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HighlightsPage 1 of 3
September 2002
HoneywellAerospace Electronic SystemsCESPhoenixP.O. Box 21111Phoenix, Arizona 850361111U.S.A.
TO: HOLDERS OF THE PRIMUS 1000 INTEGRATEDAVIONICS SYSTEM WITH INTEGRAL FMS FOR THECITATION EXCEL PILOTS MANUAL, HONEYWELL PUB.NO. A281146137
REVISION NO. 2 DATED SEPTEMBER 2002
HIGHLIGHTS
Pages that have been revised are outlined below. Remove and insertthe affected pages listed. The revision number has been added to thebottom of the revised pages and revision bars have been used toindicate the revised or added text. Insert this highlights letter in themanual in your possession ahead of page RR-1/RR-2, Record ofRevisions. The List of Effective Pages shows the order in which to insertthe attached new pages of front material into your manual.
Page No. Description of ChangeTitle Pages Revised to reflect Revision 2.
RR1/RR2 Revised to reflect Revision 2.
LEP1 thruLEP4
Revised to reflect Revision 2.
TC1, TC4thru TC6,TC9
Updated titles.
11 Added new part numbers for the PFD BezelController and Display Controller in Table 11.
17 thru 110 Added new Product Support Section. No revisionbars added.
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HighlightsPage 2 of 3
September 2002
Page No. Description of Change
211/212 Corrected Figure 21: changed aileron servo torudder servo.
35 thru 37 Revised Figure 32 to reflect new PFD BezelController. Added bullets to reflect RD/BARObutton and MINIMUMS knob on the new PFDbezel. Some text shifted.
316, 317 Revised Figure 314 to reflect new DisplayController and causing text to shift.
318, 319 Added note to reflect change to RA knob. Addedbullet to reflect new PUSH TEST button andcausing text to shift.
331 Revised Figure 320 to reflect newBARO/RADIO minimums annunciations andmove CAT II annunciation.
333 Changed lower limit of RA from 85 to 50 feet onDC and valid indication on PFD from 80 to 100.
334 Revised Figure 321 to reflect change andupdated figure title.
341 Revised Figure 323 to reflect changes.347 Updated table titles.361 Revised Figure 327 to reflect new BARO
Minimums bug; added color.365 Added bullet to reflect new BARO minumums
bug.377 Added bullets to reflect radio altitude and ILS.387 Revised Figure 342; added color.398 Updated figure title.64 Revised Figure 63.66 Revised Figure 65.68 Revised Figure 67.610 Revised Figure 69.613 Revised Figure 611.616 Revised Figure 612.
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HighlightsPage 3 of 3
September 2002
Page No. Description of Change618 Revised Figure 614.619 Revised Figure 616.621 Revised Figure 618.648 Revised Figure 636.651 Revised Figure 639.653 Revised Figure 641.729, 730 Updated titles.Index1 thruIndex12
Revised to reflect Revision 2.
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Printed in U.S.A. Pub. No. A28114613702 November 1999Revised September 2002
HoneywellAerospace Electronic SystemsCESPhoenixP.O. Box 21111Phoenix, Arizona 850361111U.S.A.
PRIMUS 1000 IntegratedAvionics System with Integral
FMS
for theCitation Excel
Pilots Manual
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ASSOCIATEMEMBER
Member of GAMA
General AviationManufacturers Association
E
PRIMUS is a U.S. registered trademark of Honeywell.
2002 Honeywell
PROPRIETARY NOTICE
This document and the information disclosed herein are proprietarydata of Honeywell. Neither this document nor the information containedherein shall be used, reproduced, or disclosed to others without thewritten authorization of Honeywell, except to the extent required forinstallation or maintenance of recipients equipment.
NOTICE FREEDOM OF INFORMATION ACT (5 USC 552) ANDDISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY(18 USC 1905)This document is being furnished in confidence by Honeywell. Theinformation disclosed herein falls within exemption (b) (4) of 5 USC 552and the prohibitions of 18 USC 1905.
All rights reserved. No Part of this book, CD, or PDF may be reproducedor transmitted in any form or by any means, electronic or mechanical,including photocopying, recording, or by any information storage andretrieval system, without the written permission of HoneywellInternational, except where a contractual arrangement exists betweenthe customer and Honeywell.
S2002
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PRIMUS 1000 Integrated Avionics System with Integral FMS
Record of RevisionsA281146137Rev 2 Sep 2002 RR1/(RR2 blank)
Record of Revisions
Upon receipt of a revision, insert the latest revised pages and disposeof superseded pages. Enter revision number and date, insertion date,and the incorporators initials on this Record of Revisions. The typedinitial H is used when Honeywell is the incorporator of the revision.
RevisionNumber
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1 Sep 2000 Sep 2000 H
2 Sep 2002 Sep 2002 H
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PRIMUS 1000 Integrated Avionics System with Integral FMS
A281146137Rev 2 Sep 2002
Table of ContentsTC1
Table of Contents
Section Page
1. INTRODUCTION 1-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . PRIMUS 1000 Integrated Avionics System 1-1. . . . . Honeywell Product Support 1-7. . . . . . . . . . . . . . . . . . . . Publication Ordering Information 1-10. . . . . . . . . . . . . . .
2. SYSTEM DESCRIPTION 2-1. . . . . . . . . . . . . . . . . . . . . General 2-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Electronic Flight Instrument System (EFIS) 2-4. . . . . . Flight Guidance System (FGS) 2-6. . . . . . . . . . . . . . . . . Air Data System (ADS) 2-7. . . . . . . . . . . . . . . . . . . . . . . PRIMUS 880 Digital Weather Radar System 2-7. . . Attitude and Heading Reference System (AHRS) 2-8. Flight Management System (FMS) 2-8. . . . . . . . . . . . . Traffic Alert and Collision Avoidance System
(TCAS) (Optional) 2-8. . . . . . . . . . . . . . . . . . . . . . . . . . Enhanced Ground Proximity Warning System
(EGPWS) (Optional) 2-8. . . . . . . . . . . . . . . . . . . . . . . . Lightning Sensor System (LSS) (Optional) 2-8. . . . . . . Other Switches and Controls 2-9. . . . . . . . . . . . . . . . . . .
3. ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) 3-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
General 3-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Controllers 3-5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Primary Flight Display (PFD) Bezel Controller 3-5. . . Multifunction Display (MFD) Bezel Controller 3-6. . Display Controller (DC) 3-16. . . . . . . . . . . . . . . . . . . . . Remote Instrument Controller 3-20. . . . . . . . . . . . . . . Multifunction Display (MFD) Controller 3-21. . . . . . . EFIS Reversionary Functions 3-26. . . . . . . . . . . . . . .
Primary Flight Display (PFD) 3-28. . . . . . . . . . . . . . . . . . . Attitude Director Indicator (ADI) Displays and
Annunciators 3-30. . . . . . . . . . . . . . . . . . . . . . . . . . . . Horizontal Situation Indicator (HSI) Displays
and Annunciators 3-43. . . . . . . . . . . . . . . . . . . . . . . . Airspeed Display 3-57. . . . . . . . . . . . . . . . . . . . . . . . . . Altimeter Display 3-61. . . . . . . . . . . . . . . . . . . . . . . . . . Vertical Speed (VS) Display 3-66. . . . . . . . . . . . . . . . . Traffic Alert and Collision Avoidance System
(TCAS) (Optional) 3-68. . . . . . . . . . . . . . . . . . . . . . . .
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3. ELECTRONIC FLIGHT INSTRUMENT SYSTEM (CONT)
Enhanced Ground Proximity Warning System(EGPWS) (Optional) 3-70. . . . . . . . . . . . . . . . . . . . .
Typical PFD Presentations 3-71. . . . . . . . . . . . . . . . . .PFD Caution and Failure Displays 3-80. . . . . . . . . . .PFD Test Mode 3-83. . . . . . . . . . . . . . . . . . . . . . . . . . .
Multifunction Display (MFD) 3-84. . . . . . . . . . . . . . . . . . .MFD Common Symbols 3-85. . . . . . . . . . . . . . . . . . . .MFD Map View 3-92. . . . . . . . . . . . . . . . . . . . . . . . . . .Weather Display in MFD Map View 3-95. . . . . . . . . .MFD Plan View 3-97. . . . . . . . . . . . . . . . . . . . . . . . . . .Checklist Display 3-99. . . . . . . . . . . . . . . . . . . . . . . . . .Traffic Alert and Collision Avoidance System(TCAS) Display (Optional) 3-101. . . . . . . . . . . . . . . . .
Enhanced Ground Proximity Warning System(EGPWS) Display (Optional) 3-107. . . . . . . . . . . . . .
MFD Failure and Warning Displays 3-112. . . . . . . . . .Display System Reversionary Modes 3-116. . . . . . . . . . .
EFIS Reversionary Modes 3-116. . . . . . . . . . . . . . . . . .Display Controller Failures 3-116. . . . . . . . . . . . . . . . . .
Display Color Coding Convention 3-117. . . . . . . . . . . . . . .
4. FLIGHT GUIDANCE SYSTEM (FGS) 4-1. . . . . . . . . . .
General 4-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Mode Selector 4-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Autopilot Controller 4-3. . . . . . . . . . . . . . . . . . . . . . . . . . .Remote Switches and Annunciators 4-5. . . . . . . . . . . .
Switches 4-5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Annunciators 4-5. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5. SYSTEM LIMITS 5-1. . . . . . . . . . . . . . . . . . . . . . . . . . . .
Attitude Director Indicator (ADI) Command Cue 5-1. .Glideslope Capture 5-1. . . . . . . . . . . . . . . . . . . . . . . . . . .Glideslope Gain Programming 5-1. . . . . . . . . . . . . . . . .Lateral Beam Sensor (LBS) 5-2. . . . . . . . . . . . . . . . . . . .Localizer Capture 5-2. . . . . . . . . . . . . . . . . . . . . . . . . . . .Localizer Gain Programming (LOC II) 5-2. . . . . . . . . . .Navigation on Course (NOC) 5-3. . . . . . . . . . . . . . . . . .True Airspeed (TAS) Gain Programming 5-3. . . . . . . . .Vertical Beam Sensor (VBS) 5-3. . . . . . . . . . . . . . . . . . .VOR Capture 5-4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VOR Over Station Sensor (OSS) 5-4. . . . . . . . . . . . . . .
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VOR After Over Station Sensor (AOSS) 5-4. . . . . . . . .System Performance and Operating Limits 5-5. . . . . .
6. MODES OF OPERATION 6-1. . . . . . . . . . . . . . . . . . . . .
Lateral Modes 6-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Heading Hold, Wings Level 6-1. . . . . . . . . . . . . . . . .Roll Hold 6-2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Heading Select 6-3. . . . . . . . . . . . . . . . . . . . . . . . . . . .VOR Navigation (NAV) 6-4. . . . . . . . . . . . . . . . . . . . .Zone of Confusion 6-10. . . . . . . . . . . . . . . . . . . . . . . . .Long Range Navigation (LRN) 6-11. . . . . . . . . . . . . .VOR Approach (VAPP) 6-14. . . . . . . . . . . . . . . . . . . . .Localizer (NAV) 6-15. . . . . . . . . . . . . . . . . . . . . . . . . . .Back Course (BC) 6-21. . . . . . . . . . . . . . . . . . . . . . . . .
Vertical Modes 6-25. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Pitch Hold 6-25. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Vertical Speed (VS) Hold 6-26. . . . . . . . . . . . . . . . . . .Flight Level Change (FLC) 6-28. . . . . . . . . . . . . . . . . .Altitude Preselect (ASEL) 6-31. . . . . . . . . . . . . . . . . . .Altitude Hold 6-36. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Vertical Navigation (VNAV) 6-38. . . . . . . . . . . . . . . . .
Instrument Landing System (ILS) 6-48. . . . . . . . . . . . . . .Overspeed Protection 6-54. . . . . . . . . . . . . . . . . . . . . . . . .Overspeed Protection in Speed Hold 6-54. . . . . . . . . . . .Go--Around (GA), Wings Level 6-55. . . . . . . . . . . . . . . . .
7. TROUBLESHOOTING 7-1. . . . . . . . . . . . . . . . . . . . . . .
Technical Support 7-1. . . . . . . . . . . . . . . . . . . . . . . . . . . .Troubleshooting Digital Avionics 7-1. . . . . . . . . . . . . . . .Accessing Maintenance Test Mode Data 7-3. . . . . . . .
How to Access Hardware/Software ID Pages 7-3. . .How to Access Event Codes (EC) 7-6. . . . . . . . . . .Event Codes Page Description 7-8. . . . . . . . . . . . . .Event Codes Listing 7-10. . . . . . . . . . . . . . . . . . . . . . .Event Codes and Possible Causes 7-11. . . . . . . . . .
Typical Problems 7-15. . . . . . . . . . . . . . . . . . . . . . . . . . . . .Lateral Mode Problems 7-15. . . . . . . . . . . . . . . . . . . .Vertical Mode Problems 7-18. . . . . . . . . . . . . . . . . . . .Combined Vertical and Lateral Mode Problems 7-20.
Ground Maintenance Test 7-21. . . . . . . . . . . . . . . . . . . . .Checklist Uploading Procedure 7-25. . . . . . . . . . . . . . . . .Checklist Loading Troubleshooting 7-28. . . . . . . . . . . . . .
Error Code 5000 7-29. . . . . . . . . . . . . . . . . . . . . . . . . .
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Table of ContentsTC4
Table of Contents (cont)Section Page
7. TROUBLESHOOTING (CONT)Error Code 5005 7-29. . . . . . . . . . . . . . . . . . . . . . . . . .
Operational Notices 7-29. . . . . . . . . . . . . . . . . . . . . . . . . . Overpowering Control Surfaces With Autopilot
and/or Yaw Damper Engaged 7-29. . . . . . . . . . . . . . AP Disconnect Switch Function to Reset a
Failure 7-30. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Autopilot/Yaw Damper Disconnects With
No Event Codes Logged 7-30. . . . . . . . . . . . . . . . . . Pilot Writeup 7-31. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Report Forms 7-31. . . . . . . . . . . . . . . . . . . . . . . . . . . . . Preliminary Considerations 7-31. . . . . . . . . . . . . . . . . Writing the Report 7-32. . . . . . . . . . . . . . . . . . . . . . . . . Commonly Used Terms 7-32. . . . . . . . . . . . . . . . . . . .
8. ACRONYMS AND ABBREVIATIONS 8-1. . . . . . . . . .
APPENDIX
A. PRIMUS 880 WEATHER RADAR SYSTEM A1. . . . Introduction A1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Weather Radar Controller A2. . . . . . . . . . . . . . . . . . . . . Typical Operating Procedures A12. . . . . . . . . . . . . . . . . .
Preliminary Control Settings A12. . . . . . . . . . . . . . . . Precautions A12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Powerup A13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tilt Management A14. . . . . . . . . . . . . . . . . . . . . . . . . .
Maximum Permissible Exposure Level (MPEL) A15. . . APPENDIX B
LIGHTNING SENSOR SYSTEM (LSS) B1. . . . . . . . Introduction B1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . System Components B5. . . . . . . . . . . . . . . . . . . . . . . . . System Controls B6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . System Display B7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Mode Annunciators B9. . . . . . . . . . . . . . . . . . . . . . . . . . . Pilot Activated SelfTest B10. . . . . . . . . . . . . . . . . . . . . .
INDEX Index1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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PRIMUS 1000 Integrated Avionics System with Integral FMS
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Table of ContentsTC5
Table of Contents (cont)
List of IllustrationsFigure Page
11 Cockpit Layout for the Citation Excel 1-5. . . . . . . . . . . .
21 System Block Diagram 2-11. . . . . . . . . . . . . . . . . . . . . . . .
31 Cockpit Layout of the EFIS 3-3. . . . . . . . . . . . . . . . . . . . 32 PFD Bezel Controller 3-5. . . . . . . . . . . . . . . . . . . . . . . . . 33 MFD Bezel Controller 3-6. . . . . . . . . . . . . . . . . . . . . . . . . 34 MFD Menu Structure 3-8. . . . . . . . . . . . . . . . . . . . . . . . . 35 Main Menu 3-9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 VNAV Submenu 3-9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 FMS VNAV Submenu 3-10. . . . . . . . . . . . . . . . . . . . . . . . . 38 VOR SNGP VNAV Submenu 3-11. . . . . . . . . . . . . . . . . . 39 FMS SNGP VNAV Submenu 3-12. . . . . . . . . . . . . . . . . .
310 VSPEED Submenu 3-13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 311 T/O SPEEDS Submenu 3-13. . . . . . . . . . . . . . . . . . . . . . . 312 LNDG SPEEDS Submenu 3-14. . . . . . . . . . . . . . . . . . . . . 313 Inoperative Menu 3-15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 314 Display Controller 3-16. . . . . . . . . . . . . . . . . . . . . . . . . . . . 315 Remote Instrument Controller 3-20. . . . . . . . . . . . . . . . . . 316 Multifunction Display Controller 3-21. . . . . . . . . . . . . . . . . 317 Checklist Index Display 3-24. . . . . . . . . . . . . . . . . . . . . . . 318 External Reversionary Select Switches 3-26. . . . . . . . . . 319 PFD Functional Divisions 3-28. . . . . . . . . . . . . . . . . . . . . . 320 Attitude Director Indicator Displays
and Annunciators 3-31. . . . . . . . . . . . . . . . . . . . . . . . . . . 321 PFD With Excessive Deviation 3-34. . . . . . . . . . . . . . . . . 322 Pitch Scale Markings 3-35. . . . . . . . . . . . . . . . . . . . . . . . . 323 Comparison Monitor Annunciators 3-41. . . . . . . . . . . . . . 324 HSI Compass Display on PFD 3-43. . . . . . . . . . . . . . . . . 325 HSI Arc Display 3-52. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 326 Airspeed Display 3-57. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 327 Altimeter Display 3-61. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 328 Altitude Select 3-63. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 329 Vertical Speed Display 3-66. . . . . . . . . . . . . . . . . . . . . . . . 330 TCAS Resolution Advisory Display 3-68. . . . . . . . . . . . . 331 EGPWS Mode and Failure Annunciators 3-70. . . . . . . . 332 Takeoff Using GoAround Mode 3-71. . . . . . . . . . . . . . . . 333 Climb to Initial Altitude 3-72. . . . . . . . . . . . . . . . . . . . . . . . 334 Enroute Cruise 3-73. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 335 Setup for Approach 3-74. . . . . . . . . . . . . . . . . . . . . . . . . . .
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Table of Contents (cont)List of Illustrations (cont)
Figure Page336 Approach Capture Tracking at Minimums 3-75. . . . . . . . 337 Comparison Monitor Annunciators 3-76. . . . . . . . . . . . . . 338 Excessive Attitude 3-78. . . . . . . . . . . . . . . . . . . . . . . . . . . . 339 PFD Failures Attitude, MADC, Heading,
Course Select, and Flight Director 3-81. . . . . . . . . . . . . 340 PFD Test Mode 3-83. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 341 MFD Display Common Symbols 3-85. . . . . . . . . . . . . . . . 342 MFD Display Symbols 3-87. . . . . . . . . . . . . . . . . . . . . . . . 343 Typical FMSGenerated Graphic Patterns 3-91. . . . . . . 344 MFD Map Display 3-92. . . . . . . . . . . . . . . . . . . . . . . . . . . . 345 Typical Map View Presentation 3-94. . . . . . . . . . . . . . . . . 346 Map View With Weather Display 3-95. . . . . . . . . . . . . . . . 347 Typical Map View Presentation With Weather 3-96. . . . 348 MFD Plan View 3-97. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 349 Typical Plan View With NAVAIDs and Flight Plan 3-98. 350 Typical Checklist Display 3-99. . . . . . . . . . . . . . . . . . . . . . 351 Typical TCAS Display Annunciators 3-102. . . . . . . . . . . . . 352 Typical TCAS Display 3-106. . . . . . . . . . . . . . . . . . . . . . . . . 353 EGPWS Shown From 6000 Feet Over
KSEA Airport 3-109. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 354 EGPWS TEST Display 3-110. . . . . . . . . . . . . . . . . . . . . . . . 355 EGPWS PopUp Display 3-111. . . . . . . . . . . . . . . . . . . . . . 356 MFD Failures and Warnings 3-112. . . . . . . . . . . . . . . . . . . 357 MFD Failure and Warning Displays 3-115. . . . . . . . . . . . .
41 Mode Selector 4-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 Autopilot Controller 4-3. . . . . . . . . . . . . . . . . . . . . . . . . . .
61 Heading Hold Mode Display 6-1. . . . . . . . . . . . . . . . . . . 62 Roll Hold Mode Display 6-2. . . . . . . . . . . . . . . . . . . . . . . 63 VOR (NAV) Mode Radial Intercept 6-4. . . . . . . . . . . . . . 64 VOR (NAV) Mode Intercept Display 6-5. . . . . . . . . . . . . 65 VOR (NAV) Mode Capture 6-6. . . . . . . . . . . . . . . . . . . . . 66 VOR (NAV) Mode Capture Display 6-7. . . . . . . . . . . . . 67 VOR (NAV) Mode Track 6-8. . . . . . . . . . . . . . . . . . . . . . . 68 VOR (NAV) Mode Tracking Display 6-9. . . . . . . . . . . . . 69 VOR (NAV) Mode Tracking Over Station 6-10. . . . . . .
610 FMS Steering Mode Capture and Tracking 6-12. . . . . . . 611 FMS NAV Mode (Typical) Display 6-13. . . . . . . . . . . . . . 612 Localizer (NAV) Mode Intercept 6-16. . . . . . . . . . . . . . . . 613 Localizer (NAV) Mode Arm Display 6-17. . . . . . . . . . . . .
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Table of Contents (cont)List of Illustrations (cont)
Figure Page614 Localizer (NAV) Mode Capture 6-18. . . . . . . . . . . . . . . . . 615 Localizer (NAV) Mode Capture Display 6-18. . . . . . . . . . 616 Localizer (NAV) Mode Tracking 6-19. . . . . . . . . . . . . . . . 617 Localizer (NAV) Mode Tracking Display 6-20. . . . . . . . . 618 Back Course Mode Intercept 6-21. . . . . . . . . . . . . . . . . . . 619 Back Course Intercept Display 6-22. . . . . . . . . . . . . . . . . 620 Back Course Capture Display 6-23. . . . . . . . . . . . . . . . . . 621 Back Course Tracking Display 6-24. . . . . . . . . . . . . . . . . 622 Vertical Speed Hold Mode Display 6-27. . . . . . . . . . . . . . 623 Flight Level Change Mode Display 6-29. . . . . . . . . . . . . . 624 ASEL Profile View 6-31. . . . . . . . . . . . . . . . . . . . . . . . . . . . 625 ASEL at the Start of Descent Display 6-32. . . . . . . . . . . 626 ASEL Armed for Capture Display 6-33. . . . . . . . . . . . . . . 627 ASEL Capture Point Display 6-34. . . . . . . . . . . . . . . . . . . 628 Aircraft Level at Preselected Altitude Display 6-35. . . . . 629 ALT Hold Mode Display 6-36. . . . . . . . . . . . . . . . . . . . . . . 630 VNAV Direct, Profile View 6-40. . . . . . . . . . . . . . . . . . . . . 631 MFD VANG Display 6-41. . . . . . . . . . . . . . . . . . . . . . . . . . 632 MFD VANG Capture Display 6-42. . . . . . . . . . . . . . . . . . . 633 VNAV Preselect, Profile View 6-43. . . . . . . . . . . . . . . . . . 634 MFD VANG Set 6-44. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 635 VGP Mode Display 6-46. . . . . . . . . . . . . . . . . . . . . . . . . . . 636 ILS Localizer Intercept 6-48. . . . . . . . . . . . . . . . . . . . . . . . 637 ILS Approach (Armed) Display 6-49. . . . . . . . . . . . . . . . . 638 ILS Mode Localizer Intercept Display 6-50. . . . . . . . . . 639 ILS Mode Tracking, Profile View 6-51. . . . . . . . . . . . . . . . 640 ILS Mode Tracking Display 6-52. . . . . . . . . . . . . . . . . . . . 641 ILS Mode Track, Profile View 6-53. . . . . . . . . . . . . . . . . . 642 GoAround Mode Display (Wings Level) 6-55. . . . . . . . 71 Display Controller 7-3. . . . . . . . . . . . . . . . . . . . . . . . . . . . 72 Hardware ID Page 1 7-4. . . . . . . . . . . . . . . . . . . . . . . . . . 73 Hardware ID Page 2 7-5. . . . . . . . . . . . . . . . . . . . . . . . . . 74 Display Controller Buttons 7-6. . . . . . . . . . . . . . . . . . . . . 75 Sample Event Codes Page on PFD 7-7. . . . . . . . . . . . . 76 Event Codes Page Layout 7-8. . . . . . . . . . . . . . . . . . . . . 77 Lateral Mode Conditions and Problems 7-16. . . . . . . . . 78 Vertical Mode Conditions and Problems 7-18. . . . . . . . . 79 Ground Maintenance Test Displays on PFD 7-23. . . . . .
710 Typical Checklist Display 7-27. . . . . . . . . . . . . . . . . . . . . . 711 Pilots Flight Plan and Squawk Sheet 7-33. . . . . . . . . . .
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Table of Contents (cont)List of Illustrations (cont)
Figure Page712 Event Code Report Form 7-35. . . . . . . . . . . . . . . . . . . . . . 713 Continued Event Code Report Form 7-37. . . . . . . . . . . .
A1 Weather Radar Controller Configuration A2. . . . . . . . . A2 Initial Offset Roll Instruction Set A4. . . . . . . . . . . . . . . . A3 Gain Knob Adjustment A5. . . . . . . . . . . . . . . . . . . . . . . . A4 Display Test Pattern, 120 Scan A13. . . . . . . . . . . . . . . . A5 Radar Beam Illumination High Altitude
12Inch Radiator A14. . . . . . . . . . . . . . . . . . . . . . . . . . . A6 Radar Beam Illumination Low Altitude
12Inch Radiator A14. . . . . . . . . . . . . . . . . . . . . . . . . . . A7 MPEL Boundary A15. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B1 Weather and Lightning Display B1. . . . . . . . . . . . . . . . . B2 Strokes for Each Symbol vs. NM B3. . . . . . . . . . . . . . . B3 Rate of Occurance Symbols B4. . . . . . . . . . . . . . . . . . . B4 Lightning Rate Symbol B4. . . . . . . . . . . . . . . . . . . . . . . . B5 LSS Components B5. . . . . . . . . . . . . . . . . . . . . . . . . . . . B6 Typical Weather Radar Controller With Integral
Lightning Sensor Control B6. . . . . . . . . . . . . . . . . . . . . B7 Typical Lightning/Weather Display on EHSI B8. . . . . .
List of TablesTable Page
11 Equipment List 1-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 Support Software Equipment 1-4. . . . . . . . . . . . . . . . . .
21 PRIMUS 1000 Integrated Avionics System 2-3. . . . .
31 Navigation Bearing Pointers 3-17. . . . . . . . . . . . . . . . . . . 32 Flight Director Reset Modes 3-19. . . . . . . . . . . . . . . . . . . 33 Heading Reversionary Switch Functions 3-26. . . . . . . . . 34 Attitude Reversionary Switch Functions 3-27. . . . . . . . . 35 Air Data Computers Reversionary Switch
Functions 3-27. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 Autopilot Messages 3-30. . . . . . . . . . . . . . . . . . . . . . . . . . . 37 FMS Vertical Deviation 3-36. . . . . . . . . . . . . . . . . . . . . . . . 38 Honeywell VNAV Vertical Deviation 3-37. . . . . . . . . . . . .
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Table of Contents (cont)List of Tables (cont)
Table Page39 Distance Display Range 3-45. . . . . . . . . . . . . . . . . . . . . . .
310 Bearing Selector 3-46. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 311 VOR NAV Source Lateral Deviation Scaling 3-47. . . . . . 312 FMS NAV Source Lateral Deviation With
GPS Valid 3-47. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 313 FMS NAV Source Lateral Deviation With
GPS Invalid 3-47. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 314 VOR TO/FROM Indicator 3-48. . . . . . . . . . . . . . . . . . . . . . 315 FMS Accuracy and Crosstrack Messages 3-49. . . . . . . 316 FMS Status Messages 3-50. . . . . . . . . . . . . . . . . . . . . . . . 317 Heading Source Annunciators 3-51. . . . . . . . . . . . . . . . . . 318 Weather Radar Return Color Code 3-53. . . . . . . . . . . . . 319 Selectable Radar Ranges 3-54. . . . . . . . . . . . . . . . . . . . . 320 Weather Warning Annunciators 3-55. . . . . . . . . . . . . . . . 321 Weather Mode Annunciators 3-56. . . . . . . . . . . . . . . . . . . 322 VSPEED Bug Identification 3-58. . . . . . . . . . . . . . . . . . . . . . . 323 Low Speed Awareness Bar Color 3-59. . . . . . . . . . . . . . . 324 TCAS Status Messages 3-69. . . . . . . . . . . . . . . . . . . . . . . 325 Weather Radar Mode Annunciators on MFD 3-89. . . . . 326 MFD TCAS Mode Annunciations 3-105. . . . . . . . . . . . . . . 327 Display Symbols 3-105. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 328 EGPWS Annunciators 3-107. . . . . . . . . . . . . . . . . . . . . . . . 329 EGPWS Terrain Elevation Relative to
Aircraft Altitude 3-108. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 330 Wraparound Failure Warnings 3-113. . . . . . . . . . . . . . . . . . 331 IC Fan Failure Warnings 3-114. . . . . . . . . . . . . . . . . . . . . . 332 IC Overheat Warnings 3-114. . . . . . . . . . . . . . . . . . . . . . . . 333 Course Pointer Color Convention 3-117. . . . . . . . . . . . . . .
51 System Performance and Operating Limits 5-5. . . . . . 52 Air Data Display Parameters and Ranges 5-8. . . . . . . .
61 VOR NAV Mode Engagement Procedure 6-4. . . . . . . . 62 LRN Mode Engagement Procedure 6-11. . . . . . . . . . . . . 63 FMS Navigation Mode Procedure 6-13. . . . . . . . . . . . . . 64 VAPP Mode Engagement Procedure 6-14. . . . . . . . . . . . 65 Localizer Mode Engagement Procedure 6-15. . . . . . . . . 66 Back Course Mode Procedure 6-21. . . . . . . . . . . . . . . . . 67 Flight Level Change Mode Engagement Procedure 6-3068 ASEL Mode Operation Procedure 6-32. . . . . . . . . . . . . . 69 Altitude Hold Procedure 6-36. . . . . . . . . . . . . . . . . . . . . . .
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Table of ContentsTC--10
Table of Contents (cont)
List of Tables (cont)
Table Page
6--10 VNAV Mode Data Entry Procedure 6-38. . . . . . . . . . . .6--11 VNAV Direct Engagement Procedure 6-41. . . . . . . . . .6--12 VNAV Preselect Engagement Procedure 6-44. . . . . . .6--13 ILS Mode Procedure 6-49. . . . . . . . . . . . . . . . . . . . . . . .
7--1 Digital and Analog System Differences 7-1. . . . . . . . .7--2 Maintenance Test and Hardware/Software
Identification Page Access Procedure 7-4. . . . . . . . .7--3 Event Code Retrieval Procedure 7-7. . . . . . . . . . . . . .7--4 Event Codes Page Description 7-9. . . . . . . . . . . . . . . .7--5 Event Codes and Possible Causes 7-11. . . . . . . . . . . .7--6 EC 0221 Troubleshooting Procedure 7-13. . . . . . . . . . .7--7 EC 0222 Troubleshooting Procedure 7-13. . . . . . . . . . .7--8 EC 0223 Troubleshooting Procedure 7-14. . . . . . . . . . .7--9 EC 0225 Troubleshooting Procedure 7-14. . . . . . . . . . .7--10 Lateral Mode Problems 7-15. . . . . . . . . . . . . . . . . . . . . .7--11 Vertical Mode Problems 7-18. . . . . . . . . . . . . . . . . . . . . .7--12 Problems Common to Both Vertical and
Lateral Modes 7-20. . . . . . . . . . . . . . . . . . . . . . . . . . . . .7--13 Ground Maintenance Test Procedure 7-21. . . . . . . . . .7--14 Checklist Upload Procedure 7-25. . . . . . . . . . . . . . . . . .7--15 Error Code 5000 Troubleshooting Procedure 7-28. . . .7--16 Definitions of Terms 7-32. . . . . . . . . . . . . . . . . . . . . . . . .
A--1 In--Flight Roll Offset Adjustment Procedure A--3. . . . .A--2 Target Alert Characteristics A--6. . . . . . . . . . . . . . . . . . .A--3 Rainfall Rate Color Coding A--9. . . . . . . . . . . . . . . . . . . .A--4 Weather Radar System Preliminary Control
Settings A--12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .A--5 PRIMUSR 880 Weather Radar System
Precautions A--12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
B--1 LSS Mode Annunciation Definitions B--9. . . . . . . . . . . . .B--2 Pilot Activated LSS Self--Test Procedure B--10. . . . . . . .
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PRIMUS 1000 Integrated Avionics System with Integral FMS
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Introduction
1. IntroductionPRIMUS 1000 INTEGRATED AVIONICS SYSTEMThis document describes the components, operating procedures, andtypical flight applications for the PRIMUS 1000 Integrated AvionicsSystem with integral FMS (IC615) installed in the Cessna CitationExcel (Model 560). Figure 11 shows the layout of the Excel cockpit.Subsystems described in this manual include the PRIMUS 1000Integrated Avionics Systems flight control system (FCS), electronicflight instrument system (EFIS), air data system (ADS), the integralflight management system (FMS), PRIMUS 880 Digital WeatherRadar SystemTraffic alert and collision avoidance system (TCAS), enhanced groundproximity warning system (EGPWS), and Lightning Strike Sensor(LSS) are optional subsystems that interface with the PRIMUS 1000Integrated Avionics System.Table 11 lists the cockpitmounted and remotemounted equipmentdescribed in this manual.
Model Unit Qty Part No.Cockpit MountedDU870 Display Unit (DU) 3 7014300901BL870 Primary Flight Display (PFD)
Bezel Controller2 7014331931
BL870 Primary Flight Display (PFD)Bezel Controller
2 7014331925
BL871 Multifunction Display (MFD)Bezel Controller
1 7014332841
DC550 Display Controller (DC) 2 7016986747DC550 Display Controller (DC) 2 7016986751MC800 Multifunction Display (MFD)
Controller1 7007062939
RI553 Remote InstrumentController
1 7016954907
Equipment ListTable 11 (cont)
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
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Introduction1-2
Model Part No.QtyUnit
WC--880 Weather Radar Controller 1 7008471--407
PC--400 Autopilot Controller 1 7003897--923
MS--560 Mode Selector 1 7018341--803
RM--850 Radio Management Unit(RMU)
2 7012100--825
CD--810 FMS Control Display Unit 1 7007549--XXX
CD--850 Clearance Delivery Head 1 7513000--835
DI--851 Distance MeasuringEquipment (DME) Indicator
2 7513006--911
Optional
MC--800 MFD Controller with TCAS 1 7007062--941
DC--550 Display Controller withSingle Cue/Crosspointer(SC/CP) Button
1 7016986--621
TCAS2000
TCAS Computer 1 7517900--55002
DL--900 FMS Data Loader 0 7016600--901
CD--810(Copilot)
FMS Control Display Unit 1 7007549--XXX
AT--850 LSS Antenna (teardrop) 1 4057697--901
LP--850 LSS Processor 1 7011822--904
WC--880 Weather Controller 1 7008471--405
Remote Mounted
IC--615(Pilot)(OptionalCopilot)
Integrated AvionicsComputer(Signal Generator (SG)/Flight Director (FD)/Autopilot (AP)/ FMS)
1 7017000--98801
Equipment ListTable 1--1 (cont)
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
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Introduction
Model Part No.QtyUnit
IC--615(Copilot)
Integrated AvionicsComputer (SG/FD/FMS)
1 7017000--99801
IC--615(Pilot)(OptionalCopilot)
Integrated AvionicsComputer(SG/FD/AP)
1 7017000--96801
IC--615(Copilot)
Integrated AvionicsComputer (SG/FD)
1 7017000--97801
SM--200 Elevator/Aileron Servo DriveAssemblyRudder Servo DriveAssembly
2
1
4006719--906
4006719--910
SB--201 Servo Bracket 3 4005842
FX--220 Flux Valve 2 2594484
AZ--850 Micro Air Data Computer(MADC)
2 7014700--914
WU--880 Receiver TransmitterAntenna (RTA)
1 7021450--801
RNZ--850RNZ--850B
Integrated Navigation (NAV)Unit
11
7510100--9317510100--933
RCZ--833E Communications (COM) Unitwith Diversity Transponder
1 or2
7510700--766
RCZ--833H Communications Unitwithout DiversityTransponder
1 7510700--769
IM--600 Configuration Module 2 7025973--02007
IM--600 Configuration Module(TCAS)
2 7025973--02005
Equipment ListTable 1--1
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137Introduction1-4
Table 1--2 lists support software equipment.
Model Unit Qty Part No.
ECP--800 Programmable Checklist 1 7021060--901
TBD Configuration ModuleProgramming Tool
1 TBD
Support Software EquipmentTable 1--2
NOTES: 1. This manual describes all system capabilities. Theitems noted as optional are not necessarily included inthe standard offering.
2. The artwork in this manual is typical. Specificinstallations may vary.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
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Cockpit Layout for the Citation ExcelFigure 1--1
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PRIMUS 1000 Integrated Avionics System with Integral FMS
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Introduction
HONEYWELL PRODUCT SUPPORT
The Honeywell SPEX program for corporate operators provides anextensive exchange and rental service that complements a worldwidenetwork of support centers. An inventory of more than 9,000 sparecomponents assures that the Honeywell equipped aircraft will bereturned to service promptly and economically. This service is availableboth during and after warranty.
The aircraft owner/operator is required to ensure that units providedthrough this program have been approved in accordance with theirspecific maintenance requirements.
All articles are returned to Reconditioned Specifications limits whenthey are processed through a Honeywell repair facility. All articles areinspected by quality control personnel to verify proper workmanshipand conformity to Type Design and to certify that the article meets allcontrolling documentation. Reconditioned Specification criteria are onfile at Honeywell facilities and are available for review. All exchangeunits are updated with the latest performance reliability MODs on anattrition basis while in the repair cycle.
When contacting a Honeywell Dealer or Customer Support Center forservice under the SPEX program, the following information regardingthe unit and the aircraft are required: Complete part number with dash number of faulty unit Complete serial number of faulty unit Aircraft type, serial number and registration number Aircraft owner Reported complaint with faulty unit Service requested (Exchange or Rental) Ship to address Purchase order number If faulty unit is IN WARRANTY:
Type of warranty (NEW PRODUCT or Exchange) Date warranty started
If faulty unit is covered under a Maintenance Contract: Type of contract Contract date Plan ID number
If faulty unit is NOT IN WARRANTY, provide billing address.
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PRIMUS 1000 Integrated Avionics System with Integral FMS
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Introduction1-8
The Honeywell Support Centers listed below will assist with processingexchange/rental orders.
24HOUR EXCHANGE/RENTAL SUPPORT CENTERS
U.S.A. DALLAS80087277399724024300
AUSTRALIA TULLAMARINE61393301411
ENGLAND BASINGSTOKE441256722200
GERMANY AOA GAUTING01728207300 (in Germany)
491728207300 (outside Germany)FRANCE TOULOUSE
33561719662SINGAPORE655421313
CUSTOMER SUPPORT CENTERS NORTH AMERICA
Dallas Support CenterHoneywell7825 Ridgepoint Dr.IRVING, TX 75063TEL: 9724024300FAX: 9724024999
Miami Support CenterHoneywell7620 N.W. 25th StreetBldg. C Unit 6MIAMI, FL 33122TEL: 3054368722FAX: 3054368532
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Northwest Support CenterHoneywell4150 Lind Avenue SouthwestRENTON, WA 98055TEL: 4252519511TLX: 320033FAX: 4252431954
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PRIMUS 1000 Integrated Avionics System with Integral FMS
A281146137Rev 2 Sep 2002 1-9
Introduction
CUSTOMER SUPPORT CENTERS REST OF THE WORLD
United Kingdom Support CenterHoneywell Avionics Systems LtdEdison Road, Ringway NorthBASINGSTOKE, HANTS,RG21 6QDENGLANDTEL: 441256722200FAX: 441256722201AOG: 441256722200TLX: 51858067
France Support CenterHoneywell Aerospace1 Rue MarcelDoret, B.P.1431701 BLAGNAC CEDEX,FRANCE (Toulouse)TEL: 33562121500FAX: 33561300258AOG: 33561719662TLX: 521635F
Singapore Support CenterHoneywell Aerospace Pte. Ltd.2 Loyang CrescentSINGAPORE 1750TEL: 655421313FAX: 655421212AOG: 655421313TLX: RS 56969 HWLSSC
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Germany Support CenterAOA Apparatebau Gauting GmbHAmmerseestrasse 4549D82131 GautingGERMANYTEL: 4989893170FAX: 498989317183After Hours AOG Service:01728207300 (in Germany)491728207300 (outside Germany)TLX: 0521702
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PRIMUS 1000 Integrated Avionics System with Integral FMS
A281146137Rev 2 Sep 2002
Introduction1-10
PUBLICATION ORDERING INFORMATION
Please contact Honeywell if: The revision services card is missing and you would like to register
for revision services. You need to submit a change of address for revision services. You need additional copies of this manual.
Send your name, address, and publication number to:HoneywellAerospace Electronic SystemsCESPhoenixP.O. Box 21111Phoenix, Arizona 850361111Attention: Publication Distribution, Dept. M/S 2H24A4
Telephone No.: (602) 4366900FAX: (602) 8227272EMAIL: CASpublicationsdistribution@cas.
honeywell.com
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--1372-1
System Description
2. System Description
GENERAL
The PRIMUSR 1000 Integrated Avionics System is an EFIS/control/display systemanda fail--passive autopilot/flight directorwithhorizontaland vertical flight guidance modes. These include all radio guidancemodes, long range navigation system tracking modes, and air datavertical modes. Either flight director can be coupled to the autopilot tocontrol the aircraft.
The integrated avionics computer (IAC) digitally processes attitude,heading, navigation, and air data information. This data is presented toeach pilot on the electronic flight instrument system (EFIS) displays.
The system displays the following:
D Heading
D Course
D Radio bearing
D Pitch and roll attitude
D Airspeed
D Altitude
D Vertical speed
D Selected altitude target with alert
D Barometric altimeter setting
D Radio altitude
D Course deviation
D Glideslope deviation
D To--From indications
D Distance indications (DME or FMS).
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137System Description2-2
Annunciators on the primary flight display (PFD) indicate the selectedflight mode. Pitch and roll commands, calculated by the IACs flightdirector function in conjunction with the mode selector, direct the pilotto reach and/or maintain the required flightpath.
The IAC is the focal point of information flow in this system. It convertsinput data and information to the pilot--selected formats, displayingthem on the attitude director indicator (ADI) and the horizontal situationindicator (HSI) on the PFD. The IAC also generates informationdisplayed on the multifunction display (MFD). It computes the flightdirector steering information for display aswell as the autopilot function.
The two IACs are interconnected so that the flight guidance functionsand symbol generator functions share, compare, and communicateblocks of information.
When engaged and coupled to the flight director, the systems autopilotcontrols the aircraft using the same commands that are displayed onthe ADI. When the autopilot is engaged and uncoupled from the flightdirector, manual pitch and roll commands can be entered using thetouch control steering (TCS) button or the autopilot PITCH wheel orTURN knob.
The IAC has a built--in multilevel self--test, including an automaticpower--up self--check, initiated testing, on--ground maintenance test,and fault storage. Refer toSection 7, Troubleshooting, for pilot--initiatedtest information.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
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System Description
The avionics system block diagram is shown in Figure 2--1. Theindividual systems that make up the PRIMUSR 1000 IntegratedAvionics System are described in Table 2--1 and in the followingparagraphs.
Availability System
Standard IC--615 Integrated Avionics Computer that includes:D Electronic Flight Instrument System (EFIS)D Flight Guidance System (FGS)
Standard AZ--850 Air Data System (ADS)
Standard PRIMUSR 880 Weather Radar System
Standard Attitude and Heading Reference System (AHRS)
Optional Traffic Alert and Collision Avoidance System (TCAS)
Optional Enhanced Ground Proximity Warning System(EGWPS)
Optional Dual Flight Management System (FMS)
PRIMUSR 1000 Integrated Avionics SystemTable 2--1
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137System Description2-4
ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS)
The EFIS includes the following line replaceable units (LRUs):
D Inside each IAC
Symbol generator (SG)
Sensor interfaces
Flight management computer (optional)
Global positioning system (GPS) sensor (optional)
D Display units (DUs) -- PFD and MFD
D PFD bezel controller
D MFD bezel controller
D Display controller
D Remote instrument controller
D MFD controller.
The EFIS displays the following:
D Pitch and roll attitude
D Heading
D Course orientation
D Flightpath commands
D Weather information
D Checklists
D Mode and source annunciators
D Air data parameters
D Long range navigation map displays
D Optional TCAS information
D Optional EGPWS information.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
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System Description
The primary features EFIS brings to the flight control system are:
D Display integration
D Flexibility
D Redundancy.
Essential display information from sensor systems, automatic flightcontrol, andnavigation are integrated into thepilots primeviewingarea.
Critical flight operation information is selected using the displaycontroller and MFD controller. These controllers are also used tooperate the checklist function. Navigation and aircraft performancedisplays are selected using the display unit--mounted bezel controllers.
Each symbol generator can drive the threedisplays. In the caseof aDUfailure, the pilots PFD can be reverted to the MFD.
The symbol generator in the IAC functions as the data processor for thedisplay system. It receives digital and discrete inputs, organizes theinformation into the correct formats as defined by the display controllersettings, and transmits the information to the DUs.
Except for the presence of an autopilot function in the No. 1 IAC, theIACs are identical and directly interchangeable. When the displaysystem is in its normal (no failure) configuration, IAC No. 1 drives thepilot displays, and IAC No. 2 drives the copilot displays. Wraparoundsignals are used for critical parameters, such as pitch or roll data,indicated airspeed (IAS), barometric altitude, and baro set.
Reversionary switches substitute failed sensors for operational ones.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137System Description2-6
FLIGHT GUIDANCE SYSTEM (FGS)
The flight guidance system includes the following units:
D Inside the IAC
Flight director function Autopilot function (optional as spare on copilots side) System monitors Flight management computer GPS sensor
D Mode selector
D Display controller
D Autopilot controller
D Servo motors (pitch/roll/yaw).
The fail--passive IAC contains the flight director, yaw damper, andautopilot. The system monitors the pilot and copilot AHRS data andservo command outputs. Servo command outputs from a computedservo model in all three axes are compared to actual commands withinput from the air data computer. If the difference between commandsexceeds certain tolerances, the autopilot is disconnected from theservos.
Monitor types are comparison, servo position, rate, and attitude.
Normal flight guidance functions are computed by the selected flightdirector, with the non--selected flight director displaying the samecommand bar formats and modes on its PFD.
The autopilot controller contains the autopilot engage, yaw damperengage, turn knob, pitch wheel, and low bank switch. Excessiveelevator trim is also annunciated. Either theNo. 1 or No. 2 flight directorcan be selected and coupled to the autopilot.
Modes are annunciatedon themodeselector andon thePFD. The flightdirector command bars on the PFD follow the flight director to displayvisual guidance for the selected mode. The navigation sensor used forthe chosenmode is selected on the display controller and annunciatedon the PFD.
The yaw damper (YD) executes basic yaw damper functions with orwithout the autopilot. When the autopilot is engaged, turn coordinationis active. The yaw damper is active when the YD or AP engage buttonon the autopilot controller is pushed.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
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System Description
AIR DATA SYSTEM (ADS)
TheADS includes dualmicro air data computers (MADCs). The systemalso includes standby airspeed and altimeter indicators that are drivendirectly from the aircraft standby pitot--static system.
The MADC is a microprocessor--based digital computer that performscomputations and supplies digital readouts. Its functions include:
D Receiving pitot--static pressures and total air temperature (TAT)inputs for computing the standard air data functions
D Outputting data (altimeter, baro set, Mach/airspeed, and verticalspeed) through the IAC for display on the PFDs
D Outputting data for the transponder, flight data recorder, flightdirector, and autopilot, as well as other elements of the flight controlsystem
D Selecting and displaying the altitude reference for altitude alertingand preselect functions through the MFD altitude select knob.
PRIMUSR 880 DIGITAL WEATHER RADAR SYSTEM
The PRIMUSR 880 Digital Weather Radar System consists of thefollowing LRUs:
D Receiver transmitter antenna (RTA)
D Weather radar controller.
The weather radar system is a lightweight, X--band digital radar withalphanumerics designed for weather detection and groundmapping. Intheweather detectionmode, storm intensity levels are displayed in fourbright colors contrasted against a deep black background. Areas ofvery heavy rainfall are displayed inmagenta, heavy rainfall in red, lesssevere rainfall in yellow, moderate rainfall in green, and little or norainfall in black (background). Areas of detected turbulence aredisplayed in soft white. Range marks and identifying numerics,displayed in contrasting colors, facilitate evaluation of storm cells.
In the ground mapping (GMAP) mode, the system parameters areoptimized to improve resolution and enhance identification of smalltargets at short ranges. The signals reflected off various groundsurfaces are displayed as magenta, yellow, or cyan (most to leastreflective).
A brief description of the PRIMUSR 880 Digital Weather Radar Systemis included inAppendixAof thismanual. A complete description isgivenin Honeywell Pub. No. A28--1146--102.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137Rev 1
System Description2-8
ATTITUDE AND HEADING REFERENCE SYSTEM(AHRS)
The AHRS generates aircraft pitch and roll information to the FGS,EFIS, and weather radar antenna. This information is used for FGScomputations that generate control commands.
The AHRS, along with the flux valve, generates stabilized headinginformation that is used by the FGS and EFIS functions and otheroptional heading displays.
FLIGHT MANAGEMENT SYSTEM (FMS)
The flight management system (FMS) manages navigation sensors toprovide composite position. Navigation, performance, flight planningcapabilities, and guidance throughout the flight are also available.
TRAFFIC ALERT AND COLLISION AVOIDANCESYSTEM (TCAS) (OPTIONAL)
TCAS receives air data information from the MADC and displays it onthe MFD with aircraft traffic and conflict avoidance information.
ENHANCED GROUND PROXIMITY WARNINGSYSTEM (EGPWS) (OPTIONAL)
The enhanced ground proximity warning system displays terrain/obstacle map information and cautions or warnings.
LIGHTNING SENSOR SYSTEM (LSS) (OPTIONAL)
The LSS detects lightning activity within a 100 NM radius around theaircraft, giving the pilot a visual display of its position and rate ofoccurrence. The LSS detects both visible and high energyelectromagnetic and electrostatic discharges.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--1372-9/(2-10 blank)
System Description
OTHER SWITCHES AND CONTROLS
D AP (Autopilot) Disconnect Switch -- The AP disconnect switch iscontrol wheel mounted. When pushed, it disconnects the autopilot.It is also used to reset monitor--induced autopilot disconnects. If theautopilot disconnects becauseamonitor in thepitch, roll, or yawaxissenses anabnormal response condition (suchas a pilots feet on therudder when the yaw damper tries to execute a yaw damperfunction), the message AP FAIL is displayed on the PFD. Toreactivate the autopilot, push the AP disconnect switch for twoseconds to reset the monitors, then autopilot can be re--engaged.
D TCS (Touch Control Steering) Button -- The TCS disconnectswitch is on the control wheel. When pushed, it enables the pilot tochange aircraft attitude, altitude, airspeed, and/or vertical speedmanually without disengaging the autopilot.
D GA (Go--Around) Button -- The GA button is on the throttle. Whenpushed, it disengages the autopilot and commands a wings level,nose up attitude.
D External Reversionary Select Switches -- These cockpit switchescontrol attitude, heading, and air data input sources for the EFIS.They are described in Section 3, Electronic Flight InstrumentSystem (EFIS).
D FD (Flight Director) Transfer Switch -- The FD transfer switch isnormally located on the center instrument panel. This switchtransfers FD1 or FD2 to the autopilot.
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PRIMUS 1000 Integrated Avionics System with Integral FMS
A281146137Rev 2Sep2002
System Description2-11/(2-12 blank)
SM200RUDDERSERVO
SM200ELEVATORSERVO
SM200AILERONSERVO
FX220FLUX VALVE
MODE DIM
FX220FLUX VALVE
AD24161@
TUNE
AZ850MICRO
AIR DATACOMPUTER
AHRS ARINC 429
ARINC 429 HDLC
IC615INTEGRATED
AVIONICSCOMPUTER
DU870 PFDWC880
WX CONTROLLER
PC400 AUTOPILOTCONTROLLER
MS560MODE SELECTOR
DC550 DISPLAYCONTROLLER
TO BOTH ICS
WU880WEATHERRADAR
DU870 MFD
MC800MFD CONTROLLER
DC550 DISPLAYCONTROLLER
FROMIC615
DU870 PFD
AZ850MICRO
AIR DATACOMPUTER
IC615INTEGRATEDAVIONICSCOMPUTER
AHRSARINC 429
ARINC 429HDLC
RI553 REMOTEINSTRUMENT CONTROLLER
RNZ851NAV UNIT
RCZ851ECOM UNIT RCZ851E
COM UNITRNZ851BNAV UNIT
CD850CLR DEL
HEAD
DI851 DMEINDICATOR
DI851 DMEINDICATOR
AV850AAUDIO CONTROL
UNIT
AV850AAUDIO CONTROL
UNIT
AT860ADF ANT
RAD ALT
TRIMSERVO
RM850RMU
RM850RMU
TUNE
FPLNEXTNAV
A
BRTDIRPERF PREV PROG
E
8
3
4
7
D 1
9
5
U
Y Z
C
CLRDEL
2
W
O P Q RI J K L
F
T V
6
M
G
B
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S 0
CD810
FPLNEXTNAV
A
BRTDIRPERF PREV PROG
E
8
3
4
7
D 1
9
5
U
Y Z
C
CLRDEL
2
W
O P Q RI J K L
F
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CD810OPTIONALAT850
ANTENNA
LP850LIGHTNINGSENSORPROCESSOR
System Block DiagramFigure 21
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--1373-1/(3-2 blank)
Electronic Flight Instrument System (EFIS)
3. Electronic Flight InstrumentSystem (EFIS)
GENERAL
The EFIS generates flightpath, flight instrument, and navigationinformation. It consists of a PFD for each pilot and an MFD on thecentral panel, with various cockpit--mounted controllers to selectfunctions and display modes. Figure 3--1 shows a cockpit layout of theEFIS.
The EFIS displays the following:
D Heading
D Attitude
D Airspeed
D Vertical speed
D Course orientation
D Flightpath commands
D Source annunciators
D Weather radar information
D Barometric and radio altitudes
D Navigation mapping information
D Flight director modes
D Checklist
D TCAS information (optional)
D EGPWS information (optional).
EFIS controllers, displays, and reversionarymodes aredescribed in thefollowing paragraphs. Refer to Section 4, Flight Guidance System, fordescriptions of the autopilot controller and the mode selector.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137 Electronic Flight Instrument System (EFIS)3-3/(3-4 blank)
S
W
E
2
4
2115
12
TUNESQ
COM
DIM
PGE
1/2
TST
STO
DME
COMI NB NAV1
TEMP- 1ATC TCASADF1
1 TA/RA
RANGE:MLS1CH:AZ:GP:ALT:
24.250021.1255
1471
500300M
NORM
DME
MEMORY- 1
110.25109.35
ANT162.5
TCAS DSPY 16
HF
25.5
TUNESQ
COM
DIM
PGE
1/2
TST
STO
DME
COMI NB NAV1
TEMP- 1ATC TCASADF1
1 TA/RA
RANGE:MLS1CH:AZ:GP:ALT:
24.250021.1255
1471
500300M
NORM
DME
MEMORY- 1
110.25109.35
ANT162.5
TCAS DSPY 16
HF
25.5
DISPLAYCONTROLLER
PILOTPFD MFD
MODESELECTOR RMU RMU
COPILOTPFD
DISPLAYCONTROLLER
MFDCONTROLLER
REMOTE INSTRUMENTCONTROLLER
AUTOPILOTCONTROLLER
AD--24068@
AUDIOPANEL
AUDIOPANEL
WEATHER RADARCONTROLLER
GAIN RADAR SLV TILTMIN MAX
OFFSTBYWX RCT
GMAPFP
PULLVAR
TST
TRB STAB TGT SECT
CONTROL DISPLAYUNIT
FPLNEXTNAV
A
BRTDIRPERF PREV PROG
E
8
3
4
7
D 1
9
5
U
Y Z
C
CLRDEL
2
W
O P Q R
I J K L
F
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Cockpit Layout of the EFISFigure 3--1
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PRIMUS 1000 Integrated Avionics System with Integral FMS
A281146137Rev 2 Sep 2002 3-5
Electronic Flight Instrument System (EFIS)
CONTROLLERS
Primary Flight Display (PFD) Bezel ControllerTwo types of PFD bezel controllers, front mounted on the PFD, are nowin use depending upon aircraft serial number. They are shown inFigure 32 and functions are listed below.
AD63968@
INCLINOMETER STANDARDALTIMETER
BUTTON
BAROMETRICALTIMETERSET KNOB
BEZEL CONTROLLER WITHOUT RAD/BARO BUTTON
BEZEL CONTROLLER WITH RAD/BARO BUTTON
MINIMUMS KNOB RAD/BAROBUTTON
PFD Bezel ControllerFigure 32
Inclinometer The ball in the glass track indicates a slip or skid.
STD (Standard) Button Push the STD button to return barometricaltimeter correction to the standard value of 29.92 inches of mercury(inHg) or 1013 hectopascals (hPa).
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PRIMUS 1000 Integrated Avionics System with Integral FMS
A281146137Rev 2 Sep 2002
Electronic Flight Instrument System (EFIS)3-6
BARO (Barometric) Knob The BARO set knob adjusts thealtimeter setting in either inHg or hPa.
NOTES: 1. When crossside MADC data is displayed on thePFD, the respective BARO set knobs do not havecontrol over the displayed BARO setting.
2. The BARO set operates independently from thedisplay controller. It is not necessary that thedisplay controller be functional to set data.
RAD/BARO Button The RAD/BARO button is a momentarypushbutton that selects RAD minimums for display on the PFD.RAD and BARO occupy the same display field on the PFD; thereforeonly one can be displayed at a time. The RAD/BARO button togglesthe display format to RAD, BARO, or OFF. The powerup default isBARO.
MINIMUMS Knob Controls the minimums set value for theselected RAD or BARO. The pilot and copilot MINIMUMS Set Knobsare independent of each other; the pilot can set and display a RADor BARO Minimums and the copilot can set and display a differentRAD or BARO Minimums.
Multifunction Display (MFD) Bezel ControllerThe five menu buttons and the two knobs on the MFD bezel controller,shown in Figure 33, are used to set vertical navigation (VNAV) dataparameters and reference speeds (VSPEEDS).
AD63969@
DATA SET KNOB ALTITUDEPRESELECT
KNOB
MENU BUTTONS
MFD Bezel ControllerFigure 33
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PRIMUS 1000 Integrated Avionics System with Integral FMS
A281146137Rev 2 Sep 2002 3-7
Electronic Flight Instrument System (EFIS)
The left rotary knob inputs data to various menus. The right rotary knobis used only to set altitude preselect inputs. Input data is sent to thedisplay controllers. If one display controller fails, the remaining displaycontroller transmits the MFD bezel controller commands.
Data Set Knob Turning this knob inputs data to various menuswhenever a SET label is displayed over the knob. It is used to setVSPEEDS and VNAV parameters.
First Menu Button This button, next to the data set knob, is areturn (RTN) button that recalls the main menu.
Menu Buttons 25 These buttons call up various submenus andselect or change parameters.
Altitude Preselect Knob This knob sets the altitude preselectdisplays on the PFDs and the MFD bezel menu. The altitudepreselect value is set in 100foot increments and can be changedat any time by rotating the knob. All menu pages on the MFD displaythe digital readout of the selected altitude.
NOTE: When the PFD is displayed on the MFD, the MFD bezelbuttons are inoperative, and parameters such as VSPEEDScannot be set. However, the MFD altitude select (ALT SEL)knob functions normally. The PFDs BARO set knobcontinues to function when the PFD is transferred to theMFD.
CONTROLLER CONVENTIONS
When a menu item is boxed, the parameter in the box is displayed onthe PFD or MFD. Selecting a boxed item deselects the item.
Parameter Selected for Display A selected parameter isdisplayed only when the item is boxed on the menu. If there is no boxaround the item, the item is not displayed.
Parameter Selected for Setting If the parameter is not boxed, thefirst push of the menu button below it boxes the parameter, or boxesdashes if the parameter is being set. The data set knob is used tochange a set value. Once the value is set, it is displayed by pushingany other menu key. Pushing the same menu button that wasselected and boxed, deselects the parameter and erases entereddata.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137Electronic Flight Instrument System (EFIS)3-8
MFD MENU STRUCTURE
The MFD menu structure is shown in Figure 3--4. The pilot can selectany of six submenu pages, control the FMS source, and select theEGPWS (optional) for display on the MFD.
AD--63971@
MFD Menu StructureFigure 3--4
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Electronic Flight Instrument System (EFIS)
MAIN MENU
Themainmenu, shown in Figure 3--5, is theMFDpower--up menu. Thecrew can select either the VNAV or VSPEED submenu, control the displayof EGPWS terrain (TERR), and/or select FMS1 or FMS2 for display. IfEGPWS is not installed, TERR is not displayed on the menu. If theaircraft has only a single FMS installed, FMS1 and FMS2 are notdisplayed.
AD--63972@
Main MenuFigure 3--5
VNAV (VERTICAL NAVIGATION) SUBMENU
The VNAV submenu, shown in Figure 3--6, selects either coupled FMSVNAV, coupled singlepoint (SNGP)VNAV, or returns (RTN) to theMAINMENU. If singlepoint VNAV is not available, the VNAV annunciator onthe MAIN MENU is not displayed, and FMS VNAV is assumed.
NOTE: The power--up default is not VNAV selected, and thereforeVNAV is not available until a selection is made.
AD--63973@
VNAV SubmenuFigure 3--6
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137Electronic Flight Instrument System (EFIS)3-10
FMS (FLIGHT MANAGEMENT SYSTEM) VNAV SUBMENU
Selecting FMS VNAV displays the FMS VNAV submenu, shown inFigure 3--7. The pilot can use this menu to cancel VNAV (CNCLVNAV)or return (RTN) to the MAIN MENU.
AD--63974@
FMS VNAV SubmenuFigure 3--7
SNGP (SINGLEPOINT) VNAV SUBMENU
The SNGP VNAV submenu calculates a singlepoint VNAV problem orreturns (RTN) to the MAINMENU. By using the SET knob and pushingthe appropriate button, the crew can enter either the start--of--descentor start--of--climb distance (whichever is appropriate) to (TO) or from(FR) a station, the station elevation (ST EL), and the target altitude(ALT). From these inputs, vertical flight path angle (VANG) and verticalspeed (VS) are calculated and displayed. The operation of the SNGPVNAV differs depending on the NAV source.
D VORNAVSource -- On power--up, the data field under the TO labelcontains dashes. When the TO button is pushed for the first time,awhite box is displayedaround thedashes, as shown inFigure 3--8,signifying that the TO distance is in the set mode.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
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Electronic Flight Instrument System (EFIS)
AD--63975@
VOR SNGP VNAV SubmenuFigure 3--8
Pushing the TO button toggles the data field between TO and FR.Use the SET knob to enter the distance to or from the VOR. TO andFR values cannot be entered at the same time. The most recentlyset value remains while the earlier set value is removed andreplacedwith dashes. TOandFRdistances range from0 to99.9NMwith a resolution of 0.1 NM.
The station elevation (ST EL) must also be entered. When theST EL button is pushed, a white box is displayed around the ST ELdata field, and station elevation can be entered using the SET knob.The setting can range from 0 to 10,000 feet, in increments of 100 feet.
A descend--to or climb--to target altitudemust also be entered, usingthe ALT knob.
Once the pilot has set the data, and if the VNAV problem is valid, acalculated VANG and VS solution is displayed. The maximum validVANG is 6.0, with a resolution of 0.1. The vertical flight path anglecan be adjusted by pushing the VANG button and setting a newangle with the SET knob.
The VS button has no function. The label and value only show thepredicted vertical speed. The predicted vertical speed gives anestimate of the climb or descent rate for the existing airspeed andselected vertical flight path angle. On power--up, or if the VNAVproblem is invalid, dashes are displayed in the VANG and VS datafields.
The VNAV setup data is routed to the flight director by pushing theVNAV button on the flight director mode selector. Once this occurs,the VNAV problem is frozen and any attempt to change the VANG,ST EL, and/or TO/FR data fields is ignored. However, if the selectedaltitude is changed, the VNAV mode can be dropped.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137Electronic Flight Instrument System (EFIS)3-12
D FMS NAV Source -- The operation of SNGP VNAV with an FMSnavigation source is similar to the operation of theVORNAVsource,except the pilot does not have to manually input station elevationbecause the FMS automatically gets it from the database. Stationelevation is used to correct DME slant range information. FMSdistance, which is linear, does not require slant range correction.The ST EL label is replaced with FR, as shown in Figure 3--9.Although TO and FR data fields are both displayed when using anFMSNAV source, TO and FR values cannot be entered at the sametime.
NOTE: Singlepoint FMS VNAV is a customer--selectable optionnot supported by all installations, including the integralFMS.
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FMS SNGP VNAV SubmenuFigure 3--9
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--1373-13
Electronic Flight Instrument System (EFIS)
VSPEED SUBMENU
The VSPEED submenu, shown in Figure 3--10, selects the takeoff speeds(T/O SPEEDS) submenu, landing speeds (LNDG SPEEDS) submenu,or returns (RTN) to the MAIN MENU.
00
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VSPEED SubmenuFigure 3--10
D T/O (Takeoff) SPEEDS Submenu -- The T/O SPEEDS submenu,shown in Figure 3--11, selects and sets three different airspeedreferences (V1, VR, and V2), or returns to the MAIN MENU. Onceselected, the airspeed bugs and their values are displayed on thePFD airspeed display as fixed or moving bugs.
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T/O SPEEDS SubmenuFigure 3--11
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137Electronic Flight Instrument System (EFIS)3-14
On power--up, three dashes are displayed under each of the V1, VR,and V2 labels.
Pushing the V1 button after power--up changes the dashes underV1 to 95 knots and two white boxes appear, one around just the95 knots, and the other around both the 95 knots and the VR label.The two boxes indicate that the VSPEED is active and can bechanged using the SET knob. Values between 40 and 450 knotscan be entered in increments of one knot.
A second push of the button removes the box around the digitalVSPEED value, leaving a single box that indicates the VSPEED is activeand cannot be changed. To activate the V1 value, push any buttonother than V1.
A third push of the V1 button removes the single box, the V1 value,and the V1 reference bug from the PFD airspeed display.
A fourth push returns to the beginning of the sequence.
Setting the value for VR is the same as described for V1, except theinitial value defaults to the value set for V1, or 95 knots if V1 has notbeen set.
Setting the value for V2 is the same as described for V1, except thefirst value defaults to the value set for VR, or 95 knots if VR has notbeen set.
D LNDG (Landing) SPEEDS Submenu -- This submenu, shown inFigure 3--12, is used to select and set two different airspeedreferences, VREF and VAPP, or return to the MAIN MENU. When thissubmenu is selected, the airspeed bugs and their values aredisplayed on the PFD airspeed display as fixed or moving bugs.
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LNDG SPEEDS SubmenuFigure 3--12
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
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Electronic Flight Instrument System (EFIS)
On power--up, three dashes are displayed under the VREF andVAPP labels.
Pushing the VREF button the first time replaces the dashesunder the VREF label with 100 knots and two white boxesappear, one around the default 100 knot VREF speed value, andthe other around both the speed value and VREF label. The twoboxes indicate that the VREF is active and can be changed usingthe SET knob. Values between 40 and 450 knots can be enteredin increments of one knot.
The second push of the button removes the box around thedigital VREF value, leaving a single box that indicates the VREF isactive and cannot be changed. To activate the value, push anybutton other than the VREF button.
A third push removes the single box, the VREF value, and thereference bug from the PFD airspeed display.
The fourth push of the VREF button returns to the beginning ofthe sequence.
Setting the value for VAPP is the same as described for VREF, exceptthat the initial value defaults to the value set for VREF (100 knots) ifVREF has not been set.
INOPERATIVE MENU
If the display controller becomes inoperative, MENU INOP is displayedon the MFD, as shown in Figure 3--13.
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Inoperative MenuFigure 3--13
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PRIMUS 1000 Integrated Avionics System with Integral FMS
A281146137Rev 2 Sep 2002
Electronic Flight Instrument System (EFIS)3-16
Display Controller (DC)The display controller, shown in Figure 314, selects display featureson the PFD. These features include HSI formats, navigation sources,weather radar, and bearing pointer selection.
DISPLAY CONTROLLER WITH TEST BUTTON
AD63980@DISPLAY CONTROLLER WITH PUSH/TEST ROTARY KNOB
PUSHTEST
TEST
Display ControllerFigure 314
HSI (Horizontal Situation Indicator) Button This button togglesthe HSI display between the full compass and arc compass formats.If the weather radar is on and the arc format is selected, weatherreturns are displayed. The powerup default is full compass.
SC/CP (Single Cue/Crosspointer) Button This button togglesbetween single cue or crosspointer ADI command bars.
NOTE: Some versions of the display controller do not have theSC/CP button. Command pointer selection is made at thetime of installation.
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PRIMUS 1000 Integrated Avionics System with Integral FMS
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Electronic Flight Instrument System (EFIS)
IN/HPA Button This button toggles between inHg and hPa unitsof measurement systems. The powerup default is the mode ineffect at powerdown.
GSPD/TTG (Groundspeed/TimeToGo) Button This buttontoggles between groundspeed and timetogo for display on theHSI. The powerup default is groundspeed.
ET (Elapsed Time) Button This button replaces the GSPD/TTGdisplay with a digital clock display. The clock can be started,stopped, and reset with multiple pushes of the ET button.
NAV (Navigation) Button At system powerup, the onsideVOR1/ILS1 (instrument landing system) information is displayed onthe HSI in green. Pushing this button displays the crosssideVOR2/ILS2 information in yellow. This button toggles betweenonside (green) or crossside (yellow) information. The powerupdefault is onside VOR/ILS.
FMS (Flight Management System) Button Pushing this buttondisplays FMS information on the HSI in magenta. Pushing thisbutton again has no effect. The FMS is disengaged by selectinganother navigation mode. LNAV is dropped when the FMS NAVsource is switched.
NOTE: On aircraft with dual FMS installations, pushing the FMSbutton a second time displays crossside FMS data inyellow. The FMS button toggles the displayed FMS databetween onside and crossside information.
BRG (Bearing) Knobs The HSI can display two independentbearing pointers. The selectable bearing sources for each pointerare described in Table 31.
Installation BRG BRG
All Aircraft OFFNAV 1
OFFNAV 2
Single ADF ADF ADFDual ADF ADF1 ADF2
Single FMS FMS FMSDual FMS FMS1 FMS2
Navigation Bearing PointersTable 31
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PRIMUS 1000 Integrated Avionics System with Integral FMS
A281146137Rev 2 Sep 2002
Electronic Flight Instrument System (EFIS)3-18
DIM Controls The DIM control for the PFD is one of two inputsthat contribute to the overall brightness of each electronic display: Ambient light sensed by the photo sensors on the PFD bezel Dimming control setting.
The DIM control sets the intensity for each display.
Turning the PFD DIM control OFF blanks the PFD, and the PFDinformation is displayed on the MFD. If both PFDs are off, thecopilots PFD is displayed on the MFD.
RA (Radio Altitude) Knob Minimums displayed on the PFD canbe adjusted by turning the RA knob as follows: Above 200 feet, in 10 foot increments Below 200 feet, in 5 foot increments The maximum RA value is 999 feet.Rotating the RA knob completely counterclockwise removes theradio altitude from the PFD display.
NOTE: In some configurations this knob functions only as a PFDDimmer. RA functions are replaced by a MINIMUMS knobon the PFD bezel, illustrated in Figure 32.
PUSH TEST Button Pushing this button generates apilotinitiated command to test the system functions. Pressing theinner dimming knob commands a system test and Radio Altimetertest. In some configurations, this will replace the TEST buttondescribed below.
TEST Button Pushing this button activates the display test mode.In the test mode, flags and cautions are displayed along with a checkof the radio altimeter. The following test sequence is displayed: Course select, heading select, radio altitude set, distance, and
groundspeed/timetogo digital readouts are replaced withamber dashes
Attitude (ATT FAIL) and heading (HDG FAIL) displays areflagged
All pointers and scales are flagged All heading related bugs and pointers are removed Flight director command cue is removed Radio altimeter digital readout displays selftest value The comparator monitor annunciates ATT, HDG, and ILS (if ILS
sources are selected on both sides)
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PRIMUS 1000 Integrated Avionics System with Integral FMS
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Electronic Flight Instrument System (EFIS)
The indicated airspeed (IAS) comparator monitor annunciatesIAS in the airspeed window
The altitude comparator monitor annunciates ALT in the altitudewindow
The word TEST is displayed at the top left of the PFD Flight director mode annunciators are removed RA (white) is annunciated.NOTES: 1. A localizer frequency must be tuned on both NAV
receivers to annunciate ILS.2. Selftest is limited to radio altimeter test only in the
air and is inhibited after glideslope or glidepathcapture.
3. The EFIS test is functional only on the ground. Theradio altimeter test is functional at all times exceptduring glideslope capture or track.
4. FD FAIL is not displayed during a pilotinitiatedtest.
5. If the aircraft is on the ground and the DC TESTbutton is pushed longer than 5 or 6 seconds, thesystem enters the initiated test mode. Refer toSection 7, Troubleshooting, for information aboutinitiated testing.
6. When the display controller fails, MENU INOP isdisplayed in the menu section of the MFD.
7. To ensure that the proper source is being used withthe selected flight director modes when sourcesare changed, the EFIS resets flight director modesas listed in Table 32.
SourceSelection
Flight Director ModesReset
NAV NavigationHDG LateralATT All modes and autopilot
disengage
Flight Director Reset ModesTable 32
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137Electronic Flight Instrument System (EFIS)3-20
Remote Instrument Controller
The remote instrument controller, shown in Figure 3--15, selects courseand heading for display on the HSIs. The functional controls are listedbelow.
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Remote Instrument ControllerFigure 3--15
D COURSE Knobs -- The COURSE knobs set the VOR navigationcourse. When the course is set, the remote instrument controllertransmits course data to the display controller, which in turntransmits the data to the IAC for the EFIS and flight directorfunctions. The left COURSE knob controls the pilots side courseselection, and the right COURSE knob controls the copilots courseselection.
Push either the left or right knob PUSH DIR button to center thatsides course arrow display with a TO flag on the HSI. This functionis inhibited when ILS or FMS is displayed.
D HEADING Knob -- The HEADING knob sets the heading bug onboth HSIs. When the heading bug is set, the symbol generatortransmits heading signals to the flight director computer.
Pushing the HEADING knob PUSH SYNC button synchronizes theheading bug to the present heading (HSI lubber line).
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
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Electronic Flight Instrument System (EFIS)
Multifunction Display (MFD) Controller
The MFD controller, shown in Figure 3--16, controls the MFD formatdisplay, symbol generator reversion, MFD dimming, checklist operation,and weather, TCAS, and map inputs. The functions and modes on theMFD are described below.
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Multifunction Display ControllerFigure 3--16
NAVIGATION
TheMAP/PLAN button, RNG switch, and VOR, DAT, and APT buttonscontrol the display mode, data, and map/plan ranges.
D MAP/PLANButton -- This button toggles between the map displayand the plan display. The power--up default is the map display withno weather.
D VOR Button -- This button controls the display of VOR/DMEsymbols and identifiers.
D DAT (Data) Button -- This button controls the display of long rangenavigation symbols and identifiers.
D APT (Airport) Button -- This button controls the display of airportlocations and identifiers.
D RNG (Range) Switch -- This switch increases or decreases theselected range from 5 to 1200 NM in preset steps. However, whenweather (WX) is selected for display, theRNG switch is disabledandthe range is controlled by the weather radar controller.
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PRIMUSR 1000 Integrated Avionics System with Integral FMS
A28--1146--137Electronic Flight Instrument System (EFIS)3-22
COLLISION ADVOIDANCE
D TCAS (Traffic Alert and Collision Avoidance System) Button --The optional TCAS button is used to select or deselect the TCAStraffic display.
WEATHER
D WX (Weather) Button -- This button controls weather radar returnson the MFD map display. If the WX button is pushed when the planview is being displayed, the plan view is replaced with the map view.
DESIGNATOR CONTROLS
The joystick and the SKP, RCL, and ENT buttons control the MFDdisplay.
D RCL (Recall) Button -- Pushing the RCL button when thedesignator is not at its home position (from which it is referenced)recalls the designator to its home position. Pushing RCL when thedesignator is at its home position recalls the designator to theaircraft symbol.
D SKP (Skip) Button -- Pushing this button skips the designatorshome position to the next waypoint. If the designator is at the lastwaypoint in the route when SKP is pushed, the designator returnsto the aircraft symbol. If the designator is offset from its homeposition, the dashed line co