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P I L O T T R A I N I N G G U I D E
Chapter 2: Automatic Flight Control System
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
For Training Purposes Only
Sept 04
AUTOMATIC FLIGHT CONTROL SYSTEM
TABLE OF CONTENTS
Page
2-i
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Table of Contents
Summary of Contents for BOMBARDIER Primus 2000XP
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Page 1: Table Of Contents
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E Chapter 2: Automatic Flight Control System TABLE OF CONTENTS Page Introduction ......................... 2-1 Description .......................... 2-1 Guidance Panel......................2-1 AFCS Schematic...................... - Page 2 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E PAGE INTENTIONALLY LEFT BLANK For Training Purposes Only 2-ii Sept 04...
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Page 3: Introduction
P I L O T T R A I N I N G G U I D E 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. - Page 4 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E 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: •...
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Page 5: Afcs Schematic
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E AFCS SCHEMATIC TOUCH TRIM SWITCHES CONTROL STEERING AP DISC (TCS) BUTTON TOGA BUTTONS THRUST CONTROL WHEEL IDLE MAX REV GUIDANCE PANEL Honeywell BANK... -
Page 6: Autopilot
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E 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. - Page 7 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E 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...
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Page 8: Autopilot Engagement
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E 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. -
Page 9: Autopilot Disengagement
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E AUTOPILOT DISENGAGEMENT Autopilot disengagement is accomplished by activating any of the following: • AP button on guidance panel •... -
Page 10: Yaw Damper
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E 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. -
Page 11: Pfd Annunciation
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E PFD ANNUNCIATION LNAV ATT2 0.88 VAPP VNAV ADC1 23500 AP ENGAGE STATUS LNAV ATT2 0.88 VAPP VNAV ADC1 23500 TOUCH CONTROL STEERING (TCS) STATUS VNAV... -
Page 12: Flight Director (Fd)
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E FLIGHT DIRECTOR (FD) The Flight Director modes of operation can be divided into two major subgroups, the Lateral modes and the Vertical modes. Only one lateral mode and one vertical mode may be active (green) at any time;... - Page 13 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E Flight director command bars appear on the PFD whenever a lateral mode is selected. The FD switch is used to remove flight director command bars. If the AP is on, the off- side button will remove the off-side flight director bar(s) only.
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Page 14: Guidance Panel
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E GUIDANCE PANEL Flight Director (FD) Switch Navigation (NAV) Switch Used to remove flight director command Used to arm lateral guidance Bank (BANK) Switch bars. - Page 15 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E GUIDANCE PANEL (Cont) AP and YD Pointers Illuminate to indicate which AP guidance computer or yaw damper channel is active. Arrows to the left mean FGC No 1 is Flight Director (FD) Switch controlling.
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Page 16: Flight Director Modes
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E FLIGHT DIRECTOR MODES LATERAL MODES SWITCH (GUIDANCE PANEL) MODE ANNUNCIATION Heading Select Based on displayed navigation source VOR / LNAV / LOC (VOR, FMS, or localizer) Based on VOR navigation source VAPP... -
Page 17: Lateral Modes
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E BASIC MODES SWITCH (GUIDANCE PANEL) MODE ANNUNCIATION None Roll Hold None Roll Hold Submode (wings level) Roll Hold Submode (heading hold) None Pitch Hold LATERAL MODES... - Page 18 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E Heading Select (HDG) Mode The heading select mode is activated via the HDG switch on the guidance panel. HDG Switch: When selected, activates heading mode.
- Page 19 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E The bank angle can also be toggled between high and low bank limits by means of the BANK switch on the guidance panel. When heading or VOR mode are active with the low bank limit, an “eyebrow”...
- Page 20 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E VOR Mode VOR mode provides for automatic intercept, capture and tracking of a selected VOR radial. This mode is used to navigate on an airway between two VOR stations. This mode is NOT to be used to intercept and track a VOR radial for a VOR approach.
- Page 21 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E CONE OF CONFUSION - is used to detect erratic radio signals encountered in the area above VOR transmitter. OSS1 monitors beam deviation and will occur when: •...
- Page 22 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E ATT2 ATT2 VNAV VNAV ADC1 ADC1 0.856M 0.856M 30.0NM 30.0NM VOR1 VOR1 VOR 1 VOR 1 SELECTED SELECTED HEADING SELECTED 030°...
- Page 23 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E Localizer (LOC) Mode Localizer mode provides for automatic intercept, capture and tracking of the front course localizer beam, to line up on the centerline of the runway in use. Localizer capture and tracking commands are based on the distance-to-transmitter.
- Page 24 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E ATT2 ATT2 VNAV VNAV ADC1 ADC1 0.856M 0.856M 10.0NM 7.0NM LOC1 LOC1 090° LOCALIZER SELECTED INBOUND 040° HEADING COURSE 090°...
- Page 25 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E Back Course (BC) Mode Back course mode provides for automatic intercept, capture, and tracking of the back course localizer signal. BC mode is identical to LOC mode except that the transmitter is located 2000 feet in front of the touch-down point.
- Page 26 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E ATT2 VNAV ADC1 0.856M LOC1 330° LOCALIZER 090° INBOUND COURSE RUNWAY Typical Capture Point BACK COURSE MODE INTERCEPT ATT2 ATT2 VNAV...
- Page 27 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E FMS Lateral Navigation (LNAV) Mode The FMS lateral steering command is a roll command which aligns the airplane with the flight plan in the FMS.
- Page 28 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E Previewed Approach Preview Navigation 23.4NM Source FMS1 LOC1 Preview Course Pointer For Training Purposes Only 2-26 Sept 04...
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Page 29: Bearing (Brg) Source
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E BEARING (BRG) SOURCE Bearing information VOR1, ADF1 or FMS1 and bearing information VOR2, ADF2 or FMS2 is selected on either the pilot’s and/or the copilot’s PFD control panel, located on the glareshield. -
Page 30: Vor/Loc Nav Source
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E VOR/LOC NAV SOURCE NAV source, VOR/LOC, is selectable on either the pilot’s and/or the copilot’s PFD control panel. NAV SRC VOR1 VOR2... -
Page 31: Fms Nav Source
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E FMS NAV SOURCE FMS source, FMS1, FMS2, FMS3 (if installed) or Navigation Display Unit (NDU), also referred to as Lasertrack (LTRK) (if installed) is selectable on either the pilot’s and/or the copilot’s PFD control panel. -
Page 32: Vertical Modes
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E FMS1 LOC1 Preview Course Pointer Preview NAV Source NOTE If FMS is the primary NAV source, the first push of the V/L button will set preview NAV source. - Page 33 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E FLC will command a proportional thrust increase/decrease during small climbs and descents. In large climbs or descents, FLC will command climb thrust or idle thrust as required.
- Page 34 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E Pitch Hold (PIT) Mode PIT mode is automatically selected when no other vertical mode is active, and the autopilot is engaged.
- Page 35 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E When VS mode is active, the pitch angle is limited to ± 20°. The vertical speed commands are from - 8000 feet/minute to + 6000 feet/minute. VS mode is activated by selecting VS on guidance panel.
- Page 36 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E Altitude Hold (ALT) Mode ALT mode is used to maintain a barometric altitude reference. ALT mode is activated automatically following preselect altitude capture (ASEL), or can be activated manually via the altitude switch (ALT) on the guidance panel to maintain a pressure altitude at time of selection.
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Page 37: Multi-Axis Modes
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E • VASEL - Operates identical to ASEL mode. VASEL submode will arm as soon as VFLC or VPTH is engaged VASEL mode is canceled whenever VALT mode engages •... - Page 38 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E Tracking performance for glideslope mode is within ± 1 dot from 700 to 100 feet (radio altimeter). ASEL is inhibited during glideslope capture. During a CAT 2 approach, EFIS will monitor for excessive deviation from the beam and will provide appropriate annunciation.
- Page 39 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E VNAV Vertical Deviation Scale H09.0NM H12.0NM LOC1 LOC1 SELECTED 045° HEADING Typical Capture Point 090° is 1/3 Dot on GS Scale LOCALIZER INBOUND COURSE...
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Page 40: Takeoff (To) Mode
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E TAKEOFF (TO) MODE TO mode provides pitch and lateral commands during the takeoff phase of flight. TO mode is activated by pushing one of the throttle-mounted TOGA buttons, while on the ground. -
Page 41: Windshear Guidance (Wshr) Mode
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E Vertical GA mode generates a fixed pitch attitude of 10°, based on power being developed by the engines. The autothrottle will provide full takeoff thrust until GA mode is cleared. - Page 42 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E For a decreasing performance shear (downdraft/tailwind), a red “WINDSHEAR” warning message will be displayed on the PFD. When WSHR mode is active, the flight director lateral and vertical modes will be deactivated and replaced by the “ROL”...
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Page 43: Automatic Emergency Descent Mode
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E AUTOMATIC EMERGENCY DESCENT MODE The “Cabin Altitude” aural warning is enunciated when cabin altitude exceeds 9000 feet. The EDM mode is automatically entered anytime the following criteria is met: •... -
Page 44: Autopilot - Flight Director Eicas Messages
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E • Activation of TCS for greater than 1 second is considered an autopilot disengagement • The autopilot is disengaged at anytime while in EDM •... - Page 45 AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E AUTOPILOT – FLIGHT DIRECTOR EICAS MESSAGES (Cont) AFCS 1 (2) FAIL Indicates that AFCS (one or both) functions has failed. The AFCS functions include yaw damper, autopilot AFCS 1 FAIL and flight director.
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Page 46: Ems Circuit Protection
AUTOMATIC FLIGHT CONTROL SYSTEM P I L O T T R A I N I N G G U I D E EMS CIRCUIT PROTECTION CIRCUIT BREAKER SYSTEM PREV NEXT EMER STAT CNTL TEST PAGE PAGE CONT For Training Purposes Only 2-44 Sept 04...
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