� (�� ������� �������� � ��&�� ���� ���������������, �� ��(����' �� (��)��� �� ����)� )������� ���� � �������,

. �� (�� ����� �������� � �����' �� �. �� 7� (��� &��� � ������� ������������� ��(����' �� ����(���� �� .��� �������� �������� �� ��(���� �� �������(�� ������� ��������,

. � ��& (�� ����� �������� � ��� ��' ��� �������� �. ��' ���4' �-�4 �� 7�����' &��� �� ��� �� �� ������� �������� 1��� ��(�����,

Canadair Regional Jet 100/200 - Automatic Flight Control System

Page 16

Page 17: 1. INTRODUCTION - · PDF file1. INTRODUCTION The automatic flight control system (AFCS) provides integration of the autopilot and flight director systems. The AFCS system consists

�.��� ��(����� (�� ������� �������� *�������� ����3+' �. (�� ����� �������� � �����' �������� ��� � ������������� ������� ��� �������� (�� ����� �������,

�� �� �� �� ��- 3��1 &��� ������ ����� ��� )� ��� ����� � ������� &�� ��(�� ������� ��������,

�������� (�� ����� ���� � ������������� ������� �(�� �������� �. ��� )�����������' �%��(� ���� ��(� ��(���� �� �)�� (���, �������� (�� ����� ���� � ������� 1� ���� ��(� ��(���� �� �)�� (���,

�������� (�� ����� � ����������� �� �� ��� &�� � &��� ��-� �� �� �� ��)������� ��� .���� .�� ���? � ���� ��-� ��� �� �� �� �� )������� ��(���� .����.�� ��(����' ��� � ���� ��-� �� �� �� �� )������� ��(���� .���� .�� ����3,�������� ��(���� ' &�� ��� ������� &����� � �1 �<���� �������� �. ������������3 �� ���' ��� ����������� &�� � �����& ��-� �� �� �� �� ���' &�� &��������� .�� �� ����� ' �� ����� �������� (�� ����� � �������' &���)�� � �����,

(4) Altitude Hold Mode

�������� ��� ���� ������� ������� �� ��(���� ��� �������� �� ����������.������, 9�� �������� ��� ���� � �������' �� �������� ��.������ � �� ���� ������� (�� ��� ��������,

9�� �������� ��� ���� � ������� 1� �� .��� ��������� � ���' ���������� ��.������ � � 1��������� )���� .��� �� 70�7' &�� � ���)����� ��(�� ��� �������� �(�� ���(������ �. ��(����,

-� �������� ��.������ � �� �� �� ������� (�� ��� �������� 1� �������� �. �������!�����, -��� � �� �� (��� �. �������� ��.������ )����,

�������� ��� ���� � ������� 1� (� �� �� ��- &��� �� �� .��� �������(����' �� 1� ����� �� �������� (�� ����� ����� &��� �� �������� (�� �����������3, � 70�7 ����' �������� ��� ��� 1� ������� 1� �� .��� ��������� � ���, ��������� � ���1���� &�� �� ���� ��(� ��(���� �� �)�� (���,

�������� ��� ���� � ������� 1� (� �� �� ��- &��� ����' 1� �������� �. �)������� ��� ����' �� 1� )������� ���� ��(����,

�������� ��� ���� � ����������� &�� � ���� ��- �� �� �� �� )���������(���� .���� �� �� (������ .��� �� (���,

(5) Speed Mode (CLB, DES, IAS)

�(��� ���� ������� ������� �� �������� �� ��� (��� ��.������ )����,9�� (��� ���� � �������' �� �� ��.������ *(������ .��� �� (���+ � �� ���� ������� ��� (���,

-� ��� (��� ��.������ ��� 1� �������� ��' � �� �� (��� 3��1, -� ��� (�����.������ � �� �� �� ������� ��� (��� 1� �� �������� �. �� �/0� �� ����������,

@(�� �������� ��(����' * ������� ��������+' (��� ���� � �� �1���,

Canadair Regional Jet 100/200 - Automatic Flight Control System

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Page 18: 1. INTRODUCTION - · PDF file1. INTRODUCTION The automatic flight control system (AFCS) provides integration of the autopilot and flight director systems. The AFCS system consists

�(��� ���� � �� (����� �� ����� �� �� ���4, ��������� �. �� (��� �������� �����(�� �� 1� (� �� �� ��::� 3��1 �� �� .��� ������� (����,

(6) Vertical Speed Mode

7������� (��� ���� ������� ������� �� �������� �� 7� ��.������ )����,9�� )������� (��� ���� � �������' �� 7� ��.������ *(������ .��� �� (���+ � �� �� �� ������� )������� (���,

-� 7� ��.������ )���� ��� 1� �����' ������� � A��'��� .���6����������' � �� �� 7� (��� &��� �� �� .��� ������� (����, -� 7� ��.������ � �� �� �� �� ������� )������� (��� 1� �� �������� �. �� �/0� �� ����������,

9�� ��(����� �� ����3�� � (�� ������� ��������' � ��& (�� ������� ���������� � 1� �� �� (���� �� �������� �. )������� (��� ����' �� �)��� �� �������������(���� �. �%� ��� (�� ������� ��������,

7������� (��� ���� � �������� ������� 1� (� �� �� 7� &��� �� �� .���������� (����, ��������� � ���1���� &�� �� ���� ��(� ��(���� �� �)�� (���,7������� (��� ���� � ������� 1� (� �� �� 7� &��� ����' 1� ������� �)������� ��� ����' �� 1� � )������� ���� ��(����,

7������� (��� ���� � ����������� &�� � ���� 7� B,B � �� 7� B,B � �� ��)������� ��(���� .���� �� �� (������ .��� �� (���, -� B,B � �� 7� ��.������)����' �� ��� ��� �. .���6������ *)���� �)�� ��'��� .���6������ ��� �� (�����&����� � ������� (����+, -� �( ����& �� (��� � (� ���)� ��.������ ��� ����&� ����& �� (��� � �����)� ��.������,

-� ��� �(����� �� �� ����)� ����, ��(���� &��� ��� ����� �. �� ������!�� � �����(�����' �� �. �� ��� � ��� �����)�� )���� ���� ��(� ����, @(�� ���� ��(���(����' ���� )������� ���� ��� ������������� ������� �� �� ��(����� ���, .�� ���� ��� ��� ��� ������������ ��(���� �� ���� ��(�' �� &��� �������� ���(����� �� �� ������� ����)� )������� ����' �� �� ��� )������� ����' ����� ������(�������� ��(���� ���� ��(�,

����1 �� �� ���� ���� � ����)�� 1� ��)�� �� ������ &��� �� �� .��� �������(����,

(7) Glideslope Mode

����� ��(� ���� &��� ������� ������� �� ��(���� ��� ����3 �� ���� ��(�,��(���� ��� 1� (��.����� .��� �1�)� �� 1���& �� ������!�� 1���,

-� ��(���� (���� � � .������� �. ��� ��� ����' &�� �� ��(���� (���� ��)���&�� .��� �� 1��� .�� � ��� ��� ���� , ��(���� &��� ��&�� ����� �. ��)������� �� ��� ��8 �. �� .��� ���� *����� �,� ���+,

Canadair Regional Jet 100/200 - Automatic Flight Control System

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Page 19: 1. INTRODUCTION - · PDF file1. INTRODUCTION The automatic flight control system (AFCS) provides integration of the autopilot and flight director systems. The AFCS system consists

����� ��(� ���� � ������������� ������� &�� �� �� �((���� ����' ��1����'&�� � )���� ������!�� � �� ������� ��)������ �����, ����� ��(� ���� � ������������� ������� 1� �� �� �. �((���� ����, 9�� �����' ���� ��(����� � �� � ������� 1� ������ ���1����' �� 1� �� �� �. � )���� ������!�� � ��������� ��)������ �����, 9�� ��(�����' ���� ��(� ���� � ������� 1������ �� ����� �. �� ������� ��)������ ���� �� �� ��)���� ������!��,

����� ��(� ����� � ����������� &�� � &��� �� �� �� �� �� )������� ���.���� �� �� ���, ����� ��(� ��(���� � ����������� &�� � ���� �� �� �� ���� )������� ��(���� .���� �� �� ���,

(8) Vertical Go-Around Mode

��������� ���� ������� � �������� (�����( �������,

��������� �. )������� �������� ���� ���� �� 1�� .��� �������� ' �� ���� ����(����' ����� ��� ���� )������� ���� ��� &���� �� .��� �������������� �� � ���������(������ ���.��������, 7������� ��� ������� ���� �������������,

9�� � �������� ��� � �� ����(���� �� �� ����' �� ����(���� &����� ���1� ��������� 1� ������ (� �� �� -2�� &���' �� 1� (� �� �� ���� ������� &���,

7������� �������� ���� � ������� 1� (� �� ����� ��� �. �� ��� ���)���������� -2�� &���� &��� ���1����, ��������� ���� � ������� 1������ �� ����(����' 1� ������� �� �/0� �� 1� �� �������� �� ��(���� �.������ ����)� ����,

��������� ���� � ����������� &�� � ���� �� �� �� �� �� )������� ��(����.���� �� �� (������ .��� �� (���,

F. Altitude Alert System

The primary flight displays (PFD’s) alert the pilots that the aircraft is approaching thepreselected altitude, or that the aircraft is deviating from a previously selected andacquired altitude. Altitude advisories are indicated on the altimeter portion of the PFD’sat the preselect altitude digital readouts (above the barometric tape). It is alsodisplayed at the preselect bugs, including the double bars (across the fine and coarsetapes).

The altitude alert system processes data from the air data computers and isindependent of autopilot or flight director mode. The ALT knob on the flight controlpanel is used to set the desired altitude.

The preselect digital readout and bugs change state and color as follows:

� At the altitude alert threshold, the readout and bugs flash magenta for approximatelyfour seconds, and a one-second aural tone sounds. The threshold is approximately1,000 feet from the selected altitude.

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� When within 200 feet from the selected altitude, the readout and bugs come onsteady to indicate altitude capture.

� If the aircraft subsequently deviates more than 200 feet from the selected altitude,the readout and altitude bugs (double bars) will flash amber and a one second tonewill be heard. The readout and altitude bugs will continue to flash amber as long asthe aircraft is deviated more than 200 feet or cancelled.

� When the airplane is --200 feet below selected altitude the flashing magenta bugsand readout will cancel.

� If the airplane subsequently continues to deviate (�1000 feet) from the selectedaltitude, a one second tone will be heard.

� When the airplane is again within 200 feet of the selected altitude, the readout andbugs will turn magenta and stop flashing.

Altitude alerts can be cancelled by pushing the ALT switch or selecting a differentaltitude. Altitude alerts are inhibited if the glideslope is captured.

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+200 FT

+100 FT

PRESELECT ALT

--100 FT

--200 FT

--1000 FT

ALTITUDE DEVIATION(DIGITAL READOUT AND BUGFLASH YELLOW CAN BECANCELLED BY PILOT.MAJOR ALT DEVIATIONAT +/-- 1000 FEET.)

DEVIATIONNOTICE

CAPTURE

DEVIATION NOTICE(SELECTED ALTITUDE BUG(DOUBLE BARS) FLASHES

IS MAGENTA)

CAPTURE(SELECTEDALTITUDE BUGAND READOUTBOTH MAGENTA)

(FLASHING WARNINGCANCELS IF NOTPREVIOUSLYCANCELLEDBY THE PILOT.)

ALTITUDE AQUISITION(DIGITAL READOUT AND 1BUGFLASH MAGENTA--MAY BECANCELLED BY PILOT;AURAL TONE SOUNDS FOR 1 SEC.)

AURAL TONEFOR 1 SECOND

AURAL TONEFOR 1 SECOND

MAGENTA, READOUT

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AFCS MSG FAILWarning (red)

IAPS DEGRADED status (white)Indicates that an IAPS bus has failed.

IAPS OVERTEMP status (white)Indicates that an IAPS overtemperaturecondition has been detected.

FD 1 or 2 FAIL status (white)Indicates that the respective flightdirector has failed.

SPEED REFS INDEPStatus (white)Comes on to indicatethat the pilot’s andcopilot’s V--speedselections are notsynchronized.

Comes on to indicatethe presence of aninvalid flight controlsystem (FCS)message.

AFCS MSG FAIL

Primary Page

<0039>

<0006>

Status Page

FD 1 FAIL

<0039>

<0039>

FD 2 FAIL

IAPS DEGRADED

IAPS OVERTEMP

SPEED REFS INDEP

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G. System Circuit Breakers

SYSTEM SUB--SYSTEM CB NAME BUS BAR CBPANEL

CBLOCATION

NOTES

IntegratedAvionics

Left AFCSIAPS LEFTAFCS

DC BAT 2 P7AvionicsProcessorSystem Right AFCS

IAPS RIGHTAFCS

DC BUS 2 2 H3

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1. AUTOPILOT

The automatic flight control system (AFCS) provides a two axes, digital, fail-passive autopilot(AP). The AP system automatically controls the aircraft in the pitch, roll and yaw axis, inresponse to flight director commands, by actuating the appropriate control surfaces. Thefail-passive AP system is protected against internal single hardware faults and limits anymalfunctioning commands to a response that is easily controlled by the pilot. Commandinputs to the ailerons and elevators are provided by servos controlled by the flight controlcomputers (FCC’s). The FCC’s input the yaw damper system to control the rudder

To engage the autopilot, the following is required.

� Both flight control computers must be operative and detecting no failures

� The AP DISC switch--bar is in the UP position

� At least one channel of the horizontal stabilizer trim is operative

� At least one yaw damper is engaged

� At least one AHRS system is operable

� At least one IRS system is operable <0025>

� At least one air data computer (ADC) is operative

� There is no significant instability of the aircraft

NOTE

Significant instability exists during the followingconditions: pitch rate over 5 degrees/second, normalacceleration less than --.4g or over.6g, roll rate over 21degrees/second, bank angle over 45 degrees, pitchangle below 15 degrees nose down or above 25degrees nose up, or when the yaw rate exceeds 9degrees/second.

The AP is annunciated with lights at the side of the AP ENG switch on the FCP and a greenAP message on the EICAS status page. During AP synchronization, the AP annunciationchanges to amber.

A warning for AP engagement during take--off is annunciated with a red CONFIG APmessage on the EICAS pimary page and a “CONFIG AUTOPILOT” aural alert.

Turbulence mode reduces autopilot gain so that flight control computer response to turbulentflight conditions is slowed and aircraft motion is smoother. Turbulence mode is selected bypushing the TURB switch on the FCP Turbulence mode cannot be selected, if the on-sidelocalizer is captured, or if the AP is disengaged. Turbulence mode can be cleared bypushing the TURB switch again, by an on--side localizer capture or by AP disengagement.

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Flight Control PanelCenter Glareshield

<0015>

Primary Flight DisplayPilot’s and Copilot’s Instrument Panels

Green indicator lights on eitherside of switch indicate engaged.

NOTE

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The autopilot can be disengaged manually by any of the following:

� Pushing either AP/SP DISC switch on the control wheels

� Pushing the AP ENG switch on the flight control panel

� Lowering the AP DISC switch-bar on the flight control panel (a red line becomes visible)

� Operating either stabilizer trim switch on the control wheels

� Pressing either TOGA switch on the thrust levers

� Switching to the standby FCC

� Pressing the yaw damper DISC pushbutton on the yaw damper panel.

Disengagement of the autopilot causes a cavalry charge aural alert to sound and the APindication on the primary flight display (PFD) turns red. The autopilot disengage warning willautomatically cancel, after approximately two repetitions of the cavalry charge, when adisengagement is mutually induced.

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Flight Control PanelCenter GlareshieldAP DISC

Lowering bar disengages autopilot.Red line becomes visible.

Pilot’s Control Wheel(Copilot’s Opposite)

AP / SP DISC (red)When pressed, disengagesautopilot and deactivatesstick pusher. Whenreleased, stick pushersystem is immediatelyreactivated, but autopilotremains disengaged.

CAVALRYCHARGE

Take--Off/ Go--Around(TOGA) SwitchesMomentary pushbuttonswitches associated withthe take--off/ go--aroundmode of the flight director.

Yaw Damper PanelCenter Pedestal

DISCUsed to disengageyaw dampers.

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Automatic AP disengagement occurs if:

� Both yaw dampers are disengaged or fail

� A failure condition is detected by the FCC monitoring circuits

� Stick shaker is activated

� Excessive attitude occurs (roll beyond 45 degrees or pitch beyond 25 degrees nose--upor 17 degrees nose--down)

� Two seconds after a windshear warning (if the autopilot has not already beendisengaged). During those two seconds, the autopilot will follow the windshearcommands.

In the event that the autopilot is disengaged due to a system fault, pressing the AP/SP DISCswitch or either TOGA switch will cancel the red flashing AP indication on the PFD andsilence the aural warning.

The automatic flight control system monitors both axes of the autopilot when engaged. If acontrol surface is detected to be significantly out of trim, an indication will appear on the PFDand a caution message will be displayed on the EICAS primary page to indicate in whichdirection that the control surface is out of trim.

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Primary Flight DisplayPilot’s and Copilot’s Instrument Panels

Aileron Mistrim Indicator (yellow)Iindicates that the ailerons are in amistrim condition, when the autopilotis engaged.

Elevator Mistrim Indicator (yellow)Indicates that the horizontal stabilizeris in a mistrim condition, when theautopilot is engaged.

<0015>

E

A

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CONFIG AP

Primary Page

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<0006>

Status Page

YD 1 INOP

YD 2 INOP

YAW DAMPER

AP TRIM IS LWD

AP TRIM IS NU

AP TRIM IS RWD

AP PITCH TRIM

AP TRIM IS ND

YD 1, 2 INOP Status(white)Comes on to indicatethat either yaw damperchannel is inoperative.

AP PITCH TRIM Caution (amber)Comes on to indicate a failure in theautopilot pitch trim system.

AP TRIM IS LWD Caution (amber)Comes on to indicate an out--of--trimcondition in the roll axis (left wing down).

AP TRIM IS NU Caution (amber)Comes on to indicate an out--of--trimcondition in the pitch axis (nose up).

AP TRIM IS ND Caution (amber)Comes on to indicatean out--of--trim conditionin the pitch axis (nose down).

AP TRIM IS RWD Caution (amber)Comes on to indicate an out--of--trimcondition in the roll axis (right wing down).

YAW DAMPER Caution (amber)Comes on when both yaw damper channels(1 & 2) are off or when all IAPS input bussesare invalid.

”Config autopilot”

<0039>

<0039>

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