BOMBARDIER Primus 2000XP Скачать руководство пользователя страница 8 | Manualshive

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P I L O T T R A I N I N G G U I D E

AUTOMATIC FLIGHT CONTROL SYSTEM

2-6

For Training Purposes Only

Sept 04

AUTOPILOT ENGAGEMENT

Autopilot is engaged via the AP button on the guidance panel. When there are no
vertical or lateral mode active, the autopilot will engage in (PIT) and (ROL) FD
modes.

Autopilot control authority:

•

Roll rate is limited to ± 7.5°/sec.

•

Pitch rate
•

± 0.3 g’s in straight and level flight

•

maximum 0.7 g’s pitch up in a turn

The autopilot can engage throughout the range:

•

Pitch = ± 50°

•

Roll = ± 75°
•

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

Autopilot control limits:

•

Roll = ± 35° except in Approach (APP) mode. When in APP mode, the roll limits
are reduced linearly from ± 25°, above 200 feet radio altitude, to ± 5° at zero feet
radio altitude

•

Pitch = ± 20°. In APP mode, the nose-down pitch limit is reduced below 300 feet,
programmed by vertical rate and radio altitude

CRS 2

PUSH DCT

Honeywell

FD

AP

CPL

YD

AP

AP

CRS 2

PUSH DCT

Honeywell

FD

AP

CPL

YD

GX_02_004

AP1

AP2

When selected,

or

will flash for

approximately 5 seconds, then steady.

AP1

AP2

20

20

10

10

20

ROL

PIT

AP1

0.88

300

00

23500

220

200

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Содержание Primus 2000XP

Страница 1: ...ngagement 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...

Страница 2: ...P I L O T T R A I N I N G G U I D E AUTOMATIC FLIGHT CONTROL SYSTEM 2 ii For Training Purposes Only Sept 04 PAGE INTENTIONALLY LEFT BLANK...

Страница 3: ...ght Instrument System EFIS the Air Data Computers ADC the Inertial Reference System IRS the Flight Management System FMS the Fault Warning Computer FWC and the Data Acquisition Unit DAU DESCRIPTION Al...

Страница 4: ...ommand bar output for display If an autopilot or flight director mode is armed or active the annunciator on the appropriate button is illuminated SPD MAN FMS CRS 1 CRS 2 PUSH DCT PUSH DCT ALT HDG DN U...

Страница 5: ...APR VS BC PUSH CHG PUSH SYNC MAX THRUST IDLE REV MAX REV ENG RUN OFF OFF R L RUDDER CONTROL SURFACE POSITION CH 1 CH 2 TRIM SYSTEM IAC 1 IAC 2 FGC 2 DUAL ELEVATOR SERVO DUAL AILERON SERVO YAW DAMPER...

Страница 6: ...el provides control functions while the low priority channel operates in a back up mode The autopilot yaw damper actuators and pitch trim interface can only be driven by the priority channel In the ev...

Страница 7: ...ion is selected via the source identifier received from selected PFD symbol generator The data received includes IRS Roll angle Normal acceleration Pitch angle Ground speed Roll rate True track angle...

Страница 8: ...throughout the range Pitch 50 Roll 75 Once engaged the autopilot will reduce the pitch and roll angles below control limits Autopilot control limits Roll 35 except in Approach APP mode When in APP mod...

Страница 9: ...isengaged and the flight director is resynchronized Releasing the TCS button reengages the servo clutches and autopilot is engaged if within normal pitch and roll limits Where applicable the flight di...

Страница 10: ...autopilot the yaw damper operates in an active standby configuration When engaged the active yaw damper will center both linear actuators The YD will not automatically engage once the airplane is airb...

Страница 11: ...30000 GX_02_008 AP1 TCS TCS DN UP P I T C H VNAV VS Pitch Wheel AP ENGAGE STATUS TOUCH CONTROL STEERING TCS STATUS VERTICAL SPEED REFERENCE VS Target Readout VS Pointer 1000 VS 1000 0 1 2 3 1 VS Targ...

Страница 12: ...vertical modes on the right side above the attitude sphere Low bank mode is annunciated via green eyebrow on top of the attitude sphere 300 LIM LNAV VPTH AP1 SPD VOR VPTH 23500 ATT2 ADC1 20 20 20 0 8...

Страница 13: ...th PFDs when Go Around GA Takeoff TO or Windshear Guidance WS modes are active 20 20 10 10 10 10 20 20 20 FD Switch Used to remove flight director command bars from the non coupled PFD GX_02_010 20 20...

Страница 14: ...heading Bank BANK Switch Used to manually select bank angle limit in HDG or VOR modes Heading HDG Button Push Synchronize PUSH SYNC Button Used to move the heading bug on PFD When pushed causes headi...

Страница 15: ...button removes both FD offside button removes offside FD AP ON AP OFF Autopilot AP Switch Used to engage and disengage autopilot When autopilot engaged the yaw damper is engaged simul taneously Diseng...

Страница 16: ...NK High Low Bank HDG or VOR mode only Eyebrow on attitude sphere low bank only VERTICAL MODES SWITCH GUIDANCE PANEL MODE ANNUNCIATION VS Vertical Speed Hold VS None Automatic Altitude Capture ASEL ALT...

Страница 17: ...6 commands are then generated to hold the bank angle The roll mode reference is reset to the current heading or current roll angle upon AP engagement Roll mode is annunciated in the lateral capture fi...

Страница 18: ...ding through an altitude of 35 050 feet the FGC automatically transitions to the low bank limit of 17 If the roll angle is greater than 6 an automatic bank limit transition will not occur until the ro...

Страница 19: ...gh frequency Omnidirectional Range VOR Localizer LOC FMS Lateral Navigation LNAV If in ROL mode when NAV is selected heading select mode is automatically activated A capture of any armed lateral navig...

Страница 20: ...commands are 14 and roll rate commands 4 sec If selected VOR is retuned to another VOR frequency while in VOR capture track or overstation VOR mode cancels and rearms automatically When the airplane...

Страница 21: ...TO FROM transition The period of time elapsed is calculated using true airspeed and altitude The higher the altitude the longer it takes to get through cone of confusion The higher the airspeed the fa...

Страница 22: ...VNAV 0 856M VOR1 CRS 090 HDG 030 SRP VOR 1 ATT2 ADC1 20 20 10 10 10 10 20 20 20 N 3 3 3 0 W 2 4 2 1 S 1 5 12 E 6 3 21 1NM VOR MODE CAPTURE VOR MODE INTERCEPT SELECTED COURSE SELECTED HEADING Typical C...

Страница 23: ...formation if the DME is valid and co located with the localizer transmitter If DME information is not available or not co located the distance to localizer is based on radio altitude true airspeed gli...

Страница 24: ...HDG 040 SRP ATT2 ADC1 20 20 10 10 10 10 20 20 20 N 3 3 30 W 2 4 21 S 1 5 12 E 6 3 10 0NM LIM LOC VS AP1 SPD VOR VNAV 0 856M LOC1 CRS 090 HDG 040 SRP ATT2 ADC1 20 20 10 10 10 10 20 20 20 N 3 3 3 0 W 2...

Страница 25: ...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 The course arrow must be set to the front course runway...

Страница 26: ...1 S 1 5 1 2 E 6 3 10 LIM HDG ALT AP1 SPD BC VNAV 0 856M LOC1 CRS 090 HDG 330 ATT2 ADC1 20 20 10 10 10 10 20 20 20 N 33 30 W 24 2 1 S 15 1 2 E 6 3 GX_02_020 BACK COURSE MODE TRACK BACK COURSE MODE CAPT...

Страница 27: ...navigation to a LOC or VOR approach via the APR or BC button The selected NAV source must be FMS NAV radio must be tuned to the approach frequency and preview mode selected to allow a NAV transfer to...

Страница 28: ...I D E AUTOMATIC FLIGHT CONTROL SYSTEM 2 26 For Training Purposes Only Sept 04 Previewed Approach DTK 360 HDG 330 SRP N 33 3 0 W 2 4 2 1 S 1 5 1 2 E 6 3 23 4NM FMS1 LOC1 Preview Navigation Source Prev...

Страница 29: ...control panel located on the glareshield MINIMUMS BARO Hpa RAD IN BARO SET NAV SRC BRG V L BRG FMS HSI Honeywell PUSH STD MINIMUMS BARO Hpa RAD IN BARO SET NAV SRC BRG V L BRG FMS HSI Honeywell PUSH...

Страница 30: ...ggle the NAV source in the following sequence on side VOR LOC X side VOR LOC on side VOR LOC CRS 360 HDG 030 VOR 1 N 3 3 30 W 2 4 21 S 1 5 12 E 6 3 VOR1 CRS 360 HDG 030 VOR VOR 2 N 3 3 30 W 2 4 21 S 1...

Страница 31: ...cancel V L as primary NAV source and will set on side FMS as primary NAV source Pushing FMS button will toggle the NAV source in the following sequence on side FMS X side FMS LTRK if installed on side...

Страница 32: ...ude is above the airplane s present altitude and there is adequate thrust FLC mode will climb at the speed reference until preselected altitude is captured If thrust is inadequate FLC mode will hold p...

Страница 33: ...airspeed tape of the selected PFD The MAN speed bug is cyan and can be in either kts or MACH FMS speed selection is programmed in the active flight plan in the FMS A Mach speed bug will appear on the...

Страница 34: ...e with altitude configuration and or airspeed changes while climbing descending or in level flight Vertical Speed VS Select Mode VS mode is used to maintain a pilot selected vertical speed reference F...

Страница 35: ...within 2000 feet of current altitude and the altitude rate required to fly a constant 0 05g capture curve is less than the current airplane inertial climb rate ASEL will capture when descending towar...

Страница 36: ...Vertical Navigation VNAV Modes VNAV mode contains 4 vertical submodes that can be flown using speed and altitude targets that are programmed in the active flight plan of the FMS A double C chord aura...

Страница 37: ...pe signals which enables the pilot to fly a fully coupled ILS approach APR modes are based on vertical path deviation and valid glideslope on the selected PFD Review the Localizer section for further...

Страница 38: ...lope arm or capture and dual couple status A valid CAT 2 status is indicated on the PFD A CAT 2 window also appears to display deviation from the beam The fully coupled dual arrow ILS approach becomes...

Страница 39: ...TURE APPROACH MODE INTERCEPT INBOUND COURSE LOCALIZER TX SELECTED HEADING Typical Capture Point Between 1 and 2 Dot RUNWAY 090 045 APPROACH MODE TRACK OUTER MARKER 4 0 7 0 MILES MIDDLE MARKER 3500 FEE...

Страница 40: ...les will provide full takeoff thrust until TO mode is cleared TO mode can be cleared by selecting the AP on PIT or by selecting another vertical mode GO AROUND GA MODE GA mode provides pitch and later...

Страница 41: ...e can be activated by either depressing the throttle mounted TOGA button or advancing the thrust levers towards takeoff when a windshear warning has been displayed on EFIS WSHR mode will provide verti...

Страница 42: ...matically disconnect the autopilot WSHR mode cannot be canceled when a Windshear Warning is present When the WSHR mode is activated the attitude at which the aircraft will reach stall speed is indicat...

Страница 43: ...rget is not manually selectable through the speed knob on the guidance panel while EDM is active Changing the FMS MAN switch position of the speed knob on the guidance panel has no effect while EDM is...

Страница 44: ...hrottles are manually disengaged and reengaged while in EDM The autothrottles are not automatically reengaged if disengaged Auto engagement occurs only upon initiation of the emergency descent mode Th...

Страница 45: ...LIGHT DIRECTOR EICAS MESSAGES Cont GX_02_045 AFCS 1 2 FAIL Indicates that AFCS one or both functions has failed The AFCS functions include yaw damper autopilot and flight director YD NOT CENTERED Indi...

Страница 46: ...CONT GX_02_046 CB AFCS SYSTEM 1 3 A T CTLR A T SERVOS AP 1 SERVOS AP 2 SERVOS GUID PANEL CH 1 GUID PANEL CH 2 AC 1 DC 1 DC1 DC 2 BATT DC ESS IN IN IN IN IN IN CCBP CB AFCS SYSTEM 2 3 IAC 1 IAC 2 IAC 3...

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