Primus 1000 Excel

AD-67719@

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.


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.


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.

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

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

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

RevisionDate

InsertionDate By

1 Sep 2000 Sep 2000 H

2 Sep 2002 Sep 2002 H

PRIMUSR 1000 Integrated Avionics System with Integral FMS

A28--1146--137Rev 2 Sep 2002 LEP--1

List of Effective Pages


Original 0. . . . Nov 1999Revision 1. . . . Sep 2000Revision 2. . . . Sep 2002

Subheading and Page Revision Subheading and Page Revision

Title Page H 2

Record of Revisions

RR--1/RR--2 H 2


LEP--1 H 2

LEP--2 H 2

LEP--3 H 2

LEP--4 H 2

Table of Contents

TC--1 H 2

TC--2 1

TC--3 1

TC--4 H 2

TC--5 H 2

TC--6 H 2

TC--7 H 2

TC--8 H 2

TC--9 H 2

TC--10 1

Introduction

1--1 H 2

1--2 1

1--3 1

1--4 0

F 1--5/1--6 0

1--7 H 2

1--8 H 2

1--9 H 2

1--10 H 2

System Description

2--1 0

2--2 0

2--3 0

2--4 0

2--5 0

2--6 0

2--7 0

2--8 1

2--9/2--10 0

F 2--11/2--12 H 2

Electronic Flight Instrument System(EFIS)

3--1/3--2 0

F 3--3/3--4 0

3--5 H 2

3--6 H 2

3--7 H 2

3--8 0

3--9 0

3--10 0

3--11 0

3--12 0

3--13 0

3--14 0

3--15 0

3--16 H 2

3--17 H 2

3--18 H 2

3--19 H 2

3--20 0

3--21 0

3--22 0

3--23 0

3--24 0

3--25 0

3--26 0

3--27 0

3--28 0

3--29 0

3--30 0

F 3--31/3--32 H 2

3--33 H 2

H indicates changed, added or deleted pages.F indicates right foldout page with a blank back.


A28--1146--137Rev 2 Sep 2002

List of Effective PagesLEP--2


Electronic Flight Instrument System(EFIS) (cont)

3--34 H 2

3--35 0

3--36 0

3--37 0

3--38 0

3--39 0

3--40 0

3--41 H 2

3--42 0

3--43 0

3--44 0

3--45 0

3--46 0

3--47 H 2

3--48 0

3--49 0

3--50 0

3--51 0

3--52 0

3--53 0

3--54 0

3--55 0

3--56 0

3--57 0

3--58 0

3--59 0

3--60 0

3--61 H 2

3--62 0

3--63 0

3--64 0

3--65 H 2

3--66 0

3--67 0

3--68 0

3--69 0

3--70 0

3--71 0

3--72 0

3--73 0

3--74 0

3--75 0

3--76 0

3--77 H 2

3--78 0

3--79 0

3--80 0

3--81 0

3--82 0

3--83 0

3--84 0

3--85 0

3--86 0

3--87 H 2

3--88 0

3--89 0

3--90 0

3--91 0

3--92 0

3--93 0

3--94 0

3--95 0

3--96 0

3--97 0

3--98 H 2

3--99 0

3--100 0

3--101 0

3--102 0

3--103 0

3--104 0

3--105 0

3--106 0

3--107 0

3--108 0

3--109 0

3--110 0

3--111 0

3--112 0

3--113 0

3--114 0

3--115 0

3--116 0

3--117/3--118 0

Flight Guidance System (FGS)

4--1 0

4--2 0

4--3 0

4--4 0

4--5/4--6 0


A28--1146--137Rev 2 Sep 2002 LEP--3



System Limits

5--1 0

5--2 0

5--3 0

5--4 0

5--5 0

5--6 0

5--7 0

5--8 0

Modes of Operation

6--1 0

6--2 0

6--3 0

6--4 H 2

6--5 H 2

6--6 H 2

6--7 H 2

6--8 H 2

6--9 H 2

6--10 H 2

6--11 0

6--12 0

6--13 H 2

6--14 0

6--15 0

6--16 H 2

6--17 H 2

6--18 H 2

6--19 H 2

6--20 0

6--21 H 2

6--22 0

6--23 0

6--24 0

6--25 0

6--26 0

6--27 0

6--28 0

6--29 0

6--30 0

6--31 0

6--32 0

6--33 0

6--34 0

6--35 0

6--36 0

6--37 0

6--38 0

6--39 0

6--40 0

6--41 0

6--42 0

6--43 0

6--44 0

6--45 0

6--46 0

6--47 0

6--48 H 2

6--49 0

6--50 0

6--51 H 2

6--52 H 2

6--53 H 2

6--54 0

6--55/6--56 0

Troubleshooting

7--1 0

7--2 0

7--3 0

7--4 0

7--5 0

7--6 0

7--7 0

7--8 0

7--9 0

7--10 0

7--11 0

7--12 0

7--13 0

7--14 0

7--15 0

7--16 0

7--17 0

7--18 0

7--19 0

7--20 0

7--21/7--22 0

F 7--23/7--24 0

7--25 0

7--26 0

7--27 0

7--28 0


A28--1146--137Rev 2 Sep 2002

List of Effective PagesLEP--4


7--29 H 2

7--30 H 2

7--31 0

7--32 0

F 7--33/7--34 0

F 7--35/7--36 0

F 7--37/7--38 0

Acronyms and Abbreviations

8--1 1

8--2 1

8--3 1

8--4 1

8--5/8--6 1

Appendix A

A--1 0

A--2 0

A--3 0

A--4 0

A--5 0

A--6 0

A--7 0

A--8 0

A--9 0

A--10 0

A--11 0

A--12 0

A--13 0

A--14 0

A--15/A--16 0

Appendix B

B--1 1

B--2 1

B--3 1

B--4 1

B--5 1

B--6 1

B--7 1

B--8 1

B--9 1

B--10 1

Index

Index--1 H 2

Index--2 H 2

Index--3 H 2

Index--4 H 2

Index--5 H 2

Index--6 H 2

Index--7 H 2

Index--8 H 2

Index--9 H 2

Index--10 H 2

Index--11 H 2

Index--12 H 2


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. . . . . . . . . . . . . . . . . . . . . . . .


A28--1146--137Rev 1

Table of ContentsTC--2

Table of Contents (cont)Section Page

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. . . . . . . . . . . . . . .


A28--1146--137Rev 1



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. . . . . . . . . . . . . . . . . . . . . . . . . .


A281146137Rev 2 Sep 2002



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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


A281146137Rev 2 Sep 2002


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. . . . . . . . . . . . . . . . . . . . . . . . . . .


A281146137Rev 2 Sep 2002


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. . . . . . . . . . . . .


A281146137Rev 2 Sep 2002



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. . . . . . . . . . .


A281146137Rev 2 Sep 2002



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. . . . . . . . . . . . .


A281146137Rev 2 Sep 2002


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. . . . . . . . . . . . . . . . . . . . . . .


A28--1146--137Rev 1


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. . . . . . . .


A281146137Rev 2 Sep 2002 1-1

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)


A28--1146--137Rev 1

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)


A28--1146--137Rev 1 1-3

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


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.


A28--1146--137 Introduction1-5/(1-6 blank)

Cockpit Layout for the Citation ExcelFigure 1--1


A281146137Rev 2 Sep 2002 1-7

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.


A281146137Rev 2 Sep 2002

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

Minneapolis Support CenterHoneywell8840 Evergreen BoulevardMINNEAPOLIS, MN 554336040TEL: 6129574051FAX: 6129574698

Ohio Support CenterHoneywell8370 Dow CircleSTRONGSVILLE, OH 44136TEL: 4402438877FAX: 4402431954

Central Support CenterHoneywell1830 Industrial AvenueWICHITA, KS 67216TEL: 3165228172FAX: 3165222693

Northwest Support CenterHoneywell4150 Lind Avenue SouthwestRENTON, WA 98055TEL: 4252519511TLX: 320033FAX: 4252431954


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

Australia Support CenterHoneywell Ltd.Trade Park DriveTULLAMARINE, 3043, VICTORIAAUSTRALIA (Melbourne)TEL: 61393301411FAX: 61393303042AOG: 61393301411TLX: 37586 HWLTUL

Germany Support CenterAOA Apparatebau Gauting GmbHAmmerseestrasse 4549D82131 GautingGERMANYTEL: 4989893170FAX: 498989317183After Hours AOG Service:01728207300 (in Germany)491728207300 (outside Germany)TLX: 0521702


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


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).


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.


A28--1146--1372-3

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



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.


A28--1146--1372-5

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.



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.


A28--1146--1372-7

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.


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.


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.


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

X

N

H

S 0

CD810

FPLNEXTNAV

A


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

X

N

H

S 0

CD810OPTIONALAT850

ANTENNA

LP850LIGHTNINGSENSORPROCESSOR

System Block DiagramFigure 21


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.


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


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

T V

6

M

G

B

X

N

H

S 0

Cockpit Layout of the EFISFigure 3--1


A281146137Rev 2 Sep 2002 3-5


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).


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


A281146137Rev 2 Sep 2002 3-7


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.


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


A28--1146--1373-9


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



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.


A28--1146--1373-11


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.



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.

AD--63976@

FMS SNGP VNAV SubmenuFigure 3--9


A28--1146--1373-13


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

AD--63977@

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.

AD--63978@

T/O SPEEDS SubmenuFigure 3--11



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.

AD--63979@

LNDG SPEEDS SubmenuFigure 3--12


A28--1146--1373-15


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.

AD--63970@

Inoperative MenuFigure 3--13


A281146137Rev 2 Sep 2002


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.


A281146137Rev 2 Sep 2002 3-17


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


A281146137Rev 2 Sep 2002


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)


A281146137Rev 2 Sep 2002 3-19


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



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.

AD--63982@

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).


A28--1146--1373-21


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.

AD--63984@

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.



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

Primus 1000 Excel

Documents

Transcript of Primus 1000 Excel