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Honeywell PRIMUS 1000 Operation Manual

Integrated avionics system

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Business and Commuter Aviation Systems

Honeywell Inc.

P.O. Box 29000

Phoenix, Arizona 85038-9000

U.S.A.

TO HOLDERS OF SYSTEM MAINTENANCE MANUAL, PUB. NO. A15--1146--063,

PRIMUS

FOR THE CESSNA CITATION ULTRA

Revision No. 2 is a full replacement of the PRIMUS 1000 Integrated Avionics System

for the Cessna Citation Ultra System Maintenance Manual, dated 30 Sep 1994, revised 1 Dec 1999.

Replace your copy of the manual with the attached revision, tabs, and spine.

This revision is a complete reissue and revision bars are not used. This manual has been converted

from WordPerfect to Interleaf publishing software and renamed to System Description and Operation

Manual. Table 3--1 was updated to reflect Honeywell Engineering Bulletin EB7020278, Revision E.

The Record of Revisions page shows Honeywell has put in the manual all revisions through Revision

No. 2, dated 1 Dec 1999.

R

1000 INTEGRATED AVIONICS SYSTEM

REVISION NO. 2 DATED 1 DEC 1999

HIGHLIGHTS

Copyright 1999 Honeywell Inc.

All Rights Reserved

Highlights

Page 1 of 2

1 Dec 1999

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Summary of Contents for Honeywell PRIMUS 1000

Page 1 WordPerfect to Interleaf publishing software and renamed to System Description and Operation Manual. Table 3--1 was updated to reflect Honeywell Engineering Bulletin EB7020278, Revision E. The Record of Revisions page shows Honeywell has put in the manual all revisions through Revision No. 2, dated 1 Dec 1999.
Page 2 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Highlights Page 2 1 Dec 1999 Copyright 1999 Honeywell Inc. All Rights Reserved...
Page 3 Business and Commuter Aviation Systems Honeywell Inc. P.O. Box 29000 Phoenix, Arizona 85038-9000 U.S.A. PRIMUS 1000 Integrated Avionics System Cessna Citation Ultra System Description and Operation Manual TITLE PAGE T-1 REVISED 1 DECEMBER 1999 PUB. NO. A15--1146--063 PRINTED IN U.S.A.
Page 4 (b) (4) of 5 USC 552 and the prohibitions of 18 USC 1905. S1999 Honeywell, PRIMUS, and SPEX are U.S. registered trademarks of Honeywell Inc. All other marks are owned by their respective companies. TITLE PAGE T-2 REVISED 1 DECEMBER 1999 Copyright 1999 Honeywell Inc.
Page 5 FOR HONEYWELL USE ONLY CONTROL NO. REPORT OF POSSIBLE DATA ERROR DATE RECEIVED To help us improve the quality of this publication, Honeywell encourages any report of possible data error. PUBLICATION INFORMATION Volume No. Publication Latest Issue Date (Book, or...
Page 6 NECESSARY IF MAILED IN THE UNITED STATES BUSINESS REPLY MAIL FIRST CLASS PERMIT NO. 3532, PHOENIX, AZ POSTAGE WILL BE PAID BY ADDRESSEE HONEYWELL INC. P.O. BOX 21111 PHOENIX, ARIZONA 85036-9975 U.S.A. ATTN: CUSTOMER SUPPORT QUALITY ADMINISTRATOR AD- 45434@ FOLD...
Page 7 FOR HONEYWELL USE ONLY CONTROL NO. CUSTOMER RESPONSE DATE RECEIVED To help us improve the quality of our publications, Honeywell encourages readers to provide input to the customer-satisfaction survey below. We welcome all comments and recommendations. PUBLICATION INFORMATION Volume No.
Page 8 NECESSARY IF MAILED IN THE UNITED STATES BUSINESS REPLY MAIL FIRST CLASS PERMIT NO. 3532, PHOENIX, AZ POSTAGE WILL BE PAID BY ADDRESSEE HONEYWELL INC. P.O. BOX 21111 PHOENIX, ARIZONA 85036-9975 U.S.A. ATTN: CUSTOMER SUPPORT QUALITY ADMINISTRATOR AD- 45434@ FOLD...
Page 9 MATERIALS HAZARD RATING CODE Honeywell uses the National Fire Protection Association system to identify the different levels of hazards that are caused by the use of a given material. A Hazard Code identifies three effects of a material on a person: health (eat, drink, touch, and breathe), fire (when and how it burns), and reactivity (chemical explosions).
Page 10 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra HEALTH HAZARD RATING IN POSITION 1 Rating Description Effect of Exposure Very bad health Very short exposures could cause DEATH or CRITICAL REMAINING hazard INJURY even after fast medical treatment. Do not breathe the vapor or come in contact with the liquid without approved protection.
Page 11 For each revision, put the revised pages in your manual and discard the superseded pages. Write the revision number and date, date put in manual, and the incorporator’s initials in the applicable columns on the Record of Revisions. The initials HI show Honeywell Inc. is the incorporator. Revision...
Page 12 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page RR--2 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 13 Revision Date in Manual from Manual * The initials HI in this column show Honeywell Inc. has done the task. Page RTR--1 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 14 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page RTR--2 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 15 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra LIST OF EFFECTIVE PAGES Original 0 . . 30 Sep 1994 Revision 1 . . 1 Jul 1995 Revision 2 . . 1 Dec 1999 Subheading and Page Subheading and Page Revision Revision Subheading and Page Revision TC--6...
Page 16 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Subheading and Page Subheading and Page Revision Revision Subheading and Page Revision 1--39 Table of Contents -- Section 1 1--40 TC1--1 TC1--2 Section 2 System Description Section 1 2--1 System Overview 2--2 1--1 1--2 Table of Contents -- Section 2.1 1--3...
Page 17 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Subheading and Page Subheading and Page Revision Revision Subheading and Page Revision 2--1--24 2--1--68 2--1--25 2--1--69 2--1--26 2--1--70 2--1--27 2--1--71 2--1--28 2--1--72 2--1--29 2--1--73 2--1--30 2--1--74 2--1--31 2--1--75 2--1--32 2--1--76 2--1--33 2--1--77 2--1--34 2--1--78 2--1--35 2--1--79...
Page 18 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Subheading and Page Subheading and Page Revision Revision Subheading and Page Revision 2--1--110 Table of Contents -- Section 2.2 2--1--111 TC2--2--1 2--1--112 TC2--2--2 2--1--113 2--1--114 Section 2.2 2--1--115 Attitude and Heading Reference System 2--1--116 2--2--1 2--1--117...
Page 19 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Subheading and Page Subheading and Page Revision Revision Subheading and Page Revision 2--3--9 2--4--30 2--3--10 2--4--31 2--3--11 2--4--32 2--3--12 2--4--33 2--3--13 2--4--34 2--3--14 Table of Contents -- Section 2.5 2--3--15 TC2--5--1 2--3--16 TC2--5--2 Table of Contents -- Section 2.4 TC2--5--3 TC2--4--1...
Page 20 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Subheading and Page Subheading and Page Revision Revision Subheading and Page Revision 2--5--30 2--6--17 2--5--31 2--6--18 2--5--32 2--6--19 2--5--33 2--6--20 2--5--34 2--6--21 2--5--35/2--5--36 2--6--22 2--5--37/2--5--38 2--6--23 2--5--39 2--6--24 2--5--40 2--6--25 2--5--41/2--5--42 2--6--26 2--5--43 2--6--27/2--6--28 2--5--44 2--6--29...
Page 21 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Subheading and Page Subheading and Page Revision Revision Subheading and Page Revision 2--6--61 2--6--105 2--6--62 2--6--106 2--6--63 2--6--107 2--6--64 2--6--108 2--6--65 2--6--109 2--6--66 2--6--110 2--6--67 Table of Contents -- Section 2.7 2--6--68 TC2--7--1 2--6--69 TC2--7--2 2--6--70...
Page 22 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Subheading and Page Subheading and Page Revision Revision Subheading and Page Revision 2--7--31 3--28 2--7--32 3--29 2--7--33/2--7--34 3--30 2--7--35 3--31 2--7--36 3--32 2--7--37 3--33 2--7--38 3--34 2--7--39/2--7--40 3--35 2--7--41 3--36 2--7--42 3--37 2--7--43 3--38 2--7--44 3--39...
Page 23 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Subheading and Page Subheading and Page Revision Revision Subheading and Page Revision 3--70 3--112 3--71 3--113 3--72 3--114 3--73 3--115 3--74 3--116 3--75 3--117 3--76 3--118 3--77 3--119 3--78 3--120 3--79 3--121 3--80 3--122 3--81 3--123...
Page 24 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Subheading and Page Subheading and Page Revision Revision Subheading and Page Revision 3--154 3--196 3--155 3--197 3--156 3--198 3--157 3--199 3--158 3--200 3--159 3--201 3--160 3--202 3--161 3--203 3--162 3--204 3--163 3--205 3--164 3--206 3--165 3--207...
Page 25 Shipping/Handling and Storage 4--15 5--1 4--16 5--2 4--17 4--18 Table of Contents -- Section 6 4--19 TC6--1 4--20 TC6--2 4--21 Section 6 4--22 Honeywell Support 4--23 6--1 4--24 6--2 4--25 6--3 4--26 6--4 4--27 6--5 4--28 6--6 4--29 4--30 Section 7...
Page 26 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Subheading and Page Subheading and Page Revision Revision Subheading and Page Revision Blank Page LEP--12 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 27 INTRO--2 Section 6 - Honeywell Support ........
Page 28 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page Digital Data Buses ............1--22 A.
Page 29 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page E. DC--550 Display Controller ......... . 2--1--10 (1) FULL/WX Button (--607, --707 only) .
Page 30 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page Operation ............. 2--1--24 A.
Page 31 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page Fault Monitoring and Display System Reversionary Modes ....2--1--144 A. EDS 1 (No. 1 Normal) Failure .
Page 32 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page SECTION 2.3 ADZ-850 MICRO AIR DATA SYSTEM ........2- -3- -1 General .
Page 33 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page SECTION 2.4 R R R R PRIMUS WEATHER RADAR SYSTEM ........2- -4- -1 General .
Page 34 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page SECTION 2.5 R R R R PRIMUS II INTEGRATED RADIO SYSTEM ........2- -5- -1 General .
Page 35 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page (2) Pilot’s/Copilot’s (1/2) Annunciator ....... . . 2--5--12 (3) MLS Tune Annunciator .
Page 36 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page SECTION 2.6 FLIGHT DIRECTOR SYSTEM ..........2- -6- -1 General .
Page 37 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page B. Flight Director Lateral (Roll) Channel Functional Operation ....2--6--20 (1) Flight Director Lateral (Roll) Modes Interface ..... . . 2--6--20 (2) Heading (HDG) Select Mode .
Page 38 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page SECTION 2.7 AUTOPILOT/YAW DAMPER SYSTEM ........2- -7- -1 General .
Page 39 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page D. Pitch Axis Autopilot Servo Loop ........2--7--29 (1) SM--200 Elevator Servo Drive and Bracket .
Page 40 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page SECTION 3 SYSTEM INTERCONNECTS ..........3- -1 SECTION 4 MAINTENANCE PRACTICES...
Page 41 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page Procedure for the CD--850 Clearance Delivery Control Head (CDH) ..4--16 A. Removal and Reinstallation Procedures ....... 4--16 B.
Page 42 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page 17. Procedure for MS--560 Mode Selector ........4--31 A.
Page 43 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page 25. Procedure for the SM--200 Servo Drive and SB--201 Drum and Bracket Assembly ............4--44 A.
Page 44 6--6 Honeywell Support Centers ..........
Page 45 Citation Ultra List of Illustrations Figure Page Figure 1--1. PRIMUS 1000 Integrated Avionics System Flow Diagram ..1--9 Figure 1--2. Instrument Panel Component Locations ......
Page 46 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations (cont) Figure Page Figure 2--1--19. VG No.1 (Pilot) Interface ........2--1--34 Figure 2--1--20.
Page 47 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations (cont) Figure Page Figure 2--1--51. MFD Functional Divisions ........2--1--110 Figure 2--1--52.
Page 48 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations (cont) Figure Page Figure 2--4--1. Typical Weather Radar Receiver Transmitter Antenna ... . 2--4--2 Figure 2--4--2. Maximum Permissible Exposure Level Boundary .
Page 49 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations (cont) Figure Page Figure 2--6--6. RI-553 Remote Instrument Controller (--903, Before Phase III) ..2--6--11 Figure 2--6--7. RI-553 Remote Instrument Controller (--907, Phase III) ... 2--6--11 Figure 2--6--8.
Page 50 ....... . 1--7 Table 1--3. Equipment Required but not Supplied by Honeywell ... . 1--8 Table 1--4.
Page 51 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Tables (cont) Table Page Table 2--1--25. Lateral Deviation Scale ........2--1--81 Table 2--1--26.
Page 52 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Tables (cont) Table Page Table 2--4--3. WC-XXX Control Functions ........2--4--8 Table 2--4--4.
Page 53 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Tables (cont) Table Page Table 2--7--2. PC-400 Autopilot Controller Leading Particulars ....2--7--5 Table 2--7--3. RG--204 Rate Gyro Leading Particulars .
Page 54 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page TC--28 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 55 1. General The purpose of this manual is to help you operate, maintain, and troubleshoot the PRIMUS 1000 Integrated Avionics System to the Line Replaceable Unit (LRU) level. Common system maintenance procedures are not presented in this manual. The best established shop and flight line practices should be used.
Page 56 PRIMUS 1000 Integrated Avionics System. This manual is organized into seven (7) sections as follows.
Page 57 Section 6 - Honeywell Support This section briefly describes Honeywell’s worldwide exchange/rental program (commonly referred to as SPEX) for spares. Phone numbers and addresses of Honeywell’s support centers are also included for your convenience. G. Section 7 - System Test and Fault Isolation This section references Honeywell Pub.
Page 58 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 6. Acronyms and Abbreviations The letter symbols for abbreviations are the same as shown in ANSI/IEEE Std 260 and ASME Y1.1, except as identified in the acronyms and abbreviations table. Acronyms and Abbreviations Table Term Definition Alternating Current...
Page 59 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Acronyms and Abbreviations Table (cont) Term Definition Cathode Ray Tube CSDB Commercial Standard Digital Bus Clockwise Direct Current DFGS Digital Flight Guidance System Decision Height DIST Distance Distance Measuring Equipment DTRK Desired Track Display Unit Electronic Display System EEPROM...
Page 60 Citation Ultra Acronyms and Abbreviations Table (cont) Term Definition Heading HDLC High Level Data Link Control HDPH Headphone High Frequency Honeywell Material Number Pressure in Hectopascals Horizontal Situation Indicator Hertz Input/Output Integrated Avionics Computer Indicated Airspeed Integrated Computer Bus IDENT Identifier...
Page 61 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Acronyms and Abbreviations Table (cont) Term Definition Marker Microwave Landing System MPEL Maximum Permissible Exposure Level Most Significant Bit Message Navigation Nautical Mile Non--Return--to--Zero Over Station Sensor PAST Pilot--Activated Self--Test Primary Flight Display Part Number POST Power--On Self--Test...
Page 62 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Acronyms and Abbreviations Table (cont) Term Definition Speed Short Range Navigation SSEC Static Source Error Correction STAB Stabilization Sensitivity Time Control Standard Traffic Advisory True Airspeed Total Air Temperature TCAS Traffic Alert and Collision Avoidance System Touch Control Steering TEMP Temporary...
Page 63 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Acronyms and Abbreviations Table (cont) Term Definition Weather Radar Control Weather WXPD Weather Radar Picture Data XSTC Extended Sensitivity Time Control Yaw Damper Page INTRO--9 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 64 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page INTRO--10 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 65 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TABLE OF CONTENTS - - SECTION 1 Section Page SECTION 1 SYSTEM OVERVIEW ............1- -1 General .
Page 66 Citation Ultra List of Illustrations Figure Page Figure 1--1. PRIMUS 1000 Integrated Avionics System Flow Diagram ... . 1--9 Figure 1--2. Instrument Panel Component Locations ......
Page 67 The PRIMUS 1000 is a completely integrated autopilot, yaw damper, flight director, and Electronic Display System (EDS) (Figure 1--1). The PRIMUS 1000 has a full complement of horizontal and vertical flight director modes. These include all radio guidance modes, Long Range Navigation (LRN) system tracking, and air data oriented vertical modes.
Page 68 (IC bus) between the two IACs. The PRIMUS 1000 is derived from a combination of existing Honeywell systems. Table 1--1 gives the components and part numbers that make up a standard system and Table 1--2 gives the optional equipment.
Page 69 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 1- -1. System Components Honeywell A/C Conn Cessna A/C Conn Reference Reference Designator System Component Part Number Designator VG--14 Vertical Gyro 7000622--901 1/C1 PN375/PN376 FX--220 Flux Valve 2594484 4/C4 UH305/UH306 CS--412 Dual Remote...
Page 70 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 1- -1. System Components (cont) Honeywell A/C Conn Cessna A/C Conn Reference Reference Designator System Component Part Number Designator WU--650 Weather Radar 7008470--822 PN866 Receiver Transmitter Antenna (With EMI Mods) WU--660 Weather Radar...
Page 71 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 1- -1. System Components (cont) Honeywell A/C Conn Cessna A/C Conn Reference Reference Designator System Component Part Number Designator RCZ--851F Integrated 7510700--807 143/C143 PT521 (TAILCONE) Comm Unit PN528 (NOSE) / (Diversity Mode S)
Page 72 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 1- -1. System Components (cont) Honeywell A/C Conn Cessna A/C Conn Reference Reference Designator System Component Part Number Designator IC--600 Integrated Avionics 7017000--81152 C190 J1A--PN364 Computer (Without AP and J1B--PN366 with TCAS Function)
Page 73 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 1- -1. System Components (cont) Honeywell A/C Conn Cessna A/C Conn Reference Reference Designator System Component Part Number Designator IC--600 Integrated Avionics 7017000--81156 C190 J1A--PN364 Computer (Without AP and J1B--PN366 with TCAS Function,...
Page 74 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 1- -3. Equipment Required but not Supplied by Honeywell Designation and Function Description Recommended Source Required Directional Gyro Free/Slave 1/DG SPST toggle, rated at Switch S2 1/2 ampere, inductive Fast Erect Switch S1...
Page 75 AND OPERATION MANUAL Citation Ultra Figure 1- -1. PRIMUS 1000 Integrated Avionics System Flow Diagram Page 1--9/(1--10 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 76 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 1- -2. Instrument Panel Component Locations Page 1--11/(1--12 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 77 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 1- -3. Citation Ultra Component Locations Page 1--13 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 78 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 1- -4. Circuit Breaker Panel Page 1--14 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 79 AND OPERATION MANUAL Citation Ultra 2. System Description The PRIMUS 1000 Integrated Avionics System LRUs, given in Table 1--1 or Table 1--2, have been organized into the following subsystems:  Electronic Display System (EDS)  Attitude and Heading Reference System (AHRS) ...
Page 80 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra A. Electronic Display System (EDS) The EDS has the following LRUs:  DU--870 Electronic Display Units - - Primary Flight Display (PFD) for each pilot - - Multifunction Display (MFD) for both pilots ...
Page 81 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. Attitude and Heading Reference System The Attitude and Heading Reference System (AHRS) is a dual system installation that is made up of the following components:  VG--14A Vertical Gyros No. 1 and No. 2 ...
Page 82 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Air data parameters displayed on the PFD are as follows:  IAS/Mach  Barometric Altitude  Vertical Speed. Air data parameters displayed on the MFD are as follows:  TAS  SAT  TAT. D.
Page 83  IC--600 Integrated Avionics Computer (IAC) No. 1 and No. 2  MS--560 Mode Selector. The PRIMUS 1000 Flight Director System features an integrated avionics computer concept that combines the normal EDS display function with the flight director function. This level of integration supplies a number of benefits over existing systems and greatly simplifies the interface requirements of the flight director function.
Page 84 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra For the flight director to do its job, it looks at the following:  What is the pilot’s desired attitude/position/heading/etc?  What is the aircraft’s actual attitude/position/heading/etc?  If there is a difference between desired and actual data, correct for the difference and control the speed at which the correction takes place.
Page 85  PC--400 Autopilot Controller  SM--200 Servos (Aileron, Elevator, and Rudder). The PRIMUS 1000 system autopilot is a fail--passive design, featuring digital attitude and servo loops. The autopilot supplies aircraft stabilization and tracking of pitch and roll steering commands from the flight director. The autopilot is not aware of which flight director mode(s), if any, are active.
Page 86 This is a small portion of the total information interchange. Most of the information transfer between subsystems is accomplished through the use of digital data buses. The data buses found in the PRIMUS 1000 Integrated Avionics System include the following: ...
Page 87 Citation Ultra A. Radio System Bus (RSB) The Honeywell RSB, as shown in Figure 1--5, is the principal communications network, interconnecting the LRUs in the PRIMUS II Integrated Radio System. All the LRUs in the radio system, except the audio control units, are connected to the RSB. Specific details regarding the operation of the radio system are covered elsewhere in this manual.
Page 88 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra All units connected to the RSB (RMU, IAC, remote NAV unit, etc.) are defined as users. The RSB users are all transformer coupled and impedance--matched to the data bus transmission lines. The bus is a shielded twisted pair, that is differentially driven. Data transmitted onto the bus drives one line more positive, and the other line more negative.
Page 89 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 192 MSEC PER FIELD MESSAGE NO. 0 1 2 3 4 5 18 19 20 21 22 23 0 PRIMARY BUS LEFT--SIDE SECONDARY RIGHT--SIDE SECONDARY EXPANSION TIME SLOT L = LEFT SIDE L R S L R S R = RIGHT SIDE S = SPARE TIME SLOT...
Page 90 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 1--26 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 91 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 1- -4 (Sheet 1). RSB Message Numbers (Normal Mode) WORD 0, 1, 2 3, 4, 5 6, 7, 8 9, 10, 11 12, 13, 14 15, 16, 17 18, 19, 20 21, 22, 23 POS.
Page 92 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 1- -4 (Sheet 2). RSB Message Numbers (Normal Mode) WORD 0, 1, 2 3, 4, 5 6, 7, 8 9, 10, 11 12, 13, 14 15, 16, 17 18, 19, 20 21, 22, 23 POS.
Page 93 Citation Ultra B. Digital Audio Bus The PRIMUS 1000 system uses a digital data bus to carry digital audio information from the remote radio system LRU to the flightcrew’s audio panels. Digitizing the audio offers the advantage of complete independence from grounding problems within the aircraft and the absolute elimination of ground noise pick--up, whine, and cross--talk.
Page 94 Figure 1- -7. Digital Audio Data Sequence C. Commercial Standard Digital Bus (CSDB) The PRIMUS 1000 system uses CSDBs for some data handling. For example, backup VOR/LOC/GS/MKR navigation display data is sent to the Radio Management Units (RMU) from the No. 2 Navigation Unit on CSDB.
Page 95 Citation Ultra D. ARINC 429 The PRIMUS 1000 system uses ARINC 429 data buses for most of the data handling. For example, MADC data is transmitted from/to various units on ARINC 429 buses. The 429 bus system is made up of transmitters and receivers connected by shielded--twisted-wire-pairs.
Page 96 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (3) Data Field -- Bits 11 thru 29 Units, ranges, resolution, refresh rate, and number of significant bits for information transferred are encoded in either Binary Coded Decimal (BCD), or binary notation. Discrete information is also sent over the ARINC 429 bus. In the data field, bits 11 thru 29 are the data bits (see Figure 1--9).
Page 97 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra In the data field, only those bits required to transmit parameter range and resolution are used, and the remaining bits are set to 0 (zero). For example, Figure 1--11 shows the data word for selected course, with an octal label of 024, and a value of 254 degrees, that only requires three characters.
Page 98 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (4) Sign Status Matrix (Bits 30 and 31) When bits 30 and 31 are being used for the Sign Status Matrix (SSM) function, the bits assignments are as shown in Table 1--5. Table 1- -5. Sign Status Matrix Bit Assignments MEANING MEANING...
Page 99 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (6) Waveform Parameters To be compatible with the transformer--coupled data bus, all ARINC 429 messages are Manchester II encoded before being applied to the bus. Unlike Non--Return--to--Zero (NRZ) data, which requires a bandwidth of dc to f (clock frequency).
Page 100 This data bus typically carries ASCII data between the computer and one or more of the LRUs in the PRIMUS 1000 system. An example is: ...
Page 101 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra H. Weather Radar Picture Data (WXPD) The weather radar picture data (WXPD) bus is a 1 MHz dedicated digital bus that interfaces with the Receiver Transmitter Antenna (RTA), MFDs, and PFDs. Picture data video information is supplied from the RTA to the MFDs and PFDs.
Page 102 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 1--40 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 103 SYSTEM DESCRIPTION This section gives a detailed description of the general operation and cockpit displays for the PRIMUS 1000 Integrated Avionics System. The operation and display descriptions of the PRIMUS 1000 Integrated Avionics System subsystems are presented in subsections. Each subsection includes interface diagrams, outline illustrations, and tables of leading particulars for each Line Replaceable Unit (LRU) are also supplied.
Page 104 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--2 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 105 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TABLE OF CONTENTS - - SECTION 2.1 Section Page SECTION 2.1 ELECTRONIC DISPLAY SYSTEM ......... . . 2- -1- -1 General .
Page 106 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page RI--553 Remote Instrument Controller ....... . 2--1--16 (1) Left COURSE Knob .
Page 107 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page C. Primary Flight Display ..........2--1--56 (1) PFD Functional Divisions .
Page 108 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations Figure Page Figure 2--1--1. IC--600 Integrated Avionics Computer (EDS Function) ... . 2--1--3 Figure 2--1--2. DU--870 Display Unit ......... 2--1--5 Figure 2--1--3.
Page 109 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations (cont) Figure Page Figure 2--1--33. BL--871 to DC--550 Interface ........2--1--55 Figure 2--1--34.
Page 110 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Tables Table Page Table 2--1--1. IC--600 Integrated Avionics Computer Leading Particulars ..2--1--3 Table 2--1--2. DU--870 Display Unit Leading Particulars ..... . 2--1--5 Table 2--1--3.
Page 111 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Tables (cont) Table Page Table 2--1--33. Selectable MFD Control Ranges ......2--1--121 Table 2--1--34.
Page 112 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page TC2--1--8 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 113 Citation Ultra SECTION 2.1 ELECTRONIC DISPLAY SYSTEM 1. General The PRIMUS 1000 Integrated Avionics System includes an Electronic Display System (EDS) with the following LRUs:  Two IC--600 Integrated Avionics Computers (IAC)  Three DU--870 Display Units (DU)  Two BL--870 Bezel Controllers for the PFD function ...
Page 114 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The EDS displays the following information in the prime viewing area on both the pilot’s and copilot’s PFD:  Pitch and roll attitude  Indicated airspeed  Barometric altitude  Selected alert altitude ...
Page 115 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 2. Component Descriptions and Locations A. IC- -600 Integrated Avionics Computer (IAC) Two IC--600 Integrated Avionics Computers (IAC) are located in the nose compartment. Figure 2--1--1 shows a graphical view of the IC--600 IAC. Table 2--1--1 gives items and specifications particular to the computer.
Page 116 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -1- -1. IC- -600 Integrated Avionics Computer Leading Particulars (cont) Item Specification Power Requirements (without autopilot):  Continuous ........28 V dc, 50 W (max) ...
Page 117 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. DU- -870 Display Units Three DU--870 Display Units are mounted in the aircraft instrument panel. Figure 2--1--2 shows a graphical view of the DU--870 Display Unit. Table 2--1--2 gives items and specifications particular to the display unit. AD- -29627- -R1@ Figure 2- -1- -2.
Page 118 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The DU--870 Display Unit (DU) is a large format (8--inch by 7--inch), 16--color, high resolution Cathode Ray Tube (CRT) and symbol generator integrated into a single LRU. The DU presents dynamic displays to the pilot as part of the EDS. The DU symbol generator uses two modes to generate the displays: stroke and raster.
Page 119 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. BL- -870 Bezel Controller The BL--870 Bezel Controller mounts on the front of each DU--870 Display Unit that is used as a PFD. Figure 2--1--3 and Figure 2--1--4 show a graphical view of the BL--870 Bezel Controller.
Page 120 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The BL--870 Bezel Controller controls the following PFD display functions: (1) Standard (STD) Button Pushing the STD button selects the standard barometric correction value for the baro set digital readout on the PFD. Barometric correction is displayed in 29.92 inHg if inches of mercury is selected, or 1013 hPa if hectopascals is selected.
Page 121 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra D. BL- -871 Bezel Controller The BL--871 Bezel Controller mounts on the front of the DU--870 Display Unit that is used as an MFD. Figure 2--1--5 shows a graphical view of the BL--871 Bezel Controller. Table 2--1--4 gives items and specifications particular to the controller.
Page 122 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra E. DC- -550 Display Controller The DC--550 Display Controller is mounted in the instrument panel next to the pilot’s and copilot’s PFD. Figure 2--1--6 and Figure 2--1--7 shows a graphical view of the DC--550 Display Controller.
Page 123 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -1- -5. DC- -550 Display Controller Leading Particulars Item Specification Dimensions (maximum):  Height ........2.25 in.
Page 124 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The display controller also supplies a data acquisition function for the following remote--mounted controllers:  PFD Bezel Controllers  MFD Bezel Controllers  MS--560 Mode Selectors  RI--553 Remote Instrument Controllers  Remote mounted Switches. Upon receiving signals from a remote controller, the display controller transmits the acquired information to the IC--600 IAC on a two--wire digital interface bus (DC/IC).
Page 125 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) HSI Button (--611, --723 only) The pilot or copilot uses the HSI button to change the PFD from a full heading compass format to a partial heading compass format. In the full heading compass mode, 360 degrees of heading are displayed.
Page 126 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (8) NAV Button The pilot or copilot uses the NAV button to select short range navigation (NAV) sources for display on the PFD. The power--up default for this selection is on--side NAV source. The toggling sequence is as follows: ...
Page 127 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (12) Radio Altitude (RA) Set Knob (--611, --723 only) The RA control is made up of a knob with a button in the center. The pilot or copilot turns the knob to adjust the RA minimums setting shown as an RA digital readout on the PFD.
Page 128 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra RI- -553 Remote Instrument Controller The RI--553 Remote Instrument Controller is mounted in the bottom of the pedestal. Figure 2--1--8 and Figure 2--1--9 shows a graphical view of the RI--553 Remote Instrument Controller. Table 2--1--8 gives items and specifications particular to the controller.
Page 129 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -1- -8. RI- -553 Remote Instrument Controller Leading Particulars Item Specification Dimensions (maximum):  Height ........1.50 in.
Page 130 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The following paragraphs describe the functions of each knob and button: (1) Left COURSE Knob The left COURSE knob is a rotary knob that controls the course select readout on the pilot’s PFD. The knob output of selected course is also sent to the flight director and autopilot for the VOR mode.
Page 131 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra G. MC- -800 MFD Controller The MC--800 MFD Controller is mounted in the top of the pedestal. Figure 2--1--10 and Figure 2--1--11 show a graphical view of the MC--800 MFD Controller. Table 2--1--9 gives items and specifications particular to the controller.
Page 132 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -1- -9. MC- -800 MFD Controller Leading Particulars Item Specification Dimensions (maximum):  Height ........2.25 in.
Page 133 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) Weather (WX) Button The WX button is used to call up weather radar returns on the MFD map display. When weather is displayed, the map range is controlled by the WC--650 Radar Controller.
Page 134 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (d) Enter (ENT) Button Operation of the ENT button depends upon whether the display is an index page or a checklist page. If the ENT button is pushed when on an index page, a checklist corresponding to the active index line selection is displayed.
Page 135 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) Enter (ENT) Button When the designator is offset, actuation of ENT causes the LAT/LON of the designator to be transmitted to the selected LRN as a requested waypoint. (d) Joystick The joystick gives four--direction control of the designator: up, down, left, and right.
Page 136 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 3. Operation A. Electronic Display System Bus Interfaces Display data is carried by several multi--user, serial asynchronous, half--duplex, digital communication buses. These display/data buses include the following:  A digital display bus output from each IC--600 IAC to each DU ...
Page 137 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -12. Display Bus Interface Page 2--1--25 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 138 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) DC--IC Data Bus The DC--550 Display Controller utilizes a DC--IC bus running at 9600 baud rate to transmit data to the IC--600 IAC. This bus, as shown in Figure 2--1--13, transmits momentary switch inputs and ground/open discretes (2--wire quadrature knob rotation data) to the IC--600 IAC from the controllers and remote switches listed below.
Page 139 (4) IC--600 IAC Reversionary Control The DC and MFD controllers together generate the reversionary modes of the PRIMUS 1000 system. Based on the MC--800 and the DC--550 switch positions given in Table 2--1--10, the IC--600 IAC drives the format on the indicated DUs. See Figure 2--1--15 for the hardware interconnect that supports reversionary control.
Page 140 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -15. Reversionary Interconnect Page 2--1--28 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 141 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -1- -10. Reversionary Control MC- -800 DC- -550 DC- -550 No.2 DU- -870 No. 1 DU- -870 (MFD) DU- -870 No. 2 No.1 Rotary Rotary PFD Dim PFD Dim Knob PFD Dim Knob Port Display...
Page 142 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -16. PRIMUS 650/870 Weather Radar Control and Picture Buses Page 2--1--30 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 143 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -17. PRIMUS 660/880 Weather Radar Control and Picture Buses Weather radar returns can be displayed on the PFD when the WX format is selected by the DC--550 Display Controller and on the MFD when WX is selected from the MC--800 MFD Controller.
Page 144 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Data representing knob and switch selections are encoded in either two’s complement fractional binary notation or binary coded decimal notation and transmitted to the WU--6XX/8XX RTA. The bus is connected by a shielded- twisted--wire pair that carries data in one direction only.
Page 145 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -18. IC to IC Bus/RS- -232 Cabin Interface If the IC--600 IAC No. 1 recognizes that another user is on the bus, it goes into synchronized processing. If no data is found on the bus before the timer expires, the IC--600 IAC enables a transmitter, resets the power--up timer, and listens for bus activity.
Page 146 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. Sensor Interface (1) Attitude Interface Dual VG--14A Vertical Gyros are standard equipment on the Citation Ultra. Either IC--600 IAC displays the cross--side attitude source. (a) VG--14A Vertical Gyro No. 1 The No.1 attitude interface, shown in Figure 2--1--19, consists of on--side (primary) and cross--side (secondary) three--wire, 400 Hz synchro pitch and roll attitude inputs.
Page 147 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) VG--14A Vertical Gyro No. 2 The No.2 attitude interface, shown in Figure 2--1--20, consists of on--side (primary) and cross--side (secondary) three--wire, 400 Hz synchro pitch and roll attitude inputs. On--side and cross--side pitch and roll attitude data are routed internally and separately to the display processor in the IC--600 IAC No.
Page 148 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) Heading Interface Dual C--14D Directional Gyros are standard equipment on the Citation Ultra. Either IC--600 IAC displays the cross--side heading source. (a) C--14D Directional Gyro No. 1 The No.1 heading interface, shown in Figure 2--1--21, consists of on--side (primary) and cross--side (secondary) three--wire, 400 Hz synchro heading inputs.
Page 149 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -21. DG No.1 and No.2 Interface Page 2--1--37 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 150 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (3) Compass Sync/Heading Valid Interface The compass system,shown in Figure 2--1--22, supplies a compass slaving error signal that is displayed on the HSI portion of the PFD to indicate proper slaving of the compass system.
Page 151 AND OPERATION MANUAL Citation Ultra (4) ARINC 429 Radio Interface For the Honeywell Radio System Bus (RSB) interface, refer to Section 1, NOTE: Figure 1--5. The IC--600 IAC radio interface is compatible with GAMA standard ARINC 429. The radio interface accepts radio data transmitted over low--speed ARINC 429 data buses with the word labels given in Table 2--1--12.
Page 152 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -23. VOR/LOC to IC- -600 IAC Interface Page 2--1--40 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 153 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) DME Receiver The DME interface (Figure 2--1--24) into the IC--600 IAC is through two ARINC 429 input ports (primary and secondary) which can be configured for single or dual DME installations. Time--to--Go, ground speed and distance are displayed on the PFD.
Page 154 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) ADF Receiver The ADF radio interface (Figure 2--1--25) into the IC--600 IAC can be configured for single or dual installations. ADF bearing is received in ARINC 429 format. Figure 2- -1- -25. ADF to IC- -600 IAC Interface (d) Radio Altimeter Interface The IC--600 IAC uses the analog signal and does not require the radio altimeter trip points from the discrete switch outputs.
Page 155 These options are defined in Table 2--1--13. Table 2- -1- -13. Configuration Options for Radio Altimeters Radio Altimeters 190J2A-70 190J2A-71 KRA--045 (King) Ground Open AA-300 (Honeywell) Open Ground ALT-55 Ground Ground Not Installed Open Open...
Page 156 (--10mv/ft Aux output) and a 28 V dc valid. Altimeter output range is --20 ft to 2500 ft. Honeywell AA--300 Radio Altimeter The AA--300 radio altimeter supplies an analog radio altitude signal (--4mv dc/ft) and a 28 V dc valid. Altimeter output range is --20 ft to 2500 ft.
Page 157 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (e) Long Range Navigation (LRN) Interface The IC-600 IAC receives LRN data over a GAMA standard ARINC 429 data bus, as shown in Figure 2--1--27. This data is processed by the IC--600 IAC to display flightplan waypoints, waypoint bearing, desired track, cross track deviation, waypoint distance, and time--to--waypoint.
Page 158 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -1- -14. LRN ARINC 429 Output Word Labels Label Description Label Description WPT/OBS Distance Desired Track Time To Go Waypoint Bearing To/From, APP, XTRK, DGR, Crosstrack Distance BISECTOR Distance Vertical Deviation Ground Speed Roll Steering Wind Speed...
Page 159 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -28. Micro Air Data Computer (MADC) Interface Page 2--1--47 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 160 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -1- -16. Air Data ARINC 429 Output Word Labels Label Description Label Description Pressure Altitude Total Air Temperature Baro Altitude Altitude Rate Mach Number Static Air Temperature Calibrated Airspeed Baro correction - HectoPascals (hPa) Max Operating Speed (Vmo) Baro correction - Inches of Mercury (inHg)
Page 161 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The serial data is a block of 13 8--bit words. Bits 0--6 of all bytes contain actual data. Bit 7 of each byte is used for data synchronization. Bit 7 of the first byte is hardwired to +5 V dc to identify the start of message and bit 7 of the remaining bytes are hardwired to ground to identify data.
Page 162 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -30. DC- -550 Display Controller Interface (Copilot) Page 2--1--50 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 163 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) RI--553 Remote Instrument Controller Function The RI--553 Remote Instrument Controller is a three- knob controller that controls selected heading and selected course. Refer to Figure 2--1--31 for a block diagram of the interface. Figure 2- -1- -31.
Page 164 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) MC--800 Multifunction Controller Functions The MC--800 MFD Controller lets the pilot select display formats and modes that change the information shown on the MFD. This includes display dimming, map or plan and weather displays, TCAS traffic advisories, resolution advisories and normal and emergency checklists.
Page 165 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -32. MC- -800 MFD Controller Interface Page 2--1--53 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 166 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (d) BL--870 Bezel Controller Functions The BL--870 Bezel Controller is mounted on the front of each DU in the PFD panel locations, and supplies the functions listed below:  IN/HPA (bezel--button on --921 controllers only) ...
Page 167 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (e) BL--871 Bezel Controller Functions The BL--871 Bezel Controller is mounted on the front of the DU in the MFD position. This controller lets the pilot select and manipulate display menu options. Four different menu pages can be displayed on the MFD; one top level page and three submenus consisting of a vertical navigation parameter set page, a takeoff speed set page, and a landing speed set page.
Page 168 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. Primary Flight Display The Primary Flight Display (PFD) is the single cockpit display where all of the required flight and navigation data is displayed. This data includes the following:  Primary aircraft attitude and heading ...
Page 169 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (1) PFD Functional Divisions The PFD is divided, as shown in Figure 2--1--34, into four functional display areas: ADI display, HSI display, mode annunciations, and air data (airspeed, altitude, and vertical speed displays). MODE ANNUNCIATIONS ALTITUDE...
Page 170 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (a) ADI Display The ADI symbols use a truncated sphere format to display standard attitude information as sensed by the VG--14A Vertical Gyro. When either the pitch or roll data becomes invalid, all scale markings are removed, the attitude sphere turns cyan, and a red annunciation of ATT FAIL appears at the top center portion of the sphere.
Page 171 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) PFD ADI Display and Annunciations The ADI supplies the following display information, as shown in Figure 2--1--35:  Sphere--type attitude display  Glideslope or vertical deviation  Radio altitude  Decision height display (Radio altitude minimums display on phase III aircraft) ...
Page 172 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -1- -18. Vertical Mode Annunciations Annunciator Description Mode Status Go--Around Capture only Glideslope Arm or Capture Altitude Hold Capture only ASEL Altitude Preselect Arm or Capture Indicated Airspeed Capture only MACH Mach Capture only VNAV...
Page 173 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -35. PFD ADI Displays and Annunciators (Before Phase III) Page 2--1--61/(2--1--62 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 174 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra FD MODE ANNUNCIATOR AUTOPILOT STATUS LATERAL VERTICAL (NOTE 2) (NOTE 2) MACH AP ENG ATTITUDE DIGITAL AIR ASEL VNAV AP FAIL SOURCE DATA SOURCE (NOTE 2) LNAV AP TEST ANNUNCIATOR ANNUNCIATOR SYMBOL RADIO TCS ENG GENERATOR ALTITUDE...
Page 175 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) Autopilot Status Messages Autopilot system status is determined by the IC-600 IAC and displayed above (top center) the attitude sphere. During normal autopilot operation a green AP ENG message is displayed. Amber warnings replace this message under appropriate conditions.
Page 176 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (d) Category 2 Excessive Deviation Monitors (Optional) When the CATII mode annunciation is displayed, the ILS excessive deviation monitors are active. If the localizer deviation exceeds the CAT2 window requirements, with radio altitude less than 500 feet, the deviation and scale is changed from green to flashing amber.
Page 177 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra There are reference marks every 5 degrees between 10 and 30 degrees. Red fly-down pitch warning chevrons appear at 45 and 65 degrees pitch up and fly-up warning chevrons appear at 35, 50, and 60 degrees pitch down. The size of the pitch warning chevrons increase as pitch attitude exceeds these values.
Page 178 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The navigation source is selected through buttons on the DC-550 Display Controller. When the vertical deviation is supplied by an FMS, a white FMS annunciation is displayed above the scale. When vertical deviation is supplied by the VNAV computer, a white VNAV is displayed above the scale.
Page 179 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (g) Marker Beacon The marker beacons are displayed below the attitude sphere in the lower right corner. Specific symbols and colors are assigned to the markers as given below: Marker Color O (outer) Blue M (middle) Amber...
Page 180 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (h) Decision Height (DH) Display The radio altitude DH set data is located below the attitude sphere, in the lower right corner, as shown on Figure 2--1--35. The range for DH set is 0 to 2500 feet. The DH value can be set within 10 feet above 200 feet Above Ground Level (AGL), and within 5 feet below that value.
Page 181 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (k) Pitch and Roll Command Cue or Cross Pointers A Command cue or cross-pointers are displayed on each PFD. Always fly the symbolic miniature aircraft to the flight director cue or cross-pointers in order to capture and maintain a desired flightpath.
Page 182 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (o) Attitude and Air Data Source Annunciators The PFD annunciates the following sources of display:  Attitude Gyro (ATT)  Micro Air Data Computer (MADC). When the normal (on-side) source is selected, the mode annunciations are suppressed.
Page 183 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (r) Radio Altitude Minimums Annunciator The RA minimums annunciator, shown in Figure 2--1--36, is displayed under two conditions, armed and captured. The annunciator is armed when the aircraft WOW indicates airborne and RA minimums is valid ( RA ² RA minimums setting + 100 feet for 5 seconds).
Page 184 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (v) Comparison Monitor Annunciators A variety of comparison monitor annunciators are provided. Selected pilot and copilot data inputs are monitored within the IC-600 IAC for reasonableness between on-side and cross-side display data (via the IC Bus). If the difference between the data exceeds a predetermined trip criteria, the miscompare is annunciated in amber on the PFD.
Page 185 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (w) Airspeed Warning Annunciator When the flight director detects an overspeed or underspeed condition, a MAX SPD or MIN SPD warning is displayed in amber to the left of the sphere. The warning remains as long as the flight director determines the overspeed or underspeed condition exists.
Page 186 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (a) Full Compass Format The Horizontal Situation Indicator (HSI) annunciations on the PFD are shown in Figure 2--1--38 or Figure 2--1--39. Compass Sync Annunciator The green compass sync annunciator indicates the state of the compass system in the slaved (AUTO) mode.
Page 187 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -38. HSI Compass Display on PFD (Before Phase III) Page 2--1--77 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 188 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra HEADING HEADING LUBBER DRIFT HEADING SOURCE DIAL SELECT LINE ANGLE ANNUNCIATIONS (NOTE) MAG1 MAG2 NAV SOURCE COMPASS SYNC ANNUNCIATOR ANNUNCIATOR VOR1 VOR2 ILS1 ILS2 DTRK COURSE SELECT/DESIRED TRACK DISPLAY DISTANCE FMS STATUS DISPLAY ANNUNCIATORS BEARING INTG...
Page 189 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -1- -23. Heading Source Annunciators No. 1 PFD No. 2 PFD Cross-Side Cross-Side On-Side Source Source On-Side Source Source Displayed Displayed Not Displayed MAG2 Not Displayed MAG1 Heading Dial (Full) Gyro stabilized magnetic compass information is displayed on the heading dial, that rotates with the aircraft throughout 360 degrees.
Page 190 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra NAV Source Annunciator The annunciation of NAV source appears in the upper right corner of the HSI area. Available navigation sources are VOR 1/2, ILS 1/2, and FMS. The color of the annunciator label changes as a function of the NAV source selected for display.
Page 191 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -1- -24. Bearing Sources Z Z Z Z f f f f Reference VOR1 VOR2 Card ADF1 ADF2 Case Card (Phase III) When the bearing pointer navigation source is invalid or a localizer frequency is chosen, the respective bearing pointer is removed.
Page 192 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra In VOR operation, each dot on either side of the aircraft symbol represents 5-degree deviation from centerline (75 ←⊥). In ILS operation, each dot represents 1-degree deviation from centerline (75 ←⊥). When FMS is the selected navigation source, each dot represents 2.5 nautical miles (NM) of crosstrack error.
Page 193 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 14 Reciprocal Course/Desired Track Pointer The pointer indicates 180 degrees from the course select/desired track pointer. 15 Wind Vector Wind vector information, that comes from the FMS, is displayed in the left of bottom center.
Page 194 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 18 FMS Status Annunciators The following FMS status messages are annunciated to the left of the compass:  Dead Reckoning (DR) - An amber DR indicates DR mode.  FMS Approach (APP) - A cyan APP indicates the FMS is in the approach mode.
Page 195 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra  If the weather radar system is active, weather information is automatically displayed on the partial compass format. Figure 2- -1- -40. HSI Partial Compass Format (Before Phase III) Page 2--1--85 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 196 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD- -50767@ Figure 2- -1- -41. HSI Partial Compass Format (Phase III) (c) Weather Radar Display When selected by the DC-550 Display Controller, weather information is displayed on the partial compass format, as shown in Figure 2--1--41. Each PFD can display independently selected weather information.
Page 197 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The RTA uses hardware and software monitors to detect and identify faults within the radar system. If WX fails, an amber FAIL message appears in the mode annunciation field. Faults are logged into nonvolatile memory by a unique fault code number.
Page 198 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Target Alert (TGT) and Variable Gain (VAR) Annunciators Directly below the WX mode annunciation line is a shared target alert and variable gain status line. The target alert annunciator warns of level 3 targets.
Page 199 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Weather Radar Return Weather radar returns (picture data) appear within the confines of a baseball diamond shaped area, bounded on the outer edge by the compass arc. The returns are color coded as shown in Table 2--1--28. WX picture data is displayed in a 90 degree pattern if sector scan has not been selected on the weather radar controller.
Page 200 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (4) Airspeed Display The airspeed display presents indicated, Mach, and maximum airspeed information. See Figure 2--1--42 for the location of annunciations described in the following paragraphs. Figure 2- -1- -42. Airspeed Display Page 2--1--90 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 201 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (a) Flight Director Speed Target Display and Reference Bug The pilot-adjustable indicated airspeed IAS/Mach target is displayed inside a partial box above the airspeed tape. When the flight director Speed (SPD) mode is engaged, the airspeed target is changed using the PC-400 Autopilot Controller PITCH wheel.
Page 202 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Upon power up, the digital readouts for the set bugs are displayed as amber dashes. As the Vspeeds are set, the digital readouts follow the airspeed reference values entered through the MFD menu option. The digital readouts are removed from the PFD when the first Vspeed value appears on the airspeed tape.
Page 203 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (g) Airspeed Display A rolling digit display of the actual current Indicated Airspeed (IAS) value is contained within a notched T-shaped box, centered on the airspeed scale. This data is a magnification of the digits on the scale and they are readable to within a 1 knot resolution.
Page 204 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (5) Altitude Display The altitude display presents current altitude, altitude preselect, barometric corrected altitude, altitude alert, and altitude trend vector information. See Figure 2--1--43 for the location of annunciations described in the following paragraphs. Figure 2- -1- -43.
Page 205 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (a) Altitude Analog Scale The altitude tape is a moving scale with a fixed pointer. Tick marks are located along the left edge of the scale at 100 foot intervals. The scale markings on the tape are labeled in 200 foot increments below 10,000 feet and in 500 foot increments above 10,000 feet.
Page 206 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) Altitude Digital Display Barometric altitude is displayed in a rolling digit window in the center of the altitude tape (fixed pointer). The left side of the rolling digit window is angled at the same slope as the chevrons.
Page 207 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (h) Low Altitude Awareness At radio altitudes of 550 feet or less, the lower part of the altitude tape linearly changes from a gray raster to brown and the altimeter scale markings are removed.
Page 208 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (a) VS Target Display The pilot-adjustable VS target is displayed inside a white box above the VS analog scale. VS target display range is from -9999 to +9999 fpm and display resolution is 100 fpm. When the VS mode is engaged from either flight director, the vertical speed target is changed using the PC-400 Autopilot Controller pitch wheel.
Page 209 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (f) VS Analog Scale The VS scale is a fixed meter-type display, with a moving pointer that rotates about a point outside of the actual display. The scale is a 134 degree arc with tick marks incremented at 500 fpm intervals.
Page 210 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (h) TCAS Status Message The TCAS status messages are presented to the left of the vertical speed display. When a TCAS RA is displayed, the vertical speed digital display notches the color of the red or green band where the pointer is located. Table 2--1--30 lists the TCAS messages annunciated on the PFD.
Page 211 PFD  Radio altimeter digital readout displays radio altimeter self test value, if radio altimeter supports self test feature; slews to 100 feet for Honeywell radio altimeter  Comparison monitor annunciates ATT, HDG, ILS, and RA  Magenta TEST is annunciated on the PFD ...
Page 212 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TEST ADC2 ATT2 FAIL 200 DH ILS1 FAIL AD- -42432- -R2@ Figure 2- -1- -45. Full Test Mode With Failure Flags (Before Phase III) Page 2--1--102 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 213 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TEST ADC2 ATT2 FAIL 200 RA ILS1 FAIL AD- -53941@ Figure 2- -1- -46. Full Test Mode With Failure Flags (Phase III) Page 2--1--103 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 214 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TEST ADC2 ATT2 FAIL 200 DH FAIL -- -- -- -- AD- -42433- -R2@ Figure 2- -1- -47. ARC Test Mode With Failure Flags (Before Phase III) Page 2--1--104 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 215 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TEST ADC2 ATT2 FAIL 200 RA FAIL -- -- -- -- AD- -53942@ Figure 2- -1- -48. ARC Test Mode With Failure Flags (Phase III) Page 2--1--105 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 216 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (9) PFD Failure Flags and Annunciations The PFD failure flags and annunciations are shown in Figure 2--1--49 or Figure 2--1--50. Refer to the figure for the location of caution and failure annunciations described below: (a) Symbol Generator Reversion Annunciation When selected on the MC-800 MFD Controller, and if the MC-800 control bus is valid, SG reversion is annunciated on the upper left-hand side of the attitude...
Page 217 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra FD FAIL FAIL ILS1 MAG2 FAIL AD- -43227- -R1@ Figure 2- -1- -49. PFD Failure Flags and Annunciations (Before Phase III) Page 2--1--107 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 218 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra FD FAIL FAIL ILS1 MAG2 FAIL AD- -53943@ Figure 2- -1- -50. PFD Failure Flags and Annunciations (Phase III) Page 2--1--108 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 219 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (e) Radio Altitude Failure In the event of a radio altimeter failure (loss of the RA valid or loss of a related I/O), amber dashes replace the radio altitude and decision height digits. (f) Distance Loss of the SRN DME valid or the FMS distance valid causes the distance digits to be replaced by amber dashes.
Page 220 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra D. Multifunction Display The Multifunction Display (MFD) is primarily used for lateral representation of the aircraft’s flight path. The MFD is also used to display various system checklist pages, as required by the flightcrew. In general, control of the MFD is accomplished using the BL-871 Bezel Controller and the MC-800 MFD Controller.
Page 221 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (a) Plan or Map Display The MFD flight path display can be presented in two basic formats: a partial arc (MAP), and a PLAN mode. The primary difference is the base reference or HOME position (the aircraft symbol) and display of current heading.
Page 222 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (d) Display Menu Window The majority of the display control functions are handled by the menus presented in this window. There is a top-level main menu and three submenus. These menus allow selection and setting of altitude select, vertical speeds, and control of the vertical navigation function.
Page 223 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The flight time remaining TO the waypoint is displayed below the IDENT in minutes. The flight time-to-go digits and label are white. Invalid time-to-go is annunciated with amber dashes in place of the digits. Figure 2- -1- -52.
Page 224 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) Flight Plan Data Various map symbols are on the MFD map display. FMS supplied map waypoints, airports and various VOR, VOR/DME, or DME-only navigation aids data are each represented using unique symbols. If available, pilot-defined holding patterns and Top Of Climb/Top Of Descent (TOC/TOD) symbols are a function of the installed FMS.
Page 225 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Airport Symbol The airport symbol is a circle that represents the location of an airport referenced to the present position. The airport symbol is drawn in cyan and the maximum number displayed at any given time is limited to four. If airports are selected for display, a cyan circle is displayed at the right center of the MFD.
Page 226 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (d) Lower Right Display Window The lower right window displays True Airspeed (TAS) and Ground Speed (GSPD) data. True Airspeed (TAS) TAS is displayed with a resolution of 1 knot in the lower right window. This data originates from the MADC, as selected on the on-side PFD.
Page 227 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (g) Heading Select Display A digital readout (cyan) of the heading bug’s current selected value is displayed above the lower left display window. The selected heading is annunciated with a white HDG label above it. Deviation between the heading display and bug, as read against the heading scale, is limited to 1 degree.
Page 228 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (3) Map Mode With Weather Display Weather information from the radar is displayed on the map format, as shown in Figure 2--1--53, only when the radar controller has been turned on and weather has been selected for display with the MC-800 Multifunction Controller.
Page 229 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -53. MFD MAP Mode With Weather Display Page 2--1--119 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 230 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) Weather Radar Mode Annunciator All basic WX modes except weather radar range and Stabilization (STAB) off, are annunciated on line 1. Refer to Table 2--1--32 for details. The RTA uses hardware and software monitors to detect and identify faults within the radar system.
Page 231 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) Target Alert/Variable Gain The annunciations for Target (TGT) alert and variable gain (VAR) are identical to those previously described in paragraph D. (2) (f) 1 and 2. However, when radar gain is selected as a variable, a value proportion to the radar controller gain setting is also displayed.
Page 232 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (g) Heading Select Bug Off Scale Arrow The heading select bug can be rotated off the compass scale when in the Map mode. When the heading select bug is off scale, a cyan arrow is displayed on the outside of the partial compass arc to indicate the shortest direction to the heading select bug.
Page 233 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -55. MFD Failure and Warning Displays (Phase III) (a) IC Fan Failure Warning The status of the cooling fans on both IC-600 IAC’s are also monitored continuously by internal sensors. If the cooling fan(s) fails, a message indicating the most probable cause of the warning is displayed.
Page 234 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) IC Overheat Warning The temperature of both IC-600 IACs are continuously monitored by internal sensors. If the sensor detects extreme temperature increases above a predetermined level, a message indicating the most probable cause of the warning is displayed.
Page 235 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (g) MADC Failure Warning MADC failures are indicated by replacing the TAS numerical values with amber dashes. (h) Weather Radar Failure Weather radar failure is annunciated by placing an amber FAIL in the weather radar mode annunciation box.
Page 236 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -56. MFD PLAN Mode Format The PLAN mode format, shown in Figure 2--1--56, is a north-up presentation of the active flight plan. The active waypoint is displayed in magenta at the center of the display.
Page 237 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (a) Navigation Source and Waypoint Data The navigation source and waypoint data are identical to those previously described for the MFD Map format. (b) Aircraft Symbol The yellow aircraft symbol moves in the display as a function of aircraft present position.
Page 238 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (h) PLAN Format Failures The PLAN mode failures, as shown in Figure 2--1--57, indicate a system malfunction. The following paragraphs describe each failure: Heading Failure Warning Loss of valid heading information removes the aircraft symbol and moves the TO waypoint to the center of the display, if not already there.
Page 239 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -57. MFD PLAN Format Failure Displays (6) Multifunction Display (MFD) Window The checklist and TCAS displays are supplied using a multifunction display window. When either function is selected, the MAP or PLAN navigation displays are slightly repositioned toward the top of the display area.
Page 240 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (a) MFD Checklist Display The checklist window is displayed with either the MFD map or plan mode, as shown in Figure 2--1--58. Normal, abnormal, and emergency checklist information stored in each IC-600 IAC is displayed. The IC-600 IAC stores up to 400 pages of pilot-defined text in non-volatile memory.
Page 241 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -58. Typical Checklist Display (b) TCAS Display Symbols (Optional) The TCAS window is activated in one of two ways:  When TCAS is selected through the MC-800 Multifunction Controller  When the automatic pop up mode is enabled through a TCAS control head, if the checklist is not active.
Page 242 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -1- -59. MFD TCAS Display Symbols The TCAS window, shown in Figure 2--1--59, has the following symbols: No Bearing Display Bearing messages (text) are displayed on two lines (or fields) in the upper right side of the TCAS window whenever the system encounters an RA or TA target that has range, but no bearing information for display.
Page 243 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TCAS Range Ring The range ring boundary is a white full arc (range ring) shown at the limits of the display window. The distance between the arc and the aircraft symbol is displayed in NM to the right of the arc. Since the MC-800 controls map/plan mode range and not TCAS, the range ring is proportional to the MFD selected range.
Page 244 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Traffic Identification  Resolution Advisory - Intruder aircraft entering the warning area, 20 to 30 seconds from the TCAS collision area are represented as a solid red square. This type of traffic results in an RA. ...
Page 245 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Data Tags Associated with each intruder is a data tag indicating the relative or absolute altitude. The data tag can include the vertical speed arrow. When relative altitude of an intruder aircraft is available, a data tag indicating relative altitude is displayed with the corresponding traffic symbol.
Page 246 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 10 TCAS Altitude Display Submodes  Above/Below Target Annunciator - The TCAS above ABV and below BLW target annunciators are displayed below the TCAS message field. Target annunciations are based on relative altitude limits sent by the TCAS computer.
Page 247 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (7) Display Menu Window (a) Top-Level MFD Menu At power-up, the top-level menu is displayed, as shown in Figure 2--1--60. The top level menu page allows selection of the three MFD submenu pages and includes the full--time altitude select set function.
Page 248 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) VNAV Submenu Page The VNAV submenu page, Figure 2--1--61, allows selection of To/From distance, Station Elevation (ST EL), Vertical Angle (VANG), and selected altitude. When pushed, the RTN key always returns the menu display to the top-level MFD menu page, not the previous submenu page.
Page 249 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra To/From (TO/FR) Pushing the bezel button below the TO legend causes a box to be displayed around the dashed distance readout. At this point the pilot has the following three options:  Push another bezel button that moves the box to the next parameter ...
Page 250 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) T/O SPEEDS Submenu Page The T/O SPEEDS submenu, Figure 2--1--62, lets the pilot select and set three different airspeed references; V1, VR, and V2. Airspeed references are displayed as fixed or moving bugs (1, R, and 2) on the PFD airspeed scale. Table 2--1--40 describes the T/O SPEEDS parameters.
Page 251 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -1- -40. T/O Vspeed Data Parameters Parameter Criteria T/O Vspeed Order T/O Vspeed order of V1, VR, V2 is always maintained in value of magnitude V1 can be set equal to but never higher than VR VR can be set equal to but never lower than V1 V2 can never be set any lower than VR V1 Set Start...
Page 252 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (d) LNDG SPEEDS Submenu Page This submenu page, Figure 2--1--63, lets the pilot select and set two different airspeed references (VREF and VAPP). When selected the references are displayed as fixed or moving bugs (RF and AP) on the PFD airspeed scale. Table 2--1--41 gives the LNDG SPEEDS parameters.
Page 253 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Similarly, selecting any one of the other buttons causes two white boxes to appear on the newly selected Vspeed, and a single white box remains around the title and digits of the previously selected Vspeed. Selecting a speed reference that has both boxes displayed causes the outline box and its respective bug to be removed, but the digits remain at the previously set value.
Page 254 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 4. Fault Monitoring and Display System Reversionary Modes The pilot can select which Symbol Generator (SG) is driving the displays and alternate heading, attitude, and air data sources by using the MC-800 MFD Controller MODE switch, DC--550 Display Controller ADC switch, or external cockpit mounted ATT REV, HDG REV, and ADC REV switches.
Page 255 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) Heading Reversionary Using the HDG REV switch, the pilot can select heading sources as given in Table 2--1--43. Table 2- -1- -43. Heading Reversionary Switch Functions Condition Pilot Copilot Power-up MAG 1 MAG 2 First Push MAG 2...
Page 256 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra D. DC-550 Display Controller Failures In the event the No. 1 DC-550 fails, the following defaults are in effect:  Full compass on PFD, WX OFF  SC/CP remains as it was before the DC went invalid ...
Page 257 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra DC-550 Display Controller Power-Up Defaults At power-up (assuming a cold start), the following DC-550 defaults are in effect:  Full compass on PFD, WX OFF  Single Cue (SC) aircraft symbol on PFD ...
Page 258 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--1--148 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 259 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TABLE OF CONTENTS - - SECTION 2.2 Section Page SECTION 2.2 ATTITUDE AND HEADING REFERENCE SYSTEM ......2- -2- -1 General .
Page 260 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations Figure Page Figure 2--2--1. VG-14A Vertical Gyro ........2--2--2 Figure 2--2--2.
Page 261 ATTITUDE AND HEADING REFERENCE SYSTEM 1. General The PRIMUS 1000 Integrated Avionics System installed in the Citation Ultra aircraft includes dual VG-14A Vertical Gyros (VG) as primary attitude references and dual C-14D Directional Gyros (DG) as primary heading references. Either IC-600 Integrated Avionics Computer (IAC) displays the cross-side attitude and heading source.
Page 262 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 2. Component Descriptions and Locations A. VG-14A Vertical Gyro Figure 2--2--1 shows a graphical view of the VG-14A Vertical Gyro. The VG-14As are located in the avionics nose bay of the aircraft. Table 2--2--1 gives leading particulars for the VG-14A.
Page 263 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -2- -1. VG-14A Vertical Gyro Leading Particulars (cont) Item Specification User Replaceable Parts ......None Mating Connector: ...
Page 264 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. C-14D Directional Gyro Figure 2--2--2 shows a graphical view of the C-14D Directional Gyro. The C-14D DGs are located in the avionics nose bay of the aircraft. Table 2--2--2 gives leading particulars for the C-14D DG.
Page 265 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -2- -2. C-14D Directional Gyro Leading Particulars (cont) Item Specification Gimbal Freedom:  Vertical (Azimuth) ......360 deg ...
Page 266 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. CS-412 Dual Remote Compensator Figure 2--2--3 shows a graphical view of the CS-412 Dual Remote Compensator. The CS-412 is located in the avionics cabin bay of the aircraft. Table 2--2--3 gives leading particulars for the CS-412.
Page 267 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra D. FX-220 Flux Valve Figure 2--2--4 shows a graphical view of the FX-220 Flux Valve. The FX-220 is located in the vertical stabilizer of the aircraft. Table 2--2--4 gives leading particulars for the FX-220. AD-32291-R1@ Figure 2- -2- -4.
Page 268 3. Operation A. Introduction The PRIMUS 1000 Digital Flight Guidance System (DFGS) contains dual VG-14A Vertical Gyros to detect actual aircraft pitch and roll attitude, and dual C-14D Directional Gyros (DG) to detect actual aircraft magnetic heading. The directional gyros employ a single CS-412 Dual Remote Compensator and each directional gyro has its own dedicated FX-220 Flux Valve.
Page 269 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra During the initialization cycle, the gyro has an internal monitor looking at the following conditions for validity:  Internal power supply voltages are good  Rotor wheel speed is at least 75% of full speed. When these conditions are satisfied, a relay inside the gyro energizes that pulls the PFD flag.
Page 270 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) Slaved Operation (AUTO Selection) In the slaved mode of operation, the inherent drift properties of the gyro are being corrected by the signal from the FX-220 Flux Valve. By combining the short-term accuracy of the gyro with the long-term accuracy of the flux valve, the system supplies good magnetic heading accuracies between 65 degrees north and south latitudes.
Page 271 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra E. CS-412 Dual Remote Compensator The CS-412 Dual Remote Compensator compensates the flux valve for single-cycle errors created by the aircraft and its electrical systems. This is done by inserting small dc voltages into the flux valve to cancel the effects of the man-made magnetic fields. Each CS-412 can compensate two separate C-14D DGs.
Page 272 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--2--12 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 273 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -2- -5. Pilot’s Attitude and Heading Reference Interface Diagram Page 2--2--13/(2--2--14 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 274 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -2- -6. Copilot’s Attitude and Heading Reference Interface Diagram Page 2--2--15/(2--2--16 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 275 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 4. Fault Monitoring Fault indications are presented on the primary flight and multifunction displays. A. Primary Flight Display (PFD) Figure 2--2--7 shows the fault indications as presented on the PFD. Attitude and heading faults displayed on the PFD are as follows: (1) Loss of Valid Pitch or Roll Information ...
Page 276 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra ATTITUDE FAIL ANNUNCIATOR (RED) LOC HDG 14500 FAIL 14000 FAILED HEADING SOURCE IDENTIFIER .410 200 RA 29.92 IN (AMBER) HDG2 - - - - - - INVALID CRS/DTK 13.1 (AMBER DASHES) HEADING FAIL ANNUNCIATOR (RED) FAIL...
Page 277 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. Multifunction Display (MFD) Figure 2--2--8 and Figure 2--2--9 show the heading fault indications as presented on the MFD with loss of valid heading information. (1) MAP Mode  Amber dash of the heading digital readout ...
Page 278 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra HEADING FAIL ANNUNCIATOR INVALID HEADING (RED) (AMBER DASHES) FMS 1 12.5 NM KDVT 12 MIN FAIL INVALID SELECTED HEADING (AMBER DASHES) - - 2 STAB GSPD BEZEL MENU DISPLAY AREA NOTE: THE DISPLAY SHOWN MAY NOT REPRESENT ACTUAL FLIGHT CONDITIONS. AD- -53712@ Figure 2- -2- -8.
Page 279 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra ’TO’ WAYPOINT TO CENTER OF DISPLAY FMS 1 12.5 NM KDVT 12 MIN 1200 1200 GSPD BEZEL MENU DISPLAY AREA NOTE: THE DISPLAY SHOWN MAY NOT REPRESENT ACTUAL FLIGHT CONDITIONS. AD--53716@ Figure 2- -2- -9. MFD PLAN MODE When Loss of Heading Valid Page 2--2--21 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 280 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--2--22 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 281 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TABLE OF CONTENTS - - SECTION 2.3 Section Page SECTION 2.3 ADZ-850 MICRO AIR DATA SYSTEM ........2- -3- -1 General .
Page 282 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations Figure Page Figure 2--3--1. AZ-850 Micro Air Data Computer ......2--3--2 Figure 2--3--2.
Page 283 ADZ-850 MICRO AIR DATA SYSTEM 1. General The PRIMUS 1000 Integrated Avionics System installed in the Citation Ultra aircraft includes two AZ-850 Micro Air Data Computers (MADC). The MADC takes inputs of static air pressure and pitot pressure, total air temperature, and baro set information. The MADC performs the necessary computations and transmits air data information via ARINC 429.
Page 284 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 2. Component Descriptions and Locations A. AZ-850 Micro Air Data Computer Figure 2--3--1 shows a graphical view of the AZ-850 Micro Air Data Computer (MADC). The MADCs are located in the avionics nose bay of the aircraft. Table 2--3--1 gives leading particulars for the MADC.
Page 285 MS-type threaded fittings and a single 79-pin electrical connector for connection of all electrical inputs and outputs. The pitot/static and outside temperature probes (not supplied by Honeywell) measure air pressure and air temperature. The operation of these probes is covered in the appropriate manufacturer’s literature.
Page 286 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. BL-870 PFD Bezel Controller Figure 2--3--3 shows a graphical view of the BL-870 PFD Bezel Controller. The BL-870 is located as part of the PFDs on the instrument panel. Table 2--3--2 gives leading particulars for the BL-870.
Page 287 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The bezel controller supplies momentary button selection to the MADC of standard barometric correction. As part of the air data system, the BL-870 PFD Bezel Controller BARO Set Knob lets entry of barometric altimeter correction setting through a two-wire grey code signal output to the MADC for rotary knob baro correction control.
Page 288 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 3. Operation A. Pilot Air Data System Figure 2--3--4 shows the pilot’s MADC interface. The inputs to the MADC consist of static and pitot pressure, total air temperature, baro set information, aircraft configuration data, Weight-On-Wheels (WOW) discrete, and a functional test discrete.
Page 289 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -3- -4. Pilot’s MADC Interface Page 2--3--7 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 290 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. Copilot’s Air Data System Figure 2--3--5 shows the copilot’s MADC Interface. The copilot’s system is identical to the pilot’s system, with the following exceptions:  The BARO knob and the STD button are both located on the copilot’s BL-870 PFD Bezel Controller ...
Page 291 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -3- -5. Copilot’s MADC Interface Page 2--3--9 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 292 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. Modes of Operation The AZ-850 MADC has three operating modes: normal, initiated test mode, and maintenance test mode as follows:  The normal mode is for normal aircraft operation.  The initiated test mode is pushed by setting the maintenance panel to test. This test is interlocked with the WOW switch and is inhibited when airspeed is greater than 50 knots.
Page 293 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Operational Range The AZ-850 MADC is capable of supplying airspeed and altitude data over the ranges specified below:  Altitude ..................-1,000 to 60,000 feet  Indicated Airspeed ................40 to 450 knots  True Airspeed ..................50 to 599 knots. G.
Page 294 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -3- -3. AZ-850 MADC Performance Accuracy Parameter Range Accuracy SSEC Barometric Altitude -1,000 to 60,000 ft From -1000 ft to sea level:..15 ft From sea level to 20,000 ft:..20 ft From 20,000 ft to 30,000 ft:..40 ft From 30,000 ft to 50,000 ft:..80 ft From 50,000 ft to 60,000 ft:..150 ft 20,000 fpm...
Page 295 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -3- -4. MADC Functional Test Outputs Parameter ARINC 429 VALUE Pressure Altitude 4,000 ft Baro Corrected Altitude 1,000 ft Altitude Rate 5,000 ft/min Calibrated Airspeed 325 kts True Airspeed 325 kts Mach 0.77 Static Air Temperature...
Page 296 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 4. Fault Monitoring Fault indications are presented on the primary flight and multifunction displays. A. Primary Flight Display (PFD) Figure 2--3--7 shows the fault indications as presented on the PFD. MADC faults displayed on the PFD are as follows. (1) If Barometric Altitude is Invalid ...
Page 297 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra - - - - - - - - - - - - LOC HDG 2250 200 RA - - - -.- - - - IN .- - - - - - M - - - - - - - - VOR1 ADF2 NOTE: THE DISPLAY SHOWN MAY NOT REPRESENT ACTUAL FLIGHT CONDITIONS.
Page 298 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. Multifunction Display (MFD) Figure 2--3--8 shows the fault indication as presented on the MFD. MADC faults displayed on the MFD are the same for the MAP and PLAN formats. If TAS is invalid, the digits are replaced with three amber dashes FMS 1 12.5 NM KDVT...
Page 299 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TABLE OF CONTENTS - - SECTION 2.4 Section Page SECTION 2.4 R R R R PRIMUS WEATHER RADAR SYSTEM ........2- -4- -1 General .
Page 300 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations Figure Page Figure 2--4--1. Typical Weather Radar Receiver Transmitter Antenna ... . 2--4--2 Figure 2--4--2. Maximum Permissible Exposure Level Boundary .
Page 301 WEATHER RADAR SYSTEM 1. General The PRIMUS 1000 Integrated Avionics System installed in the Citation Ultra aircraft includes the PRIMUS 650, 660, 870, or 880 Weather Radar system that is made up of one WU-6XX/8XX Receiver Transmitter Antenna (RTA), one WC-6XX/8XX Weather Radar Controller, and parts of the Electronic Display System (EDS).
Page 302 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 2. Component Descriptions and Locations A. WU- -6XX/8XX Weather Radar Receiver Transmitter Antenna Figure 2--4--1 shows a graphical view of a typical weather radar receiver transmitter antenna (RTA). The RTA is located in the avionics nose bay of the aircraft. Table 2--4--1 gives leading particulars for the RTA.
Page 303 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -4- -1. Weather Radar Receiver Transmitter Antenna Leading Particulars (cont) Item Specification Antenna:  Size ......... 12-inch flat plate radiator ...
Page 304 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -4- -1. Weather Radar Receiver Transmitter Antenna Leading Particulars (cont) Item Specification Receiver (WU-660/880):  IF ......... . . 60 MHz, 1st conversion 10.7 MHz, 2nd conversion ...
Page 305 Electromagnetic Fields 3 kHz to 300 GHz (IEEE C95.1-1991), recommends an exposure level of no more than 6 mW/cm@. Honeywell Inc. recommends operators follow a 6 mW/cm@ standard. Figure 2--4--2 shows MPEL for 10 mW/cm@ and 6 mW/cm@ exposure levels.
Page 306 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. WC- -6XX/8XX Weather Radar Controller Figure 2--4--3 shows a graphical view of various weather radar controllers. The controller is located on the pedestal in the cockpit of the aircraft. Table 2--4--2 gives leading particulars for the controller.
Page 307 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -4- -2. WC-XXX Weather Radar Controller Leading Particulars Item Specification Dimensions (maximum):  Height ........1.875 in.
Page 308 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -4- -3. WC-XXX Control Functions Item Functional Description RADAR A six-position (WC-650/660) or seven-position (WC-870/880) rotary switch that MODE selects the following primary radar modes:  OFF -- Removes power from the system. ...
Page 309 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -4- -3. WC-XXX Control Functions (cont) Item Functional Description SECT Momentary button that selects either full (120 degrees) or reduced (60 degrees) scan sector. Momentary button that enables the REACT. RCT is always selected in the TEST mode.
Page 310 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 3. Operation A. Introduction The PRIMUS Weather Radar System is an X-band digital radar designed for weather detection, analysis, and ground mapping. The display of this information is presented on the PFDs, the MFD, or a combination of these displays. With a single weather radar controller all displays are identical.
Page 311 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. Weather Radar System Functions The WC-XXX Weather Radar Controller selects the modes, range, and antenna tilt. The radar information is displayed on the PFD and/or MFD. Knob and switch selections on the controller are processed, converted to digital format, and transmitted to the WU-XXX RTA.
Page 312 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (3) Rain Echo Attenuation Compensation Technique (REACT/RCT) The REACT/RCT function permits the radar receiver to adjust its own sensitivity automatically to compensate for attenuation losses as the radar pulse passes through weather targets on its way to light other targets. This is done by measuring the intensity of signals, and deducing from them the density, and therefore, the attenuation of the target, and then using this information to adjust the sensitivity.
Page 313 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (6) Test (TST) Test (TST)is used to select the special test pattern to give verification of system operation (refer to Figure 2--4--8 thru Figure 2--4--10). WARNING: OUTPUT POWER IS RADIATED IN TEST MODE. To inhibit the radar from radiating in the test mode, the XMTR ON switch on the RTA is placed OFF (toward the antenna).
Page 314 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -4- -5. Target Alert Range and Depth (cont) Selected Target Target Range (NM) Depth (NM) Range (NM) 25 -- 150 50 -- 150 100 -- 175 200 -- 250 Inactive 5 -- 155 While target alert is functional at the above ranges, it is improbable that a NOTE: realistic target is strong enough to be detected if its range exceeds five times...
Page 315 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra D. Mode and Warning Annunciations The PRIMUS Weather Radar System has a number of mode and warning annunciations. The location of the WX mode and warning annunciation display fields for the PFD and MFD are illustrated in Figure 2--4--6 and Figure 2--4--7.
Page 316 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra E. Hidden Modes The PRIMUS Weather Radar System has a number of hidden modes selected by special control operations. They are not intended for use in normal operations. They are as follows: Stabilization Align Mode Entry: Scan OFF/XMTR OFF/STBY Exit:...
Page 317 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra PRIMUS 650/870 and 660/880 Weather Radar Interface Diagrams Refer Figure 2--4--4 and Figure 2--4--5 for weather radar interface diagrams. (1) Left side VG-14A Vertical Gyro The gyro supplies a two-wire, 50 mv/Deg, output of pitch attitude data and a two-wire 50 mv/Deg output of roll attitude data for antenna stabilization.
Page 318 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--4--18 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 319 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -4- -4. PRIMUS 650/870 Weather Radar System Interface Diagram Page 2--4--19/(2--4--20 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 320 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -4- -5. PRIMUS 660/880 Weather Radar System Interface Diagram Page 2--4--21/(2--4--22 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 321 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 4. Fault Monitoring Fault indications are presented on the PFD and MFD displays. A. Primary Flight Display (PFD) Figure 2--4--6 shows the fault indication as presented on the PFD. Weather (WX) radar failure, regardless of the display format, (FULL/ARC/WX), annunciates an amber WX on the lower left side of the HSI, on the PFD.
Page 322 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. Multifunction Display (MFD) Figure 2--4--7 shows the fault indication as presented on the MFD. Weather radar failure annunciates an amber WX on the lower left side on the MFD. MAG2 FMS 1 12.5 NM KDVT 12 MIN...
Page 323 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. PRIMUS 650/870 Weather Radar Test Mode After an amber WX is annunciated, the fault codes can be read by entering into the TEST mode. Figure 2--4--8 shows the PRIMUS 650/870 MFD Weather Radar Test Mode, and Table 2--4--7 and Table 2--4--8 give the PRIMUS 650 and 870 Fault Codes and Fault Descriptions, respectively.
Page 324 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -4- -7. PRIMUS 650 Fault Codes Fault Code Fault Descriptions Antenna not scanning or scanning incorrectly. Antenna stabilization errors Radar receiver fault Radar signal mixer current out of specification; probably due to defective mixer diodes.
Page 325 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -4- -8. PRIMUS 870 Fault Codes Fault Code Fault Descriptions Analog to Digital Converter Failure, > 1 minute DADC Low Speed 429 Failure for > 4 minutes Airspeed (DADC) of Analog) > 700 kts for > 4 minutes Pulse Pair Processor Failure for >...
Page 326 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2--4--9 shows the PRIMUS 650/870 PFD Weather Radar Test Mode. LNAV 14500 14000 TGT ALERT ON: RED 29.92 IN .410 TGT ALERT OFF: NOISE BAND MAG2 3000 TEST BLACK/CYAN WHITE MAGENTA 1000 YELLOW VOR1 GREEN...
Page 327 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra D. PRIMUS 660/880 Weather Radar Test Mode The PRIMUS 660/880 Weather Radar Systems can provide fault information on one of the following two formats:  Fault codes  Text codes. The selection is made during initial system installation. When a fault occurs (either in-flight or on-ground), an amber WX overrides the mode annunciation on the PFD and/or MFD displays.
Page 328 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) In-Flight TEST Display (with TEXT FAULTS Enabled) The radar is transmitting when TEST is initiated while in the air. NOTE: If the Weight-On-Wheels (WOW) input is not asserted, only the fields that follow are displayed: ...
Page 329 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra FMS 1 12.5 NM KDVT 12 MIN TEST PATTERN WITH TEXT FAULT SHOWN WX RADAR TEST MODE 46.0 TEST ANNUNCIATOR - - 2 GSPD BEZEL MENU DISPLAY AREA NOTE: THE DISPLAY SHOWN MAY NOT REPRESENT ACTUAL FLIGHT CONDITIONS. AD- -53719- -R1@ Figure 2- -4- -10.
Page 330 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -4- -9. PRIMUS 660/880 Fault Codes XREF FAULT FAULT PILOT LINE FAULT DESCRIPTION NAME MAINT TYPE STARTUP CODE 4808 4809 IOP CODE CRC 4810 DSP CODE CRC FLASH CRC RADAR FAIL PULL RTA POWER ON CONFIG TABLE...
Page 331 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -4- -9. PRIMUS 660/880 Fault Codes (cont) XREF FAULT FAULT PILOT LINE FAULT DESCRIPTION NAME MAINT TYPE 4816 DSP RAM 4817 DSP VIDEO RAM POWER ON 4855 DSP WATCHDOG CONTINUOUS MAILBOX RADAR FAIL PULL RTA 4900...
Page 332 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -4- -9. PRIMUS 660/880 Fault Codes (cont) XREF FAULT FAULT PILOT LINE FAULT DESCRIPTION NAME MAINT TYPE 4843 MULTIPLE AFC UNLOCKS 4845 AFC SWEEPING SPOKING CONTINUOUS LIKELY 4929 AFC RX DAC PULL RTA MONITOR 4930...
Page 333 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TABLE OF CONTENTS - - SECTION 2.5 Section Page SECTION 2.5 R R R R PRIMUS II INTEGRATED RADIO SYSTEM ........2- -5- -1 General .
Page 334 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page C. DI--851 DME Indicator ..........2--5--11 (1) RMU Frequency Select Annunciator .
Page 335 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations Figure Page Figure 2--5--1. Typical RM--850 Radio Management Unit ..... . . 2--5--2 Figure 2--5--2.
Page 336 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page TC2--5--4 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 337 II INTEGRATED RADIO SYSTEM 1. General The PRIMUS 1000 Integrated Avionics System installed in the Ultra aircraft includes the SRZ--850 Integrated Radio System. This radio system is also known as the PRIMUS II Integrated Radio System. It is a dual system, with system No. 1 on the left and system No. 2 on the right.
Page 338 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 2. Component Descriptions and Locations A. RM- -850 Radio Management Unit Figure 2--5--1 shows a graphical view of a typical RM--850 Radio Management Unit (RMU). The RM--850s are located in the cockpit instrument panel of the of the aircraft. Table 2--5--1 gives leading particulars for the RMU.
Page 339 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -5- -1. RM- -850 Radio Management Unit Leading Particulars Item Specification Dimensions (maximum):  Height ........5.06 in.
Page 340 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra For ease of operation, the RMU screen is divided into windows. Each window groups the data associated with a particular function of the radio system. Each window (COM, NAV, ATC, ADF, and TCAS) displays the frequency and/or operating mode of the associated function.
Page 341 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra When TCAS--I is installed, the modes are:  ATC ON Replies on Modes A with no altitude reporting  ATC ALT Replies on Modes A and C with altitude reporting  TA ONLY The TCAS traffic advisory mode is enabled When TCAS--I is not installed, the modes are: ...
Page 342 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) Transfer Keys The transfer key, when pushed, flip--flops the active frequency (Top Line) and the preset frequency (Bottom Line) of the COM or NAV window. Pushing both transfer keys simultaneously while on the ground gives entry into the aircraft maintenance mode.
Page 343 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (9) Identification (ID) Key Pushing the ID key initiates the transponder identification response mode. The ID squawk terminates after 18 seconds. The identification response mode can also be activated with the control yoke--mounted push buttons. (10) Page (PGE) Key Pushing the PGE key once changes the RMU display to the RMU Page Menu, except when operating in the Aircraft Maintenance Mode.
Page 344 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. CD- -850 Clearance Delivery Control Head (CDH) Figure 2--5--2 shows a graphical view of the CD--850 Clearance Delivery Control Head. The CD--850 CDH is located in the cockpit instrument panel of the aircraft. Table 2--5--2 gives leading particulars for the CD--850 CDH.
Page 345 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The CD--850 CDH is an alternate or emergency backup capability for tuning the No. 1 VHF COM Module and the No. 1 VHF NAV Receiver Module. This is done on private line data buses that remain operational in the event the primary Radio System Bus (RSB) tuning is not available or if the pilot/operator wishes to override the bus tuning for any reason.
Page 346 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (9) Squelch (SQ) ON/OFF Switch Alternate action button used to toggle COM squelch ON or OFF. (10) Tuning Knobs The knobs change the frequency indicated by the tuning cursor. Large knob adjusts the left two numbers and the small knob adjusts the right two numbers. (11) Normal/Emergency Mode Switch The rotary switch knob gives alternate selection of the Normal and Emergency modes.
Page 347 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. DI- -851 DME Indicator Figure 2--5--3 shows a graphical view of the DI--851 DME Indicator. The DI--851 is located in the cockpit instrument panel of the aircraft. Table 2--5--3 gives leading particulars for the DI--851. Figure 2- -5- -3.
Page 348 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The display type is Dichroic LCD with white characters on a black background. The LCD, legends on the two buttons, and the indicator identifier legend are back lit by electroluminescent lighting. The DME indicator display segments can be tested when CH and SEL are pushed together (all segments turn ON).
Page 349 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra D. AV- -850A Audio Control Unit Figure 2--5--4 shows a graphical view of the AV--850A Audio Control Unit. The AV--850A is located in the cockpit instrument panel of the aircraft. Table 2--5--4 gives leading particulars for the AV--850A.
Page 350 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -5- -4. AV- -850A Audio Control Unit Leading Particulars (cont) Item Specification Mating Connectors:  J1 ......... . . MS27473E20--A41S, HPN2500981--195 ...
Page 351 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (4) Audio Source Control Annunciator indicates that the NAV audio is selected ON. (5) Emergency (EMERG) Mode Annunciator Each control (COM, NAV, ADF, DME) combines the function of switch and volume control. Each source control energizes a particular channel’s audio when unlatched (out position) and de--energizes the audio when latched (in position).
Page 352 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (10) Marker Beacon MUTE Control The marker beacon receiver sensitivity is controlled by rotating the control. Pushing the control activates the marker mute function used to temporarily silence the marker beacon audio (non--latching). When the marker audio is muted, it remains muted as long as the audio level is above a threshold setting.
Page 353 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra E. RCZ- -851(X) Integrated Communications Unit Figure 2--5--5 shows a graphical view of the RCZ--851(X) Integrated Communications Unit. The RCZ--851(X) is located in the avionics nose bay of the aircraft. Table 2--5--5 gives leading particulars for the RCZ--851(X). Figure 2- -5- -5.
Page 354 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -5- -5. RCZ- -851(X) Integrated Communications Unit Leading Particulars (cont) Item Specification User Replaceable Parts:  XC--850 Cluster Module (RCZ--851E/G) ..HPN 7510784--904 ...
Page 355 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra In the RCZ--851F COM Unit, the transponder is the Mode S (non--diversity). In the RCZ--851G COM Unit, the cluster module connector is the same as on the RCZ--851E/F and the transponder is the ATCRBS. A heat sink is associated with the COM unit and is attached to the front of each of the modules to supply a heat path from the internal structure of the box to the front surface where there is adequate radiating surface in the free area.
Page 356 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra RNZ- -850(X) Integrated Navigation Unit Figure 2--5--6 shows a graphical view of the RNZ--850(X) Integrated Navigation Unit. The RNZ--850(X) is located in the avionics nose bay of the aircraft or in some installations the pilot’s RNZ--850(X) is located in the tailcone.
Page 357 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -5- -6. RNZ- -850(X) Integrated Navigation Unit Leading Particulars (cont) Item Specification User Replaceable Parts:  XN--850 Cluster Module (RNZ--850/850B) ..HPN 7510164--921  NV--850 Nav Module (RNZ--850/850B) ... HPN 7510134--831 ...
Page 358 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra G. AT- -860 ADF Combined Sense/Loop Antenna Figure 2--5--7 shows a graphical view of the AT--860 ADF Antenna. The AT--860 is located on the exterior of the aircraft. Table 2--5--7 gives leading particulars for the AT--860.
Page 359 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 3. Operation A. Introduction Figure 2--5--8 shows the integrated Radio System Buses (RSB). Command, control, and data communications between LRUs is via RSB. RCB within the COM and NAV units is on a ribbon cable. Digital audio from the NAV and COM units to the audio control units is via digital audio buses.
Page 360 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Each remote radio unit contains a number of functional modules. These are packaged as follows:  RCZ--851E Integrated Communications Unit - - TR--850 VHF COM Transceiver Module - - XS--852A Diversity Mode S Transponder Module - - XC--850 COM Cluster Module (RSB and Digitized Audio Interface) ...
Page 361 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Frequency and mode control of the radios can be input by the operator from either the RMU, the FMS, or the CDH. The CDH is somewhat limited since it is only connected to COM No.
Page 362 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The first page to appear on the RMU screen is POST in progress. POST lasts 45 seconds. During POST, the following is observed on the horizontal situation indicator display on both PFDs:  Marker indicators and tones annunciate in the order of 3000 Hz (WHITE IM), 1300 Hz (AMBER MM), and 400 Hz (Blue OM) ...
Page 363 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -5- -9. Radio Management Unit Interface Diagram Page 2--5--27/(2--5--28 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 364 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. CD- -850 Clearance Delivery Control Head (CDH) Interface Refer to Figure 2--5--10 for the CD--850 CDH interface diagram. The NAV ACH SHIFT LOAD and NAV ACH CLOCK inputs come from the NAV module and control when the NAV ACH DATA is sent to the NAV module.
Page 365 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -5- -10. CD- -850 Clearance Delivery Control Head Interface Diagram Page 2--5--30 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 366 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra D. DI- -851 DME Indicator Interface Refer to Figure 2--5--11 for the DI--851 DME Indicator interface diagram. All data is input to the indicators via the RSB. The indicators are receive only devices; there are no outputs.
Page 367 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra E. AV- -850A Audio Control Unit Interface Refer to Figure 2--5--12 for the AV--850A Audio Control Unit interface diagram. The AV--850A Audio Control Unit receives digitized audio from the remote units via two high--speed digital audio buses.
Page 368 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Reference Figure 2--5--12 (sheet 1) for the following:  Microphone and PTT inputs and outputs  Interphone audio and PTT  Emergency analog audio inputs from COM1 and NAV 1  Speaker outputs ...
Page 369 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--5--34 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 370 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -5- -12 (Sheet 1). AV- -850A Audio Control Unit Interface Diagram Page 2--5--35/(2--5--36 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 371 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -5- -12 (Sheet 2). AV- -850A Audio Control Unit Interface Diagram Page 2--5--37/(2--5--38 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 372 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra RCZ- -851 (X) Integrated Communication Unit Interface Refer to Figure 2--5--13 for the RCZ--851 (X) Integrated Communication Unit interface diagram. The common unit connections shown include power, ground, and RSB, all of which have been covered in previous sections.
Page 373 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--5--40 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 374 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -5- -13. RCZ- -851 (X) Integrated Communications Unit Interface Diagram Page 2--5--41/(2--5--42 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 375 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra G. RNZ- -850/850B Integrated Navigation Unit Interface Refer to Figure 2--5--14 for the RNZ--850/850B Integrated Navigation Unit interface diagram. The common unit connections shown include power, ground, and RSB, all of which have been covered in previous sections.
Page 376 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--5--44 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 377 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -5- -14. RNZ- -850/850B Navigation Unit Interface Diagram Page 2--5--45/(2--5--46 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 378 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 4. Fault Monitoring Fault indications are shown on the PFD and MFD displays and RMU. Refer to Figure 2--5--15 thru Figure 2--5--17. A. Primary Flight Display (PFD) Figure 2--5--15 shows the fault indication as presented on the PFD. Loss of valid vertical deviation from the NAV receiver causes the following to occur: ...
Page 379 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 29.92 IN - - - - - - - - - - - - Figure 2- -5- -15. PFD Radio System Failure Indications Page 2--5--48 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 380 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. Multifunction Display (MFD) Figure 2--5--16 shows the fault indication as presented on the MFD. Loss of valid distance information from the DME Module causes the following to happen:  Removal of the Morse identifier ...
Page 381 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. Radio Management Unit (RMU) Display Figure 2--5--17 shows the fault indication as presented on the RMU. Any failure of a module causes the RMU to remove the frequencies or operating commands associated with that particular function and replace them with dashes.
Page 382 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TABLE OF CONTENTS - - SECTION 2.6 Section Page SECTION 2.6 FLIGHT DIRECTOR SYSTEM ..........2- -6- -1 General .
Page 383 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page B. Flight Director Lateral (Roll) Channel Functional Operation ....2--6--20 (1) Flight Director Lateral (Roll) Modes Interface ..... . . 2--6--20 (2) Heading (HDG) Select Mode .
Page 384 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations Figure Page Figure 2--6--1. IC-600 Integrated Avionics Computer (FD Function) ....2--6--4 Figure 2--6--2. MS-560 Mode Selector (Before Phase III) .
Page 385 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page TC2--6--4 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 386 Other flight director modes can be armed to automatically become active at the proper time. The PRIMUS 1000 FGS is a split processor system. The primary processor is used for the Electronic Flight Instrument System (EFIS) and flight director functions. The secondary processor supplies servo control of the aileron, elevator, rudder, and elevator trim.
Page 387 Flight director switching allows either the pilot’s or copilot’s flight director to be coupled to the PRIMUS 1000 autopilot. This is accomplished using the remote-mounted FD1/FD2 button. The pilot’s IC-600 IAC controls the state of the flight director couple switching.
Page 388 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. Flight Director Mode Annunciation The coupled flight director annunciates the selected armed mode on its on-side PFD. When the mode is captured, the on--side PFD annunciates capture. The cross--side flight director operates independently from the coupled flight director. If the on-side SG reversion function is pushed on the coupled side, the flight director modes are reset.
Page 389 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 2. Component Descriptions and Locations A. IC-600 Integrated Avionics Computer Two IC-600 Integrated Avionics Computers (IAC) are located in the nose compartment. Figure 2--6--1 shows a graphical view of the IC-600 IAC. Table 2--6--1 gives items and specifications particular to the computer.
Page 390 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -6- -1. IC-600 Integrated Avionics Computer Leading Particulars (cont) Item Specification Power Requirements (with autopilot):  Continuous ......28 V dc, 50 W (max) ...
Page 391 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Data used to compute guidance commands are consistent with that displayed on the PFD. This data includes the following:  Displayed heading and heading flag valid  Selected course and course error  Selected heading and heading error ...
Page 392 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. MS-560 Mode Selector Figure 2--6--2 and Figure 2--6--3 shows a graphical view of the MS-560 Mode Selector. The mode selector is mounted in the glare shield in front of each pilot. Table 2-6-2 gives items and specifications particular to the mode selector.
Page 393 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -6- -2. MS-560 Mode Selector Leading Particulars (cont) Item Specification Mating Connector:  J1 ......... . . M24308/2-283F with locking hardware M24308/125-9 and hood M85049146-2-3 Mounting .
Page 394 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. DC-550 Display Controller The DC-550 Display Controller is mounted in the instrument panel next to the pilot’s and copilot’s PFD. Figure 2--6--4 and Figure 2--6--5 shows a graphical view of the DC-550 Display Controller.
Page 395 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -6- -3. DC-550 Display Controller Leading Particulars Item Specification Dimensions (maximum):  Height ........2.25 in.
Page 396 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra D. RI-553 Remote Instrument Controller The RI-553 Remote Instrument Controller is mounted in the bottom of the pedestal. The RI-553 Remote Instrument Controller lets the pilot select HEADING and COURSE references for lateral flight director modes. The front panel has a single HEADING knob and two COURSE knobs.
Page 397 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -6- -4. RI-553 Remote Instrument Controller Leading Particulars Item Specification Dimensions (maximum):  Height ........1.50 in.
Page 398 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra E. PC-400 Autopilot Controller The PC-400 Autopilot Controller gives the flight director PITCH wheel inputs for specified vertical flight director modes and a low bank angle selection for the heading select mode only. The other functions of the controller have to do with autopilot and yaw damper operation and are discussed in the applicable chapters.
Page 399 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -6- -5. PC-400 Autopilot Controller Leading Particulars (cont) Item Specification User Replaceable Parts:  Knob, Turn ........HPN 337136-1 ...
Page 400 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AG-222 Accelerometer The AG-222 Accelerometer, located in the nose compartment, is a closed-loop, force- rebalanced device with a linear output proportional to the aircraft’s vertical acceleration. The output is equal to 1.5V/g. The AG-222 receives 15 V dc power from its respective IC-600 IAC.
Page 401 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -6- -6. AG-222 Accelerometer Leading Particulars (cont) Item Specification User Replaceable Parts ......None Mating Connector .
Page 402 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) Glideslope (GS) CAP The following conditions are necessary for GS capture:  The localizer mode is either capture or track  The vertical beam sensor has tripped  GS deviation is less than 20 mV. (3) GS Track GS track occurs after the flight director has captured the vertical path and is tracking the beam.
Page 403 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (6) Localizer (LOC)/Back Course (BC) CAP LOC and BC capture occurs when the following conditions are met:  Lateral Beam Sensor has tripped  Beam deviation is less than 35mV. (7) LOC/BC TRACK Localizer and back course track signify the aircraft being on beam center and crosswind washout correction can take place.
Page 404 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (11) VOR Track VOR track occurs as the aircraft is established on beam center and the following conditions are met:  VOR capture plus 90 seconds  Lateral deviation rate is less than 50 feet/second ...
Page 405 IC-600 IAC. The default value of TAS is set for the approach speed region of flight. (d) Short Range Navigation (SRN) Radios (Not Honeywell) The SRN radios supply an RSB output of VOR and Localizer deviation data, as well as DME and marker beacon data to the IC-600 IAC.
Page 406 AND OPERATION MANUAL Citation Ultra (f) Radio Altimeter (Not Honeywell) The radio altimeter provides an analog output of absolute altitude above the terrain. This signal is used by the flight director to gain program the localizer signal. Gain programming is required, due to the directional qualities and beam convergence characteristics of the localizer antenna.
Page 407 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (k) IC-600 Integrated Avionics Computer (IAC) The IC-600 IAC performs the following, as a function of which lateral mode is active. Heading Select Mode When the heading select mode is pushed, the flight director processor in the IC-600 IAC compares actual aircraft heading against desired aircraft heading, as determined by the position of the heading select bug on the coupled side PFD.
Page 408 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Low Bank Submode The low bank submode lets the pilot select reduced-bank angle limits for the heading select mode. The mode is selected by pushing the low bank button (BNK) on the PC-400 Autopilot Controller. When active, the bank angle limit is reduced from 27.5 to 14 degrees.
Page 409 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra With the autopilot engaged, the flight director processor generates the commands as stated above, but sends them to the autopilot for automatic flight path steering. On the coupled PFD, the flight director command bar can move a little out of center and then return.
Page 410 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra As the aircraft approaches the selected course, the localizer error signal gets smaller in magnitude and the roll attitude signal now commands the pilot to roll the aircraft to a wings level condition. With the aircraft tracking the localizer beam, the following conditions exist: ...
Page 411 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--6--26 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 412 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -10 (Sheet 1). Flight Director Lateral Mode Interface - - Pilot’s Side Page 2--6--27/(2--6--28 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 413 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -10 (Sheet 2). Flight Director Lateral Mode Interface - Pilot’s Side Page 2--6--29 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 414 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -10 (Sheet 3). Flight Director Lateral Mode Interface - Pilot’s Side Page 2--6--30 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 415 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -11 (Sheet 1). Flight Director Lateral Mode Interface - Copilot’s Side Page 2--6--31/(2--6--32 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 416 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -11 (Sheet 2). Flight Director Lateral Mode Interface - Copilot’s Side Page 2--6--33 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 417 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -11 (Sheet 3). Flight Director Lateral Mode Interface - - Copilot’s Side Page 2--6--34 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 418 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The descriptions and figures in this section assume the pilot’s flight director is master. The PFD figures reflect the phase III configuration. (2) Heading (HDG) Select Mode The HDG select mode is used to intercept and maintain a magnetic heading reference.
Page 419 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (3) Heading Select Mode Engage/Reset/Disengage Logic (a) Engage Logic Required valids are as follows:  Flight director  On--side VG--14A  On--side C--14D. With the above conditions met, pushing either the:  HDG button on the MS--560 Mode Selector. ...
Page 420 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (4) VOR (NAV) Mode See Figure 2--6--12 thru Figure 2--6--18 and Table 2--6--8. The VOR mode provides for automatic intercept, capture and tracking of a selected inbound or outbound VOR radial, using the selected VOR navigation source displayed on the coupled PFD.
Page 421 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50799@ Figure 2- -6- -13. VOR (NAV) Mode Armed When reaching the LBS trip point, the flight director automatically drops the heading select mode and switches to the VOR capture phase. The following is observed on the PFD: ...
Page 422 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra SELECTED VOR STATION SELECTED COURSE TYPICAL CAPTURE POINT AD- -50801@ Figure 2- -6- -14. VOR Capture Pictorial When the course select pointer was set on the PFD, using the appropriate course knob on the RI--553 Remote Instrument Controller, the course select error signal was established.
Page 423 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50802@ Figure 2- -6- -15. VOR (NAV) Mode Capture When flying a VOR intercept, the optimum intercept angle should be 45 degrees or less. If the intercept angle is greater than 45 degrees, course cut limiting can occur. The course cut limiter functions primarily when approaching the selected VOR radial at an intercept angle greater than 45 degrees and at a high rate of speed.
Page 424 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra SELECTED SELECTED VOR STATION COURSE SECOND HEADING CHANGE TYPICAL CAPTURE POINT INITIAL GREATER THAN 2 DOTS ON HSI HEADING CHANGE AD--42493@ Figure 2- -6- -16. VOR Course Cut Limiting When the aircraft satisfies VOR track conditions, the course error signal is removed from the lateral steering command.
Page 425 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50804@ Figure 2- -6- -17. VOR Track As the aircraft approaches the VOR station, it enters a zone of unstable radio signal. This zone of confusion radiates upward from the station in the shape of a truncated cone.
Page 426 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra When over the VOR station (Figure 2--6--18), the flight director accepts and follows course changes, up to 90 degrees. The navigation (VOR) mode is canceled by the following:  Pushing the NAV button on the coupled MS--560 Mode Selector ...
Page 427 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (5) VOR Approach (VAPP) Mod The VOR approach mode is set up and flown in a manner similar to enroute VOR. However, instead of selecting the mode with the NAV button on the MS--560 Mode Selector, the APR button is pushed.
Page 428 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (6) VOR/VAPP Engage/Reset/Disengage Logic (a) VOR ARM Engage Logic Required valids are as follows:  Flight Director  On--side VG--14A.  On--side C--14D. With the above conditions good, and VOR selected as the NAV source on the on--side DC--550 Display Controller, pushing the NAV button on the coupled MS--560 Mode Selector arms the VOR mode.
Page 429 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) VOR Arm Disengage Logic The VOR arm mode automatically disengages, if any of the following conditions occur:  Flight Director not valid  On--side VG--14A or C--14D not valid  Tune to a localizer frequency ...
Page 430 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (f) VOR Capture Disengage Logic The VOR mode automatically disengages if any of the following conditions occur:  Flight Director not valid  On--side VG--14A or C--14D not valid  Tune to a localizer frequency ...
Page 431 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra VOR OSS Reset Logic The following conditions reset VOR OSS mode:  Selecting go--around  Any other lateral mode active  Pushing the NAV button on the coupled MS--560 Mode Selector  NAV source change ...
Page 432 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (7) Localizer (NAV), Localizer Approach (APR), and Back Course (BC) Modes See Figure 2--6--19 thru Figure 2--6--28 and Table 2--6--9. The localizer mode provides for automatic intercept, capture, and tracking of the front course localizer beam to line up on the centerline of the runway in use.
Page 433 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50809@ Figure 2- -6- -20. Localizer (NAV) Mode ARM With the aircraft approaching the selected course intercept, as shown in Figure 2--6--21, the LBS is monitoring localizer beam deviation, beam rate, and TAS. At the computed time, the LBS trips and captures the localizer signal.
Page 434 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra LOCALIZER INBOUND COURSE RUNWAY AD- -50810@ Figure 2- -6- -21. Localizer Capture Pictorial The flight director processor generates the proper roll command to bank the aircraft to capture and track the selected localizer signal. When flying a localizer intercept, the optimum intercept angle is 45 degrees NOTE: or less.
Page 435 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50811@ Figure 2- -6- -22. Localizer Capture When the aircraft meets the localizer capture conditions, the course error signal is removed from the lateral calculations. This leaves localizer gain programming (LOC II) to track the localizer signal, as shown in Figure 2--6--23, and to compensate for localizer beam standoff in the presence of a crosswind.
Page 436 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50813@ Figure 2- -6- -24. Localizer Track The back course (BC) mode automatically intercepts, captures, and tracks the back course localizer signal, as shown in Figure 2--6--25. When flying a back course localizer approach, glideslope capture is automatically inhibited. The BC localizer approach is set up and flown identical to a front course localizer approach, with the following differences: ...
Page 437 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra LOCALIZER INBOUND COURSE RUNWAY TYPICAL CAPTURE POINT AD- -50814@ Figure 2- -6- -25. Back Course Mode Pictorial With the aircraft outside the normal back course localizer capture limits, the PFD annunciates BC in white and HDG in green as shown in Figure 2--6--26. AD--50815@ Figure 2- -6- -26.
Page 438 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra At BC capture, the PFD annunciates BC in green, as shown in Figure 2--6--27. The BC annunciation is enclosed in a white box for 5 seconds. AD--50816@ Figure 2- -6- -27. Back Course Capture At BC capture, the IAC flight control function generates a roll command to capture and track the back course signal, as shown in Figure 2--6--28.
Page 439 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50817@ Figure 2- -6- -28. Back Course Track The BC mode is cancelled by any one of the following:  Pushing the NAV button on the coupled MS--560 Mode Selector  Pushing the APR button on the coupled MS--560 Mode Selector (Before Phase III) ...
Page 440 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The Localizer Approach mode is set up and flown identically to the localizer mode with the following differences:  On the coupled MS--560 Mode Selector, the APR button is pushed instead of the NAV button.
Page 441 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (8) Localizer/Back Course Mode Engage/Reset/Disengage Logic (a) LOC/BC ARM Engage Logic Required valids are as follows:  Flight Director  On--side VG--14A Vertical Gyro  On--side C--14D Directional Gyro  On--side displayed NAV source. With the above conditions satisfied and ...
Page 442 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) LOC/BC Arm Disengage Logic The LOC/BC arm mode automatically disengages if any of the following conditions occur:  Flight director not valid  On--side VG--14A not valid  On--side C--14D not valid ...
Page 443 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (f) LOC/BC Capture Disengage Logic The LOC/BC mode automatically disengages if any of the following conditions occur:  Flight Director not valid  On--side VG--14A or C--14D not valid  Not tuned to a localizer frequency ...
Page 444 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) Immediate FMS Capture Pushing the NAV button on the coupled MS--560 Mode Selector causes the flight director LNAV mode to annunciate in green on the coupled PFD. The flight director function immediately captures the desired track. DESIRED TRACK CAPTURE DESIRED TRACK...
Page 445 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50807@ Figure 2- -6- -30. Long Range Navigation Tracking Page 2--6--62 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 446 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The LNAV mode is canceled by the following:  Pushing the NAV button on the coupled MS--560 Mode Selector  Selecting go--around  Selecting another navigation source on the DC--550 Display Controller  Selecting another heading source on the coupled PFD ...
Page 447 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) LNAV Capture Reset Logic Reset means that a condition has occurred that has canceled the mode, but it can be re--engaged. LNAV capture is automatically reset if any of the following conditions occur: ...
Page 448 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. Flight Director Vertical (Pitch) Channel Functional Operation (1) Flight Director Vertical (Pitch) Modes Interface Figure 2--6--31 shows LRU interface for pilot’s side flight director vertical modes. Figure 2--6--32 shows LRU interface for copilot’s side flight director vertical modes. The function of each LRU for each vertical mode is discussed in the following paragraphs: (a) VG--14A Vertical Gyro...
Page 449 The navigation receiver supplies an ARINC 429 output of GS deviation data, as well as marker beacon data. (g) Long Range Navigation (LRN) Unit (Not Honeywell) The LRN unit supplies an ARINC 429 composite steering command output to the IC--600 IAC. Gain programming for the composite steering command is done in the LRN unit.
Page 450 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Vertical Speed Hold The IC--600 IAC receives vertical speed information from the on--side AZ--850 MADC. This vertical speed information becomes the reference vertical speed in the IC--600 IAC when the mode is engaged. The vertical speed reference is changed as a function of moving the PITCH wheel on the PC--400 Autopilot Controller, or by pushing and holding the TCS button while flying the aircraft manually to a new vertical speed...
Page 451 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Altitude Preselect Mode The IC--600 IAC receives inputs of uncorrected pressure altitude, baro corrected pressure altitude, and pilot selected altitude. The flight director processor combines the pressure altitude inputs through complimentary filtering to obtain more precise barometric altitude data. In the IC--600 IAC, the difference between actual aircraft altitude and selected aircraft altitude (ASEL) is defined as the altitude error signal.
Page 452 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra ILS Approach Mode When the ILS approach mode (APR) is armed, the flight director processor looks at TAS, vertical speed, and glideslope deviation to determine when to capture the glideslope. This is accomplished by the Vertical Beam Sensor (VBS).
Page 453 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--6--70 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 454 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -31 (Sheet 1). Flight Director Vertical Mode Interface - Pilot’s Side Page 2--6--71/(2--6--72 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 455 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -31 (Sheet 2). Flight Director Vertical Mode Interface - Pilot’s Side Page 2--6--73 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 456 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -31 (Sheet 3). Flight Director Vertical Mode Interface - Pilot’s Side Page 2--6--74 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 457 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -32 (Sheet 1). Flight Director Vertical Mode Interface - Copilot’s Side Page 2--6--75/(2--6--76 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 458 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -32 (Sheet 2). Flight Director Vertical Mode Interface - Copilot’s Side Page 2--6--77 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 459 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -6- -32 (Sheet 3). Flight Director Vertical Mode Interface - Copilot’s Side Page 2--6--78 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 460 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The description and figures in this section assume the pilot’s flight director is master. The PFD figures reflect the phase III configuration. The phase III configuration shows an RA minimums display instead of a DH decision height display. (2) Pitch Attitude Hold Table 2--6--11 gives the pitch attitude hold operating limits.
Page 461 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (b) Reset Logic Reset means that a condition has occurred that has canceled the mode, but it can be re--engaged. The pitch attitude hold mode is automatically reset if any of the following conditions occur: ...
Page 462 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The reference vertical speed is changed by moving the PITCH wheel on the PC--400 Autopilot Controller, or by pushing and holding the TCS button and manually flying the aircraft to a new vertical speed reference and releasing the TCS button. Input data for the vertical speed control law includes vertical speed target, actual aircraft vertical speed, normal acceleration, and pitch attitude.
Page 463 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (5) Vertical Speed (VS) Hold Mode Engage/Reset/Disengage Logic (a) Engage Logic Required valids:  Flight director  On--side VG--14A  On--side MADC. With the above conditions satisfied, pushing the VS button on the MS--560 Mode Selector engages the VS hold mode.
Page 464 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (6) Speed (SPD) Hold Mode See Figure 2--6--34 and Table 2--6--13. The speed hold mode is used to maintain a pilot-selected speed reference while flying to a new altitude reference. The SPD control law is designed to fly to a selected altitude at a selected speed and to supply limited overspeed protection during climbs and descents.
Page 465 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Input data for the speed control law includes instantaneous vertical velocity, actual aircraft IAS/Mach, normal acceleration, and pitch attitude. AD--50825@ Figure 2- -6- -34. Speed Hold Mode Table 2- -6- -13. Speed (SPD) Hold Mode Operating Limits Mode Parameter Value...
Page 466 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (7) Speed (SPD) Select Mode Engage/Reset/Disengage Logic (a) Engage Logic Required valids are as follows:  Flight director  On--side VG--14A  On--side MADC. With the above conditions satisfied, pushing the SPD button on the MS--560 Mode Selector engages the SPD Hold mode.
Page 467 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (8) Altitude Preselect (ASEL) Mode See Figure 2--6--35 and Table 2--6--14. The ASEL mode is used in conjunction with another vertical mode to climb or descend to a preselected altitude, automatically level off and maintain the barometric altitude reference.
Page 468 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The aircraft remains in the ASEL capture mode until both of the following conditions exist:  ALT error is less than 25 feet  VS is less than 300 FPM. At this time, the ASEL mode is dropped and the altitude hold mode automatically is engaged.
Page 469 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50827@ Figure 2- -6- -36. Prior to Descent - - Altitude Hold Mode Page 2--6--88 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 470 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50828@ Figure 2- -6- -37. During Descent - - ASEL Armed Mode Page 2--6--89 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 471 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50829@ Figure 2- -6- -38. Start of Flare - - ASEL Capture Page 2--6--90 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 472 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50830@ Figure 2- -6- -39. Level at New Altitude - - Altitude Hold Mode The ASEL capture mode is canceled by any of the following:  Moving the ASEL set knob on the MFD bezel controller ...
Page 473 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (9) Altitude Preselect (ASEL) Mode Engage/Reset/Disengage Logic (a) Engage Logic Required valids are as follows:  Flight Director  On--side VG--14A  On--side MADC. With the above conditions satisfied and all of the following conditions met, the ASEL mode automatically arms: ...
Page 474 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) Disengage Logic Disengage means that a condition has occurred that has canceled the mode due to a fault; the mode cannot be re--engaged until the fault is cleared. The ASEL mode automatically disengages if any of the following conditions occur: ...
Page 475 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50831@ Figure 2- -6- -40. Altitude Hold Mode Table 2- -6- -15. Altitude Hold (ALT) Mode Operating Limits Mode Parameter Value ALT Capture Range --900 to 45,000 ft 20 ft ALT Hold Capture Error 12_ Pitch Limit Pitch Rate Limit...
Page 476 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (11) Altitude Hold (ALT) Mode Engage/Reset/Disengage Logic (a) Engage Logic Required valids are as follows:  Flight Director  On--side VG--14A  On--side MADC. With the above conditions met, pushing the ALT button on the MS--560 Mode Selector engages the altitude hold mode.
Page 477 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (12) ILS Approach (GS) Mode See Figure 2--6--41 thru Figure 2--6--46, and Table 2--6--16. The vertical portion of the approach mode is used for the automatic intercept, capture and tracking of the glideslope beam. The beam is used to guide the aircraft down to the runway in a linear descent, as shown in Figure 2--6--41.
Page 478 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50819@ Figure 2- -6- -42. ILS Approach (GS and LOC) Arm With the localizer captured and outside the normal glideslope capture limits, the PFD, as shown in Figure 2--6--43, annunciates the following modes: ...
Page 479 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50820@ Figure 2- -6- -43. ILS Approach Mode-Localizer Capture As the aircraft approaches the glideslope beam, as shown in Figure 2--6--44, the VBS monitors TAS, vertical speed, and glideslope deviation in determining the correct capture point.
Page 480 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TYPICAL CAPTURE POINT IS 1/3 DOT ON GS SCALE RUNWAY AD- -50821@ Figure 2- -6- -44. ILS Approach (GS) Tracking Pictorial AD--50822@ Figure 2- -6- -45. ILS Approach (GS) Tracking Page 2--6--99 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 481 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Gain programming is performed on the glideslope signal to compensate for the aircraft closing on the glideslope antenna, and beam convergence caused by the directional properties of the glideslope antenna, as shown in Figure 2--6--46. Glideslope programming is normally accomplished as a function of the change in radio altitude on the approach.
Page 482 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -6- -16. ILS Approach Mode Operating Limits Mode Parameter Value Glideslope Capture < 150 mV glideslope deviation Capture Point Function of GS deviation, vertical speed, and TAS 10_ Pitch Command Limit Pitch Rate Limit f(TAS) 0.3 g’s max Gain Programming...
Page 483 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) ILS GS Disengage Logic Disengage means a condition has occurred that has canceled the mode due to a fault; the mode cannot be re--engaged until the fault is cleared. The GS arm mode is automatically disengaged if any of the following conditions occur: ...
Page 484 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (g) ILS GS Track Engage Logic Required valids are as follows:  Flight director  On--side VG--14A  On--side NAV source.  Radio altimeter. With the above conditions satisfied, glideslope is captured and localizer is track and radio altitude is less than 1200 ft, the ILS GS mode automatically transitions from capture to track.
Page 485 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Once the VNAV profile has been defined, the pilot pushes the VNAV button on the MS--560 Mode Selector. The VNAV mode immediately goes into capture and the aircraft flies the VANG to the defined waypoint altitude. If the pilot has selected an intercept point ahead of the aircraft by increasing the VANG, the flight director stays in the current vertical mode until the intercept point is reached.
Page 486 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -6- -17. Vertical Navigation (VNAV) Mode Operating Limits Mode Parameter Value VNAV Altitude Range Path 0 to 45,000 feet 6_ in 0.1_ increments Angle Range Elevation Range 0 to 10,000 feet 99.9 NM from VOR Bias Range 12_...
Page 487 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) Disengage Logic The VNAV mode is automatically disengaged if any of the following conditions occur:  Flight director not valid  On--side MADC not valid  On--side VG--14A not valid  NAV source not valid ...
Page 488 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra AD--50837@ Figure 2- -6- -49. Go- -Around Mode Page 2--6--107 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 489 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (17) Go--Around (GA) Mode Engage/Reset/Disengage Logic (a) Engage Logic Required valids are as follows:  Flight director  On--side VG--14A. With the above conditions satisfied, pushing the remote GA button on the pilot’s throttle engages the GA mode.
Page 490 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 4. Fault Monitoring Loss of valid flight director (FD) data from the IC--600 IAC causes the following indications shown in Figure 2--6--50:  An amber FD FAIL warning annunciator is displayed at the top left of the ADI in the FD lateral annunciator location.
Page 491 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--6--110 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 492 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TABLE OF CONTENTS - - SECTION 2.7 Section Page SECTION 2.7 AUTOPILOT/YAW DAMPER SYSTEM ........2- -7- -1 General .
Page 493 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page C. Roll Axis Autopilot Servo Loop ........2--7--23 (1) SM-200 Roll Servo Drive and Bracket .
Page 494 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations Figure Page Figure 2--7--1. IC-600 Integrated Avionics Computer (AP/YD Function) ..2--7--3 Figure 2--7--2. PC--400 Autopilot Controller ........2--7--5 Figure 2--7--3.
Page 495 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page TC2--7--4 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 496 A. Autopilot The PRIMUS 1000 Autopilot (AP) is housed in the pilot’s IC-600 IAC and is of a fail- passive design, featuring digital attitude and servo loops. The autopilot supplies attitude stabilization and tracking of pitch and roll steering commands from the flight director. The AP is not aware of which flight director mode(s), if any, are active.
Page 497 C. AP/YD System The PRIMUS 1000 Autopilot/Yaw Damper (AP/YD) system is made up of the following LRUs:  IC-600 IAC (Pilot’s) ...
Page 498 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 2. Component Descriptions and Locations A. IC-600 Integrated Avionics Computer Two IC-600 Integrated Avionics Computers (IAC) are located in the nose compartment. Figure 2--7--1 shows a graphical view of the IC-600 IAC. Table 2--7--1 gives items and specifications particular to the computer.
Page 499 Mounting ....... . . HPN 7017095--902 The primary component of the PRIMUS 1000 AP/YD system is the pilot’s IC-600 IAC.
Page 500 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. PC- -400 Autopilot Controller The PC--400 Autopilot Controller is located on the pedestal. The PC--400 Autopilot (AP) Controller is used to engage/disengage the AP and Yaw Damper (YD), as well manual control of the AP through PITCH wheel and TURN knob inputs. Figure 2--7--2 shows a graphical view of the PC--400 AP Controller.
Page 501 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (1) Autopilot (AP) Button Pushing the AP button engages the autopilot and yaw damper simultaneously. When engaged, both the AP and YD buttons light. With the autopilot and yaw damper engaged, pushing the AP button again disengages the autopilot only. The yaw damper stays engaged.
Page 502 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. RG- -204 Rate Gyro The RG--204 Rate Gyro, located in the nose compartment, supplies yaw rate data to the pilot’s IC--600 IAC for yaw damping. Yaw rate data is proportional to the rate of angular displacement about an axis perpendicular to the mounting surface.
Page 503 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra D. SM- -200 Servo Drive and SB- -201 Servo Bracket The SB--201 Servo Bracket is firmly bolted to the aircraft airframe and the drum is connected to the aircraft’s primary control rigging through cables. The SM--200 Servo Drive, with a spline output on the clutch, mates with the drum and bracket and can be removed from the drum and bracket without disturbing the aircraft rigging.
Page 504 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 2- -7- -4. Leading Particulars SM- -200 Servo Drive and SB- -201 Servo Bracket Item Specification Dimensions (maximum):  Height ........3.970 in.
Page 505 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra The SM--200 servo drive translates electrical inputs into clutched rotational mechanical outputs. Tachometer rate signals are supplied back to the IC--600 IAC servo amplifier to null the command signal. Table 2- -7- -5. SM- -200 Servo Drive Dash Number Differences Power Gear Synchro Gear...
Page 506 LRUs. For complete wiring interface data, refer to Section 3, System Interconnects, of this manual. A. Modes of Operation The PRIMUS 1000 autopilot has five modes of operation. These modes are as follows:  Heading hold and wings level  Roll hold ...
Page 507 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (3) Pitch Attitude Hold Pitch attitude hold is the basic vertical mode of the autopilot, that annunciates as PIT on the master PFD. It automatically becomes active when the following occurs:  The autopilot is engaged or ...
Page 508 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (6) Pitch Wheel Rotation of the PITCH wheel annunciates PIT on the master PFD and results in a change of pitch attitude proportional to the rotation of the wheel and in the direction of wheel movement.
Page 509 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--7--14 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 510 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -7- -5 (Sheet 1). Autopilot/Yaw Damper Interface Page 2--7--15/(2--7--16 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 511 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -7- -5 (Sheet 2). Autopilot/Yaw Damper Interface Page 2--7--17 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 512 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -7- -5 (Sheet 3). Autopilot/Yaw Damper Interface Page 2--7--18 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 513 Citation Ultra B. Autopilot/Yaw Damper Engage Logic The PRIMUS 1000 Autopilot/Yaw Damper (AP/YD) is a fail--passive system that requires two valid VG--14A vertical gyros and a single valid C--14D Directional Gyro for autopilot and YD engagement (see Figure 2--7--6). The pilot’s VG--14A and C--14D are the primary sources for the autopilot/yaw damper and monitor.
Page 514 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) Autopilot Engagement See Figure 2--7--6. To engage the aileron and elevator servo clutches, AND gate 2 must have a high output. To accomplish this, latch 1 must have its Q output high, TCS must not be active, and AND gate 4 must have a high output.
Page 515 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -7- -6. Autopilot/Yaw Damper Engage Logic Page 2--7--21/(2--7--22 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 516 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. Roll Axis Autopilot Servo Loop The autopilot roll axis servo loop (See Figure 2--7--7 and Table 2--7--6) is the same for all lateral steering modes. Since there is only one autopilot system and one servo in the roll axis, it does not matter if the steering command is heading select or localizer, the path to the servo is the same.
Page 517 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) IC-600 Integrated Avionics Computer (IAC) The IC-600 IAC receives sensor data and command inputs and processes this data in accordance with any lateral steering mode that is active. Since this is a digital computer, this processing is accomplished through software.
Page 518 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (d) Servo Amplifier The servo amplifier acts as a switch that supplies drive current to the aileron servo torque motor. A servo enable discrete is applied as a function of autopilot engagement. The servo requires 1-ampere current drive capability. The servo amplifier supplies a 480 Hz pulse width modulated, 28-volt bipolar output.
Page 519 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 2--7--26 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 520 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -7- -7. Autopilot Roll Axis Servo Loop Page 2--7--27/(2--7--28 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 521 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra D. Pitch Axis Autopilot Servo Loop The pitch autopilot servo loop (see Figure 2--7--8 and Table 2--7--7) is the same for all vertical steering modes. Since there is only one autopilot system and one servo in the pitch axis, it does not matter if the steering command is altitude hold or vertical speed hold, the path to the servo is the same.
Page 522 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) IC--600 Integrated Avionics Computer (IAC) The IC--600 IAC receives sensor data and command inputs and processes this data in accordance with any vertical steering mode that is active. Since this is a digital computer, this processing is accomplished through software.
Page 523 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (d) Servo Amplifier The servo amplifier acts as a switch to supply drive current to the elevator servo torque motor. A servo enable discrete is applied as a function of autopilot engagement. The servo requires 1--ampere current drive capability. The servo amplifier supplies a 480 Hz pulse width modulated, 28 volt bipolar output.
Page 524 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra E. Pitch Axis Autopilot Trim The autopilot processor performs elevator trim control based on elevator servo current demand. Elevator trim engagement is controlled by the autopilot engage logic and the trim clutch is wired to the same clutch output as the aileron and elevator servo clutches. The trim motor is driven in a manner to move the elevator trim tab to reduce the air load on the elevator servo.
Page 525 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -7- -8 (Sheet 1). Autopilot Pitch Axis Servo Loop Page 2--7--33/(2--7--34 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 526 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2-7-8 (Sheet 2). Autopilot Pitch Axis Servo Loop Page 2--7--35 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 527 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Rudder Axis Yaw Damper Servo Loop The yaw damper servo loop (see Figure 2--7--9) is independent from the autopilot in that it can be engaged without the autopilot being engaged. The yaw damper does not receive any commands from the flight director.
Page 528 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (d) Servo Amplifier The servo amplifier acts as a switch to supply drive current to the servo torque motor. Servo enable is applied as a function of yaw damper engagement. The servo requires 1--ampere current drive capability. The servo amplifier supplies a 480 Hz pulse-width-modulated, 28 V bipolar output.
Page 529 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) SM--200 Servo Drive and Bracket The SM--200 translates electrical input signals into a clutched mechanical output. This output is used to drive the rudder in response to yaw axis commands. A description of servo functions follows. (a) Servo Clutch The servo clutch is engaged as a function of autopilot or yaw damper engagement.
Page 530 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Figure 2- -7- -9. Autopilot Yaw damper Servo Loop Page 2--7--39/(2--7--40 blank) 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 531  IAS = 220 kts. B. Hardover/Slowover Malfunction Protection The distributed processor architecture of the PRIMUS 1000 system is designed to prevent hazards, such as autopilot hardovers. This protection ensures that failures in either processor are defeated or minimized by the monitors and/or limiters in the other processor.
Page 532 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. System Response to Failures In the event of an autopilot processor fault, the monitor disconnects the autopilot prior to any significant aircraft response. Upon monitor disconnect, a red AP OFF is displayed on the master PFD.
Page 533 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (6) Primary Roll Attitude Comparison Monitor The primary roll attitude comparison monitor compares the on-side primary roll attitude used in the primary processor with the roll attitude used in the secondary processor. This monitor validates the hardware path between processors and ensures the roll attitude computations of both processors agree.
Page 534 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (11) Auto Trim Inoperative Monitor The trim inoperative monitor supplies a warn annunciator in view of the pilot (CAS message) indicating that the elevator is not properly trimmed. This monitor does not disconnect the autopilot. (12) Autopilot/Yaw Damper Disconnect Monitor The autopilot and yaw damper disconnect monitor detect a failure of the system to disengage the autopilot and yaw damper in response to the autopilot disconnect...
Page 535 SECTION 3 SYSTEM INTERCONNECTS This section provides interconnect information as an aide in troubleshooting the PRIMUS 1000 Integrated Avionics System. The interconnect information is based on Honeywell Engineering Bulletin EB7020278, Revision E. For specific avionics wiring information, refer to the wiring diagrams in the Citation Ultra Aircraft Maintenance Manual (AMM).
Page 536 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 3--2 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 537 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 3- -1. Interconnect Information Table of Contents Para Page (Deleted) ..............3--6 (Deleted) .
Page 538 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 3- -1. Interconnect Information (cont) List of Figures Figure 4--1. Aircraft Grounding Block Diagram ........3--9 Figure 4--1A.
Page 539 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 3- -1. Interconnect Information (cont) List of Figures (cont) Figure 4--12. Weight On Wheels Switch ......... 3--183 Figure 4--13.
Page 540 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Table 3- -1. Interconnect Information (cont) 1. DELETED 2. DELETED 3. DELETED Page 3--6 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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Page 758 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 3--224 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 759 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra TABLE OF CONTENTS - - SECTION 4 Section Page SECTION 4 MAINTENANCE PRACTICES ..........4- -1 General .
Page 760 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page Procedure for the CD--850 Clearance Delivery Control Head (CDH) ... . . 4--16 A. Removal and Reinstallation Procedures ........4--16 B.
Page 761 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Section Page 17. Procedure for MS--560 Mode Selector ........4--31 A.
Page 762 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 25. Procedure for the SM--200 Servo Drive and SB--201 Drum and Bracket Assembly ............4--44 A.
Page 763 1. General This section provides instructions for removing, reinstalling, and adjusting each Line Replaceable Unit (LRU) of the PRIMUS 1000 Integrated Avionics System that has been previously installed by the aircraft manufacturer or completion center. Where applicable, instructions for replacing lamps, knobs and set screws are included. Adjustment information is called out as required.
Page 764 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. Antenna Hardware (1) Clean the airframe at the antenna mounting area to remove any foreign material. (2) Because of the insulation qualities of gaskets and leveling compounds, the mounting screws are required to supply the electrical bonding between the antennas and the aircraft (typically 15 milliohms or less is required).
Page 765 NOTES: Equivalent alternatives are permitted for materials in this list. The HMN codes in the list of materials identify the Honeywell Material Number (HMN) given to each material. Refer to the applicable leading particulars table in SECTION 2 of this manual for replacement gaskets, lamps, knobs and set screw part numbers.
Page 766 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 3. Procedure for the AG- -222 Accelerometer A. Removal and Installation Procedure Before removing the accelerometer, note the direction of the arrow on the NOTE: accelerometer to ensure proper reinstallation of the accelerometer. (1) Remove the AG-222 Accelerometer.
Page 767 (b) Unseal and remove the antenna. (c) Disconnect the cable connectors. (2) Reinstall the AT-860 ADF Antenna. (a) Place the new gasket, Honeywell Part No. 7020801--947, on the antenna. (b) Connect the cable connectors. (c) Mount the antenna and apply the appropriate sealant.
Page 768 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 5. Procedure for the AV- -850A Audio Panel A. Removal and Reinstallation Procedures (1) Remove the AV--850A Audio Panel. (a) Disengage the Dzus fasteners on the unit. (b) Slide the unit out of the aircraft mounting location and disconnect the cable connectors.
Page 769 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Warning 4 Level Adjust Apply an input signal to the WARNING 4 AUDIO input. While listening to the cockpit speaker or phones, adjust the WARNING 4 LEVEL ADJUST potentiometer (A1R43) for the desired output level. Warning 5 Level Adjust Apply an input signal to the WARNING 5 AUDIO input.
Page 770 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (c) Passenger Address (PA) System Adjustments The PA output is factory adjusted to generate 10 mW into 600 ohms. Should adjustment become necessary, proceed as follows:  Push the PA microphone select button ...
Page 771 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Mkr Mute Level The marker beacon mute Level is factory adjusted to work properly with the RNZ--850 NAV Unit and normally does not need to be adjusted. The marker beacon mute algorithm in the audio panel relies on both timing and marker beacon audio level to determine when to un--mute the marker beacon audio.
Page 772 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Voice Recorder Output Level The voice recorder output potentiometer (A3R35) is factory adjusted for 10 mW into 600 ohms. Interfacing the output to a voice recorder with input levels other than this does require adjustment of the audio panel. Refer to applicable voice recorder instructions on how to set input level.
Page 773 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. Repair Procedures Replacement of the control knobs. (1) Only the large SPEAKER and HEADPHONE knobs are field replaceable. The small knobs require removal of the front panel, and should only be serviced in an approved shop.
Page 774 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra WRNG 3 (A1R42) WRNG 4 (A1R43) WRNG 2 (A1R41) WRNG 5 (A1R44) WRNG 1 (A1R40) MIC LVL (A1R17) MKR MUTE (A1R53) SQUELCH (A1R68) MIN GAIN (A1R54) FRONT MNT PH (A3R19) A3TP1/MNT 2 MIC (A3R60) MNT 1 MIC (A3R11) LEFT SIDE ST (A2R38)* PA LVL (A2R40)
Page 775 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 6. Procedure for the AZ- -850 Micro Air Data Computer (MADC) A. Removal and Reinstallation Procedures (1) Remove the MADC. (a) Disconnect the pitot and static lines. Cap or cover the hose end connectors to keep debris out of the system.
Page 776 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 7. Procedure for the BL- -870/871 Bezel Assembly A. Removal and Reinstallation Procedures (1) Remove the BL-870/871 Bezel Assembly. (a) Loosen the two captive holding screws at the ends of the bezel assembly. (b) Gently pull the bezel assembly straight away from the display unit separating the bezel and the display unit connectors.
Page 777 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 8. Procedure for C-14D Directional Gyro A. Removal and Installation Procedure CAUTION: A GYRO CAN BE DAMAGED BY MOVING IT AFTER ELECTRICAL POWER IS REMOVED BUT BEFORE THE GYRO ROTOR STOPS. THE GYRO ROTOR WON’T COME TO A STOP FOR APPROXIMATELY 15 MINUTES AFTER ELECTRICAL POWER IS REMOVED.
Page 778 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 9. Procedure for the CD- -850 Clearance Delivery Control Head (CDH) A. Removal and Reinstallation Procedures (1) Remove the CD--850 CDH. (a) Using an 3/32--inch Allen wrench, loosen the unit mounting clamp screws accessible through holes at the sides of the front panel.
Page 779 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (6) Make sure the space between the knob and the bezel is approximately 0.030 inch (0.8 mm). (7) Tighten both setscrews with the Allen wrench. (8) Recheck spacing between the knob and the bezel to make sure that knob has not slipped during installation.
Page 780 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 10. Procedure for CS- -412 Dual Remote Compensator A. Removal and Reinstallation Procedures (1) Remove CS--412 Dual Remote Compensator. (a) Disconnect the aircraft cable connectors from the unit connectors. (b) Remove and save the hardware securing the compensator to the airframe. (2) Reinstall CS--412 Dual Remote Compensator.
Page 781 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (6) Place the aircraft on a South heading and allow the compass dial to settle. (7) Compensate for half of any difference between actual heading and compass dial indication by loosening the locking nut and adjusting N--S potentiometer on the compensator.
Page 782 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 11. Procedure for the DC- -550 Display Controller A. Removal and Reinstallation Procedures (1) Remove the DC--550 Display Controller. (a) Disengage the Dzus fasteners on the unit. (b) Slide the unit out of the aircraft mounting location and disconnect the cable connector.
Page 783 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) Replace DH/TEST and PFD DIM knobs. (a) Use a 1/32--inch Allen wrench to loosen both setscrews in the DH/TEST knob. (b) Slide the knob off the shaft. (c) Use a .048--inch Bristol wrench to loosen both setscrews in the test switch hub. (d) Slide the test switch hub off the shaft.
Page 784 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 12. Procedure for DI-851 DME Indicator A. Removal and Installation Procedure (1) Remove DI-851 DME Indicator. (a) Loosen the two larger screws on instrument panel located at upper-right and lower-left corners of indicator. (b) Slide indicator out of panel and disconnect aircraft cable connector.
Page 785 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 13. Procedure for the DU- -870 Display Units A. Removal and Reinstallation Procedures (1) Remove the DU--870 Display Unit. (a) Loosen the two captive holding screws at the ends of the bezel assembly. (b) Gently pull the bezel assembly straight away from the display unit separating the bezel and the display unit connector.
Page 786 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. Repair Procedures Cleaning of the display unit faceplate filter. The display unit faceplate is protected by a filter that reduces reflections. It is NOTE: sturdy, but it is not indestructible. (1) Inspect the outside surface for foreign material and variations in optical quality. (2) Particles of grit, dirt, or sand are to be removed with pressurized dry air or a soft camel--hair brush.
Page 787 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 14. Procedure for FX- -220 Flux Valve : Whenever a flux valve is removed and replaced, a compass swing must be NOTE performed to attain the desired long--term heading accuracy. The compass swing includes an index error adjustment of the flux valve, and compensator adjustment of the remote compensator.
Page 788 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra B. Adjustment Procedures (Index Error) (1) Apply aircraft electrical power to the attitude and heading reference system and allow several minutes for the gyros to reach operating speed and for the system to slave to the current magnetic heading.
Page 789 NOTES: The PC must have the ECP-800 Programmable Checklist Software, Honeywell Part No. 7021060-901, and the desired checklist available for use. Refer to the ECP--800 Programmable Checklist Manual for details. If the PC has Windows 3.1 or 95, do not access the ECP--800 software from the Windows prompt.
Page 790 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (3) Apply power to the avionics. Observe the RA SET area on the PFD is valid. (4) Using the on--side DC--550 Display Controller, use the RA knob to set 890 RA on the PFD.
Page 791 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (8) When the upload is complete, follow the instructions on the PC to finish. (9) Pull the appropriate IAC circuit breaker to power down the IAC. (10) Remove the RS--232 cable from the aircraft connector. (11) Push in the appropriate IAC circuit breaker to power up the IAC.
Page 792 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 16. Procedure for MC- -800 MFD Controller A. Removal and Installation Procedure (1) Remove MC--800 MFD Controller. (a) Disengage the Dzus fasteners on the unit. (b) Slide the unit out of the aircraft mounting location and disconnect the cable connector.
Page 793 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 17. Procedure for MS- -560 Mode Selector A. Removal and Installation Procedure (1) Remove MS-560 Mode Selector. (a) Remove and save the four machine screws securing the MS--560 to the instrument panel. (b) Slide the unit out of the aircraft mounting location and disconnect the cable connector.
Page 794 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 18. Procedure for the PC- -400 Autopilot Controller A. Removal and Reinstallation Procedures (1) Remove the PC--400 Autopilot Controller. (a) Disengage the Dzus fasteners on the unit. (b) Slide the unit out of the aircraft mounting location and disconnect the cable connector.
Page 795 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (2) Replace Button Lamps. CAUTION: THE BUTTON COVERS ARE HELD CAPTIVE TO THE SWITCHES WITH SPRING WIRE. BE CAREFUL NOT TO PULL THE COVER OUT TOO FAR, AS DAMAGE TO THE SWITCH CAN RESULT. Access to these lamps does not require removal of knobs or bezel.
Page 796 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 19. Procedure for the RCZ- -851(X) Integrated Communications Unit A. Removal and Reinstallation Procedures (1) Remove the RCZ--851(X) Integrated Communications Unit. (a) Cut the safety wire and loosen the thumbnuts. (b) Slowly pull forward on the unit handle to separate the unit and tray connectors and slide the unit out of the tray.
Page 797 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra C. Repair Procedures Not applicable. MIC LEVEL MASTER SIDETONE LEVEL ADJUST AUDIO ADJUST ADJUST AD- -17752@ Figure 4- -3. COM Unit Adjustment Locations Page 4--35 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 798 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 20. Procedure for RG-204 Rate Gyro A. Removal and Installation Procedure (1) Remove RG-204 Rate Gyro. (a) Disconnect the cable connector. (b) Remove and save the hardware securing the gyro to the airframe. (2) Reinstall RG-204 Rate Gyro.
Page 799 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 21. Procedure for RI- -553 Remote Instrument Controller A. Removal and Installation Procedure (1) Remove RI-553 Remote Instrument Controller. (a) Disengage the Dzus fasteners on the unit. (b) Slide the unit out of the aircraft mounting location and disconnect the cable connector.
Page 800 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 22. Procedure for the RM- -850 Radio Management Unit (RMU) A. Removal and Reinstallation Procedures (1) Remove the RM--850 RMU. (a) Loosen the clamp screws on the panel at each top corner of the unit. (b) Without turning the screws, push them straight into the panel.
Page 801 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 23. Procedure for the RNZ- -850(X) Integrated Navigation Unit A. Removal and Reinstallation Procedures (1) Remove the RNZ--850(X) Integrated Navigation Unit. (a) Cut the safety wire and loosen the thumbnuts. (b) Slowly pull forward on the unit handle to separate the unit and tray connectors and slide the unit out of the tray.
Page 802 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (1) LOC Audio Level Adjustment The LOC audio adjustment controls the VOR/LOC receiver emergency audio level out of the AV--850A. This adjustment does not affect the digital audio level from the AV--850A. Emergency audio for the VOR/LOC is a backup system for the digital audio and is connected on the side of the aircraft that has the CD--850 Clearance Delivery Control Head (CDH) installed.
Page 803 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (e) Adjust the audio level as follows:  Find the LOC AUDIO adjustment on top of the NAV unit and increase or decrease audio level as desired  For an increase of audio level, turn the adjustment clockwise ...
Page 804 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra As an alternate procedure, cross the outer marker at normal ILS approach altitudes and determine adequate marker aural and visual indication. When adjusting marker high and low sensitivity thresholds, the high NOTE: sensitivity adjustment must always be set to the desired threshold before low sensitivity adjustment is performed.
Page 805 NOTE: an assembly from customer--owned shelf stock or was obtained from Honeywell, the configuration straps have to be cut in accordance with the list in Section 3 of this manual. (a) Handle the strap board assembly by its edges and attach the flat connector to the assembly.
Page 806 (c) Cut the safety wire on the four screws securing the retaining plate. Remove and set aside the screws and the retaining plate. (d) Remove and set aside the four cable keepers, Honeywell Part No. 2518330. (e) Cut the safety wire. Remove and set aside two screws securing the swagged cable terminals to the drum.
Page 807 The other two keepers must be located at 90 degrees from the first two. (e) Install the retaining plate, Honeywell Part No. 2518332, on the slotted end of the cable keepers using the four 5/16--inch long, No. 8--32, drilled fillister--head screws removed in paragraph 25.A.(3)(c).
Page 808 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 26. Procedure for VG- -14A Vertical Gyro A. Removal and Installation Procedure (1) Remove VG-14A Vertical Gyro. (a) Disconnect the cable connector. (b) Remove and save the hardware securing the gyro to the airframe. (2) Reinstall VG-14A Vertical Gyro.
Page 809 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 27. Procedure for the WC- -6X0/8X0 Weather Radar Controller A. Removal and Reinstallation Procedures (1) Remove the WC--6X0/8X0 Weather Radar Controller. (a) Disengage the Dzus fasteners on the unit. (b) Slide the unit out of the aircraft mounting location and disconnect the cable connector.
Page 810 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra 28. Procedure for the WU- -6X0/8X0 Antenna and Receiver Transmitter Unit A. Removal and Reinstallation Procedures (1) Remove the WU-6X0/8X0 Antenna and Receiver Transmitter Unit. (a) Disconnect the cable connector from the unit. (b) Remove and set aside the hardware used to attach the unit to the airframe.
Page 811 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (d) Apply aircraft power as necessary. (e) On the WC--XXX Radar Controller, make the following selections:  RADAR = SBY  TILT = 0 degrees  GAIN = Push knob in for preset gain. (f) During the 45 second wait period, the unit sets the azimuth and elevation to 0.0 degrees independent of any external inputs.
Page 812 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (3) Roll Gain Adjustment (a) On controller select variable GAIN. (b) Adjust the vertical reference for 0 degree of pitch and 25 degrees right wing down. (c) Adjust the bottom potentiometer (ROLL) A4A1R3, if necessary, so the antenna tilts up 25 degrees in elevation or the amount of right roll injected.
Page 813 C. WU-660 Adjustment Procedures (1) Stabilization Trim Adjustments The PRIMUS 660 Digital Weather Radar System is delivered from the Honeywell factory or repair facility adjusted for correct pitch and roll stabilization and should be ready for use. However, due to the tolerances of some vertical reference sources, the user can elect to make a final adjustment whenever the radar or vertical reference is replaced on the aircraft, or if stabilization problems are observed in flight.
Page 814 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra There are two stabilization trim modes available on the display. If the STAB TRIM ENABLE strap (59J1-61) is open, only adjustment of the roll offset is available. If the STAB TRIM ENABLE strap is grounded, roll offset, pitch offset, roll gain and pitch gain are available for adjustment.
Page 815 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra (3) Pitch Offset Adjustment (a) From the Roll Offset entry menu, push the STAB key once to bring up the Pitch Offset entry menu on the display. (b) To change the pitch offset value shown on the display, pull out the GAIN knob and rotate it.
Page 816 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 4--54 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 817 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra SECTION 5 SHIPPING/HANDLING AND STORAGE Refer to manual, Pub. No. 09--1100--01, for detailed procedures for preparing all System components for storage or shipment. Page 5--1 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 818 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 5--2 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 819 6--6 Honeywell Support Centers ..........
Page 820 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra List of Illustrations Figure Page Not applicable List of Tables Table Page Not applicable Page TC6--2 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 821 Upon receipt of a rental request, Honeywell ships a fully--certified unit. The customer then ships the faulty unit to an authorized support center for service. When the faulty unit has been serviced and installed, the rental unit is returned to the designated Honeywell Support Center.
Page 822 Honeywell’s obligation under this warranty, however, shall be limited to repair of, or at Honeywell’s option, replacement of any article which is returned to Honeywell within the stipulated twelve--month warranty period.
Page 823 AND OPERATION MANUAL Citation Ultra (2) Ordering Information When placing an order, Honeywell needs the following information:  Part number with dash number of faulty unit  Serial number of faulty unit  Aircraft type, serial number, and registration number ...
Page 824 (3) Return Shipping Procedures (a) Shipping Container All components returned to Honeywell must be packed in the same (or Honeywell approved equivalent) container in which the component was received. Components which are received in IMPROPER containers may be subject to DAMAGE charges.
Page 825 Continuing assistance is provided through telephone consultation, or at your facility, as requirements dictate. For the name, address, and telephone number of the Honeywell customer engineer nearest to your facility, please call (602) 436--8981 or your nearest Honeywell support center.
Page 826  Flight Crew Familiarization  Line Maintenance Familiarization  Component Level Repair. For full details and information on Honeywell training courses or a copy of the Honeywell Customer Training Schedule, contact the Customer Training Department in Phoenix, Arizona  Tel: (602) 436--8972 ...
Page 827 MANUAL Citation Ultra SECTION 7 SYSTEM TEST AND FAULT ISOLATION Refer to manual, Pub. No. A15--1146--075, for PRIMUS 1000 Integrated Avionics System test and fault isolation procedures. Page 7--1 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 828 SYSTEM DESCRIPTION AND OPERATION MANUAL Citation Ultra Blank Page Page 7--2 1 Dec 1999 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.

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