ATA 22 B1 Autoflight - Issue 6 January 2023_Compress.pdf

BOMBARDIER DHC 8-400 (PWC PW150) ATA 22 - AUTOFLIGHT TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY B1 MAINTENANCE TRAINING MANUAL Issue 6 - January 2023 Page 1 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM YAW DAMPER PURPOSE The Yaw Damper (YD) stabilizes the aircraft on its...

BOMBARDIER DHC 8-400 (PWC PW150) ATA 22 - AUTOFLIGHT TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY B1 MAINTENANCE TRAINING MANUAL Issue 6 - January 2023 Page 1 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM YAW DAMPER PURPOSE The Yaw Damper (YD) stabilizes the aircraft on its yaw axis and is used for turn coordination. The autoflight system gives indications for manual flight control and automates flight guidance. GENERAL DESCRIPTION The autopilot pitch trim function decreases the mistrim force on the control columns when the AP is engaged. The AFCS has these functions: • • • • • • AUTOPILOT PITCH TRIM FLAP PITCH TRIM Flight Director Commands Autopilot vertical and lateral guidance Makes AP disengagement indications Yaw damping and turn coordination AP Pitch Trim Flap Pitch Trim The flap pitch trim function decreases the mistrim force on the control columns when the AP is not engaged and the flaps are in transit. FLIGHT DIRECTOR (FD) The Flight Director (FD) gives lateral and vertical guidance. AUTOPILOT (AP) The Autopilot (AP) uses data from the FD to move the aircraft control surfaces for automatic flight guidance control. AP DISENGAGE INDICATIONS Two AP disengage warnings are used to show an automatic AP disengage caused by a malfunction. The lights are located on the glareshield panel. The Flight Mode Annunciators (FMA), located on the Primary Flight Displays (PFD), show other AFCS annunciations. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 2 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - AFCS SYSTEM BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 3 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) PURPOSE Autopilot Flap AUTOPILOT PITCH TRIM The Automatic Flight Control System (AFCS) automatically incorporates the following different functions: • • • • • • • Flight Director (FD) Autopilot (AP) Tactile Control Steering (TCS) Yaw Dampening Automatic Pitch Trim The autopilot auto pitch trim function decreases the mistrim force on the control columns when the AP is engaged. FLAP AUTO PITCH TRIM The flap auto pitch trim function decreases the mistrim force on the control columns when the AP is not engaged and the flaps are in transit. FLIGHT DIRECTOR (FD) The Flight Director (FD) gives lateral and vertical guidance. AUTOPILOT (AP) The Autopilot (AP) utilises data from the FD to operate the aircraft control surfaces for automatic flight guidance control. TACTILE CONTROL STEERING (TCS) With the AP engaged, the TCS mode allows the pilots to manually adjust the control surfaces without disengaging the AP. YAW DAMPER The Yaw Damper (YD) stabilizes the aircraft on its yaw axis and is used for turn coordination. AUTOMATIC PITCH TRIM The AFCS has two separate automatic pitch trim functions: TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 4 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - AFCS BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 5 of 145 BOMBARDIER DHC 8-400 (PWC PW150) • AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) COMPONENTS The AFCS incorporates the following components: • • • • • • • • The Yaw Damper Actuator Unit (YDAU) is an electrical linear actuator. It is summed in series with the manual rudder pedal inputs to control the rudder when the YD is engaged. The pitch and roll Autopilot Actuator Units (APAU) have a separate rotary servo motor and capstan. They move the control columns and hand-wheels through cables when the AP is engaged. The APAU is the same for the pitch and roll axes. There are two autopilot disengage (A/P DIS) pushbutton switches. One or the other A/P DIS pushbutton switch is used to manually disengage the AP or to cancel an AP or YD disengage warning. The A/P DIS switches are located on the outboard side of each hand-wheel assembly. Go Around (GA) Switches Tactile Control Steering (TCS) Switches Hand-wheel Disengage Switches The AFCS has two flight directors, one single autopilot, and one yaw damper. It has a weather approach capability that is limited to Category II for ILS and Category I for MLS as follows: • • • • Non-precision VOR Front and Back Course Localizer MLS Azimuth FMS FD AP and YD TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY There are two Tactile Control Steering (TCS) pushbutton switches. One or the other TCS pushbutton switch is used to momentarily override the AP without disengaging it. The FD targets in some FD modes can change. There are two Go Around (GA) pushbutton switches to disengage the AP and select the GA FD mode (wings level). The GA pushbutton switches are located on the outboard sides of the two power levers. The two Flight Guidance Modules (FGM1, FGM2) operate independently to make calculations and control these systems: • • Each FGM can independently calculate the FD commands but two FGMs are necessary to do the AP and YD functions. FGM1 supplies the actual commands to the AP and YD actuators and FGM2 monitors the commands and their operation. The FGMs are installed in the Integrated Flight Cabinets (IFC). Electrical power is supplied to the FGMs through a Primary Power Supply Module (PPSM) in the IFC. The AP and YD are automatically disengaged if one or the other FGM has malfunctioned. The Flight Guidance Control Panel (FGCP) is used to make mode, target, navigation source, and autopilot and yaw dampener engagement selections. Flight Guidance Modules Flight Guidance Control Panel Roll Actuator Roll Capstan Pitch Actuator Pitch Capstan Yaw Damper Actuator Autopilot Disconnect Warning Lights The AFCS also has these components that are part of other assemblies: • • • Automatic Pitch Trim Two AP disengage warning lights are used to show an automatic AP disengage caused by a malfunction. The lights are located on the glareshield panel. The Flight Mode Annunciators (FMA), located on the Primary Flight Displays (PFD), show other AFCS annunciations. ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 6 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - AFCS BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 7 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION The Automatic Flight Control System (AFCS) functions in these modes: • • • • • • • • • • ARINC 429 Outputs Memory Partitioning HW Monitoring Time Partitioning HW Monitoring I/O Sequencer Analogue Reference Voltages Analogue Inputs AP and YD Engage/Disengage HW Logic The results of the POST are stored in EEPROM. If there is a long-term power interruption in flight, the FGM will not do a test. It will use the stored Power On Self Test (POST) results to determine its status. Power-On Self Test (POST) Operational Maintenance If there is a long-term power interruption while the aircraft is in flight, the FGM will not do a POST. It will use the stored Power-On Self Test (POST) results to determine its status. POWER ON SELF TESTS The AFCS does a Power On Self Test (POST) after a long-term power interruption while the aircraft is on the ground. The Power On Self Tests (POST) senses AFCS hardware malfunctions that are not continuously monitored in the operation mode or apparent to the pilots. Each FGM does a POST independently of the other FGM. Each FGM supplies discrete signal to the other to make sure that they do not start a POST at the same time. Each FGM does a POST twice before it declares a malfunction. If the POST senses a malfunction, the FGM prevents the AP and YD modes from operating. The POST tests these parameters: • • • • • • • • Programme Memory Data Memory Watch Dog Power Supplies HW Monitoring Discrete Inputs Discrete Outputs Module Validity HW logic ARINC 429 Inputs TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 8 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM moment of AP engagement. AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) For aircraft acceleration, the AFCS commands have these limits: • • • DETAILED DESCRIPTION Maximum load factor in pitch, 0.2 g Maximum roll angular acceleration, ± 4°/second² Maximum yaw angular acceleration, ± 8°/second² OPERATIONAL MODE The operational mode has these modes: • • • • • Flight Director (FD) Autopilot (AP) Tactile Control Steering (TCS) Yaw Damper (YD) Automatic pitch trim The AFCS operates when these conditions are: • • • • Indicated Air Speed is more than 1.2 VSR stall reference and less than 290 KIAS Cruise altitude between 0 and 27,000 feet (0 and 8230 meters) Decision height (DH) is 100 feet (30.5 meters) (Category II approaches) Minimum Use Height (MUH) is 51 feet (15.5 meters) The YD cannot be engaged when the aircraft roll attitude is more than ± 45°. The AP cannot be engaged when the aircraft roll attitude is more than ± 45°, or the aircraft pitch attitude is more than ± 20°. The YD always engages with an AP selection. The YD can also be engaged when the AP is not selected. The AFCS automatically synchronizes FD commands for FD mode transitions to minimize transient inputs to the control surfaces at the moment of the mode transitions. Similarly, before AP engagement, the AFCS automatically synchronizes to the existing aircraft pitch and roll attitude to minimize transient inputs to the control surfaces at the TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 9 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION FLIGHT DIRECTOR The Flight Director (FD) aircraft lateral and vertical guidance indications are shown on the PFDs for manual control of the aircraft. They are coupled to the autopilot for automatic control of the aircraft. The Flight Guidance Control Panel and the Go Around mode switches are used to make FD mode selections. The two FGMs receive inputs from the FGCP and the GA switches. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 10 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD MODE, FGCP CONTROLS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 11 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION Each FGM can independently control the FD function. They function as A master and slave in the Flight Director (FD) mode. The FGM 1 is master and FGM 2 is slave. The FGM 2 slaves to the FGM 1 FD modes. If FGM 1 malfunctions, FGM 2 automatically becomes the master. One FGM is required for the FD function. If one FGM malfunctions, the autopilot cannot be engaged but the lateral and vertical guidance modes are operable. The FD operates in these modes: • • Active Armed ACTIVE An active FD mode supplies guidance data to the PFDs for indication, and to the autopilot for automatic flight control. ARMED During an armed FD mode, the system is waiting for the necessary conditions to be satisfied. When the necessary armed conditions are satisfactory, the FD mode automatically changes to an active mode. The selected armed FD mode is shown in white. When it changes to the active mode, its indication is shown in reverse video, black letters on a green background. An asterisk is also shown when the system is not in the track mode. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 12 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD MODE, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 13 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION When the FD part of the FGM malfunctions, the Flight Mode Annunciators (FMA) at the top of the PFD shows a L FD FAIL or a R FD FAIL message. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 14 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD MODE, L OR R FD FAIL STATUS MESSAGE TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 15 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION If the two FD modes are not available because the two FGMs have malfunctioned, the FMA shows an AFCS FAIL message. The Flight Guidance Modules have these functions: • • FD mode selections Source selection and monitoring TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 16 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD MODE, AFCS FAIL STATUS MESSAGE TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 17 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM The PFDs show this FGM data: AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION The FGMs use the data that is shown on one PFD or the other to calculate the FD guidance commands. The HSI SEL pushbutton switch located on the FGCP is pushed to select which PFD is used. It uses this shown PFD data: • • • • • • • • Pitch and roll command bars Flight director mode annunciation on the Flight mode Annunciator (FMA) AFCS messages on the FMA The two PFDs show the FD command bars and mode annunciations from the master FGM. If both FGMs are serviceable, the FD data from FGM1 is shown on the two PFDs. The FD data from FGM2 is only shown on the two PFD when FGM1 has malfunctioned. In the dual FD mode, PFD1 shows FD command bars and mode annunciations from FGM1, and PFD2 shows FD command bars and mode annunciations from FGM2. The FD commands are shown in single or double cue format as programmed by the Aircraft Configuration Module (ACM). Air Data Unit (ADU1, ADU2) Attitude and Heading Reference System (AHRS1, AHRS2) Navigation (NAV1, NAV2, ILS1, ILS2, FMS1, FMS2, MLS1, MLS2) Course targets Heading targets NOTE: When operating in the Dual FD mode, each FGM uses its related navigation sources. The armed or active FD mode automatically cancels when a source required for the calculation malfunctions and an applicable message is shown on the FMA. If a FD mode is selected with source data that has malfunctioned, the armed to active mode change will not occur and a message will be shown on the FMA. When the FGMs sense a mismatch condition between two sources, the FD mode is not cancelled because the two FGMs use the same selected data. During the dual FD mode, a mismatch condition between ILS sources automatically cancels the mode. The dual FD mode also requires two serviceable AHRS and ADUs. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 18 of 145 BOMBARDIER DHC 8-400 (PWC PW150) INTENTIONALLY LEFT BLANK TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 19 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION LATERAL MODES The FD incorporates the following lateral modes: • • • • • • • • Roll hold, wings level, heading hold (Lateral Basic) Heading select VOR VOR approach Localizer Backcourse FMS LNAV MLS azimuth TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 20 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION LATERAL MODES ROLL HOLD The roll hold sub-mode gives FD commands to hold the roll attitude after a mode selection or after the Tactile Control Steering (TCS) switch is released when these conditions are: • • The AP or a vertical FD mode selection is made with no lateral mode selection The bank angle is more than 6 degrees and less than 45° When the TCS switch is pushed the roll hold sub-mode changes to the wings level sub-mode when the bank angle is less than 6°. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 21 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION LATERAL MODES WINGS LEVEL The roll hold sub-mode gives FD commands to hold a zero degree bank angle after the mode selection when these conditions are: • • The AP or a vertical FD mode selection is made with no lateral mode selection The bank angle is less than 6° When a Go Around (GA) selection is made, the FD operates in the lateral basic, wings level and pitch hold sub-mode. It stays wings level until another lateral mode is selected, or until the TCS is operated and released with the roll angle more than 6°. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 22 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD ROLL HOLD MODE, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 23 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION LATERAL MODES HEADING HOLD The heading hold sub-mode gives FD commands to hold heading after a vertical mode selection is made. In the heading hold sub-mode, the FD commands are limited to ± 13 degrees of roll attitude. The heading hold sub-mode is cancelled by any of these conditions: • • • • • • A FD HDG, NAV, APPR, BC lateral mode manual selection Automatic capture of a lateral mode The AP is disengaged while in the pitch hold mode A STBY selection on the FGCP is made A HSI SEL selection on the FGCP is made when the AP is not engaged An ADU or AHRS source reversion selection is made when the AP is not engaged The heading hold sub-mode is cancelled and its operation is inhibited by any of these conditions: • • The CAS or TAS data from the selected ADU has malfunctioned The attitude data from the selected AHRS has malfunctioned The heading hold sub-mode is cancelled and its operation is prevented when the heading data from the selected AHRS malfunctions. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 24 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD HEADING HOLD MODE, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 25 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION LATERAL MODES HEADING SELECT MODE The heading select mode gives FD commands to intercept and maintain a magnetic heading. ON AIRCRAFT WITH THE AFCS LEFT AND RIGHT COUPLED HEADING SET KNOB (822CH00013) The pilot or co-pilot heading (HDG) knob located on the FGCP is used to set the selected heading target on PFD1 and PFD2 Electronic Horizontal Situation Indicator (EHSI) heading scales. The HSI SEL pushbutton switch located on the FGCP is pushed to select which PFD is used. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 26 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD, FGCP HEADING SELECT MODE CONTROLS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 27 of 145 BOMBARDIER DHC 8-400 (PWC PW150) • AUTOFLIGHT SYSTEM The selected heading target from the FGCP has malfunctioned AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION LATERAL MODES HEADING SELECT MODE CONTINUED The FGMs use the selected heading target that is shown on the PFD to calculate the FD guidance roll commands when these conditions are: • • A HDG selection on the FGCP is made A NAV or APPR or BC selection on the FGCP is made to arm a VOR, Localizer, Back-course Localizer, or Azimuth mode In the heading select mode, the FD commands are limited to ± 24° of roll attitude, and rate limited to ± 4°/second of roll rate. The heading select mode is cancelled by any of these conditions: • • • • • • The HDG pushbutton switch on the FGCP is pushed again to cancel the mode A FD, NAV, APPR, BC lateral mode pushbutton switch on the FGCP is pushed Automatic capture of a lateral mode A STBY selection on the FGCP is made A HSI SEL selection on the FGCP is made when the AP is not engaged An ADU or AHRS source reversion selection is made when the AP is not engaged The heading select mode is cancelled and its operation is inhibited by any of these conditions: • • The heading data from the selected AHRS has malfunctioned The CAS or TAS data from the selected ADU has malfunctioned TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 28 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD HEADING SELECT MODE, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 29 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION LATERAL MODES FMS LNAV MODE On aircraft with the Flight Management System(FMS), the LNAV mode is used to track a lateral flight path calculated by the FMS. Before the NAV pushbutton switch on the FGCP is pushed for the LNAV mode, these selections must be made: • • The navigation source selector on the FGCP is set to FMS to make a navigation source selection The Multi-functional Control Display Unit (MCDU) is used to activate a lateral flight The FMS continuously supplies a roll steering command to the AFCS. The LNAV mode can be engaged if the FMS roll steering commands are valid. If it is not valid, the LNAV mode is inhibited. During the LNAV mode, the FD commands are limited to 30° roll attitude, and 4°/ second of roll rate. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 30 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD, FGCP FMS LNAV MODE CONTROLS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 31 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION LATERAL MODES FMS LNAV MODE CONTINUED There are no LNAV arm mode or capture sub-modes. The FMA shows the LNAV active message in green letters. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 32 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD FMS LNAV ACTIVE, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 33 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION LATERAL MODES ILS APPROACH MODE The ILS Approach mode is a combined lateral and vertical mode used for precision Cat I and Cat II ILS approaches. The ILS approach mode captures and tracks ILS localizer and glideslope beams. The ILS approach mode has these sub-modes: • • • • • • Localizer Arm Localizer Capture Localizer Track Glideslope Arm Glideslope Capture Glideslope Track The heading select mode is used to intercept the localizer beam. The change to a different sub-mode is done automatically by the FD. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 34 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD ILS APPROACH LOCALIZER ARM, CAPTURE, AND TRACK TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 35 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION LATERAL MODES ILS APPROACH MODE CONTINUED After the lateral mode has changed to the localizer capture or localizer track mode and the aircraft has intercepted the desired ILS glideslope beam, the glideslope arm mode changes to active. The FD automatically starts to track the glideslope beam when the aircraft has turned on to it. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 36 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD ILS APPROACH GLIDESLOPE ARM, CAPTURE, AND TRACK TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 37 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION LATERAL MODES BACK-COURSE LOCALIZER MODE The Back-course localizer mode is used to automatically intercept, capture and track the back-course localizer beam. It has these sub-modes: • • • Back-course localizer arm Back-course localizer capture Back-course localizer track The heading select mode is used to intercept the back-course localizer beam. The change to a different sub-mode is done automatically by the FD. The mode changes to the back-course localizer active mode from back-course localizer arm when the aircraft intercepts the desired localizer beam. The heading select mode is cancelled at the same time. The FD automatically starts to track the localizer beam when the aircraft has turned on to it. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 38 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD BACKCOURSE LOCALIZER ARM, CAPTURE, AND TRACK TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 39 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM • AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION • • desired runway One heading selector or the other on the FGCP is set to the intercept heading target The APPR pushbutton switch on the FGCP is pushed to arm the mode The DH knobs on the Index Control Panels ICP1 and ICP2 are set to the Decision Height (DH) DUAL FD MODE The flight director system incorporates the following combined lateral and vertical modes: • • • Instrument Landing System (ILS) Approach Mode Microwave Landing System (MLS) Approach Mode Go Around (GA). The dual FD mode is a sub-mode of the ILS Approach mode. It shows that the AFCS is in a Category II ILS approach configuration. In the dual FD sub-mode, the two FGMs independently show FD commands on their related PFDs. FGM1 supplies FD commands to PFD1, and FGM2 supplies FD commands to PFD2. FGM1 uses localizer and glideslope deviations from the VHF NAV1, air data from ADC1, attitude and vertical speed data from AHRS1, and left course data from the FGCP. FGM2 uses localizer and glideslope deviations from the right VHF NAV2, air data from ADC2, attitude and vertical speed data from AHRS2, and right course data from the FGCP. To arm ILS approach mode for the dual FD sub-mode, these selections must be made: • • • • • • The EFIS ADC Source Selection switch is set to the NORM position The EFIS ATT/HDG Source Selection switch is set to the NORM position The left navigation source selector on the FGCP is set to ILS1 to make a navigation source selection The right navigation source selector on the FGCP is set to ILS2 to make a navigation source selection VHF NAV1 and VHF NAV2 are tuned to the same localizer frequency The left and right course selectors on the FGCP are set to the course of the TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 40 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD DUAL FD PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 41 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM On the FGCP, the arrow that relates to the source still valid stays on. AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) If a mismatch condition occurs between the two ILS sources in the dual FD sub-mode, the two FGMs cancel the Dual FD sub-mode. The master FGM selects the ILS source that was selected before the dual FD sub-mode was started and it keeps the APPR mode engaged. On the FGCP, the arrow relates to the selected navigation source stays on. DETAILED DESCRIPTION DUAL FD MODE CONTINUED A CAT2 FAIL message is shown when the dual FD sub-mode is cancelled. The dual sub-mode is cancelled by any of these conditions: • • • • • • • • • • • • • One or two FGMs malfunction One or two ADUs malfunction One or two AHRS malfunction The EFIS ADC Source Selection switch is set to the both on 1 or 2 position The EFIS ATT/HDG Source Selection switch is set to the both on 1 or 2 position The left navigation source selector on the FGCP is not set to ILS1 to make a navigation source selection The right navigation source selector on the FGCP is not set to ILS2 to make a navigation source selection VHF NAV1 and VHF NAV2 are tuned to different localizer frequencies ILS data malfunction for 5 seconds or more or a mismatch condition between ILS data The localizer track and glideslope track mode are cancelled The radio altitude data malfunction The FGM1 and FGM2 flight director commands do not agree The TCS mode is active The CAT2 FAIL message is also shown when one DH is set less than 200 ft. (61 m) or malfunctions. When the Dual FD sub-mode is active, a DUAL FD message is shown in green letters on each PFD, and the arrows located on each side of the HSI SEL pushbutton switch on the FGCP come on. When the dual FD sub-mode is cancelled, the DUAL FD message goes out of view. If one ILS, ADC, or AHRS source malfunctions in the dual FD sub-mode, the two FGMs cancel the dual FD sub-mode. The master FGM selects the remaining valid source and keeps the APPR mode engaged. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 42 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD CAT2 FAIL PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 43 of 145 BOMBARDIER DHC 8-400 (PWC PW150) INTENTIONALLY LEFT BLANK TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 44 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION • vertical speed, indicated airspeed, or go around Another active vertical mode malfunctions The STBY pushbutton switch on the FGCP is pushed to cancel the mode The HSI SEL pushbutton switch on the FGCP is pushed to use the other ADU and AHRS sources An ADC or AHRS source reversion is set while the AP is engaged The pitch hold mode is cancelled when one of these conditions is correct: VERTICAL MODES • The flight director system incorporates the following vertical modes: • • • • • • • • • • Pitch hold (Vertical Basic) Altitude select Altitude hold Indicated airspeed Vertical speed FMS VNAV • Another vertical mode selection is made manual selection or automatic capture of another vertical mode The AP is disengaged while operating in the lateral basic mode. The FD also disengages A STBY or HSI SEL selection if the AP is not engaged The pitch hold mode is cancelled and its operation is inhibited by any of these conditions: • PITCH HOLD (VERTICAL BASIC) MODE The Pitch Hold mode gives FD commands to hold a pitch attitude target. The pitch attitude target is initially set to the aircraft pitch attitude that exists when the Pitch Hold mode is started. The pitch attitude target is then changed by a manual rotation of the pitch thumbwheel knob located on the FGCP. • The CAS or TAS data from the selected ADC has malfunctioned. This condition causes the FD mode to cancel The attitude data from the selected AHRS has malfunctioned. This condition causes the FD mode to cancel The pitch attitude target can also be changed when the Tactile Control Steering (TCS) function is used. The pitch attitude target is set to the aircraft pitch attitude that exists when the TCS pushbutton switch is released. In the Pitch Hold mode, the FD target pitch attitude is limited to ±20°. The FD commands are further limited to a maximum aircraft normal acceleration of ±0.2 g. The pitch hold sub-mode gives FD commands to hold the pitch attitude after a mode selection or after the Tactile Control Steering (TCS) switch is released when one of these conditions is correct: • • The AP or a lateral FD mode selection is made with no vertical mode selection The Pitch thumbwheel knob is turned and the active vertical mode is not TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 45 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD ROLL HOLD MODE, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 46 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION VERTICAL MODES ALTITUDE SELECT MODE The altitude select mode gives FD commands to get and maintain a selected altitude target. The altitude select mode has these sub-modes: • • Altitude Select Arm Altitude Capture A different FD vertical mode is used to manoeuvre the aircraft towards the selected altitude target. The Indicated Airspeed (IAS) mode in usually used when climbing to the altitude target and the Vertical Speed (VS) is used when descending to the selected altitude. The mode changes to the altitude capture mode from IAS or VS when the aircraft is near the selected altitude target. When the selected altitude target is captured, the FD automatically changes to the altitude hold (ALT) mode. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 47 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD ALTITUDE SELECT ARM, CAPTURE, AND TRACK TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 48 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION VERTICAL MODES ALTITUDE SELECT MODE CONTINUED The ALT knob on the FGCP is turned to make an altitude target selection between 0 and 27,000 feet (0 and 8320 meters) before the ALT SEL pushbutton switch on the FGCP is pushed to arm the altitude select mode. Then, the IAS or VS pushbutton switch is pushed to make the indicated airspeed or vertical speed mode active. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 49 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD, FGCP ALTITUDE SELECT MODE CONTROLS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 50 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION VERTICAL MODES ALTITUDE SELECT MODE CONTINUED The altitude select mode is armed and the indicated airspeed or vertical speed mode is active. The FMA shows the ALT SEL arm message in white letters. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 51 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD ALTITUDE SELECT MODE ARMED, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 52 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION VERTICAL MODES INDICATED AIRSPEED MODE The Indicated Air Speed (AS) mode, commands the FD to hold an IAS target. The IAS pushbutton switch on the FGCP is pushed to start the indicated airspeed mode. The IAS target is initially set to the aircraft indicated airspeed that exists when the IAS mode is started. The IAS target can then be changed by a manual selection of the pitch thumbwheel located on the FGCP. The Tactile Control Steering (TCS) function can also change the IAS target. The IAS target is set to the aircraft indicated airspeed that exists when the TCS pushbutton switch is released. The FD commands are limited to ±20° of pitch attitude, and ±0.1 g. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 53 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD, FGCP INDICATED AIRSPEED MODE CONTROLS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 54 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM • AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) • • DETAILED DESCRIPTION The HSI SEL pushbutton switch on the FGCP is pushed to use the other ADU and AHRS sources A Go Around (GA) pushbutton switch is pushed to start the GA mode An ADC or AHRS source reversion is set The indicated airspeed mode is cancelled and its operation is inhibited by any of these conditions: VERTICAL MODES • • INDICATED AIRSPEED MODE CONTINUED When the indicated airspeed mode is made active, its indication is shown in reverse video, black letters on a green background. After 5 seconds, the indication changes back to green letters on a black background. • • The Vmo data from the selected ADC has malfunctioned The CAS or TAS data from the selected ADC has malfunctioned. This condition causes the FD mode cancel The attitude data from the selected AHRS has malfunctioned. This condition causes the FD mode to cancel The FGCP malfunctions When the AFCS is set to the IAS mode, an analogue cyan IAS target indication on the IAS indication comes into view to show the same value as the Flight Mode Annunciator (FMA). The range of the IAS target is between 95 and 290 kts (176 and 538 km/h). If the airspeed is less than 95 or more than 290 kts, the IAS mode is inhibited. The maximum speed target is decreased automatically with a decrease in Vmo by the FD to avoid an overspeed condition. If the target value is more than the shown IAS scale, one half of the target indication is shown at the edge of the IAS indication. When the IAS indication shows a malfunction indication, the target indication goes out of view. The indicated airspeed mode is cancelled by any of these conditions: • • • • The IAS pushbutton switch on the FGCP is pushed again to cancel the mode Transition to the VNAV, glideslope capture, or elevation capture mode Another vertical mode pushbutton switch selection is made The STBY pushbutton switch on the FGCP is pushed to cancel the mode TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 55 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD INDICATED AIRSPEED MODE ACTIVE, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 56 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION VERTICAL MODES VERTICAL SPEED MODE The Vertical Speed mode commands the FD to hold a vertical speed target. The VS pushbutton switch on the FGCP is pushed to start the vertical speed mode. The VS target is initially set to the aircraft vertical speed that exists when the VS mode is started. The VS target can then be changed by a manual selection of the pitch thumbwheel located on the FGCP. The Tactile Control Steering (TCS) function can also change the VS target. The VS target is set to the aircraft vertical speed that exists when the TCS pushbutton switch is released. The range of the VS target is between -5000 ft./min and +5000 ft./min (-1524 m/min and +1524 m/min). If the vertical speed is less than -6000 ft./min (-1829m/min) or more than +6000 ft./min (+1829m/min), the VS mode is inhibited. The FD commands are limited to ±20° of pitch attitude, and ±0.1 g. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 57 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD, FGCP VERTICAL SPEED MODE CONTROLS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 58 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM The vertical speed mode is cancelled and its operation is inhibited by any of these conditions: AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION • • • VERTICAL MODES • The vertical speed data from the selected AHRS has malfunctioned The CAS or TAS data from the selected ADC has malfunctioned. This condition causes the FD mode cancel The attitude data from the selected AHRS has malfunctioned. This condition causes the FD mode to cancel The FGCP malfunctions VERTICAL SPEED MODE CONTINUED When the vertical speed mode is made active, its indication is shown in reverse video, black letters on a green background. After 5 seconds, the indication changes back to green letters on a black background. An analogue cyan VS target indication on the IVSI scale comes into view to show the same value as the Flight Mode Annunciator (FMA). The range of the VS target is between -5000 and +5000 ft./min (–1524 and +1524 m/ min). If the target value is more than the shown IVSI scale, one half of the target indication is shown at the edge of the IVSI indication. When the IVSI shows a malfunction indication, the target indication goes out of view. The vertical speed mode is cancelled by any of these conditions: • • • • • • • The VS pushbutton switch on the FGCP is pushed again to cancel the mode Transition to the VNAV, glideslope capture, or elevation capture mode Another vertical mode pushbutton switch selection is made The STBY pushbutton switch on the FGCP is pushed to cancel the mode The HSI SEL pushbutton switch on the FGCP is pushed to use the other ADU and AHRS sources A Go Around (GA) pushbutton switch is pushed to start the GA mode An ADC or AHRS source reversion is set TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 59 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD VERTICAL SPEED MODE ACTIVE, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 60 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM This engages the LNAV mode and arms the VNAV mode. The active vertical mode does not change when the VNAV pushbutton switch is pushed. AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION The FMS continuously sends a pitch steering command to the AFCS. VERTICAL MODES The FD automatically starts the VNAV mode from VNAV arm mode when the pitch steering command is valid. The VNAV mode commands the FD to track a pitch steering command from the FMS, which is equivalent to a pitch attitude command. VERTICAL NAVIGATION The FD commands are limited to ±20° of pitch attitude, and a maximum aircraft normal acceleration of ±0.2 g. On aircraft with a Flight Management System, the vertical navigation mode commands the FD to get and hold a vertical flight path. It has these sub-modes: • • VNAV armed VNAV active The change to a different sub-mode is done automatically by the FD. The VNAV mode is only active when the LNAV mode is also active. Before the VNAV pushbutton switch on the FGCP is pushed to arm the vertical navigation mode, these selections must be made: • • • The navigation source selector on the FGCP is set to FMS1 or FMS2 to make a navigation source selection A lateral and vertical flight plan is activated on the FMS Multi-function Control Display Unit (MCDU) The NAV pushbutton switch is pushed to start the LNAV mode The VNAV mode is armed and the LNAV mode is active. The mode changes to the VNAV active mode from VNAV arm when the aircraft intercepts the course. The heading select mode is cancelled at the same time. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 61 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD, FGCP FMS VERTICAL NAVIGATION MODE CONTROLS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 62 of 145 BOMBARDIER DHC 8-400 (PWC PW150) • • AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) The vertical navigation mode is cancelled by any of these conditions: DETAILED DESCRIPTION • VERTICAL MODES • • • • • • • VERTICAL NAVIGATION CONTINUED When the vertical navigation mode is made active, its indication is shown in reverse video, black letters on a green background. After 5 seconds, the indication changes back to green letters on a black background. During the VNAV FLC sub-mode, a magenta analogue IAS target indication an arrow with a horizontal bar on the IAS indication comes into view to show the same value as the FMS Multi-Functional Control Display Unit (MCDU). • • • When the FMS MCDU malfunctions or the IAS indication shows a malfunction indication, the target indication goes out of view. • • • • • • • • • The NAV or VNAV pushbutton switch on the FGCP is pushed again to cancel the mode The pitch thumbwheel knob is turned Another lateral mode pushbutton switch selection other than NAV is made Activating a lateral mode The related navigation source selector is set to another navigation source A Go Around (GA) pushbutton switch is pushed to start the GA mode The STBY pushbutton switch on the FGCP is pushed to cancel the mode The HSI SEL pushbutton switch on the FGCP is pushed to use the other ADU and AHRS sources An ADC or AHRS source reversion is set The vertical speed mode is cancelled and its operation is inhibited by any of these conditions: If the target value is more than the shown IAS scale, one half of the target indication is shown at the edge of the IAS indication. • The VNAV arm mode is disarmed by any of these conditions: An ADC or AHRS source reversion is set Change to vertical navigation active mode The FMS has malfunctioned The CAS or TAS data from the selected ADC has malfunctioned. This condition causes the FD mode cancel The attitude data from the selected AHRS has malfunctioned. This condition causes the FD mode to cancel The FGCP malfunctions The NAV or VNAV pushbutton switch on the FGCP is pushed again to cancel the mode Another lateral mode pushbutton switch selection other than LNAV is made Activating a lateral mode The related navigation source selector is set to another navigation source A Go Around (GA) pushbutton switch is pushed to start the GA mode An ADC or AHRS source reversion is set The STBY pushbutton switch on the FGCP is pushed to cancel the mode The HSI SEL pushbutton switch on the FGCP is pushed to use the other ADU and AHRS sources TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 63 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD FMS VERTICAL NAVIGATION MODE ACTIVE, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 64 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION VERTICAL MODES GO AROUND MODE The Go Around (GA) mode is usually used to change from an approach to a climb-out flight condition for a missed approach. One or the other Go Around (GA) pushbutton switches located on the two throttle levers is pushed to start the go around mode. A go around mode selection causes the autopilot to disengage and the FD vertical mode to change to the go around mode. All FD armed modes are also disarmed. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 65 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD, GA MODE CONTROLS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 66 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION VERTICAL MODES GO AROUND MODE CONTINUED The go around mode commands a fixed 10 degrees pitch up angle and the wings level lateral mode. The go around mode is cancelled by one of the conditions that follow: • • • • • • The AP pushbutton switch is pushed to engage the autopilot The pitch thumbwheel knob is turned (TBD) Another vertical mode pushbutton switch selection is made The STBY pushbutton switch on the FGCP is pushed to cancel the mode The HSI SEL pushbutton switch on the FGCP is pushed to use the other ADU and AHRS sources An ADC or AHRS source reversion is set A TCS pushbutton switch selection in the go around mode does not change the go around pitch target, and does not cancel the mode. When TCS pushbutton switch is released, the FD lateral mode will change to the roll hold sub-mode of the Lateral Basic mode if the aircraft bank angle is more than six degrees. The vertical speed mode is cancelled and its operation is inhibited by one of the conditions that follow: • • The CAS or TAS data from the selected ADC has malfunctioned. This condition causes the FD mode cancel The attitude data from the selected AHRS has malfunctioned. This condition causes the FD mode to cancel TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 67 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - FD GA MODE ACTIVE, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 68 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION AUTOPILOT The Autopilot (AP) moves the flight control surfaces for automatic control of the aircraft flight path. The AP pushbutton switch on the FGCP is pushed to engage the autopilot and Yaw Damper (YD) if the YD is not engaged. A malfunction condition that prevents the yaw damper from engaging also prevents the autopilot from engaging. A malfunction condition that causes the yaw damper to disengage also cause the autopilot to disengage. The AP pushbutton switch on the FGCP will engage the autopilot when all of the conditions are as follows: • • • • • • • • • • • • • • • AHRS1 and AHRS2 are valid AHRS1 and AHRS2 data do not disagree ADC 1 and ADC 2 are valid ADC 1 and ADC 2 data do not disagree The aircraft is airborne The aircraft attitude is within the AP engagement limits The manual pitch trim AP disengage discrete signal is not set. No AP disengage switch selection TCS mode has not malfunctioned TCS mode is not active The Stall Warning AP Disconnect discrete signals from SPM1 and SPM2 are not set No GA switch selection AP disengagement warnings are not active Yaw Damper function is available Internal AFCS monitoring is valid TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 69 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - AUTOPILOT MODE CONTROLS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 70 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) Two arrow shaped indication lights located adjacent to the AP pushbutton switch on the FGCP comes on to show the autopilot engage selection. An AP message in green letters is also shown on the PFD Flight Mode Annunciators (FMA). An AP message in white letters is also shown in the FMA when the autopilot mode is active. DETAILED DESCRIPTION AUTOPILOT CONTINUED The autopilot is disengaged by these selections: • • • • • AP pushbutton switch on the FGCP YD pushbutton switch on the FGCP AP disengage pushbutton switch on the hand-wheel assemblies Manual pitch trim switch on the hand-wheel assemblies Go Around pushbutton switch on the power levers The autopilot is also disengaged by any of the conditions that follow: • • • • • • • • • • • • • • • • • AHRS1 or AHRS2 has malfunctioned AHRS1 and AHRS2 data disagree ADC1 or ADC2 has malfunctioned ADC1 and ADC2 data disagree Aircraft is not airborne AP or YD pushbutton switch on the FGCP is pushed for manual disengagement Manual pitch trim-selection when the TCS mode is not active manual disengagement The control column or hand-wheel is used to manually override AP The AP disengage switch on the hand-wheel is pushed for a manual disengagement The TCS malfunctions A stall warning condition is sensed A GA pushbutton switch on a power lever is pushed manual disengagement An AP actuator failure is sensed An automatic Yaw Damper disengagement is sensed Internal AFCS monitoring has malfunctioned A long power interruption occurs The aircraft attitude is more than the AP limits TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 71 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - AUTOPILOT ACTIVE, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 72 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION AUTOPILOT CONTINUED The autopilot also has these PFD engagement indications: • • AP INHIBIT message, PFD AP FAIL message, PFD AP INHIBIT Message: If an input to the AFCS prevents AP engagement, an AP INHIBIT message in white letters is shown in on the PFD FMA. These conditions cause the AP INHIBIT message to come into view: • • • • • • • • • AHRS malfunction ADU malfunction The aircraft is not airborne The aircraft attitude is more than the AP engagement limits A GA pushbutton switch selection is made TCS is active The manual pitch trim selection is made A stall warning condition is sensed The AP disengage warnings are active TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 73 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - AUTOPILOT INHIBIT, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 74 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION AP FAIL MESSAGE If an internal malfunction prevents AP engagement, an AP FAIL message in yellow letters is shown on the PFD FMA. If the malfunction also prevents engagement of the yaw damper, an AP/YD FAIL message is shown in yellow letters. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 75 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - AUTOPILOT FAIL, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 76 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION AP FAIL MESSAGE CONTINUED The autopilot has a disengagement visual warning. Two related red AP disengage warning lights located on the glareshield come on and a continuous 4000 Hz aural tone sounds to show an automatic autopilot disengage condition. The AP disengage warning lights flash and the tone sounds until the AP pushbutton switch on the FGCP is pushed or an AP disengage pushbutton switch on a handwheel assembly is pushed. The AP disengage warning lights then stay on steady for five seconds before they go out. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 77 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - AUTOPILOT DISENGAGE, GLARESHIELD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 78 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION AP FAIL MESSAGE CONTINUED A yellow AP DISENGAGED or AP/YD DISENGAGED message also comes into view on the PFDs to show an automatic autopilot disengage condition. The AP DISENGAGED or AP/YD DISENGAGED message flashes until the AP pushbutton switch on the FGCP is pushed or an AP disengage pushbutton switch on the handwheel assemblies is pushed. The AP messages then stay on steady for five seconds before they go out. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 79 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - AUTOPILOT DISENGAGE CONTROLS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 80 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION AP FAIL MESSAGE CONTINUED When the autopilot is manually disengaged, an AP DISENGAGED or AP/YD DISENGAGED message on the PFD comes into view steady for 5 seconds and a 1.5 second aural tone sounds. NOTE: A manual AP disengage condition does not cause the AP disengage warning lights to come on. The AP cannot be engaged while the AP disengaged indications are active. When the AP is engaged, each FGM monitors the AP pitch servo torque. A pitch mistrim condition could cause a significant control column force and pitch transient when the AP disengages. If the AP pitch servo torque is more than the preset threshold, the FGMs cause the PFDs to show a yellow MISTRIM [TRIM NOSE UP] or MISTRIM [TRIM NOSE DN] message. When the AP is engaged, each FGM monitors the AP roll servo torque. A roll mistrim condition could cause a significant handwheel force and roll transient when the AP disengages. If the AP roll servo torque is more than the preset threshold, the FGMs cause the PFDs to show a yellow MISTRIM L WING DN or MISTRIM R WING DN message. The roll mistrim message is out of view when the AP pitch servo torque is less than the threshold. The pitch or roll mistrim message does not come into view when the AP is disengaged, or when TCS is active. The autopilot does not disengage automatically when a roll mistrim condition occurs or when a lateral trim is input to the control system to correct the roll mistrim condition. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 81 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AFCS - AUTOPILOT DISENGAGED, PFD INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 22 - AUTOFLIGHT Issue 6 - January 2023 Page 82 of 145 BOMBARDIER DHC 8-400 (PWC PW150) AUTOFLIGHT SYSTEM AUTOMATIC FLIGHT GUIDANCE CONTROL SYSTEM (AFCS) DETAILED DESCRIPTION TACTILE CONTROL STEERING (TCS) The TCS mode momentarily overrides the AP, without cancelling the AP mode, to manually fly the aircraft to a new FD target. A Tactile Control Steering (TCS) switch located on the pilot’s and co-pilot’s handwheels is pushed and held for TCS operation. When the TCS mode is engaged, the pitch and roll AP actuators automatically de-clutch and their monitoring is inhibited. This allows manual control of the pitch and roll flight controls with normal control forces while the autopilot mode is engaged. When the TCS mode is active, a manual selecti