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Honeywell PRIMUS 1000 Pilot's Manual

Integrated avionics system for the citation encore
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  • Page 2: Revision

    PRIMUS 1000 INTEGRATED AVIONICS SYSTEM FOR THE CITATION ENCORE PILOT’S MANUAL, HONEYWELL PUB. NO. A28–1146–134 REVISION NO. 1 DATED JANUARY 2003 HIGHLIGHTS Pages that have been revised are outlined below. Remove and insert the affected pages listed. The revision number has been added to the bottom of the revised pages and revision bars have been used to indicate the revised or added text.
  • Page 3 Page No. Description of Change 6–5 Revised Figure 6–4. 6–6 Revised Figure 6–5. 6–8 Revised Figure 6–7. 6–9 Revised Figure 6–8. 6–10 Revised Figure 6–9. 6–16 Revised Figure 6–12. 6–18 Revised Figure 6–14. 6–20 Revised Figure 6–16. 6–22 Revised Figure 6–18. 6–48 Revised Figure 6–35.
  • Page 4 Honeywell Aerospace Electronic Systems CES–Phoenix P.O. Box 21111 Phoenix, Arizona 85036–1111 U.S.A. PRIMUS 1000 Integrated Avionics System for the Citation Encore Pilot’s Manual January 2003 Printed in U.S.A. Pub. No. A28–1146–134–01 April 2000...
  • Page 5 PROPRIETARY NOTICE This document and the information disclosed herein are proprietary data of Honeywell. Neither this document nor the information contained herein shall be used, reproduced, or disclosed to others without the written authorization of Honeywell, except to the extent required for installation or maintenance of recipient’s equipment.
  • Page 6 Upon receipt of a revision, insert the latest revised pages and dispose of superseded pages. Enter revision number and date, insertion date, and the incorporator’s initials on this Record of Revisions. The typed initial H is used when Honeywell is the incorporator of the revision. Revision Revision...
  • Page 7 PRIMUS 1000 Integrated Avionics System List of Effective Pages Original Apr 2000 Revision Jan 2003 Subheading and Page Revision Subheading and Page Revision Title Page 2–6 2–7 Record of Revisions 2–8 RR–1/RR–2 2–9 2–10 List of Effective Pages 2–11/2–12 LEP–1 LEP–2 Electronic Flight Instrument System (EFIS)
  • Page 8 PRIMUS 1000 Integrated Avionics System Subheading and Page Revision Subheading and Page Revision Electronic Flight Instrument System 3–80 (EFIS) (cont) 3–81 3–35 3–82 3–36 3–83 3–37 3–84 3–38 3–85 3–39 3–86 3–40 3–87 3–41 3–88 3–42 3–89 3–43 3–90 3–44 3–91 3–45 3–92...
  • Page 9 PRIMUS 1000 Integrated Avionics System Subheading and Page Revision Subheading and Page Revision System Limits (cont) 6–40 5–5 6–41 5–6 6–42 5–7 6–43 5–8 6–44 5–9/5–10 6–45 Modes of Operation 6–46 6–1 6–47 6–2 6–48 6–3 6–49 6–4 6–50 6–5 6–51 6–6 6–52...
  • Page 10 PRIMUS 1000 Integrated Avionics System Subheading and Page Revision Subheading and Page Revision Troubleshooting (cont) 7–31 7–32 7–33/7–34 7–35/7–36 7–37/7–38 Acronyms and Abbreviations 8–1 8–2 8–3 8–4 8–5 8–6 Appendix A A–1 A–2 A–3 A–4 A–5 A–6 A–7 A–8 A–9 A–10 A–11 A–12...
  • Page 11: Table Of Contents

    ......The PRIMUS 1000 Integrated Avionics System Honeywell Product Support ....Publication Ordering Information .
  • Page 12 PRIMUS 1000 Integrated Avionics System Table of Contents (cont) Section Page 3. ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) ( ....... CONT Enhanced Ground Proximity Warning System (EGPWS) (Optional)
  • Page 13 PRIMUS 1000 Integrated Avionics System Table of Contents (cont) Section Page 5. SYSTEM LIMITS ( CONT VOR Capture ....... . VOR Over Station Sensor (OSS) .
  • Page 14 PRIMUS 1000 Integrated Avionics System Table of Contents (cont) Section Page 7. TROUBLESHOOTING ( CONT Typical Problems ......7-15 Lateral Mode Problems .
  • Page 15 PRIMUS 1000 Integrated Avionics System Table of Contents (cont) List of Illustrations Figure Page 1–1 Cockpit Layout for the Encore ....2–1 System Block Diagram .
  • Page 16 PRIMUS 1000 Integrated Avionics System Table of Contents (cont) List of Illustrations (cont) Figure Page 3–36 Approach Capture Tracking at Minimums ..3-71 3–37 Comparison Monitor Annunciators ....3-72 3–38 Excessive Attitude Display .
  • Page 17 PRIMUS 1000 Integrated Avionics System Table of Contents (cont) List of Illustrations (cont) Figure Page 6–16 Localizer (NAV) Mode Tracking ....6-20 6–17 Localizer (NAV) Mode Tracking Display .
  • Page 18 PRIMUS 1000 Integrated Avionics System Table of Contents (cont) List of Illustrations (cont) Figure Page A–1 Weather Radar Controller ..... A–2 A–2 PFD Display Weather Radar Test Pattern .
  • Page 19 PRIMUS 1000 Integrated Avionics System Table of Contents (cont) List of Tables (cont) Table Page 3–20 Weather Warning Annunciators ....3-52 3–21 Weather Mode Annunciators ....3-53 3–22 V Bug Identification...
  • Page 20 PRIMUS 1000 Integrated Avionics System Table of Contents (cont) List of Tables (cont) Table Page 7–5 Common Event Codes ..... . . 7-11 7–6 EC 0221 Troubleshooting Procedure .
  • Page 21: Introduction

    PRIMUS 1000 Integrated Avionics System Introduction THE PRIMUS 1000 INTEGRATED AVIONICS SYSTEM This document describes the components, operating procedures, and typical flight applications for the PRIMUS 1000 Integrated Avionics System in the Cessna Citation Encore (Model 560, SN 0539 and above).
  • Page 22 PRIMUS 1000 Integrated Avionics System Model Unit Part No. DC–550 Display Controller (DC) 7016986–723 MC–800 Multifunction Display (MFD) 7007062–939 Controller RI–553 Remote Instrument Controller 7016954–907 WC–660 Weather Radar Controller 7008471–667 PC–400 Autopilot Controller 7003897–923 MS–560 Mode Selector 7018341–803 AV–850A Audio Control Unit 7511001–913 RM–850 Radio Management Unit...
  • Page 23 PRIMUS 1000 Integrated Avionics System Model Unit Part No. Remote Mounted IC–600 Integrated Avionics Computer 7017000–80171 (Pilot) (Symbol Generator (SG)/ Flight Director (FD)/ Autopilot (AP) IC–600 Integrated Avionics Computer 7017000–80172 (Pilot) (SG/FD/AP/TCAS) IC–600 Integrated Avionics Computer 7017000–81171 (Copilot) (SG/FD) IC–600 Integrated Avionics Computer 7017000–81172 (Copilot)
  • Page 24: Support Software Equipment

    PRIMUS 1000 Integrated Avionics System Model Unit Part No. AZ–850 Micro Air Data Computer 7014700–601 (MADC) with RVSM (Reduced Vertical Separation Minimums) RG–204 Rate Gyro 7007453–903 AG–222 Accelerometer 7000992 RNZ–850 Integrated Navigation (NAV) 7510100–931 Unit RNZ–850B 7510100–933 RCZ–833E Communications Unit with 7510700–866 Diversity Transponder, 8.33 kHz.
  • Page 25: Cockpit Layout For The Encore

    PRIMUS 1000 Integrated Avionics System Cockpit Layout for the Encore Figure 1–1 A28–1146–134 Introduction REV 1 Jan/03 1-5/(1-6 blank)
  • Page 26: Honeywell Product Support

    All articles are returned to Reconditioned Specifications limits when they are processed through a Honeywell repair facility. All articles are inspected by quality control personnel to verify proper workmanship and conformity to Type Design and to certify that the article meets all controlling documentation.
  • Page 27 PRIMUS 1000 Integrated Avionics System The Honeywell Support Centers listed below will assist with processing exchange/rental orders. 24–HOUR EXCHANGE/RENTAL SUPPORT CENTERS U.S.A. – DALLAS AUSTRALIA – TULLAMARINE 800–872–7739 61–3–9330–1411 972–402–4300 ENGLAND – BASINGSTOKE GERMANY – AOA GAUTING 44–1256–72–2200 0172–8207300 (in Germany) 49–172–8207300 (outside Germany)
  • Page 28 PRIMUS 1000 Integrated Avionics System CUSTOMER SUPPORT CENTERS – REST OF THE WORLD United Kingdom Support Center France Support Center Honeywell Avionics Systems Ltd Honeywell Aerospace Edison Road, Ringway North 1 Rue Marcel–Doret, B.P.14 BASINGSTOKE, HANTS, 31701 BLAGNAC CEDEX, RG21 6QD...
  • Page 29: Publication Ordering Information

    PRIMUS 1000 Integrated Avionics System PUBLICATION ORDERING INFORMATION Please contact Honeywell if: The revision services card is missing and you would like to register for revision services. You need to submit a change of address for revision services. You need additional copies of this manual.
  • Page 30: System Description

    PRIMUS 1000 Integrated Avionics System System Description GENERAL The PRIMUS 1000 Integrated Avionics System is a fail–passive autopilot/flight director and display system with horizontal and vertical flight guidance modes. These include all radio guidance modes, long range navigation system tracking modes, and air data vertical modes. Either flight director can be coupled to the autopilot.
  • Page 31 PRIMUS 1000 Integrated Avionics System Annunciators on the PFD indicate the selected flight mode. Pitch and roll steering commands, calculated by the IAC’s flight director in conjunction with the mode selector, are displayed as command bars that direct the pilot to reach and/or maintain the required flight path. The IAC is the focal point of information flow in this system.
  • Page 32 PRIMUS 1000 Integrated Avionics System The avionics system block diagram is shown in Figure 2–1. The systems comprising the PRIMUS 1000 Integrated Avionics System are described in Table 2–1 and in the paragraphs that follow. Availability System Standard IC–600 Integrated Avionics Computer (IAC) that includes: Electronic Flight Instrument System (EFIS) Flight Guidance System (FGS)
  • Page 33: Electronic Flight Instrument System (Efis)

    PRIMUS 1000 Integrated Avionics System ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) The EFIS includes the following units: Inside each IAC — Symbol generator — Sensor interfaces PFD and MFD display units PFD bezel controller MFD bezel controller Display controller Remote instrument controller MFD controller.
  • Page 34: Flight Guidance System (Fgs)

    PRIMUS 1000 Integrated Avionics System Essential display information from sensor systems, automatic flight control, and navigation are integrated into the pilot’s prime viewing area. Critical flight operation information is selected using the display controller and MFD controller. These controllers are also used to operate the checklist function.
  • Page 35 PRIMUS 1000 Integrated Avionics System The fail–passive IAC contains the flight director, yaw damper, and autopilot. The system is fail–passive, using comparator monitors on the pilot and copilot vertical gyros and servo command outputs. The directional gyro and air data computer inputs assist in monitoring. Servo command outputs from a computed servo model in all three axes are compared to actual commands with input from the air data computer.
  • Page 36: Air Data System (Ads)

    PRIMUS 1000 Integrated Avionics System AIR DATA SYSTEM (ADS) The ADS includes dual micro air data computers (MADCs). NOTE: The system is backed up by standby altimeters and airspeed indicators that are driven directly from the standby pitot–static system. The MADC is a microprocessor–based digital computer that performs digital computations and supplies digital readouts.
  • Page 37: Gyroscope System

    Honeywell Pub. No. A28–1146–111. The optional PRIMUS 880 Digital Weather Radar System is described more fully in Honeywell Pub. No. A28–1146–102. GYROSCOPE SYSTEM The vertical gyro sends pitch and roll information to the FGS, EFIS, and weather radar antenna. This information is used to control the aircraft and to compute FGS commands.
  • Page 38: Primusr

    PRIMUS 1000 Integrated Avionics System PRIMUS II INTEGRATED RADIO SYSTEM The integrated radio system is described fully in Honeywell Pub. No. A28–1146–50. The PRIMUS II Integrated Radio System accomplishes the following functions: Very high frequency (VHF) communication VHF omnidirectional range (VOR)
  • Page 39: Other Switches And Controls

    PRIMUS 1000 Integrated Avionics System OTHER SWITCHES AND CONTROLS AP (Autopilot) Disconnect Button – The AP disconnect button is on the control wheel. When pushed, it disconnects the autopilot. This switch also resets monitor–induced autopilot disconnects. If the autopilot disconnects because a monitor in the pitch, roll, or yaw axis senses an abnormal response condition (for example, a pilot’s feet on the rudder when the yaw damper tries to execute a yaw damper function),...
  • Page 40: System Block Diagram

    PRIMUS 1000 Integrated Avionics System FD1/FD2 28 V DC WC–660 FMS, GNS–X/ES WEATHER RADAR GPS/LORAN C CONTROLLER (NOTE) AG–222 ACCELEROMETER WU–660 VG–14A VG–14A WX RECEIVER/ VERTICAL VERTICAL TRANSMITTER/ GYRO GYRO ANTENNA (NOTE) NO. 1 RADIO NO. 2 ALTIMETER IC–600 (SG/FD/AP) IC–600 (SG/FD) (YD ONLY) RIGHT...
  • Page 41: Electronic Flight Instrument System

    PRIMUS 1000 Integrated Avionics System Electronic Flight Instrument System (EFIS) GENERAL The EFIS generates flight path, flight instrument, and navigation information. It consists of a PFD for each pilot and an MFD on the central panel, with various cockpit–mounted controllers to select functions and display modes.
  • Page 42 PRIMUS 1000 Integrated Avionics System RADIO MANAGEMENT RADIO MANAGEMENT AUDIO CONTROL PFD (PILOT) UNIT (PILOT) MODE SELECTOR PFD (COPILOT) UNIT (COPILOT) (COPLIOT) AUDIO CONTROL (PILOT) DISPLAY CONTROLLER WEATHER RADAR DISPLAY CONTROLLER (PILOT) CONTROLLER (COPILOT) MFD CONTROLLER TUNE PREV NEXT PROG CONTROL DISPLAY PERF RADIO...
  • Page 43: Controllers

    PRIMUS 1000 Integrated Avionics System CONTROLLERS Primary Flight Display (PFD) Bezel Controller The PFD bezel controller, shown in Figure 3–2, is front–mounted on the PFD. The functions are listed below. PFD Bezel Controller Figure 3–2 Inclinometer – The ball in the glass track indicates a slip or skid. STD (Standard) Button –...
  • Page 44: Multifunction Display (Mfd) Bezel Controller

    PRIMUS 1000 Integrated Avionics System Multifunction Display (MFD) Bezel Controller The five menu buttons and the two knobs on the MFD bezel controller, shown in Figure 3–3, set vertical navigation (VNAV) data parameters and reference speeds (V SPEEDS DATA SET KNOB MENU BUTTONS ALTITUDE PRESELECT...
  • Page 45 PRIMUS 1000 Integrated Avionics System CONTROLLER CONVENTIONS When a menu item is boxed, the parameter in the box is displayed on the PFD or MFD. Selecting a boxed item deselects the item. Parameter Selected for Display – A selected parameter is displayed only when the item is boxed on the menu.
  • Page 46 PRIMUS 1000 Integrated Avionics System MAIN MENU The main menu, shown in Figure 3–5, is the MFD power–up menu. Pilots can select either the VNAV or VSPEED submenu, control the display of EGPWS terrain (TERR), and/or select FMS1 or FMS2 for display.
  • Page 47 PRIMUS 1000 Integrated Avionics System FMS VNAV SUBMENU Selecting FMS VNAV brings up the FMS VNAV submenu, shown in Figure 3–7. The crew can use this menu to cancel VNAV (CNCL VNAV) or return (RTN) to the MAIN MENU. AD–63818@ FMS VNAV Submenu Figure 3–7 SNGP (SINGLEPOINT) VNAV SUBMENU...
  • Page 48 PRIMUS 1000 Integrated Avionics System By using the SET knob and selecting the correct button, the crew can enter either the start–of–descent or start–of–climb distance to (TO) or from (FR) a station, the station elevation (ST EL), and the target altitude (ALT).
  • Page 49 PRIMUS 1000 Integrated Avionics System FMS NAV Source – The operation of SNGP VNAV with an FMS navigation source is similar to the description for the VOR NAV source, except the crew does not have to input station elevation because the FMS can extract the station elevation from its database.
  • Page 50 PRIMUS 1000 Integrated Avionics System T/O (TAKEOFF) SPEEDS SUBMENU The T/O SPEEDS submenu, shown in Figure 3–11, selects and sets three different airspeed references (V1, VR, and V2), or returns to the MAIN MENU. Once selected (activated), the airspeed bugs and their values are displayed on the PFD airspeed display.
  • Page 51: Lndg Speeds Submenu

    PRIMUS 1000 Integrated Avionics System LNDG (LANDING) SPEEDS SUBMENU The LNDG SPEEDS submenu, shown in Figure 3–12, selects and sets two different airspeed references (VREF and VAPP), or returns to the MAIN MENU. When this submenu is selected, the airspeed bugs and values are displayed on the PFD airspeed display as fixed or moving bugs.
  • Page 52: Display Controller (Dc)

    PRIMUS 1000 Integrated Avionics System INOPERATIVE MENU If the display controller becomes inoperative, MENU INOP annunciates on the MFD, as shown in Figure 3–13. AD–63814@ Inoperative Menu Figure 3–13 Display Controller (DC) The display controller, shown in Figure 3–14, selects display features on the PFD.
  • Page 53 PRIMUS 1000 Integrated Avionics System HSI Button – This button toggles the HSI display between the full compass and arc compass formats. If the weather radar is on and the arc format is selected, weather returns are displayed. The power–up default is full compass. SC/CP (Single Cue/Crosspointer) Button –...
  • Page 54 PRIMUS 1000 Integrated Avionics System BRG (Bearing) Knobs – The HSI can display two independent bearing pointers. The selectable bearing sources for each pointer are described in Table 3–1. Installation All Aircraft NAV 1 NAV 2 Single ADF Dual ADF ADF1 ADF2 Single FMS...
  • Page 55 PRIMUS 1000 Integrated Avionics System RA (Radio Altitude) Knob – The RA knob is the inner part of a concentric knob (the outer part is the DIM control). Minimums displayed on the PFD can be adjusted by turning the RA knob as follows: —...
  • Page 56 PRIMUS 1000 Integrated Avionics System NOTES: 1. A localizer frequency must be tuned on both NAV receivers to annunciate ILS. 2. Self–test is limited to radio altimeter test only in the air and is inhibited after glideslope or glidepath capture. 3.
  • Page 57: Remote Instrument Controller

    PRIMUS 1000 Integrated Avionics System Remote Instrument Controller The remote instrument controller, shown in Figure 3–15, selects course and heading for display on the HSIs. The functional controls are listed below. AD–63825@ Remote Instrument Controller Figure 3–15 COURSE Knobs – The COURSE knobs set the VOR navigation course.
  • Page 58: Multifunction Display (Mfd) Controller

    PRIMUS 1000 Integrated Avionics System Multifunction Display (MFD) Controller The MFD controller, shown in Figure 3–16, controls the MFD display format, symbol generator reversion, MFD dimming, and checklist operation, as well as weather, TCAS, and map inputs. The functions and modes on the MFD are described below. AD–63826@ Multifunction Display Controller Figure 3–16...
  • Page 59 PRIMUS 1000 Integrated Avionics System WEATHER WX (Weather) Button – This button controls weather radar returns on the MFD map display. If the plan view is being displayed when the WX button is pushed, the plan view is replaced with the map view.
  • Page 60: Index

    PRIMUS 1000 Integrated Avionics System CHECKLIST The NORM and EMER buttons display the normal and emergency checklists on the MFD. NORM (Normal) Button – Pushing this button enters the MFD’s normal checklist display function and displays the normal checklist index page on the MFD screen. The normal checklist is arranged in the order of standard flight operations.
  • Page 61: Checklist Index Display

    PRIMUS 1000 Integrated Avionics System ENT Button – The effect of pushing the ENT button depends on whether the display is an index page or a checklist page: — INDEX PAGE – Pushing ENT on an index page, as shown in Figure 3–17, displays the selected checklist.
  • Page 62 PRIMUS 1000 Integrated Avionics System — CHECKLIST PAGE – Pushing ENT on a checklist page acknowledges that the selected item is complete (green) and moves the active selection to the next incomplete (blue) item. If ENT is pushed with the active selection at the last item on a checklist, its effect depends upon whether or not the checklist is completed.
  • Page 63: Efis Reversion Controller

    PRIMUS 1000 Integrated Avionics System EFIS Reversion Controller EFIS reversion functions retain usable flight displays even after multiple failures. For example, if a PFD tube fails, its data can be displayed on the MFD, or data from a failed symbol generator can be replaced by the remaining good symbol generator.
  • Page 64 PRIMUS 1000 Integrated Avionics System HDG REV (Heading Reversion) Switch – Use this switch to select heading sources, as described in Table 3–4. Condition Pilot Copilot Power–up MAG 1 MAG 2 First Push MAG 2 MAG 1 Second Push MAG 1 MAG 2 Heading Reversion Switch Functions Table 3–4...
  • Page 65: Primary Flight Display (Pfd)

    PRIMUS 1000 Integrated Avionics System PRIMARY FLIGHT DISPLAY (PFD) The PFD is an integrated display of essential flight information. The PFD is divided into functional groups, shown in Figure 3–19, that are described below. PFD Functional Divisions Figure 3–19 Mode Annunciators – The PFD displays mode annunciators from the flight guidance system, PFD source selection, and comparison monitor functions.
  • Page 66: Attitude Director Indicator (Adi) Displays And Annunciators

    PRIMUS 1000 Integrated Avionics System HSI Display – The PFD HSI heading display receives inputs from the AHRS. The HSI display includes the following: — Full compass mode — Arc mode — Weather mode. Attitude Director Indicator (ADI) Displays and Annunciators The ADI display, shown in Figure 3–20, displays standard attitude information as described below.
  • Page 67 PRIMUS 1000 Integrated Avionics System AD–63829@ Attitude Director Indicator Displays and Annunciators Figure 3–20 A28–1146–134 Electronic Flight Instrument System (EFIS) REV 1 Jan/03 3-29/(3-30 blank)
  • Page 68: Pitch Scale Markings

    PRIMUS 1000 Integrated Avionics System Pitch Scale – The pitch scale consists of white scale markings, as shown in Figure 3–21, with reference marks every 5_ from 0_ to 30_. excessive pitch warning chevrons are displayed at 45_ and 65_ pitch up and at 35_, 50_, and 65_ pitch down.
  • Page 69 PRIMUS 1000 Integrated Avionics System Category II (CAT2) ILS Annunciators – The symbol generator displays a green or flashing amber CAT2 annunciator on the right upper portion of the PFD, above the vertical deviation scale. The CAT2 mode annunciator indicates that the excessive ILS deviation monitors are active.
  • Page 70: Pfd With Excessive Deviation Monitor

    PRIMUS 1000 Integrated Avionics System CAT2 Approach Window – A green Category II approach window on the vertical deviation scale is accompanied by a green horizontal bar. If Category II limits are exceeded, the window, scale, and pointer all change to amber, as shown in Figure 3–22. AD–63831@ PFD with Excessive Deviation Monitor Figure 3–22...
  • Page 71 PRIMUS 1000 Integrated Avionics System CAT2 Excessive Deviation Monitors – When CAT2 is displayed, the ILS excessive deviation monitors are active. If glideslope deviation exceeds Category II window requirements with radio altitude less than 600 feet, the glideslope deviation scale changes from green to flashing amber, and the glideslope pointer changes...
  • Page 72: Single Cue And Crosspointer Command Bars

    PRIMUS 1000 Integrated Avionics System Radio Altitude (RA) Minimums Set Display – The RA set display is located below and to the right of the attitude sphere. It is a three–character digital readout with a white RA label. The range is 5 to 999 feet.
  • Page 73 PRIMUS 1000 Integrated Avionics System Attitude Sphere – The attitude sphere shows the aircraft pitch and roll attitudes relative to the horizon. The sphere is filled with two colors: cyan representing the sky and brown representing the ground, separated by a white line representing the horizon. Pitch attitude is limited to ±90_, and roll attitude has a full 360_ of motion.
  • Page 74 PRIMUS 1000 Integrated Avionics System Low Bank Limit – The low bank limit indicators are displayed as green tick marks at the 14_ position on the roll attitude scale. They are a visual indication of flight director bank limits and are displayed only when the flight director is valid.
  • Page 75 PRIMUS 1000 Integrated Avionics System Radio Altitude Minimums Annunciator – The RA minimums annunciator is in the upper left area of the attitude sphere. RA minimums arm when all of the following conditions exist: — The aircraft is airborne — Radio altitude and RA minimums are valid —...
  • Page 76: Comparison Monitor Annunciators

    PRIMUS 1000 Integrated Avionics System Comparison Monitor Annunciators – Comparison monitors indicate that there is a difference between the pilot’s and copilot’s displayed data. When they are activated, all comparison monitors flash amber for ten seconds, then remain steady. Figure 3–23 shows the comparison monitor locations.
  • Page 77: Horizontal Situation Indicator (Hsi) Displays And Annunciators

    PRIMUS 1000 Integrated Avionics System Horizontal Situation Indicator (HSI) Displays and Annunciators FULL COMPASS DISPLAY The HSI annunciators on the PFD are shown in Figure 3–24. HEADING DRIFT SELECT ANGLE HEADING LUBBER LINE DIAL HEADING SOURCE ANNUNCIATORS (NOTE) FMS VNAV MAG1 ANNUNCIATOR MAG2...
  • Page 78: Drift Angle Bug Colors

    PRIMUS 1000 Integrated Avionics System Heading Select Bug and Display – The heading select bug rotates around the compass arc. The heading select bug is positioned using the HEADING knob on the instrument remote controller. HDG (white) is displayed in the lower left–hand corner of the HSI area. Directly below HDG is a cyan digital readout of the heading select...
  • Page 79: Distance Display Range

    PRIMUS 1000 Integrated Avionics System NAV Source Annunciator – The selected NAV source displayed on the course deviation indicator (CDI) is transmitted from the on–side display controller. If the on–side controller is invalid, the symbol generator processor reverts to on–side primary NAV (pilot – VOR1, copilot –...
  • Page 80: Bearing Selector

    PRIMUS 1000 Integrated Avionics System Bearing Pointers and Sources – The two bearing pointers and their symbols ) indicate bearing to the selected navaid. The bearing pointer annunciator is displayed in the lower left corner of the HSI. The annunciator color matches the bearing pointer color, cyan for the circle pointer and white for the diamond pointer.
  • Page 81 PRIMUS 1000 Integrated Avionics System The scaling for a VOR NAV source is given in Table 3–11. Full Left/Right Outer Dots Inner Dots >10° 10° 5° NOTE: Scaling can vary depending on FMS. VOR NAV Source Lateral Deviation Scaling Table 3–11 If FMS is the NAV source and the GPS is valid, the scaling is defined in Table 3–12.
  • Page 82: Vor To/From Indicator

    PRIMUS 1000 Integrated Avionics System Elapsed Time (ET), Time–To–Go (TTG), or Groundspeed (GSPD) Display – By pushing the GSPD/TTG button on the display controller, the groundspeed or time–to–go can be alternately displayed in the lower right corner. The groundspeed is calculated and displayed in magenta when the long range navigation system...
  • Page 83: Fms Accuracy And Crosstrack Messages

    PRIMUS 1000 Integrated Avionics System Wind Vector – Wind information is displayed in the lower left of the HSI. The wind is displayed in magenta for on–side data, or yellow for cross–side data. Wind direction relative to the aircraft is displayed as an arrow.
  • Page 84: Fms Annunciator Messages

    PRIMUS 1000 Integrated Avionics System The course pointer display is in the upper left corner of the HSI. If short range NAV has been selected, the label is CRS (course). If long range NAV has been selected, the label is DTRK (desired track).
  • Page 85: Heading Source Annunciators

    PRIMUS 1000 Integrated Avionics System Compass Sync Annunciator – The compass sync annunciator indicates the state of the DG in the slaved (AUTO) mode. The bar represents commands to the DG to slew the indicated direction for increased heading and for decreased heading).
  • Page 86: Hsi Arc Display

    PRIMUS 1000 Integrated Avionics System ARC DISPLAY Most of the arc display annunciators, shown in Figure 3–25, are the same as for the full compass HSI display. The differences are described below. WEATHER RADAR MODES WAIT STBY FSBY CR/R GMAP TEST FAIL FPLN...
  • Page 87: Weather Radar Return Color Code

    PRIMUS 1000 Integrated Avionics System Weather Radar Returns – Weather radar returns are displayed inside the compass arc. The returns are color coded, as described in Table 3–18. Weather (WX) Ground Map Return Mode (GMAP) Mode Level 0 Black Black Level 1 Green Cyan...
  • Page 88: Selectable Radar Ranges

    PRIMUS 1000 Integrated Avionics System The inner range ring is half of the range setting on the weather radar controller. Weather radar range is annunciated by white digits at the end of the half–range ring. The radar range, listed in Table 3–19, is selected using the weather radar controller.
  • Page 89: Weather Warning Annunciators

    PRIMUS 1000 Integrated Avionics System Weather Warnings – Directly below the weather mode annunciator line is a shared target alert (TGT) and variable gain (VAR) status line. The target alert annunciator warns of level 3 targets. displayed in place of TGT to show that the radar is operating in the variable gain mode.
  • Page 90: Weather Mode Annunciators

    PRIMUS 1000 Integrated Avionics System Weather Radar Modes – When weather is selected on the display controller, weather information is displayed on the arc format. Each PFD can display independently selected weather information. The mode annunciators, described in Table 3–21, are displayed to the left of the compass arc.
  • Page 91: Airspeed Display

    PRIMUS 1000 Integrated Avionics System Airspeed Display The airspeed sections of the PFD are shown in Figure 3–26. The upper left display shows the Federal Aviation Administration (FAA) with the low speed awareness annunciator. The lower display shows the European Joint Airworthiness Authorities (JAA) with the approved low speed awareness annunciator.
  • Page 92 PRIMUS 1000 Integrated Avionics System Overspeed Tape – The overspeed indicator is a fixed bar along the inner right side of the airspeed tape that originates at and extends to the top of the airspeed tape. Airspeed Trend Vector and Reference Line – The airspeed trend vector is a magenta bar along the outer right side of the airspeed...
  • Page 93: Low Speed Awareness Bar Color

    PRIMUS 1000 Integrated Avionics System Low Speed Awareness Bar – A low speed awareness bar indicates the aircraft condition relative to a stall. The bar starts from the bottom right side of the airspeed tape. When the amber portion reaches the airspeed reference line, the aircraft is at about 0.7_ normalized angle–of–attack (AOA).
  • Page 94 PRIMUS 1000 Integrated Avionics System Airspeed Display and Trend Vector – IAS is displayed as green rolling digits inside the display window. The digits in the window are magnified and readable to a 1 knot resolution. When the current airspeed value is equal to or exceeds the maximum allowable airspeed (V ) the digits turn red.
  • Page 95: Altimeter Display

    PRIMUS 1000 Integrated Avionics System Altimeter Display Figure 3–27 shows the annunciators located on the altimeter display and described in the paragraphs that follow. ALTITUDE ANALOG ALTITUDE SCALE SELECT DISPLAY ALTITUDE TREND VECTOR ALTITUDE AND SCALE DIGITAL DISPLAY ALTITUDE SELECT BUG BAROMETRIC ALTIMETER SETTING INCHES OF MERCURY...
  • Page 96 PRIMUS 1000 Integrated Avionics System Altitude Select Display – A selected altitude is displayed in boxed digits at the top of the altitude scale. The altitude is set with the altitude preselect knob on the MFD bezel controller. The display reads in 100–foot increments from –1000 to +60,000 feet.
  • Page 97: Altitude Select

    PRIMUS 1000 Integrated Avionics System DESCENDING TO FL 140 140 00 CYAN 15000 FT 140 00 AMBER 14200 FT 140 00 CYAN 14000 FT SELECTED ALTITUDE CYAN 13800 FT 140 00 AMBER 13000 FT 140 00 CYAN CLIMBING TO FL 140 AD–66567@ Altitude Select Figure 3–28...
  • Page 98 PRIMUS 1000 Integrated Avionics System Altitude Digital Display – A green digital altitude readout is in the display window. Current altitude is magnified in the window and is readable to within a 20–foot resolution. The display is removed when altitude information goes invalid. Metric Altitude Digital Display –...
  • Page 99 PRIMUS 1000 Integrated Avionics System Altitude Trend Vector and Scale – The altitude trend vector is a magenta bar that starts at the altitude reference line and moves vertically along the left side of the altitude tape. It indicates what altitude the aircraft will reach in six seconds if the current vertical speed is maintained.
  • Page 100: Vertical Speed (Vs) Display

    PRIMUS 1000 Integrated Avionics System Vertical Speed (VS) Display The vertical speed display, shown in Figure 3–29, is on the lower right of the PFD. It is described in the following paragraphs. VERTICAL SPEED TARGET DISPLAY VERTICAL SPEED REFERENCE LINE VERTICAL SPEED TARGET BUG VERTICAL SPEED...
  • Page 101: Traffic Alert And Collision Avoidance System (Tcas) (Optional)

    PRIMUS 1000 Integrated Avionics System For vertical speeds greater than ±3500 fpm, the pointer is positioned near the end of the scale, and the digital readout gives the actual vertical speed value. If the vertical speed goes invalid, the readout and the box are removed.
  • Page 102: Tcas Status Messages

    PRIMUS 1000 Integrated Avionics System There are two types of RAs: Corrective – A corrective RA recommends a deviation from the current vertical rate to avoid an intruder. Preventive – A preventive RA recommends avoiding certain deviations from the current vertical rate. RA directions from the TCAS computer are in the form of vertical speed commands displayed on the VSI scale.
  • Page 103: (Egpws) (Optional)

    PRIMUS 1000 Integrated Avionics System Enhanced Ground Proximity Warning System (EGPWS) (Optional) EGPWS general operating modes and failure annunciators are displayed on the PFD, as shown in Figure 3–31. EGPWS MODE ANNUNCIATIONS WIND SHEAR (RED) PULL UP (RED) GND PROX (AMBER) WIND SHEAR (AMBER) EGPWS FAILURE MODES...
  • Page 104: Typical Pfd Presentations

    PRIMUS 1000 Integrated Avionics System Typical PFD Presentations This section illustrates PFD displays typical of various phases of flight. The examples given here are representative. They do not show all display possibilities. TAKEOFF USING GO–AROUND (GA) MODE The aircraft has started the takeoff roll, as shown in Figure 3–32. modes have been selected.
  • Page 105: Climb To Initial Altitude

    PRIMUS 1000 Integrated Avionics System CLIMB TO INITIAL ALTITUDE The aircraft is on climb, accelerating through 180 kts to 200 kts in and flight level change (FLC) modes, as shown in Figure 3–33. The autopilot is engaged ENG). Altitude select is armed, and the altitude preselect digits (7000) have changed from cyan to amber,...
  • Page 106: Enroute Cruise

    PRIMUS 1000 Integrated Avionics System ENROUTE CRUISE Figure 3–34 shows the aircraft straight and level on a preselected altitude of 31,000 feet, flying hold with VOR (white) armed for capture. The autopilot is engaged ENG) and airspeed is kts or .700 Mach.
  • Page 107: Setup For Approach

    PRIMUS 1000 Integrated Avionics System SETUP FOR APPROACH Figure 3–35 shows the aircraft flying while armed for localizer and glideslope capture (white LOC and GS). The glideslope and localizer displays are in view. The cyan ASEL digits (2500) indicate the aircraft is more than 1000 feet above the approach fix altitude. Airspeed is knots.
  • Page 108: Approach Capture Tracking At Minimums

    PRIMUS 1000 Integrated Avionics System APPROACH CAPTURE TRACKING AT MINIMUMS Figure 3–36 shows the aircraft on final approach with captured and autopilot engaged ENG). The radio altitude of feet is below the 200–foot decision height, activating the box. The rising brown in the altimeter is 100 feet from the altitude reference line.
  • Page 109: Comparison Monitor Annunciators

    PRIMUS 1000 Integrated Avionics System COMPARISON MONITORING amber comparison monitor annunciators appear in various locations on the PFD, as shown in Figure 3–37. Active messages clear when the miscompare situation has been corrected. AD–63845@ Comparison Monitor Annunciators Figure 3–37 A28–1146–134 Electronic Flight Instrument System (EFIS) 3-72 REV 1 Jan/03...
  • Page 110 PRIMUS 1000 Integrated Avionics System Parameters monitored are: Pitch (PIT) attitude ±5_ Roll (ROL) attitude ±6_ Attitude (ATT) – Active only when both pitch and roll comparators are already tripped Heading (HDG) ±6_ Altitude (ALT) ±200 feet Airspeed (IAS) ±5 knots Localizer (LOC) deviation about 1/2 dot below 1200 feet AGL Glideslope (GS) deviation about 1/2 dot below 1200 feet AGL Instrument landing system (ILS) –...
  • Page 111: Excessive Attitude Display

    PRIMUS 1000 Integrated Avionics System EXCESSIVE ATTITUDE DISPLAY An excessive attitude condition occurs when the roll attitude exceeds 65_, or pitch exceeds 30_ nose up or 20_ nose down, as shown in Figure 3–38. If the excessive attitude condition is due to excessive pitch, excessive pitch chevrons are displayed.
  • Page 112 PRIMUS 1000 Integrated Avionics System To declutter the display, the following annunciators are removed when an excessive attitude condition exists: Vertical, lateral, and non–synched flight director mode annunciators Flight director arrow Low bank limit Flight director command bars Vertical deviation scale, pointer, and label Vertical track alert annunciator Marker beacons and box Radio altitude digital readout...
  • Page 113: Pfd Caution And Failure Displays

    PRIMUS 1000 Integrated Avionics System PFD Caution and Failure Displays The PFD caution and failure messages are described below. CAUTION MESSAGES Maximum Speed (MAX SPD) – The speed warning is displayed on the left side of the ADI. MAX SPD is displayed anytime IAS exceeds Traffic Alert and Collision Avoidance System (TCAS) (Optional) –...
  • Page 114 PRIMUS 1000 Integrated Avionics System Same Attitude Source – If both pilots are using normal on–side attitude sources, the attitude source is not displayed. When a new attitude source is selected, it is annunciated in white. If both pilots have selected the same attitude source, it is annunciated in amber on both PFDs.
  • Page 115: Pfd Failure Indications

    PRIMUS 1000 Integrated Avionics System FAILURE ANNUNCIATORS Failure messages, shown in Figure 3–39, are described below. AD–63846@ PFD Failure Indications Figure 3–39 Attitude Reference System Failure – Failure of either pitch or roll data is indicated by removing the pitch scale markings, turning the entire attitude sphere to cyan, and displaying ATT FAIL in the top...
  • Page 116 PRIMUS 1000 Integrated Avionics System Flight Director Failure – In the event of a flight director failure, FAIL is displayed in the lateral mode annunciator box, and the flight director mode annunciators and cues are removed. Radio Altimeter Failure – For a failure of the radio altimeter, –RA–...
  • Page 117: Pfd Test Mode

    PRIMUS 1000 Integrated Avionics System PFD TEST MODE The PFD test can be initiated with the display controller when airspeed is valid and less than 60 knots, and the weight–on–wheels (WOW) switch is in the on–ground mode. Figure 3–40 shows the invalid flags for the following PFD information: MADC Flight director...
  • Page 118: Multifunction Display (Mfd)

    PRIMUS 1000 Integrated Avionics System MULTIFUNCTION DISPLAY (MFD) Two basic formats are available on the MFD: a partial arc map view display (oriented to magnetic north) and a full arc plan view display (oriented to true north). The map format is the power–up default. The map or plan formats can be selected using the MAP/PLAN button on the MFD controller.
  • Page 119: Mfd Common Symbols And Annunciators

    PRIMUS 1000 Integrated Avionics System MFD Common Symbols and Annunciators The following symbols and concepts are common to both the map and plan formats. Figure 3–41 shows the locations of display data described in the paragraphs that follow. MFD Map Display Common Symbols Figure 3–41 Waypoint Symbol –...
  • Page 120: Mfd Display Symbols

    PRIMUS 1000 Integrated Avionics System Heading Display – The compass rose consists of a 120_ arc that is marked in 5_ increments and labeled every 30_. The compass rose rotates around the stationary aircraft symbol to show heading. The compass markings and labels are white. A green digital heading readout is displayed above the compass lubber line.
  • Page 121: Weather Radar Mode Annunciators On Mfd

    PRIMUS 1000 Integrated Avionics System Aircraft Symbol – The white aircraft symbol shows the aircraft’s position relative to the flight plan data. It is always oriented vertically. Designator Range and Bearing – Bearing and distance from the designator’s anchor point to its present position are displayed in cyan in the lower right part of the MFD.
  • Page 122 PRIMUS 1000 Integrated Avionics System Annunciator Line Mode FPLN Flight plan mode GMAP Ground map mode Normal weather radar with ground clutter reduction Weather radar with REACT and turbulence WX/T Normal weather radar with turbulence Normal weather radar on and selected for display Invalid weather control bus, invalid weather ranges...
  • Page 123 PRIMUS 1000 Integrated Avionics System Navigation Aids – Navaids are displayed in green. A maximum of four disconnected navaids are displayed. A four–character identifier is displayed to the right of each valid navaid symbol. If Navaids are selected for display, a green triangle is displayed at the right center of the MFD.
  • Page 124: Map View

    PRIMUS 1000 Integrated Avionics System Map View The map view, shown in Figure 3–43, is a heading–up presentation of an active flight plan. The active TO waypoint is displayed in magenta. A range ring is centered on the aircraft position. Weather radar returns can be displayed in the map view.
  • Page 125 PRIMUS 1000 Integrated Avionics System Lateral Deviation – Crosstrack distance information is displayed on the MFD with L or R when the path is left or right of the desired track. Distance is displayed with values from 0 to 128 NM with a resolution of 0.01 NM for distances less than 100 NM and 1 NM for distances over 100 NM.
  • Page 126: Typical Map View Presentation

    PRIMUS 1000 Integrated Avionics System Figure 3–44 shows a typical map view without weather display. AD–63852@ Typical Map View Presentation Figure 3–44 A28–1146–134 Electronic Flight Instrument System (EFIS) REV 1 Jan/03 3-89...
  • Page 127: Map View With Weather Display

    PRIMUS 1000 Integrated Avionics System Map View With Weather Display A brief description of the PRIMUS 660 Weather Radar System is included in Appendix A of this manual. Weather radar information is displayed only when the radar controller has been turned on and weather has been selected on the map format, as shown in Figure 3–45.
  • Page 128: Typical Map View With Weather

    PRIMUS 1000 Integrated Avionics System Figure 3–46 shows a typical map view presentation with weather. AD–63856@ Typical Map View With Weather Figure 3–46 A28–1146–134 Electronic Flight Instrument System (EFIS) REV 1 Jan/03 3-91...
  • Page 129: Plan View

    PRIMUS 1000 Integrated Avionics System Plan View The plan view is a north–up presentation of an active flight plan. The active TO waypoint is displayed in magenta. A range ring showing the selected display range is centered on either the aircraft’s position or the pilot designator’s position.
  • Page 130: Typical Plan View With Navaids And Flight Plan

    PRIMUS 1000 Integrated Avionics System Pilot Designator Position Data – This readout is displayed only when the designator is moved off a waypoint or home position. When activated, it provides a digital readout of the distance and bearing to the designator from the waypoint or home position. Selected Range –...
  • Page 131: Checklist Display

    PRIMUS 1000 Integrated Avionics System Checklist Display Normal and emergency checklists are displayed in a pop–up window on the MFD, as shown in Figure 3–49, and controlled by the MFD controller. Completed checklists or items within a checklist are green, and incomplete items are cyan.
  • Page 132 PRIMUS 1000 Integrated Avionics System If it becomes necessary to exit a checklist before completion (by pushing NORM again), upon re–entering the checklist the computer returns to the last item completed. If an item has been skipped, the computer will return to the skipped item. If several items have been skipped, it will return to the first skipped item.
  • Page 133: Traffic Alert And Collision Avoidance System

    PRIMUS 1000 Integrated Avionics System Traffic Alert and Collision Avoidance System (TCAS) Display (Optional) The TCAS display shows bearing, distance, and relative altitude to other Mode C and Mode S transponder–equipped aircraft in the area. The TCAS display is a zoom window on the MFD that shows an increased resolution of the intruder traffic in the vicinity of the aircraft, while allowing the pilot to display a map or plan view at a greater range.
  • Page 134: Typical Tcas Display Annunciators

    PRIMUS 1000 Integrated Avionics System The map view with optional TCAS display is shown in Figure 3–50. Typical TCAS Display Annunciators Figure 3–50 No Bearing Target Readout – Bearing messages are displayed on two lines in the upper right side of the TCAS window whenever the system encounters an RA or TA target that has range but no bearing information for display.
  • Page 135 PRIMUS 1000 Integrated Avionics System Since the MFD controls the map/plan view range, the TCAS range ring is proportional to the MFD selected range. The displayed TCAS range is based on information transmitted from the TCAS control head. The MFD software (IAC) supports 3, 6, 10, 12, 14, 15, 20, 25, 40, and 50 NM range selections in the TCAS mode.
  • Page 136: Mfd Tcas Annunciators

    PRIMUS 1000 Integrated Avionics System Automatic display of TCAS on the MFD is shown at the last selected TCAS range. However, the first selection of TCAS on the MFD after power–up always presents the 6 NM range. TCAS Altitude Display Submodes – The TCAS submodes are annunciated in the upper left corner of the TCAS window: —...
  • Page 137: Display Symbols

    PRIMUS 1000 Integrated Avionics System TCAS Traffic Symbols – TCAS uses color–coded symbols and data tags to map traffic and locate threat aircraft on the MFD. Each symbol type is a different color, as described in Table 3–28. Symbol Display Function Resolution Advisory (RA).
  • Page 138: Typical Tcas Display

    PRIMUS 1000 Integrated Avionics System Figure 3–28 shows a typical TCAS display. AD–63859@ Typical TCAS Display Figure 3–51 A28–1146–134 Electronic Flight Instrument System (EFIS) REV 1 Jan/03 3-101...
  • Page 139: Enhanced Ground Proximity Warning System

    PRIMUS 1000 Integrated Avionics System Enhanced Ground Proximity Warning System (EGPWS) Display (Optional) The EGPWS displays terrain cautions, warnings, and map information. The system is turned on or off with the TERR (terrain) button on the MFD bezel controller. When selected, the EGPWS terrain map replaces the weather radar display on the MFD.
  • Page 140: Egpws Terrain Display Vs Aircraft Altitude

    PRIMUS 1000 Integrated Avionics System The terrain data is displayed ahead of the aircraft symbol on the MFD in green, yellow, and colors that define terrain elevation relative to current aircraft altitude, as defined in Table 3–30. Terrain Elevation Relative to the Aircraft Terrain Color Terrain is 2000 feet or more above the Red/black mixture...
  • Page 141 PRIMUS 1000 Integrated Avionics System In Figure 3–52, the aircraft is 6000 feet over KSEA airport, flying north. The Olympic Mountains are displayed to the northwest of the aircraft and the Cascade Mountains lie to the northeast. The EGPWS range is set to 100 NM.
  • Page 142: Egpws Test Display

    PRIMUS 1000 Integrated Avionics System The EGPWS TEST display is shown in Figure 3–53. The TEST display is initiated using an external button. MAG1 FMS1 25.2 KPAE GSPD TERR TEST VNAV VSPEED TERR FMS1 – – – FMS2 – – AD–63861@ EGPWS TEST Display Figure 3–53...
  • Page 143: Egpws Pop-Up Display

    PRIMUS 1000 Integrated Avionics System EGPWS POP–UP MODE The EGPWS pop-up display, as shown in Figure 3–54, appears automatically when ground proximity presents an imminent danger. MAG1 FMS1 25.2 KPAE GSPD TERR TEST VNAV VSPEED TERR FMS1 – – – FMS2 –...
  • Page 144: Mfd Failure And Warning Displays

    PRIMUS 1000 Integrated Avionics System MFD Failure and Warning Displays Figure 3–55 shows the map view display with failure and warning annunciators, which are described below. DU WRAP AROUND HEADING FAILURE WARNING HEADING SELECT (AMBER) FAILURE FAILURE IC OVERHEAT WARNING FMS FAILURE (AMBER) WARNING...
  • Page 145: Wraparound Failure Warnings

    PRIMUS 1000 Integrated Avionics System DU Wraparound Failure Warning – If either IAC detects an indication on either PFD that is not being commanded by the IAC, a message is displayed in the upper left corner. Messages that can appear in this field are listed in Table 3–31. Message Pilot Response CHK PFD1...
  • Page 146: Ic Overheat Warnings

    PRIMUS 1000 Integrated Avionics System MENU INOP – A MENU INOP message is displayed in the center of the lower section of the MFD if heading goes invalid or the display controller fails. The joystick is enabled if the plan view is selected and heading is invalid.
  • Page 147: Mfd Failure And Warning Displays

    PRIMUS 1000 Integrated Avionics System Figure 3–56 shows MFD failure and warning displays. AD–63864@ MFD Failure and Warning Displays Figure 3–56 A28–1146–134 Electronic Flight Instrument System (EFIS) 3-110 REV 1 Jan/03...
  • Page 148: Display System Reversionary Modes

    PRIMUS 1000 Integrated Avionics System DISPLAY SYSTEM REVERSIONARY MODES EFIS Reversionary Modes EFIS 1 (PILOT NORMAL) FAILURE A failure of EFIS 1 (or its interface) is annunciated in one of the following ways: on the pilot PFD on the MFD on both the pilot PFD and MFD.
  • Page 149: Display Color Coding Convention

    PRIMUS 1000 Integrated Avionics System DISPLAY COLOR CODING CONVENTION Table 3–34 shows colors for the course pointer, course deviation, TO/FROM pointer, navigation source, and digital CRS/DTRK course. Navigation Source Color NAV On–side Green FMS On–side Magenta FMS/NAV Cross–side Yellow Course Pointer Color Convention Table 3–34 A28–1146–134 Electronic Flight Instrument System (EFIS)
  • Page 150: Flight Guidance System (Fgs)

    PRIMUS 1000 Integrated Avionics System Flight Guidance System (FGS) GENERAL The flight guidance system consists of a flight director, autopilot, yaw damper, and controls. The flight director outputs guidance information and displays guidance cues. The flight director autopilot maintains the flight profile selected by the flightcrew.
  • Page 151 PRIMUS 1000 Integrated Avionics System The left group of buttons on the mode selector controls the lateral modes, and the right group of buttons controls the vertical modes. When a button is pushed, its annunciator bar lights and the PFD displays the mode’s armed or captured status.
  • Page 152: Autopilot Controller

    PRIMUS 1000 Integrated Avionics System VS (Vertical Speed) Button – When the VS button is pushed, the flight director maintains the current vertical speed. A new vertical speed can be selected and maintained with either the autopilot PITCH wheel or TCS. The vertical speed target is displayed on the PFD.
  • Page 153 PRIMUS 1000 Integrated Avionics System PITCH Wheel – Moving the PITCH wheel with the autopilot engaged changes the pitch attitude in proportion to the rotation rate of the PITCH wheel and in the direction the wheel is moved. Moving the PITCH wheel cancels only altitude hold or altitude preselect capture.
  • Page 154: Remote Switches And Annunciators

    PRIMUS 1000 Integrated Avionics System TURN Knob – Rotating the TURN knob out of detent commands a roll. The roll angle is proportional to and in the direction of the TURN knob rotation. The maximum roll angle that can be input using the TURN knob is 30°.
  • Page 155: Autopilot Preflight Test

    PRIMUS 1000 Integrated Avionics System AUTOPILOT PREFLIGHT TEST The autopilot preflight test is described in Table 4–1. The power–up test (step 2 in the table below) is automatic and takes only a few seconds. It is valid if the displays are there. If the power test is not complete or fails, the displays are removed.
  • Page 156: System Limits

    PRIMUS 1000 Integrated Avionics System System Limits This section describes limits of the flight guidance system’s major functions, which are referred to throughout Section 6, Modes of Operation. ATTITUDE DIRECTOR INDICATOR (ADI) COMMAND The cue rolls or pitches to indicate an attitude that will accomplish a smooth transition to the desired flight path.
  • Page 157: Lateral Beam Sensor (Lbs)

    PRIMUS 1000 Integrated Avionics System LATERAL BEAM SENSOR (LBS) When intercepting the VOR, localizer, or back course beam, the LBS is tripped as a function of beam deviation, course error, true airspeed, and DME (if DME is available and not on HOLD). In the localizer mode, the course error is compared with the beam deviation signal to determine the LBS trip point.
  • Page 158: Navigation On Course (Noc)

    PRIMUS 1000 Integrated Avionics System NAVIGATION ON COURSE (NOC) Navigation on course occurs after initial VOR or localizer course capture. It is defined as either: The aircraft is not in over station sensor for 30 seconds, or Bank angle is less than 6°, course error is less than 22°, and either: —...
  • Page 159: Vor Capture

    PRIMUS 1000 Integrated Avionics System VOR CAPTURE VOR capture occurs when the following conditions are met: The VOR mode has been armed plus 1 second of elapsed time The lateral beam sensor has tripped. VOR OVER STATION SENSOR (OSS) The over station sensor detects the erratic radio signal encountered in the area above the VOR transmitter.
  • Page 160: System Performance And Operating Limits

    PRIMUS 1000 Integrated Avionics System SYSTEM PERFORMANCE AND OPERATING LIMITS Table 5–1 lists the system performance limits for the Citation Encore aircraft. Control or Sensor Mode Parameter Value Yaw Engage Engage Limit Up to 45_ left or right bank Damper Roll: Up to ±45_ Autopilot AP Engage...
  • Page 161 PRIMUS 1000 Integrated Avionics System Control or Sensor Mode Parameter Value On Course VOR or Roll Angle Limit VORAPR Roll Rate Limit 1_/second Crosswind Correction Up to 45_ Course Error in VOR, ±30_ in VOR APR Over Station Up to ±90_ VOR or Course Change VORAPR...
  • Page 162 PRIMUS 1000 Integrated Avionics System Control or Sensor Mode Parameter Value Glideslope/Glidepath Capture GS receiver, Beam Capture Function of beam and beam Air Data rate Computer, ±10_ and Radio Pitch Command Limit Altimeter Path Damping Vertical Acceleration Pitch Rate Limit f (TAS) Gain Programming Starts at 1200 ft radio altitude,...
  • Page 163 PRIMUS 1000 Integrated Avionics System Control or Sensor Mode Parameter Value Micro Air Data Preselect Capture –900 to 45,000 ft Preselect Computer/ Range Altitude ±6000 ft/min. Preselect on Max. VS for Capture MFD, AHRS, ±0.275g Max. Gravitational Force During Capture Maneuver ±15_ Pitch Command Limit...
  • Page 164: Air Data Display Parameters And Ranges

    PRIMUS 1000 Integrated Avionics System Table 5–2 defines the air data units of measure and their data range for this aircraft. Display Parameter Units Data Range Altitude Pressure Altitude, feet –1000 to 60,000 Baro Corrected Altitude Altitude Rate ft/min. –20,000 to +20,000 Preselect Altitude feet 0 to 60,000...
  • Page 165: Modes Of Operation

    PRIMUS 1000 Integrated Avionics System Modes of Operation LATERAL MODES Heading Hold Mode The basic autopilot lateral mode is heading hold, defined as follows: The autopilot is engaged ENG) No lateral flight director mode is selected Bank angle is less than 6_. NOTE: Basic autopilot modes are annunciated.
  • Page 166: Roll Hold Mode

    PRIMUS 1000 Integrated Avionics System Roll Hold Mode The autopilot recognizes the roll hold mode as operational when: The autopilot is engaged ENG) No lateral flight director mode is selected Bank angle is greater than 6°. When the three conditions are met, the autopilot maintains the established bank angle (with a ±35°...
  • Page 167: Heading Select Mode

    PRIMUS 1000 Integrated Avionics System Heading Select Mode The heading select mode intercepts and maintains a magnetic heading, which is set using the HEADING knob on the remote instrument controller. The mode is selected with the HDG button on the coupled– side mode selector, the HDG button lights, and is displayed on the top left of the PFD.
  • Page 168: Vor Navigation (Nav) Mode

    PRIMUS 1000 Integrated Avionics System VOR Navigation (NAV) Mode The VOR mode automatically intercepts, captures, and tracks a selected VOR radial, using the selected navigation source displayed on the coupled–side HSI. The navigation source displayed on the HSI is selected with the NAV source buttons located on the display controller. Table 6–1 describes the procedure for engaging the VOR NAV mode.
  • Page 169: Vor Nav Mode Intercept Display

    PRIMUS 1000 Integrated Avionics System On the PFD, and VOR (white) are annunciated, as shown in Figure 6–4. The IAC is armed to capture the VOR signal and generate a roll command to fly the heading select mode. VOR NAV Mode Intercept Display Figure 6–4 NOTE: If the NAV radios become invalid, the course deviation is...
  • Page 170: Vor Nav Mode Capture

    PRIMUS 1000 Integrated Avionics System VOR CAPTURE When reaching the lateral beam sensor trip point, as shown in Figure 6–5, the system automatically drops the heading select mode and switches to the VOR capture phase. VOR NAV Mode Capture Figure 6–5 In the VOR NAV capture mode, the following display changes occur: The white VOR annunciator goes out annunciator goes out...
  • Page 171: Vor Nav Mode Capture Display

    PRIMUS 1000 Integrated Avionics System Figure 6–6 shows the PFD in the VOR NAV capture mode. AD–63873@ VOR NAV Mode Capture Display Figure 6–6 The IAC generates the proper roll command to bank the aircraft to capture and track the selected VOR radial. When the course select pointer was set on the PFD using the COURSE knob on the instrument remote controller, the course select error signal was established in the IAC.
  • Page 172: Vor Nav Mode Track

    PRIMUS 1000 Integrated Avionics System VOR TRACK MODE When the aircraft meets VOR track conditions, as shown in Figure 6–7, the course error signal is removed from the lateral steering command. This leaves NAV on course and DME gain programming (if available) to track the VOR signal and to compensate for beam standoff in a crosswind.
  • Page 173: Vor Nav Mode Tracking Display

    PRIMUS 1000 Integrated Avionics System Figure 6–8 shows the PFD in the tracking mode. VOR NAV Mode Tracking Display Figure 6–8 The VOR navigation mode is cancelled by any one of the following: Pushing the NAV button on the mode selector Selecting go–around Selecting another lateral control mode Changing the selected navigation or heading source...
  • Page 174: Zone Of Confusion

    PRIMUS 1000 Integrated Avionics System Zone of Confusion As the aircraft nears the VOR zone of confusion, the radio signal becomes highly erratic. The over station sensor (OSS) monitors when the aircraft enters the zone of confusion and removes radio deviation from the roll command.
  • Page 175: Long Range Navigation (Lrn) Mode

    PRIMUS 1000 Integrated Avionics System Long Range Navigation (LRN) Mode The LRN mode is flown when the pilot selects FMS as the NAV source on the coupled–side display controller. The LRN procedure is described in Table 6–2. Step Procedure Couple either flight director to the autopilot with the FD transfer switch.
  • Page 176: Fms Mode Capture And Tracking

    PRIMUS 1000 Integrated Avionics System The FMS NAV mode is shown in Figure 6–10. FMS Mode Capture and Tracking Figure 6–10 The FMS NAV mode procedure is described in Table 6–3. Step Procedure Prepare the FMS to navigate. If necessary, set the heading bug on the HSI to the intercept heading for the selected course.
  • Page 177: Fms Nav Mode (Typical) Display

    PRIMUS 1000 Integrated Avionics System Step Procedure (cont) AD–63878@ FMS NAV Mode (Typical) Display Figure 6–11 FMS Navigation Mode Procedure Table 6–3 The LRN mode is cancelled by any one of the following: Pushing the NAV button on the mode selector Selecting go–around Changing the selected navigation steering command An invalid FMS...
  • Page 178: Vor Approach (Vapp) Mode

    PRIMUS 1000 Integrated Avionics System VOR Approach (VAPP) Mode The VOR approach procedure is described in Table 6–4. Step Procedure Couple either flight director to the autopilot with the FD transfer switch. Tune the navigation receiver to the frequency of the VOR to be used.
  • Page 179: Localizer (Nav) Mode

    PRIMUS 1000 Integrated Avionics System Localizer (NAV) Mode The localizer mode automatically intercepts, captures, and tracks the front course localizer beam to line up on the runway centerline. To engage the mode, follow the procedure described in Table 6–5. Step Procedure Couple synchronized flight director to the autopilot.
  • Page 180: Localizer (Nav) Mode Intercept

    PRIMUS 1000 Integrated Avionics System The HSI displays the position of the aircraft relative to the center of the localizer beam and the inbound course, as shown in Figure 6–12. With the heading bug set for course intercept, the heading select mode does the intercept.
  • Page 181: Localizer (Nav) Mode Arm Display

    PRIMUS 1000 Integrated Avionics System Outside the normal capture range of the localizer signal, push the NAV button on the mode selector to fly the aircraft to the intercept heading, and the system is armed for automatic localizer beam capture. LOC (white) and are annunciated on the PFD, as shown in Figure 6–13.
  • Page 182: Localizer (Nav) Mode Capture

    PRIMUS 1000 Integrated Avionics System With the aircraft nearing the selected course intercept, as shown in Figure 6–14, the lateral beam sensor monitors the localizer beam deviation. At the computed time, the lateral beam sensor trips and captures the localizer signal. The flight director drops the heading select mode and generates a roll command to bank the aircraft toward localizer beam center.
  • Page 183: Localizer (Nav) Mode Capture Display

    PRIMUS 1000 Integrated Avionics System When the capture occurs, the PFD displays enclosed in a white box for 5 seconds, as shown in Figure 6–15. AD–63882@ Localizer (NAV) Mode Capture Display Figure 6–15 As the aircraft continues toward the localizer, the flight director enters the localizer submode.
  • Page 184: Localizer (Nav) Mode Tracking

    PRIMUS 1000 Integrated Avionics System The localizer mode is cancelled by any one of the following: Pushing the NAV button on the mode selector Selecting go–around Selecting the heading select mode NAV or HDG source switching Symbol generator reversion, if on the coupled side Changing the flight director couple selection.
  • Page 185: Localizer (Nav) Mode Tracking Display

    PRIMUS 1000 Integrated Avionics System Figure 6–17 shows a typical PFD in the localizer tracking mode. AD–63884@ Localizer (NAV) Mode Tracking Display Figure 6–17 A28–1146–134 Modes of Operation REV 1 Jan/03 6-21...
  • Page 186: Back Course (Bc) Mode

    PRIMUS 1000 Integrated Avionics System Back Course (BC) Mode The back course mode intercepts, captures, and tracks the back course localizer signal, as shown in Figure 6–18. When flying a back course localizer approach, glideslope capture is inhibited automatically. Back Course Mode Intercept Figure 6–18 The back course mode is set up and flown like a front course localizer approach.
  • Page 187: Back Course Intercept Display

    PRIMUS 1000 Integrated Avionics System Step Procedure With the aircraft outside the normal back course localizer capture limits, the PFD annunciates BC (white) and HDG, as shown in Figure 6–19. AD–63886@ Back Course Intercept Display Figure 6–19 Back Course Mode Procedure Table 6–6 (cont) A28–1146–134 Modes of Operation...
  • Page 188: Back Course Capture Display

    PRIMUS 1000 Integrated Avionics System Step Procedure At back course capture, the PFD annunciates BC, enclosed in a white box for 5 seconds, as shown in Figure 6–20. AD–63887@ Back Course Capture Display Figure 6–20 Back Course Mode Procedure Table 6–6 NOTE: The back course function does not automatically intercept the localizer back course.
  • Page 189: Back Course Tracking Display

    PRIMUS 1000 Integrated Avionics System At back course capture, the IAC flight control function generates a roll command to capture and track the back course localizer signal, as shown in Figure 6–21. AD–63888@ Back Course Tracking Display Figure 6–21 The back course mode is cancelled by any one of the following: Symbol generator reversion, if on the coupled side Pushing NAV on the mode selector panel Pushing BC on the mode selector panel...
  • Page 190: Vertical Modes

    PRIMUS 1000 Integrated Avionics System VERTICAL MODES Pitch Hold Mode The pitch hold mode is the basic autopilot and flight director vertical mode. is annunciated on the PFD when this mode is active. This mode is best described by explaining the operation of pitch hold with autopilot engaged and with autopilot not engaged.
  • Page 191 PRIMUS 1000 Integrated Avionics System PITCH HOLD MODE OPERATION, AUTOPILOT NOT ENGAGED Pitch hold mode with autopilot not engaged operates as described below: Selecting a flight director lateral mode with no flight director vertical modes active displays the crosspointer horizontal command bar. The command bar represents the aircraft pitch attitude at the time the flight director lateral mode was selected.
  • Page 192: Vertical Speed (Vs) Hold Mode

    PRIMUS 1000 Integrated Avionics System Vertical Speed (VS) Hold Mode The vertical speed hold mode maintains a pilot–selected vertical speed. To initiate the mode, maneuver the aircraft to the desired climb or descent attitude, establish the vertical speed reference, and push the VS button on the mode selector.
  • Page 193: Vertical Speed Hold Mode Display

    PRIMUS 1000 Integrated Avionics System AD–63895@ Vertical Speed Hold Mode Display Figure 6–22 The vertical speed mode is cancelled by any one of the following: Pushing the VS button Selecting another vertical mode Selecting go–around Changing the flight director couple selection Symbol generator reversion, if on the coupled side Air data becomes invalid Loss of pitch data.
  • Page 194: Flight Level Change (Flc) Mode

    PRIMUS 1000 Integrated Avionics System Flight Level Change (FLC) Mode The flight level change mode is engaged by pushing the FLC button on the mode selector. The IAS/Mach reference is synchronized to the IAS/Mach being flown when the mode is engaged. When a new reference is manually selected using the PITCH wheel on the autopilot controller, the system automatically flies the new reference.
  • Page 195: Flight Level Change Mode Display

    PRIMUS 1000 Integrated Avionics System The flight level change mode is annunciated on the PFD by at the vertical capture location, as shown in Figure 6–23. AD–63897@ Flight Level Change Mode Display Figure 6–23 The pilot can maneuver the aircraft without disengaging the flight level change mode by pushing and holding the TCS button on the control wheel.
  • Page 196: Flight Level Change Mode Engagement Procedure

    PRIMUS 1000 Integrated Avionics System To fly the flight level change mode in a climb to a preselected altitude from straight and level, follow the procedure described in Table 6–7. Step Procedure Set alert altitude higher than the current altitude. Push the FLC button on the mode selector.
  • Page 197: Altitude Preselect Mode (Asel)

    PRIMUS 1000 Integrated Avionics System 3. Manual toggling between an IAS and Mach speed target is not possible. 4. The FGS cannot fly to an airspeed reference outside the normal aircraft flight envelope. The FGS limits the commanded airspeed to the maximum speed of the aircraft, annunciated by MAXSPD to the left of the ADI.
  • Page 198: Asel At The Start Of Descent

    PRIMUS 1000 Integrated Avionics System Table 6–8 describes the ASEL mode operation procedure. Step Procedure Set the new target altitude on the PFD with the ALT knob on the MFD bezel. Push either the VS or FLC button on the FGS mode selector, then set the value for vertical speed (VS mode) or airspeed (FLC mode) by using the PITCH wheel on the autopilot controller to initiate a descent toward the selected altitude.
  • Page 199: Asel Armed For Capture Display

    PRIMUS 1000 Integrated Avionics System Step Procedure After the descent is initiated, the altitude preselect mode is armed and ASEL (white) is annunciated on the PFD, as shown in Figure 6–26. The aircraft is descending through 16,000 feet at 1500 fpm.
  • Page 200: Asel Capture Point Display

    PRIMUS 1000 Integrated Avionics System Step Procedure As the aircraft descends to within 1000 feet of the target altitude, a visual alert (the altitude preselect window and readout change color from cyan to amber) and an audible alert (a one–second horn) annunciate. The visual alert remains active until the aircraft is within 200 feet of the target altitude.
  • Page 201: Aircraft Level At Preselected Altitude Display

    PRIMUS 1000 Integrated Avionics System Step Procedure After the aircraft has leveled off at the new altitude, ASEL capture is dropped and altitude hold automatically engages, as shown by in Figure 6–28. Once the aircraft has captured the altitude, any deviation of more than 200 feet activates the visual and audible alerts.
  • Page 202: Altitude Hold Mode

    PRIMUS 1000 Integrated Avionics System Altitude Hold Mode The altitude hold (ALT HOLD) mode is a vertical axis flight director mode used to maintain a barometric altitude reference. To fly ALT HOLD, follow the procedure in Table 6–11. Step Procedure Push the ALT button on the coupled–side mode selector.
  • Page 203 PRIMUS 1000 Integrated Avionics System Altitude hold maintains the altitude that existed when the mode was engaged. The reference altitude can be changed by pushing the TCS button on the control wheel, maneuvering the aircraft to a new altitude, and releasing the TCS button. Selecting the ALT HOLD mode cancels any other previously selected vertical mode.
  • Page 204: Vertical Navigation Mode (Vnav)

    PRIMUS 1000 Integrated Avionics System Vertical Navigation Mode (VNAV) The VNAV mode can be used only with the VNAV menu on the MFD. It is used to descend to an altitude at a specific VOR/DME or FMS– defined waypoint. The waypoint can be defined as being on a course TO or FROM a station.
  • Page 205 PRIMUS 1000 Integrated Avionics System Step Procedure For VOR/DME–based VNAV, enter VOR station or waypoint elevation above sea level using the SET knob on the MFD bezel. Select TO or FROM and set the distance (along–track offset) the waypoint is ahead of (TO) or beyond (FROM) the VOR or FMS waypoint.
  • Page 206: Vnav Direct

    PRIMUS 1000 Integrated Avionics System VNAV Direct Figure 6–30 shows an aircraft at FL210 expecting to fly VNAV from the present position directly to 17,000 feet at the waypoint shown. Data is entered into the system using the MFD bezel buttons. (Refer to Table 6–10 for the data entry procedure).
  • Page 207: Mfd Vang Display

    PRIMUS 1000 Integrated Avionics System After data is entered, use the procedure in Table 6–11 to fly the VNAV direct mode. Figures in the table show the menus on the MFD used to engage the VNAV direct engagement mode. Step Procedure Observe the angle displayed on the MFD, as shown in Figure 6–31.
  • Page 208: Mfd Vang Capture Display

    PRIMUS 1000 Integrated Avionics System Step Procedure When the correct VANG is displayed, push the VNAV button on the coupled–side mode selector. The VNAV and APR buttons light on the mode selector, the angle is displayed as shown in Figure 6–32, and VNAV (white) armed annunciates on the PFD.
  • Page 209: Vnav Preselect, Profile View

    PRIMUS 1000 Integrated Avionics System VNAV PRESELECT Figure 6–33 shows an aircraft at FL210 expecting a 3_ descent to 17,000 feet at the waypoint shown. VNAV Preselect, Profile View Figure 6–33 A28–1146–134 Modes of Operation REV 1 Jan/03 6-45...
  • Page 210: Mfd Vang Set

    PRIMUS 1000 Integrated Avionics System After data is entered (refer to Table 6–10 for the data entry procedure), follow the procedure in Table 6–12 to fly the VNAV preselect mode. Figure 6–34 shows the MFD menu used to engage the VNAV preselect mode.
  • Page 211 PRIMUS 1000 Integrated Avionics System VNAV mode is cancelled by any one of the following: Pushing the VNAV or any other vertical flight director mode button Glideslope capture Leveling off at the waypoint altitude Overspeed or underspeed protection transition Changing PFD navigation source Loss of DME distance or air data valid Selecting go–around Symbol generator reversion, if on the coupled side...
  • Page 212: Instrument Landing System (Ils) Approach Mode

    PRIMUS 1000 Integrated Avionics System INSTRUMENT LANDING SYSTEM (ILS) APPROACH MODE The ILS mode intercepts, captures, and tracks the front course localizer and glideslope signals to fly a fully coupled ILS approach, as shown in Figure 6–35. ILS Localizer Intercept Figure 6–35 The mode is set up and flown exactly like the localizer mode.
  • Page 213: Ils Approach (Armed) Display

    PRIMUS 1000 Integrated Avionics System The ILS approach mode procedure is described in Table 6–13. Step Procedure Couple either flight director to the autopilot with the FD transfer switch. Tune the coupled–side navigation receiver to the ILS frequency for the runway in use. Push the NAV button on the display controller to select ILS as the navigation source.
  • Page 214: Ils Approach Mode - Localizer Intercept Display

    PRIMUS 1000 Integrated Avionics System Step Procedure With the localizer captured and outside the normal glideslope capture limits, the PFD annunciates GS (white), as shown in Figure 6–37. AD–63891@ ILS Approach Mode – Localizer Intercept Display Figure 6–37 ILS Approach Mode Procedure Table 6–13 A28–1146–134 Modes of Operation...
  • Page 215 PRIMUS 1000 Integrated Avionics System The glideslope part of the ILS mode intercepts, captures, and tracks the glideslope signal. When the glideslope mode is used with the localizer approach mode, a fully coupled ILS approach can be flown. The mode is interlocked so that glideslope capture is inhibited until localizer capture has occurred.
  • Page 216: Ils Mode Tracking Display

    PRIMUS 1000 Integrated Avionics System The PFD, shown in Figure 6–39, annunciates in a white box for 5 seconds, and LOC. The NAV and APR mode selector buttons are also lit. AD–63893@ ILS Mode Tracking Display Figure 6–39 NOTE: The autopilot must be disengaged before reaching 200 feet AGL.
  • Page 217: Ils Mode Track, Profile View

    PRIMUS 1000 Integrated Avionics System The glideslope signal is gain programmed to compensate for the aircraft closing on the glideslope antenna and beam convergence caused by the directional properties of the antenna, as shown in Figure 6–40. Glideslope programming is normally a computed function of radio altitude (if available).
  • Page 218: Overspeed Protection

    PRIMUS 1000 Integrated Avionics System OVERSPEED PROTECTION When in MAXSPD, the flight guidance system adjusts the pitch to reduce airspeed to the V limit. The flight director modes remain as they were. When airspeed is reduced below the V limit, the FGS returns to the annunciated flight director mode.
  • Page 219: Go-Around Mode (Ga), Wings Level

    PRIMUS 1000 Integrated Avionics System GO–AROUND MODE (GA), WINGS LEVEL The go–around mode is normally used to transition from an approach to a climb–out condition in the event of a missed approach. The pilot selects the go–around mode by pushing the GA button located on either outboard throttle handle.
  • Page 220: Troubleshooting

    It does not describe troubleshooting down to the black box level. TECHNICAL SUPPORT The following Honeywell and Cessna support lines are available: Honeywell Hot Line: 602–436–4400 Cessna 24–hour Support Line: 316–517–6261...
  • Page 221: Accessing Maintenance Test Mode Data

    ACCESSING MAINTENANCE TEST MODE DATA NOTE: At no time should maintenance personnel attempt to replace a Honeywell unit based on event codes alone. The event codes should be used as a tool along with traditional ground test methods and other standard maintenance practices.
  • Page 222: How To Access The Hardware/Software I.d. Pages

    PRIMUS 1000 Integrated Avionics System How to Access the Hardware/Software I.D. Pages The maintenance test mode displays maintenance pages on the PFD while the aircraft is on the ground (WOW switch is set). The display controller controls the maintenance test mode. The RA knob selects display pages.
  • Page 223: Hardware Id Page 1

    PRIMUS 1000 Integrated Avionics System Table 7–2 describes the procedure to access hardware and software ID pages. Step Procedure Set the RA knob on the display controller to 640. Push and hold the TEST button for at least 5–7 seconds. While holding the TEST button, push and release PB #4.
  • Page 224: Hardware Id Page 2

    PRIMUS 1000 Integrated Avionics System Step Procedure Rotate the TEST button clockwise to RA 650 to display HW ID 2, as shown in Figure 7–3. The IC is in the maintenance test mode, and it remains in test until it is cancelled by pushing the TEST button again or by selecting an RA setting below 600.
  • Page 225: How To Access Event Codes (Ec)

    For event codes, use radio altimeter setting 670. For help with troubleshooting after the event codes have been retrieved, contact the local Cessna or Honeywell Customer Service Engineer. Refer to the booklet “Your Citation Center Support Team.” The display controllers in various installations have different button labels.
  • Page 226: Sample Event Codes Page On Pfd

    PRIMUS 1000 Integrated Avionics System To retrieve the event codes, follow the procedure in Table 7–3. Step Procedure Set the display controller RA knob to 670. Push and hold the TEST button for at least 5–7 seconds. While holding the TEST button, push and release PB #4. Release the TEST button.
  • Page 227: Event Codes Page Description

    PRIMUS 1000 Integrated Avionics System Event codes for 64 flights can be stored. Flight 65 overwrites the data from flight 01, and so on. Each flight number can store 48 event codes. The event codes pages display zeros when no events have occurred. NOTE: Flights are recorded only when an event code has occurred.
  • Page 228: Event Codes Page Description

    PRIMUS 1000 Integrated Avionics System Data on the event codes page is described in Table 7–4. Legend Display and Description Range Color Maintenance EVENT Maintenance page title. page title CODES Flight FLIGHT 01– Represents the WOW cycle 01 to 64, number current flight number where an event...
  • Page 229: Event Codes Listing

    PRIMUS 1000 Integrated Avionics System Event Codes Listing Two categories of IAC events and associated codes are: Power–up Events – These result in a latched event, identified as event codes 0001 to 0199 and all 90XX event codes. The 28 Vdc circuit breaker must be cycled off/on to reset this latched event.
  • Page 230: Common Event Codes And Possible Causes

    PRIMUS 1000 Integrated Avionics System Common Event Codes and Possible Causes Table 7–5 is a list of common event codes and possible causes. Event Code Maintenance Description Possible Causes Actions 00XX Power–Up Event Codes That Prevent Autopilot Engagement 0036 The AP elevator This is generally a Maintenance is current is not high...
  • Page 231 02XX Continuous Event Codes That Disengage the AP and YD 0214 Stick shaker went Faulty stick shaker Refer to the active when the input to IAC or Honeywell AP/YD was aircraft flown into Troubleshooting engaged. stick shaker region. Manual, A15–1146–074.
  • Page 232 PRIMUS 1000 Integrated Avionics System Event Code Maintenance Description Possible Causes Actions 03XX Power–Up Event Codes – EFIS 0320 RS–422 channel This is generally a Maintenance is No. 3 Universal nuisance code that required only when 5 Asynchronous logs infrequently. or more occurrences Receiver–Trans are observed in one...
  • Page 233: Ec 0221 Troubleshooting Procedure

    PRIMUS 1000 Integrated Avionics System Step Procedure If the fault is not caused by a crewmember overpowering the control wheel, replace the pitch servo motor. If the fault is caused by a crewmember overpowering the control wheel, the servo was backdriven. No maintenance is required.
  • Page 234: Typical Problems

    PRIMUS 1000 Integrated Avionics System Step Procedure If high roll rates occurred during turbulence, no maintenance is required. The system is operating as intended. If turbulence was not encountered, swap VGs from side to side and monitor future operation. Since the autopilot uses No.
  • Page 235: Lateral Mode Conditions And Problems

    PRIMUS 1000 Integrated Avionics System Figure 7–7 shows diagrams of typical in–flight lateral mode problems. Lateral Mode Conditions and Problems Figure 7–7 (cont) A28–1146–134 Troubleshooting 7-16 REV 1 Jan/03...
  • Page 236 PRIMUS 1000 Integrated Avionics System Lateral Mode Conditions and Problems Figure 7–7 A28–1146–134 Troubleshooting REV 1 Jan/03 7-17...
  • Page 237: Vertical Mode Problems

    PRIMUS 1000 Integrated Avionics System Vertical Mode Problems Common vertical mode problems are listed in Table 7–11. Mode Problem Air data hold modes (ALT, VS, – Oscillates IAS, MACH) – Porpoises – Does not hold reference Altitude preselect (ASEL) – Misses capture –...
  • Page 238 PRIMUS 1000 Integrated Avionics System Vertical Mode Conditions and Problems Figure 7–8 A28–1146–134 Troubleshooting REV 1 Jan/03 7-19...
  • Page 239: Combined Vertical And Lateral Mode Problems

    PRIMUS 1000 Integrated Avionics System Combined Vertical and Lateral Mode Problems Table 7–12 lists common combined vertical and lateral mode problems. Mode Problems Mode logic problems – Modes do not engage – Modes do not clear Autopilot problems – Autopilot does not engage –...
  • Page 240: Ground Maintenance Test

    PRIMUS 1000 Integrated Avionics System GROUND MAINTENANCE TEST On the ground, the system can access the status of several key internal functions in the IAC. The ground maintenance test procedure is described in Table 7–13. Step Procedure Initiate system test by powering up the aircraft on the ground.
  • Page 241: Ground Maintenance Test Displays On Pfd

    PRIMUS 1000 Integrated Avionics System AD–63916@ Ground Maintenance Test Displays on PFD Figure 7–9 A28–1146–134 Troubleshooting REV 1 Jan/03 7-23/(7-24 blank)
  • Page 242: Checklist Uploading Procedure

    PRIMUS 1000 Integrated Avionics System CHECKLIST UPLOADING PROCEDURE The checklist uploading procedure is described in Table 7–14. Step Procedure Make sure the aircraft is on the ground and powered up in standby. Locate the dual IAC connector on the pilot side, next to the right rudder pedal.
  • Page 243 PRIMUS 1000 Integrated Avionics System Step Procedure Push and release PB#1 on the display controller. The PFD blanks and an is displayed. The remains until after step 11. Use the electronic programmable checklist software on the PC to output the checklist and upload it to the pilot’s IAC. NOTE: If a checklist is already in the IAC, error code 5100 is displayed on the PC.
  • Page 244: Typical Checklist Display

    PRIMUS 1000 Integrated Avionics System Checklists cannot be downloaded from the IAC. Ensure that the checklist is saved on the PC or a floppy disk so it is available for future uploading as required. Figure 7–10 shows a typical checklist display. AD–65091@ Typical Checklist Display Figure 7–10...
  • Page 245: Checklist Loading Troubleshooting

    Try reprogramming the other IAC. If the other IAC programs, there may be problems with the IAC being programmed or in the aircraft wiring. Contact the Honeywell Checklist Product Support, noted in the electronic programmable checklist manual. Checklist Loading Troubleshooting Procedure Table 7–15...
  • Page 246: Error Code 5000

    PRIMUS 1000 Integrated Avionics System Error Code 5000 An error code 5000 means that the PC cannot communicate with the IAC. When error 5000 is received, first try the steps listed in Table 7–15. Error Code 5005 An error code 5005 usually occurs when the IAC has never been programmed with a checklist before.
  • Page 247: Ap Disconnect Switch Function To Reset A Failure

    PRIMUS 1000 Integrated Avionics System AP Disconnect Switch Function to Reset a Failure The AP disconnect switch, mounted on the control wheel, disconnects the autopilot and resets monitor–induced autopilot disconnects. If the autopilot disconnects because a monitor in the pitch, roll, or yaw axis senses control pressure (for example, a pilot’s feet on the rudder when the yaw damper tries to execute a yaw damper function), the AP FAIL...
  • Page 248: Pilot Write-Up

    1000 Integrated Avionics System PILOT WRITE–UP Report Forms Honeywell provides squawk sheets on the back of flight plan forms, Honeywell Form No. 20323–000, dated 1/99, to aid flight planning and troubleshooting. The form is shown in Figure 7–11. The sample Event Code Report forms in Figures 7–12 and 7–13 can be copied and used to record event codes if tablets of the forms are not available.
  • Page 249: Writing The Report

    PRIMUS 1000 Integrated Avionics System Writing the Report Define the problem, including specific conditions under which the problem exists, such as: Flags showing (which ones, if any) Mode or modes selected IAS when the problem occurs Period and magnitude of any oscillations Any inputs that fail to work (such as heading bug when in HDG mode).
  • Page 250: Pilot Check And Squawk Sheet

    PRIMUS 1000 Integrated Avionics System AD–63918@ Pilot Check and Squawk Sheet Figure 7–11 A28–1146–134 Troubleshooting REV 1 Jan/03 7-33/(7-34 blank)
  • Page 251: Event Code Report Form

    PRIMUS 1000 Integrated Avionics System AD–63919@ Event Code Report Form Figure 7–12 A28–1146–134 Troubleshooting REV 1 Jan/03 7-35/(7-36 blank)
  • Page 252: Continued Event Code Report Form

    PRIMUS 1000 Integrated Avionics System AD–63920@ Continued Event Code Report Form Figure 7–13 A28–1146–134 Troubleshooting REV 1 Jan/03 7-37/(7-38 blank)
  • Page 253: Acronyms And Abbreviations

    PRIMUS 1000 Integrated Avionics System Acronyms and Abbreviations Acronyms and abbreviations used in this manual are defined as follows: TERMS DEFINITION Above Alternating Current Air Data Computer Automatic Direction Finder Attitude Director Indicator Air Data System Above Ground Level AHRS Attitude and Heading Reference System Altitude ANSI...
  • Page 254: Electronic Flight Instrument System (Efis) ( Cont )

    PRIMUS 1000 Integrated Avionics System TERMS DEFINITION Dimming Direction Distance Measuring Equipment Down Dead Reckoning DTRK Desired Track Display Unit Event Code EFIS Electronic Flight Instrument System EGPWS Enhanced Ground Proximity Warning System Extended Memory Manager Engage Enter Elapsed Time Federal Aviation Administration Flight Director Flight Guidance System...
  • Page 255 PRIMUS 1000 Integrated Avionics System TERMS DEFINITION Horizontal Situation Indicator Hertz Inner Integrated Avionics Computer Indicated Airspeed Integrated Computer Instrument Landing System inHg Inches of Mercury INHIB Inhibit INTG Integrity INVD Invalid Joint Airworthiness Authorities (European) Knob Knots Latitude Lateral Beam Sensor LNDG Landing Localizer...
  • Page 256 PRIMUS 1000 Integrated Avionics System TERMS DEFINITION Outer Over Station Sensor Pushbutton Personal Computer Primary Flight Display Pitch PRCHDG Procedure Turn Heading PROX Proximity REACT/Turbulence Radio Altitude Resolution Advisory Recall Rain Echo Attenuation Compensation Technique Reversionary Radio Magnetic Indicator Radio Management Unit Range Roll Receiver Transmitter Antenna...
  • Page 257 PRIMUS 1000 Integrated Avionics System TERMS DEFINITION SYNC Synchronize Traffic Advisory True Airspeed Total Air Temperature TCAS Traffic Alert and Collision Avoidance System Touch Control System TERR Terrain Target Takeoff Top–of–Climb Top–of–Descent Track Turn Time–To–Go Transmitting UART Universal Asynchronous Receiver–Transmitter Volts VALD Valid...
  • Page 258 PRIMUS 1000 Integrated Avionics System TERMS DEFINITION Vertical Speed Vertical Speed Indicator VSPD, VSPEED Vertical Speed Vertical Track Alert Weight–On–Wheels Waypoint WSHR Windshear Weather WX/T Weather/Turbulence Crosstrack Yaw Damper A28–1146–134 Acronyms and Abbreviations REV 1 Jan/03...
  • Page 259: Primus R 660 Weather Radar System

    This appendix is an abbreviated operational description of the PRIMUS 660 Weather Radar System. For complete operating instructions, refer to Honeywell Pub. No. A28–1146–111. WARNING THE SYSTEM PERFORMS ONLY THE FUNCTIONS OF WEATHER DETECTION OR GROUND MAPPING. IT IS NOT INTENDED THAT THIS SYSTEM EITHER BE USED OR RELIED UPON FOR PROXIMITY WARNING OR ANTICOLLISION PROTECTION.
  • Page 260: Weather Radar Controller

    PRIMUS 1000 Integrated Avionics System Range marks and identifying numerics, displayed in contrasting colors, are used to evaluate the location of storm cells relative to the aircraft. The ground mapping (GMAP) function is used to improve resolution and identification of small ground targets at short ranges. The reflected signals from ground surfaces are displayed as magenta, yellow, or cyan (most to least reflective).
  • Page 261 PRIMUS 1000 Integrated Avionics System RANGE SWITCHES The range switches are two momentary contact buttons that are used to set the operating radar range. Weather ranges can be set from 5 to 300 NM full scale. In the flight plan (FPLN) mode, ranges of 500 and 1000 NM can be set.
  • Page 262 PRIMUS 1000 Integrated Avionics System TGT (TARGET) BUTTON The TGT button is used to enable and disable the radar target alert feature. Target alert is selectable in all but the 300 mile range. When selected, target alert monitors beyond the selected range and 7.5_ on each side of the aircraft heading.
  • Page 263 PRIMUS 1000 Integrated Avionics System TILT KNOB The rotary TILT knob is used to set the tilt angle of the antenna beam with relation to the aircraft’s longitudinal axis. Clockwise rotation tilts the beam upward to +15_, and counterclockwise rotation tilts the beam downward to –15_.
  • Page 264 PRIMUS 1000 Integrated Avionics System FSBY (Forced Standby) – Forced standby is an automatic, nonselectable radar mode. FSBY mode is a safety feature that inhibits the transmitter on the ground to eliminate the X–band microwave radiation hazard. The controller is wired to the weight–on–wheels (WOW) switch.
  • Page 265 PRIMUS 1000 Integrated Avionics System GMAP – Selecting the GMAP position places the radar system in the ground mapping mode. The system is fully operational and all internal parameters are set to enhance returns from ground targets. RCT compensation is inactive. CAUTION WEATHER–TYPE TARGETS ARE NOT CALIBRATED WHEN THE RADAR IS IN THE GMAP MODE.
  • Page 266 PRIMUS 1000 Integrated Avionics System TEST – The TEST position selects the radar test mode. A special test pattern is displayed to verify system operation. TEST displayed in the MFD mode field. WARNING IF THE AIRCRAFT IS ON THE GROUND AND FORCED STANDBY IS OVERRIDDEN, THE TRANSMITTER IS ON AND RADIATING X–BAND MICROWAVE ENERGY IN THE TEST MODE.
  • Page 267: Normal Operation

    Do not operate if personnel are standing too close to the 270_ forward sector of aircraft. (Refer to Maximum Permissible Exposure Level (MPEL) in this appendix.) Operating personnel should be familiar with FAA AC 20–68B, referenced in Honeywell Pub. No. 28–1146–120. PRIMUS 660 Weather Radar System Precautions Table A–4 A28–1146–134...
  • Page 268 PRIMUS 1000 Integrated Avionics System POWER–UP On power–up, select either the standby or test mode. When power is first applied, the radar is in WAIT mode for 45 seconds to let the magnetron warm up. Power sequences ON–OFF–ON lasting less than the initial 45–second wait result in a 6–second wait period.
  • Page 269 PRIMUS 1000 Integrated Avionics System AD–63923–R1@ MFD Display Weather Radar Test Pattern Figure A–3 A28–1146–134 PRIMUSr 660 Weather Radar System REV 1 Jan/03 A–11...
  • Page 270 PRIMUS 1000 Integrated Avionics System TILT MANAGEMENT The figures below show the relationship between tilt angle, flight altitude, and selected range. Figure A–4 shows the distance above and below aircraft altitude that is illuminated by the flat–plate radiator during level flight with 0_ tilt Radar Beam Illumination High Altitude 12–Inch Radiator Figure A–4...
  • Page 271: Maximum Permissible Exposure Level (Mpel

    The American National Standards Institute, in their document ANSI C95.1–1982, recommends an exposure level of no more than 5 mW/cm Honeywell Inc. recommends that operators follow the 5 mW/cm standard. Figure A–6 shows the MPEL for the 12–inch antenna and PRIMUS 660 Weather Radar System power.
  • Page 272: Index

    PRIMUS 1000 Integrated Avionics System Index Approach capture tracking, 3-71 APR button, 4-2 Abbreviations, 8-1 APT button, 3-20 Acronyms, 8-1 ATT REV switch, 3-25 ADC REV switch, 3-26 Attitude director indicator (ADI), Air data display, 3-27 3-28 parameters, 5-9 aircraft symbol, 3-35 Air data system (ADS), 2-7 airspeed warning, 3-37 air data source, 3-36...
  • Page 273 PRIMUS 1000 Integrated Avionics System Index (cont) Autopilot controller, 2-6, 4-3 emergency, 3-95 AP button, 4-4 index pages, 3-23 AP disconnect button, 4-5 loading, 7-25 autopilot preflight test, 4-6 NORM button, 3-22 BANK LIMIT switch, 4-4 normal, 3-94 GA button, 4-5 typical display, 7-27 PITCH wheel, 4-4 Climb to initial altitude, 3-68...
  • Page 274 PRIMUS 1000 Integrated Avionics System Index (cont) Designator LAT/LON, 3-84 Designator line, range/bearing, 3-86 Desired track lateral deviation, 3-43 Elapsed time, 3-45 reciprocal pointer, 3-45 Electronic flight instrument system DGR message flag, 3-47 (EFIS), 2-1, 2-4, 3-1, 3-31 DIM (dimming) control, 3-16, 3-24 cockpit layout, 3-3 Directional gyro (DG), 2-8 controller conventions, 3-7...
  • Page 275 PRIMUS 1000 Integrated Avionics System Index (cont) EMER button, 3-95 IC overheat, 3-109 Enhanced ground proximity warning MADC, 3-108 system (EGPWS) (optional), 2-9, MENU INOP, 3-109 3-66, 3-102 TAT, 3-108 color scheme, 3-103 weather radar, 3-109 messages, 3-102 radio altimeter, 3-79 pop–up display, 3-106 TCAS messages, 3-76 TEST mode, 3-105...
  • Page 276 3-46 HSI, 3-48 HSI button, 3-15 MFD map view, 3-88 HEADING knob, 3-19 Honeywell product support, 1-7 customer support centers, 1-8 North America, 1-8 IAS display, 3-56 Rest of the world, 1-9 failure displays, 3-78 exchange/rental support...
  • Page 277 PRIMUS 1000 Integrated Avionics System Index (cont) IN/HPA button, 3-15 Instrument landing system (ILS) approach mode, 6-48 Mach display, 3-56 Category II (CAT2), 3-32 Maintenance, 7-1 Integrated avionics computer (IAC), ground test, 7-21 test mode data, 7-2 Integrated avionics system (IAS), MAP/PLAN button, 3-20 Marker beacons, 3-34 INTG message flag, 3-47...
  • Page 278 PRIMUS 1000 Integrated Avionics System Index (cont) altitude preselect, 6-33 dimming control, 3-24 flight level change, 6-30 EMER button, 3-22 pitch hold, 6-26 ENT (enter) button, 3-21, 3-23 vertical speed hold, 6-28 joystick, 3-21, 3-24 VNAV mode, 6-40 MAP/PLAN button, 3-20 Multifunction display (MFD), 3-81 mode selector switch, 3-24 bezel controller, 3-6...
  • Page 279 PRIMUS 1000 Integrated Avionics System Index (cont) Multifunction display (MFD) (cont) PITCH wheel, 4-4 TCAS (optional) (cont) Preflight test, 4-6 mode messages, 3-99 Primary flight display (PFD), 3-5 no bearing readout, 3-97 air data displays, 3-27 off scale symbols, 3-98 airspeed display, 3-54 range ring, 3-97 1.3 Vstall bug (JAA), 3-57...
  • Page 280 PRIMUS 1000 Integrated Avionics System Index (cont) bezel controller, 3-5 checklist loading BARO set knob, 3-5 troubleshooting, 7-28 controller conventions, 3-7 event code retrieval, 7-7 inclinometer, 3-5 FLC mode engagement, 6-32 inoperative menu, 3-14 FMS navigation mode, 6-12 menu functions, 3-5 ground maintenance test, 7-21 STD (standard) button, 3-5 hardware/software ID page...
  • Page 281 PRIMUS 1000 Integrated Avionics System Index (cont) Resolution advisories, TCAS PRIMUS 660 Weather Radar (optional), 3-64, 3-100 System, 2-7 Reversion functions/modes, 3-25 PRIMUS 880 Weather Radar ADC REV switch, 3-26 System (Optional), 2-7 ATT REV switch, 3-25 PRIMUS II Integrated Radio display controller failures, 3-111 System, 2-9 EFIS failures, 3-111...
  • Page 282 PRIMUS 1000 Integrated Avionics System Index (cont) map view diagram, 3-97 mode messages, 3-99 no bearing readout, 3-97 Variable gain display, 3-84 off scale symbols, 3-98 Vertical beam sensor (VBS), 5-3 range ring, 3-97 Vertical deviation, 3-34, 3-79 resolution advisories, 3-64 Vertical gyro, 2-8 status messages, 3-65 fast erect switch, 2-10...
  • Page 283 PRIMUS 1000 Integrated Avionics System Index (cont) XTK message, 3-46 Warning displays, MFD, 3-107 displays, 3-110 DU wraparound, 3-108 EGPWS, 3-66 FMS, 3-108 Yaw damper, event codes, 7-11 heading select, 3-108 disengage AP/YD, 7-12 IC fan, 3-109 EFIS, 7-13 IC overheat, 3-109 Yaw damper (YD), 2-6 MADC, 3-108 YD button, 4-4...