Page 1 PRIMUS 1000 Integrated Avionics System Pilot's Manual for the Embraer 145 AD-52817@...
Page 2 Business and Commuter Aviation Systems Honeywell Inc. Box 29000 Phoenix, Arizona 85038--9000 PRIMUSr1000 Integrated Avionics System for the Embraer Model 145 Pilot’ s Manual Printed in U.S.A. Pub. No. A28--1146--112--00 August 1997...
Page 3 Honeywell Inc. Neither this document nor the information contained herein shall be used, reproduced, or disclosed to others without the written authorization of Honeywell Inc., except to the extent required for installation or maintenance of recipient’ s equipment.
Page 4 Upon receipt of a revision, insert the latest revised pages and dispose of superseded pages.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 the Record of Revisions. The typed initials HI are used when Honeywell Inc. is the incorporator. Revision Revision...
Page 5 PRIMUSr1000 Integrated Avionics System Record of Temporary Revisions Upon receipt of a temporary revision, insert the yellow temporary revision pages according to the filing instructions on each page. Then, enter the temporary revision number, issue date, and insertion date on this page.
Page 6 PRIMUSr1000 Integrated Avionics System List of Effective Pages Original Aug 1997 Subheading and Page Revision Subheading and Page Revision Title Page 2--3 2--4 Record of Revisions 2--5 RR--1/RR--2 2--6 2--7 Record of Temporary Revisions 2--8 RTR--1/RTR--2 2--9 2--10 List of Effective Pages 2--11/2--12 LEP--1 LEP--2...
Page 7 PRIMUSr1000 Integrated Avionics System Subheading and Page Revision Subheading and Page Revision Electronic Flight Instrument System 4--68 (EFIS) (cont) 4--69 4--21 4--70 4--22 4--71 4--23 4--72 4--24 4--73 4--25 4--74 4--26 4--75 4--27/4--28 4--76 4--29 4--77 4--30 4--78 4--31 4--79 4--32 4--80 4--33...
Page 8 PRIMUSr1000 Integrated Avionics System Subheading and Page Revision Subheading and Page Revision Engine Instrument and Crew Alerting 8--6 System (EICAS) (cont) 8--7 5--15 8--8 5--16 8--9 5--17 8--10 5--18 8--11 5--19 8--12 5--20 8--13 5--21 8--14 5--22 8--15 5--23 8--16 5--24 8--17 5--25...
Page 9 PRIMUSr1000 Integrated Avionics System Subheading and Page Revision Subheading and Page Revision Troubleshooting (cont) C--5 9--10 C--6 9--11 C--7 9--12 C--8 9--13/9--14 C--9 C--10 Honeywell Product Support C--11 10--1 C--12 10--2 C--13 10--3 C--14 10--4 C--15 C--16 Abbreviations C--17 11--1 C--18 11--2...
Page 10 PRIMUSr1000 Integrated Avionics System Subheading and Page Revision Subheading and Page Revision Index (cont) Index--12 Index--13 Index--14 Index--15 Index--16 Index--17 Index--18 Index--19 Index--20 Index--21 Index--22 Index--23 Index--24 A28--1146--112--00 List of Effective Pages LEP--5/(LEP--6 blank)
Page 11 PRIMUSr1000 Integrated Avionics System Table of Contents Section Page 1. INTRODUCTION ......2.
Page 12 PRIMUSr1000 Integrated Avionics System Table of Contents (cont) Section Page 4. ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) (CONT) Multifunction Display (MFD) ....4-68 MFD System Displays .
Page 13 PRIMUSr1000 Integrated Avionics System Table of Contents (cont) Section Page 7. SYSTEM LIMITS (CONT) Glideslope (GS) Gain Programming as a Radio Altitude (RA) Function ....GS Gain Programming as a RA and Vertical Speed (VS) Function .
Page 14 ....... . . 9-11 10. HONEYWELL PRODUCT SUPPORT ..
Page 15 PRIMUSr1000 Integrated Avionics System Table of Contents (cont) Section Page ....C--1 C--1 PRIMUS II RADIO SYSTEM â Introduction ....... . . C--1 System Description .
Page 16 PRIMUSr1000 Integrated Avionics System Table of Contents (cont) List of Illustrations Figure Page 1--1 PRIMUS 1000 in the Embraer 145 Cockpit ..â 2--1 PRIMUS 1000 Block Diagram ....2-11 â...
Page 17 PRIMUSr1000 Integrated Avionics System Table of Contents (cont) List of Illustrations (cont) Figure Page 4--31 TCAS II Resolution Advisory Approaching the Glideslope ....... . . 4-57 4--32 Approach Capture Tracking at DH .
Page 18 PRIMUSr1000 Integrated Avionics System Table of Contents (cont) List of Illustrations (cont) Figure Page 5--8 Crew Alerting System on EICAS Display ..5-22 5--9 EICAS Invalid Display Formats ....5-30 5--10 Backup EICAS Display on RMU -- Page 1 .
Page 19 PRIMUSr1000 Integrated Avionics System Table of Contents (cont) List of Illustrations (cont) Figure Page A--1 AHRU Block Diagram ......A--3 A--2 AHRS Controls .
Page 20 PRIMUSr1000 Integrated Avionics System Table of Contents (cont) List of Tables Table Page 1--1 Supplemental Pilot’ s Manuals ....1--2 Equipment List ......4--1 Cursor Movement/Action .
Page 21 PRIMUSr1000 Integrated Avionics System Table of Contents (cont) List of Tables (cont) Table Page 5--8 Oil Temperature Limits ......5-14 5--9 Engine Vibration Color Limits .
Page 22 PRIMUSr1000 Integrated Avionics System Table of Contents (cont) List of Tables (cont) Table Page 9--4 Problems Common to Both Vertical and Lateral Modes ........9--5 Ground Maintenance Test Procedure .
Page 23 PRIMUSr1000 Integrated Avionics System Introduction This document describes the operation, components, typical flight applications, and operating procedures for the PRIMUS 1000 Integrated Avionics System shown as part of the cockpit layout in figure 1--1, in the Embraer 145 aircraft. Subsystems described in this manual include: PRIMUS 1000 Flight Guidance System (FGS)
Page 24 PRIMUSr1000 Integrated Avionics System Model Unit Part No. Cockpit Mounted Equipment DU--870 Electronic Display Unit 7014300--901 BL--870 Primary Flight Display (PFD) 7014331--921 Bezel Controller BL--871 Multifunction/Engine (MFD) Instrument and Crew 7014332--931 Alerting System Displays (EICAS) (MFD/ EICAS) Bezel 7014332--951 Controllers PC--400 Autopilot Controller 7003897--925...
Page 25 PRIMUSr1000 Integrated Avionics System Model Unit Part No. RNZ--851 Integrated NAV Unit 7510100--VAR RCZ--851 Communications Unit with 7510700--806 Diversity Transponder RCZ--851 Communications Unit without 7510700--809 Diversity Transponder RT--910 TCAS II Computer 4066010--904 AT--910 TCAS Antenna 7514060--902 AZ--850 Micro Air Data Computer 7014700--918 (MADC) DA--800...
Page 26 PRIMUSr1000 Integrated Avionics System â PRIMUS 1000 in the Embraer 145 Cockpit Figure 1--1 A28--1146--112--00 Introduction 1-5/(1-6 blank)
Page 27 PRIMUSr1000 Integrated Avionics System System Description The PRIMUS 1000 Integrated Avionics System is a system that â includes display, flight director guidance, autopilot, and yaw damper and elevator trim functions. The integrated avionics system block diagram is shown in figure 2--1, and consists of the following units and subsystems: STANDARD Integrated Avionics Computer (IAC) that includes:...
Page 28 PRIMUSr1000 Integrated Avionics System EFIS annunciators indicate the selected autopilot/flight director mode, altitude alert, radio altitude (RA) reference and go--around mode engagement. Pitch and roll steering commands, calculated by the IAC flight director function in conjunction with the guidance controller, are displayed by command bars that direct the pilot to reach and/or maintain the required flightpath or altitude.
Page 29 PRIMUSr1000 Integrated Avionics System FLIGHT GUIDANCE SYSTEM (FGS) The flight guidance system includes the following components: Inside the IAC Flight guidance computer (No.1 IAC only) System monitors Guidance Controller Autopilot Controller Servo Motor (pitch/roll/yaw) The No. 1 IAC flight guidance computer is the fail--passive driver for the flight director, autopilot, and pitch trim.
Page 30 PRIMUSr1000 Integrated Avionics System ELECTRONIC DISPLAY SYSTEM (EDS) The EDS includes the following components: Display Symbol Generator (Inside each IAC) Display Unit (DU) -- PFD, MFD, and EICAS Bezel Controller MFD/EICAS Bezel Controller Display Controller Data Acquisition Unit (DAU) Reversionary Control Panel EICAS Reversionary Panel Remote Mounted Joystick (option).
Page 31 PRIMUSr1000 Integrated Avionics System PFD formats are selected using the DC. MFD navigation and aircraft performance displays are selected using the MFD mounted bezel controllers. If an FMS is installed, the remote--mounted MFD joystick menu is used for waypoint designation. The guidance controller contains the course, heading, selected speed, and altitude preselect controls.
Page 32 NOTE: The PRIMUS 660 Weather Radar System transmitter â power is much stronger than previous Honeywell weather radar systems. Refer to the PRIMUS 660 Weather Radar â System pilot’ s manual for ground safety information.
Page 33 II Radio â System, of this manual. For a more complete description of the PRIMUS II Radio System, refer to Honeywell Pub. No. 28--1146--050. â RADIO ALTIMETER SYSTEM The radio altimeter system includes the following components: One Radio Altimeter Receiver Transmitter Two Embraer--Supplied Antennas (Sensor Systems).
Page 34 PRIMUSr1000 Integrated Avionics System TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) This TCAS II system is described in Honeywell Pub. No. 28--1146--070, and includes the following elements: Computer Antenna. TCAS is designed to act as a backup to the ATC and the ” see and avoid”...
Page 35 PRIMUSr1000 Integrated Avionics System FLIGHT MANAGEMENT SYSTEM (FMS) (OPTION) The single FMS consists of the following: Flight Management Computer Control Display Unit (CDU) Data Loader (DL). The FMS displays lateral and vertical navigation guidance parameters, and is coupled laterally to the FGS. The CDU displays selected flight plan data.
Page 36 PRIMUSr1000 Integrated Avionics System Joystick (Option) -- This pedestal--mounted control is used with MFD JOYSTICK submenu selections to control the pilot designator (MAP view), to position the route of flight line (PLAN view), and for alternative control of the auxiliary checklist. Master Warning/Master Caution Switches -- Located on the glareshield, directly in front of each pilot, these switches flash when a respective warning or caution message is displayed on the EICAS.
Page 37 PRIMUSr1000 Integrated Avionics System RM--855 RMU IC--600 INTEGRATED AVIONICS COMPUTER AH--800 AHRU RIGHT FADEC AD--39738--R6@ PRIMUS 1000 Block Diagram Ò Figure 2--1 A28--1146--112--00 System Description 2-11/(2-12 blank)
Page 38 PRIMUSr1000 Integrated Avionics System Electronic Display System (EDS) INTRODUCTION The integrated avionics computer (IAC) electronic display system show the flightcrew flightpath, navigation, engine, and system information. Each pilot has a dedicated primary flight display (PFD) and a multifunction display (MFD). The right center display unit (DU) contains the engine instrument and crew alerting system (EICAS) display.
Page 39 PRIMUSr1000 Integrated Avionics System Cockpit Layout of EFIS Figure 3--1 A28--1146--112--00 Electronic Display System (EDS) 3-3/(3-4 blank)
Page 40 PRIMUSr1000 Integrated Avionics System MFD BEZEL CONTROLLER BASIC OPERATION The MFD bezel controller shown in figure 3--2, gives the pilot access to a variety of supplemental information through the menu item keys and rotary knob. Menu item selections are sent to the respective display controller.
Page 41 PRIMUSr1000 Integrated Avionics System Map Range Control When a parameter is not selected or being set, the rotary knob is used to select the map display range. NOTES: 1. When weather is displayed on the MFD, range is controlled from the weather radar controller. 2.
Page 42 PRIMUSr1000 Integrated Avionics System REVERSIONARY CONTROLLERS AND DIMMING PANEL System Reversionary Panel If an attitude and heading reference system (AHRS) or micro air data computer (MADC) fails, the system can be reconfigured to display the remaining good sensor on both sides of the cockpit. The remaining good sensor is selected using the AHRS or air data computer (ADC) switches on the reversionary controller shown in figure 3--3.
Page 43 PRIMUSr1000 Integrated Avionics System SG (Symbol Generator) Button -- This button selects between NORM or cross--side SG to supply the on--side displays. NOTE: When the cross side SG is selected, the PFD and MFD on both sides of the cockpit are identical since they are both driven by the cross--side SG.
Page 44 PRIMUSr1000 Integrated Avionics System Electronic Flight Instrument System (EFIS) INTRODUCTION The EFIS shown in figure 4--1, is a subsystem of the PRIMUS 1000 â Integrated Avionics System. The EFIS consists of the following components: Display Units (DU) Display Symbol Generators Part of the integrated avionics computer (IAC) Shared with engine instrument and crew alerting system (EICAS) for reversionary operation...
Page 45 PRIMUSr1000 Integrated Avionics System CRS 1 CRS 2 ASEL PUSH SYNC PUSH SYNC PUSH SYNC LOC HDG LOC HDG 5000 5000 KDVT KDVT 12.5 GSPD 12.5 GSPD 4500 4500 PLAB1 PLAB1 *PBD01 * PBD01 LL01 LL01 PLAB2 PLAB2 KDVT KDVT .410 M 200 RA 29.92 IN...
Page 46 PRIMUSr1000 Integrated Avionics System CONTROLS Primary Flight Display (PFD) Bezel Controller The PFD bezel controller shown in figure 4--2, is used to control various elements on the PFD. AD--50895@ PFD Bezel Controller Figure 4--2 IN/HPA Button -- The IN/HPA button is used to set the barometric altimeter correction in inches of mercury (inHg), or hectopascals (hPa).
Page 47 PRIMUSr1000 Integrated Avionics System Multifunction Display (MFD) Bezel Controller The MFD bezel controller is shown in figure 4--3. AD--51639@ MFD Bezel Controller Figure 4--3 The MFD bezel controller accesses several display menus and submenus. The selections from these menus are described later in this section., NOTE: When the SG reversionary switch selects the cross--side SG,...
Page 48 PRIMUSr1000 Integrated Avionics System An MFD menu operation tree is shown in figure 4--5. AD--50909--R1@ MFD Menu Tree Figure 4--5 A28--1146--112--00 Electronic Flight Instrument System (EFIS)
Page 49 PRIMUSr1000 Integrated Avionics System MFD MAIN MENU The main menu shown in figure 4--6, is the MFD power--up menu. Push the SYS MENU key on the main menu to select the MFD system menu shown in figure 4--7. AD--50897@ Main Menu Figure 4--6 SYSTEM MENU Pushing the SYS button from the main menu shown in figure 4--6,...
Page 50 PRIMUSr1000 Integrated Avionics System RTN (Return) Button -- This button returns the system menu to the main menu. If a system page is being displayed when the RTN button is pushed, the system page remains displayed. T/O (Takeoff) Button -- Pushing this button displays the takeoff system page.
Page 51 PRIMUSr1000 Integrated Avionics System ELECT (Electrical) Button -- This button selects the electrical system page for display on the MFD. When first pushed, the box around the previously selected system name, and its respective system page are removed, the menu label ELECT is boxed in white, and the electrical system page is displayed.
Page 52 PRIMUSr1000 Integrated Avionics System AD--51211@ MFD Main Menu (With FMS) Figure 4--10 RTN Button -- This button returns the menu to the main menu. SPDS (Speeds) Submenu -- Pushing the SPDS key on the MFD menu shown in figure 4--10, selects the V submenu shown in SPEEDS figure 4--11.
Page 53 PRIMUSr1000 Integrated Avionics System - VR BUTTON -- The VR button is used to select and set the rotation reference speed. When the button is pushed for the first time after power--up, the cyan dashes are replaced by the greater of 89 knots or the value of V1, if V1 has been previously set.
Page 54 PRIMUSr1000 Integrated Avionics System JSTK (Joystick) SUBMENU (option if FMS is installed) -- Pushing the joystick key on the MFD menu shown in figure 4--10, selects the joystick submenu shown in figure 4--12. AD--50903@ Joystick Submenu Figure 4--12 The joystick submenu buttons are used in conjunction with the remote joystick to control the designator on the MFD map or plan views.
Page 55 PRIMUSr1000 Integrated Avionics System - RCL (RECALL) BUTTON -- In the MAP mode, when the designator is not at its referenced waypoint, pushing the RCL button recalls the designator to that position. If the referenced waypoint was the aircraft, pushing RCL recalls the designator to the aircraft (i.e., present) position.
Page 56 PRIMUSr1000 Integrated Avionics System M/P RNG Knob -- The pilot uses the map/plan range knob to change the range scale when in the map or plan display mode. CHECKLIST MENU Pushing the CKLST button on the main menu (shown in figure 4--8), displays the checklist menu on the MFD, as shown in figure 4--13.
Page 57 PRIMUSr1000 Integrated Avionics System RTN Button -- Pushing this button, returns the bezel menu to the main menu. SKP Button -- Push this button to skip the checklist cursor to the next incomplete item on the current list. If the cursor is moved beyond the last item, the cursor moves to the beginning of the list and goes to the next incomplete item.
Page 58 PRIMUSr1000 Integrated Avionics System ENT Button -- Push the enter button to either select an item or to change a checklist item from incomplete to complete. After selection, the cursor moves to the next incomplete item in the current checklist. - ON AN INDEX PAGE -- Pushing the ENT button displays the checklist corresponding to the active index line selection.
Page 59 PRIMUSr1000 Integrated Avionics System AD--50906@ TCAS Selection from Main Menu Figure 4--14 WX (WEATHER) Pushing the WX key shown in figure 4--15, adds weather information to the MAP display. A second push of the button removes the weather information. WX on is annunciated by a white box. NOTES: 1.
Page 60 PRIMUSr1000 Integrated Avionics System MAP/PLAN Pushing the MAP PLAN button shown in figure 4--16, selects the MAP or PLAN MFD formats. Power--up default is MAP. Repeated pushes of the button cycles from MAP to PLAN and back. The selection is annunciated by a white box drawn around the selected display.
Page 61 PRIMUSr1000 Integrated Avionics System Display Controller (DC) The DC is used to select various features on the PFD. These include horizontal situation indicator (HSI) formats, navigation sources, weather display, and bearing pointer selection. The location of buttons and knobs is shown in figure 4--17. NAV 1 NAV 2 TEST...
Page 62 PRIMUSr1000 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 4--2. NAV 1 NAV 2 FMS is optional. NOTE: Navigation Bearing Pointers Table 4--2 RA (Radio Altitude) Knob/TEST Button -- These two concentric controls are used to set RA minimum altitude setting (outer knob), and to run the TEST function (inner button).
Page 63 PRIMUSr1000 Integrated Avionics System Guidance Controller Course and Heading Controls The course pointer and heading bug are controlled using the guidance controller course (CRS) and heading (HDG) knobs, shown in figure 4--18. The heading knob controls the heading bug on both sides of the cockpit (HSI/MFD).
Page 64 PRIMUSr1000 Integrated Avionics System EFIS Preflight Self--Test To run the EFIS self--test, push and hold the TEST button on the DC and verify the following: NOTES: 1. The EFIS test is only functional when the aircraft is on the ground. The test is functional at all times except during GS CAP/TRK.
Page 65 PRIMUSr1000 Integrated Avionics System - MIN is annunciated. MFD Display Test Results MAP symbols removed or replaced with dashes. SAT/TAS/TAT replaced with dashes. TCAS (option), checklist, weather displays are removed. CHK EICAS message is displayed. System pages digital displays and analog scales are invalid. EICAS Display Test Results Engine displays invalid Flaps and pitch trim invalid...
Page 66 PRIMUSr1000 Integrated Avionics System DISPLAYS Primary Flight Display (PFD) The PFD is an integrated display of attitude, navigation, and air data flight information. The PFD is divided into four functional groups shown in figure 4--19 and described below. MODE ANNUNCIATIONS AIRSPEED ALTITUDE DISPLAY...
Page 67 PRIMUSr1000 Integrated Avionics System Air Data Displays -- The PFD airspeed, altitude, and vertical speed displays receive inputs from the micro air data computer (MADC). Slip--Skid Display -- Standard slip--skid indications are displayed by the inclinometer on the PFD bezel control. PFD ATTITUDE DIRECTOR INDICATOR (ADI) See figure 4--20 for the location of the symbols and annunciations described below.
Page 68 PRIMUSr1000 Integrated Avionics System ADI and Annunciation Display Figure 4--20 A28--1146--112--00 Electronic Flight Instrument System (EFIS) 4-27/(4-28 blank)
Page 69 PRIMUSr1000 Integrated Avionics System Pitch Limit Indicator -- The pitch limit indicator symbol is displayed on the PFD attitude indicator sphere as shown in table 4--9. Margin to Stall Symbol Color Greater than 11° Symbol removed Between 11°and 6° Green Between 3°and 5°...
Page 70 PRIMUSr1000 Integrated Avionics System Vertical Deviation Scale -- The white vertical deviation scale appears on the right side of the attitude sphere. The navigation source for this scale is selected by the DC from any one of the following sources: ILS glideslope (green pointer) VNAV from the FMS (magenta pointer).
Page 71 PRIMUSr1000 Integrated Avionics System Low Altitude Awareness Display -- Low altitude awareness is displayed on the barometric altitude tape. At 550 feet AGL, a rising ground brown raster, topped with a yellow horizontal line, that represents 0 feet AGL, starts rising from the bottom of the altitude tape.
Page 72 PRIMUSr1000 Integrated Avionics System NOTES: 1. When the AHRS is in DG mode, the on--side heading source annunciations are DG1, DG2, respectively. 2. When the MAG heading is invalid, the source annunciation is an amber HDG1 or HDG2. Autopilot Status Annunciations -- Displays the engage status of the autopilot.
Page 73 PRIMUSr1000 Integrated Avionics System Radio Altitude (RA) Decision Height Annunciator -- When actual radio altitude decreases to within 100 feet of the set value, a box is placed in the lower right corner of the attitude sphere. When the actual radio altitude is equal to or less than the set value, and amber MIN is placed in the box and it flashes for 10 seconds.
Page 74 PRIMUSr1000 Integrated Avionics System Attitude Source Annunciation -- The attitude source, either AHRS 1 or AHRS 2, is selected using the switches on the reversionary control panel. These switches select the source for the attitude display on the PFD. This display is always amber and it indicates that the displayed attitude source is in reversion.
Page 75 PRIMUSr1000 Integrated Avionics System CAT 2 ANNUNCIATOR CAT2 4500 CAT 2 DEVIATION SCALE AND POINTER 200 RA .410 29.92 IN 359 CRS ILS1 13.1 NM 1000 VOR1 ADF2 5MIN AD--50915--R1@ PFD With CAT II Annunciations Figure 4--21 The green CAT2 mode annunciation is an indication that the conditions for a CAT2 approach are present and the excessive ILS deviation monitors are active on the PFD.
Page 76 PRIMUSr1000 Integrated Avionics System - IAS and baro altitude must be valid on both PFDs. - There are no SG, AHRS, or ADC reversions. - There are no comparison monitor annunciations - Two symbol generators must be operational. If these criterias are not met when the APR mode is selected, the system defaults out of CAT2 because it is programmed to assume that the pilot does not care to perform the ILS approach with the CAT2 monitors active.
Page 77 PRIMUSr1000 Integrated Avionics System FULL COMPASS DISPLAY The HSI annunciations on the PFD are shown in figure 4--22. Refer to the figure to see the location of the annunciations described. LOC HDG 4500 200 RA .410 29.92 IN 359 CRS ILS1 13.1 NM 1000...
Page 78 PRIMUSr1000 Integrated Avionics System Drift Angle Bug -- If available from the FMS, the drift angle bug with respect to the lubber line represents drift angle left or right of the desired track. The drift angle bug with respect to the compass card represents the actual track of the aircraft.
Page 79 PRIMUSr1000 Integrated Avionics System Groundspeed, Time--To--Go, Elapsed Time -- Depending on the relation with the DC, this display can be GSPD, TTG to the active waypoint, or ET. The range of values for each parameter are shown in table 4--10. Parameter Range GSPD...
Page 80 PRIMUSr1000 Integrated Avionics System Navigation Symbol Colors -- The color of the course pointer, distance display, groundspeed, lateral deviation, and navigation source annunciation is listed in table 4--11. On--Side Navigation Color Source Selected Short range navigation Green Magenta Same navigation source on both sides Yellow or secondary NAV source Navigation Symbol Colors...
Page 81 PRIMUSr1000 Integrated Avionics System ARC DISPLAY Most of the arc display annunciators, shown in figure 4--23 , are the same as that for full compass HSI display. The differences are described below. LNAV VNAV ASEL ADC2 14500 FMS HEADING 14000 (FHDG) ATT2 FMS STATUS...
Page 82 PRIMUSr1000 Integrated Avionics System NOTES: 1. The APP and TERM annunciators are related to FMS supplied approaches as described in table 4--12. 2. The INTEG annunciation indicates that the GPS sensor does not meet the required integrity calculations for the current phase of flight. 3.
Page 83 PRIMUSr1000 Integrated Avionics System Mode Annunciation R/TMode Annunciation Color R/T in warm--up WAIT Green REACT mode Green Ground Clutter Reduction P880 Green (Option) RCT and GCR Modes GR/R P880 Green (Option) Active Forced Standby FSBY Green Standby STBY Green Test Mode TEST Green Green...
Page 84 PRIMUSr1000 Integrated Avionics System Weather Radar TGT/VAR Annunciations -- When the weather radar supplies a target, a cyan TGT is displayed below the HSI. When the target is triggered, TGT turns amber. When variable radar gain is selected, TGT is replaced with VAR. Off Scale Arrows -- In the arc mode, the heading bug can be rotated off the compass scale.
Page 85 PRIMUSr1000 Integrated Avionics System AIRSPEED DISPLAY The airspeed section of the PFD is shown in figure 4--24. A description of airspeed annunciations is given below. AIRSPEED BUG DIGITAL DISPLAY Vmo/Mmo INDICATOR BAR AIRSPEED SET AIRSPEED TREND ROLLING AIRSPEED VECTOR DIGITAL DISPLAY AIRSPEED REFERENECE LINE IAS ANALOG SCALE...
Page 86 PRIMUSr1000 Integrated Avionics System When FLC is selected on the guidance controller, the FGC selects the preprogrammed values for a climb or descent. The preprogrammed value for climb is an airspeed, and for descent, a rate of descent. When in a climb, the cyan airspeed bug is placed at the pre--programmed airspeed value.
Page 87 PRIMUSr1000 Integrated Avionics System When the FGS enters the MAX SPEED mode, the annunciator MAX SPEED is displayed in amber to the left of the ADI. Takeoff V Display -- If the aircraft is on the ground V , and SPEED are displayed in digital tabular form inside the lower portion of the airspeed tape.
Page 88 PRIMUSr1000 Integrated Avionics System ALTIMETER DISPLAY The altimeter display is shown in figure 4--25. Refer to the figure for the location of annunciations described in the paragraphs that follow. ALTITUDE ALERT PRESELECT DISPLAY ALTITUDE SELECT 14500 ALTITUDE TREND VECTOR CURRENT ALTITUDE DIGITAL DISPLAY ALTITUDE REFERENCE LINE...
Page 89 PRIMUSr1000 Integrated Avionics System Altitude Alert Preselect Display -- This data is displayed at the top of the altitude scale. The data is set by the guidance controller altitude select knob. The set data is cyan. When the aircraft is within the altitude alert operating region, the box around the set data turns from white to amber.
Page 90 PRIMUSr1000 Integrated Avionics System Each 1000-- and 500--foot altitude increment is enhanced, respectively, with a double or single chevron shape. This shape, along with the shape of the altimeter reference line and altitude select bug, are designed to align when the selected and current altitudes are on an increment of 1000 or 500 feet.
Page 91 PRIMUSr1000 Integrated Avionics System VERTICAL SPEED (VS) DISPLAY The VS display is shown in figure 4--26. Refer to the figure for the location of annunciations described below. TCAS STATUS WHITE AMBER TCAS TEST TCAS TEST TCAS OFF TCAS OFF TA ONLY TA ONLY VERTICAL SPEED ANALOG...
Page 92 PRIMUSr1000 Integrated Avionics System TCAS II Resolution Advisory Display -- The TCAS II system displays a green “ fly to target”band and a red “ do--not--fly”band on the vertical speed display that commands the pilot to comply with a resolution advisory (RA) to avoid a potential aircraft conflict. Vertical Speed Digital Display -- A green digital display of the actual VS value is located on the zero reference line.
Page 93 PRIMUSr1000 Integrated Avionics System Typical PFD Presentations This section shows PFD presentations that the pilot can see during various flight phases. These examples do not show all display possibilities, they are intended to represent common presentations. TAKEOFF (TO) MODE The aircraft has started the takeoff roll, as shown in figure 4--27. TO and HDG modes have been selected.
Page 94 PRIMUSr1000 Integrated Avionics System CLIMB TO INITIAL ALTITUDE The aircraft is on climb, approaching 250 knots in HDG select and IAS hold modes, as shown in figure 4--28. The AP and YD are engaged. Altitude select is armed and the amber altitude preselect digits indicate that the aircraft is between 1000 and 250 feet from the 7000--foot selected altitude.
Page 95 PRIMUSr1000 Integrated Avionics System ENROUTE CRUISE The aircraft is in straight and level flight on a preselected altitude of 31,000 feet, flying HDG select and ALT hold with VOR armed for capture, as shown in figure 4--29. AP and YD are engaged. Airspeed is 220 knots, which is 0.70 Mach.
Page 96 PRIMUSr1000 Integrated Avionics System SETUP FOR APPROACH The aircraft is flying HDG select and vertical speed (VS) while armed for localizer (LOC) and glideslope (GS) capture, as shown in figure 4--30. The glideslope and localizer displays are in view. The amber ASEL digits and box indicate the aircraft is in excess of 1000 feet above the approach fix of 4000 feet.
Page 97 PRIMUSr1000 Integrated Avionics System TERMINAL AREA The aircraft is in the terminal area, flying the heading select mode with the LOC and GS armed. Altitude (ALT) hold is on, as shown in figure 4--31. A TCAS descent resolution advisory is displayed on the vertical speed scale.
Page 98 PRIMUSr1000 Integrated Avionics System APPROACH CAPTURE TRACKING AT RA MINIMUMS The aircraft is setup on final approach with LOC and GS captured, as shown in figure 4--32. The radio altitude of 100 feet is below the 200--foot minimum altitude, therefore the amber MIN is boxed. The rising brown in the altimeter is 100 feet away from the altitude reference line.
Page 99 PRIMUSr1000 Integrated Avionics System COMPARISON MONITORING The amber comparison monitor annunciators shown in figure 4--33, are in various locations on the PFD. Active messages are cleared when the miscompare situation has been corrected. Comparison monitor parameters are given in table 4--17. AD--50914--R1@ Comparison Monitor Annunciators Figure 4--33...
Page 100 PRIMUSr1000 Integrated Avionics System Parameter Monitored Tolerances Pitch (PIT) Attitude ±5_ Roll (ROL) Attitude ±6_ Attitude (ATT) Active only when both pitch and roll comparators are already tripped. Heading (HDG) ±6_ (level flight) Altitude (ALT) ±200 feet Airspeed (IAS) ±5 knots Localizer (LOC) deviation ±40 µA (»...
Page 101 PRIMUSr1000 Integrated Avionics System PFD Caution and Failure Display CAUTION (AMBER) ANNUNCIATIONS The PFD with caution and failure annunciations is shown in figure 4--34. AD--50928@ PFD With ARC HSI Display and Caution/Failure Annunciations Figure 4--34 Same Attitude Source -- If the pilot and copilot are using their normal attitude sources, there is no attitude source annunciated.
Page 102 PRIMUSr1000 Integrated Avionics System Course Select Failure -- Failure of the course select signals, replaces the display with amber dashes and removes the course pointer from the display. This indication is also given in the event of an invalid heading display or FMS source. Flight Director (FD) Failure -- In the event of a flight director failure, an amber FD FAIL is displayed in the lateral mode annunciation box, and the flight director mode annunciations and cue are removed.
Page 103 PRIMUSr1000 Integrated Avionics System AD--50929--R1@ PFD Caution Indications for Vertical and Course Deviation Figure 4--35 Autopilot Status Annunciations -- These annunciations display the engage status of the autopilot. The annunciation is displayed above and left of center of the attitude sphere. Refer to table 4--3 for annunciations and colors.
Page 104 PRIMUSr1000 Integrated Avionics System Yaw Damper Status Annunciation Display Type Color Engaged Steady Green Autopilot test AP TEST Steady Amber Normal YD disconnect 5 second flash Amber Abnormal YD 5 second Amber disconnect flash, then steady Yaw Damper Status Annunciations Table 4--18 TCAS Messages -- The TCAS status display is located to the left of the vertical speed scale.
Page 105 PRIMUSr1000 Integrated Avionics System FAILURE (RED) ANNUNCIATIONS PFD failure annunciations are shown in figure 4--36. Refer to the figure while reading the descriptions that follow. -- -- Failure Indications for ATT, MADC, HDG, CRS Select and FD Figure 4--36 Attitude Reference System Failure -- Failure of either the pitch or roll data is indicated by removing the pitch scale markings, turning the entire attitude sphere to cyan and displaying a red ATT FAIL in the top center of the attitude sphere.
Page 106 PRIMUSr1000 Integrated Avionics System Heading (HDG) Select Failure -- Failure of the heading select signals replaces the HDG display with amber dashes. The heading bug is removed from the display. This indication is also given in the event of an invalid heading display. EXCESSIVE ATTITUDE DECLUTTER The excessive attitude declutter display shown in figure 4--37, is decluttered when an unusual attitude condition is displayed.
Page 107 PRIMUSr1000 Integrated Avionics System Monitored Parameter Tolerance Bank angle Greater than ±65_ Pitch attitude up Greater than 30_ Pitch attitude down Greater than 20_ Excessive Attitude Declutter Parameters Table 4--20 The following items are removed from the display when the logic in table 4--20 has been satisfied: FD mode annunciations and command bars and couple arrow Marker beacons...
Page 108 PRIMUSr1000 Integrated Avionics System AD--50931--R1@ PFD Test Mode Figure 4--38 Multifunction Display (MFD) The MFD has two major format areas: MFD Map MFD Plan. In either of these formats, a window area can display any of the following selection: System Displays NOTE: One of several system displays is shown in the lower part of the MFD, but not when weather, TCAS, or the checklist...
Page 109 PRIMUSr1000 Integrated Avionics System Certain symbols are available with either display format. Some symbols are only available with specific display formats. The lower portion of the MFD is always reserved for displaying the display menu and submenu sections. NOTE: The symbols related to navigation are available on the MFD only if the optional FMS is installed.
Page 110 PRIMUSr1000 Integrated Avionics System Upper Left Area - FMS source annunciator - Active waypoint in magenta - Distance and time--to--go to active waypoint. Mid--Left Side - WIND VECTOR -- Wind vector shows the magnitude and direction of the wind, in green. - WEATHER (WX) RADAR MODE ANNUNCIATIONS -- All modes, except weather radar range, are annunciated in this area as described in table 4--21.
Page 111 PRIMUSr1000 Integrated Avionics System - AMBER FAIL ANNUNCIATION -- When the amber FAIL annunciation is displayed (optional PRIMUS 880 Weather Radar â System only), selecting the test mode displays the weather radar system fault code data in place of the tilt information. Refer to the PRIMUS 880 Weather Radar maintenance handbook for specific â...
Page 112 PRIMUSr1000 Integrated Avionics System MFD MAP DISPLAY MFD map displays are shown in figure 4--40 HEADING SOURCE ANNUNCIATION MAG 1/2 HEADING DIGITAL DG 1/2 (NOTE) REFERENCE HEADING HDG 1/2 LINE DISPLAY MAG1 --35 DRIFT BUG KDVT --25 12.5 HEADING SELECT BUG PLAB1 MID--RANGE *PBD01...
Page 113 PRIMUSr1000 Integrated Avionics System Heading Source Annunciations -- The heading source for this display is the same source that drives the on--side PFD. Cross--side data is displayed in amber. When the pilot and copilot horizontal situation indicator (HSI) heading sources are the same, they are annunciated in amber as is the heading source on the MFD.
Page 114 PRIMUSr1000 Integrated Avionics System NOTES: 1. If checklist is selected for display, the joystick cannot be used with the MAP designator. 2. The JSTK submenu can only be accessed if the optional FMS is installed. Navigation Symbols -- Both the map and plan MFD displays use common navigation symbols to describe flight plans.
Page 115 PRIMUSr1000 Integrated Avionics System MAP FAILURE AND WARNING DISPLAYS Map failure and warning displays are shown in figure 4--42. AD--50937--R1@ Map Failure/Warning Figure 4--42 EICAS Failure Message -- CHK EICAS is displayed to indicate that the EICAS wrap--around monitor has detected a difference between what EICAS is displayed and what the DAUs have sent to the EICAS for display.
Page 116 PRIMUSr1000 Integrated Avionics System Weather Radar Failure -- This failure is shown by displaying an amber FAIL in the weather radar mode annunciation box. NOTE: If the optional PRIMUS 880 Digital Weather Radar System is installed, when the amber FAIL annunciation is displayed, selecting the test mode causes the weather radar system fault codes to be displayed (in amber) in place of the digital tilt data.
Page 117 PRIMUSr1000 Integrated Avionics System 2900 AD--51826--R1@ Map Mode With Weather Figure 4--44 MFD PLAN MODE The plan mode shown in figure 4--45, is a north--up presentation of the active flight plan. The active waypoint is displayed in magenta at the center of the display.
Page 118 PRIMUSr1000 Integrated Avionics System FMS desired track lines. NOTE: Weather display is not available in the plan mode. MFD Plan View Figure 4--45 Aircraft Symbol -- The aircraft symbol moves on the display as a function of aircraft present position. The aircraft symbol is a visual cue to the actual aircraft position relative to true north and the active flight plan.
Page 119 PRIMUSr1000 Integrated Avionics System A bearing and distance display of the designator’ s position relative to its anchor waypoint is also displayed. PLAN MODE FAILURE AND WARNING DISPLAYS Plan mode caution and warning annunciations are shown in figure 4--46. Refer to the figure to find the location of failure and warning annunciations described below.
Page 120 PRIMUSr1000 Integrated Avionics System TYPICAL PLAN MODE PRESENTATION Figure 4--47 shows a typical plan mode display. AD--50941--R1@ Typical Plan Mode With Navaid Components and Flight Plan Figure 4--47 CHANGING A WAYPOINT Adding a waypoint is a routine operation on the MFD. Table 4--22 describes the procedure to change a waypoint.
Page 121 PRIMUSr1000 Integrated Avionics System Step Procedure Use the JSTK submenu from the MFD’ s MFD menu (and the external joystick) to move the designator to the location of the new waypoint, as shown in the display below. Use the ENT bezel button from the JSTK submenu to send the new waypoint designated position to the FMS control display unit.
Page 122 PRIMUSr1000 Integrated Avionics System MFD DISPLAY WINDOW The checklist and TCAS displays are shown on an MFD display window. When either the map or plan function is selected, the MFD’ s map or plan navigation displays are slightly repositioned toward the top of the MFD.
Page 123 PRIMUSr1000 Integrated Avionics System AD--50945--R2@ Typical Checklist Display Figure 4--48 Pushing the CKLST MFD bezel menu button, displays the master index. Normal, abnormal, or emergency indexes are selected from the master index. The normal checklists are arranged in the order of standard flight operations.
Page 124 PRIMUSr1000 Integrated Avionics System The SKP, LNBK, RCL, PAG, and ENT menu selections control the emergency checklist. The emergency checklist is used the same way as the NORM except for the action taken at the completion of a checklist. When the emergency checklist is completed, all checklist items are removed from the page and EMERGENCY PROCEDURE COMPLETE is written below the amber checklist title.
Page 125 PRIMUSr1000 Integrated Avionics System No Bearing Target Readout -- No bearing data when system has range but not bearing information. TCAS Range Ring -- The TCAS range ring is a white 60°arc with the aircraft symbol as its centerpoint. The digital value at the right end of the arc is the range in NM.
Page 126 PRIMUSr1000 Integrated Avionics System MFD System Displays The data acquisition units (DAU) collect all the information required for the system displays. This information is displayed in the lower third of the MFD and it is selected using the MFD bezel menu SYS button. NOTE: The last selected system display is shown on the MFD unless the TCAS or checklist display is selected.
Page 127 PRIMUSr1000 Integrated Avionics System ENGINE T/O STATUS ARROW ENGINE T/O DATA AIRCRAFT DOOR TEMPERATURE STATUS ENTRY ANTI--ICE STATUS ANNUNCIATION ENGINE OIL LEVEL AD--50947--R1@ Takeoff Display Figure 4--50 Aircraft Door Status -- The display in figure 4--50, also indicates the status of the aircraft doors. Closed doors are shown in green. An open door is indicated by a red DOOR OPEN message.
Page 128 PRIMUSr1000 Integrated Avionics System Takeoff Mode 1 Takeoff Mode 2 Annunciation T/O--1 ALT T/O--1 ALT T/O--2 ALT T/O--3 Engine T/O Mode Logic Table 4--23 Engine T/O Status Arrow -- This arrow moves up and down the three categories (T/O MODE, REF TO TEMP, and REF A--ICE) to indicate a valid status condition.
Page 129 PRIMUSr1000 Integrated Avionics System Cabin and Cockpit (CKPT) Temperature -- Current temperatures in each section is displayed in ° C and ranges from --54°to 54° C. Oxygen Pressure -- Oxygen pressure is displayed in pounds per square inch (PSI) and has color codes that are described in table 4--24.
Page 130 PRIMUSr1000 Integrated Avionics System FUEL SYSTEM The fuel system display shown in figure 4--52, displays summary information concerning the fuel supply. It gives the following information. AD--50949@ Fuel Page Figure 4--52 Tank Fuel Quantity -- Left and right tank fuel quantity is shown by an analog scale and pointer with a digital readout.
Page 131 PRIMUSr1000 Integrated Avionics System NOTES: 1. The pointer and digital readout have the same color as the scale. 2. When the fuel quantity enters the amber or red range, the digital display is boxed. The box flashes for the first five seconds. 3.
Page 132 PRIMUSr1000 Integrated Avionics System HYDRAULIC (HYD) SYSTEM The hydraulic system display shows the major elements of the hydraulic system that is shown in figure 4--53. The elements include: AD--50950@ Hydraulic (HYD) System Page Figure 4--53 HYD Pressure and Fluid Quantity -- The hydraulic pressure and fluid quantity limits for both systems are given in table 4--27.
Page 133 PRIMUSr1000 Integrated Avionics System Electric Hydraulic Pump Status -- The electric hydraulic pumps can be switched ON and OFF. The ON/OFF status is shown on the display. Brake Temperature -- Brake temperature is displayed on vertical analog scales that act as a monitor reference. The pointer and scale are green and remains green until the pointer enters the yellow region.
Page 134 PRIMUSr1000 Integrated Avionics System Bus Voltage and Amperage Loads -- A generator volts and amps display is normally shown in green for the following dc power sources: Generators 1 through 4 (GEN 1/2/3/4) Auxiliary power unit (APU) and ground power unit (GPU) DC Power Interconnect Buses -- The dc power interconnect buses are normally displayed in green.
Page 135 PRIMUSr1000 Integrated Avionics System System Display Failure Annunciation Failures (or invalid data) are shown on system displays by replacing digital data with dashes and remove the analog scale pointers. These can be seen when EFIS TEST button on the DC is pushed. DISPLAY SYSTEM REVERSIONARY MODES EFIS 1 (Pilot Normal) Failure -- A failure of SG 1 in DGC 1 (or its interface) shows itself in one of the following manners:...
Page 136 Either radio management unit (RMU) can be selected to display certain navigation data in an HSI arc format. The RMU operation is described in Honeywell Pub. No. A28--1146--050. This section details the use of the RMU for the standby navigation display role.
Page 137 PRIMUSr1000 Integrated Avionics System The standby navigation display shown in figure 4--55, displays a typical enroute VOR course with the ADF and VOR bearing pointers in view. AD--50953@ Standby Navigation Display (Typical) Figure 4--55 The paragraphs that follow detail specific symbols. Refer to figure 4--56 for an RMU backup navigation display.
Page 138 PRIMUSr1000 Integrated Avionics System MARKER BEACON AD--50954--R1@ RMU Backup Navigation Display Figure 4--56 ADF Bearing Pointer -- The bearing pointer, and its legend and digital position display are white. When the pointer (or its tail) is not in view, a double white arrow is displayed above the compass arc, on either the left or right side, indicating its location.
Page 139 PRIMUSr1000 Integrated Avionics System VOR Pointer Out of View Right/Left -- When the VOR pointer is out of the range displayed on the RMU ND, an arrow above the compass to either the right or left, shows the shortest direction to the VOR pointer.
Page 140 PRIMUSr1000 Integrated Avionics System Tune Box -- Items that are displayed in the tune box can be changed using the RMU TUNE knob. Selected Course -- The selected course in the tune box can be set using the RMU TUNE knob. Lateral Deviation Indicator -- The lateral deviation indicator is part of the course pointer.
Page 141 PRIMUSr1000 Integrated Avionics System AD--50955@ RMU Backup Navigation Display With Failures Figure 4--57 A28--1146--112--00 Electronic Flight Instrument System (EFIS) 4-101/(4-102 blank)
Page 142 PRIMUSr1000 Integrated Avionics System Engine Instrument and Crew Alerting System (EICAS) INTRODUCTION The EICAS shown in figure 5--1, is a part of the electronic display system. It has the following components: Electronic Display Unit (1) Display Symbol Generator Part of the Display Guidance Computer Shared with EFIS Data Acquisition Units (DAU) (2) EICAS Bezel Controller (1)
Page 143 PRIMUSr1000 Integrated Avionics System AD--50956--R1@ EICAS Block Diagram Figure 5--1 A28--1146--112--00 Engine Instrument and Crew Alerting System (EICAS) 5-3/(5-4 blank)
Page 144 PRIMUSr1000 Integrated Avionics System CONTROLS EICAS Bezel Controller The EICAS bezel controller is shown in figure 5--2. The rotary knob is used to scroll the amber and cyan CAS messages. AD--50957--R2@ EICAS Bezel Controller Figure 5--2 Master Warning and Caution Annunciation Switches The master caution and warning annunciation switches are located on the glare shield adjacent to the display controllers (DC).
Page 145 PRIMUSr1000 Integrated Avionics System DISPLAYS EICAS Display The engine instrument and caution advisory display is divided into five functional areas, as shown in figure 5--4. The areas include the following: Primary Engine Display Crew Alerting System Gear/Flaps/Spoiler Cabin Pressurization and Auxiliary Power Unit (APU) Status Pitch/Roll/Yaw Trim Display.
Page 146 PRIMUSr1000 Integrated Avionics System Primary Engine Displays The engine displays shown in figure 5--5, receive their information from two DAUs. The two DAUs are each dual channel and receive various aircraft engine and sensor data. One channel is primary, and both channels process the data in parallel.
Page 147 PRIMUSr1000 Integrated Avionics System Annunciations are as follows: Ignition (IGN) Thrust reverser display status Thrust rating mode Full authority digital engine control (FADEC) status Engine auxiliary power reserve (ATTCS). AD--50960@ EICAS Engine Instruments Display Figure 5--5 A28--1146--112--00 Engine Instrument and Crew Alerting System (EICAS)
Page 148 PRIMUSr1000 Integrated Avionics System FAN (N ) SPEED DISPLAY Analog Scale -- The fan arc is white. The ranges are listed in table 5--1. Lower Limit Upper Limit Color (%RPM) (%RPM) White 100.0 100.1 110.0 Analog Scale Table 5--1 When the analog pointer enters the red range, the normally white pointer and digital fan readout turn red.
Page 149 PRIMUSr1000 Integrated Avionics System Annunciation Meaning Continous Climb Cruise (To be determined) T/O--1 Takeoff Mode 1 T/O--2 Takeoff Mode 2 T/O--3 Takeoff Mode 3 ALT T/O--1 Alternate Takeoff Mode 1 ALT T/O--2 Alternate Takeoff Mode 2 ALT T/O--3 Alternate Takeoff Mode 3 R--MODE Reversion Mode NOTE: At the time of publication of this manual, not all FADEC modes were...
Page 150 PRIMUSr1000 Integrated Avionics System INTERSTAGE TURBINE TEMPERATURE (ITT) DISPLAY ITT Analog Scale -- The scale listed in table 5--3, is color banded, as to indicate normal and parameter exceedance ranges. Lower Upper Operating Condition Color Limit Limit All modes except White 0 _ C 921 _ C...
Page 151 PRIMUSr1000 Integrated Avionics System DIGITAL TURBINE (N ) DISPLAY This shows the speed of the engine turbine as a percentage of rotation speed. Refer to table 5--5 for the range of N Lower Limit Upper Limit Color (%RPM) (%RPM) Green 102.4 102.5 120.0...
Page 152 PRIMUSr1000 Integrated Avionics System Lower Limit Upper Limit Color (PSI) (PSI) Amber Green Amber Oil Pressure Limits for N >88% Table 5--7 FUEL FLOW (FF PPH FLOW) DIGITAL DISPLAY The white digits display a range of 0 to 4400 PPH with a resolution of 10 PPH.
Page 153 PRIMUSr1000 Integrated Avionics System OIL TEMPERATURE (OIL _ C) DISPLAY The digital display for oil temperature is displayed in _ C. Resolution is 1 _ C. Color coding of the digits is listed in table 5--8. Lower Limit Upper Limit Color (_ C) (_ C)
Page 154 PRIMUSr1000 Integrated Avionics System GEAR/FLAPS/SPOILER POSITIONS Landing Gear Position -- The landing gear position is indicated by annunciations in three boxes; left, nose and right. Table 5--10, defines the annunciations. Gear Position Annunciation Color White (note 1) Down Green (note 1) Transit Diagonal lines Amber...
Page 155 PRIMUSr1000 Integrated Avionics System Condition Color Logic Condition D Green --Flaps position is as selected NOTES: 1. When flap condition A or B exists, the flap position digital display is boxed in the same color. 2. Only 0° , 9°,22° , 33° , 45°are displayed if flap control units are valid (other positions are denoted by a dash (--)).
Page 156 PRIMUSr1000 Integrated Avionics System NOTES: 1. When the pitch trim is > +1° , UP is annunciated above the digital display. 2. When the pitch trim is < --1° , DN is annunciated above the digital display. 3. When pitch trim is < --1° , the minus (--) sign is removed.
Page 157 PRIMUSr1000 Integrated Avionics System CABIN PRESSURE AND AUXILIARY POWER UNIT (APU) STATUS Cabin pressurization and the APU status are displayed in the lower left corner of the EICAS. The annunciations are described below. Cabin Pressurization -- Cabin climb/descent rate is displayed in feet per minute (fpm).
Page 158 PRIMUSr1000 Integrated Avionics System Color Percentage of RPM Amber < 95 Green 96 -- 104 Amber 104 -- 110 111 < APU Turbine Speed as a Percentage of RPM Table 5--15 Color Percentage of RPM Green < 680 ° C Amber 681°C -- 717°C 718°C <...
Page 159 PRIMUSr1000 Integrated Avionics System Figure 5--6 shows a typical EICAS display. AD--50961--R1@ EICAS in the Takeoff Condition (Typical) Figure 5--6 PRIMARY ENGINE DISPLAYS FAILURE INDICATIONS Data Acquisition Unit (DAU) Failure -- A DAU failure is indicated on the primary engine display by removing the data pointers from all the arc displays on the failed side.
Page 160 PRIMUSr1000 Integrated Avionics System Engine Instrument Test -- If on the ground, when the No. 1 EFIS DC test button is pushed, the failure flags are shown. The test display is shown only as long as the TEST button is pushed. Figure 5--7 shows the gear/flaps/spoiler display, cabin pressurization and APU status display, and pitch/roll/yaw trim displays.
Page 161 PRIMUSr1000 Integrated Avionics System Crew Alerting System (CAS) The crew alerting system has the following characteristics: 15 message lines maximum 18 characters per line maximum One message status line CAS display declutter through the EICAS bezel rotary knob Master warning/caution button acknowledgement of messages CAS computed system messages.
Page 162 PRIMUSr1000 Integrated Avionics System The CAS display is in the upper right half of the EICAS display. The color convention and displayed priority for messages on the CAS display are defined in table 5--17. Color Message Warnings (top of the message stack) Amber Cautions (middle of the message stack) Advisories and status (bottom of the message...
Page 163 PRIMUSr1000 Integrated Avionics System APU FIRE D ENG 1 FIRE D AUTOPILOT FAIL ENG 2 FIRE D BAGG SMOKE ENG ATTCS FAIL BATT 1 OVTEMP D FUEL 1 LO LEVEL BATT 2 OVTEMP D FUEL 2 LO LEVEL BLD 1 LEAK GPWS D BLD 2 LEAK ICE COND -- A/I INOP D...
Page 164 PRIMUSr1000 Integrated Avionics System If there are amber messages already on the CAS display when a new amber message becomes active, the new message is put at the top of the amber message stack. If the existing amber or cyan messages are scrolled of the display, the amber and cyan message stacks are brought back on the CAS display with the new message displayed at the top of the amber stack.
Page 165 PRIMUSr1000 Integrated Avionics System E1 ATS SOV OPN IC 2 OVERHEAT E1 CTL A FAIL IC 2 WOW INOP E1 CTL B FAIL IC BUS FAIL E1 EXTBTL A INOP ICE DET 1 FAIL E1 EXTBTL B INOP ICE DET 2 FAIL E1 FIREDET FAIL ICE DETECTORS FAIL E1 FUEL LO PRESS...
Page 166 PRIMUSr1000 Integrated Avionics System COMPUTED CAUTION (AMBER) MESSAGES BLD 1/2 TEMP -- This message results from a combination of engine bleed air valve positions and high cooler outlet temperatures on No. 1 and No. 2 engines. ELEC EMER ABNORM -- This message is annunciated when the contacts for any of the four generators, the APU generator, or the GPU generator indicate they are closed but both the L and R essential contacts also indicate they are closed.
Page 167 PRIMUSr1000 Integrated Avionics System ADVISORY MESSAGES (CYAN) The cyan message flashes on the CAS display for 5 seconds, and then goes steady. No pilot interaction is required to acknowledge this type of message. If there are cyan messages already on the CAS display when a new cyan message becomes active, the new message is displayed at the top of the cyan message stack.
Page 168 PRIMUSr1000 Integrated Avionics System COMPUTED ADVISORY MESSAGES E 1--2 IDL STP FAIL -- This message indicates that the flight idle stop has failed regardless of whether the aircraft is on the ground or in the air. Message Inhibit -- During the takeoff and landing phases of flight, all red, amber, and cyan messages (except as noted in the respective message lists) are inhibited from being displayed.
Page 169 PRIMUSr1000 Integrated Avionics System AD--50964@ EICAS Invalid Display Formats Figure 5--9 EICAS Reversionary Modes LOSS OF THE DISPLAY UNIT Setting either pilot’ s reversionary control panel MFD knob to EICAS displays the EICAS on that side’ s MFD. LOSS OF DISPLAY GUIDANCE COMPUTER (DGC) SYMBOL GENERATOR This is indicated by a red X on the EICAS display unit.
Page 170 EICAS data in abbreviated format. Under some conditions, the No. 1 RMU can be automatically selected to display engine data. Normal operation of the RMU is described in Honeywell Pub. No. 28--1146--050. This section describes the use of the RMU for the backup EICAS display.
Page 171 PRIMUSr1000 Integrated Avionics System PAGE 1 Figure 5--10 shows page 1 of the EICAS display on the RMU. It displays this data: engine fan speed analog and digital display Digital display of: ITT -- interstage turbine temperature turbine speed FF PPH -- fuel flow in pounds/hr OIL P -- oil pressure OIL T -- oil temperature spoiler and flap positions.
Page 172 PRIMUSr1000 Integrated Avionics System PAGE 2 Figure 5--11 shows page 2 of the EICAS display on the RMU. It displays the following data: Digital display of: FQ LB -- fuel quantity in pounds FLAPS -- flap position Landing gear down and locked EICAS messages.
Page 173 PRIMUSr1000 Integrated Avionics System Backup EICAS Display Failure Indications See figure 5--12 for an illustration of the failure indications of the backup EICAS display. Failure of the RMU to display engine data is annunciated with ENGINE DATA UNAVAILABLE. data failure is shown with a red X and removal of the pointer. Digital data failure is shown by amber dashes.
Page 174 PRIMUSr1000 Integrated Avionics System Flight Guidance System (FGS) GUIDANCE CONTROLLER (GC) The GC shown in figure 6--1, is used to operate the functions listed below. CRS 1 CRS 2 ASEL PUSH SYNC PUSH SYNC PUSH SYNC AD--50968@ Guidance Controller Figure 6--1 Engages and disengages the autopilot and yaw damper.
Page 175 PRIMUSr1000 Integrated Avionics System AP Disengage -- Normally, the autopilot is disengaged by pushing the AP disconnect button located on the outboard side of each control wheel. The autopilot can also be disengaged by any one of the following: Pushing the AP or YD button on the GC Operating the pilot’...
Page 176 PRIMUSr1000 Integrated Avionics System Flight Director (FD) Mode Selection HDG (Heading) Button -- When the HDG button is pushed, the flight director computer is commanded to follow the inputs from the heading bug on the selected HSI. The command bars on the PFD are driven to follow the position of the heading bug.
Page 177 PRIMUSr1000 Integrated Avionics System FD1/FD2 Buttons -- The FD1/FD2 buttons are used to select and deselect the display of on--side flight director command bars as described in table 6--1. Condition Effect Effect Autopilot FD Command Bars AP disengaged Out of view (no FD modes selected) In view (both sides) Removes only the...
Page 178 PRIMUSr1000 Integrated Avionics System Remote Autopilot Switches and Annunciators Pitch Wheel and Turn Knob Controls -- Refer to the autopilot controller section (page 6--6), for a description of the PITCH wheel and TURN knob controls. AP Disconnect Switch -- The AP disconnect switch is mounted on the control wheel.
Page 179 PRIMUSr1000 Integrated Avionics System Message Description AP AIL MISTRIM Autopilot has detected the aileron out of trim. AP ELEV MISTRIM Autopilot has detected the elevator out of trim. AUTO TRIM FAIL Autopilot elevator trim has failed. AUTOPILOT FAIL The autopilot has failed. YAW DAMPER FAIL Autopilot has detected that the yaw damper has failed.
Page 180 PRIMUSr1000 Integrated Avionics System TURN Knob The TURN knob must be in detent (center position) before the autopilot can be engaged. Rotating the TURN knob out of detent commands a roll. The roll angle is proportional to and in the direction of TURN knob rotation.
Page 181 PRIMUSr1000 Integrated Avionics System System Limits GLOSSARY OF TERMS This section describes the flight guidance system (FGS) major functions that are referred to throughout Section VIII, Modes of Operation. These functions are listed alphabetically below: Attitude Director Indicator (ADI) Command Cue Glideslope (GS) Gain Programming as a Radio Altitude (RA) Function GS Gain Programming as a RA and Vertical Speed (VS) Function GS Capture (CAP)
Page 182 PRIMUSr1000 Integrated Avionics System Glideslope (GS) Gain Programming as a Radio Altitude (RA) Function Gain programming starts after the VBS trips. The gain is programmed as a function of RA. If the RA altimeter is invalid, gain programming occurs at GS capture and is controlled by a runway height estimator. The value estimated is a function of GS capture, GS track, and middle marker.
Page 183 PRIMUSr1000 Integrated Avionics System When the LBS trips, the flight director commands a turn toward the desired VOR radial or runway at the optimum point to capture the beam. If the intercept angle to the beam center is very shallow, the LBS does not trip until the aircraft is near beam center.
Page 184 PRIMUSr1000 Integrated Avionics System Vertical Beam Sensor (VBS) The VBS determines the point of glideslope capture using a number of inputs. The VBS is armed when the NAV radio is tuned to a LOC frequency, the LOC receiver is valid, and the LBS is tripped. The VBS trips as a function of VS, TAS, and glideslope deviation.
Page 185 PRIMUSr1000 Integrated Avionics System SYSTEM PERFORMANCE AND OPERATING LIMITS Table 7--1 lists the system performance limits for the aircraft. Table 7--2 defines the units of measure and their data range for this aircraft. Control or Mode Sensor Parameter Value Yaw Damper Yaw Engage Engage Limit No limit...
Page 186 PRIMUSr1000 Integrated Avionics System Control or Mode Sensor Parameter Value On Course VOR, Roll Angle Limit ±12_ VORAPR, or FMS (cont) Roll Rate Limit 1_ /sec Crosswind Correction Up to ±45_ Course Error in VOR, ±30_in VAPP Over Station Course Change Up to ±90_ Roll Angle Limit ±7_of Roll...
Page 187 PRIMUSr1000 Integrated Avionics System Control or Mode Sensor Parameter Value Pitch Sync TCS Switch on Pitch Attitude ±20_max. Wheel Command ALT Hold Micro Air Data ALT Hold Engage 0 to 37,000 ft Computer Range ALT Hold Engage ±20 ft Error Pitch Limit ±20_ Pitch Rate Limit...
Page 188 PRIMUSr1000 Integrated Avionics System Display Parameter Units Data Range Altitude Pressure Altitude feet --1000 to 60,000 Baro Corrected feet --1000 to 60,000 Altitude Altitude Rate ft/min. --20,000 to +20,000 Preselect Altitude feet 0 to 60,000 Baro Set inHg 22 to 32 Baro Set 745 to 1083.5 Airspeed/...
Page 189 PRIMUSr1000 Integrated Avionics System Modes of Operation HEADING (HDG) HOLD MODE, WINGS LEVEL The basic lateral mode of the autopilot is heading hold. The heading hold mode is defined as: Autopilot is engaged No lateral flight director mode is selected Bank angle is less than 6_ .
Page 190 PRIMUSr1000 Integrated Avionics System ROLL HOLD MODE The autopilot recognizes the roll hold mode as being operational when: No lateral flight director mode is selected, and The aircraft bank angle is greater than 6_ , but less than 35_ , and The autopilot is engaged.
Page 191 PRIMUSr1000 Integrated Avionics System HEADING SELECT MODE The heading select mode is used to maintain a magnetic heading. The desired heading is set using the HDG knob on the guidance controller (GC). The mode is selected with the HDG button on the GC and is annunciated on the HDG button and also by a green HDG on the top left side of the PFD.
Page 192 PRIMUSr1000 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 HSI. The navigation source displayed on the HSI is a function of the NAV source buttons located on the display controller (DC).
Page 193 PRIMUSr1000 Integrated Avionics System VOR Navigation Mode Radial Intercept View Figure 8--3 9500 AD--50970--R1@ VOR Navigation Mode Intercept PFD Figure 8--4 A28--1146--112--00 Modes of Operation...
Page 194 PRIMUSr1000 Integrated Avionics System When reaching the lateral beam sensor (LBS) trip point, as shown in figure 8--5, the system automatically drops the heading select mode and switches to the VOR capture phase. The following is displayed on the PFD (see figure 8--6): The white VOR annunciator extinguishes The green HDG annunciator extinguishes A green VOR is annunciated and is enclosed in a white box for 8...
Page 195 PRIMUSr1000 Integrated Avionics System AD--50973--R1@ VOR Navigation Mode Capture Figure 8--6 When the aircraft meets the VOR track conditions the course error signal is removed from the lateral steering command. This leaves radio deviation and DME gain programming (if available) to track the VOR signal and to compensate for beam standoff in the presence of a crosswind.
Page 196 PRIMUSr1000 Integrated Avionics System AD--50975--R1@ VOR Navigation Mode Tracking Figure 8--7 When the aircraft approaches a VOR station, it enters a zone of unstable radio signal, shown in figure 8--8. This zone of confusion radiates upward from the station in the shape of a truncated cone. In this area, the radio signal becomes highly erratic and it is best to remove it from the roll command.
Page 197 PRIMUSr1000 Integrated Avionics System ZONE OF CONFUSION A0SS1 A0SS2 AD--50976@ VOR Navigation Mode -- Tracking Over Station Figure 8--8 VOR APPROACH (VAPP) MODE A VOR approach procedure is described in table 8--2. The APR button annunciator on the GC is lit and VAPP is displayed in white on the PFD. The IAC applies gains appropriate for an approach.
Page 198 PRIMUSr1000 Integrated Avionics System Step Procedure Set the heading bug on the HSI to the intercept heading for the selected course. Push the APR button on the GC. VOR Approach Mode Engagement Procedure Table 8--2 FLIGHT MANAGEMENT SYSTEM (FMS) NAVIGATION MODE (OPTION) The FMS mode is flown when the pilot selects FMS on the DC.
Page 199 PRIMUSr1000 Integrated Avionics System Pushing the flight director NAV mode select button annunciates the FMS mode in green on the PFD as shown in figure 8--9. The flight control function of the IAC directs the aircraft to a desired track intercept.
Page 200 PRIMUSr1000 Integrated Avionics System LOCALIZER (LOC) MODE The localizer mode automatically intercepts, captures, and tracks the front course localizer beam to line up on the centerline of the runway in use. Before mode engagement, the pilot performs the procedure described in table 8--4. Step Procedure Couple either the pilot’...
Page 201 PRIMUSr1000 Integrated Avionics System --2000 AD--50980--R1@ Localizer Mode Arm Display Figure 8--10 With the aircraft approaching the selected course intercept, as shown in figure 8--11, the LBS monitors localizer beam deviation, beam rate, and TAS. At the computed time, the lateral beam sensor (LBS) trips and captures localizer signal.
Page 202 PRIMUSr1000 Integrated Avionics System Localizer Mode Capture Plan View Figure 8--11 NOTES: 1. When flying a localizer intercept, the optimum intercept angle is 45_ . 2. The pilot should not intercept the localizer at angles greater than 90_ . At angles greater than 90_ , the system automatically captures the back course.
Page 203 PRIMUSr1000 Integrated Avionics System Localizer Capture Display Figure 8--12 Lateral gain programming is required to adjust the gain applied to the localizer signal due to the aircraft approaching the localizer antenna, and beam convergence caused by the directional qualities of the antenna.
Page 204 PRIMUSr1000 Integrated Avionics System When the system acquires the localizer capture conditions, the course error signal is removed from the lateral calculations. This leaves localizer gain programming to track the localizer signal, as shown in figure 8--13, and to compensate for localizer beam standoff in the presence of a crosswind.
Page 205 PRIMUSr1000 Integrated Avionics System BACK COURSE (BC) MODE The BC mode automatically intercepts, captures, and tracks the back course localizer signal, as shown in figure 8--15. When flying a back course localizer approach, glideslope capture is automatically inhibited. The BC mode is set up and flown similar to a front course localizer approach.
Page 206 PRIMUSr1000 Integrated Avionics System Step Procedure Push the NAV button on the GC. With the aircraft outside the normal back course localizer capture limits, and more than 105_off the localizer front course heading, the PFD annunciates BC in white and HDG in green, as shown in the display below.
Page 207 PRIMUSr1000 Integrated Avionics System When the back course mode is selected by pushing the NAV button on the mode selector with ILS displayed on EFIS, and the selected course being more than 105_off the aircraft heading, logic in the IAC’ s flight control function establishes internal reverse polarity of the course error and localizer signals.
Page 208 PRIMUSr1000 Integrated Avionics System INSTRUMENT LANDING SYSTEM (ILS) APPROACH MODE The ILS approach mode automatically intercepts, captures, and tracks the front course localizer and glideslope signals, as shown in figure 8--17, so the pilot can fly a fully coupled ILS approach. The mode is set up and flown similar to the localizer mode.
Page 209 PRIMUSr1000 Integrated Avionics System Step Procedure Couple either the pilot’ s or copilot’ s flight director to the autopilot using the CPL switch on the GC. Tune the coupled side navigation receiver to the published ILS frequency for the runway in use. Push the NAV button on the coupled side DC to select ILS as the navigation source.
Page 210 PRIMUSr1000 Integrated Avionics System Step Procedure With the localizer captured, and outside the normal glideslope capture limits, the PFD annunciates, as shown in the display below. LOC in green GS in white --2000 AD--50991--R1@ ILS Approach Mode Procedure Table 8--6 The glideslope portion of the approach mode is used to automatically intercept, capture, and track the glideslope beam.
Page 211 PRIMUSr1000 Integrated Avionics System As the aircraft approaches the glideslope (GS) beam, as shown in figure 8--18, the vertical beam sensor (VBS) monitors TAS, vertical speed, and GS deviation to determine the correct capture point. At glideslope capture, the computer drops any other vertical mode that was in use, and automatically generates a pitch command to track the glideslope beam.
Page 212 PRIMUSr1000 Integrated Avionics System 1500 AD--50993--R1@ ILS Approach Mode Tracking PFD Figure 8--19 Gain programming is performed on the GS signal to compensate for the aircraft closing on the GS antenna and beam convergence caused by the directional properties of the antenna, as shown in figure 8--20. GS programming is normally a computed function of radio altitude (if available).
Page 213 PRIMUSr1000 Integrated Avionics System RADIO ALTITUDE BETWEEN 1200 AND 1500 FEET RADIO ALTITUDE BETWEEN 200 AND 300 FEET OUTER MIDDLE RUNWAY MARKER MARKER 4.0--7.0 MILES 3500 FEET AD--50992@ ILS Approach Mode Tracking, Profile View Figure 8--20 PITCH HOLD MODE The pitch hold mode is the basic autopilot and flight director vertical mode.
Page 214 PRIMUSr1000 Integrated Avionics System TAKEOFF MODE When the aircraft is on the ground, pushing the throttle--mounted go--around switch sets the PFD command bars to a fixed pitch up attitude of 12°. The vertical mode annunciation is a green TO, as shown in figure 8--21.
Page 215 PRIMUSr1000 Integrated Avionics System VERTICAL SPEED HOLD MODE The vertical speed (VS) hold mode is used to automatically maintain the aircraft at a pilot--selected vertical speed reference. To initiate the VS mode, the pilot can maneuver the aircraft to any climb or descent attitude, establish the vertical speed reference, and engage the VS mode.
Page 216 PRIMUSr1000 Integrated Avionics System ASEL 8500 7500 29.92 1000 VOR2 15.0 1000 VOR2 GSPD AD--50994--R3@ Vertical Speed Hold Mode PFD Figure 8--22 SPEED HOLD MODE The speed (SPD) hold mode is engaged by pushing the SPD button on the GC. The indicated airspeed (IAS)/Mach reference is synchronized to the IAS/Mach being flown when the mode is engaged.
Page 217 PRIMUSr1000 Integrated Avionics System The SPD mode is basically an airspeed mode, however, it differs from a standard IAS or Mach mode in the following ways: Although SPD mode (in the long term), tracks the reference airspeed, short--term emphasis is on vertical speed. This minimizes vertical speed excursions due to disturbances or large airspeed changes.
Page 218 PRIMUSr1000 Integrated Avionics System ASEL 8500 7500 29.85 VOR1 12.5 1500 VOR2 GSPD AD--50995--R3@ Speed Hold Mode PFD Figure 8--23 The pilot can maneuver the aircraft without disengaging the mode, by pushing and holding the TCS button on the control wheel. When TCS is released, the airspeed target is the current airspeed.
Page 219 PRIMUSr1000 Integrated Avionics System Step Procedure With the autopilot engaged, set the speed reference on the coupled side PFD to the reference IAS/Mach number, using the SPD knob. Advance throttle position to attain climb power. Speed Mode Engagement Procedure Table 8--7 The aircraft climbs toward the preselected altitude, maintaining the speed reference.
Page 220 PRIMUSr1000 Integrated Avionics System Preprogrammed Direction Altitude Values Descend All altitudes --2000 fpm 0--10,000 feet 240 knots 10,000 feet to 240 knots to 270 12,000 feet knots linearly Climb 12,000 feet to 270 knots 17,377 feet 17,377 feet to 0.56 Mach 37,000 feet Flight Level Change Descend and Climb Parameters Table 8--8...
Page 221 PRIMUSr1000 Integrated Avionics System levels off on the correct altitude, while the other vertical mode is used to fly to the desired altitude. The procedure to fly an ASEL mode is described in table 8--9. Step Procedure Set the desired altitude in the PFD altitude preselect window.
Page 222 PRIMUSr1000 Integrated Avionics System The ASEL mode automatically arms when the aircraft climbs or descends towards the alert altitude and the following conditions are met: ASEL altitude is more than 250 feet from the current altitude Computed vertical speed is greater that actual vertical speed Vertical speed is greater than 100 fpm for 3 seconds Glideslope is not captured.
Page 223 PRIMUSr1000 Integrated Avionics System 18,000 FEET PRESENT ALTITUDE 16,000 FEET FLARE SELECTED ALTITUDE 15,000 FEET AD--50996@ Altitude Preselect Plan View Figure 8--24 Step Procedure Set the selected altitude on the PFD. Engage the VS mode to descend toward the selected altitude. See display below.
Page 224 PRIMUSr1000 Integrated Avionics System Step Procedure The mode is armed, as shown in the display below. The altitude flare point (ASEL capture) is dependent on vertical speed, as shown in the display below. 15500 Altitude Preselect Mode Procedure Table 8--10 (cont) A28--1146--112--00 Modes of Operation 8-36...
Page 225 PRIMUSr1000 Integrated Avionics System Step Procedure ALT SEL capture is dropped and ALT HOLD is automatically engaged, as shown in the display below. .470 Altitude Preselect Mode Procedure Table 8--10 A28--1146--112--00 Modes of Operation 8-37...
Page 226 PRIMUSr1000 Integrated Avionics System ALTITUDE HOLD (ALT HOLD) MODE The altitude hold (ALT HOLD) mode is a vertical flight director mode used to maintain a barometric altitude reference. To fly ALT HOLD mode, follow the procedure in table 8--11. Step Procedure Put the aircraft into any lateral flight director mode.
Page 227 PRIMUSr1000 Integrated Avionics System Selecting the SG reversionary on the active side Coupling to the cross--side FD. The on--side AHRU or MADC become invalid. WINDSHEAR (WDSHEAR) MODE The windshear system uses a combination of detection and guidance. The windshear detection computer annunciates an amber or red WDSHEAR on the PFD for increasing performance or decreasing performance windshears, respectively.
Page 228 PRIMUSr1000 Integrated Avionics System The windshear mode is cancelled by one of the following events: Selecting any vertical mode on the GC Selecting GA below 2500ft without a WDSHEAR annunciation present Coupling to cross side PFD Selecting the SG reversionary on the active side. NOTES: 1.
Page 229 PRIMUSr1000 Integrated Avionics System GO--AROUND (GA) MODE (WINGS LEVEL) The GA mode is normally used to transition from a landing approach to a climb out condition in the event of a missed approach. The pilot selects GA mode by pushing the GA button located on either outboard throttle handle.
Page 230 PRIMUSr1000 Integrated Avionics System 1500 Go--Around Mode (Wings Level) PFD Figure 8--26 A28--1146--112--00 Modes of Operation 8-42...
Page 231 PRIMUSr1000 Integrated Avionics System Troubleshooting This section describes conditions associated with suspected malfunctions in the flight control system. Proper awareness helps the pilot make write--ups that convey the necessary information to maintenance personnel. As a result, unnecessary and expensive flight time to verify pilot squawks can be greatly reduced.
Page 232 PRIMUSr1000 Integrated Avionics System Rule 1 states that system conditions must be considered before the writeup is made. To aid in determining these conditions, the following type of questions must be answered. Are any flags in view or fault annunciators lit (obvious problems)? Is the problem in pitch, roll, or yaw axis or a combination thereof? Is the problem present in all modes or only under specific conditions such as:...
Page 233 PRIMUSr1000 Integrated Avionics System Commonly Used Terms Frequently, phrases or terms used in pilot writeups are not clearly understood by all persons concerned. Table 9--1 lists some of the most common terms and their definitions. Term Definition Autopilot Active Controls continually move in still air with small command errors.
Page 234 PRIMUSr1000 Integrated Avionics System Typical Problems Some of the typical problems associated with flight control systems are listed below. The list assumes the autopilot is engaged and is broken down into lateral mode problems, vertical mode problems, and problems that are common to both vertical and lateral modes. Illustrations that show the most common lateral and vertical mode problems are included.
Page 235 PRIMUSr1000 Integrated Avionics System AD--51002@ Lateral Mode Conditions and Problems Figure 9--1 (cont) A28--1146--112--00 Troubleshooting...
Page 236 PRIMUSr1000 Integrated Avionics System AD--51003@ Lateral Mode Conditions and Problems Figure 9--1 A28--1146--112--00 Troubleshooting...
Page 237 PRIMUSr1000 Integrated Avionics System VERTICAL MODE PROBLEMS Refer to table 9--3 and see figure 9--2 for an in--flight pattern graphic representation of vertical mode problems. Mode Problem Air data hold modes (ALT, VS, -- Oscillates IAS, MACH) -- Porpoising -- Does not hold reference Altitude preselect (ASEL) -- Misses capture -- Undershoots capture...
Page 238 PRIMUSr1000 Integrated Avionics System AD--51005--R1@ Vertical Mode Conditions and Problems Figure 9--2 A28--1146--112--00 Troubleshooting...
Page 239 PRIMUSr1000 Integrated Avionics System COMBINED VERTICAL AND LATERAL MODE PROBLEMS Refer to table 9--4 for 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 -- Autopilot does not follow commands -- Stick bump -- Stick buzz...
Page 240 PRIMUSr1000 Integrated Avionics System Step Procedure As each function is satisfactorily tested, the FAIL/INVD (fail/invalid) annunciator changes to PASS/VALD (pass/valid). NOTE: Air data sensor, accelerometer, and rate or turn sensor inputs are the only inputs tested during this test. All other tests are strictly internal IAC processing tests.
Page 241 PRIMUSr1000 Integrated Avionics System MULTIFUNCTION DISPLAY (MFD) CHECKLIST UPLOAD PROCEDURE The MFD checklist is stored in each display guidance computer. Table 9--6 is the procedure used to set up the aircraft to access checklists. Step Procedure The aircraft must be on the ground and powered up in standby.
Page 242 PRIMUSr1000 Integrated Avionics System Step Procedure Continue to hold the TEST knob for about 10 seconds and then release the knob. The page in step 6 remains on the PFD. Momentarily push the first (#1) button from the left on the EFIS DC.
Page 243 Try reprogramming the other IAC. If the other IAC takes the program, the problem is likely to be the IAC or aircraft wiring. Contact Honeywell Checklist Product Support that is given in the Electronic Programmable Checklist manual. Troubleshooting Procedure Table 9--7...
Page 244 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 245 PRIMUSr1000 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 CANADA -- OTTAWA 800--USA--SPEX 800--267--9947 (800--872--7739) ENGLAND -- BASINGSTOKE AUSTRALIA -- TULLAMARINE 44--256--51111 61--3--330--1411 FRANCE -- TOULOUSE...
Page 246 PRIMUSr1000 Integrated Avionics System United Kingdom Support France Support Center Center Honeywell Aerospace Ltd Honeywell Avionics Systems Ltd 1, Rue Marcel--Doret Edison Road, Ringway North 31700 TOULOUSE--BLAQNAC BASINGSTOKE, HANTS, FRANCE RG 21 2QD Telephone: 33--62--121500 ENGLAND After Hours -- AOG:...
Page 247 Additional copies of this manual can be obtained by contacting: Honeywell Inc. P.O. Box 29000 Business and Commuter Aviation Systems Phoenix, Arizona 85038--9000 Attention: Publication Distribution, Dept. M/S V19A1 Telephone No.: (602) 436--5553 FAX: (602) 436--1588 A28--1146--112--00 Honeywell Product Support 10-4...
Page 248 PRIMUSr1000 Integrated Avionics System 11. Abbreviations Abbreviations used in this manual are defined as follows: ABBREVIATION EQUIVALENT ABNORM Abnormal Above Air Data Computer Automatic Direction Finder Attitude Director Indicator Air Data System AFCS Automatic Flight Control System Above Ground Level AHRS Attitude and Heading Reference System AHRU...
Page 249 PRIMUSr1000 Integrated Avionics System ABBREVIATION EQUIVALENT Course Deviation Indicator Control Display Unit Check CKLST Checklist CKPT Cockpit Climb Closed Central Maintenance Computer Communication Continues Course Cruise Clockwise Data Acquisition Unit Display Controller Descend Directional Gyro Display Guidance Computer Degrade Dimming Data Loader Distance Measuring Equipment Down...
Page 250 PRIMUSr1000 Integrated Avionics System ABBREVIATION EQUIVALENT FADEC Full Authority Digital Engine Control Flight Director Fuel Flow Flight Guidance System FHDG FMS Heading Flight Level FLC, FLCH Flight Level Change Flight Management System FP, FPLN Flight Plan Feet Per Minute From FSBY, FSTBY Forced Standby Go--Around...
Page 251 PRIMUSr1000 Integrated Avionics System ABBREVIATION EQUIVALENT inHg Inches of Mercury INPH Interphone INTEG Integrity Interstage Turbine Temperature JSTK Joystick Kilogram Kilograms Per Hour LAT/LON Latitude/Longitude Lateral Beam Sensor LN BK Line Back Localizer Low Pressure Left/Right Low Speed Awareness MADC Micro Air Data Computer Magnetic MAINT...
Page 252 PRIMUSr1000 Integrated Avionics System ABBREVIATION EQUIVALENT Outer Marker Open Over Station Sensor Page PAST Pilot--Activated Self--Test Passenger Address Primary Flight Display POST Power--On Self--Test Pounds Per Hour PRESS Pressure Pounds per Square Inch Radio Altitude Recall Rain Echo Attenuation Compensation Technique Reference Radio Management Unit RNAV...
Page 253 PRIMUSr1000 Integrated Avionics System ABBREVIATION EQUIVALENT Storage, Store Stop SXTK Offset Sync Synchronize Traffic Advisory True Airspeed Total Air Temperature TCAS Traffic Alert and Collision Avoidance System Touch Control Steering TEMP Temperature TERM Terminal Target TKNB Turn Knob TO, T/O Takeoff Track Test...
Page 254 PRIMUSr1000 Integrated Avionics System Appendix A AHZ--800 Attitude and Heading Reference System (AHRS) INTRODUCTION The AHRS is a self--contained strapdown system that computes velocity, heading, and attitude data. It does not compute position information. The AHRS digital outputs the following: Primary attitude Magnetic heading Body linear accelerations...
Page 255 PRIMUSr1000 Integrated Avionics System TRUE AIRSPEED MADC AHRU INTEGRATED AVIONICS PITCH, ROLL, HEADING, COMPUTER FUNTIONS CONTROL NO. 1 MADC MAGNETIC NORTH LONG TERM STABILITY FLUX VALVE INTEGRATED AVIONICS COMPUTER FLUX VALVE COMPENSATION, NO. 2 INSTALLATION ORIENTATION MEMORY SERIAL MODULE WEIGHT--ON--WHEELS PITCH, ROLL P650 SHOP MAINTENANCE...
Page 256 PRIMUSr1000 Integrated Avionics System ATTITUDE AND HEADING REFERENCE UNIT The AHRU is the main electronics assembly of the AHRS. It contains an inertial sensor assembly that includes the fiber optic gyros and accelerometers. These measure accelerations and angular rates of the aircraft.
Page 257 PRIMUSr1000 Integrated Avionics System MAG/DG (Magnetic/Directional Gyro) Switch -- When the pilot inputs the MAG value, either a flux valve compensated heading, or DG only heading is displayed. NOTES: 1. If MAG is selected while in level flight, the AHRS instantly returns to flux valve slaving.
Page 258 PRIMUSr1000 Integrated Avionics System OPERATION Standard Operation The standard AHRS operating modes are the normal mode for attitude, and the MAG mode for heading. After the system is turned on, AHRS enters these modes automatically, if all system components and signals are valid. In the normal mode, true airspeed from the MADC is used to compensate for acceleration--induced error sources inherent to the vertical gyro system.
Page 259 PRIMUSr1000 Integrated Avionics System Reduced Performance Operation Two reduced performance modes are available: basic mode for attitude, and DG mode for heading. The basic mode is annunciated and entered automatically when true airspeed from the MADC becomes invalid. The basic mode is annunciated by lighting a white AHRS BASIC MODE message on the EICAS.
Page 260 PRIMUSr1000 Integrated Avionics System PILOT SELF--TEST After the AHRS is valid, the pilot can manually initiate AHRS test with the display controller (DC) TEST button. When the AHRS test is activated, the annunciations in table A--3 are displayed. The following parameters are also displayed: 5°pitch up attitude 45°roll attitude right wing down...
Page 261 PRIMUSr1000 Integrated Avionics System move from 115°to 0°. If the alignment is successful, the failure flags are removed and the AHRS is valid. If not, the 5--second cycle starts again. If the heading card stops and does not step to an indication of 0° , the initialization of the AHRS has not been completed correctly.
Page 262 PRIMUSr1000 Integrated Avionics System TAKEOFF IN DG MODE Takeoff with one AHRS in the DG mode is not recommended. Return the system to the normal slaved mode by setting the MAG/DG to MAG. NOTE: If a third heading source is available, it can be used as the primary data in place of the AHRS ,if slaved operation cannot be achieved.
Page 263 660 Weather Radar System that is installed in the Embraer 145. For complete operating instructions on the PRIMUS 660 Weather Radar System, 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 PROX- IMITY WARNING OR ANTICOLLISION PROTECTION.
Page 264 PRIMUSr1000 Integrated Avionics System 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). WEATHER RADAR CONTROLLER Controls and Indicators Controls and display features described below are numbered to match...
Page 265 PRIMUSr1000 Integrated Avionics System (RAIN ECHO ATTENUATION COMPENSATION TECHNIQUE) SWITCH The RCT switch is a toggle--contact switch that is used to select the RCT mode. The RCT circuitry compensates for attenuation of the radar signal as it passes through rainfall. The cyan field indicates areas where further compensation is not possible.
Page 266 PRIMUSr1000 Integrated Avionics System Selected Range Target Depth Target Range (NM) (NM) (NM) 5--155 10--160 25--150 50--150 100--175 200--250 300--350 FP (Flight Plan) 5--155 Target Alert Characteristics Table B--1 SECT (SECTOR) SWITCH The SECT switch is a toggle switch that selects either the normal 14 looks/minute 120°...
Page 267 PRIMUSr1000 Integrated Avionics System In the slaved conditions, both controllers must be off before the radar system turns off. MODE Switch The MODE switch is a rotary switch that is used to select one of the following functions: OFF -- Turns the radar system off. An amber WX is displayed in the MFD mode field.
Page 268 PRIMUSr1000 Integrated Avionics System Rainfall Rate (mm/hr)* Color 1--4 Green 4--12 Yellow 12--50 Greater than 50 Magenta * Millimeters per hour Rainfall Rate Color Cross Reference Table B--2 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.
Page 269 PRIMUSr1000 Integrated Avionics System FP (Flight Plan) -- In the FP position, the WX transmitter is placed in standby and the PFD or MFD map range has been selected up to 1000 NM. There is no radar data displayed in this mode. NOTE: When weather is not selected for display, the MFD has its own range control.
Page 270 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, that is referenced in Honeywell Pub. No. 28--1146--120. PRIMUS 660 Weather Radar System Precautions Table B--3 â...
Page 271 PRIMUSr1000 Integrated Avionics System POWERUP On powerup, 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 272 PRIMUSr1000 Integrated Avionics System AD--53423--R2@ MFD Display Weather Radar Test Pattern Figure B--3 â A28--1146--112--00 PRIMUS 660 Weather Radar System B--10...
Page 273 PRIMUSr1000 Integrated Avionics System TILT MANAGEMENT Figures B--4 and B--5 show the relationship between tilt angle, flight altitude, and selected range. The figures show the distance above and below aircraft altitude that is illuminated by the flat--plate radiator during level flight with 0_tilt and shows a representative low altitude situation, with antenna adjusted for 3.95_up--tilt.
Page 274 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 B--6 shows the MPEL for the 12--inch antenna and PRIMUS 660 Weather Radar power.
Page 275 A functional block diagram of the integrated radio system is shown in figure C--1. This appendix is a summary of the systems operation. Refer to Honeywell Pub. No. 28--1140--50 for a complete description of the PRIMUS II Radio System. â...
Page 276 PRIMUSr1000 Integrated Avionics System PRIMUS â II Radio System Interface Block Diagram Figure C--1 â A28--1146--112--00 PRIMUS II Radio System C--3/(C--4 blank)
Page 277 PRIMUSr1000 Integrated Avionics System SYSTEM DESCRIPTION General The PRIMUS II Radio System is comprised of the following cockpit Ò controls and remote radio units. Integrated Navigation Unit Integrated Communications Unit Audio Panel Radio Management Unit (RMU) Tuning Backup Control Head. Except for the audio panel, all data for these control functions are transmitted through a radio system bus.
Page 278 PRIMUSr1000 Integrated Avionics System Integrated Communication Unit The integrated communication unit, also known as the COM unit, is identical in concept to the integrated NAV unit. It contains internal modules that interface through a cluster module to the radio system bus for operation.
Page 279 PRIMUSr1000 Integrated Avionics System Tuning Backup Control Head The tuning backup control head is an additional backup system that controls the copilot’ s VOR receiver and communication transceiver. RADIO MANAGEMENT UNIT (RMU) OPERATION General The RMU is the central control unit for the radio system. Two RMUs are mounted on the center pedestal, forward of the engine throttle quadrants.
Page 280 PRIMUSr1000 Integrated Avionics System Controls See figure C--2 for the location of the controls and indicators described below. Radio Management Unit Controls Figure C--2 Transfer Key -- When pushed, the transfer keytoggles between the active frequency (top line) and the preset frequency (second line) of the window.
Page 281 PRIMUSr1000 Integrated Avionics System Function Keys - SQ (SQUELCH) KEY -- Pushing the SQ key opens the COM radio squelch and any noise or signal present in the radio can be heard in the audio system. The squelch button is strictly a toggle. The letters SQ are annunciated along the top line of the COM window when the squelch is opened.
Page 282 PRIMUSr1000 Integrated Avionics System Page Menu Figure C--3 - TST (TEST) KEY -- Pushing TST activates the internal self--test circuits for the component associated with the yellow cursors present position. The self--test is a complete end--to--end test of the function. Hold the TST button down for the duration of the test, about 2 seconds for COM transceiver, 5--to--7 seconds for DME, ATC, ADF, and about 20 seconds for NAV (VOR/ILS).
Page 283 PRIMUSr1000 Integrated Avionics System Memory Pages There are 12 memory locations associated with both the NAV and COM windows. In all cases, these two windows preset frequency memory functions work identically. Changing a preset NAV or COM frequency on the main tuning page, shown in figure C--4, is done by putting the yellow cursor over the frequency using the line select button, and changing the frequency with the tuning knobs.
Page 284 PRIMUSr1000 Integrated Avionics System CAUTION ALL SWITCHES POSITIONED ON THIS PAGE REMAIN IN THE SAME STATUS AFTER POWER DOWN. THE RADIO PRE- FLIGHT SHOULD INCLUDE THE RADIO ON--OFF PAGE TO EN- SURE THAT ALL MODULES ARE ON. A SWITCH LEFT OFF IS INDI- CATED BY DASHES IN THE CORRESPONDING FREQUENCY WINDOW ON THE MAIN PAGE, AND BY AN ERROR MESSAGE FOR THE TURNED--OFF MODULE DURING POWER--ON SELF--TEST.
Page 285 PRIMUSr1000 Integrated Avionics System VHF Communications Transceiver Operation The COM frequency select is in the upper left corner of the screen. The COM window has three lines, all associated with frequency. The top line displays the active frequency of the COM, while the second line displays either the memory frequency or a scratchpad frequency, depending on the last operation by the pilot.
Page 286 PRIMUSr1000 Integrated Avionics System AD--51019--R2@ RMU in COM Tuning Mode Figure C--6 Use the tuning knobs to set the frequency (i.e., 123.55, as shown in figure C--7). The TEMP--1 label indicates that the temporary frequency can be stored in MEMORY--1. AD--51021--R2@ RMU Tuning Figure C--7...
Page 287 PRIMUSr1000 Integrated Avionics System Push the top left COM transfer key, shown in figure C--8, to exchange the preset and active frequencies. If required, the 118.00 preset frequency can be changed to the next frequency, using the tuning knobs or by pushing the line select key to bring up the next frequency from memory.
Page 288 PRIMUSr1000 Integrated Avionics System Message Description When the microphone is stuck on for approximately MIC STK two (2) minutes, a beep sounds on the audio and an MIC STK is displayed until the MIC button is released. Ten seconds after the MIC STK annunciation is displayed, the selected transmitter automatically turns off.
Page 289 PRIMUSr1000 Integrated Avionics System Navigation Receiver Operation The NAV frequency select window is in the upper right corner of the main tuning page shown in figure C--10. The NAV window is identical to the COM in that it has two lines, each associated with frequencies. AD--51024--R2@ NAV Frequency Select Window Figure C--10...
Page 290 PRIMUSr1000 Integrated Avionics System The message AUX ON is displayed at the top of the NAV window when the NAV is being controlled by the tuning backup control head. The RMU is then locked out from control of that NAV. NOTE: Under certain circumstances, some integrated automatic flight...
Page 291 PRIMUSr1000 Integrated Avionics System DME HOLD DME hold is annunciated by splitting the NAV window, as shown in figure C--12. While in hold, the actual DME can be tuned independent of the active VOR or ILS. AD--51025--R2@ DME Hold Figure C--12 In normal VOR/ILS/DME operations, one of the six DME channels is paired with the active frequency and another with the preset frequency.
Page 292 PRIMUSr1000 Integrated Avionics System When the NAV window is split, an amber H (hold) is displayed in the lower (DME) window. The H indicates that the distance display (DME or TACAN) is not paired with the VOR/ILS navigation data. When the H is displayed, the other aircraft systems HOLD annunciators also light.
Page 293 PRIMUSr1000 Integrated Avionics System RMU ATC/TCAS Controls Figure C--13 The line select key opposite the ATC legend places the cursor over the transponder code to be changed. The large outer tuning knob controls the left two digits; the smaller inner knob controls the two right digits. Line Select Keys -- The first push of a line select key moves the yellow cursor to surround the data line associated with that line select key.
Page 294 PRIMUSr1000 Integrated Avionics System Transponder Select (1/2) Button -- When the cursor is located in the ATC window, this key is used to select the cross--side transponder. The transponder in operation is indicated by a 1 or 2 located in front of the selected mode. Since only one transponder can be operated at a time, the selected ATC transponder code is duplicated on each RMU.
Page 295 PRIMUSr1000 Integrated Avionics System Annunciation Extended Altitude Window Size 2700 feet above own aircraft and 2700 feet NORMAL below own aircraft 7000 feet above own aircraft and 2700 feet ABOVE below own aircraft 2700 feet above own aircraft and 7000 feet BELOW below own aircraft Extended Altitude Modes...
Page 296 PRIMUSr1000 Integrated Avionics System ATC FAILURE WARNINGS If the squitter function or the transmitter of the active Mode S Transponder fails in flight, a SQUITTR INOP warning message is displayed in red at the bottom of the ATC window. This message indicates that the selected TCAS compatible Mode S Transponder has lost some of its ability to operate as part of a collision avoidance system.
Page 297 PRIMUSr1000 Integrated Avionics System CONTROLS The following controls are used to operate the ADF. Refer to figure C--14 for control locations. ADF Controls Figure C--14 Frequency Select Key -- Push this key to place a cursor around the ADF frequency. The frequency can be changed using the large outer TUNE knob to control the left two digits, and the smaller inner TUNE knob to control the right two digits.
Page 298 PRIMUSr1000 Integrated Avionics System Annunciation Mode ADF adds a beat frequency oscillator for detection of cw signals. Maximum audio clarity and fidelity. No bearing VOICE determination. ADF Modes Table C--6 Part of a dual bandwidth design, the VOICE mode transmits high quality audio in the pilot headsets or cabin speakers.
Page 299 PRIMUSr1000 Integrated Avionics System 90°relative bearing position and removes ADF bearing needles from electronic flight instrument displays until HF transmission ceases. This avoids possible interference caused by bearing inaccuracy. SINGLE ADF INSTALLATION Single ADF installations operate the same as dual configurations except that the ADF window annunciator does not identify a side number.
Page 300 Then it will command each remote unit to perform its self--test. For more information on POST, refer to Honeywell Pub. No. 28--1140--50. In addition, each remote radio function has a pilot--activated self--test (PAST) that performs a very comprehensive check of the individual functions.
Page 301 PRIMUSr1000 Integrated Avionics System Sub--System Test Duration in Seconds 5 to 7 5 to 7 5 to 7 NAV (VOR/ILS) PAST Self--Test Approximate Durations Table C--7 After the test is complete, the green PASS or red ERR (Error) legend is displayed in the window. Releasing the test button at any time, immediately returns the function to normal operation.
Page 302 FAIL separately. Repeat for transponder 2. NOTES: 1. If a Honeywell TCAS is installed, it does not require that the TST button to be held to activate its test sequence. A momentary push starts TCAS (but only TCAS) testing. 2. With a Honeywell TCAS installed, it is possible to hold the TST button long enough (8 seconds), with other conditions in the right sequence, to force TCAS and the TCAS traffic display into the maintenance mode.
Page 303 PRIMUSr1000 Integrated Avionics System VOR/ILS/MARKER/DME PAST Refer to table C--10 for the VOR/ILS/marker/DME PAST procedures. NOTE: While in flight, this test may be inhibited by other aircraft systems (e.g., by autopilot while on approach tracking). Step Procedure Adjust the selected course for zero degree. Position cursor in NAV window.
Page 304 PRIMUSr1000 Integrated Avionics System ADF PAST Refer to table C--11 for the ADF PAST procedures. Step Procedure Position cursor in ADF window. Push and hold the TST button. The results are: ADF TEST message will appear on the RMU. ADF bearing pointer slews to 135_± 10_ . Audio tone is heard through the audio system.
Page 305 PRIMUSr1000 Integrated Avionics System AUDIO PANEL OPERATION General Two audio panels (figure C--15) are mounted on the aircraft instrument panel, outboard of the electronic display units. A third audio panel is mounted at the observers station. MASK Audio Panel Figure C--15 Controls The audio panel receives digitized audio from remote radio units, decodes the audio, controls the gain (volume) and routing of the various...
Page 306 PRIMUSr1000 Integrated Avionics System COM1, COM2, COM3, and HF Microphone Switches -- These switches are used to connect the on--side cockpit microphone to the selected transceiver. The received audio from the selected transceiver is routed to the on--side speaker or headphone at an internally preset level, regardless of the setting of the COM or HF audio source (on/off/volume) control located below the switches.
Page 307 PRIMUSr1000 Integrated Avionics System SPKR and HDPH Controls -- These controls are used to adjust the overall on--side speaker and headphone volume. They function in series with the individual audio source controls. S.T. Level Control -- The sidetone level control is used to prevent undesirable feedback of speaker sidetone audio into the transmitting microphone.
Page 308 PRIMUSr1000 Integrated Avionics System AD--51036--R2@ Tuning Backup Control Head Figure C--16 Normal Mode In the normal mode, the tuning backup control head can be used to control the co--pilot’ s COM 2 and NAV 2 frequencies. The frequencies selected by a crew member using the tuning backup control head are displayed on both the tuning backup control head and the No.
Page 309 PRIMUSr1000 Integrated Avionics System Controls and Annunciations The tuning backup control head controls and indicators shown in figure C--17, are described below. Tuning Backup Control Head Controls and Annunciations Figure C--17 Remote Tune Annunciator -- The remote tune annunciator is only active when the system is strapped for NAV only or COM only tuning.
Page 310 PRIMUSr1000 Integrated Avionics System Transmit (TX) Annunciator -- This annunciator indicates when the copilot’ s COM transmitter is transmitting. NAV AUDIO On/Off Switch -- This alternate action button is used to toggle NAV audio on or off to the audio panel in in the EMER mode.
Page 311 PRIMUSr1000 Integrated Avionics System Index Abbreviations, 11-1, 11-2 ADF operation, C--24 ADF operation with HF transmitters, C--26 Controls, C--25 ADF frequency STO button, C--26 ADF mode select key, C--25 Frequency select key, C--25 Frequency/mode select (TUNE) knobs, C--26 General, C--24 Single ADF installation, C--27 Air data system (ADS), 2-5 Altitude hold (ALT HOLD) mode, 8-37...
Page 312 PRIMUSr1000 Integrated Avionics System Index (cont) Operation, A--7 Reduced performance operation, A--8 Standard operation, A--7 Pilot self--test, A--9 Pilot initiated self--test annunciations, A--9 Power--up test, A--8 Pilot self--test annunciations, A--8 Audio panel, C--6 Audio panel operation, C--33 Controls, C--33 Audio source (COM, HF, NAV, ADF, and DME) controls, C--34 BOOM/MASK switch, C--34 COM1, COM2, COM3, and HF microphone switches, C--34...
Page 313 PRIMUSr1000 Integrated Avionics System Index (cont) VHF COM PAST, C--29 Procedure, C--29 VOR/ILS/marker/DME PAST, C--31 VOR/ILS/marker/DME PAST procedure, C--31 Cockpit mounted equipment, 1-2 Controls, 4-5, 5-5 Display controller (DC), 4-20 EFIS preflight self--test, 4-23 Self--test, 4-23 Instrument test, 4-24 Switching test, 4-24 EICAS bezel controller, 5-5 Guidance controller course and heading controls, 4-22 Multifunction display (MFD) bezel controller, 4-6...
Page 314 PRIMUSr1000 Integrated Avionics System Index (cont) Display controller (DC), 4-20 BRG (bearing) knobs, 4-21 ET (elapsed time) button, 4-20 FMS (flight management system) button (optional), 4-20 FULL/WX button, 4-20 GSPD/TTG (groundspeed/time--to--go) button, 4-20 NAV (navigation) button, 4-20 RA (radio altitude) knob/TEST button, 4-21 Displays, 4-25, 5-6 Backup EICAS display, 5-31 Backup EICAS display failure indications, 5-34...
Page 315 PRIMUSr1000 Integrated Avionics System Index (cont) PFD caution and failure display, 4-61 Caution (AMBER) annunciations, 4-61 Excessive attitude declutter, 4-66 Failure (RED) annunciations, 4-65 PFD test mode, 4-67 Primary engine displays, 5-7 Cabin pressure and auxiliary power unit (APU) status, 5-18 Digital turbine (N2) display, 5-12 Engine ignition (IGN) annunciation, 5-11 Engine vibration display, 5-14...
Page 316 PRIMUSr1000 Integrated Avionics System Index (cont) Electronic display system (EDS), 2--4, 3-1, 3-5, 3-6 Introduction, 3-1 MFD bezel controller basic operation, 3-5 Bezel controls, 3-5 Controller conventions, 3-6 Map range control, 3-6 Reversionary controllers and dimming panel, 3-7 Data acquisition unit (DAU) reversionary panel, 3-8 Dimming panel, 3-8 System reversionary panel, 3-7 Electronic flight instrument system (EFIS), 4-1, 4-5, 4-6...
Page 317 PRIMUSr1000 Integrated Avionics System Index (cont) Equipment Air data system, 2-5 Attitude and heading reference system, 2-6, A--1 Cockpit mounted, 1-2 Electronic display system, 2-4, 3--1 Flight guidance system (FGS), 2-3, 6--1 Flight management system, 2-9 Integrated radio system, 2-7 List, 1-2 Optional, 1-3 Optional list, 2-1...
Page 318 PRIMUSr1000 Integrated Avionics System Index (cont) GS capture (CAP), 7-2 GS gain programming as a RA and vertical speed (VS) function, Lateral beam sensor (LBS), 7-2 Lateral gain programming, 7-3 Localizer/back course (BC) track, 7-3 True airspeed (TAS) gain programming, 7-3 Vertical beam sensor (VBS), 7-4 VOR after over station sensor (AOSS), 7-4 VOR capture (CAP), 7-4...
Page 319 CRS sync, 4-22 HDG sync, 4-22 Heading hold mode, wings level, 8-1 Heading select mode, 8-3 Honeywell product support, 10-1, 10-2 Customer support centers -- North America, 10-2 Publication ordering information, 10-4 Support centers, 10-2, 10-3 24--hour exchange/rental support centers, 10-2...
Page 320 PRIMUSr1000 Integrated Avionics System Index (cont) Maximum permissible exposure level (MPEL), B--12 Memory pages, C--11 MFD bezel controller basic operation, 3-5 Bezel controls, 3-5 Momentary selection, 3-5 Parameter display selection, 3-5 Settable parameters, 3-5 Submenu selection, 3-5 Toggle selection, 3-5 Controller conventions, 3-6 Parameter selected for display, 3-6 Parameter selected for setting, 3-6...
Page 321 PRIMUSr1000 Integrated Avionics System Index (cont) Modes of operation, 8-1, 8-2 Altitude hold (ALT HOLD) mode, 8-37 Engagement procedure, 8-37 Altitude preselect (ASEL) mode, 8-32 Engagement procedure, 8-32 Mode procedure, 8-34 Back course (BC) mode, 8-17 Flight procedure, 8-17 Flight level change (FLC) mode, 8-31 Descend and climb parameters, 8-31 Flight management system (FMS) navigation mode (option), 8-10 Engagement procedure, 8-10...
Page 322 PRIMUSr1000 Integrated Avionics System Index (cont) Heading select bug, 4-73 Heading source annunciations, 4-73 Navigation symbols, 4-74 Pilot designator, 4-73 Range rings, 4-73 Map failure and warning displays, 4-75 EICAS failure message, 4-75 FMS failures, 4-76 Heading failure and flags, 4-75 MADC failures, 4-75 Weather radar failure, 4-76 MFD common symbols, 4-69...
Page 323 PRIMUSr1000 Integrated Avionics System Index (cont) M/P RNG button, 4-17 PAG (page) button, 4-16 RCL button, 4-16 RTN button, 4-16 SKP button, 4-16 M/P RNG (map/plan range) rotary knob, 4-6 Map/plan, 4-19 MENU INOP (inoperative), 4-6 Menu inop display, 4-6 MFD main menu, 4-8 MFD menu, 4-10 Joystick submenu, 4-13...
Page 324 PRIMUSr1000 Integrated Avionics System Index (cont) PFD caution and failure display, 4-61 Caution (amber) annunciations, 4-61 Autopilot status annunciations, 4-63 Common symbol generator, 4-61 Course deviation failure, 4-62 Course select failure, 4-62 Distance display failures, 4-62 Flight director (FD) failure, 4-62 Maximum/minimum speed (MAX/MIN SPD), 4-64 Radio altimeter failure, 4-62 Same air data source, 4-61...
Page 325 PRIMUSr1000 Integrated Avionics System Index (cont) Primary engine displays, 5-7 Cabin pressure and auxiliary power unit (APU) status, 5-18 APU exhaust temperature, 5-19 APU status, 5-18 APU turbine speed as a percentage of RPM, 5-19 Cabin pressurization, 5-18 Color differential pressure display, 5-18 Digital turbine (N2) display, 5-12 Engine ignition (IGN) annunciation, 5-11 Ignitor annunciation color definition, 5-11...
Page 326 PRIMUSr1000 Integrated Avionics System Index (cont) Primary flight display (PFD) bezel controller, 4-5 Airspeed display, 4-45 Airspeed rolling digit display, 4-47 Airspeed trend vector, 4-46 Airspeed/mach reference bug and display, 4-45 Indicated Airspeed (IAS) analog scale, 4-46 Indicated airspeed comparison monitor, 4-47 Low speed awareness (LSA), 4-47 Mach display, 4-47 Takeoff Vspeed display, 4-47...
Page 327 PRIMUSr1000 Integrated Avionics System Index (cont) NAV course deviation indicator (CDI) with TO/FROM indication, 4-40 NAV source distance, 4-40 Navigation (NAV) source annunciations, 4-37 Navigation symbol colors, 4-40 Wind vector (available if FMS is installed), 4-40 Functional divisions, 4-25 ADI (attitude director indicator) display, 4-25 Air Data displays, 4-26 HSI (horizontal situation indicator) display, 4-25 Mode annunciations, 4-25...
Page 328 PRIMUSr1000 Integrated Avionics System Index (cont) Yaw damper annunciations, 4-26 STD (standard) button, 4-5 Vertical speed (VS) display, 4-51 Flight director VS target display and bug, 4-51 TCAS II resolution advisory display, 4-52 TCAS status message, 4-52 Vertical speed analog scale, 4-52 Vertical speed digital display, 4-52 PRIMUS 660 Weather Radar System, 2-6, B--1, B--2...
Page 329 PRIMUSr1000 Integrated Avionics System Index (cont) Integrated navigation unit, C--5 Radio management unit (RMU), C--6 Tuning backup control head, C--7 Tuning backup control head operation, C--35 Controls and annunciations, C--37 Emergency mode, C--36 General, C--35 Normal mode, C--36 Procedures ADF PAST procedure, C--32 Altitude hold mode engagement procedure, 8-37 Altitude preselect mode engagement procedure, 8-32 Altitude preselect mode procedure, 8-34...
Page 330 PRIMUSr1000 Integrated Avionics System Index (cont) Controls and annunciations, C--20 General, C--20 Built--in--test (BIT), C--28 ADF PAST, C--32 ATC transponder and TCAS PAST, C--30 General, C--28 Pilot--activated self--test (PAST), C--28 VHF COM past, C--29 VOR/ILS/marker/DME PAST, C--31 Cross--side operation, C--27 General, C--7 Maintenance, C--32 Memory pages, C--11...
Page 331 PRIMUSr1000 Integrated Avionics System Index (cont) SG (symbol generator) button, 3-8 Reversionary modes, EICAS, 5-30 Loss of display guidance computer (DGC) symbol generator, 5-30 Loss of the display unit, 5-30 Roll hold mode, 8-2 Speed hold mode, 8-28 Engagement procedure, 8-30 Standby navigation display, 4-96 RMU backup navigation display, 4-98 ADF bearing pointer, 4-98...
Page 332 PRIMUSr1000 Integrated Avionics System Index (cont) Flight management system (FMS) (Option), 2-9 Other switches and controls, 2-9 AP (autopilot) disconnect switch, 2-9 External AHRS switches, 2-9 GA (go--around) button, 2-9 Joystick (option), 2-10 Master warning/master caution switches, 2-10 N2 override switch, 2-10 TCS (touch control steering) button, 2-9 PRIMUS 660 Weather Radar System, 2-6, B--1...
Page 333 PRIMUSr1000 Integrated Avionics System Index (cont) TakeOff mode, 8-26 Vertical speed hold mode, 8-27 Tilt management Radar beam illumination high altitude -- 12--inch radiator, B--11 Radar beam illumination low altitude --12--inch radiator, B--11 Traffic alert and collision avoidance system (TCAS), 2-8 Troubleshooting, 9-1, 9-2 Ground maintenance test, 9-9 Test procedure, 9-9...
Page 334 PRIMUSr1000 Integrated Avionics System Index (cont) Setup for approach, 4-56 Takeoff (TO) mode, 4-53 Terminal area, 4-57 Vertical speed hold mode, 8-27 VHF communications transceiver operation, C--13 Basic COM tuning, C--13 COM messages, C--15 VOR approach (VAPP) mode, 8-9 Engagement procedure, 8-9 VOR navigation (NAV) mode, 8-4 Engagement Procedure, 8-4 Weather radar controller, B--2...

Honeywell PRIMUS 1000 Pilot's Manual

1 Introduction

2 System Description

3 Electronic Display System (Eds)

4 Electronic Flight Instrument System

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Summary of Contents for Honeywell PRIMUS 1000

Honeywell PRIMUS 1000 Pilot's Manual

1 Introduction

2 System Description

3 Electronic Display System (Eds)

4 Electronic Flight Instrument System

Quick Links

Related Manuals for Honeywell PRIMUS 1000

Summary of Contents for Honeywell PRIMUS 1000

Table of Contents